AMM-Vol1_05_11_12_Rev21

AQUILA AT01Aviation by Excellence GmbH

MAINTENANCE MANUAL AQUILA Aviation by Excellence GmbH

MAINTENANCE MANUALMODEL AQUILA AT01Doc.-No. MM-AT01-1020-100 Issued: September, 2001

This document is protected by copyright. All associated rights, in particular those of translation, reprinting, reproduction by photo mechanical or similar means and storing in data processing facilities in whole or part are reserved.

AQUILA Aviation by Excellence GmbH Flugplatz 14959 Schnhagen

Phone:++49 33 731 707 - 0 Fax: ++49 33 731 707 - 11 e-mail: [email protected]


MAINTENANCE MANUAL


Table of Contents

MAINTENANCE MANUAL

TABLE OF CONTENTS

Cha/Sec/Sub

Title TABLE OF CONTENTS INTRODUCTION LIST OF EFFECTIVE CHAPTERS

04 04-00-00 05 05-00-00 05-00-01 05-20-00 05-30-00 05-50-00 06 06-00-00 06-10-00 06-20-00 06-30-00 07 07-00-00 07-10-00 08 08-00-00 08-10-00 08-20-00 09 09-00-00 09-10-00 09-20-00 10 10-00-00 10-10-00 10-11-00 10-20-00 10-30-00 11 11-00-00

AIRWORTHINESS LIMITATIONS Airworthiness Limitations - General TIME LIMITS / MAINTENANCE CHECKS Time Limits / Maintenance Checks - General Component Time Limits Scheduled Maintenance Checks Daily Inspections Unscheduled Maintenance Checks DIMENSIONS AND AREAS Dimensions And Areas - General Aircraft Dimensions and Areas Aircraft Zoning Access/Inspection Plates LIFTING AND SHORING Lifting and Shoring - General Jacking LEVELING AND WEIGHING Leveling and Weighing - General Weighing Leveling TOWING AND TAXIING Towing and Taxiing - General Towing Taxiing PARKING, MOORING, STORAGE AND RETURN TO SERVICE Parking, Mooring, Storage and Return to Service - General Parking Storage Mooring Return to Service PLACARDS AND MARKINGS Placards and Markings - General

TOC

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MAINTENANCE MANUAL

TABLE OF CONTENTS (Cont.)

Cha/Sec/Sub 11-20-00 11-30-00 12 12-00-00 12-10-00 12-11-00 12-12-00 12-13-00 12-14-00 12-15-00 12-16-00 12-17-00 12-20-00 12-21-00 12-22-00 12-23-00 12-24-00 12-30-00 20 20-00-00 20-10-00 20-11-00 21 21-00-00 21-20-00 21-20-00 21-40-00 23 23-00-00 23-10-00 23-10-00 23-50-00 24 24-00-00 24-00-00 24-20-00 24-20-00 24-30-00

Title Exterior Placards Interior Placards SERVICING Servicing - General Replenishing - Description Fuel Servicing Engine Oil - Servicing Induction Air Filter - Servicing Cooling System - Servicing Brake System - Servicing Tires - Servicing Battery - Servicing Scheduled Servicing - Description Lubricants - Description Lubrication - Servicing Aircraft Exterior - Cleaning and Care Aircraft Interior - Cleaning and Care Unscheduled Servicing STANDARD PRACTICES AIRFRAME Standard Practices Airframe - General Fastener Identification and Torque Data Conversion Data VENTILATION AND HEATING Ventilation and Heating - General Fresh Air Distribution - Description Fresh Air Distribution - Maintenance Practices Heating - Maintenance Practices COMMUNICATIONS Communications - General Speech Communication - Description Speech Communication - Maintenance Practices Audio Integrating - Maintenance Practices ELECTRICAL POWER Electrical Power - General Electrical Power - Troubleshooting Alternator System - Description Alternator System - Maintenance Practices Battery System - Description

TOC

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Cha/Sec/Sub 24-30-00 24-40-00 24-60-00 24-61-00 25 25-00-00 25-10-00 25-11-00 25-21-00 25-50-00 25-60-00 25-60-00 25-60-01 27 27-00-00 27-10-00 27-10-00 27-20-00 27-20-00 27-30-00 27-30-00 27-31-00 27-31-00 27-50-00 27-50-00 28 28-00-00 28-10-00 28-10-00 28-20-00 28-20-00 28-40-00 28-40-00 31 31-00 00 31-10-00 31-30-00

Title Battery - Maintenance Practices External Power - Maintenance Practices Electrical Load Distribution Description Circuit Breaker - Maintenance Practices EQUIPMENT / FURNISHINGS Equipment / Furnishings - General Seats - Maintenance Practices Restraint Systems - Maintenance Practices Cabin Interior - Maintenance Practices Cargo Tie Downs - Maintenance Practices Emergency - Description Emergency - Maintenance Practices Fire Extinguisher - Maintenance Practices FLIGHT CONTROLS Flight Controls - General Aileron Control System - Description Aileron Control System - Maintenance Practices Rudder Control System - Description Rudder Control System - Maintenance Practices Elevator Control System - Description Elevator Control System - Maintenance Practices Elevator Trim Control System - Description Elevator Trim Control System - Maintenance Practices Flap Control System - Description Flap Control System - Maintenance Practices FUEL Fuel - General Fuel Storage - Description Fuel Storage - Maintenance Practices Fuel Distribution - Description Fuel Distribution - Maintenance Practices Fuel Indicating - Description Fuel Indicating - Maintenance Practices INDICATING / RECORDING SYSTEMS General Instrument Panel - Maintenance Practices Recorders - Maintenance Practices

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Cha/Sec/Sub 32 32-00-00 32-10-00 32-10-00 32-20-00 32-20-00 32-40-00 32-40-00 33 33-00-00 33-40-00 34 34-00-00 34-10-00 34-10-00 34-11-00 34-11-00 34-20-00 34-21-00 34-40-00 34-41-00 34-50-00 51 51-00-00 51-10-00 51-20-00 52 52-00-00 52-10-00 53 53-00-00 53-10-00 53-10-00 55 55-00-00 55-10-00 55-20-00

Title LANDING GEAR Landing Gear - General Main Gear - Description Main Gear - Maintenance Practices Nose Gear - Description Nose Gear - Maintenance Practices Wheels and Brakes - Description Wheels and Brakes - Maintenance Practices LIGHTS Lights - General Exterior Lights - Maintenance Practices NAVIGATION Navigation - General Pitot / Static System - Description Pitot / Static System - Maintenance Practices Stall Warning System - Description Stall Warning System - Maintenance Practices Attitude and Direction - Maintenance Practices Integrated Flight System - Maintenance Practices Independent Position Determining - Maintenance Practices FLARM Collision Warning System - Maintenance Practices Dependent Position Determining - Maintenance Practices STRUCTURES Structures - General Fiberglass Laminate Structures - Maintenance Practices Repair of Fiberglass Laminate Components DOORS Doors - General Canopy - Maintenance Practices FUSELAGE Fuselage - General Fuselage - Main Frame fuselage - Maintenance Practices STABILIZERS Stabilizers - General Horizontal Stabilizer - Maintenance Practices Elevator - Maintenance Practices

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Cha/Sec/Sub 55-30-00 55-40-00 57 57-00-00 57-10-00 57-50-00 61 61-00-00 61-00-00 61-10-00 61-20-00 71 71-00-00 71-00-01 71-00-01 71-00-01 71-10-00 71-20-00 71-60-00 74 74-00-00 74-10-00 75 75-00-00 75-10-00 75-10-01 76 76-00-00 76-10-00 77 77-00-00 77-10-00 77-20-00 78 78-00-00 78-10-00

Title Vertical Stabilizer - Maintenance Practices Rudder - Maintenance Practices WINGS Wings - General Wings- Maintenance Practices Control Surfaces - Maintenance Practices PROPELLER Propeller - General Troubleshooting Propeller Assembly - Maintenance Practices Propeller control - Maintenance Practices POWERPLANT Powerplant - General Engine Description Troubleshooting - ROTAX Engines 912S ROTAX Engines 912S - Maintenance Practices Cowling - Maintenance Practices Engine Mount - Maintenance Practices Air Induction System - Maintenance Practices IGNITION SYSTEM Ignition System - General Ignition System - Maintenance Practices COOLING SYSTEM Cooling System - General Engine Cooling System - Maintenance Practices Winterization Kit - Maintenance Practices ENGINE CONTROLS Engine Controls - General Engine Controls - Maintenance Practices ENGINE INDICATING Engine Indicating - General Power - Maintenance Practices Temperature - Maintenance Practices EXHAUST Exhaust - General Exhaust - Maintenance Practices Page 05 05.11.12

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MAINTENANCE MANUAL


Cha/Sec/Sub 79 79-00-00 79-10-00 79-20-00 79-30-00 79-31-00 80 80-00-00 80-10-00 91 91-00-00

Title OIL Oil - General Oil Tank - Maintenance Practices Oil Cooler - Maintenance Practices Oil Temperature Measuring System - Maintenance Practices Oil Pressure Measuring System - Maintenance Practices STARTING Starting - General Starter - Maintenance Practices CHARTS AND DIAGRAMS Charts and Diagrams - General

TOC

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Record of Revisions

MAINTENANCE MANUAL

RECORD OF REVISIONS Revision Number Date of Revision Date Inserted By Revision Number Date of Revision Date Inserted By

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21

01.10.01 29.10.01 05.11.01 07.11.01 26.11.01 01.03.02 15.03.02 22.03.02 14.05.02 18.05.02 08.07.02 26.04.05 28.10.05 18.01.06 30.04.08 15.09.09 02.03.10 21.06.10 25.11.10 24.02.11 05.11.12


MAINTENANCE MANUAL


Record of Temp. Revisions

MAINTENANCE MANUAL

RECORD OF TEMPORARY REVISIONS Temp. Revision Number Page Date of Revision By Date Removed By


MAINTENANCE MANUAL


Introduction

MAINTENANCE MANUAL

INTRODUCTION

1. General This maintenance manual provides to maintenance personnel all information necessary for the maintenance of the AQUILA AT01. It contains detailed descriptions of the systems, troubleshooting and maintenance practices. This handbook only contains maintenance practices to be carried out on the aircraft, e.g. removal and installation of components. Maintenance, repairs and inspections must be accomplished in accordance with the instructions given in this Maintenance Manual (MM). 2. List of Technical Publications A. Use the MM in conjunction with the technical publications listed in the table 01. NOTE: Due to the multiplicity of equipment coming onto the market the following list may be incomplete. If there is no information given on a certain component, use the documentation provided by the manufacturer of this component.

Table 01 - List of Technical Publications

No.

Manual No./Part No. Doc-No. AFM-AT01-1010100-E, Revision A.01 or a later Revision ROTAX Part No. 899735 Edition 2, Rev. 0, October 01/2009, or a later Revision ROTAX Part No. 899471 Edition 2, Rev. 0, May 01/2009, or a later Revision ROTAX Part No. 899371 Edition 1, Rev. 1, January 01/2007, or a later Revision

Title

available from Aquila Aviation by Excellence GmbH

1

Airplane Flight Manual Maintenance Manual ROTAX Engine Type 912 Series (Line Maintenance) OM ROTAX Engine Type 912 Series

2

BRP-Rotax

3

BRP-Rotax

4

IPC ROTAX Engine Type 912 Series

BRP-Rotax

5

Operation & Installation Manual, E-124, Issue No. 34, March 11, Hydraulically Controlled Variable Pitch 2005 or a later Issue Propeller E-699, Issue No. 7, Sep. 15, 2004 or a later Issue E-1046, Issue No. 3, April 20, 2005 or a later Issue Hydraulic Constant Speed Governors P41( )-( ) . . Hydraulic Propeller Governor w/ Reverse P - 9 ( ) ( ) - ( ) series

mt-Propeller Entwicklung GmbH mt-Propeller Entwicklung GmbH mt-Propeller Entwicklung GmbH

6

7

Page 01

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Table 01 - List of Technical Publications (Cont.)

No.

Manual No./Part No. 006-15545-0002, Rev. 2, December 1999, or a later Revision 006-10607-0000, Rev. 0, November 1999, or a later Revision 190-00140-02, latest Revision

Title Honeywell Maintenance Manual, Bendix/King KT 76 C ATCRBC Transponder Honeywell Installation Manual, Bendix/King KMD 150 MFD/GPS

available from

8

Honeywell International Inc. Honeywell International Inc.

9

10

400 Series Installation Manual

Garmin International

11

190-00149-01, latest Revision

GMA 340 Audio Panel Installation Manual


12

006-10563-0004, latest Revision 190-00207-02, latest Revision 190-00181-02, latest Revision 560-0404-03a or any later Revision

Installation Manual Bendix/King KT 73 Garmin International Mode S Transponder GTX 330 Transponder Installation Manual

13


14

500 Series Installation Manual


15

Apollo SL30 NAV/COMM Installation Manual

Garmin AT, Inc.

16

500-301, latest Revision

FlymapL Installation Manual

Stauff Systec GmbH

17

---, latest Revision

Installation Manual FLARM Collision Warning Unit GTX 328 Transponder Installation Manual

FLARM

18

190-00420-04, latest Revision DMA 174 L Ref. 0139162 L, latest Revision DOC 06006C Ref. 0141922C, latest Revision


19

Installation Manual/Operation Manual/ Inspection Log Martec SERPE-IESM Kannad 406 AF Installation Manual/Operation Manual/ Inspection Log Martec SERPE-IESM Kannad 406 AF-Compact

20

INTRODUCTION

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Table 01 - List of Technical Publications (Cont.)

No.

Manual No./Part No.

Title

available from

21

190-01007, latest Revision

GTN6XX/7XX AML STC Installation Manual


22

190-01134-11, latest Revision 900-00003-001, latest Revision

GMA 350/350H Installation Manual


23

EFD1000 and EFD500 Software Version 2.x Installation Manual VT-01 Transponder Installation Manual VT-02 Transponder Installation Manual

Aspen Avionics

24

01.0200.11E, latest Revision

Garrecht Avionik GmbH

25

02.0200.11E, latest Revision

Garrecht Avionik GmbH

Page 03

INTRODUCTION

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Introduction

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3. Structure of the Maintenance Manual The MM has been prepared in accordance with the Air Transport Association (ATA) Specification Number 100 for Manufacturers Technical Data. A. Classification of Subject Matter The MM is divided into 5 major sections. Each of these sections is sub-divided into chapters. A list of effective pages and the table of contents are provided at the beginning of each MM chapter. (1) (2) (3) (4) (5) General Airframe Systems Structures Propeller Power Plant Ch. 05 - 12 Ch. 20 - 37 Ch. 51 - 57 Ch. 61 Ch. 71 - 80

Each chapter is identified by a separator sheet with the chapter number and the title.

B.

Page Numbering System (1) The page numbering system consists of three-element numbers separated by dashes. The first element identifies a system: e.g. 27 Flight Controls (a chapter) The second element identifis a subsystem in the system: e.g. 27-30 Elevator (a section) If the system comprises several subsystems, further sections are added: e.g. 27 - 31 Elevator Trim Control (a further section) The last number permits the identification of the individual units in a system or subsystem. However, this number is only used when detailed description of such individual units is required. Example:

27 - 10 - 00

Chapter/ System (here FlightControls)

Section/ Subsystem (here Ailerons)

Subject/ Unit

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(2) When the chapter/system element number is followed by zeros in the section/subsystem and subject/unit element number (28-00-00), the information is applicable to the entire system. (3) When the section/subsystem element number is followed by zeros in the subject/unit element number (28-20-00), the information is applicable to subsystem within the system. (4) The subject/unit element number is used to identify information applicable to units within the subsystems. This breakdown of the chapters provides a good overview and facilitates the exchange of revised pages. Since most of the systems are relatively simple, the third element is used only in the more complex systems, i.e. if it appears necessary to describe a unit or device in greater detail. (5) All maintenance data given in the MM is divided into specific types of information. This facilitates work with the manual. For this purpose, page number blocks are reserved depending on type of information. Page 1 - 99 Page 101 - 199 Page 201 - 299 Page 301 - 399 Page 401 - 499 Page 501 - 599 Page 601 - 699 Page 701 - 799 Page 801 - 899 Description and Operation Troubleshooting Maintenance Practices Servicing Removal/Installation Adjustment/Test Inspection/Check Cleaning/Painting Repairs

Example page number:

Page 301 12 - 17 - 00 15.11.04 Servicing Battery

First page with service instructions Publication date

(6) Figures are numbered consecutively within each topic. Example: Fig. 201 Fig. 202 1. Illustration for maintenance 2. Illustration for maintenance etc.

C.

Page Order (1) In the front of the manual: Title Table of Contents Record of Revisions

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Record of Temporary Revisions Introduction List of Effective Chapters

(2) Each chapter begins with: Title Table of Contents D. Figures The figures within the sections of a chapter are numbered in accordance with the appropriate page number block. Numbering begins with one (1) and is continuous.

4. Using the Maintenance Manual A. To obtain information about a specific system, refer to the List of Effective Chapters in the front of the manual to find the corresponding chapter number. In the table of contents of the respective chapter, one then finds more detailed information about the arrangement of material.

Meter Common Pin 2 (blk) Pin 2 (blk) Pin 2 (bik) Pin 3 (grn) Pin 3 (grn) Pin 3 (grn) Pin 3 (grn)

Meter Plus Pin 4 (red) Pin 1 (wht) Pin 3 (grn) Pin 1 (wht) Pin 1 (wht) Pin 1 (wht) Pin 1 (wht)

PSI 0 0 0 0 10 30 60

Desired Value (VDC) 4.95 to 5.0 1.70 to 2.10 1.70 to 2.10 -0.003 to +0.003 0.031 to +0.034 0.028 to +0.032 0.028 to +0.032

Unit under test 3010016,17,18 3010016,17,18 3010016,17,18 3010016,17,18 3010016 3010017 3010018

EFFECTIVITY

Aircraft equipped with VM 1000 Engine Management System

77-40-00

Page 101 13.07.01

effectivity block

Effectivity Block Figure 01

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B.

Effectivity This Maintenance Manual is "customized". It includes the following effectivity identification system to show modification and/or configuration differences. (1) The MM starts with a List of Effective Chapters. Each chapter is listed with date of issue or revision. (2) To identify the aircraft an effectivity statement (i.e. Garmin Avionics) or a six-digit numeric indicator is shown in the effectivity column in the table of contents if applicable. (a) The six-digit numeric indicator begins with the last three digits of the lowest assigned number, to indicate first effectivity, and ends with the last three digits of the highest assigned number, to indicate last effectivity, of an unbroken sequence of assigned numbers. A hyphen is shown between the numbers. Open ended effectivity is indicated by "999" in the last effectivity if applicable. For example: 023-999 indicates aircraft 023 and subsequent. (3) Effectivity Block The system provides further direct annotation of applicability on the pages. On pages not applicable for all aircraft, an effectivity block appears at the bottom left-hand corner. Effectivity identification may be a six-digit numeric indicator (ref. to (2)(a)) or an effectivity statement (refer to Figure 01). The information on that page applies only to the aircraft noted in the effectivity block. NOTE: Pages with no effectivity block may be followed by pages with effectivity blocks and vice versa and have identical page numbers.

C.

Revisions (1) Maintenance manual revisions, caused by variety of reasons (regulation changes, technical changes, typographical errors, etc.), will be published regularly. Revision notification contains a note explaining the revision along with: - the revised manual chapters - the reason of revision - the affected airplane serial numbers

(2) Should a revision be urgently required between regular updating, a temporary revision will be issued. The relevant pages are yellow and will usually be incorporated in the next scheduled revision of the maintenance manual. (3) Identifying revised material (a) Revisions and-/or additions will be identified by a vertical black line (revision bar) in the outer margin of the page opposite the text/illustration that has been changed.

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(b) When technical changes result in unaltered texts slipping on to a different page, a revision bar will be placed in the outside margin, opposite the chapter/section/subject, page number and date of all affected pages, providing no other revision bar appears on the page. (4) Incorporating revisions into the manual (a) In order to keep track of revisions and to facilitate the use of the manual, a revision always affects the entire chapter, i.e. all pages of a chapter have the same date of issue or revision and the entire chapter is replaced during a revision. (b) MM revisions contain an effectivity page. Chapters to be removed or inserted are listed in sequence and assigned with the respective action. Incorporation of revisions into the manual must be documented in the record of revisions at the front of the MM. (c) Temporary revisions are issued as single pages and must be incorporated according to the notes on the effectivity page delivered with the revision. They become invalid and must be removed when the corresponding permanent revision is issued.

D.

WARNINGS, CAUTIONS, and NOTES When carrying out maintenance on the airplane, general safety and maintenance rules should always be observed. In addition, the MM contains warnings, cautions and notes to highlight or emphasize important and critical instructions. WARNING: Hazard for maintenance personnel! CAUTION: Hazard for systems and equipment! NOTE: Specific information

E.

Abbreviations Where it appears reasonable, abbreviations are used. They conform to recognized standards.

INTRODUCTION

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List of Chapters

MAINTENANCE MANUAL

LIST OF EFFECTIVE CHAPTERS

Chapter Title GENERAL Introduction Airworthiness Limitations Time Limits / Maintenance Checks Dimensions and Areas Lifting & Shoring Leveling and Weighing Towing and Taxiing Parking, Mooring, Storage & Return to Service Placards and Markings Servicing

Date*

04 05 06 07 08 09 10 11 12

05.11.12 28.10.05 05.11.12 26.04.05 02.03.10 27.09.01 02.03.10 02.03.10 05.11.12 05.11.12

AIRFRAME SYSTEMS 20 21 23 24 25 27 28 31 32 33 34 Standard Practices Airframe Ventilation and Heating Communications Electrical Power Equipment and Furnishings Flight Controls Fuel Indicating/Recording Systems Landing Gear Lights Navigation 05.11.12 08.07.02 30.04.08 05.11.12 05.11.12 24.02.11 05.11.12 05.11.12 15.03.02 05.11.12 05.11.12

STRUCTURES 51 52 53 55 57 Structures Doors Fuselage Stabilizers Wings 05.11.12 05.11.12 14.05.02 14.05.02 18.01.06

PROPELLER 61 Propeller 26.04.05


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Chapter Title

Date*

POWER PLANT 71 74 75 76 77 78 79 80 91 Power Plant Ignition Engine Cooling System Engine Controls Engine Indicating Exhaust Oil Starting Charts and Wiring Diagrams 26.04.05 29.10.01 26.04.05 26.04.05 26.11.01 07.11.01 07.11.01 05.11.01 30.04.08

* The date refers to the issue / revision date of the respective chapter.


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CHAPTER 4 AIRWORTHINESS LIMITATIONS


MAINTENANCE MANUAL


Airworthiness Limitations

MAINTENANCE MANUAL

RECORD OF REVISIONS - CHAPTER 4 Revision Number Date of Revision 14.09.01 Revised Pages LBA Approval Signature and Date

Descriptions of Revisions Original Issue

01

20.06.02

LOEP Page 01 LOR Page 01 Sec 04-00-01 Page 01, 02

1st Revision 1st Revision Revised Paragraph 2.B., 2.D.

02

28.10.05

ROR Page 01 TOC Page 01 Sec 04-00-00 Page 01

2nd Revision 1st Revision General Revision

Page 01

04 - RECORD OF REVISIONS

28.10.05


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MAINTENANCE MANUAL

TABLE OF CONTENTS

Title

Chapter Section Subject

Page 1 1 1 1

AIRWORTHINESS LIMITATIONS .................................................................04-00-00 Introduction 04-00-00 Airworthiness Limitations 04-00-00 Continued Airworthiness 04-00-00

Page 01

04 - TOC

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MAINTENANCE MANUAL

AIRWORTHINESS LIMITATIONS - GENERAL

1. Introduction This chapter gives information on mandatory replacement times of structural parts, and where applicable, on inspection periods for airframe structure for the AQUILA AT01. All mandatory limitations listed are established by the airframe manufacturer. Compliance with the specified times and intervals is mandatory for maintaining the airworthiness of the aircraft. THE "AIRWORTHINESS LIMITATIONS" CHAPTER IS LBA APPROVED. THE "AIRWORTHINESS LIMITATIONS" CHAPTER IS FAA APPROVED AND SPECIFIES MAINTENANCE REQUIRED UNDER SECS. 43.16 AND 91.403 OF THE FEDERAL AVIATION REGULATIONS UNLESS AN ALTERNATIVE PROGRAM HAS BEEN FAA APPROVED.

2. Airworthiness Limitations A. A comprehensive airframe inspection is mandatory after 6000 h of flight time to reach an extension of replacement time. The corresponding inspection program will be announced by the AQUILA Technische Entwicklungen GmbH prior to the highest time AQUILA AT01 reaching 6000 h. Outside Painting of the Airframe All structural parts which are imposed to direct vertical sunlight have to be painted WHITE except of areas provided for registration signs and warning paint. Repairs Repairs for which is no description in chapter 51 of this manual may only be carried out under the authority of the manufacturer or with a special repair approval from the manufacturer.

B.

C.

3. Continued Airworthiness Scheduled inspections of the airplane including replacement and overhaul of defined components are required to ensure Continued Airworthiness of the AQUILA AT01 airplane. Maintenance Checklists and Time Limits as listed in Chapter 05 should be applied to ensure Continued Airworthiness of the AQUILA AT01 unless an alternate inspection programme is agreed on with the competent National Civil Aviation Authority.

04-00-00

Page 01 28.10.05


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MAINTENANCE MANUAL

CHAPTER 5 TIME LIMITS / MAINTENANCE CHECKS


MAINTENANCE MANUAL


Maintenance Checks

MAINTENANCE MANUAL

TABLE OF CONTENTS

Title


Page 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

TIME LIMITS / MAINTENANCE CHECKS - GENERAL ...........................05-00-00 Introduction 05-00-00 General Description 05-00-00 COMPONENT TIME LIMITS .........................................................................05-00-01 General 05-00-01 Component Time Limits 05-00-01 SCHEDULED MAINTENANCE CHECKS....................................................05-20-00 General 05-20-00 Inspection Time Intervals Chart AQUILA AT01 05-20-00 DAILY INSPECTIONS ......................................................................................05-30-00 General 05-30-00 Preflight Inspection 05-30-00 After Flights 05-30-00 UNSCHEDULED MAINTENANCE CHECKS .............................................05-50-00 General 05-50-00 Special Inspections 05-50-00

05 - TOC

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Maintenance Checks

MAINTENANCE MANUAL

TIME LIMITS / MAINTENANCE CHECKS - GENERAL

1. Introduction A. This chapter provides scheduled and unscheduled maintenance checks and inspections for the AQUILA AT01, recommended by the Type Certificate Holder AQUILA Aviation by Excellence GmbH as well as the time limits for service life limited components and parts.

2. General Description In the following, a brief description and intended purpose of each section of this chapter is given. A. Section 05-00-00 - Time limits / Maintenance Checks - General. This section provides a general overview of the content and purpose of this chapter. Section 05-00-01 Component Time Limits. This section contains the time limits of all service life limited components and parts and recommended time between overhaul (TBO) for components. Section 05-20-00 - Scheduled Maintenance Checks. This section contains information about recommended scheduled maintenance and inspections. The recommended maintenance and inspection program for the systems and components of the AQUILA AT01 as well as the relevant intervals are embodied in a checklist included in this section. Section 05-30-00 - Daily Inspections. In this section the preflight check and the checks after flights are described. Section 05-50-00 - Unscheduled Maintenance Checks. This section specifies checks, which have to be conducted after unusual events and incidences such as hard landings.

B.

C.

D.

E.

05-00-00

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Maintenance Checks

MAINTENANCE MANUAL

COMPONENT TIME LIMITS

1. General A. Different components and parts of the aircraft are certified for specific service life. When reaching this time limit, the respective item must be replaced or overhauled. In order to monitor permissible service life the installation or removal of each item must be recorded in the aircraft logbook. Where an interval is given in both flight time and calendar time, the limit which is reached first must be applied.

2. Component Time Limits A. Under certain circumstances the replacement or overhaul of components may be required before the time limits listed below are rached. Replacement time limits, mandated by the type certificate holder AQUILA Aviation by Excellence GmbH:

B.

Chapter 25

Component / Part Restraint assy Pilot / Co-Pilot Rubber elements of the elastomer spring package at the nose gear Flexible hoses of the aircraft brake system Engine shock mounts

Replacement Time no

Overhaul 12 years

32

5 years

no

32

10 years

no

71

with engine overhaul

no

05-00-01

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Maintenance Checks

C.

Vendor Established Component Time Limits Chapter 25 25 Component / Part ELT battery Fire extinguisher Air Total Fire extinguisher H3R ASPEN internal battery KMD 150 MFD/GPS internal battery WINTER instruments Propeller MTV-21-A/175-05 Propeller governor Woodward A210786 Propeller governor P-410-13 Propeller governor P-850-12 Engine ROTAX 912S Replacement Time Note 1 10 years Overhaul no Note 4

25

12 years

no

31

3 years

no

34

10 years (recommended) no no

no

34 61

Note 6 2000 h or 6 years Note 2 6 years, with engine Note 4 2000 h or 6 years Note 2 2000 h or 6 years Note 2 2000 h or 15 years, 1500 h or 12 years, 1200 h or 10 years, Note 3 no

61

no

61

no

61

no

71

no

71

ROTAX mechanical fuel pump ROTAX flexible fuel lines ROTAX rubber parts of the engine (V-belt, hoses, carburetor parts)

5 years

71

5 years

no

71

5 years Note 3

no

05-00-01

Page 02 05.11.12


MAINTENANCE MANUAL

71

Rubber hoses of the cooling system Oil hoses

5 years

no

71

on condition Note 5 200 h

no

71

Spark plugs

no

NOTES: Note 1: Note 2: Refer to manufacturer instructions for battery replacement time limits. Refer to latest issue of the mt-propeller Service Bulletin No. 1.-( ), and to the mtpropeller E-124 Operation and Installation Manual. Refer to the latest issues of BRP-Rotax concerning the Time Between Overhaul, i.e. Service Bulletins, Service Information, and to the ROTAX Aircraft Engines Maintenance Manual for ROTAX Engine Type 912 Serie. Refer to manufacturer instruction for overhauling. Component has to be checked at every annual inspection. If in good condition service life is extended another 12 months. The maximum service life of 10 years must not be exceeded. Though there is no TBO for these instruments, the manufacturer recommends that airspeed indicators and altimeters are subjected to retesting after 5 years.

Note 3:

Note 4: Note 5:

Note 6:

05-00-01

Page 03 05.11.12


MAINTENANCE MANUAL


Maintenance Checks

MAINTENANCE MANUAL

SCHEDULED MAINTENANCE CHECKS

1. General A. The inspection time intervals chart contained in this chapter shows the recommended intervals at which maintenance and maintenance checks should be carried out on the aircraft. Annual inspections and 100 hour inspections on the AQUILA AT01 must include all inspection items as required by FAR 43, Appendix D, Scope and detail of annual/100h inspections. Chapter 4 Airworthiness Limitations of this manual defines the inspection intervals for continued airworthiness. The following inspection time intervals chart is aircraft-specific and to be used to document the inspections carried out on a specific aircraft. It should not to be used as the primary inspection checklist. B. If an aircraft is being operated under unusual environmental conditions, maintenance intervals may be reduced.

2. AQUILA AT01 Inspection Time Interval Chart A. The maintenance and checks listed are to be carried out at the specified intervals and documented appropriately. NOTE: For new aircraft the first check is carried out after 25 hours and should be of the extent of a 100-hour inspection. Where an interval is given in both flight time and calendar time, the limit which is reached first must be applied.

NOTE:

B.

Due to recent ROTAX publications the maintenance checks given for the ROTAX engine may not be up to date. Refer to the latest revisions of ROTAX Engine Type 912 Series Maintenance Manual and Service Bulletins. Maintenance of the electrical system has to be done in accordance with the applicable national regulations. Due to the multiplicity of equipment coming onto the market, no maintenance instructions are given for electronic equipment. For information on a certain component use the documentation provided by the manufacturer of this component.

C.

D.

NOTES:

Maintenance Manual for ROTAX Engine Type 912 Series (refer to List of Technical Publications in the Introduction section of this manual). MT* mt-propeller E-124 Operation and Installation Manual (refer to List of Technical Publications in the Introduction section of this manual). TSN Time Since New

R*

05-20-00

Page 01 05.11.12


MAINTENANCE MANUAL

Maintenance Checks

C.

AQUILA AT01 Inspection Time Intervals Chart:

Aircraft S/N

Operating Hours

Registration Number Date

Engine S/N

Operating Hours TTSN / TTSO: Operating Hours TTSN / TTSO:

Propeller S/N

Type of Inspection

No.

Pre-Inspection / Engine Ground Test

Reference

Interval 100 h Add.

Initials

1.

Check that the following documents are up-to-date and available upon request. - AT01 Maintenance Manual; - AT01 Airplane Flight Manual; - Aircraft Log Book and Required Certificates; - Engine and Propeller Log Books - Equipment List and Weight and Balance Record; - Airworthiness Directives; - Service Bulletins and Service Information; - Services Time Record. Airworthiness directives - Verify all airworthiness directives have been complied with. Service letters, service bulletins, and service information Verify all Aquila GmbH and suppliers service letters, service bulletins, and service information have been complied with. Service time records, equipment list and weight and balance records - Check. Update if necessary. Aircraft file and technical documentation - Verify complete and in proper order. Engine and engine compartment - Clean for leakage check. Perform an engine test run as follows: Start engine and warm-up at 820 RPM for approx. 2 minutes, continue at 1030 RPM, duration depends on ambient temperature until oil temperature reaches 50 C. Rudder pedal brakes and parking brake - Check for proper operation Propeller governor - Set 1700 RPM and monitor the manifold pressure. Reduce engine speed by moving the propeller control to 200 RPM. Note the RPM drop and manifold pressure. Increase RPM to 1700 RPM. Repeat three times.

AT01 Maintenance Manual, AT01 Airplane Flight Manual

X

2.

X

3.

X

4.

X

5.

X

6.

R* 12-00-00 Sec. 2.1 R* 12-00-00 Sec. 2.8

X

7.

X

1 year

32-40-00

MT* E-124

05-20-00

Page 02 05.11.12


Maintenance Checks

MAINTENANCE MANUAL

No.

Pre-Inspection / Engine Ground Test (Cont.)

Reference

Interval 100 h Add.

Initials

RPM drop: _______RPM / Man. Press :_______in. Hg Engine instruments - Check engine parameters. Magneto RPM drop - Set 1700 RPM. Check that RPM drop is less than 120 RPM while operating on one magneto and no more than a 50 RPM drop difference between left and right magnetos. RPM drop left magneto :_______RPM RPM drop right magneto:_______RPM Carburetor heat - Pull carburetor heat knob at 1700 RPM. Engine RPM should show a drop of at least 20 RPM. RPM drop:_______RPM Engine full power - Advance throttle to full forward. Tachometer should read 2265 50 RPM. Full power RPM:_______RPM Engine idle - Move throttle control lever to full aft. Tachometer should read 750 +50 RPM. Idle RPM:_______RPM Cool down engine at 1100 RPM. Shut down engine, set the ignition switch and the master switch to the OFF position. Remove ignition key from aircraft. 8. Airframe, power plant, propeller - Do a walk around to detect damages, fluid leaks or other abnormalities. Fuselage and empennage - Clean. Aircraft interior - Clean and vacuum. Record all malfunctions and abnormalities. X R* 12-00-00 Sec. 2.8

9. 10. 11.

X X X

No.

Engine

Reference

Interval 100 h Add.X 1 year

Initials

1.

Engine cowling - Remove engine cowling. Check for cracks, overheated areas, deformation, loose or missing fasteners. Check condition of fire protect paint and heat resistance shielding. Engine oil - Drain and change. Remove old oil filter from engine and install new oil filter. 12-12-00 R* 12-20-00 Sec. 11.3, 11.4

2.

X

50 h 1) 1 year

1) If more than 30% of operation hours have been flown with leaded fuel e.g.: AVGAS 100LL (SI-912-016)

05-20-00

Page 03 05.11.12


MAINTENANCE MANUAL

Maintenance Checks

No.

Engine (Cont.)

Reference

Interval 100 h Add.

Initials

CAUTION: DO NOT USE AIRCRAFT ENGINE OIL. Due to the friction clutch and the high stresses in the reduction gear 4-stroke motor cycle oils are recommended. For suitable lubricants and oil change intervals, see ROTAX Operators Manual and latest appropriate ROTAX publications. Remove oil drain screw from oil tank. Drain old oil and dispose of in accordance with environmental regulations. Remove oil filter from engine and install a new oil filter. Lubricate mating sealing ring of new oil filter with engine oil. Tighten new oil filter by hand. Renew gasket ring of drain screw on oil tank. Tighten drain screw to 25 Nm (220 in. lb). Check oil tank - Refill oil tank with approx. 3 liters of oil. For oil quality, see Operators Manual and SI-912-016 latest edition. Refilled:______________Quantity:_______L

SI-912-016 latest Rev. SB-912-033 latest Rev.

SI-27-1997, latest Rev. SI-912-010, latest Rev. SB-912-040, latest Rev. R* 12-20-00 Sec. 11.2, 11.6

3.

Oil change Cut open old oil filter and check for particles.

R* 12-20-00 Sec. 11.5

X

50 h 1) 1 year

Findings_____________________ 4. Visual inspection of the magnetic plug for accumulation of chips Check compression by differential pressure method. Test pressure: 6 bar (appr. 6000 hpa / 87 psi) Pressure drop: max. 25% cyl. 1 2 3 4 Pressure drop: 6. _____ _____ _____ _____ R* 12-20-00 Sec. 3 SB-912-029, latest Rev. R* 12-20-00 Sec. 4 R* 12-00-00 Sec. 9.3 12-14-00 R* 12-20-00 Sec. 9.1 75-10-00 X 1 year X 1 year X 1 year recommended 50 h R* 12-20-00 Sec. 12 R* 12-20-00 Sec. 5 X 1 year

5.

200 h

Cooling air ducts, engine baffling and cylinder cooling fins - Check for obstructions, cracks, wear and general condition. Check for signs of abnormal temperatures. Check crankcase for cracks.

7.

Leakage bore at the base of the water pump - Check for signs of leakage. Cooling system - Flush the cooling system where conventional coolants are used.

8.

when replacing the coolant

9.

Coolant hoses and lines - Check for damage, leakage, hardening due to heat, porosity, loose connections and secure attachments. Check routing for kinks and narrow bends.

1) If more than 30% of operation hours have been flown with leaded fuel e.g.: AVGAS 100LL (SI-912-016)

05-20-00

Page 04 05.11.12


Maintenance Checks

MAINTENANCE MANUAL

No.

Engine (Cont.)

Reference

Interval 100 h Add.

Initials

10.

Coolant expansion tank - Check for damage and abnormalities. Inspect rubber protection plate on tank base for secure fit. Check coolant level, replenish as necessary. Check coolant with densimeter. Check gasket of radiator cover, inspect pressure control valve, and return valve. The pressure control valve opens at 1,2 bar (18 psi). Overflow bottle - Inspect for damage and abnormalities. Verify coolant level, replenish as necessary. Inspect venting bore in cap of overflow bottle for clear passage. Line from exp. tank to overflow bottle - Check for damage, leakage and clear passage. Oil and coolant radiator - Check for obstructions, leaks and security of attachment. If necessary, clean cooling fins and do a pressure leakage test. Oil lines - Inspect for damage, leakage, hardening due to heat, porosity, security of connections and attachments. Check routing for kinks or narrow bends. Check fire protection shielding. Oil tank vent line - Check for proper routing, for obstructions and clear passage

R* 12-20-00 Sec. 9.1 75-10-00 SB-912-043, latest Rev.

X

1 year

11.

R* 12-20-00 Sec. 9.5 75-10-00

X

1 year

12.

79-20-00

X

1 year

13.

R* 12-20-00 Sec. 4

X

1 year

14.

X

1 year

15.

Fuel lines - Check for damage, leakage, hardening due to heat, R* 12-20-00 porosity, secure connections and attachments. Sec. 4 Check routing for kinks or narrow bends. If applicable check also steel fuel lines for cracks and scuffing marks. Fuel selector / shut-off valve - Check for security of attachment. Check that the valve engages noticeable into the positions LEFT, RIGHT, and OFF. Filter element of electrical fuel pump - inspect and clean. 28-20-00 Para. 4, 5 12-17-00

X

1 year

16.

X

1 year

17.

X

1 year

18.

Battery - Clean. Check correct acid level, charge and capacity. Check battery vent case for obstructions and proper routing. If necessary, replenish and charge battery. Battery tray, terminals and cables - Check for security, corrosion and general condition. Starter - Check security of attachment and electrical connections. Alternator - Check attachment and V-belt tension. Inspect electrical connections.

X

1 year

19.

X

1 year

20.

R* 12-00-00 Sec. 6.1 R* 12-20-00 Sec. 6

X

1 year

21.

X

1 year

22.

Spark plugs - Remove all spark plugs, check the heat range R* 12-20-00 designation, clean, check electrode gap and adjust if necessary. Sec. 14.2 Replace as required.

X

1 year

05-20-00

Page 05 05.11.12


MAINTENANCE MANUAL

Maintenance Checks

No.

Engine (Cont.)

Reference

Interval 100 h Add.

Initials

23.

Spark plug connectors - Check that resistance spark plug connectors fit tightly on the spark plugs. Minimum pull-off force is 30 N (7 lb). Replace spark plugs R* 12-20-00 Sec. 14.2 X 1)

200 h

24.

200 h 1 year 1 year

25.

Oil temperature / oil pressure sensor - Check for tight fit and condition. Exhaust system - Check attachment screws and springs for security and fit. Inspect system for damage and missing parts. Visual inspection of the muffler, exhaust pipes and mounting flanges for cracks, corrosion and leakage. Check heat shielding for condition. Cabin heat - Check heat shroud and heat ducts for damage and security of attachment. Check heat control function. Exhaust muffler - Remove heat shroud from muffler and inspect muffler for condition, corrosion and leakage. WARNING: FAILURE TO INSPECT MUFFLER FOR LEAKS COULD RESULT IN CARBON MONOXIDE ENTERING THE CABIN, LEADING TO SERIOUS INJURY OR DEATH! 78-10-00

X

26.

X

1 year

27.

X

1 year

28.

200 h

29.

Propeller gear box - Check the friction torque in free rotation on gearboxes with overload clutch. Actual friction torque is measured: _________Nm

R* 12-20-00 Sec. 15

X

1 year

30.

Propeller gear box - Series 3 (with overload clutch) and more than 30% of operation hours flown with leaded fuel inspect overload clutch Propeller gear box - Check the propeller gearbox (with overload clutch).

R* 05-50-00 Sec. 2 SB-912-033 R* 12-20-00 Sec. 15.2 SB-912-041 R* 12-20-00 Sec. 10.2 X

600 h

31.

1000 h 800 h 2) 1 year

32.

Carburetors - Check carburetor synchronization. Mechanical or pneumatic synchronization.

Inspect the float chamber assy for contamination and corrosion. Sec. 10.5 33. Carburetors - Check the ventilation of the float chambers. Any trouble with float chamber ventilation impairs engine and carburetor function and must therefore be avoided. Check that the passage of the ventilation lines is free and that no kinks can arise. Carburetors - Removal/assembly of the two carburetors for carburetor inspection. Rotax Heavy MM, 73-00-00 Sec. 3.1 200 h

34.

200 h

1) if more than 30% of operation hours have been flown with leaded fuel e.g.: AVGAS 100LL (SI-912-016) 2) depending on engine S/N

05-20-00

Page 06 05.11.12


Maintenance Checks

MAINTENANCE MANUAL

No.

Engine (Cont.)

Reference

Interval 100 h Add.

Initials

35.

Carburetors - Check the free movement of the carburetor actuation (throttle lever and starting carburetor). Check that the Bowden cable allows full travel of the throttle lever from stop to stop. Carburetor sockets and drip tray - Inspect the carburetor for damage and abnormalities, check for cracks, wear and good condition. Take note of any changes caused by temperature.

R* 12-20-00 Sec. 10.5

X

1 year

36.

Rotax Heavy MM, 73-00-00

200 h 1)

37.

Airbox assy - Check for damage, security of attachment and condition. Inspect connected air hoses for condition and leakage. Check that the flaps can be moved through their full arc of travel for hot and filtered ram air. Air filter - Inspect and clean. Renew if necessary. Clean air filter casing. Check the drain hole at the bottom of casing for obstructions or blockage. Other external engine accessories - Inspect screws and nuts of all other external engine parts and accessories for tight fit. Inspect safety wiring if applicable, replace as necessary. Engine mounts (manufactured by ROTAX and AQUILA) Check mounts for deformation, cracks, corrosion, security and damage from heat. Check mounting bolts for condition and correct torque value. At engine (4 bolts M10): 35 Nm At shock mounts (4 bolts M10): 25 Nm At firewall (4 bolts M10): 30 Nm Inspect shock mounts for deterioration. R* 12-20-00 Sec. 3.1 SB-912-028, latest Rev. SB-AT01-022, latest Rev. R* 12-20-00 sec. 2

X

1 year

38.

X

1 year

39.

X

1 year

40.

X

1 year

41.

Engine test run - Attach cowling and perform an engine test run as described above in Pre-Inspection/Engine Ground Test. After engine test run, re-tighten oil filter by hand and examine engine and engine compartment for signs of leakage. Compare results with first engine test run. Check oil level, replenish as necessary.

17-10-00 05-20-00

X

1 year

R* 12-10-00 Sec. 4.1

No.

Propeller

Reference

Interval 100 h Add.

Initials

1.

Spinner - Remove from aircraft and check for delamination and cracks. Spinner plate - Check for cracks and fit. Blade root and hub area - Examine for oil and grease leaks. Propeller blades - Check blade play (up to 3 mm [1/8 in.] allowed).

61-10-00

X

2. 3. 4.

X X X

1) See SB-912-030 - latest edition.

05-20-00

Page 07 05.11.12


MAINTENANCE MANUAL

Maintenance Checks

No.

Propeller (Cont.)

Reference

Interval 100 h Add.X X

Initials

5. 6.

Propeller blades - Check blade angle play. (max. 2) Hub - Inspect outside condition of the hub and parts for cracks, corrosion and deterioration. Check nuts for low pitch - Inspect for tightness and safety wire. Propeller assy - Check safetying. Propeller flange stop nuts - Check correct torque value (45 - 47 Nm). Propeller blades - Visual inspection for damage, repair if necessary. Attach spinner. MT* E-124 Para. 6.2.1 thru 6.10

7.

X

8. 9.

X X

10.

X

No.

Fuselage / Cabin

Reference

Interval 100 h Add.X

Initials

1.

Prepare aircraft for visual checks: Remove cabin carpets and floorboards; Remove glare shield; Remove baggage compartment floorboard; Remove access panel of the baggage compartment bulkhead; Remove access panel 210AB. Fuselage shell - Visual inspection for paint coat damage, dents, cracks, holes, distortion and other evidence of failure. All unpainted parts for delamination (white spots). Lower fin - Inspect fin and lower rudder for signs of breakage. Check skid plate for wear. Canopy - Examine the acrylic glass for cracking, crazing and general condition. Inspect tubular canopy hinge frame and brackets for cracks, distortion, corrosion, wear, and security of attachment. Check the gas spring strut for sufficient power and evidence of leakage. Canopy locking - Check the canopy locking mechanism operates correctly. Check wear of parts. Check existence of the locking pin. The pin has to protrude the cover by approx. 2 mm. All cases of lacking locking pins have to be reported to the type certificate holder (contact information: see cover sheet). Check function of the locking pin. The canopy locking mechanism must not be too smooth-running. In the locked position of the latch, a smooth running release of the latch due to in-flight vibrations must not be possible. If necessary, readjust locking pin.

06-30-00 X

2.

3.

X

4.

X

5.

52-10-00

X

05-20-00

Page 08 05.11.12


Maintenance Checks

MAINTENANCE MANUAL

No.

Fuselage / Cabin (Cont.)

Reference

Interval 100 h Add.

Initials

6.

Baggage door - Check door seal, door latching mechanism, and door hinge for defects and condition. Inspect door structure for cracks or other damage. Seat belts/harnesses for pilot / co-pilot - Check for proper operation, condition, and security of attachment. Seats - Check security of attachment of the seat assy to aircraft structure. Check operation of seat adjustment mechanism and seat stops. Inspect gas spring struts for oil leakage or other damage. Seats - Check ease of movement - if required remove seats, clean and lubricate seat rails. Center Console - Visually examine the parts of the engine controls, lines, and cables, located in the center console. Main landing gear - Inspect fuselage structure at such points and areas where the main landing gear is attached. Check for stress marks, distortion, disbonding, and delamination. Inspect main landing gear strut brackets for distortion, cracks, corrosion, and security of attachment. Check wear and condition of the polyamide inserts. Check bolts for correct torque. Wheel fairings - Check condition and correct fit. Parking brake valve - Check for evidence of leakage especially at the brake line connections. Check control assy for damage. Flap actuator - Check for wear and damage, for secure mechanical connections and loose or missing lock devices. Check electrical wiring for wear, damage, and proper routing. Inspect electrical connections and switches for security, corrosion and poor condition. Check function of the limit switches and position indicator. Elevator trim system - Check the actuator and the springs for security, wear and damage. Check safetying. Check electrical wiring for wear, insulation damage, and proper routing. Inspect electrical connections and switches for security, corrosion and poor condition. Perform system test and check the correct function of the position indicator. Aileron and elevator control - Check the control sticks, the brackets and the control rods for distortion, cracks, chafing, corrosion and security. Examine all bearings for condition and secure fit. Check safetying. Check travel of control surfaces if the control stick is in the full forward /neutral/ aft, and full left /neutral/ right positions. Verify no binding or jumpy movement of the control sticks through their full range of travel. 25-10-00

X

7.

X

8.

X

9.

Ann.

10.

Ann.

11.

X

12. 13.

X X

14.

X

15.

X

16.

X

05-20-00

Page 09 05.11.12


MAINTENANCE MANUAL

Maintenance Checks

No.

Fuselage / Cabin (Cont.)

Reference

Interval 100 h Add.

Initials

17.

Rudder control - Check rudder control weldment and rudder bellcrank for cracks, distortion, chafing and security. Examine rudder control support brackets, rudder pedal pivot brackets and connection of the rudder controls with the nose gear steering tubes for security, condition and correct splintering. Check centering of springs and cables. Inspect control cables, control cable guides, cable connections, turnbuckles and hardware for correct installation, corrosion, wear, safetying and proper operation. Rudder / aileron control interconnection - Check condition and correct function. Brake lines and brake master cylinder in the forward cabin area - Check for security and signs of leakage. Brake reservoir - Check for leakage and system for trapped air. Inspect the vent valve in the filler cap of the brake reservoir for obstruction and blockage. Make sure the hydraulic brake fluid level is correct and replenish, if necessary. Only use hydraulic brake fluid of the required grade. Hydraulic brake fluid - Renew. Fuel lines - Check for leakage and security. Wing main bolts - Inspect for proper fit, condition and correct safetying. Wing main bolts - Remove for visual inspection and lubrication. Engine and propeller controls - Check for proper function, security of attachment and for evidence of wear. Exterior / interior placards and markings - Check presence, legibility, and security. Consult A210 Pilots Operating Handbook and Airplane Flight Manual for required placards. 11-20-00 11-30-00 57-10-00

X

18.

X

19.

X

20.

X

21. 22. 23.

2 years X X

24.

57-10-00

500 h or 5 years X

25.

26.

X

No.

Wings, Ailerons, Flaps

Reference

Interval 100 h Add.

Initials

1.

Wings with winglets, ailerons, and flaps - Visual inspection for paint coat damage, dents, cracks, holes, distortion and other evidence of failure. Examine all unpainted parts for delamination (white spots). Wing spars in the fuselage belly - Remove spar covering and perform visual inspection of the spar web, the bonding between the spar web and the carbon fiber spar cap strip, as well as the attachment of the root ribs to the spars. Check security and function of control system brackets attached to the spars.

X

2.

Ann.

05-20-00

Page 10 05.11.12


Maintenance Checks

MAINTENANCE MANUAL

No.

Wings, Ailerons, Flaps (Cont.)

Reference

Interval 100 h Add.

Initials

3.

Drain and vent holes - Check for blockage and suspect appearance of any liquid. Ailerons - Check aileron hinges, bearings, and hinge brackets for security and excessive play. Check bolts and nuts for proper safetying. Examine aileron pushrod for correct installation with stop nuts. Check aileron actuation assembly for suspect binding, and excessive play. Aileron hinges - Check play allowed: - Axial 1,00 mm ( 0.04 in.) - Radial 0,30 mm ( 0.01 in.) Aileron control system - Measure the play in the aileron control system with the control surface locked. Apply a lateral force of 30 N (6.7 lb) to the control stick the maximum play allowed on the top of the stick is 10 mm (0.4 in.) for both sides. The play should be measured for both control sticks. If excessive play is detected, investigate cause. Flaps - Check hinge brackets for damaged paint, cracks and delamination. Check bearings for correct fit and excessive play. Check the correct safetying of all hinge bolts and castle nuts with cotter pins. Flaps - Check flap hinges for play allowed: - Axial 0,30 mm ( 0.01 in.) - Radial 0,30 mm ( 0.01 in.) Measure the play in the flap control system at the flap trailing edge, at the inboard flap end. Max. play allowed with flaps in take-off and landing positions: 5 mm (0.2 in.). No play with flaps retracted. Flaps and ailerons - Check that the gap between fuselage and flaps, between flaps and ailerons, and at the outboard end of the ailerons is at least 2 mm ( 0.08 in.). Stall warning system - Check for condition and proper operation. For serial numbers from AT01-100 to AT01-126: Bonding between wing spar and upper shell - Check condition Navigation / strobe lights - Check operation, condition of glass, and security of attachments. Inner fuel tank ribs - Check connection of fuel and vent lines to the fuel tank and the flange gasket of the fuel level sensors for signs of leakage. Fuel vent lines - Check for blockage. Fuel tank drain valves - Check for correct function and leakage. 57-10-00 SB-AT01-002 lates Rev. 33-40-00

X

4.

X

5.

X

6.

X

7.

X

8.

X

9.

X

10.

X

11.

Ann.

12.

X

13.

28-10-00 28-20-00 28-40-00 X X

Ann.

14. 15.

05-20-00

Page 11 05.11.12


MAINTENANCE MANUAL

Maintenance Checks

No.

Wings, Ailerons, Flaps (Cont.)

Reference

Interval 100 h Add.

Initials

16.

Fuel filler caps - Check for proper function and leakage.

X

17.

Tie-down points - Check thread and structure around the tiedown attach points for any damage.

10-20-00

X

No.

Empennage, Elevator, Rudder

Reference

Interval 100 h Add.

Initials

1.

Empennage - Inspect complete surface of the vertical and horizontal stabilizers, the elevator and the rudder for dents, cracks, holes and delamination. Rudder hinge, elevator hinge and bellcranks - Check brackets and bellcranks for security of attachment and corrosion. Examine bearings for binding and excessive play. Check correct safetying of the lower rudder pivot pin with castellated nut and cotter pin. Hinge play and control surface positioning - Verify clearance between horizontal stabilizer and elevator horns and clearance between vertical stabilizer and rudder horn is at least 1 mm (0.04 in.). Check elevator hinge and rudder hinge play max. allowed: - Axial 0,30 mm ( 0.01 in.) - Radial 0,30 mm ( 0.01 in.) Elevator control system - Measure the play in the elevator control system with the control surface locked. Apply a force of 50 N (11.2 lb) forwards and then backwards to the control stick - the maximum play allowed on the top of the stick is 10 mm (0.4 in.) for both sides. Rudder - Remove rudder if there is noticeable play. Examine the elevator actuation assembly inside the vertical stabilizer. Check for any damage, for correct installation and function and for security and wear. Inspect rudder hinge brackets, rudder yoke and control cable thimble-eyes for security, conditions and wear. Lubricate control cable thimble-eyes as required. Rudder rigging - Set rudder pedals in neutral position. Verify the rudder and the nose landing gear are also in neutral position. Set rudder pedals to fully left and then to full right. The rudder must hit the rudder travel stops and the distance from rudder pedal to firewall must be sufficient to apply the pedal brake. Adjust position of the rudder pedals by varying the length of nose wheel steering tubes. Adjust rudder neutral position and control cable tension by means of the turnbuckles in the cabin area. 55-40-00

X

2.

X

3.

Ann.

4.

Ann.

5.

Ann.

6.

27-20-00

X

05-20-00

Page 12 05.11.12


Maintenance Checks

MAINTENANCE MANUAL

No.

Nose and Main Landing Gear

Reference

Interval 100 h Add.

Initials

1. 2.

Landing gear fairings - Remove and clean. Wheel fairings - Clean. Check for paint coat damage, cracks, dents and delamination. Fairing mounts - Inspect for cracks, distortion or other damage. Wheels and rims - Clean. Check tires for wear, cuts, foreign matter and deterioration. Inspect rims for security, deformation, cracks and other damage. Examine wheel bearings for excessive play, corrosion and irregular operation. Check tire pressure and proper location of the red slide marks. Nose gear strut mount - Check for deformation, cracks, and corrosion. Check nose gear strut journal bearing for proper operation, play and correct safetying. Nose gear strut and elastomer package - Check strut for deformation, stress marks, and cracks. Inspect correct installation of the nose wheel fork. Inspect elastomer package for wear, deterioration, cracks, correct fit and security. Check journal bearings of the elastomer package for play and condition. Nose wheel steering - Inspect nose wheel steering tubes for condition, excessive play and correct safetying. Check return springs at nose gear strut for security and verify they are tension-free, when the nose wheel is in neutral position. Main landing gear - Check main gear struts for deformation, cracks, damage to the paint coat, and corrosion. Inspect wheel axles for security of attachment to struts and for any damage. Wheel bearings - Clean and lubricate. Wheel brakes - Clean. Check freedom of movement of the pistons and pressure plates. Inspect brake disks and brake linings for condition and wear. Replace brake disk if worn below 4,3 mm (0.17 in.). Replace brake linings when worn to 2,6 mm (0.10 in.). Inspect brake fluid carrying lines at the main landing gear for condition, leakage, and security of attachment. 12-22-00 32-40-00

X X

3. 4.

X X

5.

X

6.

X

7.

X

8.

X

9. 10.

Ann. X

05-20-00

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MAINTENANCE MANUAL

Maintenance Checks

No.

Electrical System / Avionics

Reference

Interval 100 h Add.X

Initials

1.

Electrical wiring system - Check the complete electrical wiring system for security, damage, wear and secure fit. Check all cable connections for tight fit, good contact, corrosion and condition. Instruments - Check instrument panel mounting brackets for security and condition. Examine instruments for security of attachment. Check electrical cables, hoses and lines for correct installation, condition and proper routing. Inspect air filter of the pitot / static system for obstructions and contamination. Pitot / static system - Check pitot tube for security of attachment, condition and obstructions. Check pitot and static pressure lines for correct installation, condition, water and proper routing.

R* 12-20-00 Sec. 14.1

2.

Ann.

3.

X

No.

Return to Service

Reference

Interval 100 h Add.

Initials

1.

Install wheel fairings. Install seats (if removed). Install cabin floor boards. Install baggage compartment floorboard. Install access panel of the baggage compartment bulkhead. Install access panel 210AB. Flight controls - Check for full range of travel and excessive friction. Flaps - Operate through full extension and retraction for steady and complete deployment. Check correct limit switches operation at CRUISE, T/O and LDG flap positions. Verify the corresponding flap switch position and the corresponding flap position indicator reading. Elevator trim - Check for full range of travel and excessive friction. Inspect proper operation of the trim control switch, limit switches, and the trim position indicator. Verify that elevator control forces decrease or increase when operating elevator trim. Engine and propeller controls - Check full range of motion without any obstruction or excessive friction to travel. Check throttle and propeller control levers friction lock. Foreign items - Remove any foreign items from the aircraft.

X

06-30-00 X

2.

3.

X

4.

X

5.

X

6.

X

05-20-00

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MAINTENANCE MANUAL

The aircraft is airworthy and meets the condition specified in the aircraft data sheet. All maintenance required by Service Information and Airworthiness Directives and all prescribed scheduled maintenance checks have been carried out. Service Station: Next inspection when _______ hours of operation have been reached. Place, Date

Name, Signature of Mechanic

Name, Signature of Inspector

Stamp

05-20-00

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Maintenance Checks

MAINTENANCE MANUAL

DAILY INSPECTIONS

1. General A. Pre-flight and post-flight checks must be carried out daily when the aircraft is in operation.

2. Pre-flight check A. This check must be carried out before the first flight of the day. In this way, the general condition of the aircraft and its engine can be ascertained. The scope of the pre-flight check is listed in the AQUILA AT01 Airplane Flight Manual, Section 4. Pre-flight checks are essential for flight safety as numerous accidents can be traced back to inadequate pre-flight checks.

3. Post-flight check A. This check should be carried out after the final flight of the day. For the most part, it is a visual inspection. The check should contain all points of the pre-flight check. (1) Supplementary measures: (a) Re-fuel (b) Check that the aircraft is properly parked (Refer to 10-10-00). (c) Check the logbook entries for remarks about faults or defects, and for correct number of landings and flight hours. (d) If necessary, moor the aircraft (Refer to 10-20-00).

B.

05-30-00

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Maintenance Checks

MAINTENANCE MANUAL

UNSCHEDULED MAINTENANCE CHECKS

1. General A. Special checks are to be carried out when an incident has occurred that may have caused damage to the aircraft or impaired airworthiness. In addition, a 25-hour inspection must be carried out on new aircraft and its engine, on overhauled engines and after extensive airframe repairs.

2. Special Checks A. 25-Hour Inspection After the first 25 hours of operation of a new aircraft and its engine or an overhauled engine or after extensive airframe repairs, an inspection of the extent of a 100-hour inspection must be carried out (Refer to 05-20-00). After the first 25 hours of operation of new or overhauled engine, the engine and the propeller must be inspected. Refer to ROTAX Aircraft Engines Maintenance Manual for ROTAX Engines Type 912 Series for detailed information on this inspection.

B.

Hard Landing After an excessively hard landing or other unusual loading of the landing gear a thorough inspection of the affected components and their attachments is required. Even if no obvious defects are detectable, a visual inspection must be carried out. Perform the following: (1) Prepare aircraft for visual checks as follows: (a) Remove engine cowling (refer to 71-10-00). (b) Remove landing gear fairings. (c) Inside the cabin and baggage compartment - remove carpets and floorboards as required to gain access to the landing gear mounting brackets (Refer to 25-21-009). (2) Inspect main landing gear. (a) Check wheel fairings for cracks, dents and delamination. (b) Check fairing mounts for cracks, distortion and other damage. (c) Check fuselage structure visually at such points and areas where the main landing gear is attached. Check for stress marks, distortion, disbonding, and delamination. Check main landing gear strut brackets for distortion, cracks and security of attachment. Check condition of the polyamide inserts. Check bolts for correct torque. (d) Check main gear struts for deformation and cracks. Examine wheel axles for security of attachment to struts and for any damage. (e) Inspect tires for integrity and proper location of the red slide marks. (f) Inspect brake fluid carrying lines at the main landing gear for condition, leakage, and security of attachment.

05-50-00

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Maintenance Checks

(3) Inspect nose landing gear. (a) Check wheel fairing for cracks, dents and delamination. (b) Inspect fairing mounts for cracks, distortion and other damage. (c) Check nose gear strut mount for deformation and cracks. Check nose gear strut journal bearing for proper operation and play. (d) Check strut for deformation, stress marks, and cracks. Check elastomer package for deterioration, cracks, correct fit and security. Check journal bearings of the elastomer package for play and condition. (e) Inspect nose wheel steering tubes for condition and excessive play. (f) Inspect tire for integrity and proper location of the red slide marks. (4) Re-mount all items removed during the inspection. (5) Perform a brake and steering system operational test (refer to 32-40-00). C. Engine Fire After an engine, carry out the following: WARNING: IF IT IS SUSPECTED THAT PARTS OF THE STRUCTURE OR COWLING COULD HAVE BEEN DAMAGED BY HIGH TEMPERATURES (INDICATED BY BLISTERING ON THE PROTECTIVE COATING), THE MANUFACTURER MUST BE CONTACTED FOR DEFECT APPRAISAL BEFORE THE AIRCRAFT IS FLOWN AGAIN.

(1) (2) (3) (4) (5) (6) (7) (8) (9) (10) (11) (12) D.

Disconnect battery (refer to 24-30-00). Remove engine cowling (refer to 72-10-00). Examine engine cowling. Check for signs of fire damage. Examine electrical cables for damaged insulation. Examine fuel lines for damage of the fire-protection sleeves. Check oil lines for damage of the fire-protection sleeves. Check air filter element for fire damage. Examine engine mount and shock mounts for any fire damage. Check all other hoses and pipes, as well as all gaskets and seals for fire damage. Replace damaged items. Re-mount engine cowling (refer to 72-10-00). Perform an engine test run (refer to 05-20-00).

Violent Stop of the Engine In event that the propeller has touched the ground or the engine has been inadvertently stopped violently (shock loading), the propeller gear box must be disassembled and inspected by an authorized workshop. For further information on engine inspections necessary after a propeller ground strike and for more general information, refer to the relevant technical documents and the ROTAX Maintenance Manual. CAUTION: ONLY QUALIFIED TECHNICIANS (AUTHORIZED BY THE NATIONAL AVIATION AUTHORITY AND AFTER SUCCESSFULLY COMPLETING THE RELEVANT ROTAX TRAINING COURSE) ARE AUTHORIZED TO PERFORM THIS WORK.

Check additional equipment (external alternator, hydraulic governor, ignition unit, coolant and oil hoses) for damage.

05-50-00

Page 02 05.11.12


MAINTENANCE MANUAL

CHAPTER 06 DIMENSIONS AND AREAS


MAINTENANCE MANUAL


Dimensions and Areas

MAINTENANCE MANUAL

TABLE OF CONTENTS

Title


Page 1 1 1 1 1 1 2 1 1 1 1 1

DIMENSIONS AND AREAS - GENERAL .....................................................06-00-00 Introduction 06-00-00 General Description 06-00-00 AIRCRAFT DIMENSIONS AND AREAS.......................................................06-10-00 General 06-10-00 Dimensions and Areas 06-10-00 Weight and Static Moments of Control Surfaces 06-10-00 AIRCRAFT ZONING ........................................................................................06-20-00 General 06-20-00 Description 06-20-00 ACCESS/INSPECTION PLATES .....................................................................06-30-00 General 06-30-00

Page 01

06 - TOC

26.04.05


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MAINTENANCE MANUAL

DIMENSIONS AND AREAS - GENERAL

1. Introduction A. This chapter provides information about dimensions and control surface travel and tolerances of the AQUILA AT01. Furthermore, this chapter contains information about aircraft zoning, access and inspection plates. Dimensions are presented to aid the operator and/or maintenance personnel in ground handling the aircraft, e.g. in hangars with small park areas. The knowledge about aircraft zoning and position of access / inspection plates facilitates the locating and access to aircraft components.

B.

2. General Description The following sets out a brief description and intended purpose of each section of this chapter: A. Section 6-00-00 - Dimensions and Areas - General. This section provides a general overview of content and purpose of the chapter. Section 6-10-00 - Aircraft Dimensions and Areas. This section provides aircraft dimensions and identifies areas of the aircraft. Section 6-20-00 - Aircraft Zoning. This section shows illustrations of all aircraft zones. Section 6-30-00 - Access and Inspection Plates. This section contains the position and numbering of all accesses and of all inspection plates.

B.

C. D.

06-00-00

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MAINTENANCE MANUAL



MAINTENANCE MANUAL

AIRCRAFT DIMENSIONS AND AREAS

1. General A. B. The wing and tail spans are measured parallel to the respective reverence level. Refer to Figure 1 for an illustration of aircraft dimensions.

2. Dimensions and Areas Aircraft Overall: Wing Span Overall Length Heigth max. 10,3 m 7,3 m 2,3 m 33.8 ft 23.9 ft 7.55 ft

Wing: Wing Profile Wing Area Dihedral Angle Mounting Angle MAC Max. Load HQ 42 mod. 10,5 m +4,5 0 +2,5 0 1,07 m 71,4 kg/m 3.52 ft

113.6 ft

Ailerons (both): Area Up Travel Down Travel Neutral Position 0,65 m 16 + 1,5 11 + 1,0 0 up 7.0 ft

Flaps (both): Area Flap Setting (Ground) Up Takeoff Landing 0 17 35 1,23 m Tolerance Left 0 1,5 1,5 13.31 ft

Right 0 1,5 1,5

06-10-00

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MAINTENANCE MANUAL

Horizontal Stabilizer and Elevator: Profile Area (entire) MAC Elevator Area Up Travel Down Travel Span Fx 71/L150-30 2,0 m 0,68 m 0,58 m 23 1,5 24 1,5 3,0 m 9.87 ft

21.64 ft 2.24 ft 6.28 ft

Vertical Stabilizer and Rudder: Profile Area Rudder Area Travel Fx 71/L150-30 1,45 m 0,44 m 29 1,5

15.67 ft 4.76 ft

Landing Gear: Wheel Track Wheel Base Nose Gear Wheel Size Main Gear Wheel Size 2,0 m 1,68 m 5.00-5 5.00-5 6.58 ft 5.51 ft

3. Weight and Static Moments of Control Surfaces Control Surface Weight kg Aileron Fowler Flap1) Elevator2) Rudder 1,35 - 2,0 2,7 - 3,4 4,3 - 5,4 3,5 - 4,5 Control Surface Static Moment Ncm 20 - 90 500 - 660 -30 - +40 20 - 80

1) Weight values are shown for one flap. The Moment is shown for both flaps in 35 position the flap actuator disconnected. 2) Weight values shown for elevator assembly including both elevator halves.

06-10-00

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MAINTENANCE MANUAL

2,3 (7.55)

1,68 (5.51) 7,3 (23,9)

10,3 (33,8)

2,0 (6,58)

MAC 1,07 (3.52)

MAC 0,68 (2.24)

3,0 (9.87)

Aircraft Dimensions [ m (ft.)] Figure 1

06-10-00

Page 03 26.04.05


MAINTENANCE MANUAL



MAINTENANCE MANUAL

AIRCRAFT ZONING

1. General A. The AQUILA AT01 is divided into numbered zones to provide a method for locating components or parts throughout the aircraft. This Aircraft zoning corresponds to the usual standard. The zones are identified by a (3) three-digit number. The first digit in the sequence denotes the major zone: Major Zones: (1) (2) (3) (4) (5) (6) 100 - Forward side of firewall and forward. 200 - Aft side of firewall to rear door post of the baggage door. 300 - Rear door post of the baggage door to end of aircraft. 500 - Left wing. 600 - Right Wing. 700 - Landing Gear.

B.

The second digit in the sequence further divides the zones into sub-zones (Zone 110 - Propeller and Spinner, Zone 120 - upper and lower cowling). The third digit (if needed) divides the subzone into further subdivisions. Example: 124 Major Zone Sub-Zone Further Sub-Zone

2. Description A. For a breakdown of the aircraft zones, refer to Figure 1.

06-20-00

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MAINTENANCE MANUAL

120

340

110

310

211(Interior)

722 720 110 120 520 510

721

610

620

210 222 310 221 223

Instrument Panel

122 330 320 124

121 123

Firewall Aircraft Zones Figure 1

06-20-00

Page 02 26.04.05



MAINTENANCE MANUAL

ACCESS & INSPECTION PLATES

1. General A. Accesses / inspection plates on the AQUILA AT01 are used to gain access to various systems, components and parts of structure during maintenance and for inspection. The access and inspection plates are designated logically. (1) System of numbering of the access / inspection plates All access / inspection plates are identified using a series of numbers and letters which specify zone (see section 6-20-00) and location within this zone. Primary identifiers follow the threenumber sequence, with the first plate identified as A, the second as B and so on. Locators follow the primary identifier and denote top, left, right or internal orientation of the plate.

B.

Example: 340AL Vertical Stabilizer left-hand side

First access / inspection plate In this region

2. Description A. For an illustration that shows the various accesses / inspection plates used on the AQUILA AT01, refer to Figure 1. 210AB Wing Removal /Installation, Aileron / Flap Control Systems, Fuel System, Wing Structure. Left Flap Actuation Lever Right Flap Actuation Lever Left Inboard Fuel Tank Rib, Fuel / Vent Lines, Fuel Lever Sender Right Inboard Fuel Tank Rib, Fuel / Vent Lines, Fuel Lever Sender Left Aileron Bellcrank Right Aileron Bellcrank

510AB 610AB 510BB 610BB 520AB 620AB

06-30-00

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MAINTENANCE MANUAL

610AB

510AB

620AB 610BB

210AB 510BB

520AB

Access / Inspection Plates Figure 1

06-30-00

Page 02 26.04.05


MAINTENANCE MANUAL

CHAPTER 07 LIFTING AND SHORING


MAINTENANCE MANUAL


Lifting and Shoring

MAINTENANCE MANUAL

TABLE OF CONTENTS

Title


Page 1 1 1 201 201 201 201 202

LIFTING AND SHORING - GENERAL.........................................................07-00-00 Introduction 07-00-00 General Description 07-00-00 JACKING.............................................................................................................07-10-00 General 07-10-00 Tools, Equipment and Material 07-10-00 Jacking Procedure 07-10-00 Lifting 07-10-00

Page 01

07 - TOC

02.03.10


MAINTENANCE MANUAL


Lifting and Shoring

MAINTENANCE MANUAL

LIFTING AND SHORING - GENERAL

1. Introduction A. This chapter describes procedures used to lift and shore the aircraft. The necessary equipment for lifting and shoring is provided and described how use it during the procedures.

2. General Description In the following, a brief description and intended purpose of each section of this chapter is given. A. Section 7-00-00 - Lifting and Shoring - General. This section provides a general overview of content and purpose of the chapter. Section 7-10-00 - Jacking. This section contains procedures, supplementary information and required equipment for jacking the aircraft.

B.

07-00-00

Page 01 02.03.10


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Lifting and Shoring

MAINTENANCE MANUAL

JACKING

1. General A. The AQUILA AT01 is raised at two points and supported at the tail. The jack points are located at the bottom of the fuselage root ribs. (see Fig. 201). Special adapters must be installed prior to lifting. If needed the AQUILA AT01 may be lifted at a hoist.

B.

2. Tools, Equipment and Material Required in 3.A 3.A 3.A 3.A Quantity 2 2 1 2 Equipment Jack Adapter Tail Stand Wing Trestles Parts No. Manufacturer Commercially available AQUILA A. b. E. AG Commercially available Commercially available

3. Jacking Procedure A. Jacking the Aircraft CAUTION: DO NOT RAISE THE AIRCRAFT OUTSIDE IF THE WIND VELOCITY IS MOORE THEN 6 KNOTS.

(1) Position aircraft on a hard, flat, level surface. In the open air set the aircraft with the nose into the wind. CAUTION: USE ONLY JACKS IN COMBINATION WITH ADAPTERS DELIVERED BY AQUILA A. B. E. AG.

(2) Install adapters to jack points (marked red). (3) Place jacks at the correct positions under the fuselage (see Fig. 201) and extend to engage with the jacking points. (4) Remove wheel chocks. (5) Place the tail stand with adapter under the lower fin and extend to engage with the lower fin skid plate. Secure tail stand lock. (6) Raise jacks simultaneously, keeping the aircraft as level as possible. (7) Secure jack locks. (8) Place the wing trestles in position under each wing (Zone 530 /630).

B.

Lowering The Aircraft (1) Remove the wing trestles from under the wings. (2) Check, the area immediately under and over the aircraft is clear. (3) Slowly lower the jacks simultaneously, keeping the aircraft as level as possible.

07-10-00

Page 201 02.03.10


Lifting and Shoring

MAINTENANCE MANUAL

(4) When the main tires are resting on the ground, lower the jacks completely and remove them. (5) Remove tail stand. (6) Remove adapters from jack points.

4. Lifting A. Lifting Procedure (1) The airplane may be lifted with a one-ton (2205 lbs) hoist for maintenance purposes. The front sling is hooked to the two upper engine mount bars. The aft sling is positioned around

B A

A B

- Jack Points (right / left hand) - Tail Stand Positioning Zone

Aircraft Jack Points Figure 201

07-10-00

Page 202 02.03.10


MAINTENANCE MANUAL

CHAPTER 08 LEVELING AND WEIGHING


MAINTENANCE MANUAL


Leveling and Weighing

MAINTENANCE MANUAL

TABLE OF CONTENTS

Title


Page 1 1 1 201 201 201 201 201 201 201 201

LEVELING AND WEIGHING - GENERAL..................................................08-00-00 Introduction 08-00-00 General Description 08-00-00 Weighing .............................................................................................................08-10-00 General 08-10-00 Tools, Equipment and Material 08-10-00 Weighing Procedure 08-10-00 Leveling...............................................................................................................08-20-00 General 08-20-00 Tools, Equipment and Material 08-20-00 Leveling Procedure 08-20-00

08 - TOC

Page 01 27.09.01


MAINTENANCE MANUAL


Leveling and Weighing

MAINTENANCE MANUAL

LEVELING AND WEIGHING - GENERAL

1. Introduction A. This chapter provides all the necessary information to properly level the aircraft and to prepare it for weighing.

2. General Description In the following, a brief description and intended purpose of each section of this chapter is given. A. Section 8-00-00 - Leveling and Weighing - General. This section provides a general overview of content and purpose of the chapter. Section 8-10-00 - Weighing.

Documents

AMM-Vol1_05_11_12_Rev21