BACHELOR’S THESIS

2006:18 HIP

JOHAN WIKSTÉNMARCUS JOHANSSON

B. Sc. PROGRAMMEAeronautical Engineering

Luleå University of TechnologyDepartment of Civil and EnvironmentalDivision of Operation and Maintenance

2006:18 HIP • ISSN: 1404 - 5494 • ISRN: LTU - HIP - EX - - 06/18 - - SE

Maintenance and ReliabilityWith Focus on Aircraft Maintenance

and Spares Provisioning

SAMMANFATTNING Den här rapporten är ett resultat av det examensarbete som utförts i ämnet underhållssäkerhet, med sina relaterade områden. En ingående studie i logistisk support företogs också, för att fördjupa förståendet av dess roll i, och hur detta påverkar, underhålls procedurerna. Då ämnet underhåll är stort, har fokus lagts på att undersöka möjligheten att med hjälp av befintliga arkiv, förbättra underhålls procedurerna och i viss mån även reservdelsförsörjningen. Arbetet gäller underhålls procedurer inom flygindustrin och har utförts i enlighet med gällande regler och föreskrifter från luftfartsmyndigheten. Arbetet har utförts på Avdelningen för Operation and Maintenance Enginering vid LTU, under en tio veckors period vårterminen 2006. Uppdragsgivare var Luleå Flygteknik, som tillhandahöll material och expertis inom flygunderhåll och dess procedurer. Författarna vill här ta tillfället i akt att tacka alla som på ett eller annat sätt bidragit till, eller medverkat, i arbetet. Ett speciellt tack tillskrivs följande personer för deras medverkan och för delgivandet av expertis och kunskaper under arbetets gång, dessa personer är: Prof. Uday Kumar (examinator LTU), Aditya Parida (handledare LTU), Arne Nissen (Adjunkt LTU) och Jan Viklund (uppdragsgivare och handledare LFT). Luleå Maj 2006 Johan Wikstén Marcus Johansson

SUMMARY This report is the result of a study performed on maintenance reliability and, its, related issues. Studies of logistic support issues have also been performed to understand its important role in maintenance practice. Due to the extensive topics of maintenance, the focus in this study has been set to the investigation of the possibilities to make use of existing records for improvement in maintenance procedures and in some manner, also spare parts provisioning. The study focuses on the maintenance procedures in the aviation industry and, has been carried out in accordance with aviation regulating authority. The study has been performed at the Division of Operation and Maintenance Engineering at Luleå University of Technology (LTU) during ten weeks in the spring semester of 2006. Sponsor for the study was Luleå FlygTeknik (LFT) which provided material and expertise in aviation maintenance and its procedures. The authors wish to thank every person who has, in one way or another, been contributing or involved in this study. A especially thank you, are directed to the following persons for their participation and for sharing their expertise during the study, they are: Prof. Uday Kumar (examiner LTU), Aditya Parida (supervisor LTU) and Jan Viklund (sponsor and supervisor LFT). Luleå May 2006 Johan Wikstén Marcus Johansson

ABBREVIATIONS AND EXPLANATIONS AMP Aircraft Maintenance Plan ATA Air Transportation Association of America EASA European Aviation Safety Agency FFOP Failure Free Operating Period FMEA Failure Mode and Effect Analysis LFT Luleå FlygTeknik MDT Mean Down Time MFOP Maintenance Free Operating Period MLDT Mean Logistic Delay Time MMH Maintenance Man Hour MPD Maintenance Plan Document MRB Maintenance Review Board MSG Maintenance Steering Group MTBCF Mean Time Between Critical Failure MTBF Mean Time Between Failure MTBM Mean Time Between Maintenance MTBO Mean Time Between Overhaul MTBUR Mean Time Between Unscheduled Removal MTTF Mean Time To Failure MTTR Mean Time To Repair PART A sub part of EASA regulation document RCM Reliability Centered Maintenance TFh Total Flight hours VAT Value Added Tax

CHAPTER 1 1

INTRODUCTION 1

1.1 BACKGROUND 1 1.2 PROBLEM STATEMENT 2 1.3 PURPOSE 2 1.4 AIM 2 1.6 SCOPE AND LIMITATIONS 2 1.7 METHODOLOGY 2

CHAPTER 2 4

LITERATURE STUDIES AND INTERVIEWS 4

2.1 RELIABILITY 4 2.1.1 PROBABILITY THEORY 4 2.1.2 PROBABILITY/RELIABILITY DISTRIBUTION 5 2.1.3 RELIABILITY MEASUREMENTS 6 2.1.4 FAILURE FUNCTION 6 2.1.5 RELIABILITY FUNCTION 7 2.2 MAINTENANCE 8 2.2.1 MAINTAINABILITY AND ITS CONCEPTS 9 2.2.2 MAINTAINABILITY MEASUREMENTS 9 2.2.3 MAINTENANCE AND ITS CONCEPTS 10 2.2.4 MAINTENANCE COST 12 2.3 OPTIMIZATION OF MAINTENANCE 13 2.3.1 PREVENTIVE MAINTENANCE AND RELIABILITY 13 2.3.2 MSG3, RELIABILITY CENTERED MAINTENANCE 15 2.3.3 RCM PROCESS 16 2.4 LOGISTICS 19 2.4.1 HISTORY 19 2.5 INTEGRATED LOGISTIC SUPPORT 19 2.5.1 MAINTENANCE PLANNING 20 2.5.2 SUPPLY SUPPORT 20 2.5.3 SUPPORT AND TEST EQUIPMENT 21 2.5.4 MANPOWER AND PERSONNEL 21 2.5.5 TRAINING AND TRAINING DEVICES 22 2.5.6 TECHNICAL DATA 22 2.5.7 COMPUTER RESOURCES SUPPORT 23 2.5.8 HANDLING, STORAGE, AND TRANSPORTATION 23 2.5.9 FACILITIES 24 2.5.10 DESIGN INTERFACE 24 2.6 AVIATION LOGISTICS 24 2.7 INTERVIEWS 25

CHAPTER 3 27

AUTHORITY REGULATIONS 27

3.1 CERTIFYING AUTHORITY 27 3.2 MAINTENANCE REVIEW BOARD (MRB) 29 3.3 AIRCRAFT MAINTENANCE PROGRAM (AMP) 30

CHAPTER 4 31

MAINTENANCE TASK COMPILING 31

4.1 MAINTENANCE TASK COMPILING 31 4.2 SAMPLE AIRCRAFT FLEET 32 4.3 DETERMINE THE SCHEDULED MAINTENANCE 32 4.4 DETERMINE THE UNSCHEDULED MAINTENANCE 32 4.5 MAINTENANCE DATA ANALYSIS 34 4.5.1 ANALYSIS OF FAILURE OCCURRENCE 34 4.5.2 ANALYSIS OF PREVENTIVE MAINTENANCE 35

CHAPTER 5 38

DISCUSSION 38

5.1 ANALYSIS REFLECTIONS 38 5.2 LOGISTIC SOFTWARE 40 5.3 SPARES PROVISIONING OPTIMIZATION 40 5.3.1 ANALYSIS OF PREVIOUS EXAMPLES 41

CHAPTER 6 42

RECOMMENDATIONS 42

CHAPTER 7 43

CONCLUSION 43

CHAPTER 8 44

REFERENCES 44

8.1 LITERATURE 44 8.2 WEB 45

APPENDIX 46

Chapter 1

INTRODUCTION 1.1 Background Maintaining a repairable system can be a complex task from economical and reliability point of view. High reliability is most essential which may not be connected with high costs. Due to the multidisciplinary characteristic of maintenance which consists of management planning, equipment, facilities, inventory and human resources, it is hard to overview and manage the maintenance tasks. If a system is not maintained correctly, it will sooner or later cease to perform its required function with loss of safety and availability, besides reliability which will lead to several losses like economical, structural and in the worst case fatal injuries to humans. Within the aviation industry, the operational requirements are high and because of the consequences of failure, the maintenance procedures governed by strict legislation under strict directive from regulating authority. These directives are developed in a structured way of national requirements like international safety standards. The scheduled maintenance of an aircraft contains hundreds of timely/cyclic based inspections and replacements of parts. These can be divided into about 40, or more, groups with different periodic intervals, which are developed from maintenance strategy like MSG3. Even if a system is maintained, deviations will occur, these deviations must be considered separately since they have a tendency to occur randomly at times and these are the unscheduled maintenance tasks. All implemented maintenance tasks, scheduled as well as unscheduled, must be recorded and archived. For small and medium companies, it seems like this information is rarely used to improve the organization. Even if there are already developed software’s available on the market, which takes care of probability calculations of failures and spare part optimization, the burden of license fees is too high for the small and medium maintenance organizations to justify the use of these. Savings can be made by using the knowledge of previous maintenance data, although the use of an adopted software would be more effective, a simpler and cheaper analytic method can improve the logistic tasks like maintenance planning, spares, etc, and will also affect positively on aircraft availability and unpredicted expenses.

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1.2 Problem statement The cost of maintenance in the aviation industry is high and there is always a continuous process of cutting costs, which has to be done without interfering with safety and airworthiness. Due to the demands from the authorities, there is a source of information in the maintenance records. Our task is to compile these information’s and investigate for analyzing it and further, to give suggestions of how to implement these statistical results in the maintenance and logistic planning.

1.3 Purpose The main purpose of this work is to develop a methodology that will, facilitate improvement of the logistic function of spare part handling, analyze the existing source of information that has been collected in compliance with regulating authorities. Additionally, this study may affect areas such as aircraft maintenance planning, availability and reliability. Altogether, they will have a long term effect on the safety and economy, we will also enhance our knowledge in the topic of maintenance reliability.

1.4 Aim The aim of this study is to improve maintenance decision making, using the existing maintenance data.

1.6 Scope and limitations This study is limited to small and medium maintenance organizations in the aviation industry. To keep this study within reasonable limits, we will only focus on the stock holding of spare parts and study planned and unplanned maintenance tasks of three sample aircrafts, where the unplanned maintenance is restricted to the following ATA-groups (Air Transport Association): ATA25, 32, 72, 76 and 79, and no notice is taken of the delegation within the subgroups of these.

1.7 Methodology To reach the aim previously stated, we will do the literature study on maintenance reliability and logistic support theory, besides, analyze the authority regulation by studying PART-M, PART-145 and a MRB/MPD-AMP system from the aviation industry including the ATA-100 system. We will also make interviews with, for this topic, relevant people. We will identify the demanded maintenance tasks performed during one year, divided into four quarters, for three sample aircrafts which are recognized in different lifetime periods with few, mid and many running hours to give some idea of the different characteristics of failure due to age. The process of this study is illustrated in Figure 1.1.

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Identification of problem and

purpose

Literature studies

MRB/MPD AMP-system

studies

Recommendation

Conclusion

Report writing

Analyze the data and tasks

Discussion

Identifying maintenance

tasks and data

Compiling maintenance

tasks

Figure 1.1 The process of the study The maintenance data will be collected, classified and analyzed to give an overview of the study. Out of this, we hope to develop a theoretical method to achieve the above stated aim and be able to give recommendations that will affect on the reliability, safety and economy for the small or medium sized maintenance organization. Further, we will give suggestions regarding further investigations of the subject.

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Chapter 2

LITERATURE STUDIES AND INTERVIEWS 2.1 Reliability Ever since the very beginning of the industrial era, customers have demanded more, better and faster deliveries of products and services, all these at lower costs. In other words, they want to get value for their money spent. This problem is due to the fact that one produces, what someone else consumes, the consumer has to rely on the producer, that the product will deliver value as expected and the producer must as far as possible try to fulfill the consumers needs and demands, this is important due to the competitive market. “Operators want infinite performance, at zero life-cycle costs, with 100% availability from the day they take delivery to the day they dispose it.” (Kumar et al., 2000) This is of course the ideal request, but of course impossible to achieve. The operators demand is to get as close as possible to this extreme, or at least closer than their competitors. One step to reach a high level of availability is to increase the reliability of the products, although this on its own, one can’t fulfill all those demands, but it is a link in the chain consisting of reliability, maintenance and logistic support, where maintenance comes as a natural part of reliability.

2.1.1 Probability theory Probability theory is applicable in various situations where the outcome is uncertain, such as in experiments, trials and repeated processes etc. where predictions have to be made. This is a topic that plays a leading role in modern science. In fact it was previously developed as a tool to guess the outcome of some games of chance, however, subchapter 2.1 is not intended to describe this topic in detail with theorems and proofs, but just give some brief overview of concepts in probability that may be applied to problems during this study considering reliability, maintenance and logistic support.

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2.1.2 Probability/Reliability distribution There are some theoretical probability distributions that imply to reliability study and analysis. However, we will only explain functions which are applicable for the continuous time variable. Exponential distribution is well defined by a single parameter that controls the scale of the distribution. The exponential distribution is positively skewed, with the smallest possible value, zero. A unique property of the exponential distribution is that it is the only continuous distribution that has memory less property, that mean the conditional probability depends only on remaining duration and is independent of the current age of the item. This property is exploited to a great extend in reliability theory. The general formula for the probability density function of the exponential distribution is

( ) tetf λλ −= 0 < t < ∞

The general formula for the reliability function of the exponential distribution is

( ) tetR λ−= where MTBF

1=λ

(Leitch, 1995)

Poisson discrete distribution is a theoretical distribution where the number of occurrences is paired with an event of a given period of time and its probability. This is useful when it’s not possible to observe a finite sequence of trials. The observations take place over a continuum, such as time. The Poisson distribution is used to model the number of events occurring within a given time interval.

The formula for the Poisson probability distribution function is

!)(

xetP

x

x

μμ −⋅= μ is defined as the expected value λt

(Billinton et al., 1983) The formula for the Poisson cumulative distribution function is:

∑=

− ⋅=

t

i

i

ietF

0 !)( μμ

(NIST/SEMATECH, web)

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2.1.3 Reliability measurements Broadly the reliability metrics are classified as: 1. Basic Reliability Measures, 2. Mission Reliability Measures, 3. Operational Reliability Measures and 4. Contractual Reliability Measures. Basic Reliability Measures are used to predict system’s ability to operate without maintenance and logistic support. Reliability measures like reliability function and failure function fall under this category. Mission Reliability Measures are used to predict systems ability to complete mission. Reliability measures such as mission reliability, Maintenance Free Operating Period (MFOP), Failure Free Operating Period (FFOP), and hazard function fall under this category. Operational Reliability Measures are used to predict the performance of the system when operated in a planned environment including the combined effect of design, quality, environment, maintenance, support policy, etc. Measures such as Mean Time Between Maintenance (MTBM), Mean Time Between Overhaul (MTBO), Maintenance Free Operating Period (MFOP), Mean Time Between Critical Failure (MTBCF) and Mean Time Between Unscheduled Removal (MTBUR) fall under this category. Contractual Reliability Measure is used to define measure and evaluate the manufacturers program. Contractual reliability is calculated by considering design and manufacturing characteristics. Basically it is the inherent reliability characteristic. Measures such as Mean Time To Failure (MTTF), Mean Time Between Failure (MTBF) and Failure rate fall under this category. (Kumar et al., 2000)

2.1.4 Failure function Failure function is a basic reliability measure and is defined as the probability that an item will fail before or at the moment of operating time t. Here time t is used in a generic sense and it can have units such as number of landings, flying hours, number of cycles, etc., depending on the operational profile and the utilization of the system. Failure function is equal to the probability that the time-to-fail random variable will be less than or equal a particular value t. The failure function is usually represented as F(t). (Kumar et al., 2000) Failure function is an increasing function where F(0) = 0 and F(∞) = 1.

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Applications of the failure function: F(t) is the probability that an item will fail by time t, F(t) is the fraction of items that will fail by time t and 1-F(t) is the probability that an item will survive up to time t.

Failure Function

Increasing function Probability of failure by given age

Fraction of items that fail by given

age

Figure 2.2 Properties of failure function

2.1.5 Reliability function Reliability is the ability of the item to maintain the required function for a specified period of time under given operating conditions. Reliability function R(t) is defined as the probability that the system will not fail during the stated period of time t, under stated operating conditions. Applications of the reliability function: R(t) is the probability that an individual item survives up to time t, R(t) is the fraction of items in a population that survives up to time t and R(t) is the basic function used for many reliability measures and system reliability prediction.

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2.2 Maintenance Maintenance and maintainability has always been important to the industry as it affects the performance as well as the finance. For commercial airlines, maintenance costs are approximately 10% of the airlines total costs. Operators would like their systems to be functional and available for safe operation when ever required. To achieve this there are in fact several ways to go, one of them is to construct systems that are extremely reliable which consequently will result in higher acquisition cost, another way is to design systems that are easy and quick to repair when they fail, or some combination of these two described methods would do. Maintenance is a necessary action to sustain and restore the performance, reliability and safety of the item. The definition of maintenance can be described as: “The combination of all technical and administrative actions, including supervision actions, intended to remain an item in, or restore it to, a state in which it can perform a required function”. (BS 4778, 1991) The main objective of maintenance is to ensure the availability of the system. For aircraft, maintenance is an essential part of airworthiness. Further more, critical failures are under no circumstances allowed to occur during flight. Terminologically, maintenance is divided in corrective and predictive maintenance in accordance to ISO/SS 13306 standard, predictive maintenance is further divided into preventive maintenance (time-based) and conditional maintenance (condition-based). SeeFigure 2.3

Maintenance

Corrective Maintenance

Predictive Maintenance

Condition Based

Predetermined (Time based)

Scheduled Scheduled, continuous

or on request

Immediate Deferred

After a detected fault Before a detected fault

Figure 2.3 ISO/SS 13306 standardization of maintenance terminology

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2.2.1 Maintainability and its concepts Even if the ideal situation would be that an item could maintain its performance and/or function for ever, this can in reality never be achieved. Therefore, it must be maintained, thus for the user it is important to know; when and how often maintenance tasks should be performed, how they should be performed, how many people will be needed and what skills and how much training they will need, how much restoration will cost, how long the system will be down, and what facilities and equipment will be required. In the aviation industry, several of these questions are strictly regulated by the authorities. It is a common misperception that maintainability is simply the ability to reach a component for required maintenance tasks, which is called accessibility. There are other factors like, visibility, testability, simplicity and interchangeability which must be considered. Additionally, one must consider the environment in which it operates.

2.2.2 Maintainability measurements The maintainability measure can be represented using the probability that the maintenance task will be completed by a stated time. Since the time used for maintenance is a random variable one can use the cumulative distribution function of the elapsed time to find the percentage of maintenance task that will be completed within a specific time. Mean Time to Repair (MTTR) is a method to measure maintainability. MTTR is the expected value of items repair time. Maintenance Man Hour (MMH) is also known as maintenance labour hours and is an estimate of the expected total man hour needed to accomplish the maintenance, the MMH value can be larger than MTTR due to the fact that it is often possible and sometimes even necessary to employ more than one person on a given activity or task. Another characteristic of system design pertaining to maintainability is in optimizing the mix between preventive and corrective maintenance. In the aviation industry it is a common way to reach this mix by built in redundancy, both doubled and tripled, which allows certain components to fail during flight, this is mostly used where the items have an unpredictable life time or constant hazardous rate, like electronic components, but also some components pertaining high level of risk when failing. However redundant components will add to the cost of the system and often reduces its load carrying capacity. Corrective maintenance can be expensive if the failure causes damage to other components. Additionally it also causes loss in availability, so the main objective for the maintainability engineer is to strike the balance between these maintenance issues. Prognostics can help but these too have their own problems of reliability.

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2.2.3 Maintenance and its concepts Maintenance can be explained as all actions taken to keep a system running and to ensure that it is keeping an acceptable standard in which it is able to operate at the required levels of efficiency and effectiveness. The objectives of maintenance are to:

1. Reduce consequences of failure. 2. Extend the life of the system, by keeping the system in a proper condition for a

longer time. In other words, to increase the “up” time of the system. 3. Ensure that the system is fit and safe to use. 4. Ensure that the condition of the system meets all regulatory requirements. 5. Maintain the value of the system. 6. Maintain reliability and achieve a high level of safety. 7. Maintain the systems availability and therefore minimize the life cycle cost.

The purpose of maintenance is to keep systems in a state of functioning in accordance with their design and to restore them to a similar state as and then required. (Kumar et al., 2000) As said before, the maintenance tasks can be classified into three categories namely corrective, preventive and conditional maintenance task. Corrective is performed after a failure has occurred, while preventive and conditional maintenance is performed by schedule. The difference between these last two classes may some times be difficult to see, since both of them mostly are scheduled. The main difference is that in preventive maintenance, the item is either replaced or repaired in accordance to a predetermined maintenance plan, while conditional maintenance represents scheduled inspections where, as an outcome, replacement or repair may be required.

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Corrective maintenance task is a set of activities which is performed with the intension of restoring the functionality or performance i.e. after failure. The duration of corrective maintenance task, DMTc, represents the elapsed time needed for successful completion of the task. See Figure 2.4. Corrective maintenance task is also referred to as an unscheduled or unplanned maintenance task.

Figure 2.4 Corrective maintenance task activities (adapted, source, Kumar et al., 2000)

Item failed Fault location Disassembly

Repair or

Replacement

Assembly Test and Check Disassembly

Verification MTBF

DMTc?

Corrective maintenance task activities

CMT start

CMT complet

Preventive maintenance task is a maintenance activity that is performed in order to reduce the probability of failure of an item/system or to maximize the operational benefit. The duration of the preventive maintenance task, DMTp, represents the elapsed time needed for the successful completion of the task. See Figure 2.5

Figure 2.5 Preventive maintenance task activities (adapted, source, Kumar et al., 2000)

Disassembly

Replacement

Assembly Test and Check

Verification MTBF

DMTp

Preventive maintenance task activities

PMT start

PMT complete

Tp

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Conditional maintenance task recognizes that a change in condition and/or performance is likely to precede a failure so the maintenance task should be based on the actual condition of the item. Preventive action is taken when it is believed that an incipient failure has been detected. Thus through monitoring of some condition parameters it would be possible to identify the most suitable instant of time at which preventive maintenance tasks should take place. The duration of conditional maintenance task, DMTm, represents the elapsed time needed for the successful completion of the task. See Figure 2.6

Figure 2.6 Conditional maintenance task activities (adapted, source, Kumar et al., 2000)

Conditional maintenance task activities

Inspection/ Examination

Data

collection

Condition assessment

Condition interpretation

Decision making

DMTm

COT start

COT complete

FMTI/FMTE

2.2.4 Maintenance cost The cost of maintenance task is the cost associated with each corrective or preventive task whether time-based or condition-based. The expected corrective costs are the total cost of maintenance resources needed to repair or replace the failed items. Similarly, the expected preventive maintenance cost is the total of maintenance resources needed to inspect and/or examine an item before a failure takes place and to replace any items failed. The sum of the corrective and preventive maintenance cost is the total cost throughout a systems life and the overhead costs, which consists of all costs other than direct material, labour, and plant equipment. The cost of maintenance can be divided in two categories: Direct cost of maintenance task and indirect cost of maintenance task. Direct costs consists of cost of spare parts, material, personnel, tools and support, equipment, facilities and technical data. Indirect costs consists the cost of management and administration staff needed for the successful completion of the task, also costs related to a complete or partial loss due to availability. It also includes overhead costs as heating, insurance, taxes, facilities, electricity, telephone and IT. These costs are difficult to deduce to a specific cost carrier. As a conclusion of maintenance cost one can say that the total cost of maintenance task, is the sum of direct and indirect costs

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2.3 Optimization of maintenance The objective of maintenance optimization models is to determine the optimum maintenance tasks that minimize the downtime while providing the most effective use of systems in order to secure the desired results at the lowest possible costs, taking all possible constraints into account. The models can be either quantitative or procedure based such as reliability centered maintenance, age related or total productive maintenance (Kumar et al., 2000) The most frequent criteria for developing maintenance models are:

1. Minimizing; maintenance cost, down time and time to repair. 2. Maximizing; revenue, profit, time between failure and availability. 3. Achieving required level of reliability and safety.

The need of adequate maintenance planning is the most common cause of developing mathematical models and their algorithms. These should provide optimal solutions to the following question: when should an item be repaired, replaced, inspected or examined? The mathematical model provides answer to the above question, based on information available and chosen criteria. Modeling of the relation between the operating cost per unit time or the system availability and the preventive maintenance interval is a traditional method in use. An additional measure which also has to be considered are Mean Down Time (MDT), which represents the total time the aircraft is out of operation due to maintenance.

2.3.1 Preventive maintenance and reliability It is a fact that in some cases preventive maintenance induces an increase of hazardous rate, for example considering items, which do not wear out, scheduled replacements may actually likely induce failures. But items subject to failure mechanisms such as wear, corrosion, fatigue, etc, should be considered for preventive maintenance. The hazard function could be either decreasing, increasing or be constant. Then the hazard rate for an item is decreasing due to operating time, maintenance aimed to restoring it to as new condition is actually not advisable.

Hazard rate

Operating time R

Figure 2.7 Decreasing hazard rate

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An items time to failure, is exponential distributed, if it has a constant hazardous rate. That mean, the probability of failure during the next time increment remains unchanged throughout the lifetime of the item, indicating that it is as good as new, no matter how long it has operated. Preventive maintenance is irrelevant in this case though a replacement will make no difference to the failure probability.

Figure 2.8 Constant hazard rate

Hazard rate

Operating time R

Scheduled replacement at any time will theoretically improve the reliability of a system which has an increasing hazard function. In order to optimize preventive replacement, it is therefore necessary to know the following for each item, the time-to-failure distribution, the cost of failure and the cost of scheduled replacement, and the effectiveness of maintenance after scheduled replacement.

Figure 2.9 Increasing hazard rate

Hazard rate

Operating time R

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2.3.2 MSG3, Reliability Centered Maintenance Reliability Centered Maintenance, (RCM), has its roots in the aviation industry in the late 1960s in conjunction with the introduction of the Boeing 747. The maintenance requirements from the Federal Aviation Administration resulted in a maintenance plan on which maintenance tasks were so extensive that the airlines probably would not have been able to operate the 747 with profit. As a result, the Federal Aviation Authority formed a Maintenance Steering Group, (MSG), consisting operator, manufacturer and regulator. They researched the maintenance area of particular importance to various systems, so that a logical and generally applicable approach could be used for developing maintenance strategies that could ensure maximum safety and reliability with minimization of cost. Further on, this resulted in MSG-2 and finally in the 1980s in MSG-3. The RCM study has established that there where six failure related patterns, the most common failure pattern show a failure rate decreasing with age before going into a period of random failure pattern, and most uncommon pattern show a failure rate which is constant with age before going into a period of increasing failure rate. See all six kinds of patterns established in Figure 2.10.

Figure 2.10 Different pattern of failure rate (source, Kumar et al., 2000)

1) Bathtub curve; decreasing, constant and gradually increasing failure rate

2) Low failure rate then item is new, quick increase to constant rate

3) Constant to gradually increasing failure rate

4) Constant failure rate

5) Gradually increasing failure rate 6) Decreasing to constant failure rate

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2.3.3 RCM Process The process is used to identify system functions, the way these functions fail and the consequences of the failures and apply this information to develop an appropriate maintenance tasks to prevent system failures. Primarily, one can say that the objective of RCM is to preserve systems functions taking into account objectives as minimizing costs, safety and environmental goals, and finally meeting operational goals. Additionally objectives of RCM can be described as follows:

• To eliminate ineffective preventive maintenance tasks • To focus maintenance effort on failures that may affect health, safety,

environment, economic, operation and any other business related consequences

• To increase system availability • To ensure system achieves inherent level of reliability • To achieve the above mentioned goals at minimum operation, maintenance

and support costs

Figure 2.11 The RCM closed process (adapted from Kumar et al., 2000)

RCM Decision Analysis

System Design System Selection

Failure Consequences

Failure Mode, Effect and Analysis

Failure Mode, Characteristics

Failure and Maintenance

Records

Maintenance task evaluation

Redesign

No preventive maintenance

Preventive maintenance

Maintenance Schedules

Implementation of Maintenance task

Functional Breakdown

FBD

The RCM process begins with failure mode, effect and analysis, (FMEA), which identifies the systems failure modes in a systematic and structured manner. Every one of these failure modes is then examined to determine the optimal maintenance task to reduce or avoid the severity of each failure. In this process, most of the following issues have been taken into account, namely cost, safety, and environmental and operational consequences.

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The RCM methodology varies within different industrial areas, but the basic steps are however quite common to all applications, including MSG-3. The RCM compromises the following steps:

1. System selection. 2. Perform Failure Modes and Effect Analysis. 3. RCM decision logic process. Identification of failure consequences. 4. Selection of maintenance tasks.

System selection are the first step where the areas which is assumed to benefit most from the analysis are specified, even though all areas would probably draw some benefit from RCM analysis. It is also necessary to identify the level of assembly at which the analysis should be conducted. Questions like; will an improvement in preventive maintenance reduce cost and improve reliability and safety? Does the current maintenance strategy include a large portion of time based maintenance that could be replaced with condition based? Is there a known design problem that is causing failures and results in high maintenance costs? These are common questions which occur during this phase of the process. Failure Mode and Effects Analysis is a systematic approach to identify all possible ways in which failure of a system can occur together with its causes and thus the failures potential effect on the system. It is performed to find out how each item in a system is likely to fail and what happens if it does. The FMEA does additionally often include an evaluation of the failure criticality- and assessment of the severity of the failure effect and its probability of occurrence. This is in fact two steps which is called failure mode effect critically analysis (FMECA) when combined. RCM Decision Logic Process analyses the consequences of each failure mode and identifies an applicable and maintenance task by using the principle that a maintenance task is worth doing if its deals successfully with the consequences of the failure mode which it is meant to prevent. For each failure mode, there are some questions to be asked:

1. Can the user detect the failure? 2. Does the failure mode have an affect on health of the user? 3. Does the failure mode have an affect on safety and the environment? 4. Is the cost of failure and its consequential damage greater than the cost of

preventing the failure? 5. Does the failure mode have an affect on the operational performance? 6. Does the failure mode have an affect on the appearance?

The answers are in the simple “yes” and “no” format which make them easy to record on a RCM decision worksheet. The consequences of each failure are identified based on decision logic as illustrated in Figure 2.12.

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Figure 2.12 Identification of consequences of failures (source, Kumar et al., 2000)

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2.4 Logistics Logistics are defined as the process of planning, implementing and controlling the efficient and cost-effective flow and storage of materials, process inventory, finished parts and all related information from the point of origin to the point of consumption, for the purpose of conforming to customers’ requirements (Logistics World, web). One may say that, it is the science of ensuring that the right products reach the right place, in the right quantity, at the right time, to satisfy the customers’ demands.

2.4.1 History The origin of logistics can be found in the Second World War. It was important to achieve an effective support line to getting the necessary supplies and right equipment on to the front, this to enhance the fighting moral, as well as the possibilities to hold on to the captured land. These experiences were adopted by the civil market soon after the war. The logistics theory evolved during the early 50s, and with the beginning of the computer age, it was implemented in the trade market, which contains of manufacturing and sales management. During this period, a new logistic process emerged. The new process involved all phases through a products life time, from its early development on to its disposal. This evolved to what we today know as Integrated Logistic Support.

2.5 Integrated Logistic Support Integrated Logistics Support is explained as, the process of management, which facilitates the development and integration of the individual logistic support elements to specify, design, development, acquirement, test, field, and support systems. There are usually ten elements mentioned, and this is what it’s all about:

1. Maintenance planning 2. Supply support 3. Support and Test Equipment and Equipment support 4. Manpower and personnel 5. Training and training support 6. Technical data 7. Computer Resources support 8. Facilities 9. Handling, Storage, and Transportation 10. Design interface

These elements must be developed within the system engineering effort, and in coordination with each other. (Logistics World, web) Some compromises may be required between the elements in order to acquire a system that is affordable, operable, supportable, sustainable, transportable, and environmentally sound within the available resources. The planning for a system is normally contained in an Integrated Logistics Support Plan. The planning activities coincide with development of the system acquisition strategy, and the program will be tailored accordingly. The above mentioned elements are explained in detail, in numerical order (Wikipedia, 2001, web).

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2.5.1 Maintenance Planning Maintenance planning begins early in the acquisition process with development of the maintenance concept. It is conducted to evolve and establish requirements and tasks to be accomplished for achieving, restoring, and maintaining the operational capability for the life of the system. Maintenance planning relies on something called, Level Of Repair Analysis, which is a function within the system acquisition process. The maintenance planning contains of:

1. Define the actions and support that is necessary to ensure that the system attains the specified system readiness objectives within minimum Life Cycle Cost.

2. Setting up specific criteria for repair, requirements, testability, reliability, and maintainability, support equipment requirements and manpower skills and facility requirements.

3. State specific maintenance tasks, to be performed on the system. 4. Define actions and support required for fielding and marketing the system. 5. Address warranty considerations. 6. The maintenance concept must ensure prudent use of manpower and

resources. When formulating the maintenance concept, analysis of the proposed work environment on the health and safety of maintenance personnel must be considered.

7. Conduct a Level Of Repair Analysis, to optimize the support system, in terms of Life Cycle Costs, readiness objectives, design for disposal, maintenance task distribution, support equipment, and manpower and personnel requirements.

8. Minimize the use of hazardous materials and the generation of waste.

2.5.2 Supply Support Supply support, encompasses all management actions, procedures, and techniques used to determine the requirements to:

1. Acquire support items and spare parts. 2. Catalog the items. 3. Receive the items. 4. Store and warehouse the items. 5. Transfer the items to where they are needed. 6. Issue the items. 7. Dispose of secondary items. 8. Provide for initial support of the system. 9. Acquire, distribute, and replenish inventory.

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2.5.3 Support and Test Equipment Support and test equipment includes all required equipments, mobile and fixed, that is needed to perform all support functions, except that equipment which is an integral part of the system. This category also encompasses planning and acquisition of logistic support for the required equipments. It contains of:

1. Handling and maintenance equipment. 2. Tools (hand tools as well as power tools). 3. Metrology and measurement devices. 4. Calibration equipment. 5. Test equipment. 6. Automatic test equipment. 7. Support equipment for on- and off-equipment maintenance. 8. Special inspection equipment and depot maintenance plant equipment, which

includes all equipment and tools required to assemble, disassemble, test, maintain, and support the production and/or depot repair of end items or components.

2.5.4 Manpower and Personnel Manpower and personnel involves the identification and acquisition of skilled personnel with grades required to operate and maintain a system over its whole lifetime. Manpower requirements are developed and personnel assignments are made to meet the support demands throughout the life cycle of the system. Manpower requirements are based on related Integrated Logistics Support elements and other considerations. Human factors engineering or behavioral research is frequently applied to ensure a good man-machine interface. Manpower requirements are found on accomplishing the logistics support mission in the most efficient and economical way. This element includes the requirements during the planning and decision process to optimize numbers, skills, and positions. This area considers:

1. Man-machine and environmental interface. 2. Special skills. 3. Human factors considerations during the planning and decision process.

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2.5.5 Training and Training Devices Training and training devices support encompasses the processes, procedures, techniques, training devices, and equipment used to train personnel to operate and support a system. This element defines qualitative and quantitative requirements for the training of operating and support personnel throughout the life cycle of the system. It includes requirements for:

1. Factory training. 2. Instructor and key personnel training. 3. New equipment training team. 4. Resident training. 5. Sustain trainings. 6. User training. 7. Disposal and safe procedures training.

Embedded training devices, features, and components are designed and built into a specific system to provide training or assistance in the use of the system. The design, development, delivery, installation, and logistic support of required embedded training features, mockups, simulators, and training aids are also included.

2.5.6 Technical Data Data and Technical Publications consist of scientific or technical information that is necessary to translate system requirements into discrete engineering and logistic support documentation. Technical data is used in the development of repair manuals, maintenance manuals, user manuals, and all other documents that are used to operate or support the system. Technical data includes, but may not be limited to:

1. Technical manuals. 2. Technical and supply bulletins. 3. Transportability guidance technical manuals. 4. Maintenance expenditure limits and calibration procedures. 5. Repair parts and tools lists. 6. Maintenance allocation charts. 7. Preventive maintenance instructions. 8. Drawings/specifications/technical data packages. 9. Software documentation. 10. Provisioning documentation. 11. Depot maintenance work requirements. 12. Identification lists. 13. Component lists. 14. Product support data. 15. Flight safety critical parts list for aircraft. 16. Lifting and tie down pamphlet/references. 17. Hazardous Material documentation.

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2.5.7 Computer Resources Support Computer Resources Support includes the facilities, hardware, software, documentation, manpower, and personnel needed to operate and support computer systems and the software within those systems. Computer resources include both stand-alone and embedded systems. This element is usually planned, developed, implemented, and monitored by a Computer Resources Working Group, or Computer Resources Integrated Product Team, that documents the approach and tracks progress via a Computer Resources Life-Cycle Management Plan. Developers will need to ensure that planning actions and strategies contained in the Integrated Logistics Support Plan are complementary and that computer resources support for the operational software, and Automatic Test Equipment software, support software is available where and when it is needed.

2.5.8 Handling, Storage, and Transportation This element includes resources and procedures to ensure that all equipment and support items are preserved, packaged, packed, marked, handled, transported, and stored properly for short- and long-term requirements. It includes material-handling equipment and packaging, handling and storage requirements, and pre-positioning of material and parts. It also includes preservation and packaging level requirements and storage requirements (for example, sensitive, proprietary, and controlled items). This element includes planning and programming the details associated with movement of the system in its shipping configuration to the ultimate destination via transportation modes and networks available and authorized for use. It further encompasses establishment of critical engineering design parameters and constraints (e.g., width, length, height, component and system rating, and weight) that must be considered during system development. Customs requirements, air shipping requirements, rail shipping requirements, container considerations, special movement precautions, mobility, and transportation asset impact of the shipping mode or the contract shipper must be carefully assessed. This planning must consider:

1. System constraints (such as design specifications, item configuration, and safety precautions for hazardous material).

2. Special security requirements. 3. Geographic and environmental restrictions. 4. Special handling equipment and procedures. 5. Impact on spare or repair parts storage requirements. 6. Emerging new technologies, methods, or procedures and resource-intensive

procedures. 7. Environmental impacts and constraints.

These factors are measured by Mean Logistic Delay Time (MLDT), which also includes waiting time for personnel and parts.

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2.5.9 Facilities The Facilities logistics element is composed of a variety of planning activities, all of which are directed toward ensuring that all required permanent or semi permanent operating and support facilities are available concurrently with system fielding. Planning must be comprehensive and include the need for new construction as well as modifications to existing facilities. Facility construction can take from 5 to 7 years from concept formulation to user occupancy. It also includes studies to define and establish impacts on life cycle cost, funding requirements, facility locations and improvements, space requirements, environmental impacts, duration or frequency of use, safety and health standards requirements, and security restrictions. Also included are any utility requirements, for both fixed and mobile facilities, with accent on limiting requirements of insufficient or unique resources.

2.5.10 Design Interface Design interface is the relationship of logistics-related design parameters of the system to its projected or actual support resource requirements. These design parameters are expressed in operational terms rather than as inherent values and specifically relate to system requirements and support costs of the system. Programs such as "design for testability" and "design for disposal" must be considered during a system design. The basic items that need to be considered as part of design interface include:

1. Reliability requirements. 2. Maintainability requirements. 3. Standardization requirements. 4. Interoperability requirements. 5. Safety requirements. 6. Security requirements. 7. Usability requirements. 8. Environmental requirements. 9. Privacy requirements, particularly for computer systems. 10. Legal requirements.

2.6 Aviation logistics Aviation logistics does not differ from the basic logistics theory, although there is a complex regulation demand that needs to be complied during the logistics process development. This to meet the airworthiness directives set by national/international regulating authorities.

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2.7 Interviews During our work, several cost and time-period related questions arose. We needed answers to these questions, otherwise we should not been able to calculate the time span, as well as costs related to unscheduled maintenance tasks. By time span, we mean the different time periods that an aircraft is standing on the ground because of unexpected failures, i.e. MDT, MTTF and MTTR. The costs are dedicated to the costs of labour, aircraft standing time (i.e. staff, passenger, etc) and spare parts, until the failure is rectified. Our questions were asked to, and answered by our sponsor Jan Viklund at LFT. Some questions were ATA-group related, and were thereby repeated through the most failure frequent ATA- groups. In our case, the ATA-25, 32, 72, 76 and 79 groups. By getting number and figures related to each question, we were able to calculate a mean value for every cost and time aspect for the regarding ATA-group. This means that our figures are all fictive and in some manner even exaggerated. What were the questions and what answers did we get? They are all listed in Table 2.1 below. Questions Answers What is the cost when an Aircraft is standing on the ground unintentionally?

An unexpected interruption in operation of a 160 pass aircraft costs approx. 100.000Sek / day (≈10.000$ / day).

What is the MTTR figure for ATA-group 25,32,72,76 and 79?

ATA-25 ≈1-3h, ATA-32 ≈1-8h, ATA-72 ≈16h ATA-76 ≈4-5days+ 8h ctr flight, ATA-79 ≈1-5h

What is the MDT figure for the regarding ATA-groups?

Add 20% to the MTTR-figure and you will have the approximate MDT-figure.

What is the cost for spare parts regarding to the ATA-groups?

ATA-25≈500-30000$, ATA-32≈60-80$/h(leasing account, brakes most freq. 1500$ ea), ATA-72 ≈(leasing account) ATA-76 ≈ 150.000$, ATA-79 ≈100-500$

What is the cost of keeping spare parts in stock, like personnel and facilities?

This is a complex question. In the organizations closure you will regard the stock as an asset, not an expense. You might have a cost initially when parts are purchased but it will be converted in to an asset in the closure. Usually consumables are kept in stock, like filters, tires, relays, gaskets and bulbs.

How long does it take to get the parts, ASAP?

From the US you will get the part within 12hours. From the EU you will get the part within 3hours.

Where is the bottleneck in the logistic system?

It is often the Toll that creates most of the delays and waiting time. The figures in the previous question is depending on if the consignment is stuck in a Toll random sample check or not.

What is the maintenance cost to repair or replace parts, approximately?

The labor and facility cost can be said to be 65$ per hour plus social fees of 32%, plus profit margin of 20%. This counts to approximately 103$ per hour.

What is the cost to repair or replace parts, approximately?

For this question we had prepared a list of maintenance tasks which can be seen in Appendix I

Table 2.1 Questions and answers from interview

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Out of these questions and answers, we were able to create a cost calculation model to show if savings could bee made out of preventive actions. See chapter 4.5.2 Analyses of preventive maintenance. Further more, some short, on the spot, interviews with people of certain knowledge have been done as the questions have emerged. These questions, mostly reliability and probability related, have been directed to some people at the Division of maintenance engineering, at LTU. The answers to these questions were important to create progress of our knowledge in, and the development of, the theoretical part of our work. Another important event in the work have been the partly presentations with the examiner, supervisor and sponsor. During these meetings, we have discussed the work, its progress, and if we have been able to keep on the track. Answers to any resulting questions have also been given during these meetings.

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Chapter 3

AUTHORITY REGULATIONS 3.1 Certifying authority Each country has a certifying authority, which supervise each and every happening in the respective aviation industry and its organizations. A standardized system of regulation is often used as a base for the creations of the national law and regulations. Swedish authority was earlier complied with Joint Aviation Regulation (JAR), but now since joining the European Union, regulations are complied with the European Aviation Safety Agency (EASA) standard. Since, there are political and cultural differences within the union, the EASA standard is thought to be a common foundation, on to which the union members can rely on their regulations. This will make the procedures in the aviation industry alike, no matter in which country you might be in. To highlight the main thought by the EASA standard, the following text is brought from the EASA agency structure (EASA, 2005, web): In order to ensure that decisions on safety issues are free from all political interference. Decisions must be in the hands of a neutral and independent decision maker invested with the necessary powers. This is why the safety decisions of the agency will be taken by its executive director, as is already the case in most countries which have developed systems for aviation safety regulation.

Executive Director

Rulemaking Certification Quality Administrative

Organization

Continuing Airworthiness

Production

Design

Figure 3.1 EASA organizational chart (modified organizational chart, source EASA, 2005)

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Since these decisions directly affect people and organizations, the Regulation creates an independent “Board of Appeal”, whose role is to check that the Executive Director has correctly applied European legislation in this field. The Executive Director is appointed by the Agency’s Management Board. The Board, which brings together representatives of the Member States and the Commission, is responsible for the definition of the Agency’s priorities, the establishment of the budget and for monitoring the Agency’s operation. The Advisory Body of Interested Parties assists the Management Board in its work. It comprises organizations representing aviation personnel, manufacturers, commercial and general aviation operators, maintenance industry, training organizations and air sports. This study will be performed according to the regulations in EASA Part-145 and Part-M, advised through the department of Certification-Organization-Continuing Airworthiness. See figure 3.1 above The following Department explanation is brought to you from EASA Certification Directives. Certification The Agency’s Certification work also includes all post-certification activities, such as the approval of changes to, and repairs of, aeronautical products and their components, as well as the issuing of airworthiness directives to correct any potentially unsafe situation. All type-certificates are therefore now issued by the European Aviation Safety Agency and are valid throughout the European Union. On the same date the Agency became the competent authority to approve and oversee the organizations involved in the design of aeronautical products, parts and appliances. It also carries out the same role for foreign organizations involved in the manufacture or maintenance of such products. To execute its tasks within the present period of building up its resources, the Agency relies on national aviation authorities who have historically filled this role and concludes contractual arrangements to this effect. EASA’s maintenance-related activities are executed in accordance with Regulation (EC) 2042/2003 and its associated annexes. On an organizational level, certification of maintenance organizations is handled by the ‘Continuing Airworthiness’ team of the ‘Organization Approvals’ unit within the Certification directorate.

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Airworthiness The Agency is responsible for the design of products, parts and appliances designed, manufactured or used by persons under the regulatory oversight of European Union Member States. In that context it shall issue airworthiness directives to ensure the continuing airworthiness of such products, parts and appliances. When doing so, the Agency only exercises the responsibilities of a State of Design or those related to the design of such products, parts and appliances of a State of Registry. Airworthiness directives are therefore addressed to the holders of the design approvals affected by such airworthiness directives. The dissemination of airworthiness directives to aircraft owners is a responsibility of the State of Registry and does not belong to the Agency. For products, parts and appliances, for which the Agency only exercises the design responsibilities of the State of registry, its policy is to endorse automatically the airworthiness directives issued by the State of design, except if it itself issues a different airworthiness directive before the date of effectivity of the State of design airworthiness directive. Only those airworthiness directives issued by the Agency itself are published. The complete directives of EASA Part-M and Part-145 regulations can be read at the EASA website see references.

3.2 Maintenance Review Board (MRB) The purpose of a MRB is to establish an initial maintenance program during the development of a new aircraft. A Maintenance Proposal Document (MPD) will be assessed by the MRB. When the MRB is satisfied with the solving of every outstanding point resulting from the MPD, a MRB-report will be published and distributed as a part of all airworthiness material such as, maintenance manuals and service bulletins, which are required for a type certification. Normally, before the report is being published, the MRB is deciding if there should be an establishment of a regular periodic revision program. It is also decided whether a full or a part reconvening of the MRB is necessary to implement the revision process. MRB can also be applied to individual power plants and equipment if there are alternative fits on the aircraft. It can also be used on retrofit actions on any already certified aircraft.

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3.3 Aircraft Maintenance Program (AMP) The AMP is based on several publications and documents, such as, aircraft- and engine manufacturer maintenance manual, airplane flight manual, parts catalogs, service bulletins, airworthiness directives and other state authority regulations. A list of the latest revision must be kept by the operators´ technical department. The operator is responsible for the technical documents. The maintenance program inspection intervals can be expressed either in flight time as well as in calendar time and/or cycles. The AMP is often structured in different chapters and related sub-chapters. First there is a section which consists of different lists and contents and further, there is a General section containing contents of, Applicability, Cross-references, Permitted variations and Airworthiness directives, etc. This is followed by the Maintenance procedures section, which in detail describes what to do, whether it is a special/periodic inspection or an overhaul. These detailed inspections are themselves divided into ATA-100 sub-group numbers. The Daily inspection procedures are also located in this section.

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Chapter 4

MAINTENANCE TASK COMPILING 4.1 Maintenance task compiling Maintenance tasks is described as, what to maintain and how, at a certain time. Each task is connected to a special part on the aircraft. Several tasks can be, and are, performed at the same time. Maintenance tasks can also consist of inspections, to determine a parts condition, and if necessary replacement. Scheduled maintenance of an aircraft is important to withstand the high requests of safety from authorities, and of course the passengers, after all, they are the customers. For the operator it is important to get high availability to the aircraft, because, they are running a business and want it to generate money, preferred profit. Aircrafts are very expensive, and the operator needs to do down payments according to their instalment plan. This is easiest done by shuttle people from destination A to B, and not by standing broken down on the ground. To gain maximum availability and safety, a maintenance plan, AMP, is developed by the operator with directions from aircraft manufacturer, MRB/MPD, and with approval from aviation authorities to gain airworthiness. This plan describes what to do, when to do and how to do the maintenance tasks. The logistics planning is likewise playing an important roll in an aircraft’s availability. This by getting the right parts at the right time and at the right quantity, or by keeping high failure frequent parts in stock. Also tool and facility requirements and human recourses are a key factor to this subject. Some operators possess facilities and personnel, or are buying maintenance services from maintenance organizations, at several airports, which mean that they are able to make their maintenance at different locations, depending on their, at the time, needed requirements. This will dramatically improve their aircrafts availability. By spreading the maintenance tasks through time, the chance to detect any oncoming failure is vastly improved, because, by dismantling one part from the aircraft for maintenance or replacement, you might be able to spot any deflections you had not been able to do otherwise. For example fatigue cracks in mountings, shields, pipes and airframe that would have been covered by the part or hidden behind. Even just by glance into the parts mounting compartment may reveal if something is out of order. This it self will contribute to increase on safety. To be able to show the spread in time of the maintenance tasks, we will use a sample aircraft fleet, and show all scheduled tasks during a timeframe of one year. We will add a randomised result of unscheduled tasks as well. The tasks are then compiled and analysed. For a visual effect, the compilation is also drawn in graphical diagrams. See Figure 4.1 or Appendix II.

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4.2 Sample aircraft fleet Since the remarks/defects data from aviation operators commonly is confidential, it is hard to receive data for this study, this is due to its security and the competitive market with few actors. Although, some data has been provided, covering different aircraft types and sizes, and to protect the sources of these, we choose to use three unspecified sample aircrafts which represents the mean average of these data. These three aircrafts does also represent 10% of a minor to medium average fleet. The aircrafts are:

• Aircraft s/n 5 with initially 33350 runtime hours i.e. an aircraft near the end of its life time cycle.

• Aircraft s/n 17 with initially 18620 runtime hours i.e. an aircraft in the middle of its life time cycle.

• Aircraft s/n 29 with initially 2130 runtime hours i.e. an aircraft in the beginning of its life time cycle.

To be reasonable we assume that an aircraft in this average fleet flies 5 hours a day 6 days a week i.e. 1560 hours a year. Further on we assume that 1 flying hour equals 1 cycle which is a reasonable assumption for domestic flights. 1 cycle equals one take off and landing i.e. one flight, notice, this is only valid for short distance flights.

4.3 Determine the scheduled maintenance All scheduled maintenance tasks in the AMP were studied, inspections and replacements, based on cycles, and monthly intervals, were translated into run time hours based on the assumptions made earlier in chapter 4.2 above. The tasks were divided into three groups; “scheduled inspections”, “special inspections/hard time components” and “overhaul and life limits”. All tasks in each group which shall be performed at the same timely interval is indexed together to minimize the amount of data, see Appendix I. A study of the initial status of the aircrafts was done to determine what tasks have been done until the beginning of the timeframe, and when previously were done. We do assume that all aircrafts has been operated under the same AMP conditions since they first entered into operation. Further on, we determined what tasks should be done, and when, within the timeframe.

4.4 Determine the unscheduled maintenance Only five of the most frequent ATA groups will be undertaken in this study to represent the defects on the sample fleet. From the data provided, an average rate of the probability is determined in percentage on how likely it is, that an item fails (in respect of time limits for this study we regarding each group as one item) during one flying our.

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The result of this study gives the following probability: ATA Description Probability to fail/flight hour (%) 25 Equipment/Furnishings 1,67 32 Landing gear 0,83 72 Engine 0,3 76 Engine controls 0,27 79 Oil 0,56 Table 4.1 The probability to fail for each ATA group When the probability of failure per flight hour is determined for each ATA group, we can determine the defects spread over the year, by randomize a number between 1-100 for each run time hour during one year i.e. 1560 times per aircraft and ATA group. Every time the randomized number is equal to, or less, than the probability factor it will give us a defect, and also which runtime hour the defect occurs. The planned and unplanned tasks were compiled into diagrams were the y-axis represents the amount of tasks, and the x-axis represents days, one diagram for each quarter of the year. For examples, see Figure 4.1 or Appendix II. The maintenance tasks is indexed in Table 4.2, see Appendix I for specification of each index.

Aircraft s/n 5 4th qtr 2006

0

2

4

6

8

10

12

14

2006-10-08 2006-10-15 2006-10-22 2006-10-29 2006-11-05 2006-11-12 2006-11-19 2006-11-26 2006-12-03 2006-12-10 2006-12-17 2006-12-24

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

Figure 4.1 The expected maintenance situation for the 4th qtr of 2006

Aircraft s/n 5 Maintenance tasks 4th qtr Date Task Date Task

2006-10-08 ATA 25 2006-11-24 a 2006-10-08 a 2006-11-25 ATA 72 2006-10-17 ATA 79 2006-11-30 ATA 79 2006-10-20 4,a,b 2006-12-06 2,a,b,e,h,I 2006-10-22 ATA 32 2006-12-08 ATA 32 2006-10-27 ATA 72 2006-12-10 ATA 72 2006-11-01 a 2006-12-12 ATA 25 2006-11-12 a 2006-12-13 ATA 72 2006-11-13 ATA 25 2006-12-17 ATA 25 2006-11-15 ATA 79 2006-12-17 a 2006-11-15 c 2006-12-29 a

Table 4.2 Index of maintenance tasks, see Appendix I for further details

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4.5 Maintenance data analysis Maintenance managers and engineers are frequently using the data information that they do collect as the organizations daily work proceeds. They do not, however, share their information with other organizations. Maintenance data are available, but not shared, from many different sites all over the world. If this information is used in an effective manner, it has the potential to be used by maintenance organizations, to gain advantages over their competitors. The best way to accommodate this is, to share relevant information amongst each user which is connected to the regarding system, in a uniform and accurate manner. The information should also be provided timely, to improve its statistic impact. Due to the increasing use of the internet, maintenance organizations can have an on-line access connection to all the supporting information, and can be used by maintenance engineers and managers for analysis and the predicting of any future maintenance requirements. By collecting and performing analysis of gathered maintenance data, the stocking and purchasing process will be supported. To complete the information share task, it should also contain all information on the technical system, and the location of the sharing asset. By this, measurements of the maintenance systems performance and the comparison of the environmental impact of the maintenance tasks can be made.

4.5.1 Analysis of failure occurrence The Poisson probability mass function and cumulative distribution function are widely used in the aviation industry since they give a good approximation. Let us take a look at the ATA 32 group as an example: The total number of ATA 32 incidents in our fleet was 35, MTBF were calculated to 131 hours. For one quarter during one year, the three aircrafts in our fleet flies 1170 hours (TFh).

λt is given by MTBFTFht =λ and by calculating the Poisson probability distribution

function ƒ(t) and the Poisson cumulative distribution function F(t), the following diagram can be drawn:

Probable number of ATA 32 failures during three months

00,02

0,040,06

0,080,1

0,120,14

0 5 10 15 20 25

Number of failures

Pro

babi

lity

dist

ribut

ion

func

tion

0

0,25

0,5

0,75

1

Cum

ulat

uve

dist

ribu

tion

func

tion

Probability distribution function Cumulative distribution function

Figure 4.2 Poisson probability- and cumulative- distribution functions of ATA 32 during three months.

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It becomes clear how many times this item is likely to fail, and how certain this approximation is. The thinner and higher the probability mass function is, the more certain the prediction is. In this case one may say that it is most likely that this item will fail 7-10 times within the time frame of three months. Based on this information decisions about spares provisioning may be possible to take, even though there are more factors to be considered. This is further discussed in chapter 5.

4.5.2 Analysis of preventive maintenance There is a need for more information than MTBF to be able to say something about the outcome of for example if extra checks would be profitable, so other measurements which where calculated and approximated was MTTR, MDT, cost of the part needed, cost of repair/hour (labor, facility and VAT) incubation time of failure and finally, the cost of operational losses due to down time. All with reference to the interview, this unfortunately, is our only available source of this kind of information. Thereby, simplifications and assumptions had to be made, especially to fit our minimized sample fleet. A very simple model was developed, based on this information that will help us to see the impact that extra checks would do on the total cost. Let’s say that there are a number of failures expected to randomly occur within a certain period of time, based on knowledge of the past. Then, if extra checks are performed in a given time interval, how likely is it, that one inspection will reveal a failure within its incubation time? Or, as another approach, how many of these failures are likely to be revealed within their incubation time? The last approach seems to give some valuable information, let’s keep that track for a moment. If we consider the probability of survival R(t) and failure rate F(t), within a limited time period as an exponential distribution, they would be represented by:

tetR λ−=)( and where tetF λ−−= 1)(MTBF

1=λ

Then, if we know the incubation time ti for the failure, we can calculate the probability to reveal failures within time ti from time zero, see Figure 4.3, to let’s say 14% i.e it’s probable that 14% of the failures occurs during that period of time. If we choose to do extra checks at a certain time interval tc, the probability to reveal failures at time tc would be 14% of the remaining 32% i.e 4,48%.

Figure 4.3 Exponential distribution

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So, with knowledge of the total flight hours within the time frame TFh, the cost of the unscheduled maintenance i.e down time DTcost, incubation time ti, MTBF, how long a extra check would take Ct, the interval of extra checks Ci, MTTR (to repair the failure), MDT, the maintenance cost per hour Mcost and the cost of the part needed Pcost, we can calculate the approximate savings, or losses, that the extra check would gain. The number of the expected failures Nf during the period of time represents by:

MTBFTFhN f =

The number of failures probable revealed Frevealed will then be

frevealed NtFF ⋅= )( If no extra checks are performed, we assume that all failures occur during or before operation, and therefore, instantly results in operational losses, the total cost would then be approximated to:

( ) ftttchecksno NDTMDTPMMTTRcTot ⋅⋅++⋅= coscoscos.. The total cost of these extra checks (repair excluded) can be calculated with:

ittchecks C

TFhMCcTot ⋅⋅= cos.

The total costs to repair the failures revealed due to these checks, here we assume that these repairs do not affect on the operational availability, are then:

( ) revealedttfrevealed FPMMTTRcTot ⋅+⋅= coscos.. All failures will probably, and most certain, not be revealed during these checks. So, the total costs for the rest of the failures will then be:

( ) ( )revealedftttfunrevealed FNDTMDTPMMTTRcTot −⋅⋅++⋅= coscoscos.. So, to examine if it would give any savings to perform extra checks due to a failure that randomly and frequently occur, we just calculate the difference between the total costs when no extra checks are performed, and the total cost when performing extra checks i.e

( )funrevealedfrevealedcheckschecksno cTotcTotcTotcTotresult ... .... ++−=

36

This theory was used for ATA 32, we assumed that this failure has the incubation time it = 15 flight hours and extra checks are performed at an interval of 200 hours, the result is presented in Figure 4.4. The result are in fact not realistic, due to our limitation where we choose to consider the ATA groups as single parts, though there would be a lot of different failures, on different parts. The most common failures in ATA 32 would probably be related to sensors and switches, but if factors based on statistics over a certain failure that occurs randomly and frequent, this model can be, although not perfect, but anyway an approximate tool.

Figure 4.4 Calculation of result with extra checks To check if Frevealed is likely true, we did a validation of these data where the failures randomly where distributed over a certain period of time. And when we relate these data to the extra checks, we can see if we will be able to reveal any failures. See Figure 4.5, see the complete set for the fleet in Appendix IV.

2006

-01-

02

2006

-01-

16

2006

-01-

30

2006

-02-

13

2006

-02-

27

2006

-03-

13

2006

-03-

27

2006

-04-

10

2006

-04-

24

2006

-05-

08

2006

-05-

22

2006

-06-

05

2006

-06-

19

2006

-07-

03

2006

-07-

17

2006

-07-

31

2006

-08-

14

2006

-08-

28

2006

-09-

11

2006

-09-

25

2006

-10-

09

2006

-10-

23

2006

-11-

06

2006

-11-

20

2006

-12-

04

2006

-12-

18

Incidents Checks

Figure 4.5 The test shows that we probable would reveal 2 out of 11 failures with these extra checks during a period of three months These tests were randomized several times, some times we where able to spot up to seven failures other times down to zero failures but most often around three to four failures. So we must keep in mind that this is due to the characteristics of randomization.

37

Chapter 5

DISCUSSION 5.1 Analysis reflections The data analysis in the previous chapter shows very optimistic numbers due to the limitations which were necessary to keep this study within reasonable limits. There are a lot of factors left which has to be taken into consideration. First of all, only the main landing gear ATA 32-10-00 contains of one to two hundred parts with differentiated prices. So, the reducing of all these parts to only one part gives a relative high failure rate for this ATA group, and then, we use the most common spare part price, although, there are most likely some kind of parts which have a higher failure rate than others, for example the brake system or sensors, switches, actuators, electrical wires, its connectors and tubing which all are exposed to vibrations and extreme changes of ambient conditions and some of them to bending and mechanical wear. Frequent failures among components like these mentioned, can be spotted and maybe prevented by following up and analyze the maintenance deviation reports. Another thing to take into consideration is the fact that the operators are commonly leasing the aircrafts, or parts of it, such as engines and landing gears. This is not enough, there is also another economical issue which has to be considered, see, if the part is easy to replace, and the failure consequence is not directly intruding the area of safety, which is a valid situation with duplex or triplex redundant systems, there are probably no need for preventive checks. On the other hand, this situation requires a good logistic support so that the part is available just in time when they are needed. This is a key to keep a good financial balance.

38

Finally, we would like to attach great importance to the fact that this study doesn’t consider the influence of the aircrafts certain age, this due to lack of information. Generally, is that the maintenance costs for an aircraft over its life cycle can be defined as a bathtub curve. See Figure 5.1. Initially, in sector a, this is the test period, the aircraft are tested under several operating conditions, after this period, the aircraft is delivered to the operator and begins to operate. The total maintenance cost are relatively high at the beginning, this is due to teething troubles, and evaluation of the actual maintenance needs. The sampling period starts in sector c when the optimal level of maintenance is reached and no teething troubles remains. The curve will tend to increase after a while, this is due to structural problems like corrosion and fatigue, which are strictly connected to the aircrafts age, and due to this, heavy maintenance tasks must be performed. The organization disposes the aircraft during sector c. To be more specific one may say that large airline organizations generally buy their aircrafts at the beginning of sector b, and disposes them somewhere in the first half of sector c, while small and medium sized airliners generally buy their aircrafts somewhere around the transition of sector b and c, and disposes them in the beginning of sector d.

Figure 5.1 Cost of maintenance during an aircrafts life cycle The three aircrafts in our sample fleet would be represented like this; Aircraft s/n 5 would be found in the beginning of sector d, aircraft s/n 17 would be found in the beginning of sector c and aircraft s/n 29 would be found in the beginning of sector b. This is a reality that must be considered during the maintenance and spare part planning.

39

5.2 Logistic software This study were initially performed to find a model to serve as a basis for spares provisioning strategy as well as improvement of AMP strategy, but, why invent the wheel once again?, there are a lot of software companies where some of them spent up to 30 years of data analysis and development of mathematical strategies. The one and only valid answer of this question would be that the license fees for such a software tool are too high in comparison with the money saved by using it, at least for smaller organizations. The license fees for a sufficient software regarding maintenance and spares provisioning optimization, are commonly quite high, approximately 10 000$ for one year. For the major sized operators this investment commonly gives a great payback. What about the minor operators and the organizations which are contracted by the operators? It may be difficult for a maintenance organization to convince the operator that more maintenance with higher maintenance cost, will reduce the long term cost due to increase of availability. So, a simple tool which gives an approximate result of how much there is, if any, to save, would be motivated to develop. However, this simple model is not perfect, but it may be a base for further development.

5.3 Spares provisioning optimization So, can this information also be used for spares provisioning optimization? The answer is yes. There are a lot of factors to consider and since the lack of data we will only discuss this theoretically. With knowledge of the estimated probable number of failures for a given time, for example three months see Figure 4.2, one may forecast the upcoming need for spares. By considering the parts failure frequencies, MLDT i.e waiting time for spares etc., MTTR, price and the stock holding capabilities it is possible to optimize the spares provisioning. To enlighten this topic, two examples are given as follows: Example 1: Once again we will refer to Figure 4.2 Lets say that this figure shows the probable amount of failures regarding to gear “down and locked” indicator light bulbs, for the whole fleet. From the figure we estimate that 8 to 9 bulbs will fail during a period of three months. The price of these bulbs is relatively low and they don’t require a lot of stocking space, but the consequence is that the aircraft will not be airworthy until the bulb is replaced, which is a relatively easy and quick task. As a conclusion to this example one may say that the cost of stocking the bulbs constitute a fraction of the cost of aircraft downtime, so the recommendation would be to keep at least 20 to 25 bulbs in stock for the three months period. Figure 5.2 Indicators

40

Example 2: Let’s say that an aircraft in landing configuration are on its final approach and exposed to wind shear, this result in a hard touch down. After inspection, severe structural damage to the main landing gears is detected. This situation are commonly not high frequent in the failure statistics, so it’s not expected to occur very often. The price of a main landing gear or the cost of repair is quite high, the MTTR is quite long and the difference between MLDT and MTTR is big, this means that one are able

receive the new landing gear from the manufacturer or overhaul department during the time of which it takes to disassemble the old landing gear from the aircraft. Due to the high price, the operator usually pays a cycle based fee to the manufacturer or overhaul department, in which it includes the costs of repair, overhaul and storage of landing gears. Thereby it is no need for the operator to store landing gears at a tremendous cost.

Figure 5.3 Broken landing gear Note! The pictures in Figure 5.2 and 5.3 doesn’t have anything to do with the examples

5.3.1 Analysis of previous examples The above mentioned examples are both fictive but realistic, and speculated as a result of our research during this study. They are perhaps extreme as examples but, they should be treated as opposite end points along an axis of failure scenarios. In the middle section between these extremes, there will be a difficult task to optimize the spare parts provisioning. The use of for the purpose developed logistic software will make the decisions easier on to the spares provisioning. Although this is a powerful tool, it is seldom used by mid and small sized organizations due to the high license fees. They are depending on their engineers and technicians and their gathered experiences. In fact, they are proven to make very precise forecasts just by using their common sense in conjunction with hard facts. A side effect to this is that the forecasts have an ability to be subjective due to different people’s different experiences about the same event. It can now be seen that, if a competitive software is used by a competent person with a delightful feeling for occurring events and requested needs, will be a optimal configuration in the quest of spare parts provisioning optimization.

41

Chapter 6

RECOMMENDATIONS It would be simple to recommend the organization to keep statistic records over all the measurements mentioned in chapter 4.5 but, it’s not as easy as it seems. Even if all organizations keeps records of deviations, they most likely doesn’t keep records of the exact costs of each individual deviation and the actions taken i.e. the cost of; the waiting for part and waiting for repair time, the actual mean time to repair, labor and facility costs and the cost of spare parts needed. From these data and from the data in the records already kept, it is possible to calculate all important measurements and develop a strategy like the one mentioned in chapter 4.5. If such a strategy are developed one may be able to monitor and, in detail, analyze the costs of deviations regarding to preventive tasks and spare parts in storage. Thereby, the possibility of savings of unscheduled maintenance costs can be achieved. With a well developed method one may find the optimal balance in maintenance and its costs, or to be more precisely, the cost of preventive maintenance vs. unscheduled maintenance for each component see Figure 6.1. It can clearly be seen that, the lowest total maintenance cost is at the curves intersection. The graph is pure fictive, but with a well performing record philosophy, one may be able to create a similar graph with hardcore data.

Cost of preventive- vs. unsceduled maintenance

n/r actions

$

Unsceduled Preventive Total cost

Optimal balance

Figure 6.1 Illustration of a possible relation between preventive vs. unscheduled maintenance for one single part.

42

Chapter 7

CONCLUSION Maintenance is a very vast subject which contains of various disciplines and components. In the study, we analyzed the operation and maintenance data for reliability, availability and costs. The study concludes maintenance task compiling with tasks recognized and divided in to scheduled and unscheduled tasks. The failure occurrences were analyzed and further, a preventive maintenance effect analysis was performed. The logistics influence on maintenance planning, including spare parts provisioning, was theoretically discussed. All aspects were not considered due to the limited timeframe of the study and the difficulties to receive applicable data. Although, there is scope for conducting further studies of this topic, because, there are benefits to gain if the maintenance records is structured and analyzed in a suitable manner. This makes the overview of the maintenance procedures and decision making more accurate. Even though the initial cost of restructuring the maintenance record keeping system may be high, it will certainly give a positive impact on the total maintenance cost. For large and medium sized maintenance organizations, a well performing and purposefully developed software will be a good investment. The maintenance planning and the follow-up are therefore performed by statistics and experiences. For small maintenance organizations, the cost of such software is higher than the savings that can be achieved. After all, it is up to the organization to make the decision, based on its economical circumstances and if it is economically justified to implement commercial logistic software into the organization, or finance the development of an adapted, much simpler but less effective system.

43

Chapter 8

REFERENCES 8.1 Literature Billinton Roy, Allan Ronald N (1983) Reliability Evaluation of Engineering Systems London: Pitman Books Limited ISBN 0-273-08484-4 Blischke Wallace R, Murthy D. N. Prabhakar (2000) Reliability: Modeling,Prediction and Optimization New York: John Wiley & Sons, Inc ISBN 0-471-18450-0 British Standard BS 4778, (1991), Section 3.2 Glossary of Internationale Terms British Standard Institutes, London Kumar U Dinesh, Crocker John Knezevic J, El-Haram M (2000) Reliability, maintenance and logistic support: a life cycle approach Dordrecht: Kluwer Academic Publisher Group ISBN 0-412-84240-8 Leitch Roger D (1995) Reliability Analysis for Engineers New York: Oxford University Press ISBN 0-19-856372-8 Rigdon Steven E, Basu Asit P (2000) Statistical Methods for the Reliability of Repairable Systems New York: John Wiley & Sons, Inc ISBN 0-471-34941-0 Slack Nigel, Chambers Stuart, Harland Christine, Harrison Alan, Johnston Robert (1995) Operations management London: Pitman Publishing ISBN 0-273-60316-7 Wolstenholme Linda C (1999) Reliability modeling: a statistical approach Boca Raton: Chapman & Hall/CRC ISBN 1-58488-014-7

44

8.2 Web NIST/SEMATECH e-Handbook of Statistical Methods, http://www.itl.nist.gov/div898/handbook/, accessed 18 May 2006 Logistics World The World wide Directory of Transportation and Logistics, http://www.logisticsworld.com, accessed 18 May 2006 Systecon AB Logistics Support Consultancy and Software (2001), http://www.systecon.se, accessed 18 May 2006 Wikipedia the free encyclopedia (2001), http://en.wikipedia.org, accessed 18 May 2006 EASA European Aviation Safety Agency (2005), http://www.easa.eu.int/home, accessed 18 May 2006

45

Appendix

46

Appendix I This Appendix contains a table describing which tasks each notation of the scheduled maintenance in Appendix II consists of.

I

Sced

uled

insp

ectio

nsIn

terv

al (h

rs/c

ycl)

Cal

enda

r tim

e (m

onth

s)1

Pha

se 1

200

242

Pha

se 2

400

243

Pha

se 3

600

244

Pha

se 4

800

24Sp

ecia

l ins

pect

ions

/htc

Pos:

ATA

nr:

Inte

rval

(hrs

/cyc

l)C

alen

dar t

ime

(mon

ths)

aC

omp.

driv

e be

lt, A

ir co

nditi

oner

17

50b

Bat

tery

che

ck, R

udde

r boo

st fi

lter

12,4

820

0c

Bat

tery

aci

d ch

eck

1339

03

dFu

sula

ge p

ress

ure

bulk

head

750

0e

Win

g ce

nter

sec

tion

6360

0f

Sta

nd b

y po

wer

sup

ply

5578

06

gLa

nd.g

ear,

Cab

.doo

rs, F

usul

age,

Eng

.oil

and

air f

ilter

1,2,

3,5,

15,1

8,20

,27,

34,3

6,44

,51,

5810

00h

Pow

er le

vers

4612

00i

Spa

rcap

53

34.2

0; 2

6.20

; 25.

6015

6012

jLi

ght p

anel

ass

embl

es24

08.0

020

00k

Win

g ce

nter

sec

tion

6423

4018

lFu

el p

robe

3824

00m

Pre

ssur

e bu

lkhe

ad14

2500

nA

ltim

.sys

t, O

xyg.

syst

, Pito

.sys

t, S

tatic

sys

t9,

43,4

5,57

34.0

031

2024

oE

ngin

e m

ount

2636

00p

Land

ing

gear

act

uato

rs4,

639

0030

qE

mer

g.do

or, F

ire e

stin

g, F

ligt c

ontro

l pul

ley

brac

kets

21,3

1,32

5000

rFi

re.e

stin

g, O

xyg.

cyl,

Spa

rcap

, Win

g bo

lt

29,4

2,54

,60

7800

60s

Axe

l ass

emb,

Dra

g br

ace,

Ret

ract

.gea

rbox

, Sho

ck a

bsor

ber

10,1

1,22

,23,

47,4

9,50

8000

tFu

sel&

Pre

s.bu

lkhe

ad, F

usel

, Fra

me,

Stri

ng, S

kin,

Ws

corn

, Fc

br

8,16

,33,

35,3

7,41

,52,

5910

000

uFi

re.e

stin

g, M

ain

gear

act

uato

r28

,318

720

144

Ove

rhao

ul a

nd li

felim

its

ATA

nr:

Inte

rval

(hrs

/cyc

l)C

alen

dar t

ime

(mon

ths)

IIn

stru

men

t air

filte

r37

.00

600

IIE

ngin

e oi

l and

P3

air f

ilter

s72

.00;

73.

1010

00III

Hot

sec

tion

insp

ectio

n72

.00

1800

IVB

atte

ry c

heck

/repl

acem

ent

3000

VO

xyge

n sh

ut o

ff va

lve

35.0

031

2024

VI

Eng

ine

over

haul

72.0

0; 6

1.20

; 73.

10; 7

3.20

; 75.

30; 7

9.20

3600

VII

Pro

pelle

r61

.10

4000

VIII

Cab

in d

oor l

atch

es50

00IX

Act

uato

rs32

.30

7500

XB

rake

s sy

stem

and

flam

.liqu

id c

arry

ing

hose

s 32

.40

7800

60XI

Land

ing

gear

mot

or32

.30

8000

XII

All

win

g at

tach

bol

ts, n

uts

and

barr

el n

ut a

ssem

bles

9360

72XIII

Cab

in d

oor a

ttach

ing

hard

war

e, w

s fra

me

scre

ws

1000

0XIV

Life

lim

its o

n en

gine

sta

tic a

nd ro

tatin

g pa

rt72

.00

2000

0XV

All

win

g at

tach

bol

ts, n

uts

and

barr

el n

ut a

ssem

bles

2340

018

0XVI

Life

lim

its o

n en

gine

sta

tic a

nd ro

tatin

g pa

rt, w

ing

stru

ctur

e fa

tigue

72.0

030

000

XVII

Hor

izon

tal a

nd v

ertic

al s

tabi

lizer

4500

0

Appendix II This Appendix contains of bar charts over the scheduled and unscheduled maintenance for the three sample aircrafts together with explanation tables. Be aware that each task in these charts/tables actually contains of several tasks which is to be performed at the same timely interval, refer to Appendix I for details.

II

Aircraft s/n 5

Aircraft s/n 5 1st qtr 2006

0

2

4

6

8

10

12

14

2006-01-02 2006-01-09 2006-01-16 2006-01-23 2006-01-30 2006-02-06 2006-02-13 2006-02-20 2006-02-27 2006-03-06 2006-03-13 2006-03-20

Date

Num

ber o

f tas

ksSceduled tasks Unsceduled tasks

Aircraft s/n 5 2nd qtr 2006

0

2

4

6

8

10

12

14

2006-04-04 2006-04-11 2006-04-18 2006-04-25 2006-05-02 2006-05-09 2006-05-16 2006-05-23 2006-05-30 2006-06-06 2006-06-13 2006-06-20

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

Aircraft s/n 5 3rd qtr 2006

0

2

4

6

8

10

12

14

2006-07-07 2006-07-14 2006-07-21 2006-07-28 2006-08-04 2006-08-11 2006-08-18 2006-08-25 2006-09-01 2006-09-08 2006-09-15 2006-09-22

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

Aircraft s/n 5 4th qtr 2006

0

2

4

6

8

10

12

14

2006-10-08 2006-10-15 2006-10-22 2006-10-29 2006-11-05 2006-11-12 2006-11-19 2006-11-26 2006-12-03 2006-12-10 2006-12-17 2006-12-24

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

II-i

Aircraft s/n 5 Maintenance tasks 1st qtr Maintenance tasks 2nd qtr Maintenance tasks 3rd qtr Maintenance tasks 4th qtr 2006-01-02 ATA 25 2006-04-04 a 2006-07-07 ATA 32 2006-10-08 ATA 25 2006-01-06 ATA 32 2006-04-14 ATA 25 2006-07-07 a 2006-10-08 a 2006-01-12 2,a,b 2006-04-16 ATA 76 2006-07-08 ATA 25 2006-10-17 ATA 79 2006-01-15 ATA 79 2006-04-16 4,a,b 2006-07-12 ATA 32 2006-10-20 4,a,b 2006-01-20 ATA 32 2006-04-21 ATA 32 2006-07-18 3,a,b,e,I,III 2006-10-22 ATA 32 2006-01-24 a 2006-04-27 a 2006-07-19 ATA 32 2006-10-27 ATA 72 2006-02-05 a,d 2006-05-03 ATA 72 2006-07-20 ATA 25 2006-11-01 a 2006-02-06 2006-05-09 a 2006-07-24 ATA 79 2006-11-12 a 2006-02-10 ATA 79 2006-05-14 ATA 72 2006-07-26 ATA 32 2006-11-13 ATA 25 2006-02-14 c,f 2006-05-16 c 2006-07-30 a 2006-11-15 ATA 79 2006-02-16 a 2006-05-20 ATA 32 2006-08-02 ATA 76 2006-11-15 c 2006-02-26 ATA 25 2006-05-21 a 2006-08-11 a 2006-11-24 a 2006-03-03 ATA 32 2006-06-02 1,a,b,d,g,j,II 2006-08-12 ATA 72 2006-11-25 ATA 72 2006-03-23 a 2006-06-03 ATA 25 2006-08-13 ATA 76 2006-11-30 ATA 79 2006-06-04 ATA 79 2006-08-15 c,f,i,n,V 2006-12-06 2,a,b,e,h,I 2006-06-09 ATA 25 2006-08-15 ATA 25 2006-12-08 ATA 32 2006-06-13 ATA 25, ATA 32 2006-08-17 ATA 76 2006-12-10 ATA 72 2006-06-13 a 2006-08-20 ATA 79 2006-12-12 ATA 25 2006-06-25 a 2006-08-21 ATA 25 2006-12-13 ATA 72 2006-08-22 a 2006-12-17 ATA 25 2006-08-25 ATA 32 2006-12-17 a 2006-08-29 ATA 25, ATA 32 2006-12-29 a 2006-08-30 ATA 25 2006-09-03 4,a,b 2006-09-15 a 2006-09-16 ATA 25 2006-09-20 ATA 32 2006-09-26 ATA 25 2006-09-27 a,d

II-ii

Aircraft s/n 17

Aircraft s/n 17 1st qtr 2006

0

2

4

6

8

10

12

14

2006-01-08 2006-01-15 2006-01-22 2006-01-29 2006-02-05 2006-02-12 2006-02-19 2006-02-26 2006-03-05 2006-03-12 2006-03-19 2006-03-26

Date

Num

ber o

f tas

ksSceduled tasks Unsceduled tasks

Aircraft s/n 17 2nd qtr 2006

0

2

4

6

8

10

12

14

2006-04-06 2006-04-13 2006-04-20 2006-04-27 2006-05-04 2006-05-11 2006-05-18 2006-05-25 2006-06-01 2006-06-08 2006-06-15 2006-06-22 2006-06-29

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

Aircraft s/n 17 3rd qtr 2006

0

2

4

6

8

10

12

14

2006-07-02 2006-07-09 2006-07-16 2006-07-23 2006-07-30 2006-08-06 2006-08-13 2006-08-20 2006-08-27 2006-09-03 2006-09-10 2006-09-17

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

Aircraft s/n 17 4th qtr 2006

0

2

4

6

8

10

12

14

2006-10-02 2006-10-09 2006-10-16 2006-10-23 2006-10-30 2006-11-06 2006-11-13 2006-11-20 2006-11-27 2006-12-04 2006-12-11 2006-12-18

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

II-iii

Aircraft s/n 17 Maintenance tasks 1st qtr Maintenance tasks 2nd qtr Maintenance tasks 3rd qtr 2006-01-08 a 2006-04-06 ATA 25 2006-07-02 1,a,b 2006-01-13 ATA 25 2006-04-10 ATA 25 2006-07-06 ATA 25 2006-01-17 ATA 32 2006-04-12 a 2006-07-08 ATA 32 2006-01-19 a 2006-04-16 ATA 79 2006-07-13 ATA 76 2006-01-24 c,f,i,k,n,u,V,XII 2006-04-24 a 2006-07-14 a 2006-01-25 ATA 76 2006-04-26 a 2006-07-25 a,c,d,f,p 2006-01-31 a 2006-05-07 a 2006-07-30 ATA 32 2006-02-06 ATA 25 2006-05-13 ATA 32 2006-07-31 ATA 25 2006-02-12 2,a,b 2006-05-15 ATA 32, ATA 79 2006-08-04 ATA 76 2006-02-16 ATA 32 2006-05-18 4,a,b,e,h,l,I 2006-08-06 a 2006-02-18 ATA 25 2006-05-21 ATA 25 2006-08-09 ATA 25 2006-02-23 a 2006-05-30 ATA 25 2006-08-15 ATA 25 2006-03-02 ATA 25 2006-05-30 a 2006-08-18 2,a,b,II 2006-03-07 a 2006-06-04 ATA 25 2006-08-23 ATA 72 2006-03-15 ATA 25 2006-06-08 ATA 25 2006-08-29 ATA 32 2006-03-19 a 2006-06-09 a 2006-08-29 a 2006-03-20 ATA 25 2006-06-12 ATA 32 2006-09-02 ATA 25, ATA 79 2006-03-27 ATA 25, ATA 79 2006-06-13 ATA 32 2006-09-04 ATA 25 2006-03-30 3,a,b,d,g,II 2006-06-14 ATA 25 2006-09-10 a 2006-06-20 a 2006-09-22 a 2006-06-22 ATA 79 2006-06-26 ATA 79 2006-06-30 Maintenance tasks 4th qtr 2006-10-02 ATA 32 2006-10-03 ATA 32 2006-10-04 3,a,b,e,I,III 2006-10-06 ATA 25 2006-10-15 a 2006-10-21 ATA 25 2006-10-25 c 2006-10-27 a 2006-10-29 ATA 25 2006-10-30 ATA 76 2006-10-31 ATA 32 2006-11-04 ATA 25 2006-11-07 ATA 76 2006-11-08 a 2006-11-10 ATA 25 2006-11-19 4,a,b,d,g,j,m,q,t,VII,VIII,XIII,XIV2006-11-27 ATA 25 2006-12-01 a 2006-12-13 a 2006-12-24 a

II-iv

Aircraft s/n 29

Aircraft s/n 29 1st qtr 2006

0

2

4

6

8

10

12

14

2006-01-05 2006-01-12 2006-01-19 2006-01-26 2006-02-02 2006-02-09 2006-02-16 2006-02-23 2006-03-02 2006-03-09 2006-03-16 2006-03-23 2006-03-30

Date

Num

ber o

f tas

ksSceduled tasks Unsceduled tasks

Aircraft s/n 29 2nd qtr 2006

0

2

4

6

8

10

12

14

2006-04-02 2006-04-09 2006-04-16 2006-04-23 2006-04-30 2006-05-07 2006-05-14 2006-05-21 2006-05-28 2006-06-04 2006-06-11 2006-06-18 2006-06-25

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

Aircraft s/n 29 3rd qtr 2006

0

2

4

6

8

10

12

14

2006-07-11 2006-07-18 2006-07-25 2006-08-01 2006-08-08 2006-08-15 2006-08-22 2006-08-29 2006-09-05 2006-09-12 2006-09-19 2006-09-26

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

Aircraft s/n 29 4th qtr 2006

0

2

4

6

8

10

12

14

2006-10-01 2006-10-08 2006-10-15 2006-10-22 2006-10-29 2006-11-05 2006-11-12 2006-11-19 2006-11-26 2006-12-03 2006-12-10 2006-12-17 2006-12-24

Date

Num

ber o

f tas

ks

Sceduled tasks Unsceduled tasks

II-v

Aircraft s/n 29 Maintenance tasks 1st qtr Maintenance tasks 2nd qtr Maintenance tasks 3rd qtr

2006-01-05 a 2006-04-02 ATA 25 2006-07-11 a 2006-01-17 3,a,b 2006-04-04 ATA 79 2006-07-11 ATA 25 2006-01-27 ATA 32 2006-04-10 a 2006-07-17 ATA 25 2006-01-29 a 2006-04-21 1,a,b 2006-07-23 3,a,b,d,g,I,II,IV 2006-01-30 ATA 25 2006-04-21 ATA 25, ATA 79 2006-08-04 a 2006-02-01 ATA 25 2006-04-24 ATA 32 2006-08-08 ATA 76 2006-02-09 a 2006-04-30 ATA 25 2006-08-11 ATA 25 2006-02-10 ATA 25 2006-05-04 a 2006-08-15 a 2006-02-19 c,f,k 2006-05-10 ATA 25 2006-08-16 ATA 76 2006-02-21 a 2006-05-16 a 2006-08-20 c,f,i,n,V 2006-03-05 ATA 25 2006-05-17 ATA 25 2006-08-24 ATA 32 2006-03-06 ATA 25 2006-05-18 ATA 25 2006-08-27 a 2006-03-06 4,a,b,e,h,l,I 2006-05-23 c 2006-08-28 ATA 25 2006-03-11 ATA 25 2006-05-28 a 2006-08-31 ATA 72 2006-03-17 a 2006-05-30 ATA 25 2006-09-08 4,a,b 2006-03-24 ATA 79 2006-05-29 ATA 79 2006-09-13 ATA 25 2006-03-29 a,d,m 2006-06-03 ATA 79 2006-09-14 ATA 25 2006-03-30 ATA 25 2006-06-06 2,a,b 2006-09-17 ATA 25

2006-06-18 a 2006-09-18 ATA 25 2006-06-22 ATA 25 2006-09-20 a 2006-06-23 ATA 72 2006-09-28 ATA 25 2006-06-30 a Maintenance tasks 4th qtr

2006-10-01 a 2006-10-02 ATA 25 2006-10-03 ATA 76 2006-10-04 ATA 79 2006-10-11 ATA 25 2006-10-13 a 2006-10-14 ATA 72 2006-10-18 ATA 25, ATA 32 2006-10-25 ATA 72 2006-10-25 a,b 2006-10-27 ATA 25 2006-11-02 ATA 25 2006-11-03 ATA 76 2006-11-17 a,d 2006-11-19 a 2006-11-23 ATA 79 2006-11-28 ATA 79 2006-11-29 a 2006-12-06 ATA 32 2006-12-10 ATA 32 2006-12-10 2,a,b,e,h,o,I,III,VI 2006-12-13 ATA 32 2006-12-20 ATA 32 2006-12-22 a 2006-12-29 ATA 79

II-vi

Appendix III This Appendix contains of combined bar charts and graphs which describes the probable number of failures during three months for the five ATA groups which was studied. Based on Poisson’s functions, probability mass function and cumulative distribution function.

III

Probable number of ATA 25 failures during three months

0

0,02

0,04

0,06

0,08

0,1

0 5 10 15 20 25 30 35 40 45

Number of failures

Pro

babi

lity

dist

ribu

tion

func

tion

0

0,25

0,5

0,75

1

Cum

ulat

uve

dist

ribu

tion

func

tion

Probability distribution function Cumulative distribution function

Probable number of ATA 32 failures during three months

00,02

0,040,06

0,080,1

0,120,14

0 5 10 15 20 25

Number of failures

Pro

babi

lity

dist

ribu

tion

func

tion

0

0,25

0,5

0,75

1

Cum

ulat

uve

dist

ribu

tion

func

tion

Probability distribution function Cumulative distribution function

Probable number of ATA 72 failures during three months

0

0,05

0,1

0,15

0,2

0,25

0,3

0 2 4 6 8 10 12 14

Number of failures

Pro

babi

lity

dist

ribu

tion

func

tion

0

0,25

0,5

0,75

1

Cum

ulat

uve

dist

ribu

tion

func

tion

Probability distribution function Cumulative distribution function

III-i

Probable number of ATA 76 failures during three months

0

0,05

0,1

0,15

0,2

0,25

0 2 4 6 8 10 12 14 16

Number of failures

Pro

babi

lity

dist

ribu

tion

func

tion

0

0,25

0,5

0,75

1

Cum

ulat

uve

dist

ribu

tion

func

tion

Probability distribution function Cumulative distribution function

Probable number of ATA 79 failures during three months

0

0,05

0,1

0,15

0,2

0 2 4 6 8 10 12 14 16 18 20

Number of failures

Pro

babi

lity

dist

ribu

tion

func

tion

0

0,25

0,5

0,75

1

Cum

ulat

uve

dist

ribu

tion

func

tion

Probability distribution function Cumulative distribution function

III-ii

Appendix IV This Appendix contains of a test of distribution of failure, relative extra checks for the sample fleet.

IV

Test

of d

istri

butio

n of

failu

re re

lativ

e ex

tra c

heck

s for

the

sam

ple

fleet

2006-01-02

2006-01-16

2006-01-30

2006-02-13

2006-02-27

2006-03-13

2006-03-27

2006-04-10

2006-04-24

2006-05-08

2006-05-22

2006-06-05

2006-06-19

2006-07-03

2006-07-17

2006-07-31

2006-08-14

2006-08-28

2006-09-11

2006-09-25

2006-10-09

2006-10-23

2006-11-06

2006-11-20

2006-12-04

2006-12-18

Inci

dent

sCh

ecks

2006-01-02

2006-01-16

2006-01-30

2006-02-13

2006-02-27

2006-03-13

2006-03-27

2006-04-10

2006-04-24

2006-05-08

2006-05-22

2006-06-05

2006-06-19

2006-07-03

2006-07-17

2006-07-31

2006-08-14

2006-08-28

2006-09-11

2006-09-25

2006-10-09

2006-10-23

2006-11-06

2006-11-20

2006-12-04

2006-12-18

Inci

dent

sCh

ecks

2006-01-02

2006-01-16

2006-01-30

2006-02-13

2006-02-27

2006-03-13

2006-03-27

2006-04-10

2006-04-24

2006-05-08

2006-05-22

2006-06-05

2006-06-19

2006-07-03

2006-07-17

2006-07-31

2006-08-14

2006-08-28

2006-09-11

2006-09-25

2006-10-09

2006-10-23

2006-11-06

2006-11-20

2006-12-04

2006-12-18

Inci

dent

sCh

ecks

Appendix V This Appendix contains of sample aircraft maintenance program AMP. The AMP is a real AMP, originally compiled by LFT, adapted by the authors to fit their sample aircraft fleet.

IV

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-1

0 INTRODUCTION Chapter: Page: 0 INTRODUCTION 0.0 Contents 0-1 – 0-2 0.1 List of effective pages 0-3 – 0-10 0.2 Distribution list 0-11 0.3 Record of Revision 0-12 1 GENERAL 1.1 Commitment by the Operator 1-1 1.2 Applicability 1-2 1.3 Related documents 1-3 1.4 Cross-reference to AMC OPS 1.910(a) &(b) Appendix 1 1-4 1.5 Anticipated utilisation 1-5 1.6 Procedures for escalation of established check periods 1-6 1.7 Programme basis 1-7 1.8 Amendments to the approved Programme 1-8 1.9 Permitted variations to maintenance periods 1-9 1.10 Periodic review of maintenance programme contents 1-10 1.11 Airworthiness directives incorporated in daily and periodic

inspections 1-11 2 MAINTENANCE PROCEDURES 2.1 General 2-1 2.2 Daily inspection 2-2 2.3 Periodic inspections 2-3 2.3 Periodic inspections 2-4 2.4 Special inspections 2-4 2.4 Special inspections 2-5 2.5 Overhaul and life limits – Aircraft 2-5 2.5 Overhaul and life limits – Aircraft 2-6 2.6 Overhaul and life limits – Engine 2-7 2.6 Overhaul and life limits – Engine 2-8

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-2 0 INTRODUCTION Chapter: Page: 3 PHASE 1 Instructions Card 3-1 - 3-32 4 PHASE 2 Instructions Card 4-0 – 4-35 5 PHASE 3 Instructions Card 5-0 – 5-34 6 PHASE 4 Instructions Card 6-0 – 6-33 6 Wings Lubrication 6-34 6 Thread Lubrications Chart 6-35 7 Hard Time Components / Special Inspections 7-1 – 7-5 8 Raisbeck Systems 200-hrs Inspection 8-1

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-3 0.1 LIST OF EFFECTIVE PAGES Page: Chapter: Details: Date: Revision:

0-1 0 INTRODUCTION 2005-03-01 1 0-1 0 INTRODUCTION 2005-03-01 1 0-1 0 INTRODUCTION 2005-03-01 1 0-2 0 INTRODUCTION 2005-03-01 1 0-3 0 LIST OF EFFECTIVE PAGES 2005-03-01 1 0-4 0 LIST OF EFFECTIVE PAGES 2005-03-01 1 0-5 0 LIST OF EFFECTIVE PAGES 2005-03-01 1 0-6 0 LIST OF EFFECTIVE PAGES 2005-03-01 1 0-7 0 LIST OF EFFECTIVE PAGES 2005-03-01 1 0-8 0 LIST OF EFFECTIVE PAGES 2005-03-01 1 0-9 0 LIST OF EFFECTIVE PAGES 2005-03-01 1 0-10 0 LIST OF EFFECTIVE PAGES 2005-03-01 1 0-11 DISTRIBUTION LIST 2005-03-01 1 0-12 RECORD OF REVISION 2005-03-01 1

SCAA Approval date:

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-4 0.1 LIST OF EFFECTIVE PAGES Page: Chapter: Details: Date: Revision:

1-1 1 COMMITMENT BY THE OPERATOR 2005-03-01 1 1-2 1 APPLICABILITY 2005-03-01 1 1-3 1 RELATED DOCUMENTATION 2005-03-01 1 1-4 1 CROSS-REFERENCE TO AMC OPS 1.910(a) & (b) APPENDIX 1 2005-03-01 1 1-5 1 ANTICIPATED UTILISATION 2005-03-01 1 1-6 1 PROCEDURES FOR ESCALATION OF ESTABLISHED CHECK 2005-03-01 1 1-7 1 PROGRAM BASIS 2005-03-01 1 1-8 1 AMENDMENTS TO THE APPROVED PROGRAMME 2005-03-01 1 1-9 1 PERMITTED VARIATIONS TO MAINTENANCE PERIODS 2005-03-01 1 1-10 1 PERMITTED VARIATIONS TO MAINTENANCE PERIODS,

continue 2005-03-01 1

1-11 1 PERIODIC REVIEW OF MAINTENANCE PROGRAMME CONTENTS

2005-03-01 1

1-12 1 AIRWORTHINESS DIRECTIVES INCORPORATED IN DAILY AND PERIODIC INSPECTIONS

2005-03-01 1

2-1 2 MAINTENANCE DETAILS - SE-XXX 2005-03-01 1 2-2 2 DAILY INSPECTION 2005-03-01 1 2-3 2 SCHEDULED INSPECTION PROGRAM 2005-03-01 1 2-4 2 SCHEDULED INSPECTION PROGRAM, continue 2005-03-01 1 2-4 2 SPECIAL INSPECTIONS 2005-03-01 1 2-5 2 SPECIAL INSPECTIONS, continue 2005-03-01 1 2-5 2 OVERHAUL AND LIFE LIMITS ON AIRCRAFT 2005-03-01 1 2-6 2 OVERHAUL AND LIFE LIMITS ON AIRCRAFT, continue 2005-03-01 1 2-7 2 ENGINE LIFE LIMIT PARTS 2005-03-01 1 2-8 2 ENGINE LIFE LIMIT PARTS, continue 2005-03-01 1

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Date: 2005-03-01 Revision: 1

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3-0 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-1 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-2 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-3 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-4 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-5 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-6 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-7 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-8 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-9 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-10 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-11 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-12 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-13 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-14 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-15 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-16 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-17 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-18 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-19 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-20 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-21 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-22 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-23 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-24 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-25 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-26 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-27 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-28 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-29 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1

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A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-6 0.1 LIST OF EFFECTIVE PAGES Page: Chapter: Details: Date: Revision: 3-30 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-31 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1 3-32 3 PHASE 1 INSPECTION DETAILS 2005-03-01 1

4-0 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-1 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-2 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-3 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-4 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-5 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-6 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-7 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-8 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-9 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-10 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-11 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-12 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-13 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-14 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-15 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-16 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-17 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-18 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-19 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-20 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-21 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-22 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-23 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-24 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1

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A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-7 0.1 LIST OF EFFECTIVE PAGES Page: Chapter: Details: Date: Revision: 4-25 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-26 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-27 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-28 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-29 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-30 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-31 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-32 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-33 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-34 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1 4-35 4 PHASE 2 INSPECTION DETAILS 2005-03-01 1

5-0 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-1 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-2 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-3 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-4 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-5 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-6 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-7 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-8 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-9 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-10 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-11 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-12 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-13 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-14 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-15 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-16 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1

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A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-8 0.1 LIST OF EFFECTIVE PAGES Page: Chapter: Details: Date: Revision: 5-17 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-18 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-19 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-20 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-21 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-22 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-23 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-24 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-25 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-26 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-27 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-28 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-29 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-30 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-31 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-32 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-33 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1 5-34 5 PHASE 3 INSPECTION DETAILS 2005-03-01 1

6-0 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-1 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-2 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-3 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-4 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-5 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-6 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-7 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-8 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-9 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-9 0.1 LIST OF EFFECTIVE PAGES Page: Chapter: Details: Date: Revision: 6-10 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-11 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-12 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-13 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-14 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-15 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-16 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-17 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-18 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-19 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-20 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-21 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-22 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-23 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-23 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-25 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-26 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-27 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-28 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-29 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-30 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-31 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-32 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1 6-33 6 PHASE 4 INSPECTION DETAILS 2005-03-01 1

6-34 6 WINGS LUBRICATION 2005-03-01 1 6-35 6 THREAD LUBRICATIONS CHART 2005-03-01 1

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Date: 2005-03-01 Revision: 1

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7-1 7 HARD TIME COMPONENTS / SPECIAL INSPECTIONS 2005-03-01 1 7-2 7 HARD TIME COMPONENTS / SPECIAL INSPECTIONS 2005-03-01 1 7-3 7 HARD TIME COMPONENTS / SPECIAL INSPECTIONS 2005-03-01 1 7-4 7 HARD TIME COMPONENTS / SPECIAL INSPECTIONS 2005-03-01 1 7-5 7 HARD TIME COMPONENTS / SPECIAL INSPECTIONS 2005-03-01 1

8-1 8 RAISBECK SYSTEMS 200-HRS INSPECTION 2005-03-01 1

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A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-11 0.2 DISTRIBUTION LIST Copy No: Position -/Company: Name: 1 Luftfartsstyrelsen, SCAA N/A Hard Copy 2 Accountable Manager CD-ROM 3 Maintenance Manager CD-ROM 4 Quality Manager CD-ROM 5 Part-145 organisation “Line

Maintenance” CD-ROM

6 Part-145 organisation “ Base Maintenance”

CD-ROM

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 0-12 0.3 RECORD OF REVISION Pos: Revision No: Revision date: Insert date: Signature: 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-1 1 GENERAL 1.1 COMMITMENT BY THE OPERATOR This maintenance programme, upon which the SCAA approval of Sample Fleet under JAR-OPS 1 subpart M is based, defines and specifies maintenance that is required to be carried out on the aircraft specified. The programme is approved by the undersigned and must be complied with, as applicable, in order to ensure that the aircraft and material are kept airworthy. The contents of this programme is subject to periodic (annual or more frequent) review to ensure that they reflect current Type Certificate holders recommendations, revisions to maintenance manuals, mandatory requirements and maintenance needs of the aircraft, modifications and service experience. It is further understood that practices and procedures to satisfy the programme must be to the standards specified in the Type Certificate holders Maintenance Instructions. It is accepted that these procedures do not override the necessity of complying with any new or amended regulation published by EASA/SCAA from time to time where these new or amended regulations are in conflict with this programme. It is understood that SCAA will approve Sample Fleet whilst SCAA is satisfied that the procedures are being followed. It is further understood that SCAA reserves the right to suspend or cancel the maintenance programme approval of the organisation, as applicable, if SCAA has evidence that the procedures are not followed or valid.

.......................................... Maintenance Manager (Nominated Postholder for Maintenance)

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-2 1.2 APPLICABILITY 1.2.1 The Aircraft Maintenance Programme, AMP is applicable on the following aircraft: 1. AIRCRAFT REGISTRATION: SE-XXX 2. AIRCRAFT TYPE: Sample Aircraft 3. S/N: 17 4. ENGINE TYPE: TURBOPROP 5. PROPELLER TYPE: QUIET TURBOFAN The programme is designed by Luleå Flygteknik ( SE.145.0112) and used by the operator Sample Fleet , Luleå, in accordance with the companies Maintenance Management Exposition, MME.

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page:1-3

1.3 RELATED DOCUMENTATION 1.3.1 Maintenance Management Exposition (MME) Contains details of the maintenance organisation structure, the procedures that must be followed to satisfy the maintenance responsibility of JAR-OPS 1.890 and the quality functions of JAR-OPS 1.900. 1.3.2 Maintenance Contract(s) - JAR-OPS 1 Subpart M-maintenance

Contains details of the arrangements made with a Part-145 approved maintenance organisation to ensure that the following is accomplished: a. All maintenance in accordance with this programme (JAR-OPS 1.890 (a) (3)) b. Rectification to an approved standard of defects and damages (1.890 (a) (2)) c. Any Operational Directive, Airworthiness Directive and any other continued

Airworthiness Requirement made mandatory by the Authority (1.890 (a) (5)) d. Modifications in accordance with an approved standard (1.890 (a) (6))

Note: For details of documentation from manufacturers and authorities for which this programme is based on, refer to AMP 1.7.

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-4 1.4 ANTICIPATED UTILISATION The maintenance programme contains inspection intervals in flight time as well as calendar time and cycles, for the Phase Inspections 1 to 4, (Ref: chapter 3 to 6). Special inspections ( Ref: chapter 7 and 8 ) and component overhauls having both flight time, calendar time and or flight cycle inspection or overhaul intervals are also listed with both variables. As a result, the maintenance programme is applicable regardless of the aircrafts utilisation rate.

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-5 1.5 PROCEDURES FOR ESCALATION OF ESTABLISHED CHECK

PERIODS Established check periods can only be escalated when at least one of the following criteria’s exists: Pos: Criteria: a. The operator can show that the applicable check period is not relevant in the

Operators operating environment.

b. Results from numerous previous inspections show that an escalation is warranted.

c. The operator has received approval from the Type Certificate Holder to escalate the check period.

In all cases, the operator must get approval from SCAA, to get approval the operator must send the following to SCAA: Pos: Criteria: a. The proposed revision to the maintenance programme b. Justification to the proposed change (see also 1.8)

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-6 1.6 PROGRAM BASIS The maintenance programme is based on the following publications and documents. A list of the latest revision is kept by the operator Sample Fleet technical department. Responsible for the technical documents is the operator, ( JAR-OPS 1 subpart M ). Publication No:

Publication Title: Manufacturer/ Authority

101-590010-127

Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual

Raytheon - FAA

Raytheon Electronic Publications System Raytheon - FAA 85-120 Raisbeck Engineering – Maintenance Manual Raisbeck / FAA 3021442 Engine Maintenance Manual P&W / TC 3021444 Engine Illustrated Parts Catalog P&W / TC SB Raytheon / FAA SB Engine Service Bulletins P&W / TC AD Airworthiness Directives Type Certificate Holder’s

Aviation Authority JAR-OPS 1 Joint Aviation Requirements - Commercial Air

Transportation - Aeroplane EASA/SCAA

Part - 145 Joint Aviation Requirements - Approved Maintenance Organisations

EASA

BCL-D Drifts bestämmelser för civil luftfart ( Sweden) SCAA BCL-M Materiel bestämmelser för civil luftfart (

Sweden) SCAA

AC-43/13 FAA

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-7 1.7 AMENDMENTS TO THE APPROVED PROGRAMME Amendments (revisions) to the approved programme must be made regularly to reflect changes in the manufacturer -/ authorities demands, but also recommendations, modifications and company service experience. Revisions will be made and send to SCAA for approval, if changes in the procedures is or are necessarily. At least one of the following criteria below will state an revision. Pos: Criteria: 1 Additions of tasks. 2 Deletions of tasks. 3 Modifications to tasks. 4 Changes in tasks frequencies. 5 Changes to the list of aircraft subject to the maintenance program. Amendments are prepared by the operators maintenance manager, who then sends the following to SCAA: Pos: 1 The proposed revision of the operators maintenance program.

2 Justification to every change, such as:

a. amendments to source documents. b. modifications and repairs. c. data arising from the monitoring of the maintenance program.

If the revision are approved, SCAA will stamp and sign the programme list of effective pages and then send the page of effective list back to the operator. Until the Authority has approved the amendment, the previously approved revision must be used.

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-8 1.8 PERMITTED VARIATIONS TO MAINTENANCE PERIODS The operator may only vary the periods prescribed by the programme with the approval of SCAA. A permitted variation should not be understood to be a maintenance planning tool, but as an exceptional means to allow the operator to fly for a limited period of time until the required maintenance is performed. Acceptable reasons for requesting a permitted variation may include unforeseen workload peak in the maintenance organisation, so that it is not physically possible to perform the required maintenance on time.

The maximum variation of a prescribed period is indicated below: Items controlled by: Operating limits: Maximum variations Flights hours: 5000 flying hours or less: 10% Flights hours: More than 5000 flying hours: 500 flying hours Calendar time: 1 year or less: 10% or 1 month whichever is the

lesser Calendar time: More than 1 year, but not

exceeding 3 years: 2 months

Calendar time: More than 3 years: 3 months Flight Cycle: 5000 cycles or less 5 % Note 2. Flight Cycle: 5000 cycles or more 250 cycles Note 2. Note 1: For items controlled by more than one limit, the more restrictive limit shall be applied. Note 2: Maximum variations level is in accordance with JAA-Leflet 26. 1.8.1 Restrictions in permitted variations The operator is NOT allowed to accept variations from the aircraft maintenance programs procedures as described below. Pos: 1 Life limitations 2 Airworthiness directives 3 Maintenance Program tasks which have been classified as mandatory by the TC-holder

or by the Authority.

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-9 1.8 PERMITTED VARIATIONS TO MAINTENANCE PERIODS, continues 1.8.2 Application of aircraft information the local authority, SCAA Pos: Information: 1 Aircraft identifikation 2 Justification of the need for such a variation 3 Proposed extension 4 Current inspection status of the aircraft 5 List of aircraft deferred defects which are affected by the variation 6 Confirmation that continued compliance with mandatory life limitation is not affected

by the variation, and where deemed necessary by the Authority, updated list of AD`s, life limited parts, etc.

7 Compensation tasks (i. e. additional maintenance tasks undertaken to be performed before the new proposed limit)

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-10 1.9 PERIODIC REVIEW OF MAINTENANCE PROGRAMME CONTENTS The Operators Maintenance Manager is responsible for reviewing the maintenance programme at regular basis. Upon receipt of revisions of the technical publications, the Maintenance Manager shall check whether these revisions affects the maintenance program. Apart from these revisions, the operators Maintenance Manager and/or staff from the Operators Maintenance Department, shall review the maintenance programme annually for continued validity in the light of operating experience.

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 1-11 1.10 AIRWORTHINESS DIRECTIVES INCORPORATED IN DAILY AND

PERIODIC INSPECTIONS The following recurrent airworthiness directives are applicable to the aircraft, but the inspection intervals do not coincide within the Phase-Inspections 1 to 4. Therefore, those airworthiness directives are followed up individually. The technical department of Sample Fleet controlled those items in two ways:

1. By using a hard copy following up system. The binder-/system includes an AD-index list and a hard copy of all existing AD`s on the aircraft type, both AD`s which are applicably, and AD`s which are not. There is also a chapter in the binder which tells if the AD`s are incorporated in the companies computerized follow-up system.

2. Sample Fleet is using on behalf of Luleå Flygteknik the computerized system “CAMS”

( Computerized Aircraft maintenance System ), for follow-up of all scheduled and unscheduled items.

1.11.1 Example of repetitive AD`s incorporated in the computerized follow up system AD No: SB No: Description: Inspection interval: 89.19.04R1 2040R3 Wing Skins 600 hrs / 18 months 93.25.07 2472R3 Aft Fuselage Stringers 600 hrs

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 2-1 2 MAINTENANCE DETAILS - SE-XXX

2.1 General Chapter two contains following information about: Pos: 1 Inspections 2 Component overhaul 3 Mandatory replacement schedules for the aircraft 2.1.1 Documentations The inspections, overhauls, life limits, etc outlined below in 2.2 to 2.6, should contain a reference to a document issued by the TC-holder or the Authority and the revision status (date) of this document unless the item has been introduced by the operator.

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 2-2 2.2 Daily inspection Daily inspection shall be accomplished prior to the first flight of each day. This inspection consists of visual examinations and functional checks to determine that the aircraft is completely operational and ready for safe flight. This inspection can be performed by a pilot, after he/she has received proper training and has been certified by the operators maintenance manager. The inspection shall be performed in accordance with the Flight Manual.

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 2-3 2.3 SCHEDULED INSPECTION PROGRAM A complete inspection cycle is 800 hours or 24 months. The inspection cycle is divided into four phases and each inspection cycle is done at 200 hours with each consecutive phase 200 hours after the previous phase. The Phase 1, 2, 3 and 4 inspections provide a thorough inspection of specific components and systems and occur at 200-hour intervals. A complete inspection cycle is as follows:

Scheduled Inspections: Interval: Calendar time: Chapter: Phase 1 200 hrs 24 MOS 3 Phase 2 400 hrs 24 MOS 4 Phase 3 600 hrs 24 MOS 5 Phase 4 800 hrs 24 MOS 6 2.3.1 Program Regulations

Pos: Detail Regulation: 1 A complete scheduled inspection ( or all phase 1, 2, 3, and 4 inspections ) must be

accomplished within a 24-calendar-month period. Any part of the inspection which has not been accomplished will be become due immediately. Completion of the phase 1, 2, 3 and 4 inspections shall be considered as a complete inspection.

2 The inspections program requires that no aircraft exceed 12 months without completing at least one phase inspection.

3 Should an aircraft exceed the limitations of the companies inspection program, the aircraft must accomplish all phase 1, 2, 3 and 4 inspections, or a complete inspection, to re-establish the aircraft’s inspection cycle.

2.3.2 Acceptable deviations from the schedule inspection program Pos: Deviation Tolerance: Max. deviations: 1 The Operator Authorizes the following inspection interval

tolerances for phase inspections +/- 20 hours

2.3.3 Periodic Inspections on Raisbeck - Systems installed on the aircraft

Scheduled Inspections: Interval: Chapter: Quiet Turbofan Propeller 200 hrs 8 Ram Air Recovery System 200 hrs 8 Enhanced Performance Leading Edges System 200 hrs 8

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A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 2-4 2.3 SCHEDULED INSPECTION PROGRAM, continue 2.3.4 Acceptable deviations from the schedule inspection program of the Raisbeck - System Pos: Deviation Tolerance: Max. deviations: 1 The Operator Authorizes the following inspection interval

tolerances for the periodic inspections. +/- 20 hours

2.4 SPECIAL INSPECTIONS This section consists of components that are subject to a thorough inspection based on calendar time, operating hours or cycles which do not coincide with the intervals established by the scheduled inspection program. Sample Aircraft Special inspections

Inspection Interval Chapter: Hard Time Components /Special Inspection

Various inspection intervals 7

2.4.1 Limitations Pos: Nomenclature: Tolerance: 1 Calendar date limited items +/- 12 days per 12 calendar

months is allowed 2 Flight hours limited items +/- 10 % is allowed 3 Flight cycle limited items +/- 10 % is allowed 2.4.2 Recurrent AD-inspections Referring to: Operators Maintenance Program, MP-200, 1.11 and 1.11.1 Note: Inspection intervals for Airworthiness Directives ( AD`s ) is not allowed to be exceeded.

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 2-5 2.4 SPECIAL INSPECTIONS, continue 2.4.3 Requirement in accordance with the National Requirements ATA: Component: Action: Interval: Ref:

34.00 Altimeter Biannual inspection 24 months BCL-M 4-3 34.00 Airspeed indicator Biannual inspection 24 months BCL-M 4-3 34.20 Compass Compass Swing 12 months BCL-M 4-3 26.20 Fire Extinguisher - Fwd Pressure check 12 months 26.20 Fire Extinguisher - Aft Pressure check 12 months 25.60 First aid kit Check contents 12 months 25.60 Life vests Functional check 12 months 08.00 Aircraft Weighing 48 months JAR-OPS 1 2.5 OVERHAUL AND LIFE LIMITS ON AIRCRAFT Structural limitations

Component: Life limit: Reference: Cabin Door Forward and Aft Side Latches (or bayonets) (4) Safelife

5000 cycles

Cabin Door Upper Latch Hooks (2) and Attaching Hardware

10000 cycles

Wing and Associated Structure Fatigue Safelife 30000 hoursHorizontal and Vertical Stabilizer 45000 hoursWindshield Frame Screws 10000

cycles All Wing Attach Bolts, Nuts and Barrel Nut Assemblies – Steel Components

6 years

All Wing Attach Bolts, Nuts and Barrel Nut Assemblies – Inconel Components

15 years

AFM Revision January

2002. Section II - Limitations

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 2-6 2.5 OVERHAUL AND LIFE LIMITS ON AIRCRAFT, continue 2.5.1 Additional overhaul and life limits Overhaul or replacement must be performed no later than period prescribed. Items NOT listed are to be overhauled or replaced “On condition”. If “On condition” items are worn, inoperative, inaccurate, intermittent and are not repairable through normal maintenance practices, they must be overhauled or replaced.

ATA

Component:

Action:

TBO:

Ref:

32.30 Actuators (Mechanical) Overhaul 7500 cycles Chapter 32 32.30 Landing Gear Motor (Mechanical) Overhaul 8000 cycles / 6 years Chapter 32

32.40 Brake System Hoses (Only hoses exposed in wheel well)

Replace 5 years Chapter 32

25.60 ELT Replace battery Battery due date Chapter 25 72.00 Engine Oil Filter Replace 1000 hours Chapter 79

71.00 Flammable-Liquid-Carrying Hoses (Raytheon Aircraft supplied hoses only) Replace 5 years Chapter 71

61.10 Propeller Overhaul 4000 hrs / 6 years Hartzell SL 61M 35.00 Passenger Oxygen Shutoff Valve Replace o-rings 24 months Chapter 35 37.00 Instrument Air Filter Replace 600 hours Chapter 37

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 2-7 2.6 ENGINE LIFE LIMIT PARTS Note: Pos: Requirements: In accordance with: 1 Overhauls, Hot Section Inspection and replacement of

life limited components are to be: Pratt & Whitney SB 3002 and 3003.

2.6.1 Engine Hard Time Components ATA Part No. Component Action Interval Ref 72.00 PT6A-41 Engine Overhaul 3600 hrs basic,

Note 1 SB 3003

72.00 PT6A-41 Engine HIS 1800 hrs SB 3003 61.20 Propeller

Synchrophaser Overhaul Engine TBO Woodward

SB33580A 61.20 8210-007E Propeller Governor Overhaul Engine TBO +

500 hrs SB 3003

73.10 10585E Oil-To-Fuel Heater Overhaul Engine TBO + 500 hrs

SB 3003

73.10 025323-300-03

Fuel Pump Overhaul Engine TBO + 500 hrs

SB 3003

73.10 3244801-1 Flow Divider & Dump Valve

Overhaul Engine TBO + 500 hrs

SB 3003

73.10 3029268 P3 Air Filter Replace 1000 hrs MM 73-10-07 73.10 3244707-7 Torque Limiter Overhaul Engine TBO +

500 hrs SB 3003

73.20 3244755-22 Fuel Control Unit Overhaul Engine TBO + 500 hrs

SB 3003

75.30 3100922-05 Bleed Valve HP Overhaul Engine TBO + 500 hrs

SB 3003

75.30 3100923-02 Bleed Valve LP Overhaul Engine TBO + 500 hrs

SB 3003

79.20 3024996 Thermostat Housing Assy

Overhaul Engine TBO + 500 hrs

SB 3003

Note 1: TBO Extension is permitted in accordance with P&W SB 3003, §3.C. Transfer of existing TBO Extension Programme (7500 hours TBO) from previous operator is allowed, using a specific formula.

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A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 2-8 2.6 ENGINE LIFE LIMIT PARTS, continue 2.6.2 Life Limitations on Engines Static and Rotating Parts ATA: Part

No: Component: Action: Interval: ACF: FCF: Ref:

72 3021911 Hub, Compressor (1st Stage)

Life 20000 cycl

3 1 P&W SB 3002

72 Rotor, Compressor Life 20000 cycl

3 1 P&W SB 3002

72 3023112 Disk, Compressor (2nd Stage)

Life 20000 cycl

3 1 P&W SB 3002

72 3023113 Disk, Compressor (3rd

Stage) Life 20000

cycl 3 1 P&W SB

3002 72 3017463 Impeller, Centrifugal Life 20000

cycl 3 1 P&W SB

3002 72 3024711 Disk, Compressor

Turbine Life 20000

cycl 10 1 P&W SB

3002 72 3029312 Disk, Power Turbine

(1st Stage) Life 30000

cycl 10 1 P&W SB

3002 72 3029313 Disk, Power Turbine

(2nd Stage) Life 30000

cycl 10 1 P&W SB

3002 ACF = Abbreviated Cycle Factor FCF = Flight Count Factor Component life is calculated in accordance with the following formula: Accumulated Total Cycles = [No. of Starts + ((No. of Flights – No. of Starts)/ Abbreviated Cycle Factor)] x Flight Count Factor Example: Abbreviated Cycle Factor = 10 No. of Starts = 3000 No. of Flights = 9000 Flight Count Factor = 1 [3000 + ((9000 – 3000)/ 10)] x 1 = [3000 + 600] x 1 = 3600

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-1 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

NKF W/O:

SE- XXX

Date:

A/C TT: A/C TOTCYC:

Phase 1 inspection in accordance with RAYTHEON AIRCRAFT SCHEDULED INSPECTION PROGRAM, PHASE 1 INSPECTION shall be in use for documentation of the scope of work. Ref: MM 5-20-00.

Raisbeck Systems 200-hour inspection in accordance with Appendix 6 performed. Certifies that the work specified except as otherwise specified was carried out in accordance with PART – 145.50, and in respect to that work the aircraft is considered ready for release to service. CRS Signature:

CRS Approval:

Pos:

Action:

Sign

SECTION / AREA / DESCRIPTION: ATA Ref: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

A. Nose Section ( there are no inspections during phase 1 )

N/A N/A N/A

B. NOSE AVIONIC COMPARTMENT 1. VACCUM REGULATOR VALVE FILTER – INSPECT FOR BLOCKAGE

12-20-00 37-00-00

C. NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT

AC.43.13.1B/2A

D. NOSE GEAR 1. WHEEL a) INSPECT WHEEL FOR WEAR, DAMAGE and CORROSION b) INSPECT WHEEL BEARINGS and RACES for WEAR, PITTING, CRACKS ,DISCOLORATION, RUST or other indications of damage.

32-40-00 CMM

2. TIRE a) INSPECT FOR WEAR AND DETEIORATION b) CHECK FOR CORRECT INFLATION

12-20-00 CMM

3. SHIMMY DAMPER – INSPECT FOR LEAKS, SECURITY AND ATTACHEMENT

12-20-00 32-20-00

4. NOSE GEAR DRAG BRACE STOP LUGS- INSPECT FOR CRACK, DAMAGE OR DIST.

12-20-00 32-20-00

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-2 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: D. NOSE GEAR, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

5. NOSE GEAR STEERING STOP – INSPECT STEERING STOP FOR DAMAGE OR DISTORSION

12-20-00 32-20-00

6. LANDING AND TAXI LIGHTS – INSPECT FOR BROKEN LENSES OR BULBS

33-40-00

7. STEERING LINKAGE – INSPECT NOSE GEAR STEERING MECHANISM AND ATTACHED HARDWARE FOR WEAR, DAMAGE AND CORROSION

32-50-00

8. NOSE LANDING GEAR STRUT – CHECK STRUT FOR LEAKAGE AND CORRECT EXTENSION

12-20-00 32-20-00

9. NOSE GEAR RETRACT AND EMERGENCY EXTENSION CHAINS (Mechanical Gear) - INSPECT, CLEAN AND LUBRICATE CHAINS

32-30-00

10. ELECTRICAL WIRING AND EQUIPMENT – INSPECT FOR CHAFING, DAMAGE, PROPER ROUTING OF WIRE BUNDLES AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

E. PILOTS COMPARTMENT 1. RETURN AIR INLET FILTERS – INSPECT FILTERS IN RETURN AIR INLET OF THE FORWARD VENT BLOWER

21-50-00

2. WINDSHIELD a) INSPECT WINDSHIELD FOR CRACKS AND VISIBILITY IMPAIRMENT b) INSPECT WINDSHIELD WEATHER SEAL (Silicone) FOR DEBONDING, CRACKS OR WEAR c) INSPECT WINDSHIELD WEATHER HUMP SEAL (Polysulfide) FOR DEBONDING, CRACKS OR WEAR d) INSPECT WINDSHIELD ATTACHEMENT SCREWS FOR 20-INCH-POUNDS OF TORQUE

56-10-00

3. WINDOWS – INSPECT EXTERIOR SURFACE OF COCKPIT SIDE WINDOWS FOR DEEP SCRATCHES, CRACKS, CHIPS OR EXCESS CRAZING OR OTHER DAMAGE

56-15-00

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A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-3 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: E. PILOTS COMPARTMENT, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. ALTERNATE AIR VALVE – DRAIN OFF ALL MOISTURE

34-00-00

5. SEAT TRACKS – INSPECT SEAT TRACKS FOR DAMAGE AND WEAR

25-10-00

6. PORTABLE FIRE EXTINGUISHER – INSPECT THE BOTTLE FOR SIGNS OF DAMAGE AND MOUNT FOR SECURITY OF ATTACHMENT

26 CMM

7. SEATS, SEAT BELTS AND SHOULDER HARNESSES – INSPECT SEATS, SEAT BELTS AND SHOULDER HARNESSES FOR DETERIORATION

25-10-00

8. BRAKE FLUID RESERVOIR PRESSURE EQUALIZATION ORIFICE – INSPECT FOR BLOCKAGE

32-40-00

9. UPHOLSTERY PANELS – INSPECT FOR SECURITY OF ATTACHMENT

N/A

10. FLIGHT CONTROL CABLE TENSION – CHECK AILERON CONTROL CABLE TENSION

27

11. ALTITUDE WARNING SWITCH – PERFORM THE CABIN ALTITUDE WARNING PRESSURE SWITCH TEST

21-20-00

F. CABIN SECTION 1. WINDOWS – INSPECT EXTERIOR SURFACE OF WINDOWS FOR DEEP SCRATCHES, CRACKS, CHIPS AND EXCESSIVE CRAZING OR OTHER DAMAGE

56-15-00

2. ROTATING OR FLASHING BEACON – INSPECT FOR CRACKED OR BROKEN LENSES

33-40-00

3. ACCESS DOORS – INSPECT FOR FIT AND ATTACHMENT

N/A

4. OUTFLOW AND SAFETY VALVES – DRAIN CONTROL LINE

12-20-00

5. SEAT TRACKS – INSPECT SEAT TRACKS FOR DAMAGE AND WEAR

25-20-00

6. AFT EVAPORATOR FILTER – INSPECT AFT EVAPORATOR FILTER

21-50-00

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Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-4 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: F. CABIN SECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

7. SEATS, SEAT BELTS AND SHOULDER HARNESSES a) INSPECT SEATS, SEAT BELTS AND SHOULDER HARNESSES FOR DETERIORATION OR MISSING COMPONENTS b) INSPECT SHOULDER HARNESS ATTACHMENT POST FOR CRACKED, WORN, BRITTLE OR MISSING GROMMET

25-20-00

8. OXYGEN SYSTEM a) INSPECT OXYGEN SYSTEM INSTALLATION FOR DAMAGE AND SECURITY OF ATTACHMENT b) OXYGEN SYSTEM FUNCTIONAL TEST – PERFORM TEST

35-00-00

9. TOILET – INSPECT FOR SPILLAGE AND LEAKAGE BELOW THE TOILET

38-30-00

10. CABIN ENTRANCE DOOR (BB-582) a) INSPECT THE DOOR SEAL FOR CUTS, ABRASIONS AND SECURITY OF ATTACHMENT b) INSPECT THE CABIN DOOR SUPPORT CABLES FOR WEAR, DAMAGE AND SECURITY OF ATTACHMENT

52-10-00

11. CABIN CARGO DOOR AND CABIN ENTRANCE DOOR

N/A for BB-582 due to s/n

N/A N/A

12. LANDING GEAR HYDRAULIC LINES – INSPECT FOR LEAKS, DAMAGE AND SECURITY OF ATTACHMENT

N/A

13. PORTABLE FIRE EXTINGUISHER – INSPECT BOTTLE FOR DAMAGE AND SECURITY

26 CMM

G. REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAINS – INSPECT REAR FUSELAGE DRAINS

53-10-00

2. ELT - BATTERY a) INSPECT FOR LEAKAGE, CORROSION OR LOOSE LEADS b) DETERMINE REMAINING USEFUL LIFE

25-60-00

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Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: G. REAR FUSELAGE AND EMPENNAGE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

3. NAVIGATION LIGHTS AND ROTATING OR FLASHING BEACONS – INSPECT FOR BROKEN OR CRACKED LENSES

33-40-00

4. ACCESS DOORS – INSPECT FOR FIT AND SECURITY OF ATTACHMENT

N/A

5. VENTRAL FIN DRAIN HOLES – INSPECT THE DRAIN HOLES IN THE BOTTOM OF THE VENTRAL FIN FOR OBSTRUCTIONS

53-10-00

6. DEICER BOOTS – INSPECT FOR DETERI- ORATION, DAMAGE AND ATTACHMENT

N/A

7. RUDDER AND TRIM TAB DRAIN HOLES – INSPECT THE DRAIN HOLES FOR OBSTRUCTIONS

N/A

8. STATIC WICKS – INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT

23-60-00

9. RUDDER BOOST FILTER (With Autopilot) – REPLACE FILTER

27-21-00

10. FLIGHT CONTROL CABLE TENSION – INSPECT ELEVATOR, ELEVATOR TAB, RUDDER AND RUDDER TAB CONTROL CABLE TENSIONS

27

H. LEFT-HAND OUTBOARD WING 1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - DETERMINE THAT THE DRAIN HOLES ARE OPEN IN THE WING CENTER SECTION AND OUTBOARD WING UPPER ATTACHMENT FITTINGS

57-00-00

3. LIGHTS a) INSPECT THE NAVIGATION AND RECOGNITION LIGHTS FOR BROKEN OR CRACKED LENSES b) INSPECT THE STROBE LIGHT FOR BROKEN OR CRACKED LENSES

33-40-00

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-6 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: H. LEFT-HAND OUTBOARD WING, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE WING FOR LEAKAGE

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT EXTERIOR OPENINGS OF VENTS FOR OBSTRUCTIONS

28-10-00

5. INTEGRAL FUEL TANK – INSPECT THE EXTERIOR SURFACE OF THE INTEGRAL TANK ACCESS DOORS FOR LEAKS

28-10-00

6. DEICER BOOTS – INSPECT EXTERIOR SURFACE FOR DETERIORATION, DAMAGE AND ATTACHMENT

30-10-00

7. ACCESS DOORS (INSPECTION PANELS) – INSPECT FOR FIT AND ATTACHMENT

6-50-00

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

9. AILERON AND TRIM TAB . CHECK TRIM TAB FREE PLAY

27-10-00

10. LEFT HAND OUTBOARD WING AREA – INSPECT SKIN, STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

11. AILERON AND OUTBOARD FLAP – INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION. IF DAMAGE OR CORROSION IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA.

AC.43.13-1B/2A

12. ELECTRICAL WIRING AND EQUIPMENT – INSPECT FOR CHAFING, DAMAGE, PROPER ROUTING OF WIRE BUNDLES AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-7 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: H. LEFT-HAND OUTBOARD WING, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

13. FLIGHT CONTROL COMPONENTS, CABLES AND PULLEYS a) INSPECT CONTROL SYSTEM COMPONENTS (PUSHRODS, TURNBUCKLES, END FITTINGS CASTINGS. Etc.) FOR BULGES, SPLITS, BENDS OR CRACKS WHICH ARE CONDITIONS FOR REPLACEMENT b) INSPECT CONTROL SYSTEM CABLES, PULLEYS, AND ASSOCIATED EQUIPMENT FOR WEAR, CRACKS, BREAKS, ATTACHMENT ALIGNMENT, CLEARANCE AND PROPER OPERATION. REPLACE CABLES THAT HAVE MORE THAN THREE BROKEN WIRES IN ANY GIVEN THREE-FOT CABLE LENGTH OR HAVE EVIDENCE OF CORROSION c) INSPECT AILERON CONTROL CABLE TENSION d) INSPECT AILERON TAB CONTROL CABLE TENSION

27

14. FLAPS AND ACTUATORS a) INSPECT FLAP 90 deg. DRIVE, CABLE AND ACTUATOR FOR ATTACHMENT b) INSPECT FLAP TRACKS FOR WEAR c) PERFORM FLAP SAFETY MECHANISM FUNCTIONAL TEST

27-50-00

15. FUEL PLUMBING – INSPECT FOR LEAKS CHAFING OR DAMAGE AND ATTACHMENT

28

16. HINGED ACCESS DOORS ABOVE DOORS NO. 13 AND 14 – INSPECT FOR CRACKS OR DAMAGE TO HINGE AND FASTENERS

6-50-00

I. LEFT HAND WING CENTER SECTION 1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE CENTER SECTION FOR LEAKS

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT THE EXTERIOR OPENINGS OF THE VENTS FOR OBSTRUCTIONS

28-10-00

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-8 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: I. LEFT HAND WING CENTER SECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

3. ACCESS DOORS (INSPECTION PANELS) - INSPECT FOR FIT AND ATTACHMENT

6-50-00

4. ENGINE FIRE EXTINGUISHER a) INSPECT PLUMBING FOR SECURITY OF ATTACHMENT b) CHECK FIRE BOTTLE PRESSURE GAUGE

26-20-00

5. FUEL PUMPS – INSPECT THE PUMPS FOR LEAKS AND SECURITY OF ATTACHMENT

28-20-00

6. LANDING GEAR HYDRAULIC POWER PACK AND MOTOR (if installed) a)INSPECT THE HYDRAULIC POWER GEAR-UP AND GEAR-DOWN PORT SCREENS b) INSPECT THE LANDING GEAR HYDRAULIC SYSTEM BLEED AIR PRESSURE OVERBOARD RELIEF ORIFICE SCREEN FOR BLOCKAGE c) INSPECT THE HYDRAULIC POWER PACK FILL RESERVOIR SCREEN d) INSPECT ALL PLUMBING ATTACH FOR LEAKS AND SECURITY OF ATTACHMENT

32-31-00

7. LEFT-HAND WING CENTER SECTION AREA – INSPECT SKIN, STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA

57 SIRM AC.43.13-1B/2A

8. FLAPS AND ACTUATORS a) INSPECT FLAP 90 deg DRIVE, CABLE AND ACTUATOR FOR ATTACHMENT b) INSPECT FLAP TRACKS FOR WEAR

27-50-00

9. LEADING EDGE AND NACELLE FUEL PLUMBING – INSPECT FUEL PLUMBING FOR LEAKS, DAMAGE AND SECURITY OF ATTACHMENT

28-20-00

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-9 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: I. LEFT HAND WING CENTER SECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

10. FLIGHT CONTROL COMPONENTS, CABLES AND PULLEYS a) INSPECT CONTROL SYSTEM COMPONENTS (PUSHRODS, TURNBUCKLES, END FITTINGS CASTINGS, etc.) FOR BULGES, SPLITS, BENDS OR CRACKS WHICH ARE CONDITIONS FOR REPLACEMENT b) INSPECT CONTROL CABLES, PULLEYS AND ASSOCIATED EQUIPMENT FOR WEAR, CRACKS, BREAKS, ATTACHMENT, ALIGNMENT, CLEARANCE AND PROPER OPERATION. REPLACE CABLES THAT HAVE MORE THAN THREE BROKEN WIRES IN ANY GIVEN THREE-FOOT CABLE LENGTH OR HAVE EVIDENCE OF CORROSION

27

11. ELECTRICAL WIRING AND EQUIPMENT – INSPECT FOR CHAFING, DAMAGE AND PROPER ROUTING OF WIRE BUNDLES AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

12. BLEED AIR BYPASS VALVE – CHECK BLEED AIR VALVE AT HEAT EXCHANGER FOR OPERATION OF LINKAGE TO BUTTERFLY VALVE AND OPERATION OF ACTUATOR MOTOR

21-40-00

J. LEFT-HAND MAIN LANDING GEAR AREA 1. WHEELS a) INSPECT WHEELS FOR WEAR, DAMAGE AND CORROSION

N/A

b) INSPECT WHEEL BEARINGS AND RACES FOR WEAR, PITTING, CRACKS, DISCOLORATION, RUST OR OTHER INDICATIONS OF DAMAGE

CMM

2. BRAKES – INSPECT BRAKE DISCS, LININGS AND PLUMBING FOR WEAR DAMAGE, LEAKS, CORROSION AND SECURITY OF ALL COMPONENTS

32-40-00 CMM

SAMPLE FLEET

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-10 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: J. LEFT-HAND MAIN LANDING GEAR AREA, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

3. BRAKE DEICING ( if installed) a) INSPECT MANIFOLD FOR BLOCKED ORIFICES b) INSPECT EXTERIOR OF LINES, HOSES AND CONNECTIONS FOR LEAKAGE AND ATTACHMENT

30-21-00

4. TIRES – INSPECT TIRES FOR WEAR, DETERIORATION AND CORRECT INFLATION

12-20-00 CMM

5. LEFT-HAND MAIN LANDING GEAR STRUT – CHECK STRUT FOR LEAKS AND PROPER EXTENSION

12-20-00

6. ELECTRICAL WIRING AND EQUIPMENT – INSPECT EXPOSED WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND PROPER ROUTING AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

7. MAIN GEAR ACTUATOR a) ACTUATOR (Mechanical Gear) 1. INSPECT ACTUATOR SUPPORT BRACKETS FOR VISIBLE DAMAGE, WEAR AND LOOSE AND MISSING FASTENERS 2. INSPECT BRACKETS FOR LOOSE OR MISSING RIVETS 3. INSPECT ACTUATOR FOR LEAKAGE OF INTERNAL LUBRICANT

32-30-00

8. DRAG BRACE a) INSPECT FOR SECURITY OF ATTACH FITTINGS

32-10-00

b) INSPECT DOWNLOCK BOLTS FOR PROPER TORQUE ( finger-tight and safety-wired)

CMM

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-11 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: J. LEFT-HAND MAIN LANDING GEAR AREA, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

9. LEFT-HAND MAIN LANDING GEAR AREA – INSPECT WHEEL AND GEAR DOOR STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

K. LEFT-HAND ENGINE 1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FIREWALL FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

4. PROPELLERS – INSPECT FOR DAMAGE AND ATTACHMENT (spinner removal required)

61-10-00 61-11-00 61-12-00

5. ENGINE OIL FILTER – INSPECT FOR METAL PARTICLES

P&W

6. LEFT-HAND ENGINE – INSPECT ALL SYSTEMS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. CHECK ALL TUBES AND HOSES FOR GENERAL CONDITION, LEAKS AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-12 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION:

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

L. RIGHT-HAND OUTBOARD WING 1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - DETERMINE THAT THE DRAIN HOLES ARE OPEN IN THE WING CENTER SECTION AND OUTBOARD WING UPPER ATTACHMENT FITTINGS

57-00-00

3. LIGHTS a) INSPECT THE NAVIGATION AND RECOGNITION LIGHTS FOR BROKEN OR CRACKED LENSES b) INSPECT THE STROBE LIGHT FOR BROKEN OR CRACKED LENSES

33-40-00

4. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE WING FOR LEAKAGE

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT EXTERIOR OPENINGS OF VENTS FOR OBSTRUCTIONS

28-10-00

5. INTEGRAL FUEL TANK – INSPECT THE EXTERIOR SURFACE OF THE INTEGRAL TANK ACCESS DOORS FOR LEAKS

28-10-00

6. DEICER BOOTS – INSPECT EXTERIOR SURFACE FOR DETERIORATION, DAMAGE AND ATTACHMENT

30-10-00

7. ACCESS DOORS (INSPECTION PANELS) – INSPECT FOR FIT AND ATTACHMENT

6-50-00

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

9. AILERON AND TRIM TAB . CHECK TRIM TAB FREE PLAY

27-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-13 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: L. RIGHT-HAND OUTBOARD WING,continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

10. LEFT HAND OUTBOARD WING AREA – INSPECT SKIN, STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

11. AILERON AND OUTBOARD FLAP – INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION. IF DAMAGE OR CORROSION IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA.

AC.43.13-1B/2A

12. ELECTRICAL WIRING AND EQUIPMENT – INSPECT FOR CHAFING, DAMAGE, PROPER ROUTING OF WIRE BUNDLES AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

13. FLIGHT CONTROL COMPONENTS, CABLES AND PULLEYS a) INSPECT CONTROL SYSTEM COMPONENTS (PUSHRODS, TURNBUCKLES, END FITTINGS CASTINGS. Etc.) FOR BULGES, SPLITS, BENDS OR CRACKS WHICH ARE CONDITIONS FOR REPLACEMENT b) INSPECT CONTROL SYSTEM CABLES, PULLEYS, AND ASSOCIATED EQUIPMENT FOR WEAR, CRACKS, BREAKS, ATTACHMENT ALIGNMENT, CLEARANCE AND PROPER OPERATION. REPLACE CABLES THAT HAVE MORE THAN THREE BROKEN WIRES IN ANY GIVEN THREE-FOT CABLE LENGTH OR HAVE EVIDENCE OF CORROSION c) INSPECT AILERON CONTROL CABLE TENSION

27

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-14 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: L. RIGHT-HAND OUTBOARD WING,continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

14. FLAPS AND ACTUATORS a) INSPECT FLAP 90 deg. DRIVE, CABLE AND ACTUATOR FOR ATTACHMENT b) INSPECT FLAP TRACKS FOR WEAR c) PERFORM FLAP SAFETY MECHANISM FUNCTIONAL TEST

27-50-00

15. FUEL PLUMBING – INSPECT FOR LEAKS CHAFING OR DAMAGE AND ATTACHMENT

28

16. HINGED ACCESS DOORS ABOVE DOORS NO. 13 AND 14 – INSPECT FOR CRACKS OR DAMAGE TO HINGE AND FASTENERS

6-50-00

M. RIGHT- HAND WING CENTER SECTION 1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE CENTER SECTION FOR LEAKS

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT THE EXTERIOR OPENINGS OF THE VENTS FOR OBSTRUCTIONS

28-10-00

3. ACCESS DOORS (INSPECTION PANELS) - INSPECT FOR FIT AND ATTACHMENT

6-50-00

4. BATTERY a) SERVICE BATTERY AS REQUIRED

12-20-00

b) REMOVE BATTERY AND INSPECT THE BATTERY BOX, CABLES AND VENT TUBES FOR DETERIORATION OR OBSTRUCTIONS c) REMOVE BATTERY AND INSPECT THE BATTERY BOX AND CABLES FOR DETERIORATION OR OBSTRUCTIONS

24-31-00

4. ENGINE FIRE EXTINGHUISER a) INSPECT PLUMBING FOR SECURITY OF ATTACHMENT b) CHECK FIRE BOTTLE PRESSURE GAUGE

26-20-00

5. FUEL PUMPS – INSPECT THE PUMPS FOR LEAKS AND SECURITY OF ATTACHMENT

28-20-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-15 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

M. RIGHT- HAND WING CENTER SECTION continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

7. RIGHT-HAND WING CENTER SECTION AREA - INSPECT SKIN, STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA

57 SIRM AC.43.13-1B/2A

8. FLAPS AND ACTUATORS a) INSPECT FLAP 90 deg DRIVE, CABLE AND ACTUATOR FOR ATTACHMENT b) INSPECT FLAP TRACKS FOR WEAR

27-50-00

9. LEADING EDGE AND NACELLE FUEL PLUMBING – INSPECT FUEL PLUMBING FOR LEAKS, DAMAGE AND SECURITY OF ATTACHMENT

28-20-00

10. FLIGHT CONTROL COMPONENTS, CABLES AND PULLEYS a) INSPECT CONTROL SYSTEM COMPONENTS (PUSHRODS, TURNBUCKLES, END FITTINGS CASTINGS, etc.) FOR BULGES, SPLITS, BENDS OR CRACKS WHICH ARE CONDITIONS FOR REPLACEMENT b) INSPECT CONTROL CABLES, PULLEYS AND ASSOCIATED EQUIPMENT FOR WEAR, CRACKS, BREAKS, ATTACHMENT, ALIGNMENT, CLEARANCE AND PROPER OPERATION. REPLACE CABLES THAT HAVE MORE THAN THREE BROKEN WIRES IN ANY GIVEN THREE-FOOT CABLE LENGTH OR HAVE EVIDENCE OF CORROSION

27

11. ELECTRICAL WIRING AND EQUIPMENT – INSPECT FOR CHAFING, DAMAGE AND PROPER ROUTING OF WIRE BUNDLES AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

12. BLEED AIR BYPASS VALVE – CHECK BLEED AIR VALVE AT HEAT EXCHANGER FOR OPERATION OF LINKAGE TO BUTTERFLY VALVE AND OPERATION OF ACTUATOR MOTOR

21-40-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-16 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: M. RIGHT- HAND WING CENTER SECTION continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

13. REFRIGERANT LINES AND PRESSURE SWITCHES – INSPECT LINES AND SWITCHES FOR LEAKAGE, DAMAGE AND ATTACHMENT

21.50.00

N. RIGHT-HAND MAIN LANDING GEAR AREA 1. WHEELS a) INSPECT WHEELS FOR WEAR, DAMAGE AND CORROSION

N/A

b) INSPECT WHEEL BEARINGS AND RACES FOR WEAR, PITTING, CRACKS, DISCOLORATION, RUST OR OTHER INDICATIONS OF DAMAGE

CMM

2. BRAKES – INSPECT BRAKE DISCS, LININGS AND PLUMBING FOR WEAR DAMAGE, LEAKS, CORROSION AND SECURITY OF ALL COMPONENTS

32-40-00 CMM

3. BRAKE DEICING ( if installed) a) INSPECT MANIFOLD FOR BLOCKED ORIFICES b) INSPECT EXTERIOR OF LINES, HOSES AND CONNECTIONS FOR LEAKAGE AND ATTACHMENT

30-21-00

4. TIRES – INSPECT TIRES FOR WEAR, DETERIORATION AND CORRECT INFLATION

12-20-00 CMM

5. LEFT-HAND MAIN LANDING GEAR STRUT – CHECK STRUT FOR LEAKS AND PROPER EXTENSION

12-20-00

6. ELECTRICAL WIRING AND EQUIPMENT – INSPECT EXPOSED WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND PROPER ROUTING AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-17 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: N. RIGHT-HAND MAIN LANDING GEAR AREA continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

7. MAIN GEAR ACTUATOR a) ACTUATOR (Mechanical Gear) 1. INSPECT ACTUATOR SUPPORT BRACKETS FOR VISIBLE DAMAGE, WEAR AND LOOSE AND MISSING FASTENERS 2. INSPECT BRACKETS FOR LOOSE OR MISSING RIVETS 3. INSPECT ACTUATOR FOR LEAKAGE OF INTERNAL LUBRICANT

32-30-00

8. DRAG BRACE a) INSPECT FOR SECURITY OF ATTACH FITTINGS

32-10-00

b) INSPECT DOWNLOCK BOLTS FOR PROPER TORQUE ( finger-tight and safety-wired)

CMM

9. RIGHT-HAND MAIN LANDING GEAR AREA – INSPECT WHEEL AND GEAR DOOR STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

O. RIGHT-HAND ENGINE 1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FIREWALL FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-18 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. PROPELLERS – INSPECT FOR DAMAGE AND ATTACHMENT (spinner removal required)

61-10-00 61-11-00 61-12-00

5. ENGINE OIL FILTER – INSPECT FOR METAL PARTICLES

P&W

6. RIGHT-HAND ENGINE – INSPECT ALL SYSTEMS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. CHECK ALL TUBES AND HOSES FOR GENERAL CONDITION, LEAKS AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

P. LANDING GEAR RETRACTION NOTE: Mechanical and Hydraulic Landing Gear Systems – Since battery voltage is not sufficient to properly cycle The landing gear, use only an external power source Capable of delivering and maintaining 28.25 +/- 0.25 Volts throughout the extension and retraction cycles when performing the landing gear retraction inspection.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-19 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: P. LANDING GEAR RETRACTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. RETRACT MECHANISM – CHECK RETRACTION SYSTEM FOR PROPER OPERATION OF ALL COMPONENTS THROUGH AT LEAST TWO COMPLETE CYCLES

32

2. DOORS AND LINKAGE a) CHECK DOOR FOR DAMAGE, OPERATION AND FIT b) CHECK DOOR LINKAGE FOR WEAR, DAMAGE AND RIGGING

32

3. DOWNLOCK INDICATOR SWITCHES a) CHECK FOR SECURITY AND PROPER OPERATION OF SWITCHES b) CLEAN TERMINALS AND CONNECTORS AS REQUIRED c) CHECK WIRING FOR DAMAGE AND SECURITY OF CONNECTION

32-60-00

4. UPLOCK INDICATOR SWITCHES a) CHECK FOR SECURITY AND PROPER OPERATION OF SWITCHES b) CLEAN TERMINALS AND CONNECTORS AS REQUIRED c) CHECK WIRING FOR DAMAGE AND SECURITY OF CONNECTION

32-60-00

5. WARNING HORN – CHECK OPERATION 32-60-00 6. MAIN GEAR DOWNLOCKS – CHECK LOCKING MECHANISM FOR POSITIVE ENGAGEMENT IN EXTENDED POSITION

32

7. SAFETY SWITCH – CHECK FOR PROPER OPERATION

32-60-00

8. ACTUATORS – CHECK FOR NOISE, BINDING AND PROPER RIGGING

32-30-00 32-31-00

9. LIMIT SWITCHES – (Mechanical Gear) a) CHECK FOR CORRECT ADJUSTMENT b) CHECK FOR SECURITY OF ATTACHMENT

32-60-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-20 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: P. LANDING GEAR RETRACTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

10. EMERGENCY EXTENSION (Mechanical Gear) CHECK SYSTEM FOR FREEDOM OF OPERATION AND POSITIVE ENGAGEMENT OF DOWNLOCKS. CAUTION: Do not continue operation after receiving a gear-down indication on all gears. Further movement of the handle could damage the drive mechanism and prevent subsequent electrical gear retraction. The landing gear cannot be retracted manually.

32-30-00

11. NOSE GEAR RETRACT CHAIN (Mechanical Gear) a) INSPECT CHAINS FOR BROKEN LINKS, EXCESSIVE PIN AND LINK WEAR, MISALIGNMENT, RUST, CORROSION AND DIRT b) CHECK SPROCKETS FOR EXCESSIVE WEAR AND HOOK-SHAPED TEETH c) CHECK FOR PROPER CHAIN TENSION d) CHECK NOSE GEAR AND NOSE GEAR LINKAGE CLEARANCE FROM ELECTRICAL WIRES AND OBSTRUCTIONS

32-30-00

12. PLACARDS – CHECK THAT ALL PLACARDS ARE IN PLACE AND ARE LEGIBLE

11-00-00

13. LANDING GEAR RETRACTION – INSPECT ALL LANDING GEAR COMPONENTS AND ATTACHING HARDWARE, STRUCTURE AND HYDRAULIC LINES FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

14. LANDING GEAR MOTOR CONTROLLER (Mechanical Gear) – INSPECT CONTROLLER FOR PITTED OR DAMAGED CONTACTS, REPAIR AS NECESSARY

CMM

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-21 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

NOTE: The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Sample Airsraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual for the engine start and run procedures.

N/A

1. FIREWALL SHUTOFF FUEL VALVES - CHECK FOR PROPER OPERATION

Ref: NOTE

2. CROSSFEED FUEL VALVE – CHECK FOR PROPER OPERATION

Ref: NOTE

3. STANDBY PUMPS – CHECK FOR PROPER OPERATIONS

Ref: NOTE

4. STARTER GENERATOR a) CHECK STARTER FOR OPERATION b) CHECK GENERATOR FOR OUTPUT

Ref: NOTE

5. IGNITION a) CHECK FOR PROPER OPERATION b) CHECK FOR ANNUNCIATOR PANEL LIGHT ILLUMINATION

Ref: NOTE

6. ENGINE OIL – CHECK FOR PROPER PRESSURE AND TEMPERATURE LIMITS

Ref: NOTE

7. FUEL QUANTITY GAGES – CHECK OPERATION

Ref: NOTE

8. INTERSTAGE TURBINE TEMPERATURE – CHECK FOR CORRECT LIMITS ON ENGINE START

Ref: NOTE

9. VACUUM SYSTEM – CHECK FOR CORRECT LIMITS

Ref: NOTE

10. PNEUMATIC PRESSURE GAGE – CHECK FOR CORRECT PRESSURE

Ref: NOTE

11. PNEUMATIC SYSTEM SHUTOFF VALVES – CHECK FOR PROPER OPERATION

Ref: NOTE

12. GYRO INSTRUMENTS – CHECK FOR ERRATIC OR NOISY OPERATION

Ref: NOTE

13. PROPELLERS – PERFORM FLIGHT IDLE TOQUE CHECK

Ref: NOTE

14. AUTOFEATHERING CHECK – Refer to: AUTOFEATHERING SYSTEM OPERATIONAL CHECK

61-21-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-22 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

15. PROPELLER SYNCHROPASER – Refer to: AUTOFEATHER SYSTEM OPERATIONAL CHECK

61-21-00

16. PROPELLER GOVERNOR – CHECK GOVERNOR OPERATION ( Including feathering And reversing)

Ref: NOTE

17. IDLE RPM – CHECK FOR CORRECT RPM ( both high and low rpm)

Ref: NOTE

18 AC INVERTERS – CHECK FOR PROPER OPERATION

Ref: NOTE

19. RUDDER BOOST – CHECK FOR PROPER OPERATION

Ref: NOTE

20. AUTO-IGNITION a) CHECK FOR PROPER OPERATION b) CHECK FOR ANNUNCIATOR PANEL ILLUMINATION

Ref: NOTE

21. PROPELLER DEICER – CHECK FOR PROPER OPERATION AND CYCLING. Refer to chapter 30 of the Beech King Air Series Component Maintenance Manual

N/A

22. ENGINE INTERIAL ANTI-ICER – CHECK FOR PROPER OPERATION AND RIGGING

Ref: NOTE

23. SURFACE DEICE SYSTEM – CHECK FOR PROPER OPERATION AND CYCLING

Ref: NOTE

24. BRAKE DEICE SYSTEM (if installed) – CHECK FOR PROPER OPERATION WITH ENGINES RUNNING

Ref: NOTE

25. ELECTRICAL SYSTEM – PERFORM FUNCTIONAL CHECKS

Ref: NOTE

26. ENVIRONMENTAL SYSTEM – CHECK FOR PROPER OPERATION IN: a) MANUAL HEAT MODE b) MANUAL COOL MODE c) AUTOMATIC MODE

Ref: NOTE

27. REFRIGERANT LEVEL – CHECK FOR PROPER LEVEL

Ref: NOTE

28. AUTOPILOT – CHECK FOR PROPER OPERATION AS OUTLINED BY THE APPLICABLE Sample Aircraft Pilots Operating Handbook or SCAA Approved Airplane Flight Manual Supplement

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-22 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

29. STALL WARNING – CHECK FOR PROPER OPERATION

Ref: NOTE

30. ENGINE FIRE DETECTORS – Perform system test according to instructions found in the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual

N/A

31. ENGINE FIRE EXTINGUISHERS – Perform system test according to instructions found in the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual

N/A

32. PRESSURIZATION SYSTEM – CHECK FOR PROPER OPERATION Refer to the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual and perform system test

N/A

33. AUXILIARY FUEL TRANSFER JET PUMPS – CHECK FOR PROPER OPERATION

Ref: NOTE

34. CONDITION LEVER – CHECK FOR CLEAN SHUTDOWN AT IDLE-CUT-OFF

Ref: NOTE

35. PITOT TUBE – CHECK FOR PROPER HEATING AT THE UNIT AND FOR OBSTRUCTIONS

Ref: NOTE

36. LANDING AND TAXI LIGHTS – CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

37. OUTBOARD WING LIGHTS ( R/H AND L/H) - CHECK OPERATION OF ALL NAVIGATION AND STROBE LIGHTS

Ref: NOTE

38. COCKPIT LIGHTS – CHECK OPERATION OF ALL COCKPIT LIGHTS

Ref: NOTE

39. EFIS COOLING BLOWERS (if installed) – CHECK OPERATION

Ref: NOTE

40. ELECTRIC ELEVATOR TRIM – CHECK FOR PROPER OPERATION

Ref: NOTE

41. ENGINE AND PROPELLER CONTROLS – CHECK FOR FREEDOM OF MOVEMENT FULL TRAVEL AND FRICTION-LOCK OPERATION

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-23 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

42. STATIC SYSTEM – INSPECT ALTERNATE AIR VALVE FOR OPERATION

Ref: NOTE

43. WINDSHIELD – PERFORM HEATED OPERATIONAL CHECK

Ref: NOTE

44. THRESHOLD LIGHT – CHECK FOR PROPER OPERATION

Ref: NOTE

45. AUXILIARY ELECTRIC HEAT (if installed) – CHECK FOR PROPER OPERATION OF THE ELECTRIC HEAT SYSTEM

Ref: NOTE

46. CABIN AND COMPARTMENT LIGHTS – CHECK FOR PROPER OPERATION

Ref: NOTE

47. PILOTS AN COPILOTS SEATS, SEATS BELTS- AND SHOULDER HARNESSES – CHECK SEAT ADJUSTMENT MECHANISM, SEAT BELTS AND SHOULDER HARNESS INERTIA REEL FOR OPERATION

Ref: NOTE

48. CABIN SEATS, SEAT BELTS AND SHOULDER HARNESSES – CHECK SEAT ADJUSTMENT MECHANISM, SEAT BELTS AND SHOULDER HARNESS INERTIA REEL FOR OPERATION

Ref: NOTE

49. CABIN ENTRANCE DOOR: a) CHECK THAT FOLDING STEPS DO NOT FOLD TOO SOON AND THAT THEY FOLD PROPERLY WITHOUT INTERFERENCE b) CHECK CABIN DOOR UNLOCK ANNUNCIATOR FOR PROPER OPERATION c) INSPECT CABIN DOOR DAMPER FOR LEAKAGE AND PROPER OPERATION

Ref: NOTE

50. EMERGENCY EXIT ( WITH DOOR INSTALLED ) a) CHECK EMERGENCY RELEASE HANDLES (inside and outside) AND LATCH MECHANISM FOR OPERATION b) CHECK THAT LATCHES OPEN AND CLOSE FREELY

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-24 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

51. EMPENNAGE CONTROL SURFACES a) CHECK FOR FREEDOM OF MOVEMENT b) CHECK OPTIONAL TRIM ACTUATORS AND MOTORS FOR SMOOTHNESS OF OPERATION

Ref: NOTE

52. REAR FUSELAGE AND EMPENNAGE LIGHTS - CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

53. AILERON (LH AND RH) – CHECK FOR FREEDOM OF MOVEMENT

Ref: NOTE

54. AILERON TRIM TAB – CHECK TRIM TAB ACTUATOR FOR SMOOTHNESS OF OPERATION AND ATTACHMENT

Ref: NOTE

55. FUEL TANK HEATED VENTS (LH AND RH) – CHECK THE OPERATION OF THE HEATED VENTS. THEY SHOULD BE WARM TO THE TOUCH

Ref: NOTE

56. STALL WARNING HEAT – CHECK FOR PROPER OPERATION

Ref: NOTE

57. FLAPS AND ACTUATORS ( Inboard, Outboard, LH and RH) – CHECK FLAPS FOR NOISY OR ERRATIC OPERATION

Ref: NOTE

58. WING CENTER SECTION LIGHTS – CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

59. ENGINE INDUCTION SYSTEM (LH AND RH)- CHECK THE INERTIAL VANE AND BYPASS DOOR FOR MOVEMENT WITH THE MAIN AND STANDBY ACTUATOR MOTORS.

Ref: NOTE

60. EXTERNAL POWER RELAY – CHECK FOR PROPER OPERATION

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-25 PHASE 1 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: R. POST INSPECTION ITEMS

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. AIRPLANE CLEANED AND SERVICED AS REQUIRED

12-20-00

2. LUBRICATE AS NECESSARY 12-20-00 3. ENGINE INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST – CHECK FOR OIL LEAKS, SECURITY AND ATTACHMENT OF ALL COMPONENTS

4. AIRWORTHINESS DIRECTIVES AND SERVICE BULLETINS – MUST BE REVIEWED AND COMPLIED WITH AS REQUIRED

5. ADDITIONAL INSPECTION REQUIREMENTS- ENSURE THAT SPECIAL INSPECTION REQUIREMENTS ARE COMPLIED WITH AT THE APPROPRIATE INTERVALS

6. IN-FLIGHT WORKSHEETS – ALL DISCREPANCIES NOTED BY THE PILOT MUST BE CHECKED AND CORRECTED AS REQUIRED

7. EMERGENCY LOCATOR TRANSMITTER – CHECK FOR PROPER OPERATION AND ENSURE ELT IS ARMED BEFORE RETURNING AIRPLANE TO SERVICE

25-60-00

8. OXYGEN SYSTEM PRESSURE – CHECK FOR PROPER PRESSURE

12-10-00

9. EMERGENCY AND SURVIVAL EQUIPMENT- ENSURE ALL NECESSARY EMERGENCY AND SURVIVAL EQUIPMENT IS INSTALLED IN THE AIRPLANE AND IS SERVICEABLE

10. PLACARDS – DETERMINE THAT ALL REQUIRED PLACARDS ARE IN PLACE AND LEGIBLE

11-20-00 POH

11. LOGBOOK ENTRY – ENSURE THAT LOG BOOKS ARE FILLED OUT PROPERLY

MME

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-26 PHASE 1 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: NOSE LANDING GEAR

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1 WHEEL BEARINGS MOBIL AVIATION GREASE SHC 100

PHASE 1

2 GREASE FITTINGS MIL-G-81322 PHASE 1 3. NOSE WHEEL STEERING

MECHANISM MIL-G-81322 GREASE

PHASE 1

4. UPPER AND LOWER NOSE GEAR STRUT BEARING

AEROSHELL 17

PHASE 1

5. DRAG BRACE BOLTS WITH GREASE FITTINGS. ROTATE BOLT WITH WRENCH, IF UNABLE TO ROTATE, REMOVE AND CLEAN Note: Grease must appear at both ends of bolt. If not, remove and clean grease passage.

MIL-G-81322 PHASE 1

CAUTION: DO NOT MIX different brands of grease as this will cause decreased bearing life. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication. NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-27 PHASE 1 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: MAIN LANDING GEAR

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. HIGH FLOTATION GEAR DOOR LINKAGE

LPS No: 3 Metal Protector

PHASE 1

2. GREASE FITTINGS MIL-G-81322 PHASE 1 3. DOOR HINGES AND

RETRACT LINKAGE MIL-L-7870 PHASE 1

4. WHEEL BEARINGS MOBIL AVIATION GREASE SHC 100

PHASE 1

5. DRAG LEG HOOK, SPRING AND GUIDE

LPS No: 3 Metal Protector (Apply Sparingly)

PHASE 1

6. DRAG BRACE BOLTS WITH GREASE FITTINGS. ROTATE BOLT WITH WRENCH, IF UNABLE TO ROTATE, REMOVE AND CLEAN Note: Grease must appear at both ends of bolt. If not, remove and clean grease passage.

MIL-G-81322 PHASE 1

7 RETRACT ACTUATOR CLEVIS

AEROSHELL 17

PHASE 1

NOTE: After washing the airplane, lubricate all lubrication points. CAUTION: DO NOT MIX different brands of grease as this will cause decreased bearing life. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-28 PHASE 1 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: RUDDER CONTROL,

LANDING GEAR RETRACT (MECHANICAL) SYSTEMS LUBRICATION

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. RUDDER TRIM TAB TUBE

MIL-L-7870 PHASE 1

2. RUDDER TRIM TAB HINGE

MIL-L-7870 PHASE 1

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-29 PHASE 1 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: AILERON AND FLAP

CONTROL SYSTEM LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. AILERON TRIM TAB HINGE

BRAYCO 300/LPS-1

PHASE 1

2. AILERON TRIM TAB TUBE END

MIL-L-7870 PHASE 1

3. FLAP TRACKS Spray with a dry lubricant

PHASE 1

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-30 PHASE 1 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: CONTROL COLUMN,

RUDDER AND ELEVATOR CONTROL SYSTEMS LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. ELEVATOR TRIM TAB TUBE

MIL-L-7870 PHASE 1

2. ELEVATOR TRIM TAB HINGES

BRAYCO 300 PHASE 1

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-31 PHASE 1 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: ENGINE CONTROL

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. CONTROL ROD ENDS MIL-G-23827 PHASE 1 2. CAM PLATES AND PIN Lubriplate No.

130AA PHASE 1

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-32 PHASE 1 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: PROPELLER

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. PROPELLER BLADE BEARINGS (2 lube fittings per blade)

Aeroshell Grease No. 6, Aeroshell Grease No 7, Aeroshell Grease No. 22, Exxon 5114EP, Rayco 22C as defined by the manufacturers decal on the piston hub of the propeller

PHASE 1

2 LOW PITCH STOP RODS (3 per propeller)

Marvel Mystery Oil

PHASE 1

WARNING: Remove the lubrication fitting opposite the one being serviced. Failure to do so could result in damage to the propeller bearings and seals.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 3-32 PHASE 1 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: EMERGENCY EXIT AND

CABIN DOOR LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1 CABIN DOOR: Latching Mechanism

MIL-L-7870 OIL

PHASE 1

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-0 PHASE 2 INSPECTION FINAL RELEASE

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

NKF W/O:

SE-XXX

Date:

A/C TT: A/C TOTCYC:

Phase 2 inspection in accordance with RAYTHEON AIRCRAFT SCHEDULED INSPECTION PROGRAM, PHASE 2 INSPECTION shall be in use for documentation of the scope of work. Ref: MM 5-20-00.

Certifies that the work specified except as otherwise specified was carried out in accordance with PART – 145.50, and in respect to that work the aircraft is considered ready for release to service. CRS Signature:

CRS Approval:

Pos:

Action:

Sign

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-1 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: B. NOSE AVIONIC COMPARTMENT

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. VACCUM REGULATOR VALVE FILTER – INSPECT FOR BLOCKAGE

12-20-00 37-00-00

2. INSTRUMENT AIR FILTER – INSPECT FOR CLEANLINESS

12-20-00 37-00-00

C. NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT – INSPECT ALL EXPOSED ELECTRICAL WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND SECURITY OF ATTACHMENT

AC.43.13.1B/2A

2. FORWARD EVAPORATOR FILTER - INSPECT FORWARD EVAPORATOR FILTER

21-50-00

3. CONDENSER BLOWER – INSPECT FITTINGS FOR DIRT, GREASE, MOISTURE AND SECURITY OF ATTACHMENT

21-50-00

D. NOSE GEAR 1. WHEEL a) INSPECT WHEEL FOR WEAR, DAMAGE and CORROSION b) INSPECT WHEEL BEARINGS and RACES for WEAR, PITTING, CRACKS ,DISCOLORATION, RUST or other indications of damage.

32-40-00 CMM

2. TIRE a) INSPECT FOR WEAR AND DETEIORATION b) CHECK FOR CORRECT INFLATION

12-20-00 CMM

3. SHIMMY DAMPER – INSPECT FOR LEAKS, SECURITY AND ATTACHEMENT

12-20-00 32-20-00

4. NOSE GEAR DRAG BRACE STOP LUGS- INSPECT FOR CRACK, DAMAGE OR DIST.

12-20-00 32-20-00

5. NOSE GEAR STEERING STOP – INSPECT STEERING STOP FOR DAMAGE OR DISTORSION

12-20-00 32-20-00

6. LANDING AND TAXI LIGHTS – INSPECT FOR BROKEN LENSES OR BULBS

33-40-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-2 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: D. NOSE GEAR, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

7. NOSE GEAR LOWER DRAG LEG – REMOVE NOSE GEAR DRAG BRACE BOLT AND INSPECT LOWER DRAG LEG HOLE FOR CORROSION AND WEAR

CMM

8. NOSE GEAR ACTUATOR a) INSPECT ACTUATOR SUPPORT BRACKETS FOR DAMAGE, CRACKS AND LOOSE OR MISSING FASTENERS b) INSPECT ACTUATOR AND PLUMBING FOR LEAKAGE

32

E. PILOTS COMPARTMENT 1. RETURN AIR INLET FILTERS – INSPECT FILTERS IN RETURN AIR INLET OF THE FORWARD VENT BLOWER

21-50-00

2. WINDSHIELD a) INSPECT WINDSHIELD FOR CRACKS AND VISIBILITY IMPAIRMENT b) INSPECT WINDSHIELD WEATHER SEAL (Silicone) FOR DEBONDING, CRACKS OR WEAR c) INSPECT WINDSHIELD WEATHER HUMP SEAL (Polysulfide) FOR DEBONDING, CRACKS OR WEAR

56-10-00

3. WINDOWS – INSPECT EXTERIOR SURFACE OF COCKPIT SIDE WINDOWS FOR DEEP SCRATCHES, CRACKS, CHIPS OR EXCESS CRAZING OR OTHER DAMAGE

56-15-00

4. ALTERNATE AIR VALVE – DRAIN OFF ALL MOISTURE

34-00-00

5. SEAT TRACKS – INSPECT SEAT TRACKS FOR DAMAGE AND WEAR

25-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-3 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: F. CABIN SECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. WINDOWS – INSPECT EXTERIOR SURFACE OF WINDOWS FOR DEEP SCRATCHES, CRACKS, CHIPS AND EXCESSIVE CRAZING OR OTHER DAMAGE

56-15-00

2. ROTATING OR FLASHING BEACON – INSPECT FOR CRACKED OR BROKEN LENSES

33-40-00

3. ACCESS DOORS – INSPECT FOR FIT AND ATTACHMENT

N/A

4. OUTFLOW AND SAFETY VALVES – DRAIN CONTROL LINE

12-20-00

5. SEAT TRACKS – INSPECT SEAT TRACKS FOR DAMAGE AND WEAR

25-20-00

6. PRESSURIZATION DUCTS – INSPECT FOR SECURITY OF ATTACHMENT

21-20-00

7. UPHOLSTERY PANELS – INSPECT FOR ATTACHMENT AND SECURITY

N/A

G. REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAINS – INSPECT REAR FUSELAGE DRAINS

53-10-00

2. ELT - BATTERY a) INSPECT FOR LEAKAGE, CORROSION OR LOOSE LEADS b) DETERMINE REMAINING USEFUL LIFE

25-60-00

3. NAVIGATION LIGHTS AND ROTATING OR FLASHING BEACONS – INSPECT FOR BROKEN OR CRACKED LENSES

33-40-00

4. ACCESS DOORS – INSPECT FOR FIT AND SECURITY OF ATTACHMENT

N/A

5. VENTRAL FIN DRAIN HOLES – INSPECT THE DRAIN HOLES IN THE BOTTOM OF THE VENTRAL FIN FOR OBSTRUCTIONS

53-10-00

6. DEICER BOOTS – INSPECT FOR DETERI- ORATION, DAMAGE AND ATTACHMENT

N/A

7. RUDDER AND TRIM TAB DRAIN HOLES – INSPECT THE DRAIN HOLES FOR OBSTRUCTIONS

N/A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-4 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: G. REAR FUSELAGE AND EMPENNAGE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

9. EMPENNAGE AND CONTROL SURFACES a) CHECK ELEVATOR TRIM TAB FREE PLAY b) CHECK RUDDER TRIM TAB FREE PLAY c) INSPECT ELEVATOR AND RUDDER HINGE BRACKETS AND THEIR SPAR ATTACH AREAS

27-30-00 27-20-00 27-30-00 27-20-00

H. LEFT-HAND OUTBOARD WING 1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - DETERMINE THAT THE DRAIN HOLES ARE OPEN IN THE WING CENTER SECTION AND OUTBOARD WING UPPER ATTACHMENT FITTINGS

57-00-00

3. LIGHTS a) INSPECT THE NAVIGATION AND RECOGNITION LIGHTS FOR BROKEN OR CRACKED LENSES b) INSPECT THE STROBE LIGHT FOR BROKEN OR CRACKED LENSES

33-40-00

4. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE WING FOR LEAKAGE

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT EXTERIOR OPENINGS OF VENTS FOR OBSTRUCTIONS

28-10-00

5. INTEGRAL FUEL TANK – INSPECT THE EXTERIOR SURFACE OF THE INTEGRAL TANK ACCESS DOORS FOR LEAKS

28-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-5 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: H. LEFT-HAND OUTBOARD WING, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

6. DEICER BOOTS – INSPECT EXTERIOR SURFACE FOR DETERIORATION, DAMAGE AND ATTACHMENT

30-10-00

7. ACCESS DOORS (INSPECTION PANELS) – INSPECT FOR FIT AND ATTACHMENT

6-50-00

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

I. LEFT HAND WING CENTER SECTION 1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE CENTER SECTION FOR LEAKS

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT THE EXTERIOR OPENINGS OF THE VENTS FOR OBSTRUCTIONS

28-10-00

3. ACCESS DOORS (INSPECTION PANELS) - INSPECT FOR FIT AND ATTACHMENT

6-50-00

4. ENGINE FIRE EXTINGUISHER a) INSPECT PLUMBING FOR SECURITY OF ATTACHMENT b) CHECK FIRE BOTTLE PRESSURE GAUGE c) PERFORM THE FIRE EXTINGUISHING SYSTEM FUNCTIONAL TEST

26-20-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-6 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: J. LEFT-HAND MAIN LANDING GEAR AREA

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. WHEELS a) INSPECT WHEELS FOR WEAR, DAMAGE AND CORROSION

N/A

b) INSPECT WHEEL BEARINGS AND RACES FOR WEAR, PITTING, CRACKS, DISCOLORATION, RUST OR OTHER INDICATIONS OF DAMAGE

CMM

2. BRAKES – INSPECT BRAKE DISCS, LININGS AND PLUMBING FOR WEAR DAMAGE, LEAKS, CORROSION AND SECURITY OF ALL COMPONENTS

32-40-00 CMM

3. BRAKE DEICING ( if installed) a) INSPECT MANIFOLD FOR BLOCKED ORIFICES b) INSPECT EXTERIOR OF LINES, HOSES AND CONNECTIONS FOR LEAKAGE AND ATTACHMENT

30-21-00

4. TIRES – INSPECT TIRES FOR WEAR, DETERIORATION AND CORRECT INFLATION

12-20-00 CMM

5. LEFT-HAND MAIN LANDING GEAR STRUT – CHECK STRUT FOR LEAKS AND PROPER EXTENSION

12-20-00

6. ELECTRICAL WIRING AND EQUIPMENT – INSPECT EXPOSED WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND PROPER ROUTING AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

7. MAIN GEAR ACTUATOR a) ACTUATOR (Mechanical Gear) 1. INSPECT ACTUATOR SUPPORT BRACKETS FOR VISIBLE DAMAGE, WEAR AND LOOSE AND MISSING FASTENERS 2. INSPECT ACTUATOR FOR LEAKAGE OF INTERNAL LUBRICANT

32-30-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-7 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: K. LEFT-HAND ENGINE

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

4. PROPELLERS a) INSPECT FOR DAMAGE AND ATTACHMENT (spinner removal required) b) INSPECT THE CARBON BLOCK PIN FOR FREEDOM OF MOVEMENT c) CHECK FOR NO METAL-TO-METAL CONTACT BETWEEN THE BRASS RING AND THE REVERSING LEVER d) INSPECT MECHANICAL FEEDBACK RING STOP RODS AND SPRINGS FOR DAMAGE

61

e) INSPECT THE REVERSING LINKAGE FOR CORRECT ADJUSTMENT, EVIDENCE OF BINDING AND SECURITY OF ATTACHMENT

76-00-00

5. HIGH PRESSURE FUEL PUMP FILTERS – INSPECT THE ENGINE-DRIVEN HIGH PRESSURE FUEL PUMP FILTERS

P&W

6. ENGINE OIL FILTER – INSPECT FOR METAL PARTICLES

P&W

7. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT – (Sundstrand pumps only)-INSPECT FOR FRETTING AND/OR CORROSION WHEN REPLACING OUTLET FILTER

P&W 73-10-02

8. DRAIN PLUGS – INSPECT ALL DRAIN PLUGS FOR LEAKAGE, SECURITY AND SAFETYING

79-00-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-8 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: K. LEFT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

9. COWLING – REMOVE ENTIRE COWLING AND INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION

71-10-00

10. OIL COOLER – INSPECT OIL COOLER AND PLUMBING FOR LEAKAGE, DAMAGE AND ATTACHMENT

79-00-00

11. OIL PRESSURE SNUBBER (p/n: 3R1) WITH POROUS TYPE ELEMENT – CLEAN ELEMENT

12-10-00

12. AFT COWLING ACCESS DOOR LATCHES – CHECK ADJUSTMENT OF LATCHES

71-10-00

13. FIRE SEALS-INSPECT FOR CONDITION 71-00-00 14. ENGINE EXHAUST SYSTEM a) INSPECT ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION b) INSPECT THE EXHAUST SYSTEM AND VISIBLE PORTIONS OF THE POWER TURBINE FOR BURNING, DISTORSION, DAMAGE AND CRACKS

P&W 78-00-00

15. ENGINE AND PROPELLERS CONTROLS a) CHECK CONTROLS AND ASSOCIATED EQUIPMENT FOR BINDING, STIFF OPERATION FULL TRAVEL AND FRICTION LOCK b) INSPECT CONTROLS, BOLTS, NUTS COTTER PINS AND SAFETIES FOR CORROSION, DAMAGE AND ATTACHMENT NOTE: Special attention should be made to the cam box.

N/A

c) INSPECT CONTROL CABLES FOR DAMAGE SUCH AS CRIMPS, CUTS, ABRASIONS OR TIGHT BENDS. IF EXTERIOR COVERING IS RUPTURED, PERFORM LEAK TEST

12-20-00

16. CONTROL CABLE BOOTS – INSPECT THE CONTROL CABLE BOOTS FOR EXCESSIVE COMPRESSION, TWIST, WEAR OR AGING WHICH COULD CAUSE BINDING

N/A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-9 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: K. LEFT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

17. STARTER GENERATOR – INSPECT ONE SET OF BRUSHES FOR INDICATIONS OF EXCESSIVE WEAR OR DAMAGE (determine Wear by observing diagonal groove on brush)

24-30-00

18. COMPRESSOR INLET – REMOVE THE AIR INLET SCREEN AND INSPECT THE COMPRESSOR INLET AREA, STRUTS, FIRST STAGE BLADES AND VANES FOR DIRT DEPOSITS, CORROSION, EROSION, CRACKS AND DAMAGE BY FOREIGN OBJECTS. Refer To the Engine Maintenance Manual for corrective Action.

P&W

19. MAGNETIC CHIP DETECTOR a) REMOVE AND VISUALLY INSPECT PLUG FOR METAL PARTICLES AND DAMAGE b) CHECK LIGHT IN ANNUNCIATOR PANEL FOR PROPER OPERATION

12-10-00

20. ENGINE a) INSPECT FUEL NOZZLES PER MANUFACTURERS MANUAL b) INSPECT ENGINE IN ACCORDANCE WITH THE INSTRUCTIONS FOUND IN THE ENGINE MANUFACTURERS MANUAL

P&W

21. IGNITION EXCITER a) INSPECT EXCITER AND ELECTRICAL HARNESS FOR DAMAGE AND SECURITY OF ATTACHMENT b) INSPECT THAT SUPPLY CABLE AND IGNITION CABLE CONNECTORS ARE INSTALLED AND SAFETIED

74-00-00

22. SPARK IGNITERS PLUGS – INSPECT THE IGNITER PLUGS AS DESCRIBED IN THE ENGINE MAINTENANCE MANUAL

P&W

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-10 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: K. LEFT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

23. FUEL PURGE SYSTEM/FUEL DRAIN COLLECTOR SYSTEM 1. CHECK TANK, PUMP, PUMP FILTER AND PLUMBING FOR LEAKS AND SECURITY OF ATTACHMENT 2. PERFORM A PRESSURE TEST ON THE COLLECTOR TANK 3. CHECK WIRING TO COLLECTOR PUMP AND TANK FLOAT SWITCH FOR DAMAGE AND SECURITY OF ATTACHMENT 4. CHECK COLLECTOR PUMP FOR PROPER OPERATION

71-70-00

24. LEFT-HAND ENGINE – INSPECT ALL SYSTEMS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. CHECK ALL TUBES AND HOSES FOR GENERAL CONDITION, LEAKS AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

25. ENGINE MOUNT TRUSS ASSEMBLY a) INSPECT FOR CRACKS, DENTS, CHAFING AND CORROSION, SPECIAL ATTENTION SHOULD BE MADE TO AREAS AROUND CLAMPS b) INSPECT VIBRATION ISOLATORS (mounts) FOR DETERIORATION, DAMAGE AND ATTACHMENT

71-20-00

26. INDUCTION SYSTEM a) CHECK THE INERTIAL ANTI-ICER VANE AND BYPASS DOOR FOR FREEDOM OF MOVEMENT AND CORRECT TRAVEL WITH THE ELECTRICAL ACTUATOR AND THE MANUAL OVERRIDE b) INSPECT THE ENGINE INLET SCREEN, INERTIAL SEPARATOR AND AIR INLET DUCT FOR OBSTRUCTION AND DAMAGE

30-20-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-11 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: K. LEFT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

27. ENGINE FIRE DETECTION SYSTEM a) FIRE DETECTION SYSTEM – CHECK ALL FIRE DETECTORS FOR SENSITIVITY AND CONTINUITY 1. CHECK THAT FIRE DETECTION SENSOR ELEMENT IS NOT KINKED, CHAFED OR BENT AT A RADIUS OF LESS THAN 2 INCHES 2. CHECK THAT THE FIRE DETECTION SENSOR ELEMENT DOES NOT TOUCH THE SOURROUNDING STRUCTURE AND THAT ATTACHMENT POINTS ARE SECURE 3. CHECK THE FIRE DETECTION SYSTEM FOR CONTINUITY

26-10-00

28. PROPELLER SYNCHROPHASER – TYPE 1 1. INSPECT FOR PROPER GAP BETWEEN PICKUPS AND TARGETS

61-22-00

2. INSPECT DRIVE UNIT FOR DAMAGE, SECURITY OF ATTACHMENT, ELECTRICAL CONNECTIONS, WEAR AND PROPER RIGGING 3. CHECK ROD END BEARING FOR DAMAGE AND LUBRICATION

CMM

29. AUTOFEATHER AND AUTOIGNITION PRESSURE SWITCHES – INSPECT SECURITY OF ATTACHEMENT, LEAKAGE AND ELECTRICAL CONNECTION FOR SECURITY

61-21-00 74-00-00

30. PRIMARY PROPELLER GOVERNOR – INSPECT FOR SECURITY OF ATTACHMENT, LEAKAGE, AND SECURITY OF ELECTRICAL CONNECTORS AND WIRING

61-20-00

31. OVERSPEED GOVERNOR – INSPECT FOR SECURITY OF ATTACHMENT, LEAKAGE AND SECURITY OF ELECTRICAL CONNECTORS AND WIRING

61-20-00

32. ENVIRONMENTAL BLEED AIR FLOW CONTROL VALVE – INSPECT VALVE AND ASSOCIATED EQUIPMENT, ELECTRICAL WIRING AND DUCTS FOR DAMAGE, SECURITY OF CONNECTIONS AND ATTACHMENT

21-10-00 21-11-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-12 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: L. RIGHT-HAND OUTBOARD WING

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - DETERMINE THAT THE DRAIN HOLES ARE OPEN IN THE WING CENTER SECTION AND OUTBOARD WING UPPER ATTACHMENT FITTINGS

57-00-00

3. LIGHTS a) INSPECT THE NAVIGATION AND RECOGNITION LIGHTS FOR BROKEN OR CRACKED LENSES b) INSPECT THE STROBE LIGHT FOR BROKEN OR CRACKED LENSES

33-40-00

4. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE WING FOR LEAKAGE

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT EXTERIOR OPENINGS OF VENTS FOR OBSTRUCTIONS

28-10-00

5. INTEGRAL FUEL TANK – INSPECT THE EXTERIOR SURFACE OF THE INTEGRAL TANK ACCESS DOORS FOR LEAKS

28-10-00

6. DEICER BOOTS – INSPECT EXTERIOR SURFACE FOR DETERIORATION, DAMAGE AND ATTACHMENT

30-10-00

7. ACCESS DOORS (INSPECTION PANELS) – INSPECT FOR FIT AND ATTACHMENT

6-50-00

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-13 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: M. RIGHT-HAND WING CENTER SECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE CENTER SECTION FOR LEAKS

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT THE EXTERIOR OPENINGS OF THE VENTS FOR OBSTRUCTIONS

28-10-00

3. ACCESS DOORS (INSPECTION PANELS) - INSPECT FOR FIT AND ATTACHMENT

6-50-00

4. BATTERY a) SERVICE BATTERY AS REQUIRED

12-20-00

b) REMOVE BATTERY AND INSPECT THE BATTERY BOX, CABLES AND VENT TUBES FOR DETERIORATION OR OBSTRUCTIONS

24-31-00

5. ENGINE FIRE EXTINGUISHER a) INSPECT PLUMBING FOR SECURITY OF ATTACHMENT b) CHECK FIRE BOTTLE PRESSURE GAUGE c) PERFORM THE FIRE EXTINGUISHING SYSTEM FUNCTIONAL TEST

26-20-00

N. RIGHT-HAND MAIN LANDING GEAR AREA 1. WHEELS a) INSPECT WHEELS FOR WEAR, DAMAGE AND CORROSION

N/A

b) INSPECT WHEEL BEARINGS AND RACES FOR WEAR, PITTING, CRACKS, DISCOLORATION, RUST OR OTHER INDICATIONS OF DAMAGE

CMM

2. BRAKES – INSPECT BRAKE DISCS, LININGS AND PLUMBING FOR WEAR DAMAGE, LEAKS, CORROSION AND SECURITY OF ALL COMPONENTS

32-40-00 CMM

3. BRAKE DEICING ( if installed) a) INSPECT MANIFOLD FOR BLOCKED ORIFICES b) INSPECT EXTERIOR OF LINES, HOSES AND CONNECTIONS FOR LEAKAGE AND ATTACHMENT

30-21-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-14 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: N. RIGHT-HAND MAIN LANDING GEAR AREA, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. TIRES – INSPECT TIRES FOR WEAR, DETERIORATION AND CORRECT INFLATION

12-20-00 CMM

5. LEFT-HAND MAIN LANDING GEAR STRUT – CHECK STRUT FOR LEAKS AND PROPER EXTENSION

12-20-00

6. ELECTRICAL WIRING AND EQUIPMENT – INSPECT EXPOSED WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND PROPER ROUTING AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

7. MAIN GEAR ACTUATOR a) ACTUATOR (Mechanical Gear) 1. INSPECT ACTUATOR SUPPORT BRACKETS FOR VISIBLE DAMAGE, WEAR AND LOOSE AND MISSING FASTENERS 2. INSPECT ACTUATOR FOR LEAKAGE OF INTERNAL LUBRICANT

32-30-00

O. RIGHT-HAND ENGINE 1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-15 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

4. PROPELLERS a) INSPECT FOR DAMAGE AND ATTACHMENT (spinner removal required) b) INSPECT THE CARBON BLOCK PIN FOR FREEDOM OF MOVEMENT c) CHECK FOR NO METAL-TO-METAL CONTACT BETWEEN THE BRASS RING AND THE REVERSING LEVER d) INSPECT MECHANICAL FEEDBACK RING STOP RODS AND SPRINGS FOR DAMAGE

61

e) INSPECT THE REVERSING LINKAGE FOR CORRECT ADJUSTMENT, EVIDENCE OF BINDING AND SECURITY OF ATTACHMENT

76-00-00

5. HIGH PRESSURE FUEL PUMP FILTERS – INSPECT THE ENGINE-DRIVEN HIGH PRESSURE FUEL PUMP FILTERS

P&W

6. ENGINE OIL FILTER – INSPECT FOR METAL PARTICLES

P&W

7. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT – (Sundstrand pumps only)-INSPECT FOR FRETTING AND/OR CORROSION WHEN REPLACING OUTLET FILTER

P&W 73-10-02

8. DRAIN PLUGS – INSPECT ALL DRAIN PLUGS FOR LEAKAGE, SECURITY AND SAFETYING

79-00-00

9 . RIGHT-HAND ENGINE – INSPECT ALL SYSTEMS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. CHECK ALL TUBES AND HOSES FOR GENERAL CONDITION, LEAKS AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-16 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

10.COWLING – REMOVE ENTIRE COWLING AND INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION

71-10-00

11. OIL COOLER – INSPECT OIL COOLER AND PLUMBING FOR LEAKAGE, DAMAGE AND ATTACHMENT

79-00-00

12. OIL PRESSURE SNUBBER (p/n: 3R1) WITH POROUS TYPE ELEMENT – CLEAN ELEMENT

12-10-00

13. AFT COWLING ACCESS DOOR LATCHES – CHECK ADJUSTMENT OF LATCHES

71-10-00

14. FIRE SEALS-INSPECT FOR CONDITION 71-00-00 15. ENGINE EXHAUST SYSTEM a) INSPECT ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION b) INSPECT THE EXHAUST SYSTEM AND VISIBLE PORTIONS OF THE POWER TURBINE FOR BURNING, DISTORSION, DAMAGE AND CRACKS

P&W 78-00-00

16. ENGINE AND PROPELLERS CONTROLS a) CHECK CONTROLS AND ASSOCIATED EQUIPMENT FOR BINDING, STIFF OPERATION FULL TRAVEL AND FRICTION LOCK b) INSPECT CONTROLS, BOLTS, NUTS COTTER PINS AND SAFETIES FOR CORROSION, DAMAGE AND ATTACHMENT NOTE: Special attention should be made to the cam box.

N/A

c) INSPECT CONTROL CABLES FOR DAMAGE SUCH AS CRIMPS, CUTS, ABRASIONS OR TIGHT BENDS. IF EXTERIOR COVERING IS RUPTURED, PERFORM LEAK TEST

12-20-00

17. CONTROL CABLE BOOTS – INSPECT THE CONTROL CABLE BOOTS FOR EXCESSIVE COMPRESSION, TWIST, WEAR OR AGING WHICH COULD CAUSE BINDING

N/A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-17 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

18. COMPRESSOR INLET – REMOVE THE AIR INLET SCREEN AND INSPECT THE COMPRESSOR INLET AREA, STRUTS, FIRST STAGE BLADES AND VANES FOR DIRT DEPOSITS, CORROSION, EROSION, CRACKS AND DAMAGE BY FOREIGN OBJECTS. Refer To the Engine Maintenance Manual for corrective Action.

P&W

19. MAGNETIC CHIP DETECTOR a) REMOVE AND VISUALLY INSPECT PLUG FOR METAL PARTICLES AND DAMAGE b) CHECK LIGHT IN ANNUNCIATOR PANEL FOR PROPER OPERATION

12-10-00

20. ENGINE a) INSPECT FUEL NOZZLES PER MANUFACTURERS MANUAL b) INSPECT ENGINE IN ACCORDANCE WITH THE INSTRUCTIONS FOUND IN THE ENGINE MANUFACTURERS MANUAL

P&W

21. IGNITION EXCITER a) INSPECT EXCITER AND ELECTRICAL HARNESS FOR DAMAGE AND SECURITY OF ATTACHMENT b) INSPECT THAT SUPPLY CABLE AND IGNITION CABLE CONNECTORS ARE INSTALLED AND SAFETIED

74-00-00

22. SPARK IGNITERS PLUGS – INSPECT THE IGNITER PLUGS AS DESCRIBED IN THE ENGINE MAINTENANCE MANUAL

P&W

23. FUEL PURGE SYSTEM/FUEL DRAIN COLLECTOR SYSTEM 1. CHECK TANK, PUMP, PUMP FILTER AND PLUMBING FOR LEAKS AND SECURITY OF ATTACHMENT 2. PERFORM A PRESSURE TEST ON THE COLLECTOR TANK 3. CHECK WIRING TO COLLECTOR PUMP AND TANK FLOAT SWITCH FOR DAMAGE AND SECURITY OF ATTACHMENT 4. CHECK COLLECTOR PUMP FOR PROPER OPERATION

71-70-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-18 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

24. ENGINE MOUNT TRUSS ASSEMBLY a) INSPECT FOR CRACKS, DENTS, CHAFING AND CORROSION, SPECIAL ATTENTION SHOULD BE MADE TO AREAS AROUND CLAMPS b) INSPECT VIBRATION ISOLATORS (mounts) FOR DETERIORATION, DAMAGE AND ATTACHMENT

71-20-00

25. INDUCTION SYSTEM a) CHECK THE INERTIAL ANTI-ICER VANE AND BYPASS DOOR FOR FREEDOM OF MOVEMENT AND CORRECT TRAVEL WITH THE ELECTRICAL ACTUATOR AND THE MANUAL OVERRIDE b) INSPECT THE ENGINE INLET SCREEN, INERTIAL SEPARATOR AND AIR INLET DUCT FOR OBSTRUCTION AND DAMAGE

30-20-00

27. ENGINE FIRE DETECTION SYSTEM a) FIRE DETECTION SYSTEM – CHECK ALL FIRE DETECTORS FOR SENSITIVITY AND CONTINUITY 1. CHECK THAT FIRE DETECTION SENSOR ELEMENT IS NOT KINKED, CHAFED OR BENT AT A RADIUS OF LESS THAN 2 INCHES 2. CHECK THAT THE FIRE DETECTION SENSOR ELEMENT DOES NOT TOUCH THE SOURROUNDING STRUCTURE AND THAT ATTACHMENT POINTS ARE SECURE 3. CHECK THE FIRE DETECTION SYSTEM FOR CONTINUITY

26-10-00

28. PROPELLER SYNCHROPHASER – TYPE 1 1. INSPECT FOR PROPER GAP BETWEEN PICKUPS AND TARGETS

61-22-00

2. INSPECT DRIVE UNIT FOR DAMAGE, SECURITY OF ATTACHMENT, ELECTRICAL CONNECTIONS, WEAR AND PROPER RIGGING 3. CHECK ROD END BEARING FOR DAMAGE AND LUBRICATION

CMM

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-19 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

29. AUTOFEATHER AND AUTOIGNITION PRESSURE SWITCHES – INSPECT SECURITY OF ATTACHEMENT, LEAKAGE AND ELECTRICAL CONNECTION FOR SECURITY

61-21-00 74-00-00

30. PRIMARY PROPELLER GOVERNOR – INSPECT FOR SECURITY OF ATTACHMENT, LEAKAGE, AND SECURITY OF ELECTRICAL CONNECTORS AND WIRING

61-20-00

31. OVERSPEED GOVERNOR – INSPECT FOR SECURITY OF ATTACHMENT, LEAKAGE AND SECURITY OF ELECTRICAL CONNECTORS AND WIRING

61-20-00

32. ENVIRONMENTAL BLEED AIR FLOW CONTROL VALVE – INSPECT VALVE AND ASSOCIATED EQUIPMENT, ELECTRICAL WIRING AND DUCTS FOR DAMAGE, SECURITY OF CONNECTIONS AND ATTACHMENT

21-10-00 21-11-00

33. STARTER GENERATOR – INSPECT ONE SET OF BRUSHES FOR INDICATIONS OF EXCESSIVE WEAR OR DAMAGE (determine Wear by observing diagonal groove on brush)

24-30-00

34. AIR CONDITIONING COMPRESSOR a) INSPECT FOR SECURITY OF ATTACHMENT AND OIL LEAKS b) INSPECT FOR WEAR AND LUBRICATE THE SPLINE ON THE PULLEY END OF THE QUILL SHAFT c) INSPECT DRIVE BELT FOR DETERIORATION WEAR AND PROPER TENSION

21-50-00

d) CHECK FOR PROPER COMPRESSOR OIL LEVEL

12-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-20 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: P. LANDING GEAR RETRACTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

NOTE: Mechanical and Hydraulic Landing Gear Systems – Since battery voltage is not sufficient to properly cycle The landing gear, use only an external power source Capable of delivering and maintaining 28.25 +/- 0.25 Volts throughout the extension and retraction cycles when performing the landing gear retraction inspection.

1. RETRACT MECHANISM – CHECK RETRACTION SYSTEM FOR PROPER OPERATION OF ALL COMPONENTS THROUGH AT LEAST TWO COMPLETE CYCLES

32

2. DOORS AND LINKAGE a) CHECK DOOR FOR DAMAGE, OPERATION AND FIT b) CHECK DOOR LINKAGE FOR WEAR, DAMAGE AND RIGGING

32

3. DOWNLOCK INDICATOR SWITCHES a) CHECK FOR SECURITY AND PROPER OPERATION OF SWITCHES b) CLEAN TERMINALS AND CONNECTORS AS REQUIRED c) CHECK WIRING FOR DAMAGE AND SECURITY OF CONNECTION

32-60-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-21 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: P. LANDING GEAR RETRACTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. UPLOCK INDICATOR SWITCHES a) CHECK FOR SECURITY AND PROPER OPERATION OF SWITCHES b) CLEAN TERMINALS AND CONNECTORS AS REQUIRED c) CHECK WIRING FOR DAMAGE AND SECURITY OF CONNECTION

32-60-00

5. WARNING HORN – CHECK OPERATION 32-60-00 6. MAIN GEAR DOWNLOCKS – CHECK LOCKING MECHANISM FOR POSITIVE ENGAGEMENT IN EXTENDED POSITION

32

7. SAFETY SWITCH – CHECK FOR PROPER OPERATION

32-60-00

8. ACTUATORS – CHECK FOR NOISE, BINDING AND PROPER RIGGING

32-30-00 32-31-00

9. LIMIT SWITCHES – (Mechanical Gear) a) CHECK FOR CORRECT ADJUSTMENT b) CHECK FOR SECURITY OF ATTACHMENT

32-60-00

10. EMERGENCY EXTENSION (Mechanical Gear) CHECK SYSTEM FOR FREEDOM OF OPERATION AND POSITIVE ENGAGEMENT OF DOWNLOCKS. CAUTION: Do not continue operation after receiving a gear-down indication on all gears. Further movement of the handle could damage the drive mechanism and prevent subsequent electrical gear retraction. The landing gear cannot be retracted manually.

32-30-00

11. NOSE GEAR RETRACT CHAIN (Mechanical Gear) a) CHECK FOR PROPER CHAIN TENSION b) CHECK NOSE GEAR AND NOSE GEAR LINKAGE CLEARANCE FROM ELECTRICAL WIRES AND OBSTRUCTIONS

32-30-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-22 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: P. LANDING GEAR RETRACTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

12. PLACARDS – CHECK THAT ALL PLACARDS ARE IN PLACE AND ARE LEGIBLE

11-00-00

13. LANDING GEAR RETRACTION – INSPECT ALL LANDING GEAR COMPONENTS AND ATTACHING HARDWARE, STRUCTURE AND HYDRAULIC LINES FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Q. OPERATIONAL INSPECTION NOTE: The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual for the engine start and run procedures.

N/A

1. FIREWALL SHUTOFF FUEL VALVES - CHECK FOR PROPER OPERATION

Ref: NOTE

2. CROSSFEED FUEL VALVE – CHECK FOR PROPER OPERATION

Ref: NOTE

3. STANDBY PUMPS – CHECK FOR PROPER OPERATIONS

Ref: NOTE

4. STARTER GENERATOR a) CHECK STARTER FOR OPERATION b) CHECK GENERATOR FOR OUTPUT

Ref: NOTE

5. IGNITION a) CHECK FOR PROPER OPERATION b) CHECK FOR ANNUNCIATOR PANEL LIGHT ILLUMINATION

Ref: NOTE

6. ENGINE OIL – CHECK FOR PROPER PRESSURE AND TEMPERATURE LIMITS

Ref: NOTE

7. FUEL QUANTITY GAGES – CHECK OPERATION

Ref: NOTE

8. INTERSTAGE TURBINE TEMPERATURE – CHECK FOR CORRECT LIMITS ON ENGINE START

Ref: NOTE

9. VACUUM SYSTEM – CHECK FOR CORRECT LIMITS

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-23 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

10. PNEUMATIC PRESSURE GAGE – CHECK FOR CORRECT PRESSURE

Ref: NOTE

11. PNEUMATIC SYSTEM SHUTOFF VALVES – CHECK FOR PROPER OPERATION

Ref: NOTE

12. GYRO INSTRUMENTS – CHECK FOR ERRATIC OR NOISY OPERATION

Ref: NOTE

13. PROPELLERS – PERFORM FLIGHT IDLE TOQUE CHECK

Ref: NOTE

14. AUTOFEATHERING CHECK – Refer to: AUTOFEATHERING SYSTEM OPERATIONAL CHECK

61-21-00

15. PROPELLER SYNCHROPASER – Refer to: AUTOFEATHER SYSTEM OPERATIONAL CHECK

61-21-00

16. PROPELLER GOVERNOR – CHECK GOVERNOR OPERATION ( Including feathering And reversing)

Ref: NOTE

17. IDLE RPM – CHECK FOR CORRECT RPM ( both high and low rpm)

Ref: NOTE

18 AC INVERTERS – CHECK FOR PROPER OPERATION

Ref: NOTE

19. RUDDER BOOST – CHECK FOR PROPER OPERATION

Ref: NOTE

20. AUTO-IGNITION a) CHECK FOR PROPER OPERATION b) CHECK FOR ANNUNCIATOR PANEL ILLUMINATION

Ref: NOTE

21. PROPELLER DEICER – CHECK FOR PROPER OPERATION AND CYCLING. Refer to chapter 30 of the Beech King Air Series Component Maintenance Manual

N/A

22. ENGINE INTERIAL ANTI-ICER – CHECK FOR PROPER OPERATION AND RIGGING

Ref: NOTE

23. SURFACE DEICE SYSTEM – CHECK FOR PROPER OPERATION AND CYCLING

Ref: NOTE

24. BRAKE DEICE SYSTEM (if installed) – CHECK FOR PROPER OPERATION WITH ENGINES RUNNING

Ref: NOTE

25. ELECTRICAL SYSTEM – PERFORM FUNCTIONAL CHECKS

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-24 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

26. ENVIRONMENTAL SYSTEM – CHECK FOR PROPER OPERATION IN: a) MANUAL HEAT MODE b) MANUAL COOL MODE c) AUTOMATIC MODE

Ref: NOTE

27. REFRIGERANT LEVEL – CHECK FOR PROPER LEVEL

Ref: NOTE

28. AUTOPILOT – CHECK FOR PROPER OPERATION AS OUTLINED BY THE APPLICABLE Beech Super King Air 200 and B200 Pilots Operating Handbook or SCAA Approved Airplane Flight Manual Supplement

Ref: NOTE

29. STALL WARNING – CHECK FOR PROPER OPERATION

Ref: NOTE

30. ENGINE FIRE DETECTORS – Perform system test according to instructions found in the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual

N/A

31. ENGINE FIRE EXTINGUISHERS – Perform system test according to instructions found in the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual

N/A

32. PRESSURIZATION SYSTEM – CHECK FOR PROPER OPERATION Refer to the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual and perform system test

N/A

33. AUXILIARY FUEL TRANSFER JET PUMPS – CHECK FOR PROPER OPERATION

Ref: NOTE

34. CONDITION LEVER – CHECK FOR CLEAN SHUTDOWN AT IDLE-CUT-OFF

Ref: NOTE

35. PITOT TUBE – CHECK FOR PROPER HEATING AT THE UNIT AND FOR OBSTRUCTIONS

Ref: NOTE

36. LANDING AND TAXI LIGHTS – CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

37. OUTBOARD WING LIGHTS ( R/H AND L/H) - CHECK OPERATION OF ALL NAVIGATION AND STROBE LIGHTS

Ref: NOTE

38. COCKPIT LIGHTS – CHECK OPERATION OF ALL COCKPIT LIGHTS

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-25 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

39. EFIS COOLING BLOWERS (if installed) – CHECK OPERATION

Ref: NOTE

40. ELECTRIC ELEVATOR TRIM – CHECK FOR PROPER OPERATION

Ref: NOTE

41. ENGINE AND PROPELLER CONTROLS – CHECK FOR FREEDOM OF MOVEMENT FULL TRAVEL AND FRICTION-LOCK OPERATION

Ref: NOTE

42. STATIC SYSTEM – INSPECT ALTERNATE AIR VALVE FOR OPERATION

Ref: NOTE

43. WINDSHIELD – PERFORM HEATED OPERATIONAL CHECK

Ref: NOTE

44. THRESHOLD LIGHT – CHECK FOR PROPER OPERATION

Ref: NOTE

45. AUXILIARY ELECTRIC HEAT (if installed) – CHECK FOR PROPER OPERATION OF THE ELECTRIC HEAT SYSTEM

Ref: NOTE

46. CABIN AND COMPARTMENT LIGHTS – CHECK FOR PROPER OPERATION

Ref: NOTE

47. PILOTS AN COPILOTS SEATS, SEATS BELTS- AND SHOULDER HARNESSES – CHECK SEAT ADJUSTMENT MECHANISM, SEAT BELTS AND SHOULDER HARNESS INERTIA REEL FOR OPERATION

Ref: NOTE

48. CABIN SEATS, SEAT BELTS AND SHOULDER HARNESSES – CHECK SEAT ADJUSTMENT MECHANISM, SEAT BELTS AND SHOULDER HARNESS INERTIA REEL FOR OPERATION

Ref: NOTE

49. CABIN ENTRANCE DOOR: a) CHECK THAT FOLDING STEPS DO NOT FOLD TOO SOON AND THAT THEY FOLD PROPERLY WITHOUT INTERFERENCE b) CHECK CABIN DOOR UNLOCK ANNUNCIATOR FOR PROPER OPERATION c) INSPECT CABIN DOOR DAMPER FOR LEAKAGE AND PROPER OPERATION

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-26 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

50. EMERGENCY EXIT ( WITH DOOR INSTALLED ) a) CHECK EMERGENCY RELEASE HANDLES (inside and outside) AND LATCH MECHANISM FOR OPERATION b) CHECK THAT LATCHES OPEN AND CLOSE FREELY

Ref: NOTE

51. EMPENNAGE CONTROL SURFACES a) CHECK FOR FREEDOM OF MOVEMENT b) CHECK OPTIONAL TRIM ACTUATORS AND MOTORS FOR SMOOTHNESS OF OPERATION

Ref: NOTE

52. REAR FUSELAGE AND EMPENNAGE LIGHTS - CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

53. AILERON (LH AND RH) – CHECK FOR FREEDOM OF MOVEMENT

Ref: NOTE

54. AILERON TRIM TAB – CHECK TRIM TAB ACTUATOR FOR SMOOTHNESS OF OPERATION AND ATTACHMENT

Ref: NOTE

55. FUEL TANK HEATED VENTS (LH AND RH) – CHECK THE OPERATION OF THE HEATED VENTS. THEY SHOULD BE WARM TO THE TOUCH

Ref: NOTE

56. STALL WARNING HEAT – CHECK FOR PROPER OPERATION

Ref: NOTE

57. FLAPS AND ACTUATORS ( Inboard, Outboard, LH and RH) – CHECK FLAPS FOR NOISY OR ERRATIC OPERATION

Ref: NOTE

58. WING CENTER SECTION LIGHTS – CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

59. ENGINE INDUCTION SYSTEM (LH AND RH)- CHECK THE INERTIAL VANE AND BYPASS DOOR FOR MOVEMENT WITH THE MAIN AND STANDBY ACTUATOR MOTORS.

Ref: NOTE

60. EXTERNAL POWER RELAY – CHECK FOR PROPER OPERATION

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-27 PHASE 2 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: R. POST INSPECTIONS ITEMS

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. AIRPLANE CLEANED AND SERVICED AS REQUIRED

12-20-00

2. LUBRICATE AS NECESSARY 12-20-00 3. ENGINE INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST – CHECK FOR OIL LEAKS, SECURITY AND ATTACHMENT OF ALL COMPONENTS

4. AIRWORTHINESS DIRECTIVES AND SERVICE BULLETINS – MUST BE REVIEWED AND COMPLIED WITH AS REQUIRED

5. ADDITIONAL INSPECTION REQUIREMENTS- ENSURE THAT SPECIAL INSPECTION REQUIREMENTS ARE COMPLIED WITH AT THE APPROPRIATE INTERVALS

6. IN-FLIGHT WORKSHEETS – ALL DISCREPANCIES NOTED BY THE PILOT MUST BE CHECKED AND CORRECTED AS REQUIRED

7. EMERGENCY LOCATOR TRANSMITTER – CHECK FOR PROPER OPERATION AND ENSURE ELT IS ARMED BEFORE RETURNING AIRPLANE TO SERVICE

25-60-00

8. OXYGEN SYSTEM PRESSURE – CHECK FOR PROPER PRESSURE

12-10-00

9. EMERGENCY AND SURVIVAL EQUIPMENT- ENSURE ALL NECESSARY EMERGENCY AND SURVIVAL EQUIPMENT IS INSTALLED IN THE AIRPLANE AND IS SERVICEABLE

10. PLACARDS – DETERMINE THAT ALL REQUIRED PLACARDS ARE IN PLACE AND LEGIBLE

11-20-00 POH

11. LOGBOOK ENTRY – ENSURE THAT LOG BOOKS ARE FILLED OUT PROPERLY

MME

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-28 PHASE 2 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: NOSE LANDING GEAR

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1 WHEEL BEARINGS MOBIL AVIATION GREASE SHC 100

PHASE 2

2 GREASE FITTINGS MIL-G-81322 PHASE 2 3. NOSE WHEEL STEERING

MECHANISM MIL-G-81322 GREASE

PHASE 2

4. UPPER AND LOWER NOSE GEAR STRUT BEARING

AEROSHELL 17

PHASE 2

5. DRAG BRACE BOLTS WITH GREASE FITTINGS. ROTATE BOLT WITH WRENCH, IF UNABLE TO ROTATE, REMOVE AND CLEAN Note: Grease must appear at both ends of bolt. If not, remove and clean grease passage.

MIL-G-81322 PHASE 2

CAUTION: DO NOT MIX different brands of grease as this will cause decreased bearing life. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication. NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-29 PHASE 2 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: MAIN LANDING GEAR

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. HIGH FLOTATION GEAR DOOR LINKAGE

LPS No: 3 Metal Protector

PHASE 2

2. GREASE FITTINGS MIL-G-81322 PHASE 2 3. DOOR HINGES AND

RETRACT LINKAGE MIL-L-7870 PHASE 2

4. WHEEL BEARINGS MOBIL AVIATION GREASE SHC 100

PHASE 2

5. DRAG LEG HOOK, SPRING AND GUIDE

LPS No: 3 Metal Protector (Apply Sparingly)

PHASE 2

6. DRAG BRACE BOLTS WITH GREASE FITTINGS. ROTATE BOLT WITH WRENCH, IF UNABLE TO ROTATE, REMOVE AND CLEAN Note: Grease must appear at both ends of bolt. If not, remove and clean grease passage.

MIL-G-81322 PHASE 2

7 RETRACT ACTUATOR CLEVIS

AEROSHELL 17

PHASE 2

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-30 PHASE 2 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: RUDDER CONTROL,

LANDING GEAR RETRACT (MECHANICAL) SYSTEMS LUBRICATION

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. RUDDER TRIM TAB TUBE

MIL-L-7870 PHASE 2

2. RUDDER TRIM TAB HINGE

MIL-L-7870 PHASE 2

3. RUDDER TRIM TAB ACTUATOR

MIL-G-23827 PHASE 2

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-31 PHASE 2 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: AILERON AND FLAP

CONTROL SYSTEM LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. AILERON TRIM TAB HINGE

BRAYCO 300/LPS-1

PHASE 2

2. AILERON TRIM TAB TUBE END

MIL-L-7870 PHASE 2

3. FLAP TRACKS Spray with a dry lubricant

PHASE 2

4. AILERON QUADRANT MIL-L-7870 PHASE 2 5. AILERON BELLCRANKS MIL-L-7870 PHASE 2 6. TRIM TAB ACTUATOR MIL-G-23827 PHASE 2 NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-32 PHASE 2 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: CONTROL COLUMN,

RUDDER AND ELEVATOR CONTROL SYSTEMS LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. ELEVATOR TRIM TAB TUBE

MIL-L-7870 PHASE 2

2. ELEVATOR TRIM TAB HINGES

BRAYCO 300 PHASE 2

3. PEDAL AND BELLCRANK LINKAGE

MIL-L-7870 PHASE 2

4. RUDDER TRIM TAB ACTUATOR

MIL-G-23827 PHASE 2

5. ELEVATOR TRIM TAB ACTUATOR

MIL-G-23827 PHASE 2

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-33 PHASE 2 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: ENGINE CONTROL

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. CONTROL ROD ENDS MIL-G-23827 PHASE 2 2. CAM PLATES AND PIN Lubriplate No.

130AA PHASE 2

3. AIR-CONDITIONER COMPRESSOR QUILL SHAFT

MOLYKOTE M-77

PHASE 2

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-34 PHASE 2 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: PROPELLER

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. PROPELLER BLADE BEARINGS (2 lube fittings per blade)

Aeroshell Grease No. 6, Aeroshell Grease No 7, Aeroshell Grease No. 22, Exxon 5114EP, Rayco 22C as defined by the manufacturers decal on the piston hub of the propeller

PHASE 2

2 LOW PITCH STOP RODS (3 per propeller)

Marvel Mystery Oil

PHASE 2

WARNING: Remove the lubrication fitting opposite the one being serviced. Failure to do so could result in damage to the propeller bearings and seals.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 4-35 PHASE 2 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: EMERGENCY EXIT AND

CABIN DOOR LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. CABIN DOOR: Latching Mechanism (pins included)

MIL-L-7870 OIL

PHASE 2

2. TRACK MOLYKOTE G-N PASTE PRODUCT

PHASE 2

3. GUIDE MIL-L-23398 FORM A AND MOLYKOTE 505

PHASE 2

4. LATCH MIL-L-23398 FORM A AND MOLYKOTE 505

PHASE 2

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-0 PHASE 3 INSPECTION FINAL RELEASE

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

NKF W/O:

SE-XXX

Date:

A/C TT: A/C TOTCYC:

Phase 3 inspection in accordance with RAYTHEON AIRCRAFT SCHEDULED INSPECTION PROGRAM, PHASE 3 INSPECTION shall be in use for documentation of the scope of work. Ref: MM 5-20-00.

Certifies that the work specified except as otherwise specified was carried out in accordance with PART – 145.50, and in respect to that work the aircraft is considered ready for release to service. CRS Signature:

CRS Approval:

Pos:

Action:

Sign

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-1 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: B. NOSE AVIONIC COMPARTMENT

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. VACCUM REGULATOR VALVE FILTER – INSPECT FOR BLOCKAGE

12-20-00 37-00-00

C. NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT – INSPECT ALL EXPOSED ELECTRICAL WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND SECURITY OF ATTACHMENT

AC.43.13.1B/2A

D. NOSE GEAR 1. WHEEL a) INSPECT WHEEL FOR WEAR, DAMAGE and CORROSION b) INSPECT WHEEL BEARINGS and RACES for WEAR, PITTING, CRACKS ,DISCOLORATION, RUST or other indications of damage.

32-40-00 CMM

2. TIRE a) INSPECT FOR WEAR AND DETEIORATION b) CHECK FOR CORRECT INFLATION

12-20-00 CMM

3. SHIMMY DAMPER – INSPECT FOR LEAKS, SECURITY AND ATTACHEMENT

12-20-00 32-20-00

4. NOSE GEAR DRAG BRACE STOP LUGS- INSPECT FOR CRACK, DAMAGE OR DIST.

12-20-00 32-20-00

5. NOSE GEAR STEERING STOP – INSPECT STEERING STOP FOR DAMAGE OR DISTORSION

12-20-00 32-20-00

6. LANDING AND TAXI LIGHTS – INSPECT FOR BROKEN LENSES OR BULBS

33-40-00

7. STEERING LINKAGE – INSPECT NOSE GEAR STEERING MECHANISM AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION

32-50-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-2 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: E. PILOTS COMPARTMENT

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. RETURN AIR INLET FILTERS – INSPECT FILTERS IN RETURN AIR INLET OF THE FORWARD VENT BLOWER

21-50-00

2. WINDSHIELD a) INSPECT WINDSHIELD FOR CRACKS AND VISIBILITY IMPAIRMENT b) INSPECT WINDSHIELD WEATHER SEAL (Silicone) FOR DEBONDING, CRACKS OR WEAR c) INSPECT WINDSHIELD WEATHER HUMP SEAL (Polysulfide) FOR DEBONDING, CRACKS OR WEAR d) INSPECT WINDSHIELD ATTACHMENT SCREWS FOR 20-INCH-POUNDS TORQUE

56-10-00

3. WINDOWS – INSPECT EXTERIOR SURFACE OF COCKPIT SIDE WINDOWS FOR DEEP SCRATCHES, CRACKS, CHIPS OR EXCESS CRAZING OR OTHER DAMAGE

56-15-00

4. ALTERNATE AIR VALVE – DRAIN OFF ALL MOISTURE

34-00-00

5. SEAT TRACKS – INSPECT SEAT TRACKS FOR DAMAGE AND WEAR

25-10-00

6. PORTABLE FIRE EXTINGUISHER – INSPECT THE BOTTLE FOR SIGNS OF DAMAGE AND MOUNT FOR SECURITY OF ATTACHMENT

26 CMM

7. SEATS, SEAT BELTS AND SHOULDER HARNESSES – INSPECT SEATS, SEAT BELTS AND SHOULDER HARNESSES FOR DETERIORATION

25-10-00

8. BRAKE FLUID RESERVOIR PRESSURE EQUALIZATION ORIFICE – INSPECT FOR BLOCKAGE

32-40-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-3 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: E. PILOTS COMPARTMENT, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

9. PILOTS COMPARTMENT – INSPECT SKIN, STRUCTURE, SEATS AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION. IF DAMAGE OR CORROSION IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

10. ELECTRICAL WIRING AND EQUIPMENT – INSPECT FOR CHAFING, DAMAGE, PROPER ROUTING OF WIRE BUNDLES AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

11. REFRIGERANT LINES AND SERVICE VALVES - INSPECT LINES FOR LEAKAGE, DAMAGE AND ATTACHMENT

21-50-00

12. RUDDER PEDALS a) INSPECT RUDDER PEDALS FOR WEAR, CLEARENCE AND ATTACHMENT b) INSPECT RUDDER PEDAL LINKAGE FOR WEAR, DAMAGE, ATTACHMENT AND OPERATION

27-20-00

13. FLIGHT CONTROL COMPONENTS, CABLES AND PULLEYS

a) INSPECT CONTROL SYSTEM COMPONENTS (pushrods, turnbuckles, end Fittings, castings etc.) FOR BULGES, SPLITS BENDS OR CRACKS WHICH ARE CONDITIONS FOR REPLACEMENT

b) INSPECT CONTROL CABLES, PULLEYS AND ASSOCIATED EQUIPMENT FOR WEAR, CRACKS, BREAKS, ATTACHMENT, ALIGNMENT, CLEARANCE AND PROPER OPERATION. REPLACE CABLES THAT HAVE MORE THAN THREE BROKEN WIRES IN ANY GIVEN THREE-FOOT CABLE LENGTH OR HAVE EVIDENCE OF CORROSION

27

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-4 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: E. PILOTS COMPARTMENT, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

14. BRAKE SYSTEM – INSPECT BRAKE SYSTEM COMPONENTS AND PLUMBING FOR LEAKAGE AND ATTACHMENT

32-40-00

15. INSTRUMENT PANEL, PLUMBING AND WIRING – INSPECT INSTRUMENT PANEL, SUBPANELS, PLACARDS, SHOCK MOUNTS AND INSTRUMENT PLUMBING FOR DAMAGE ATTACHMENT, CHAFING AND HOSES FOR HARDNESS OR CRACKS

39-10-00

16. CONTROL COLUMN a) INSPECT FOR WEAR, DAMAGE, CORROSION ATTACHMENT AND OPERATION b) INSPECT CONTROL WHEEL ADAPTER FOR CRACKS IN THE WELD AREA OF ADAPTER OR FORWARD SIDE OF CONTROL WHEEL c) INSPECT CONTROL WHEEL SWITCHES FOR CONDITION AND SECURITY OF ATTACHMENT

27-10-00

17. PEDESTAL a) INSPECT PEDESTAL COMPONENTS AND PLUMBING FOR DAMAGE ATTACHMENT AND CHAFING AND HOSES FOR HARDNESS OR CRACKS

39-10-00

b) INSPECT CONDITION LEVER CONTROL GATES FOR WEAR

76-00-00

18. PRESSURIZATION CONTROLLER a) INSPECT FOR SECURITY OF ATTACHMENT, PLUMBING AND WIRING FOR DAMAGE AND CONNECTION SECURITY b) INSPECT FILTER IN CONTROLLER ASSEMBLY LOCATED WITHIN THE PEDESTAL

21-30-00

19. EMERGENCY LANDING GEAR EXTENSION - INSPECT THE EMERGENCY EXTENSION HANDLE ASSEMBLY AND LINKAGE FROM THE HANDLE TO THE EMERGENCY EXTENSION PUMP FOR PROPER INSTALLATION, WEAR AND SECURITY OF ATTACHMENT

N/A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-5 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: E. PILOTS COMPARTMENT, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

20. ACCESS DOORS – INSPECT FOR FIT AND ATTACHMENT

N/A

21. HEATED WINDSHIELD – INSPECT HEATED WINDSHIELD ANTISTATIC COATING AND TAB BONDING

56-10-00

22. RELIEF TUBE a) INSPECT PLUMBING AND STORAGE BOX FOR CORROSION b) INSPECT RELIEF TUBE OUTLET AREA FOR CORROSION

N/A

23. DUAL BUS FEEDER AND FUEL PANEL DIODES – INSPECT DIODES PER INSPECTION PROCEDURE IN MAINTENANCE MANUAL

24-50-00

24. ALTITUDE WARNING SWITCH – PERFORM THE CABIN ALTITUDE WARNING PRESSURE SWITCH TEST

21-30-00

25. ENVIRONMENTAL SYSTEM a) INSPECT DUCTS FOR CONDITION AND SECURITY OF INSTALLATION b) CHECK DUCTS FOR EVIDENCE OF THERMAL LEAKS AND/OR DEGRADATION, SUCH AS DISCOLORATION OF DUCT INSULATOR, ADJACENT STRUCTURE OR COMPONENTS c) PHYSICALLY INSPECT DUCTS BY TOUCHING DUCTS, CHECKING FOR THERMAL DETERIORATION, DEFORMATION OF THE DUCTS, AND PROPER CONNECTION AT THE JOINTS

N/A

d) PERFORM THE BLEED AIR BYPASS VALVE OPERATIONAL CHECK PROCEDURE

21-40-00

e) PERFORM AIR-DUCT TEMPERATURE SENSE ELEMENT CHECKS PROCEDURE

21-60-00

f) PERFORM THE CABIN TEMPERATURE CONTROL BOX FUNCTIONAL TEST PROCEDURE

21-60-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-6 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: F. CABIN SECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. WINDOWS – INSPECT EXTERIOR SURFACES OF WINDOWS FOR DEEP SCRATCHES, CRACKS, CHIPS AND EXCESSIVE CRAZING OR OTHER DAMAGE

56-15-00

2. ROTATING OR (FLASHING) BEACON - INSPECT FOR CRACKED OR BROKEN LENSES

33-40-00

3. ACCESS DOORS – INSPECT FOR FIT AND ATTACHMENT

N/A

4. OUTFLOW AND SAFETY VALVES a) DRAIN OUTFLOW VALVE CONTROL LINE (TWO LOCATIONS)

12-20-00

b) INSPECT PLUMBING AND COMPONENTS FOR ATTACHMENT

21-30-00

c) INSPECT SAFETY VALVE SCREEN 12-20-00 d) INSPECT POPPET AND SEAT OF BOTH VALVES

12-20-00

e) PERFORM FUNCTIONAL TEST OF OUTFLOW AND SAFETY VALVES

21-30-00

5. AFT EVAPORATOR FILTERS – INSPECT AFT EVAPORATOR FILTER

21-50-00

6. SEATS, SEAT BELTS AND SHOULDER HARNESSES a) INSPECT SEAT BELTS AND SHOULDER HARNESS FOR DETERIORATION AND MISSING COMPONENTS b) INSPECT SHOULDER HARNESS ATTACHMENT POST FOR CRACKED, WARN BRITTLE OR MISSING GROMMETS

25-20-00

7. SEAT TRACKS – INSPECT SEAT TRACKS FOR DAMAGE AND WEAR

25-20-00

8. OXYGEN SYSTEM a) INSPECT OXYGEN SYSTEM INSTALLATION FOR DAMAGE AND SECURITY OF ATTACHMENT b) PERFORM THE APPROPRIATE OXYGEN SYSTEM FUNCTIONAL TEST

35-00-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-7 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: F. CABIN SECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

9. TOILET – INSPECT FOR SPILLAGE AND LEAKAGE BELOW THE TOILET

38-30-00

10. CABIN ENTRANCE DOOR a) INSPECT THE DOOR SEAL FOR CUTS, ABRASIONS AND SECURITY OF ATTACHMENT b) INSPECT DOOR SEAL SOLENOID VALVE AND PRESSURE REGULATOR VALVE FOR SECURITY AND ELECTRICAL CONNECTION c) INSPECT THE CABIN DOOR SUPPORT CABLES FOR WEAR, DAMAGE AND SECURITY d) INSPECT DOOR LATCHING MECHANISM AND CABLES FOR DAMAGE, DETERIORATION AND SECURITY OF ATTACHMENT

52-10-00

e) INSPECT UPPER LATCH HOOKS AND RETRAINING PINS FOR RIGGING, WEAR AND DAMAGE. (Pin removal and inspection Required). f) INSPECT UPPER LATCH HOOKS FOR PROPER TENSION g) INSPECT SIDE LATCH BOLTS (bayonets) AND ROLLERS FOR RIGGING AND FREEDOM OF MOVEMENT

52-10-00

h) INSPECT THE CABIN DOOR UNLOCKED ANNUNCIATOR SWITCH SPRING

52-70-00

11. AVIONICS EQUIPMENT AND RACKS (if installed) – INSPECT AVIONICS EQUIPMENT AND RACKS FOR SECURITY OF ATTACHMENT

N/A

12. BULKHEADS – INSPECT FOR WATER TRAPS N/A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-8 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: F. CABIN SECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

13. FLIGHT CONTROL COMPONENTS, CABLES AND PULLEYS a)INSPECT CONTROL SYSTEM COMPONENTS (pushrods, turnbuckles, end fittings, castings, etc) FOR BULGES, SPLITS, BENDS AND CRACKS WHICH ARE CONDITIONS FOR REPLACEMENT b) INSPECT CONTROL CABLES, PULLEYS AND ASSOCIATED EQUIPMENT FOR CRACKS, DAMAGE, ATTACHMENT, ALIGNMENT, CLEARANCE AND PROPER OPERATION. REPLACE CABLES THAT HAVE MORE THAN THREE BROKEN WIRES IN ANY GIVEN THREE-FOOT CABLE LENGTH OR HAVE EVIDENCE OF CORROSION

27

14. LANDING GEAR HYDRAULIC LINES – INSPECT FOR LEAKS, DAMAGE AND SECURITY OF ATTACHMENT

N/A

15. FLAP MOTOR AND DRIVES – INSPECT FOR DAMAGE AND ATTACHMENT

27-50-00

16. AILERON QUADRANT REGULATOR – INSPECT FOR SECURITY, ATTACHMENT, OPERATION AND TRAVEL

27-10-00

17. BELLY DRAIN VALVES – INSPECT FOR POSSIBLE OBSTRUCTIONS

N/A

18. CABIN WINDOW ATTACH FRAMES – PERFORM INSPECTION AND REPAIR OF WINDOW ATTACH FRAMES

56-15-00

19. CABIN SECTION AREA – INSPECT SKIN, STRUCTURE, SEATS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE OR CORROSION IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA.

AC.43.13-1B/2A

20. PNEUMATIC PRESSURE REGULATOR, VACUUM EJECTOR AND DEICER DISTRIBUTION VALVE-INSPECT EQUIPMENT AND PLUMBING FOR SECURITY

N/A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-9 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: F. CABIN SECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

21. CONTROL CABLE SEALS – INSPECT FOR DAMAGE, SECURITY, CLEANLINESS AND LUBRICATION

27

22. AUTOPILOT COMPONENTS – INSPECT COMPONENTS FOR SECURITY OF ATTACHMENT

22

23. RELIEF TUBE a) INSPECT PLUMBING AND STORAGE BOX FOR CORROSION b) INSPECT RELIEF TUBE OUTLET AREA FOR CORROSION

N/A

24. ANTENNAS – INSPECT ALL EXTERNAL ANTENNAS FOR LEADING EDGE EROSION AND CONDITION OF BASE SEALS

N/A

25. PORTABLE FIRE EXTINGUISHER – INSPECT BOTTLE FOR SIGNS OF DAMAGE AND SECURITY

26 CMM

26. CABIN DOORS AND EMERGENCY EXITS a) INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION. IF DAMAGE OR CORROSION IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

b) INSPECT CORNER AREAS OF EMERGENCY EXIT (removed) FOR CRACKS AND ABRASION IN AREA OF CURVATURE BETWEEN SEAL AND OUTHER FACE OF EXIT

52-20-00

27. EMERGENCY EXITS ( With door installed and properly rigged) a) INSPECT LATCHES FOR DAMAGE AND CHECK ALL MOVING PARTS FOR PROPER OPERATION b) CHECK FOR PROPER LATCH ADJUSTMENT AND SEAL OF CLOSED LATCHES

N/A

28. ELECTRICAL WIRING AND EQUIPMENT - INSPECT ALL EXPOSED ELECTRICAL WIRING AND EQUIPMENT FOR CHAFING DAMAGE AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-10 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: F. CABIN SECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

29. ENVIRONMENTAL SYSTEM a) INSPECT DUCTS FOR CONDITION AND SECURITY OF INSTALLATION b) CHECK DUCTS FOR EVIDENCE OF THERMAL LEAKS AND/OR DEGRADATION, SUCH AS DISCOLORATION OF DUCT INSULATOR, ADJACENT STRUCTURE OR COMPONENTS c) PHYSICALLY INSPECT DUCTS BY TOUCHING DUCTS, CHECKING FOR THERMAL DETERIORATION, DEFORMATION OF THE DUCTS, AND PROPER CONNECTION ET THE JOINTS

N/A

G. REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAINS – INSPECT REAR FUSELAGE DRAINS

53-10-00

2. ELT - BATTERY a) INSPECT FOR LEAKAGE, CORROSION OR LOOSE LEADS b) DETERMINE REMAINING USEFUL LIFE

25-60-00

3. NAVIGATION LIGHTS AND ROTATING OR FLASHING BEACONS – INSPECT FOR BROKEN OR CRACKED LENSES

33-40-00

4. ACCESS DOORS – INSPECT FOR FIT AND SECURITY OF ATTACHMENT

N/A

5. VENTRAL FIN DRAIN HOLES – INSPECT THE DRAIN HOLES IN THE BOTTOM OF THE VENTRAL FIN FOR OBSTRUCTIONS

53-10-00

6. DEICER BOOTS – INSPECT FOR DETERI- ORATION, DAMAGE AND ATTACHMENT

N/A

7. RUDDER AND TRIM TAB DRAIN HOLES – INSPECT THE DRAIN HOLES FOR OBSTRUCTIONS

N/A

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

9. RUDDER BOOST FILTER (With Autopilot) – REPLACE FILTER

27-21-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-11 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: H. LEFT-HAND OUTBOARD WING

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - DETERMINE THAT THE DRAIN HOLES ARE OPEN IN THE WING CENTER SECTION AND OUTBOARD WING UPPER ATTACHMENT FITTINGS

57-00-00

3. LIGHTS a) INSPECT THE NAVIGATION AND RECOGNITION LIGHTS FOR BROKEN OR CRACKED LENSES b) INSPECT THE STROBE LIGHT FOR BROKEN OR CRACKED LENSES

33-40-00

4. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE WING FOR LEAKAGE

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT EXTERIOR OPENINGS OF VENTS FOR OBSTRUCTIONS

28-10-00

5. INTEGRAL FUEL TANK – INSPECT THE EXTERIOR SURFACE OF THE INTEGRAL TANK ACCESS DOORS FOR LEAKS

28-10-00

6. DEICER BOOTS – INSPECT EXTERIOR SURFACE FOR DETERIORATION, DAMAGE AND ATTACHMENT

30-10-00

7. ACCESS DOORS (INSPECTION PANELS) – INSPECT FOR FIT AND ATTACHMENT

6-50-00

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

9. AILERON AND TRIM TAB . CHECK TRIM TAB FREE PLAY

27-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-12 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION I. LEFT HAND WING CENTER SECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE CENTER SECTION FOR LEAKS

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT THE EXTERIOR OPENINGS OF THE VENTS FOR OBSTRUCTIONS

28-10-00

3. ACCESS DOORS (INSPECTION PANELS) - INSPECT FOR FIT AND ATTACHMENT

6-50-00

4. ENGINE FIRE EXTINGUISHER a) INSPECT PLUMBING FOR SECURITY OF ATTACHMENT b) CHECK FIRE BOTTLE PRESSURE GAUGE

26-20-00

5. FUEL PUMPS – INSPECT THE PUMPS FOR LEAKS AND SECURITY OF ATTACHMENT

28-20-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-13 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: J. LEFT-HAND MAIN LANDING GEAR AREA

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. WHEELS a) INSPECT WHEELS FOR WEAR, DAMAGE AND CORROSION

N/A

b) INSPECT WHEEL BEARINGS AND RACES FOR WEAR, PITTING, CRACKS, DISCOLORATION, RUST OR OTHER INDICATIONS OF DAMAGE

CMM

2. BRAKES – INSPECT BRAKE DISCS, LININGS AND PLUMBING FOR WEAR DAMAGE, LEAKS, CORROSION AND SECURITY OF ALL COMPONENTS

32-40-00 CMM

3. BRAKE DEICING ( if installed) a) INSPECT MANIFOLD FOR BLOCKED ORIFICES b) INSPECT EXTERIOR OF LINES, HOSES AND CONNECTIONS FOR LEAKAGE AND ATTACHMENT

30-21-00

4. TIRES – INSPECT TIRES FOR WEAR, DETERIORATION AND CORRECT INFLATION

12-20-00 CMM

5. LEFT-HAND MAIN LANDING GEAR STRUT – CHECK STRUT FOR LEAKS AND PROPER EXTENSION

12-20-00

6. ELECTRICAL WIRING AND EQUIPMENT – INSPECT EXPOSED WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND PROPER ROUTING AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

7. MAIN GEAR ACTUATOR a) ACTUATOR (Mechanical Gear) 1. INSPECT ACTUATOR SUPPORT BRACKETS FOR VISIBLE DAMAGE, WEAR AND LOOSE AND MISSING FASTENERS 2. INSPECT ACTUATOR FOR LEAKAGE OF INTERNAL LUBRICANT

32-30-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-14 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: J. LEFT-HAND MAIN LANDING GEAR AREA, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

8. DRAG BRACE a) INSPECT FOR SECURITY OF ATTACH FITTINGS

32-10-00

b) INSPECT DOWNLOCK BOLTS FOR PROPER TORQUE ( finger-tight and safety-wired)

CMM

9. LEFT-HAND MAIN LANDING GEAR AREA – INSPECT WHEEL AND GEAR DOOR STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

9. LEFT-HAND MAIN LANDING GEAR AREA – INSPECT WHEEL AND GEAR DOOR STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

K. LEFT-HAND ENGINE 1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FIREWALL FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

4. PROPELLERS – INSPECT FOR DAMAGE AND ATTACHMENT (spinner removal required)

61-10-00 61-11-00 61-12-00

5. ENGINE OIL FILTER – INSPECT FOR METAL PARTICLES

P&W

6. LEFT-HAND ENGINE – INSPECT ALL SYSTEMS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. CHECK ALL TUBES AND HOSES FOR GENERAL CONDITION, LEAKS AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-15 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: L. RIGHT-HAND OUTBOARD WING

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - DETERMINE THAT THE DRAIN HOLES ARE OPEN IN THE WING CENTER SECTION AND OUTBOARD WING UPPER ATTACHMENT FITTINGS

57-00-00

3. LIGHTS a) INSPECT THE NAVIGATION AND RECOGNITION LIGHTS FOR BROKEN OR CRACKED LENSES b) INSPECT THE STROBE LIGHT FOR BROKEN OR CRACKED LENSES

33-40-00

4. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE WING FOR LEAKAGE

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT EXTERIOR OPENINGS OF VENTS FOR OBSTRUCTIONS

28-10-00

5. INTEGRAL FUEL TANK – INSPECT THE EXTERIOR SURFACE OF THE INTEGRAL TANK ACCESS DOORS FOR LEAKS

28-10-00

6. DEICER BOOTS – INSPECT EXTERIOR SURFACE FOR DETERIORATION, DAMAGE AND ATTACHMENT

30-10-00

7. ACCESS DOORS (INSPECTION PANELS) – INSPECT FOR FIT AND ATTACHMENT

6-50-00

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

9. AILERON AND TRIM TAB . CHECK TRIM TAB FREE PLAY

27-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-16 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: M. RIGHT-HAND WING CENTER SECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE CENTER SECTION FOR LEAKS

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT THE EXTERIOR OPENINGS OF THE VENTS FOR OBSTRUCTIONS

28-10-00

3. ACCESS DOORS (INSPECTION PANELS) - INSPECT FOR FIT AND ATTACHMENT

6-50-00

4. BATTERY a) SERVICE BATTERY AS REQUIRED

12-20-00

b) REMOVE BATTERY AND INSPECT THE BATTERY BOX, CABLES AND VENT TUBES FOR DETERIORATION OR OBSTRUCTIONS

24-31-00

5. ENGINE FIRE EXTINGHUISER a) INSPECT PLUMBING FOR SECURITY OF ATTACHMENT b) CHECK FIRE BOTTLE PRESSURE GAUGE

26-20-00

6. FUEL PUMPS – INSPECT THE PUMPS FOR LEAKS AND SECURITY OF ATTACHMENT

28-20-00

N. RIGHT-HAND MAIN LANDING GEAR AREA 1. WHEELS a) INSPECT WHEELS FOR WEAR, DAMAGE AND CORROSION

N/A

b) INSPECT WHEEL BEARINGS AND RACES FOR WEAR, PITTING, CRACKS, DISCOLORATION, RUST OR OTHER INDICATIONS OF DAMAGE

CMM

2. BRAKES – INSPECT BRAKE DISCS, LININGS AND PLUMBING FOR WEAR DAMAGE, LEAKS, CORROSION AND SECURITY OF ALL COMPONENTS

32-40-00 CMM

3. BRAKE DEICING ( if installed) a) INSPECT MANIFOLD FOR BLOCKED ORIFICES b) INSPECT EXTERIOR OF LINES, HOSES AND CONNECTIONS FOR LEAKAGE AND ATTACHMENT

30-21-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-17 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: N. RIGHT-HAND MAIN LANDING GEAR AREA, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. TIRES – INSPECT TIRES FOR WEAR, DETERIORATION AND CORRECT INFLATION

12-20-00 CMM

5. RIGHT-HAND MAIN LANDING GEAR STRUT – CHECK STRUT FOR LEAKS AND PROPER EXTENSION

12-20-00

6. ELECTRICAL WIRING AND EQUIPMENT – INSPECT EXPOSED WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND PROPER ROUTING AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

7. MAIN GEAR ACTUATOR a) ACTUATOR (Mechanical Gear) 1. INSPECT ACTUATOR SUPPORT BRACKETS FOR VISIBLE DAMAGE, WEAR AND LOOSE AND MISSING FASTENERS 2. INSPECT ACTUATOR FOR LEAKAGE OF INTERNAL LUBRICANT

32-30-00

8. DRAG BRACE a) INSPECT FOR SECURITY OF ATTACH FITTINGS

32-10-00

b) INSPECT DOWNLOCK BOLTS FOR PROPER TORQUE ( finger-tight and safety-wired)

CMM

9. RIGHT-HAND MAIN LANDING GEAR AREA – INSPECT WHEEL AND GEAR DOOR STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE IS FOUND, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-18 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: O. RIGHT-HAND ENGINE

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FIREWALL FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

4. PROPELLERS – INSPECT FOR DAMAGE AND ATTACHMENT (spinner removal required)

61-10-00 61-11-00 61-12-00

5. ENGINE OIL FILTER – INSPECT FOR METAL PARTICLES

P&W

6. RIGHT-HAND ENGINE – INSPECT ALL SYSTEMS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. CHECK ALL TUBES AND HOSES FOR GENERAL CONDITION, LEAKS AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

P. LANDING GEAR RETRACTION NOTE: Mechanical and Hydraulic Landing Gear Systems – Since battery voltage is not sufficient to properly cycle The landing gear, use only an external power source Capable of delivering and maintaining 28.25 +/- 0.25 Volts throughout the extension and retraction cycles when performing the landing gear retraction inspection

N/A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-19 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: P. LANDING GEAR RETRACTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. RETRACT MECHANISM – CHECK RETRACTION SYSTEM FOR PROPER OPERATION OF ALL COMPONENTS THROUGH AT LEAST TWO COMPLETE CYCLES

32

2. DOORS AND LINKAGE a) CHECK DOOR FOR DAMAGE, OPERATION AND FIT b) CHECK DOOR LINKAGE FOR WEAR, DAMAGE AND RIGGING

32

3. DOWNLOCK INDICATOR SWITCHES a) CHECK FOR SECURITY AND PROPER OPERATION OF SWITCHES b) CLEAN TERMINALS AND CONNECTORS AS REQUIRED c) CHECK WIRING FOR DAMAGE AND SECURITY OF CONNECTION

32-60-00

4. UPLOCK INDICATOR SWITCHES a) CHECK FOR SECURITY AND PROPER OPERATION OF SWITCHES b) CLEAN TERMINALS AND CONNECTORS AS REQUIRED c) CHECK WIRING FOR DAMAGE AND SECURITY OF CONNECTION

32-60-00

5. WARNING HORN – CHECK OPERATION 32-60-00 6. MAIN GEAR DOWNLOCKS – CHECK LOCKING MECHANISM FOR POSITIVE ENGAGEMENT IN EXTENDED POSITION

32

7. SAFETY SWITCH – CHECK FOR PROPER OPERATION

32-60-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-20 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: P. LANDING GEAR RETRACTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

8. ACTUATORS – CHECK FOR NOISE, BINDING AND PROPER RIGGING

32-30-00 32-31-00

9. LIMIT SWITCHES – (Mechanical Gear) a) CHECK FOR CORRECT ADJUSTMENT b) CHECK FOR SECURITY OF ATTACHMENT

32-60-00

10. EMERGENCY EXTENSION (Mechanical Gear) CHECK SYSTEM FOR FREEDOM OF OPERATION AND POSITIVE ENGAGEMENT OF DOWNLOCKS. CAUTION: Do not continue operation after receiving a gear-down indication on all gears. Further movement of the handle could damage the drive mechanism and prevent subsequent electrical gear retraction. The landing gear cannot be retracted manually.

32-30-00

11. NOSE GEAR RETRACT CHAIN (Mechanical Gear) a) CHECK FOR PROPER CHAIN TENSION b) CHECK NOSE GEAR AND NOSE GEAR LINKAGE CLEARANCE FROM ELECTRICAL WIRES AND OBSTRUCTIONS

32-30-00

12. PLACARDS – CHECK THAT ALL PLACARDS ARE IN PLACE AND ARE LEGIBLE

11-00-00

13. LANDING GEAR RETRACTION – INSPECT ALL LANDING GEAR COMPONENTS AND ATTACHING HARDWARE, STRUCTURE AND HYDRAULIC LINES FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-21 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

NOTE: The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual for the engine start and run procedures.

N/A

1. FIREWALL SHUTOFF FUEL VALVES - CHECK FOR PROPER OPERATION

Ref: NOTE

2. CROSSFEED FUEL VALVE – CHECK FOR PROPER OPERATION

Ref: NOTE

3. STANDBY PUMPS – CHECK FOR PROPER OPERATIONS

Ref: NOTE

4. STARTER GENERATOR a) CHECK STARTER FOR OPERATION b) CHECK GENERATOR FOR OUTPUT

Ref: NOTE

5. IGNITION a) CHECK FOR PROPER OPERATION b) CHECK FOR ANNUNCIATOR PANEL LIGHT ILLUMINATION

Ref: NOTE

6. ENGINE OIL – CHECK FOR PROPER PRESSURE AND TEMPERATURE LIMITS

Ref: NOTE

7. FUEL QUANTITY GAGES – CHECK OPERATION

Ref: NOTE

8. INTERSTAGE TURBINE TEMPERATURE – CHECK FOR CORRECT LIMITS ON ENGINE START

Ref: NOTE

9. VACUUM SYSTEM – CHECK FOR CORRECT LIMITS

Ref: NOTE

10. PNEUMATIC PRESSURE GAGE – CHECK FOR CORRECT PRESSURE

Ref: NOTE

11. PNEUMATIC SYSTEM SHUTOFF VALVES – CHECK FOR PROPER OPERATION

Ref: NOTE

12. GYRO INSTRUMENTS – CHECK FOR ERRATIC OR NOISY OPERATION

Ref: NOTE

13. PROPELLERS – PERFORM FLIGHT IDLE TOQUE CHECK

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-22 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

14. AUTOFEATHERING CHECK – Refer to: AUTOFEATHERING SYSTEM OPERATIONAL CHECK

61-21-00

15. PROPELLER SYNCHROPASER – Refer to: AUTOFEATHER SYSTEM OPERATIONAL CHECK

61-21-00

16. PROPELLER GOVERNOR – CHECK GOVERNOR OPERATION ( Including feathering And reversing)

Ref: NOTE

17. IDLE RPM – CHECK FOR CORRECT RPM ( both high and low rpm)

Ref: NOTE

18 AC INVERTERS – CHECK FOR PROPER OPERATION

Ref: NOTE

19. RUDDER BOOST – CHECK FOR PROPER OPERATION

Ref: NOTE

20. AUTO-IGNITION a) CHECK FOR PROPER OPERATION b) CHECK FOR ANNUNCIATOR PANEL ILLUMINATION

Ref: NOTE

21. PROPELLER DEICER – CHECK FOR PROPER OPERATION AND CYCLING. Refer to chapter 30 of the Beech King Air Series Component Maintenance Manual

N/A

22. ENGINE INTERIAL ANTI-ICER – CHECK FOR PROPER OPERATION AND RIGGING

Ref: NOTE

23. SURFACE DEICE SYSTEM – CHECK FOR PROPER OPERATION AND CYCLING

Ref: NOTE

24. BRAKE DEICE SYSTEM (if installed) – CHECK FOR PROPER OPERATION WITH ENGINES RUNNING

Ref: NOTE

25. ELECTRICAL SYSTEM – PERFORM FUNCTIONAL CHECKS

Ref: NOTE

26. ENVIRONMENTAL SYSTEM – CHECK FOR PROPER OPERATION IN: a) MANUAL HEAT MODE b) MANUAL COOL MODE c) AUTOMATIC MODE

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-23 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

28. AUTOPILOT – CHECK FOR PROPER OPERATION AS OUTLINED BY THE APPLICABLE Beech Super King Air 200 and B200 Pilots Operating Handbook or SCAA Approved Airplane Flight Manual Supplement

Ref: NOTE

29. STALL WARNING – CHECK FOR PROPER OPERATION

Ref: NOTE

30. ENGINE FIRE DETECTORS – Perform system test according to instructions found in the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual

N/A

31. ENGINE FIRE EXTINGUISHERS – Perform system test according to instructions found in the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual

N/A

32. PRESSURIZATION SYSTEM – CHECK FOR PROPER OPERATION Refer to the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual and perform system test

N/A

33. AUXILIARY FUEL TRANSFER JET PUMPS – CHECK FOR PROPER OPERATION

Ref: NOTE

34. CONDITION LEVER – CHECK FOR CLEAN SHUTDOWN AT IDLE-CUT-OFF

Ref: NOTE

35. PITOT TUBE – CHECK FOR PROPER HEATING AT THE UNIT AND FOR OBSTRUCTIONS

Ref: NOTE

36. LANDING AND TAXI LIGHTS – CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

37. OUTBOARD WING LIGHTS ( R/H AND L/H) - CHECK OPERATION OF ALL NAVIGATION AND STROBE LIGHTS

Ref: NOTE

38. COCKPIT LIGHTS – CHECK OPERATION OF ALL COCKPIT LIGHTS

Ref: NOTE

39. EFIS COOLING BLOWERS (if installed) – CHECK OPERATION

Ref: NOTE

40. ELECTRIC ELEVATOR TRIM – CHECK FOR PROPER OPERATION

Ref: NOTE

41. ENGINE AND PROPELLER CONTROLS – CHECK FOR FREEDOM OF MOVEMENT FULL TRAVEL AND FRICTION-LOCK OPERATION

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-24 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

42. STATIC SYSTEM – INSPECT ALTERNATE AIR VALVE FOR OPERATION

Ref: NOTE

43. WINDSHIELD – PERFORM HEATED OPERATIONAL CHECK

Ref: NOTE

44. THRESHOLD LIGHT – CHECK FOR PROPER OPERATION

Ref: NOTE

45. AUXILIARY ELECTRIC HEAT (if installed) – CHECK FOR PROPER OPERATION OF THE ELECTRIC HEAT SYSTEM

Ref: NOTE

46. CABIN AND COMPARTMENT LIGHTS – CHECK FOR PROPER OPERATION

Ref: NOTE

47. PILOTS AN COPILOTS SEATS, SEATS BELTS- AND SHOULDER HARNESSES – CHECK SEAT ADJUSTMENT MECHANISM, SEAT BELTS AND SHOULDER HARNESS INERTIA REEL FOR OPERATION

Ref: NOTE

48. CABIN SEATS, SEAT BELTS AND SHOULDER HARNESSES – CHECK SEAT ADJUSTMENT MECHANISM, SEAT BELTS AND SHOULDER HARNESS INERTIA REEL FOR OPERATION

Ref: NOTE

49. CABIN ENTRANCE DOOR: a) CHECK THAT FOLDING STEPS DO NOT FOLD TOO SOON AND THAT THEY FOLD PROPERLY WITHOUT INTERFERENCE b) CHECK CABIN DOOR UNLOCK ANNUNCIATOR FOR PROPER OPERATION c) INSPECT CABIN DOOR DAMPER FOR LEAKAGE AND PROPER OPERATION

Ref: NOTE

50. EMERGENCY EXIT ( WITH DOOR INSTALLED ) a) CHECK EMERGENCY RELEASE HANDLES (inside and outside) AND LATCH MECHANISM FOR OPERATION b) CHECK THAT LATCHES OPEN AND CLOSE FREELY

Ref: NOTE

51. EMPENNAGE CONTROL SURFACES a) CHECK FOR FREEDOM OF MOVEMENT b) CHECK OPTIONAL TRIM ACTUATORS AND MOTORS FOR SMOOTHNESS OF OPERATION

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-25 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

52. REAR FUSELAGE AND EMPENNAGE LIGHTS - CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

53. AILERON (LH AND RH) – CHECK FOR FREEDOM OF MOVEMENT

Ref: NOTE

54. AILERON TRIM TAB – CHECK TRIM TAB ACTUATOR FOR SMOOTHNESS OF OPERATION AND ATTACHMENT

Ref: NOTE

55. FUEL TANK HEATED VENTS (LH AND RH) – CHECK THE OPERATION OF THE HEATED VENTS. THEY SHOULD BE WARM TO THE TOUCH

Ref: NOTE

56. STALL WARNING HEAT – CHECK FOR PROPER OPERATION

Ref: NOTE

57. FLAPS AND ACTUATORS ( Inboard, Outboard, LH and RH) – CHECK FLAPS FOR NOISY OR ERRATIC OPERATION

Ref: NOTE

58. WING CENTER SECTION LIGHTS – CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

59. ENGINE INDUCTION SYSTEM (LH AND RH)- CHECK THE INERTIAL VANE AND BYPASS DOOR FOR MOVEMENT WITH THE MAIN AND STANDBY ACTUATOR MOTORS.

Ref: NOTE

60. EXTERNAL POWER RELAY – CHECK FOR PROPER OPERATION

Ref: NOTE

R. POST INSPECTIONS ITEMS 1. AIRPLANE CLEANED AND SERVICED AS REQUIRED

12-20-00

2. LUBRICATE AS NECESSARY 12-20-00 3. ENGINE INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST – CHECK FOR OIL LEAKS, SECURITY AND ATTACHMENT OF ALL COMPONENTS

4. AIRWORTHINESS DIRECTIVES AND SERVICE BULLETINS – MUST BE REVIEWED AND COMPLIED WITH AS REQUIRED

5. ADDITIONAL INSPECTION REQUIREMENTS- ENSURE THAT SPECIAL INSPECTION REQUIREMENTS ARE COMPLIED WITH AT THE APPROPRIATE INTERVALS

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-26 PHASE 3 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: R. POST INSPECTIONS ITEMS, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

6. IN-FLIGHT WORKSHEETS – ALL DISCREPANCIES NOTED BY THE PILOT MUST BE CHECKED AND CORRECTED AS REQUIRED

7. EMERGENCY LOCATOR TRANSMITTER – CHECK FOR PROPER OPERATION AND ENSURE ELT IS ARMED BEFORE RETURNING AIRPLANE TO SERVICE

25-60-00

8. OXYGEN SYSTEM PRESSURE – CHECK FOR PROPER PRESSURE

12-10-00

9. EMERGENCY AND SURVIVAL EQUIPMENT- ENSURE ALL NECESSARY EMERGENCY AND SURVIVAL EQUIPMENT IS INSTALLED IN THE AIRPLANE AND IS SERVICEABLE

10. PLACARDS – DETERMINE THAT ALL REQUIRED PLACARDS ARE IN PLACE AND LEGIBLE

11-20-00 POH

11. LOGBOOK ENTRY – ENSURE THAT LOG BOOKS ARE FILLED OUT PROPERLY

MME

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-27 PHASE 3 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: NOSE LANDING GEAR

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1 WHEEL BEARINGS MOBIL AVIATION GREASE SHC 100

PHASE 3

2 GREASE FITTINGS MIL-G-81322 PHASE 3 3. NOSE WHEEL STEERING

MECHANISM MIL-G-81322 GREASE

PHASE 3

4. UPPER AND LOWER NOSE GEAR STRUT BEARING

AEROSHELL 17

PHASE 3

5. DRAG BRACE BOLTS WITH GREASE FITTINGS. ROTATE BOLT WITH WRENCH, IF UNABLE TO ROTATE, REMOVE AND CLEAN Note: Grease must appear at both ends of bolt. If not, remove and clean grease passage.

MIL-G-81322 PHASE 3

CAUTION: DO NOT MIX different brands of grease as this will cause decreased bearing life. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication. NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-28 PHASE 3 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: MAIN LANDING GEAR

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. HIGH FLOTATION GEAR DOOR LINKAGE

LPS No: 3 Metal Protector

PHASE 3

2. GREASE FITTINGS MIL-G-81322 PHASE 3 3. DOOR HINGES AND

RETRACT LINKAGE MIL-L-7870 PHASE 3

4. WHEEL BEARINGS MOBIL AVIATION GREASE SHC 100

PHASE 3

5. DRAG LEG HOOK, SPRING AND GUIDE

LPS No: 3 Metal Protector (Apply Sparingly)

PHASE 3

6. DRAG BRACE BOLTS WITH GREASE FITTINGS. ROTATE BOLT WITH WRENCH, IF UNABLE TO ROTATE, REMOVE AND CLEAN Note: Grease must appear at both ends of bolt. If not, remove and clean grease passage.

MIL-G-81322 PHASE 3

7 RETRACT ACTUATOR CLEVIS

AEROSHELL 17

PHASE 3

8. DOWNLOCK HOOK AND PIN

PERMASLICK G or an airdrying solid film lubricant per MIL-L-23398

PHASE 3

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-29 PHASE 3 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: RUDDER CONTROL,

LANDING GEAR RETRACT (MECHANICAL) SYSTEMS LUBRICATION

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. RUDDER TRIM TAB TUBE

MIL-L-7870 PHASE 3

2. RUDDER TRIM TAB HINGE

MIL-L-7870 PHASE 3

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-30 PHASE 3 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: AILERON AND FLAP

CONTROL SYSTEM LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. AILERON TRIM TAB HINGE

BRAYCO 300/LPS-1

PHASE 3

2. AILERON TRIM TAB TUBE END

MIL-L-7870 PHASE 3

3. FLAP TRACKS Spray with a dry lubricant

PHASE 3

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-31 PHASE 3 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: CONTROL COLUMN,

RUDDER AND ELEVATOR CONTROL SYSTEMS LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. ELEVATOR TRIM TAB TUBE

MIL-L-7870 PHASE 3

2. ELEVATOR TRIM TAB HINGES

BRAYCO 300 PHASE 3

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-32 PHASE 3 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: ENGINE CONTROL

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. CONTROL ROD ENDS MIL-G-23827 PHASE 3 2. CAM PLATES AND PIN Lubriplate No.

130AA PHASE 3

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-33 PHASE 3 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: PROPELLER

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. PROPELLER BLADE BEARINGS (2 lube fittings per blade)

Aeroshell Grease No. 6, Aeroshell Grease No 7, Aeroshell Grease No. 22, Exxon 5114EP, Rayco 22C as defined by the manufacturers decal on the piston hub of the propeller

PHASE 3

2 LOW PITCH STOP RODS (3 per propeller)

Marvel Mystery Oil

PHASE 3

WARNING: Remove the lubrication fitting opposite the one being serviced. Failure to do so could result in damage to the propeller bearings and seals.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 5-34 PHASE 3 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: EMERGENCY EXIT AND

CABIN DOOR LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. CABIN DOOR: Latching Mechanism (pins included)

MIL-L-7870 OIL

PHASE 3

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-0 PHASE 4 INSPECTION FINAL RELEASE

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

NKF W/O:

SE-XXX

Date:

A/C TT: A/C TOTCYC:

Phase 4 inspection in accordance with RAYTHEON AIRCRAFT SCHEDULED INSPECTION PROGRAM, PHASE 4 INSPECTION shall be in use for documentation of the scope of work. Ref: MM 5-20-00.

Certifies that the work specified except as otherwise specified was carried out in accordance with PART – 145.50, and in respect to that work the aircraft is considered ready for release to service. CRS Signature:

CRS Approval:

Pos:

Action:

Sign

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-1 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: A. NOSE SECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. NOSE SECTION – INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION. IF DAMAGE OR CORROSION IS FOUND IN A GIVEN AREA CHECK THE ADJACENT AREA

N/A

2. RADOME – INSPECT THE EXTERIOR SURFACE FOR CRACKS IN THE PAINT AND FIBERGLASS SUBSTRATE

N/A

B. NOSE AVIONICS COMPARTMENT 1. VACCUM REGULATOR VALVE FILTER – INSPECT FOR BLOCKAGE

12-20-00 37-00-00

2. INSTRUMENT AIR FILTER – INSPECT FOR CLEANLINESS

12-20-00 37-00-00

3. AVIONICS EQUIPMENT AND RACKS - INSPECT FOR SECURITY OF ATTACHMENT

N/A

4. AVIONICS COMPARTMENT AREA - INSPECT FOR CORROSION, TRAPPED WATER AND INDICATIONS OF WATER LEAKAGE

N/A

5. ELECTRICAL WIRING AND EQUIPMENT – INSPECT FOR CHAFING, DAMAGE, PROPER ROUTING OF WIRE BUNDLES AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

6. DOORS, FASTENERS AND SEAL – INSPECT SEAL FOR DETERIORATION AND DOORS AND LATCHES FOR PROPER ADJUSTMENT AND FIT

N/A

7. NOSE AVIONICS COMPARTMENT – INSPECT SKIN, STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

C. NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT – INSPECT ALL EXPOSED ELECTRICAL WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND SECURITY OF ATTACHMENT

AC.43.13.1B/2A

2. FORWARD EVAPORATOR FILTER - INSPECT FORWARD EVAPORATOR FILTER

21-50-00

3. CONDENSER BLOWER – INSPECT FITTINGS FOR DIRT, GREASE, MOISTURE AND SECURITY OF ATTACHMENT

21-50-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-2 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: C. NOSE LANDING GEAR AREA, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. REFRIGERANT LINES, SERVICE VALVES AND HIGH PRESSURE RELIEF VALVE – INSPECT LINES AND VALVES FOR LEAKAGE, DAMAGE ATTACHMENT AND SURFACE CORROSION

21-50-00

5. NOSE LANDING GEAR AREA – INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION. IF DAMAGE OR CORROSION IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

D. NOSE GEAR 1. WHEEL a) INSPECT WHEEL FOR WEAR, DAMAGE and CORROSION b) INSPECT WHEEL BEARINGS and RACES for WEAR, PITTING, CRACKS ,DISCOLORATION, RUST or other indications of damage.

32-40-00 CMM

2. TIRE a) INSPECT FOR WEAR AND DETEIORATION b) CHECK FOR CORRECT INFLATION

12-20-00 CMM

3. SHIMMY DAMPER – INSPECT FOR LEAKS, SECURITY AND ATTACHEMENT

12-20-00 32-20-00

4. NOSE GEAR DRAG BRACE STOP LUGS- INSPECT FOR CRACK, DAMAGE OR DIST.

12-20-00 32-20-00

5. NOSE GEAR STEERING STOP – INSPECT STEERING STOP FOR DAMAGE OR DISTORSION

12-20-00 32-20-00

6. LANDING AND TAXI LIGHTS a) INSPECT FOR BROKEN LENSES OR BULBS b) CONFIRM CORRECT FOCUS OF LANDING AND TAXI LIGHTS

33-40-00

7. NOSE GEAR LOWER DRAG LEG – REMOVE NOSE GEAR DRAG BRACE BOLT AND INSPECT LOWER DRAG LEG HOLE FOR CORROSION AND WEAR

CMM

8. NOSE GEAR ACTUATOR a) INSPECT ACTUATOR SUPPORT BRACKETS FOR DAMAGE, CRACKS AND LOOSE OR MISSING FASTENERS b) INSPECT ACTUATOR AND PLUMBING FOR LEAKAGE

32

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-3 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION: D. NOSE GEAR, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

9. NOSE GEAR COMPONENTS – INSPECT ALL COMPONENTS AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND SURFACE CORROSION

32

10. NOSE GEAR – INSPECT NOSE GEAR, ATTACHING STRUCTURE AND ALL COMPONENTS FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

E. PILOTS COMPARTMENT 1. RETURN AIR INLET FILTERS – INSPECT FILTERS IN RETURN AIR INLET OF THE FORWARD VENT BLOWER

21-50-00

2. WINDSHIELD a) INSPECT WINDSHIELD FOR CRACKS AND VISIBILITY IMPAIRMENT b) INSPECT WINDSHIELD WEATHER SEAL (Silicone) FOR DEBONDING, CRACKS OR WEAR c) INSPECT WINDSHIELD WEATHER HUMP SEAL (Polysulfide) FOR DEBONDING, CRACKS OR WEAR d) INSPECT WINDSHIELD ATTACHMENT SCREWS FOR 20-INCH-POUNDS TORQUE

56-10-00

3. WINDOWS – INSPECT EXTERIOR SURFACE OF COCKPIT SIDE WINDOWS FOR DEEP SCRATCHES, CRACKS, CHIPS OR EXCESS CRAZING OR OTHER DAMAGE

56-15-00

4. ALTERNATE AIR VALVE – DRAIN OFF ALL MOISTURE

34-00-00

5. SEAT TRACKS – INSPECT SEAT TRACKS FOR DAMAGE AND WEAR

25-10-00

F. CABIN SECTION 1. WINDOWS – INSPECT EXTERIOR SURFACES OF WINDOWS FOR DEEP SCRATCHES, CRACKS, CHIPS AND EXCESSIVE CRAZING OR OTHER DAMAGE

56-15-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-4 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION F. CABIN SECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

2. ROTATING OR (FLASHING) BEACON - INSPECT FOR CRACKED OR BROKEN LENSES

33-40-00

3. ACCESS DOORS – INSPECT FOR FIT AND ATTACHMENT

N/A

4. OUTFLOW AND SAFETY VALVES – DRAIN CONTROL LINE

12-20-00

5. SEAT TRACKS – INSPECT SEAT TRACKS FOR DAMAGE AND WEAR

25-20-00

6. PRESSURIZATION DUCTS – INSPECT FOR SECURITY OF ATTACHMENT

21-20-00

7. FLAPPER VALVE – CHECK FOR PROPER OPERATION AND EXCESSIVE AIR NOISE

21-20-00

G. REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAINS – INSPECT REAR FUSELAGE DRAINS

53-10-00

2. ELT - BATTERY a) INSPECT FOR LEAKAGE, CORROSION OR LOOSE LEADS b) DETERMINE REMAINING USEFUL LIFE

25-60-00

3. NAVIGATION LIGHTS AND ROTATING OR FLASHING BEACONS – INSPECT FOR BROKEN OR CRACKED LENSES

33-40-00

4. ACCESS DOORS – INSPECT FOR FIT AND SECURITY OF ATTACHMENT

N/A

5. VENTRAL FIN DRAIN HOLES – INSPECT THE DRAIN HOLES IN THE BOTTOM OF THE VENTRAL FIN FOR OBSTRUCTIONS

53-10-00

6. DEICER BOOTS – INSPECT FOR DETERI- ORATION, DAMAGE AND ATTACHMENT

N/A

7. RUDDER AND TRIM TAB DRAIN HOLES – INSPECT THE DRAIN HOLES FOR OBSTRUCTIONS

N/A

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-5 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION G. REAR FUSELAGE AND EMPENNAGE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

9. EMPENNAGE AND CONTROL SURFACES a) CHECK ELEVATOR TRIM TAB FREE PLAY b) CHECK RUDDER TRIM TAB FREE PLAY c) INSPECT ELEVATOR AND RUDDER HINGE BRACKETS AND THEIR SPAR ATTACH AREAS

27-30-00 27-20-00 27-30-00 27-20-00

10. CABIN PRESSURIZATION OVERBOARD DUMP SYSTEM (if installed)-INSPECT LOUVER AND SCREEN FOR OBSTRUCTION AND HOSES FOR SECURITY

N/A

11. ELECTRICAL WIRING AND EQUIPMENT- INSPECT FOR CHAFING, DAMAGE, PROPER ROUTING OF WIRE BUNDLES AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

12. AVIONICS AND AUTOPILOT EQUIPMENT AND RACKS – INSPECT AVIONICS AND AUTOPILOT EQUIPMENT AND RACKS FOR SECURITY, CORROSION AND SIGNS OF WATER LEAKAGE

N/A

13. VERTICAL STABILIZER – INSPECT FRONT AND REAR SPARS OF THE VERTICAL STABILIZER FOR LOOSE OR MISSING RIVETS OR FASTENERS

N/A

14. CONTROL CABLE SEALS – INSPECT FOR DETERIORATION, SECURITY, CLEANLINESS AND LUBRICATION

27

15. FLIGHT CONTROL COMPONENTS, CABLES AND PULLEYS a) INSPECT THE CONTROL SYSTEM COMPONENTS (pushrods, turnbuckles, castings, Etc.) FOR BULGES, SPLITS OR CRACKS WHICH ARE CONDITIONS FOR REPLACEMENT b) INSPECT CONTROL CABLES, PULLEYS AND ASSOCIATED EQUIPMENT FOR CRACKS, WEAR, BREAKS, ATTACHMENT, ALIGNMENT, CLEARANCE AND PROPER OPERATION. REPLACE CABLES THAT HAVE MORE THAN THREE BROKEN WIRES IN ANY GIVEN THREE-FOOT CABLE LENGTH OR HAVE EVIDENCE OF CORROSION

27

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-6 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION G. REAR FUSELAGE AND EMPENNAGE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

16. OXYGEN SYSTEM PLUMBING – INSPECT PLUMBING FOR SECURITY OF ATTACHMENT

35-00-00

17. REAR FUSELAGE AND EMPENNAGE AREA- INSPECT SKIN, STRUCTURE, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. IF DAMAGE OR CORROSION IS FOUND IN A GIVEN AREA, CHECK THE ADJACENT AREA

AC.43.13-1B/2A

H. LEFT-HAND OUTBOARD WING 1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - DETERMINE THAT THE DRAIN HOLES ARE OPEN IN THE WING CENTER SECTION AND OUTBOARD WING UPPER ATTACHMENT FITTINGS

57-00-00

3. LIGHTS a) INSPECT THE NAVIGATION AND RECOGNITION LIGHTS FOR BROKEN OR CRACKED LENSES b) INSPECT THE STROBE LIGHT FOR BROKEN OR CRACKED LENSES

33-40-00

4. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE WING FOR LEAKAGE

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT EXTERIOR OPENINGS OF VENTS FOR OBSTRUCTIONS

28-10-00

5. INTEGRAL FUEL TANK – INSPECT THE EXTERIOR SURFACE OF THE INTEGRAL TANK ACCESS DOORS FOR LEAKS

28-10-00

6. DEICER BOOTS – INSPECT EXTERIOR SURFACE FOR DETERIORATION, DAMAGE AND ATTACHMENT

30-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-7 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION H. LEFT-HAND OUTBOARD WING, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

7. ACCESS DOORS (INSPECTION PANELS) – INSPECT FOR FIT AND ATTACHMENT

6-50-00

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

I. LEFT HAND WING CENTER SECTION 1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE CENTER SECTION FOR LEAKS

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT THE EXTERIOR OPENINGS OF THE VENTS FOR OBSTRUCTIONS

28-10-00

3. ACCESS DOORS (INSPECTION PANELS) - INSPECT FOR FIT AND ATTACHMENT

6-50-00

4. ENGINE FIRE EXTINGUISHER a) INSPECT PLUMBING FOR SECURITY OF ATTACHMENT b) CHECK FIRE BOTTLE PRESSURE GAUGE

26-20-00

J. LEFT-HAND MAIN LANDING AREA 1. WHEELS a) INSPECT WHEELS FOR WEAR, DAMAGE AND CORROSION

N/A

b) INSPECT WHEEL BEARINGS AND RACES FOR WEAR, PITTING, CRACKS, DISCOLORATION, RUST OR OTHER INDICATIONS OF DAMAGE

CMM

2. BRAKES – INSPECT BRAKE DISCS, LININGS AND PLUMBING FOR WEAR DAMAGE, LEAKS, CORROSION AND SECURITY OF ALL COMPONENTS

32-40-00 CMM

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-8 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION J. LEFT-HAND MAIN LANDING AREA, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

3. BRAKE DEICING ( if installed) a) INSPECT MANIFOLD FOR BLOCKED ORIFICES b) INSPECT EXTERIOR OF LINES, HOSES AND CONNECTIONS FOR LEAKAGE AND ATTACHMENT

30-21-00

4. TIRES – INSPECT TIRES FOR WEAR, DETERIORATION AND CORRECT INFLATION

12-20-00 CMM

5. LEFT-HAND MAIN LANDING GEAR STRUT – CHECK STRUT FOR LEAKS AND PROPER EXTENSION

12-20-00

6. ELECTRICAL WIRING AND EQUIPMENT – INSPECT EXPOSED WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND PROPER ROUTING AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

7. MAIN GEAR ACTUATOR a) ACTUATOR (Mechanical Gear) 1. INSPECT ACTUATOR SUPPORT BRACKETS FOR VISIBLE DAMAGE, WEAR AND LOOSE AND MISSING FASTENERS 2. INSPECT ACTUATOR FOR LEAKAGE OF INTERNAL LUBRICANT

32-30-00

K. LEFT-HAND ENGINE 1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-9 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION K. LEFT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. PROPELLERS a) INSPECT FOR DAMAGE AND ATTACHMENT (spinner removal required) b) INSPECT THE CARBON BLOCK PIN FOR FREEDOM OF MOVEMENT c) CHECK FOR NO METAL-TO-METAL CONTACT BETWEEN THE BRASS RING AND THE REVERSING LEVER d) INSPECT MECHANICAL FEEDBACK RING STOP RODS AND SPRINGS FOR DAMAGE

61

e) INSPECT THE REVERSING LINKAGE FOR CORRECT ADJUSTMENT, EVIDENCE OF BINDING AND SECURITY OF ATTACHMENT

76-00-00

5. HIGH PRESSURE FUEL PUMP FILTERS – INSPECT THE ENGINE-DRIVEN HIGH PRESSURE FUEL PUMP FILTERS

P&W

6. ENGINE OIL FILTER – INSPECT FOR METAL PARTICLES

P&W

7. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT – (Sundstrand pumps only)-INSPECT FOR FRETTING AND/OR CORROSION WHEN REPLACING OUTLET FILTER

P&W 73-10-02

8. DRAIN PLUGS – INSPECT ALL DRAIN PLUGS FOR LEAKAGE, SECURITY AND SAFETYING

79-00-00

9. COWLING – REMOVE ENTIRE COWLING AND INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION

71-10-00

10. OIL COOLER – INSPECT OIL COOLER AND PLUMBING FOR LEAKAGE, DAMAGE AND ATTACHMENT

79-00-00

11. OIL PRESSURE SNUBBER (p/n: 3R1) WITH POROUS TYPE ELEMENT – CLEAN ELEMENT

12-10-00

12. AFT COWLING ACCESS DOOR LATCHES – CHECK ADJUSTMENT OF LATCHES

71-10-00

13. FIRE SEALS-INSPECT FOR CONDITION 71-00-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-10 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION K. LEFT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

14. ENGINE EXHAUST SYSTEM a) INSPECT ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION b) INSPECT THE EXHAUST SYSTEM AND VISIBLE PORTIONS OF THE POWER TURBINE FOR BURNING, DISTORSION, DAMAGE AND CRACKS

P&W 78-00-00

15. ENGINE AND PROPELLERS CONTROLS a) CHECK CONTROLS AND ASSOCIATED EQUIPMENT FOR BINDING, STIFF OPERATION FULL TRAVEL AND FRICTION LOCK b) INSPECT CONTROLS, BOLTS, NUTS COTTER PINS AND SAFETIES FOR CORROSION, DAMAGE AND ATTACHMENT NOTE: Special attention should be made to the cam box.

N/A

c) INSPECT CONTROL CABLES FOR DAMAGE SUCH AS CRIMPS, CUTS, ABRASIONS OR TIGHT BENDS. IF EXTERIOR COVERING IS RUPTURED, PERFORM LEAK TEST

12-20-00

16. CONTROL CABLE BOOTS – INSPECT THE CONTROL CABLE BOOTS FOR EXCESSIVE COMPRESSION, TWIST, WEAR OR AGING WHICH COULD CAUSE BINDING

N/A

17. STARTER GENERATOR – INSPECT ONE SET OF BRUSHES FOR INDICATIONS OF EXCESSIVE WEAR OR DAMAGE (determine Wear by observing diagonal groove on brush)

24-30-00

18. COMPRESSOR INLET – REMOVE THE AIR INLET SCREEN AND INSPECT THE COMPRESSOR INLET AREA, STRUTS, FIRST STAGE BLADES AND VANES FOR DIRT DEPOSITS, CORROSION, EROSION, CRACKS AND DAMAGE BY FOREIGN OBJECTS. Refer To the Engine Maintenance Manual for corrective Action.

P&W

19. MAGNETIC CHIP DETECTOR a) REMOVE AND VISUALLY INSPECT PLUG FOR METAL PARTICLES AND DAMAGE b) CHECK LIGHT IN ANNUNCIATOR PANEL FOR PROPER OPERATION

12-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-11 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION K. LEFT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

20. ENGINE a) INSPECT FUEL NOZZLES PER MANUFACTURERS MANUAL b) INSPECT ENGINE IN ACCORDANCE WITH THE INSTRUCTIONS FOUND IN THE ENGINE MANUFACTURERS MANUAL

P&W

21. IGNITION EXCITER a) INSPECT EXCITER AND ELECTRICAL HARNESS FOR DAMAGE AND SECURITY OF ATTACHMENT b) INSPECT THAT SUPPLY CABLE AND IGNITION CABLE CONNECTORS ARE INSTALLED AND SAFETIED

74-00-00

22. SPARK IGNITERS PLUGS – INSPECT THE IGNITER PLUGS AS DESCRIBED IN THE ENGINE MAINTENANCE MANUAL

P&W

23. FUEL PURGE SYSTEM/FUEL DRAIN COLLECTOR SYSTEM 1. CHECK TANK, PUMP, PUMP FILTER AND PLUMBING FOR LEAKS AND SECURITY OF ATTACHMENT 2. PERFORM A PRESSURE TEST ON THE COLLECTOR TANK 3. CHECK WIRING TO COLLECTOR PUMP AND TANK FLOAT SWITCH FOR DAMAGE AND SECURITY OF ATTACHMENT 4. CHECK COLLECTOR PUMP FOR PROPER OPERATION

71-70-00

24. LEFT-HAND ENGINE – INSPECT ALL SYSTEMS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. CHECK ALL TUBES AND HOSES FOR GENERAL CONDITION, LEAKS AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-12 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION L. RIGHT-HAND OUTBOARD WING

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - DETERMINE THAT THE DRAIN HOLES ARE OPEN IN THE WING CENTER SECTION AND OUTBOARD WING UPPER ATTACHMENT FITTINGS

57-00-00

3. LIGHTS a) INSPECT THE NAVIGATION AND RECOGNITION LIGHTS FOR BROKEN OR CRACKED LENSES b) INSPECT THE STROBE LIGHT FOR BROKEN OR CRACKED LENSES

33-40-00

4. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE WING FOR LEAKAGE

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT EXTERIOR OPENINGS OF VENTS FOR OBSTRUCTIONS

28-10-00

5. INTEGRAL FUEL TANK – INSPECT THE EXTERIOR SURFACE OF THE INTEGRAL TANK ACCESS DOORS FOR LEAKS

28-10-00

6. DEICER BOOTS – INSPECT EXTERIOR SURFACE FOR DETERIORATION, DAMAGE AND ATTACHMENT

30-10-00

7. ACCESS DOORS (INSPECTION PANELS) – INSPECT FOR FIT AND ATTACHMENT

6-50-00

8. STATIC WICKS a) INSPECT FOR DAMAGE AND SECURITY OF ATTACHMENT b) CHECK THE STATIC WICK FOR PROPER BONDING TO THE AIRPLANE

23-60-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-13 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION M. RIGHT-HAND WING CENTER SECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. FUEL PROBES – INSPECT FOR LEAKS AT POINTS OF ATTACHMENT

28-40-00

2. FUEL TANKS AND VENTS a) INSPECT THE EXTERIOR OF THE CENTER SECTION FOR LEAKS

28-10-00

b) INSPECT FUEL CAP AND ANTISIPHON VALVE FOR DAMAGE AND ATTACHMENT

CMM

c) INSPECT THE EXTERIOR OPENINGS OF THE VENTS FOR OBSTRUCTIONS

28-10-00

3. ACCESS DOORS (INSPECTION PANELS) - INSPECT FOR FIT AND ATTACHMENT

6-50-00

4. BATTERY a) SERVICE BATTERY AS REQUIRED

12-20-00

b) REMOVE BATTERY AND INSPECT THE BATTERY BOX, CABLES AND VENT TUBES FOR DETERIORATION OR OBSTRUCTIONS

24-31-00

5. ENGINE FIRE EXTINGHUISER a) INSPECT PLUMBING FOR SECURITY OF ATTACHMENT b) CHECK FIRE BOTTLE PRESSURE GAUGE

26-20-00

N. RIGHT-HAND MAIN LANDING GEAR AREA 1. WHEELS a) INSPECT WHEELS FOR WEAR, DAMAGE AND CORROSION

N/A

b) INSPECT WHEEL BEARINGS AND RACES FOR WEAR, PITTING, CRACKS, DISCOLORATION, RUST OR OTHER INDICATIONS OF DAMAGE

CMM

2. BRAKES – INSPECT BRAKE DISCS, LININGS AND PLUMBING FOR WEAR DAMAGE, LEAKS, CORROSION AND SECURITY OF ALL COMPONENTS

32-40-00 CMM

3. BRAKE DEICING ( if installed) a) INSPECT MANIFOLD FOR BLOCKED ORIFICES b) INSPECT EXTERIOR OF LINES, HOSES AND CONNECTIONS FOR LEAKAGE AND ATTACHMENT

30-21-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-14 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION N. RIGHT-HAND MAIN LANDING GEAR AREA, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. TIRES – INSPECT TIRES FOR WEAR, DETERIORATION AND CORRECT INFLATION

12-20-00 CMM

5. RIGHT-HAND MAIN LANDING GEAR STRUT – CHECK STRUT FOR LEAKS AND PROPER EXTENSION

12-20-00

6. ELECTRICAL WIRING AND EQUIPMENT – INSPECT EXPOSED WIRING AND EQUIPMENT FOR CHAFING, DAMAGE AND PROPER ROUTING AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

7. MAIN GEAR ACTUATOR a) ACTUATOR (Mechanical Gear) 1. INSPECT ACTUATOR SUPPORT BRACKETS FOR VISIBLE DAMAGE, WEAR AND LOOSE AND MISSING FASTENERS 2. INSPECT ACTUATOR FOR LEAKAGE OF INTERNAL LUBRICANT

32-30-00

O. RIGHT-HAND ENGINE 1. PROPELLER DEICER – INSPECT PROPELLER DEICE SYSTEM (spinner removal required)

30-60-00 CMM

2. P3 AIR FILTER – INSPECT THE FILTER FOR CLEANLINESS

P&W

3. FUEL FILTERS AND SCREENS - INSPECT THE FIREWALL FILTER FOR EVIDENCE OF FOREIGN MATTER, CORROSION OR MICROBIOLOGICAL GROWTH IN THE FUEL SYSTEM. IF ANY MICROBIOLOGICAL GROWTH IS FOUND, USE BIBOR JF ADDITIVE

28-20-00 12-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-15 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

4. PROPELLERS a) INSPECT FOR DAMAGE AND ATTACHMENT (spinner removal required) b) INSPECT THE CARBON BLOCK PIN FOR FREEDOM OF MOVEMENT c) CHECK FOR NO METAL-TO-METAL CONTACT BETWEEN THE BRASS RING AND THE REVERSING LEVER d) INSPECT MECHANICAL FEEDBACK RING STOP RODS AND SPRINGS FOR DAMAGE

61

e) INSPECT THE REVERSING LINKAGE FOR CORRECT ADJUSTMENT, EVIDENCE OF BINDING AND SECURITY OF ATTACHMENT

76-00-00

5. HIGH PRESSURE FUEL PUMP FILTERS – INSPECT THE ENGINE-DRIVEN HIGH PRESSURE FUEL PUMP FILTERS

P&W

6. ENGINE OIL FILTER – INSPECT FOR METAL PARTICLES

P&W

7. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT – (Sundstrand pumps only)-INSPECT FOR FRETTING AND/OR CORROSION WHEN REPLACING OUTLET FILTER

P&W 73-10-02

8. DRAIN PLUGS – INSPECT ALL DRAIN PLUGS FOR LEAKAGE, SECURITY AND SAFETYING

79-00-00

9. COWLING – REMOVE ENTIRE COWLING AND INSPECT SKIN, STRUCTURE AND ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION

71-10-00

10. OIL COOLER – INSPECT OIL COOLER AND PLUMBING FOR LEAKAGE, DAMAGE AND ATTACHMENT

79-00-00

11. OIL PRESSURE SNUBBER (p/n: 3R1) WITH POROUS TYPE ELEMENT – CLEAN ELEMENT

12-10-00

12. AFT COWLING ACCESS DOOR LATCHES – CHECK ADJUSTMENT OF LATCHES

71-10-00

13. FIRE SEALS-INSPECT FOR CONDITION 71-00-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-16 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

14. ENGINE EXHAUST SYSTEM a) INSPECT ATTACHING HARDWARE FOR WEAR, DAMAGE AND CORROSION b) INSPECT THE EXHAUST SYSTEM AND VISIBLE PORTIONS OF THE POWER TURBINE FOR BURNING, DISTORSION, DAMAGE AND CRACKS

P&W 78-00-00

15. ENGINE AND PROPELLERS CONTROLS a) CHECK CONTROLS AND ASSOCIATED EQUIPMENT FOR BINDING, STIFF OPERATION FULL TRAVEL AND FRICTION LOCK b) INSPECT CONTROLS, BOLTS, NUTS COTTER PINS AND SAFETIES FOR CORROSION, DAMAGE AND ATTACHMENT NOTE: Special attention should be made to the cam box.

N/A

c) INSPECT CONTROL CABLES FOR DAMAGE SUCH AS CRIMPS, CUTS, ABRASIONS OR TIGHT BENDS. IF EXTERIOR COVERING IS RUPTURED, PERFORM LEAK TEST

12-20-00

16. CONTROL CABLE BOOTS – INSPECT THE CONTROL CABLE BOOTS FOR EXCESSIVE COMPRESSION, TWIST, WEAR OR AGING WHICH COULD CAUSE BINDING

N/A

17. STARTER GENERATOR – INSPECT ONE SET OF BRUSHES FOR INDICATIONS OF EXCESSIVE WEAR OR DAMAGE (determine Wear by observing diagonal groove on brush)

24-30-00

18. COMPRESSOR INLET – REMOVE THE AIR INLET SCREEN AND INSPECT THE COMPRESSOR INLET AREA, STRUTS, FIRST STAGE BLADES AND VANES FOR DIRT DEPOSITS, CORROSION, EROSION, CRACKS AND DAMAGE BY FOREIGN OBJECTS. Refer To the Engine Maintenance Manual for corrective Action.

P&W

19. MAGNETIC CHIP DETECTOR a) REMOVE AND VISUALLY INSPECT PLUG FOR METAL PARTICLES AND DAMAGE b) CHECK LIGHT IN ANNUNCIATOR PANEL FOR PROPER OPERATION

12-10-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-17 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

20. ENGINE a) INSPECT FUEL NOZZLES PER MANUFACTURERS MANUAL b) INSPECT ENGINE IN ACCORDANCE WITH THE INSTRUCTIONS FOUND IN THE ENGINE MANUFACTURERS MANUAL

P&W

21. IGNITION EXCITER a) INSPECT EXCITER AND ELECTRICAL HARNESS FOR DAMAGE AND SECURITY OF ATTACHMENT b) INSPECT THAT SUPPLY CABLE AND IGNITION CABLE CONNECTORS ARE INSTALLED AND SAFETIED

74-00-00

22. SPARK IGNITERS PLUGS – INSPECT THE IGNITER PLUGS AS DESCRIBED IN THE ENGINE MAINTENANCE MANUAL

P&W

23. FUEL PURGE SYSTEM/FUEL DRAIN COLLECTOR SYSTEM 1. CHECK TANK, PUMP, PUMP FILTER AND PLUMBING FOR LEAKS AND SECURITY OF ATTACHMENT 2. PERFORM A PRESSURE TEST ON THE COLLECTOR TANK 3. CHECK WIRING TO COLLECTOR PUMP AND TANK FLOAT SWITCH FOR DAMAGE AND SECURITY OF ATTACHMENT 4. CHECK COLLECTOR PUMP FOR PROPER OPERATION

71-70-00

24. RIGHT-HAND ENGINE – INSPECT ALL SYSTEMS, ALL COMPONENTS AND ATTACHING HARDWARE FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT. CHECK ALL TUBES AND HOSES FOR GENERAL CONDITION, LEAKS AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-18 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION O. RIGHT-HAND ENGINE, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

25. AIR CONDITIONING COMPRESSOR a) INSPECT FOR SECURITY OF ATTACHMENT AND OIL LEAKS b) INSPECT FOR WEAR AND LUBRICATE THE SPLINE ON THE PULLEY END OF THE QUILL SHAFT c) INSPECT DRIVE BELT FOR DETERIORATION WEAR AND PROPER TENSION

21-50-00

d) CHECK FOR PROPER COMPRESSOR OIL LEVEL

12-10-00

26. REFRIGERANT LINES AND SERVICE VALVES - INSPECT LINES AND VALVES FOR LEAKAGE, DAMAGE AND ATTACHMENT

21-50-00

P. LANDING GEAR RETRACTION NOTE: Mechanical and Hydraulic Landing Gear Systems – Since battery voltage is not sufficient to properly cycle The landing gear, use only an external power source Capable of delivering and maintaining 28.25 +/- 0.25 Volts throughout the extension and retraction cycles when performing the landing gear retraction inspection.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-19 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION P. LANDING GEAR RETRACTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. RETRACT MECHANISM – CHECK RETRACTION SYSTEM FOR PROPER OPERATION OF ALL COMPONENTS THROUGH AT LEAST TWO COMPLETE CYCLES

32

2. DOORS AND LINKAGE a) CHECK DOOR FOR DAMAGE, OPERATION AND FIT b) CHECK DOOR LINKAGE FOR WEAR, DAMAGE AND RIGGING

32

3. DOWNLOCK INDICATOR SWITCHES a) CHECK FOR SECURITY AND PROPER OPERATION OF SWITCHES b) CLEAN TERMINALS AND CONNECTORS AS REQUIRED c) CHECK WIRING FOR DAMAGE AND SECURITY OF CONNECTION

32-60-00

4. UPLOCK INDICATOR SWITCHES a) CHECK FOR SECURITY AND PROPER OPERATION OF SWITCHES b) CLEAN TERMINALS AND CONNECTORS AS REQUIRED c) CHECK WIRING FOR DAMAGE AND SECURITY OF CONNECTION

32-60-00

5. WARNING HORN – CHECK OPERATION 32-60-00 6. MAIN GEAR DOWNLOCKS – CHECK LOCKING MECHANISM FOR POSITIVE ENGAGEMENT IN EXTENDED POSITION

32

7. SAFETY SWITCH – CHECK FOR PROPER OPERATION

32-60-00

8. ACTUATORS – CHECK FOR NOISE, BINDING AND PROPER RIGGING

32-30-00 32-31-00

9. LIMIT SWITCHES – (Mechanical Gear) a) CHECK FOR CORRECT ADJUSTMENT b) CHECK FOR SECURITY OF ATTACHMENT

32-60-00

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-20 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION P. LANDING GEAR RETRACTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

10. EMERGENCY EXTENSION (Mechanical Gear) CHECK SYSTEM FOR FREEDOM OF OPERATION AND POSITIVE ENGAGEMENT OF DOWNLOCKS. CAUTION: Do not continue operation after receiving a gear-down indication on all gears. Further movement of the handle could damage the drive mechanism and prevent subsequent electrical gear retraction. The landing gear cannot be retracted manually.

32-30-00

11. NOSE GEAR RETRACT CHAIN (Mechanical Gear) a) CHECK FOR PROPER CHAIN TENSION b) CHECK NOSE GEAR AND NOSE GEAR LINKAGE CLEARANCE FROM ELECTRICAL WIRES AND OBSTRUCTIONS

32-30-00

12. PLACARDS – CHECK THAT ALL PLACARDS ARE IN PLACE AND ARE LEGIBLE

11-00-00

13. LANDING GEAR RETRACTION – INSPECT ALL LANDING GEAR COMPONENTS AND ATTACHING HARDWARE, STRUCTURE AND HYDRAULIC LINES FOR GENERAL CONDITION AND SECURITY OF ATTACHMENT

AC.43.13-1B/2A

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-21 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION Q. OPERATIONAL INSPECTION

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

NOTE: The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual for the engine start and run procedures.

N/A

1. FIREWALL SHUTOFF FUEL VALVES - CHECK FOR PROPER OPERATION

Ref: NOTE

2. CROSSFEED FUEL VALVE – CHECK FOR PROPER OPERATION

Ref: NOTE

3. STANDBY PUMPS – CHECK FOR PROPER OPERATIONS

Ref: NOTE

4. STARTER GENERATOR a) CHECK STARTER FOR OPERATION b) CHECK GENERATOR FOR OUTPUT

Ref: NOTE

5. IGNITION a) CHECK FOR PROPER OPERATION b) CHECK FOR ANNUNCIATOR PANEL LIGHT ILLUMINATION

Ref: NOTE

6. ENGINE OIL – CHECK FOR PROPER PRESSURE AND TEMPERATURE LIMITS

Ref: NOTE

7. FUEL QUANTITY GAGES – CHECK OPERATION

Ref: NOTE

8. INTERSTAGE TURBINE TEMPERATURE – CHECK FOR CORRECT LIMITS ON ENGINE START

Ref: NOTE

9. VACUUM SYSTEM – CHECK FOR CORRECT LIMITS

Ref: NOTE

10. PNEUMATIC PRESSURE GAGE – CHECK FOR CORRECT PRESSURE

Ref: NOTE

11. PNEUMATIC SYSTEM SHUTOFF VALVES – CHECK FOR PROPER OPERATION

Ref: NOTE

12. GYRO INSTRUMENTS – CHECK FOR ERRATIC OR NOISY OPERATION

Ref: NOTE

13. PROPELLERS – PERFORM FLIGHT IDLE TOQUE CHECK

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-22 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

14. AUTOFEATHERING CHECK – Refer to: AUTOFEATHERING SYSTEM OPERATIONAL CHECK

61-21-00

15. PROPELLER SYNCHROPASER – Refer to: AUTOFEATHER SYSTEM OPERATIONAL CHECK

61-21-00

16. PROPELLER GOVERNOR – CHECK GOVERNOR OPERATION ( Including feathering And reversing)

Ref: NOTE

17. IDLE RPM – CHECK FOR CORRECT RPM ( both high and low rpm)

Ref: NOTE

18 AC INVERTERS – CHECK FOR PROPER OPERATION

Ref: NOTE

19. RUDDER BOOST – CHECK FOR PROPER OPERATION

Ref: NOTE

20. AUTO-IGNITION a) CHECK FOR PROPER OPERATION b) CHECK FOR ANNUNCIATOR PANEL ILLUMINATION

Ref: NOTE

21. PROPELLER DEICER – CHECK FOR PROPER OPERATION AND CYCLING. Refer to chapter 30 of the Beech King Air Series Component Maintenance Manual

N/A

22. ENGINE INTERIAL ANTI-ICER – CHECK FOR PROPER OPERATION AND RIGGING

Ref: NOTE

23. SURFACE DEICE SYSTEM – CHECK FOR PROPER OPERATION AND CYCLING

Ref: NOTE

24. BRAKE DEICE SYSTEM (if installed) – CHECK FOR PROPER OPERATION WITH ENGINES RUNNING

Ref: NOTE

25. ELECTRICAL SYSTEM – PERFORM FUNCTIONAL CHECKS

Ref: NOTE

26. ENVIRONMENTAL SYSTEM – CHECK FOR PROPER OPERATION IN: a) MANUAL HEAT MODE b) MANUAL COOL MODE c) AUTOMATIC MODE

Ref: NOTE

27. REFRIGERANT LEVEL – CHECK FOR PROPER LEVEL

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-23 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

28. AUTOPILOT – CHECK FOR PROPER OPERATION AS OUTLINED BY THE APPLICABLE Beech Super King Air 200 and B200 Pilots Operating Handbook or SCAA Approved Airplane Flight Manual Supplement

Ref: NOTE

29. STALL WARNING – CHECK FOR PROPER OPERATION

Ref: NOTE

30. ENGINE FIRE DETECTORS – Perform system test according to instructions found in the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual

N/A

31. ENGINE FIRE EXTINGUISHERS – Perform system test according to instructions found in the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual

N/A

32. PRESSURIZATION SYSTEM – CHECK FOR PROPER OPERATION Refer to the Sample Aircraft Pilots Operating Handbook and SCAA Approved Airplane Flight Manual and perform system test

N/A

33. AUXILIARY FUEL TRANSFER JET PUMPS – CHECK FOR PROPER OPERATION

Ref: NOTE

34. CONDITION LEVER – CHECK FOR CLEAN SHUTDOWN AT IDLE-CUT-OFF

Ref: NOTE

35. PITOT TUBE – CHECK FOR PROPER HEATING AT THE UNIT AND FOR OBSTRUCTIONS

Ref: NOTE

36. LANDING AND TAXI LIGHTS – CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

37. OUTBOARD WING LIGHTS ( R/H AND L/H) - CHECK OPERATION OF ALL NAVIGATION AND STROBE LIGHTS

Ref: NOTE

38. COCKPIT LIGHTS – CHECK OPERATION OF ALL COCKPIT LIGHTS

Ref: NOTE

39. EFIS COOLING BLOWERS (if installed) – CHECK OPERATION

Ref: NOTE

40. ELECTRIC ELEVATOR TRIM – CHECK FOR PROPER OPERATION

Ref: NOTE

41. ENGINE AND PROPELLER CONTROLS – CHECK FOR FREEDOM OF MOVEMENT FULL TRAVEL AND FRICTION-LOCK OPERATION

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-24 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

42. STATIC SYSTEM – INSPECT ALTERNATE AIR VALVE FOR OPERATION

Ref: NOTE

43. WINDSHIELD – PERFORM HEATED OPERATIONAL CHECK

Ref: NOTE

44. THRESHOLD LIGHT – CHECK FOR PROPER OPERATION

Ref: NOTE

45. AUXILIARY ELECTRIC HEAT (if installed) – CHECK FOR PROPER OPERATION OF THE ELECTRIC HEAT SYSTEM

Ref: NOTE

46. CABIN AND COMPARTMENT LIGHTS – CHECK FOR PROPER OPERATION

Ref: NOTE

47. PILOTS AN COPILOTS SEATS, SEATS BELTS- AND SHOULDER HARNESSES – CHECK SEAT ADJUSTMENT MECHANISM, SEAT BELTS AND SHOULDER HARNESS INERTIA REEL FOR OPERATION

Ref: NOTE

48. CABIN SEATS, SEAT BELTS AND SHOULDER HARNESSES – CHECK SEAT ADJUSTMENT MECHANISM, SEAT BELTS AND SHOULDER HARNESS INERTIA REEL FOR OPERATION

Ref: NOTE

49. CABIN ENTRANCE DOOR: a) CHECK THAT FOLDING STEPS DO NOT FOLD TOO SOON AND THAT THEY FOLD PROPERLY WITHOUT INTERFERENCE b) CHECK CABIN DOOR UNLOCK ANNUNCIATOR FOR PROPER OPERATION c) INSPECT CABIN DOOR DAMPER FOR LEAKAGE AND PROPER OPERATION

Ref: NOTE

50. EMERGENCY EXIT ( WITH DOOR INSTALLED ) a) CHECK EMERGENCY RELEASE HANDLES (inside and outside) AND LATCH MECHANISM FOR OPERATION b) CHECK THAT LATCHES OPEN AND CLOSE FREELY

Ref: NOTE

51. EMPENNAGE CONTROL SURFACES a) CHECK FOR FREEDOM OF MOVEMENT b) CHECK OPTIONAL TRIM ACTUATORS AND MOTORS FOR SMOOTHNESS OF OPERATION

Ref: NOTE

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-24 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION Q. OPERATIONAL INSPECTION, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

52. REAR FUSELAGE AND EMPENNAGE LIGHTS - CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

53. AILERON (LH AND RH) – CHECK FOR FREEDOM OF MOVEMENT

Ref: NOTE

54. AILERON TRIM TAB – CHECK TRIM TAB ACTUATOR FOR SMOOTHNESS OF OPERATION AND ATTACHMENT

Ref: NOTE

55. FUEL TANK HEATED VENTS (LH AND RH) – CHECK THE OPERATION OF THE HEATED VENTS. THEY SHOULD BE WARM TO THE TOUCH

Ref: NOTE

56. STALL WARNING HEAT – CHECK FOR PROPER OPERATION

Ref: NOTE

57. FLAPS AND ACTUATORS ( Inboard, Outboard, LH and RH) – CHECK FLAPS FOR NOISY OR ERRATIC OPERATION

Ref: NOTE

58. WING CENTER SECTION LIGHTS – CHECK OPERATION OF ALL LIGHTS

Ref: NOTE

59. ENGINE INDUCTION SYSTEM (LH AND RH)- CHECK THE INERTIAL VANE AND BYPASS DOOR FOR MOVEMENT WITH THE MAIN AND STANDBY ACTUATOR MOTORS.

Ref: NOTE

60. EXTERNAL POWER RELAY – CHECK FOR PROPER OPERATION

Ref: NOTE

R. POST INSPECTIONS ITEMS 1. AIRPLANE CLEANED AND SERVICED AS REQUIRED

12-20-00

2. LUBRICATE AS NECESSARY 12-20-00 3. ENGINE INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST – CHECK FOR OIL LEAKS, SECURITY AND ATTACHMENT OF ALL COMPONENTS

4. AIRWORTHINESS DIRECTIVES AND SERVICE BULLETINS – MUST BE REVIEWED AND COMPLIED WITH AS REQUIRED

5. ADDITIONAL INSPECTION REQUIREMENTS- ENSURE THAT SPECIAL INSPECTION REQUIREMENTS ARE COMPLIED WITH AT THE APPROPRIATE INTERVALS

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-25 PHASE 4 INSPECTION

Sample Aircraft This Phase Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SECTION / AREA / DESCRIPTION R. POST INSPECTIONS ITEMS, continue

ATA Ref: NON CERTIFYING STAFF:

CERTIFYING STAFF:

6. IN-FLIGHT WORKSHEETS – ALL DISCREPANCIES NOTED BY THE PILOT MUST BE CHECKED AND CORRECTED AS REQUIRED

7. EMERGENCY LOCATOR TRANSMITTER – CHECK FOR PROPER OPERATION AND ENSURE ELT IS ARMED BEFORE RETURNING AIRPLANE TO SERVICE

25-60-00

8. OXYGEN SYSTEM PRESSURE – CHECK FOR PROPER PRESSURE

12-10-00

9. EMERGENCY AND SURVIVAL EQUIPMENT- ENSURE ALL NECESSARY EMERGENCY AND SURVIVAL EQUIPMENT IS INSTALLED IN THE AIRPLANE AND IS SERVICEABLE

10. PLACARDS – DETERMINE THAT ALL REQUIRED PLACARDS ARE IN PLACE AND LEGIBLE

11-20-00 POH

11. LOGBOOK ENTRY – ENSURE THAT LOG BOOKS ARE FILLED OUT PROPERLY

MME

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-26 PHASE 4 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: NOSE LANDING GEAR

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1 WHEEL BEARINGS MOBIL AVIATION GREASE SHC 100

PHASE 4

2 GREASE FITTINGS MIL-G-81322 PHASE 4 3. NOSE WHEEL STEERING

MECHANISM MIL-G-81322 GREASE

PHASE 4

4. UPPER AND LOWER NOSE GEAR STRUT BEARING

AEROSHELL 17

PHASE 4

5. DRAG BRACE BOLTS WITH GREASE FITTINGS. ROTATE BOLT WITH WRENCH, IF UNABLE TO ROTATE, REMOVE AND CLEAN Note: Grease must appear at both ends of bolt. If not, remove and clean grease passage.

MIL-G-81322 PHASE 4

6. DOOR HINGES AND RETRACT LINKAGE

MIL-L-7870 OIL

PHASE 4

7. UPPER AND LOWER NOSE GEAR STRUT BEARING

MIL-G-23827 GREASE

PHASE 4

8. SHIMMY DAMPER ATTACH BOLTS

LPS No. 3 Metal Protector

PHASE 4

CAUTION: DO NOT MIX different brands of grease as this will cause decreased bearing life. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication. NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-27 PHASE 4 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: MAIN LANDING GEAR

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. HIGH FLOTATION GEAR DOOR LINKAGE

LPS No: 3 Metal Protector

PHASE 4

2. GREASE FITTINGS MIL-G-81322 PHASE 4 3. DOOR HINGES AND

RETRACT LINKAGE MIL-L-7870 PHASE 4

4. WHEEL BEARINGS MOBIL AVIATION GREASE SHC 100

PHASE 4

5. DRAG LEG HOOK, SPRING AND GUIDE

LPS No: 3 Metal Protector (Apply Sparingly)

PHASE 4

6. DRAG BRACE BOLTS WITH GREASE FITTINGS. ROTATE BOLT WITH WRENCH, IF UNABLE TO ROTATE, REMOVE AND CLEAN Note: Grease must appear at both ends of bolt. If not, remove and clean grease passage.

MIL-G-81322 PHASE 4

7 RETRACT ACTUATOR CLEVIS

AEROSHELL 17

PHASE 4

8. UNSEALED ACTUATOR SUPPORT BEARINGS

MIL-G-23827 PHASE 4

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-28 PHASE 4 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: RUDDER CONTROL,

LANDING GEAR RETRACT (MECHANICAL) SYSTEMS LUBRICATION

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. RUDDER TRIM TAB TUBE

MIL-L-7870 PHASE 4

2. RUDDER TRIM TAB HINGE

MIL-L-7870 PHASE 4

3. RUDDER TRIM TAB ACTUATOR

MIL-G-23827 PHASE 4

4. RUDDER TRIM TAB CABLE SEAL

MIL-G-23827 PHASE 4

5. RUDDER CABLE SEALS MIL-G-23827 PHASE 4 6. RETRACT CHAINS AND

EMERGENCY EXTENSION CHAIN

Clean chains with a cloth dampended with solvent (34, chart 201, 91-00-00). Lubricate chain with SAE 30W mineral oil. Wipe off excess oil

PHASE 4

7. EMERGENCY EXTENSION MECHANISM

MIL-L-7870 PHASE 4

8 TORQUE TUBE SPLINES MIL-G-23827 PHASE 4 9. LANDING GEAR CHAIN

IDLER SPROCKET BEARINGS

MIL-G-23827 PHASE 4

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-29 PHASE 4 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: AILERON AND FLAP

CONTROL SYSTEM LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. AILERON TRIM TAB HINGE

BRAYCO 300/LPS-1

PHASE 4

2. AILERON TRIM TAB TUBE END

MIL-L-7870 PHASE 4

3. FLAP TRACKS Spray with a dry lubricant

PHASE 4

4. AILERON QUADRANT MIL-L-7870 PHASE 4 5. AILERON BELLCRANKS MIL-L-7870 PHASE 4 6. TRIM TAB ACTUATOR MIL-G-23827 PHASE 4 7. AILERON TAB CABLE

SEALS MIL-G-23827 PHASE 4

8. AILERON CABLE SEALS MIL-G-23827 PHASE 4 9. FLAP ACTUATOR PISTON MIL-L-2105 PHASE 4 10. FLAP MOTOR GEARBOX MIL-G-10924 PHASE 4 11. FLAP SAFETY SWITCH LPS-1 or

equalling PHASE 4

NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-30 PHASE 4 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: CONTROL COLUMN,

RUDDER AND ELEVATOR CONTROL SYSTEMS LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. ELEVATOR TRIM TAB TUBE

MIL-L-7870 PHASE 4

2. ELEVATOR TRIM TAB HINGES

BRAYCO 300 PHASE 4

3. CHAIN Preclean with a cloth dampened with solvent (34, chart 201, 91-00-00). Lubricate chain with SAE 30W mineral oil. Wipe off excess oil.

PHASE 4

4. PEDAL AND BELLCRANK LINKAGE

MIL-L-7870 PHASE 4

5. RUDDER TRIM TAB ACTUATOR

MIL-G-23827 PHASE 4

6. ELEVATOR TRIM TAB ACTUATOR

MIL-G-23827 PHASE 4

8. ELEVATOR TRIM TAB CABLE SEAL

MIL-G-23827 PHASE 4

9. ELEVATOR CABLE SEAL MIL-G-23827 PHASE 4 NOTE: After washing the airplane, lubricate all lubrication points.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-31 PHASE 4 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: ENGINE CONTROL

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. CONTROL ROD ENDS MIL-G-23827 PHASE 4 2. CAM PLATES AND PIN Lubriplate No.

130AA PHASE 4

3. AIR-CONDITIONER COMPRESSOR QUILL SHAFT

MOLYKOTE M-77

PHASE 4

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-32 PHASE 4 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: PROPELLER

LUBRICATION: LUBRICANT: INTERVAL: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1. PROPELLER BLADE BEARINGS (2 lube fittings per blade)

Aeroshell Grease No. 6, Aeroshell Grease No 7, Aeroshell Grease No. 22, Exxon 5114EP, Rayco 22C as defined by the manufacturers decal on the piston hub of the propeller

PHASE 4

2 LOW PITCH STOP RODS (3 per propeller)

Marvel Mystery Oil

PHASE 4

3. LINKAGE (All moving parts)

MIL-G-21164 PHASE 4

WARNING: Remove the lubrication fitting opposite the one being serviced. Failure to do so could result in damage to the propeller bearings and seals.

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-33 PHASE 4 INSPECTION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: EMERGENCY EXIT AND

CABIN DOOR LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. CABIN DOOR: Latching Mechanism (pins included)

MIL-L-7870 OIL

PHASE 4

2. TRACK Molykote G-N Paste Product

PHASE 4

3. GUIDE MIL-L-23398 Form A and Molykote 505

PHASE 4

4. LATCH MIL-L-23398 Form A and Molykote 505

PHASE 4

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-34 WINGS LUBRICATION

Sample Aircraft LUBRICATION CARD This Lubrication Card is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: EMERGENCY EXIT AND

CABIN DOOR LUBRICATION:

LUBRICANT: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1. LOWER FORWARD WING BOLTS

MIL-C-16173 Grade 2 Corrosion Preventive Compound

First Scheduled Inspection after Wing Installation and Annually thereafter

2. UPPER FORWARD WING BOLTS

MIL-C-16173 Grade 2 Corrosion Preventive Compound

First Scheduled Inspection after Wing Installation and Annually thereafter

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 6-35 THREAD LUBRICANTS CHART

Sample Aircraft This Lubrications Chart is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

Pos: Type of Line: Lubricant: 1. Pressurization Control Tapered Threads and Straight Threads 92 PS/T ( white ) 2. Brakes MIL-H-5606 Hydraulic Fluid 3. Fuel and Fuel Press. Lines VV-P-236 Anti-seize compound 4. Oil and Oil Press. Lines MIL-G-6032, Lubricant Grease ( Oil and Gasoline

Resistant) 5. Autopilot 92 PS/T (white) Straight and Tapered Threads 6. Oxygen MIL-T-27730 Size 1 Teflon Tape 7. Pitot and Static Straight Threads and Tapered Threads 92 PS/T (white) 8 Hydraulic Fluid of the System or Locktite Hydraulic Sealant Cat. #92

or Cat. #69 9. Vacuum TT-A-580 Anti-seize Compound (White Lead Base ) 10. Refrigerant Brayco 815Z 11. Deicer Straight Threads and Tapered Threads, 92 PS/T (White) 12. Fire Extinguisher 92 PS/T (White)

13. Bleed Air M-77 (P/N of Dow Corning)

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 7-1 HARD TIME COMPONENTS / SPECIAL INSPECTIONS

Sample Aircraft This Special Inspections is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004. SPL = Special Inspecktion

MOS = Months CYC = Cycles HRS = Hours

Pos: ITEM: INSPECTION: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

1 ACTUATOR CLEVIS, MAIN LANDING GEAR

SPL/MRB 1000 CYC

2 ACTUATOR CLEVIS, NOSE LANDING GEAR

SPL/MRB 1000 CYC

3 ACTUATOR, MAIN LANDING GEAR (Mechanical Gear)

SPL/MRB 1000 CYC

4 ACTUATOR, MAIN LANDING GEAR (Mechanical Gear)

SPL/MRB 30 MOS

5 ACTUATOR, NOSE LANDING GEAR (Mechanical Gear)

SPL/MRB 1000 CYC

6 ACTUATOR, NOSE LANDING GEAR (Mechanical Gear)

SPL/MRB 30 MOS

7 AFT FUSELAGE AREA AND AFT PRESSURE BULKHEAD

SPL/MRB 500 CYC

8 AFT FUSELAGE AREA AND AFT PRESSURE BULKHEAD

SPL/MRB 10000 CYC

9 ALTIMETER-PITOT-STATIC SYSTEM

SPL/ NAT. REQ.

24 MOS

10 AXLE ASSEMBLY AND TORQUE KNEE, NOSE LANDING GEAR

SPL/MRB 8000 CYC OR 72 MOS

11 AXLE ASSEMBLY AND TORQUE KNEE, MAIN LANDING GEAR

SPL/MRB 8000 CYC OR 72 MOS

12 BATTERY, EMERGENCY CAPACITY TEST

SPL/MRB 200 HRS

13 BATTERY, LEAD ACID SPL/MRB 3 MOS 14 BULKHEAD, FORWARD

PRESSURE SPL/MRB 2500 CYC

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 7-2 HARD TIME COMPONENTS / SPECIAL INSPECTIONS

Sample Aircraft This Special Inspections is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

SPL = Special Inspecktion

MOS = Months CYC = Cycles HRS = Hours

Pos: ITEM: INSPECTION: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

15 CABIN DOOR AND FUSELAGE FRAME

SPL/MRB 1000 CYC

16 CABIN DOOR AND FUSELAGE FRAME

SPL/MRB 10000 CYC

17 COMPRESSOR DRIVE BELT, AIR-CONDITIONER

SPL/MRB 50 HRS

18 DOOR, CABIN SPL/MRB 1000 CYC 19 DOOR, CABIN SPL/MRB 5000 CYC 20 DOOR, EMERGENCY

EXIT ( Escape Hatch) SPL/MRB 1000 CYC

21 DOOR, EMERGENCY EXIT ( Escape Hatch)

SPL/MRB 5000 CYC

22 DRAG BRACE, NOSE LANDING GEAR

SPL/MRB 8000 CYC OR 72 MOS

23 DRAG BRACE, MAIN LANDING GEAR

SPL/MRB 8000 CYC OR 72 MOS

24 EDGELIGHTED PANEL ASSEMBLIES

SPL/MRB 2000 HRS OR 48 MOS

25 ENGINE, HOT SECTION INSPECTION

SPL/MRB PER P&W SB. 3003

26 ENGINE MOUNT VIBRATION ISOLATORS

SPL/MRB ENGINE TBO OR 4000 HRS

27 FILTER, ENGINE OIL (Replace)

SPL/MRB 1000 HRS

28 FIRE EXTINGHUISER, CABIN

SPL/MRB 144 MOS

29 FIRE EXTINGHUISER, ENGINE

SPL/MRB 60 MOS

30 FIRE EXTINGHUISER, PILOTS COMPARTMENT

SPL/MRB 144 MOS

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 7-3 HARD TIME COMPONENTS / SPECIAL INSPECTIONS

Sample Aircraft This Special Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004. SPL = Special Inspecktion

MOS = Months CYC = Cycles HRS = Hours

Pos: ITEM: INSPECTION: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

31 FLEXIBLE SHAFT, FLAPS SPL/MRB 5000 CYC 32 FLIGHT CONTROL

PULLEY BRACKETS AND CASTINGS

SPL/MRB 5000 CYC

33 FLIGHT CONTROL PULLEY BRACKETS AND CASTINGS

SPL/MRB 10000 CYC

34 FRAME WEB, FUSELAGE SPL/MRB 1000 CYC 35 FRAME WEB, FUSELAGE SPL/MRB 10000 CYC 36 FRAMES, FUSELAGE

SUBFLOOR SPL/MRB 1000 CYC

37 FRAMES, FUSELAGE SUBFLOOR

SPL/MRB 10000 CYC

38 FUEL PROBE (Nacelle) SPL/MRB 2400 HRS OR 30 MOS

39 N/A N/A N/A N/A N/A 40 N/A N/A N/A N/A N/A 41 INSTRUMENT PANEL

STRINGERS AND SUPPORT BRACKETS

SPL/MRB 10000 CYC

42 OXYGEN CYLINDER TEST (Standard Weight) ( DOT 3AA 1800)

SPL/MRB 60 MOS

43 OXYGEN SYSTEM PASSENGER SHUTOFF VALVE O-RING ( Refer to Chapter 5-11-00).

SPL/MRB 24 MOS

44 P3 AIR FILTER ( REPLACE)

SPL/MRB 1000 HRS

45 PITOT SYSTEM SPL/MRB NAT.REQ.

24 MOS

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 7-4 HARD TIME COMPONENTS / SPECIAL INSPECTIONS

Sample Aircraft This Special Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004. SPL = Special Inspecktion

MOS = Months CYC = Cycles HRS = Hours

Pos: ITEM: INSPECTION: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

46 POWER LEVERS STOP PIN, PEDESTAL

SPL/MRB 1200 HRS

47 RETRACT GEAR BOX AND CLUTCH (Mechanical Gear)

SPL/MRB 8000 CYC OR 72 MOS

48 RUDDER BOOST FILTER ( Replace Without Autopilot)

SPL/MRB 200 HRS

49 SHOCK ABSORBER, NOSE LANDING GEAR

SPL/MRB 8000 CYC OR 72 MOS

50 SHOCK ABSORBER, NOSE LANDING GEAR

SPL/MRB 8000 CYC OR 72 MOS

51 SKIN, EXTERIOR AIRFRAME

SPL/MRB 1000 CYC

52 SKIN, EXTERIOR AIRFRAME

SPL/MRB 10000 CYC

53 SPAR CAP, FORWARD UPPER AND LOWER

SPL/MRB 12 MOS

54 SPAR CAP, FORWARD UPPER AND LOWER

SPL/MRB 60 MOS

55 STANDBY POWER SUPPLY BATTERY

SPL/MRB 6 MOS

56 STARTER GENERATOR QAD ATTACHMENT FLANGE

SPL/MRB WHEN S-G IS REMOVED

57 STATIC SYSTEM SPL/MRB NAT.REQ.

24 MOS

58 WINDSHIELD CORNERS DOUBLERS AND CLIPS

SPL/MRB 1000 CYC

59 WINDSHIELD CORNERS DOUBLERS AND CLIPS

SPL/MRB 10000 CYC

60 WING BOLT, INCONEL (Inspect)

SPL/MRB 60 MOS

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 7-5 HARD TIME COMPONENTS / SPECIAL INSPECTIONS

Sample Aircraft This Special Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004. SPL = Special Inspecktion

MOS = Months CYC = Cycles HRS = Hours

Pos: ITEM: INSPECTION: INTERVAL: NON CERTIFYING STAFF:

CERTIFYING STAFF:

61 WING BOLT, INCONEL REPLACE Refer to SIRM 62 WING BOLT, SHEAR REPLACE Refer to SIRM 63 WING CENTER SECTION

UPPER BONDED SURFACE PANEL

SPL/MRB 600 HRS

64 WING CENTER SECTION UPPER BONDED SURFACE PANEL

SPL/MRB 18 MOS

Sample Fleet

AMP AIRCRAFT MAINTENANCE PROGRAM

Date: 2005-03-01 Revision: 1

A/C: Sample Aircraft REG: SE-XXX S/N: 17 Page: 8-1 RAISBECK SYSTEMS 200-HRS INSPECTION

Sample Aircraft INSTRUCTION AND RELEASE CARD This Special Inspection is based on P/N 101-590010-19 Revision B9 – October, 2004, REPS Revision 20A – December 2004.

NKF W/O:

SE-XXX

Date:

A/C TT: A/C TOTCYC:

Certifies that the work specified except as otherwise specified was carried out in accordance with PART – 145.50, and in respect to that work the aircraft is considered ready for release to service. CRS Signature:

CRS Approval:

Pos:

Action:

Sign

Pos: Action: MM-Ref: NON

CERTIFYING STAFF:

CERTIFYING STAFF:

1 INSPECT LH PROPELLER 1.2.1 2 LUBRICATE LH PROPELLER 1.2.8 3 INSPECT RH PROPELLER 1.2.1 4 LUBRICATE RH PROPELLER 1.2.8 5 INSPECT LH RAM AIR RECOVERY

SYSTEM 2.2.1

6 INSPECT LH INERTIAL PARTICLE SEPARATOR ACTUATION MECHANISM

2.2.3

7 LUBRICATE THE LH PARTICLE SEPARATOR HINGE AND THE ACTUATOR LINKAGE

2.2.4

8 INSPECT RH RAM AIR RECOVERY SYSTEM

2.2.1

9 INSPECT RH INERTIAL PARTICLE SEPARATOR ACTUATION MECHANISM

2.2.3

10 LUBRICATE THE RH PARTICLE SEPARATOR HINGE AND THE ACTUATOR LINKAGE

2.2.4

11 INSPECT THE ENHANCED PERFORMANCE LEADING EDGES SYSTEM

3.2.1

12 LUBRICATE MAIN LANDING GEAR DOORS

6.2.7