G150 MTM

FlightSafety International, Inc.Marine Air Terminal, LaGuardia Airport

Flushing, NewYork 11371(718) 565-4100

www.flightsafety.com

GULFSTREAM G150MAINTENANCE TRAINING

MANUAL

VOLUME 1

FlightSafetyinternational

Courses for the G150 and other Gulfstream aircraft are taught at the following FlightSafety learningcenter:

FlightSafety InternationalDFW Learning Center3201 East Airfield DriveDFW Airport, TX 75261-9428(972) 534-3200

Copyright 2006 by FlightSafety International, Inc.All rights reserved.

Printed in the United States of America.

INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES

LIST OF EFFECTIVE PAGES

Dates of issue for original and changed pages are:Revision ..... 0 ........... May 2006Revision ..... 1............ July 2008

NOTE:For printing purposes, revision numbers in footers occur at the bottom of every pagethat has changed in any way (grammatical or typographical revisions, reflow of pages,and other changes that do not necessarily affect the meaning of the manual).

THIS PUBLICATION CONSISTS OF THE FOLLOWING:

*Zero in this column indicates an original page.

Page *RevisionNo. No.Cover ...................................................... 0Copyright ................................................ 0iiix .......................................................... 11-11-2 .................................................... 12-i2-iv .................................................... 02-1............................................................ 12-22-4 .................................................... 02-5............................................................ 12-6............................................................ 04-i4-ii ...................................................... 14-iii4-iv.................................................... 04-1............................................................ 14-24-3 .................................................... 05-05-1 .................................................... 16-06-2 .................................................... 06-3............................................................ 16-4............................................................ 06-5............................................................ 16-66-7 .................................................... 06-8............................................................ 16-96-11 .................................................. 07-0............................................................ 07-1............................................................ 18-08-1 .................................................... 09-09-2 .................................................... 09-3............................................................ 19-4............................................................ 0

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Page *RevisionNo. No.

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21-64........................................................ 021-6521-67 ............................................ 121-68........................................................ 022-i .......................................................... 122-ii .......................................................... 022-iii ........................................................ 122-iv ........................................................ 022-1.......................................................... 122-222-5 ................................................ 022-622-7 ................................................ 122-8.......................................................... 022-922-26 .............................................. 123-i .......................................................... 123-ii .......................................................... 023-iii ........................................................ 123-iv ........................................................ 023-123-24 .............................................. 124-i .......................................................... 024-ii24-iv ................................................ 124-1.......................................................... 124-2.......................................................... 024-324-4 ................................................ 124-5.......................................................... 024-624-7 ................................................ 124-8.......................................................... 024-924-13 .............................................. 124-14........................................................ 024-15........................................................ 124-16........................................................ 024-17........................................................ 124-18........................................................ 024-19........................................................ 124-20........................................................ 024-21........................................................ 124-22........................................................ 024-2324-42 ............................................ 125-i .......................................................... 1



25-ii .......................................................... 025-iii ........................................................ 125-iv ........................................................ 025-125-18 .............................................. 126-i .......................................................... 026-ii26iii .................................................. 126-iv ........................................................ 026-126-2 ................................................ 126-326-4 ................................................ 026-526-8 ................................................ 126-9.......................................................... 026-1026-11 ............................................ 126-1226-13 ............................................ 026-14........................................................ 126-1526-17 ............................................ 026-1826-19 ............................................ 126-20........................................................ 026-21........................................................ 126-22........................................................ 026-2326-25 ............................................ 126-26........................................................ 026-2726-42 ............................................ 127-i27-iv ................................................ 127-1.......................................................... 127-2.......................................................... 027-3.......................................................... 127-4.......................................................... 027-5.......................................................... 127-6.......................................................... 027-7.......................................................... 127-8.......................................................... 027-927-15 .............................................. 127-16........................................................ 027-1727-19 ............................................ 127-20........................................................ 027-21........................................................ 1

27-22........................................................ 027-23........................................................ 127-24........................................................ 027-25........................................................ 127-26........................................................ 027-27........................................................ 127-28........................................................ 027-29........................................................ 127-3027-32 ............................................ 027-33........................................................ 127-34........................................................ 027-35........................................................ 127-36........................................................ 027-37........................................................ 127-38........................................................ 027-39........................................................ 127-40........................................................ 027-4127-45 ............................................ 127-46........................................................ 027-4727-49 ............................................ 127-50........................................................ 027-5127-55 ............................................ 127-56........................................................ 027-5727-63 ............................................ 127-64........................................................ 027-6527-69 ............................................ 127-70........................................................ 027-71........................................................ 127-7227-73 ............................................ 027-7427-82 ............................................ 128-i28-ii .................................................. 028-iii ........................................................ 128-iv ........................................................ 028-1.......................................................... 128-2.......................................................... 028-3.......................................................... 1



28-4.......................................................... 028-528-7 ................................................ 128-828-9 ................................................ 028-1028-11 ............................................ 128-12........................................................ 028-13........................................................ 128-14........................................................ 028-15........................................................ 128-16........................................................ 028-1728-44 ............................................ 129-i .......................................................... 129-ii .......................................................... 029-iii ..........................................................129-iv ..........................................................029-1.......................................................... 129-2.......................................................... 029-329-7 ................................................ 129-829-12 .............................................. 029-13........................................................ 129-1429-17 ............................................ 0

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NOTICEThe material contained in this training manual is based on information obtained from theaircraft manufacturers Airplane Flight Manual, Pilot Manual and Maintenance Manuals. Itis to be used for familiarization and training purposes only.

At the time of printing, it contained then-current information. In the event of conflictbetween data provided herein and that in publications issued by the manufactureror the FAA, that of the manufacturer or the FAA shall take precedence.

We at FlightSafety want you to have the best training possible. We welcome anysuggestions you might have for improving this manual or any other aspect of ourtraining program.

FOR TRAINING PURPOSES ONLY


CONTENTSVOLUME 1

CHAPTERTITLE ATANUMBER

INTRODUCTIONATA 100AIRCRAFT GENERAL 4-12AIR CONDITIONING 21FLIGHT GUIDANCE SYSTEM 22COMMUNICATIONS 23ELECTRICAL POWER 24EQUIPMENTAND FURNISHINGS 25FIRE PROTECTION 26FLIGHT CONTROLS 27FUEL 28HYDRAULIC POWER 29ICEAND RAIN PROTECTION 30

Revision 1 1-1FOR TRAINING PURPOSES ONLY

GULFSTREAM G150 MAINTENANCE TRAINING MANUAL

This training manual provides a description of the major airframe and engine systemsinstalled in the Gulfstream G150. This information is intended as an instructional aidonly; it does not supercede, nor is it meant to substitute for, any of the manufacturersor operating manuals. This material has been prepared from the basic design data, andall subsequent changes in the aircraft appearance or system operation will be coveredduring academic training and subsequent revisions to this manual.

The second chapter of this manual, ATA 100,i s an in t roduc t ion to the Ai r Transpor tAssociation format for aircraft maintenancemanuals. It is intended to describe simply thebasic format for all ATA 100 MaintenanceManual chapters and also to explain wherevariations may exist from one manufacturer toanother.

Each chapter following ATA 100 of thisbook has listed on the divider tab the ATAchapter(s) included, such as 24 Electrical

Power. In some cases it is appropriate, fortraining purposes, to include more than oneATA chapter in one chapter of this book, suchas Chapters 4 through 12 in Aircraft General.The tab marked 412 Aircraft General in-dicates that applicable ATA 100 MaintenanceManual Chapters 4 through 12 are covered inthat chapter. Any chapter not included in themanufacturers Maintenance Manual for thisparticular aircraft is not included in the chap-ter of this training manual.

INTRODUCTION

Th i s manua l i s i n two pa r t s : t h e ba s i cMaintenance Training Manual and the sup-plemental Maintenance Schematic Manual(MSM). The MSM contains schematics to beused only as a tool in understanding a system.The cor respond ing schemat i c ( s ) in theMaintenance Manual must be used when per-forming maintenance.

The goal of this course is to provide the verybest training program for the clients in ourmaintenance program. So that there is no un-certainty about what is expected of the client,the following basic objectives are presentedfor this course.

Given the Maintenance Manual, class notes,and this training manual (as specified by theFlightSafety instructor), the client will be ableto pass a written examination upon completionof this course to the grading level prescribedby the FlightSafety Director of MaintenanceTraining. The maintenance technician will beable to:

Outline the ATA 100 system used formaintenance documentation, includ-ing the major chapter headings andsymbology.

Describe the meaning and application ofeach piece of manufacturers mainte-nance documentation and use the doc-umentation in practical applications.

Outline the recommended maintenanceschedule.

Locate major components without ref-erence to documentation and other com-ponents with the aid of documentation.

Describe the operation of all major sys-tems in the normal and various abnormaloperating modes.

Perform maintenance preflight and post-flight inspections.

Perform selected normal and emergencycockpit procedures as required for en-gine start/runup, APU start, batterycheck.

The FlightSafety instructor will modify thestated overall conditions and criteria to satisfyselected performance requirements, when ap-propriate. The performance levels specifiedwill not vary from those listed.

NOTES

Revision 11-2 FOR TRAINING PURPOSES ONLY


Revision 0 2-i

ATA 100CONTENTS

Page

INTRODUCTION ................................................................................................................... 2-1

GENERAL............................................................................................................................... 2-1

DOCUMENTATION ............................................................................................................... 2-3

General ............................................................................................................................. 2-3

Revisions .......................................................................................................................... 2-3

Serialization ..................................................................................................................... 2-3

HOW TO USE THE MAINTENANCE MANUAL ................................................................... 2-3

Division of Subject Matter ............................................................................................... 2-3Standard Numbering System ........................................................................................... 2-5

List of Effective Pages ..................................................................................................... 2-5

Revisions .......................................................................................................................... 2-5



Revision 0 2-iii

ILLUSTRATIONFigure Title Page

2-1 ATA 100 Numbering ................................................................................................ 2-4

TABLESTables Title Page

2-1 Information Effectivity ............................................................................................. 2-2

2-2 Gulfstream G150 Maintenance Manual Division Chapters ..................................... 2-2





INTRODUCTIONThe purpose of this chapter is to describe the arrangement, numbering system, and spe-cial features of the Air Transport Association format for aircraft maintenance manuals.To take advantage of all the material presented in an ATA 100 manual, the maintenancetechnician must become thoroughly familiar with the outline and contents presented forany given aircraft.

GENERALATA Specification No. 100 is issued by theAir Transport Association of America as theSpecification for Manufacturers TechnicalData. It establishes a standard for the presen-tation of certain data produced by aircraft, en-gine, and component manufacturers, requiredfor support of their respective products. Underthis format, the Maintenance Manual is bro-ken down into standard chapters as defined by

ATA 100. Each chapter covers a specific areaof maintenance information, such as Chapter10, Parking and Mooring, or a specific sys-tem, such as Chapter 32, Landing Gear. Alldata pertaining to a given system is locatedwithin its chapter, regardless of whether the in-formation is mechanical, hydraulic, or elec-trical in nature. The chapters are arranged inalphabetical order.

ATA 100



All aircraftALL:

Table 2-1. INFORMATION EFFECTIVITY

AIRCRAFT GENERALTime Limits/Maintenance ChecksDimensions and AreasLifting and ShoringLeveling and WeighingTowing and TaxiingParking and MooringPlacardsServicing

56789

101112

AIRFRAME SYSTEMSAir conditioningAutoflightCommunicationsElectrical PowerEquipment/FurnishingsFire ProtectionFlight ControlsFuelHydraulic PowerIce and Rain ProtectionIndicating/Recording SystemsLanding GearLightsNavigationOxygenPneumaticsWater/WasteAuxiliary Power

212223242526272829303132333435363849

STRUCTURESStructuresDoorsFuselageNacelles/PylonsStabilizersWindowsWings

51525354555657

Chapter Title Chapter Title

POWERPLANTPowerplantEngine Fuel and ControlIgnitionEngine ControlsEngine IndicatingExhaustOilStarting

7173747677787980

Table 2-2. GULFSTREAM G150 MAINTENANCE MANUAL DIVISION CHAPTERS

DOCUMENTATIONGENERALThe Gulfstream G150 Maintenance Manual isprepared in accordance with the Air TransportAssociation from the manufacturers techni-cal data. The Maintenance Manual providessufficient information to enable a mechanic un-familiar with the aircraft to service, trou-bleshoot, test, adjust and repair systems, andto remove and install any unit normally re-quiring such action on the line of the mainte-nance hangar.

The Maintenance Manual is available on CD-ROM, microfiche and paper.

REVISIONSNormal RevisionsEach chapter of the Maintenance Manual in-cludes an effectivity page, record of temporaryrevisions, and table of contents. Each pagewill bear a page effectivity date in the lowerright corner that will correspond to the chap-ter effectivity page listing.

Temporary RevisionsAdditional information which becomes avail-able will be provided through temporary re-visions. This service is used to provide, withoutdelay, new information which will assist inmaintaining safe and efficient flight/groundoperations. The temporary revisions are nor-mally incorporated into the MaintenanceManual at the next regularly scheduled revi-sion so that they become a permanent part ofthe manual.

SERIALIZATIONThe Maintenance Manual information effec-tivity is placed in the lower margin of each pageas indicated in Table 2-1.

HOW TO USE THEMAINTENANCEMANUALDIVISION OF SUBJECTMATTERThe Gulfstream G150 Maintenance Manual isdivided into four major sections:AircraftGeneral, Airframe Systems, Structures,and Powerplant. Each major section is, inturn, separated into chapters with each chap-ter having its own effectivity page and tableof contents. Only the applicable chapters areincluded in any particular aircraft MaintenanceManual.

The Gulfstream G150 Maintenance Manualchapter division is described in Table 2-2.

NOTES





FIRSTELEMENT

SECONDELEMENT

CHAPTER/SECTION NUMBERING

SECTION (SUBSYSTEM)DISTRIBUTION

EXAMPLES:

SYSTEMAIR CONDITIONING

SUBSYSTEMTEMPERATURE

CONTROL

SUBSYSTEMCOOLING

TEMPERATURECONTROL

UNITMANUAL

SHUTOFF SWITCH

THIRDELEMENT

SUBJECT (UNIT)BLOWER

FIRST PAGE OFMAINTENANCE PRACTICES

PAGE 201MAY 1/77 DATE OF PAGE ISSUE

NOTE: THIS FIGURE IS FOR ILLUSTRATIVE PURPOSES ONLY.

COVERAGE

CHAPTER (SYSTEM)AIR CONDITIONING

21-20-01

21-00-00

21-60-00

21-62-00

21-62-03

WHEN CHAPTER (SYSTEM) ELEMENT NUMBER IS FOLLOWED BY ZEROS IN SECTION AND SUBJECT ELEMENTS, INFORMATION IS APPLICABLE TO THE ENTIRE SYSTEM.WHEN SECTION (SUBSYSTEM) ELEMENT NUMBER IS FOLLOWED BY ZEROS IN SUBJECT ELEMENT, INFORMATION IS APPLICABLE TO SUBSYSTEM AS A WHOLE.

THIS DIGIT REPRESENTS A SUBSUBSYS-TEM. INFORMATION IS APPLICABLE TO SUBSUBSYSTEM AS A WHOLE.

INFORMATION IS APPLICABLE TO SPECIFIC UNIT (COMPONENT) OF SUBSYSTEM.

Figure 2-1. ATA 100 Numbering

STANDARD NUMBERINGSYSTEMThe numbering system identifies and segre-gates subject matter by chapter (system), sec-tion (subsystem), and subject (unit). Thesystem is a conventional dash-number break-down of three two-digit elements (Figure 2-1 ) . W h e n r e f e r r e d t o a s a u n i t , t h ethree-element number (chapter/section/sub-ject) is called the chapter/section number.The chapter/section number is located in thelower right corner of each page with the pagenumber and date.

A page numbering system allows further break-down of information for rapid retrieval. Allmaintenance information is separated into spe-cific types of information (topics), and blocksof page numbers are assigned to each. The fol-lowing page number blocks are used in theGulfstream G150 manual:

PAGES TOPICS

1 through 99 .............Description/Operation

101 through 199 ................Troubleshooting

201 through 299....... Ma in tenancePractices

Simple units may not require description andoperation, or troubleshooting information; insuch cases, unused page number blocks areomitted. In addition, for those items requiringmany types of maintenance practices, pageblock 201 through 299 is omitted and mainte-nance practices and their page numbering arebroken down as follows:

PAGES TOPICS

301 through 399 ...........................Servicing

401 through 499 .........Removal/Installation

501 through 599 ................Adjustment/Test 601 through 799...............Inspection/Check

PAGES TOPICS

701 through 799..............Cleaning/Painting

801 through 899.............. ApprovedRepairs

Each new topic of information starts with page1, 101, 201, 301, etc., and continues within thepage numbering block as necessary; unusedpage number blocks are omitted.

Illustrations use the same numbering sequenceas the block in which they appear. For exam-ple, Figure 202 is the second figure in theMaintenance Practices section.

LIST OF EFFECTIVE PAGESA list of effective pages is provided with eachMaintenance Manual chapter. All pages in thechapter are listed in sequence on the list of ef-fective pages with the most recent revision datefor each page. A revised list of effective pagesis provided for each Maintenance Manual re-vision. Pages revised or added in the current re-vision are indicated by an asterisk.

REVISIONSAdditions, deletions, or revisions to the textin an existing section are identified by a re-vision bar in the margin of the page, adjacentto the change.

When an existing illustration is revised, apointing hand appears in the illustration,pointing to the modified area. New art addedto an existing section is identified by a sin-gle pointing hand next to the figure title andfigure number.



CHAPTER 412AIRCRAFT GENERAL

CONTENTSPage

INTRODUCTION.................................................................................................................... 4-1

GENERAL............................................................................................................................... 4-1

TIME LIMITS/MAINTENANCE CHECKS .......................................................................... 4-4

Airworthiness Limitations Section................................................................................... 4-4

Component Maintenance Requirements .......................................................................... 5-1

Unscheduled Maintenance Checks .................................................................................. 5-1

DIMENSIONS AND AREAS ................................................................................................. 6-1

Stations ............................................................................................................................. 6-3

Dimensions....................................................................................................................... 6-9

Areas .............................................................................................................................. 6-10

Zones .............................................................................................................................. 6-11

LIFTING AND SHORING...................................................................................................... 7-1

Aircraft Jacking ................................................................................................................ 7-1

Emergency Lifting............................................................................................................ 7-1

Shoring ............................................................................................................................. 7-1

LEVELING ANDWEIGHING............................................................................................... 8-1

Aircraft Weight and Balancing......................................................................................... 8-1

Aircraft Leveling .............................................................................................................. 8-1

TOWING AND TAXIING....................................................................................................... 9-1

Main Landing Gear Towing ............................................................................................. 9-1

Nose Landing Gear Towing ............................................................................................. 9-3


Revision 1 4-iFOR TRAINING PURPOSES ONLY

Taxiing.............................................................................................................................. 9-5

PARKING AND MOORING ................................................................................................ 10-1

Parking and Storage ....................................................................................................... 10-1

Mooring.......................................................................................................................... 10-1

PLACARDS AND MARKINGS........................................................................................... 11-1

SERVICING .......................................................................................................................... 12-1

Replenishing................................................................................................................... 12-1

Scheduled Servicing (Lubrication) ................................................................................ 12-1Unscheduled Servicing .................................................................................................. 12-2

Electrical System............................................................................................................ 12-5

Toilet .............................................................................................................................. 12-9

Fuel System.................................................................................................................. 12-11

Hydraulic System......................................................................................................... 12-17

Landing Gear ............................................................................................................... 12-25

Ice and Rain Protection Systems ................................................................................. 12-29

Lights and Navigation Emergency Batteries and Power Supplies .............................. 12-29

Oxygen System............................................................................................................ 12-31

Engine Oil .................................................................................................................... 12-33

APU Oil ....................................................................................................................... 12-37


Revision 14-ii FOR TRAINING PURPOSES ONLY

ILLUSTRATIONSFigure Title Page4-1 Gulfstream G150 ...................................................................................................... 4-2

6-1 Exterior Dimensions ................................................................................................. 6-0

6-2 Fuselage Axis Coordinate System............................................................................ 6-2

6-3 Fuselage Stations ...................................................................................................... 6-4

6-4 Flight Control Stations ............................................................................................. 6-6

6-5 Fuselage Dimensions................................................................................................ 6-8

7-1 Jacking Pads ............................................................................................................. 7-0

8-1 Aircraft Leveling ...................................................................................................... 8-0

9-1 Main Landing Gear Towing ..................................................................................... 9-0

9-2 Nose Landing Gear Towing...................................................................................... 9-2

9-3 Engine Danger Zones ............................................................................................... 9-4

9-4 G150 Turning Radius ............................................................................................... 9-6

10-1 Mooring Attachment Points ................................................................................... 10-0

12-1 Lubrication Figure (Typical) .................................................................................. 12-012-2 Nicad Batteries ....................................................................................................... 12-4

12-3 Electrolyte Level Check ......................................................................................... 12-6

12-4 Flush-Toilet Servicing ............................................................................................ 12-8

12-5 Refuel/Defuel Panel ............................................................................................. 12-12

12-6 Acceptable/Unacceptable Bonding Practices....................................................... 12-14

12-7 Hydraulic Servicing ............................................................................................. 12-18

12-8 Hydraulic Reservoirs Pressurization .................................................................... 12-20

12-9 Main Hydraulic System External Power Source Installation .............................. 12-22

12-10 Auxiliary Hydraulic Accumulator Charging........................................................ 12-24


Revision 0 4-iiiFOR TRAINING PURPOSES ONLY

12-11 Brake Wear Indication.......................................................................................... 12-26

12-12 Emergency Light Locations ................................................................................. 12-28

12-13 Oxygen Filler Valve ............................................................................................. 12-30

12-14 Engine Oil System Servicing ............................................................................... 12-32

12-15 APU Oil System Servicing .................................................................................. 12-36

TABLESTable Title Page6-1 Dimensions ............................................................................................................... 6-9

6-2 Areas....................................................................................................................... 6-10

6-3 Zones ...................................................................................................................... 6-11

12-1 Fuel Tank Capacities ............................................................................................ 12-10

12-2 Approved Hydraulic Fluids.................................................................................. 12-16


Revision 04-iv FOR TRAINING PURPOSES ONLY



INTRODUCTIONThis chapter covers general information about the Gulfstream G150 Chapters 4 through12. All values, such as pressures, temperatures, rpm and power are used for informa-tion, training and illustrative purposes only. Refer to the current Aircraft MaintenanceManual and approved Airplane Flight Manual for specific values and tolerances.

GENERALThe Gulfstream G150 is a swept-wing, twin-engine monoplane designed to accommodatea crew of two and a maximum of eight passen-gers in spacious comfort. The aircraft featuresa large, optimized cabin, highly integratedav ion ics , and excep t iona l pe r fo rmance

capabilities. It is a pressurized, twin turbofan,low wing, transport-category aircraft utiliz-ing an all-metal airframe. New generation com-pos i t e ma te r i a l s a re used in secondarystructures where appropriate.

CHAPTER 412AIRCRAFT GENERAL



Figure 4-1. Gulfstream G150

The Gulfstream G150 (Figure 4-1) incorpo-rates a low-drag/high-lift wing that has beenoptimized for both high-speed/high-altitudeflight and low approach speeds. The aircraft'sdouble-swept, three dimensional airfoil al-lows excellent high-speed performance. Theleading-edge slats combine with trailing-edgeslotted fowler flaps for excellent low-speedcharacteristics. Winglets provide drag reduc-tion by controlling tip vortices, allowinghigher takeoff weights under high and hotconditions and improving long-range cruiseperformance.

All landing gear have dual wheels for safetyand stability. The aircraft is easy to land withits low-wing, leading-edge devices and artic-ulated shock absorber-type trailing-link gear.Aircraft main landing gear are equipped withan anti-skid device on each wheel. The noselanding gear is a direct telescope type and isequipped with an electro-hydraulic steeringsystem.

The aircraft is powered by two HoneywellTFE731-40AR-200G advanced technology,turbofan engines that generate 4,420-poundsof static thrust up to 76F. The aircraft enginesare pylon mounted on the upper aft fuselage.Thrust reversers are standard.

The custom design includes the cockpit, pas-senger cabin, and lavatory. Ample allowancefor baggage stowage is provided in the 55cubic foot baggage compartment. Access to thebaggage compartment is accessible through aside-opening door facilitating crew handlingof baggage and cargo.

An auxiliary power unit (APU) is standardaboard the aircraft with in-flight start and usecapabilities. The APU provides electricalpower, air conditioning, and heating duringground operations. These same capabilities areavailable in flight if required.

Chapters 5 through 12 of the AMM are prima-rily concerned with ground handling, servic-ing, and aircraft care, with chapter titles asfollows:

5Time Limits/Maintenance Checks 6Dimensions and Areas 7Lifting and Shoring 8Leveling and Weighing 9Towing and Taxiing 10Parking and Mooring 11Placards and Markings 12Servicing

NOTES



TIME LIMITS/MAINTENANCE CHECKSThe G150 maintenance program was preparedwith the intent of providing the maximumamount of flexibility for the G150 operator.Chapter 5, General, 05-20-00, ComponentMaintenance Requirements, contains all ther equ i r emen t s o f the MSG-3 de r ivedMaintenance Review Board (MRB) Reportplus Gulfstream recommended inspections.The recommended in spec t i ons r e f l e c tGulfstream's understanding of the fleet ex-pectations of dispatch reliability and act as ameans of verifying the inspection intervalschosen in the MRB Report for their potentialeconomic impact.

AIRWORTHINESS LIMITATIONSSECTIONSection 05-10-10 of the AMM provides a listof structural areas to be inspected and engineservice-life limits of critical life-limited com-ponents. These areas are subdivided with lo-cations and pages of instruction on methodsand procedures for inspection. It also gives thenumber of flight hours of the first inspection(threshold hours), followed by inspections atspecific flight-hour intervals.

Damage tolerance analysis on the G150 showsthat the aircraft structure can safely sustaindamage in the form of cracks for a sufficientlylong time to permit timely detection and re-pair of such cracks. The "AirworthinessLimitations Section" provides a set procedureof inspection for structural cracks throughoutthe life of the aircraft. It also provides a recordof any structural cracks found. Detail draw-ings locate precisely the areas which analy-sis has predicted are most susceptible tostructural damage. A large foldout locator ofthe fuselage shows the areas, station num-bers, and figures to refer to for detail draw-ings of the areas to be inspected.

NOTES

Revision 1FOR TRAINING PURPOSES ONLY


5-0

COMPONENT MAINTENANCEREQUIREMENTSSection 05-20-00 of the AMM contains all theprogrammed maintenance operations and fre-quencies to be carried out on the G150 aircraft.

The scheduled inspection intervals selected forthe G150 aircraft are included in this section.

UNSCHEDULEDMAINTENANCE CHECKSSection 05-50-00 of the AMM provides main-tenance checks and inspections on the G150aircraft which are directed by special or un-usual conditions encountered during aircraftground handling, takeoff/landing or airborneincidents.

The unscheduled maintenance checks coverabnormal aircraft operation and include thefollowing:

Lightning strike inspection Hard/overweight landing inspection Flight controls difficult to operate/jammed

High energy stop on landing or takeoffinspection

Bird strike inspection Severe air turbulence/maneuver Overspeed inspection High velocity ground gusts Flap/slat airspeed exceedences inspec-tion

Hail damage to aircraft/engine inspec-tion

The applicable inspection must be performedto determine and evaluate the extent of dam-age in local areas and adjacent structure.

NOTES





55 FT 7 IN(16.94 M)

56 FT 9 IN(17.30 M)

18 FT 5 IN(5.93 M)

Figure 6-1. Exterior Dimensions

DIMENSIONS ANDAREASDimensions and areas are used to aid the op-erator/maintenance personnel in ground han-dling the aircraft and location of components.

This chapter provides aircraft dimensions andareas which locate all major structural com-ponents, systems components and aircraftzones. Aircraft dimensions, areas and speci-fications are provided along with identifica-tion of access doors, access panels, removablefairings and composite structures.

This chapter contains charts, diagrams, figuresand text which give details of the aircraft sta-tions, dimensions, areas, zones, access doors,access panels, removable fairings and compos-ite structures.

Dimensions denote area, linear measurement,performance, radii, range of motion, ratiosand weights.

The exterior dimensions of the G150 are shownin Figure 6-1.

NOTES





FUSELAGE REFERENCEPLANE (FS 0.00)

VERTICAL REFERENCEPLANE (BL 0.00)

HORTIZONTAL REFERENCEPLANE (WL 100.00)

Figure 6-2. Fuselage Axis Coordinate System

STATIONSAircraft stations provide detailed dimensionalinformation for the aircraft in three axes.Station numbers are used to provide dimen-sions and locate components, structures andzones.

Aircraft stations are derived from the geom-etry of the aircraft. The geometry is evolvedabout three basic, perpendicular referenceplanes defining the fuselage coordinate System(FCS). The reference planes that define theFCS are:

Fuselage station plane (FS) Vertical reference plane (BL) Horizontal reference plane or line (WL)

The basic FCS is made up of a global coordi-nate system with three axes, labeled X,Y andZ. The three axes define measurements oflength (X), width (Y) and height (Z) (Figure6-2). Additionally, the intersecting axes defineplanes which segment the aircraft for dimen-sioning. The relationship between the axes,planes and conventional drawing terminol-ogy are:

Station numbers segment aircraft referenceplanes into 1 inch sections providing a stan-dard unit of measurement for dimensions. Allmajor components, structures and aircraftzones can be located utilizing applicable in-tersecting or parallel aircraft stations knownas fuselage stations (FS), butt lines (BL) andwater lines (WL), measured in inches fromfixed points of reference. When coordinatesare used together, they intersect at one point.

The intersection point of the three coordi-nates is the location of the component, struc-ture or work area.

NOTES



AXIS PLANE DRAWING REFERENCE

X

Y

Z

ZY

XZ

XY

FUSELAGESTATION (FS)

BUTT LINE (BL)

WATER LINE(WL)

Revisio

n0

6-4

FO

RT

RA

ININ

GP

UR

PO

SE

SO

NLY

GU

LF

ST

RE

AM

G1

50

MAIN

TENANCE

TRAIN

INGM

ANUAL

Figure 6-3. Fuselage Stations

WL 0.00

P

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WL 1679.00(66.1")

WL 1122.65(44.1")

WL 455.00(17.9")

WL 00.00

FuselageFuselage Station (FS)Fuselage stations (Figure 6-3) represent edgesof vertical planes perpendicular to the hori-zontal reference plane in side view and per-pendicular to the vertical reference plane inplan view. Fuselage stations dimension and lo-cation points are from fuselage station 0.Fuselage station 0 is located 135.65 inches for-ward of alignment points 14L/14R, also knownas datum reference points. Points 14L/14Rare the protruding rivets heads located in FWDfuselage at STA. 135.65, BL 36.99, WL35.00. Reference point 14L is the raised rivetjust forward of the main entry door. Referencepoint 14R is located on the right side of thefuselage directly across from point 14L.Fuselage stations show measurement of lengthalong the longitudinal axis (X).

WaterLine (WL)Water lines represent edges of planes paral-lel to the horizontal reference plane. Waterlines parallel the fuselage center line and lo-cate points, components and distances abovea theoretical datum line WL 0. The WL 0 isbottom of the fuselage.Water lines show meas-urement of height along the vertical axis (Y).

Butt Line (BL)Butt lines represent the edges of vertical planesto the left or right of and parallel to the ver-tical reference plane at BL 0 (aircraft centerline). Butt lines show measurement of widthto the left or right of the aircraft center linealong the lateral axis (Z). Measurements ininches, to the left of BL 0 are designated leftbutt line and measurements to the right of BL0 are designated right butt line.

NOTES





RIB 0

RIB 1

RIB 2RIB 3

RIB 4RIB 5

RIB 6

RIB 7RIB 8

RIB 9RIB 10

RIB 11RIB 12

RIB 13RIB 14

RIB 15RIB 16

RIB 17RIB 18

RIB 19RIB 20

RIB 21RIB 22RIB 23

HORIZONTALSTABILIZER

WING

VERTICALSTABILIZER

BL23.00(684.20 MM)

BL0

BL0

BL5.60(142.24 MM)

BL14.00(355.80 MM)

BL18.156(461.18 MM)

BL33.00(838.20 MM)

BL41.53(1054.86 MM)

BL56.00(1422.40 MM)

BL69.00(1752.60 MM)

BL82.73(2101.34 MM)

BL96.00(2438.40 MM)

BL110(2794 MM)

BL107.90(2740.65 MM)

BL108.80(2763.52 MM)

WL50.966(1294.536 MM)

WL86.80(2204.72 MM)

WL35.00(889.00 MM)

WL50.00(1270.00 MM)

WL66.00(1576.40 MM)

WL82.0(2082.80 MM)

WL93.00(2352.00 MM)

WL109.10(2771.14 MM)

WL110.85(2815.59 MM)

WL0.0

WL78.571(1995.703 MM)

WL82.766(2102.258 MM)

WL102.00(2590.80 MM)

WL116.56(2960.52 MM)

WL167.75(4260.85 MM)

WL174.60(4434.84 MM)

WL179.50(4559.30 MM)

Figure 6-4. Flight Control Stations

WingRib StationsRib stations (Figure 6-4) represent planes per-pendicular to wing reference plane and planeof the rear beam. Rib stations are measuredfrom Rib 0 outboard along the rear beam.

Flap StationsFlap stations represent planes perpendicularto the cone axis. Flap stations are measuredfrom flap station 0 and the trace of BL 0 at thewing reference plane.

Aileron StationsAileron stations represent planes perpendi-cular to the aileron hinge line. Aileron stationsare measured from aileron station 0, intersec-tion of aileron hinge line and BL 0 at the wingreference plane.

Winglet StationsWinglet stations represent planes perpendicu-lar to the winglet reference plane.Winglet sta-tions are measured from winglet station 0 at theintersection of the wing reference plane and thewinglet reference plane to the winglet tip.

Vertical StabilizerFin StationsFin stations represent planes perpendicularto the centerline of the vertical stabilizer cen-ter beam. Fin stations are measured from finstation 0, which is the perpendicular line ex-tension that intersects the vertical stabilizercenter beam.

Rudder StationsRudder stations (Figure 6-4) represent planesperpendicular to the rudder hinge center line.Rudder stations are measured from rudder sta-tion 0, which is the intersection of the rudderhinge center line and vertical stabilizer WL 0.

Horizontal StabilizerStabilizer StationsStabilizer stations (Figure 6-4) representplanes perpendicular to the horizontal stabi-lizer. Stabilizer stations are measured from sta-bilizer station 0 and the trace of BL 0 athorizontal stabilizer reference plane.

Elevator StationsElevator stations represent planes perpendi-cular to the elevator hinge line. Elevator sta-tions are measured from elevator station 0and the trace of BL 0 at horizontal stabilizerreference plane.

PowerplantNacelle StationsNacelle stations represent vertical planes per-pendicular to the nacelle centerline (nacelleBL 0, nacelle WL 0) and define length alongthe engine.

Nacelle Butt LineNacelle butt lines represent vertical planesparallel to the nacelle center line and definewidth of the engine. Nacelle butt line 0 is lo-cated at the nacelle center line.

Nacelle Water LineNacelle water lines represent horizontal planesparallel to the nacelle centerline and definevertical height of the engine. Nacelle water line0 is located at the nacelle center.

Powerplant Radial PlanesPowerplant radial planes extend from the en-gine centerline, located at the intersection ofpowerplant butt line 0 and powerplant waterline 0. Powerplant radial planes are measuredin degrees counterclockwise from top center(powerplant radial plane 0) looking aft.





69

69

69

54

48

178

Figure 6-5. Fuselage Dimensions

DIMENSIONSDimensions include, but are not limited to,fuselage length, width and height, wingspan,turning radius and aircraft weights.

Dimensions are measured in planes parallel orperpendicular to the horizontal reference planeand expressed in feet, inches and meters



EXTERIOR DIMENSIONS

COCKPIT DIMENSIONS

CABIN DIMENSIONS

BAGGAGE COMPARTMENT DIMENSIONS

OVERALL LENGTH

OVERALL HEIGHT

OVERALL SPAN

56'9"

18'5"

55'7"

69"

55.2"

70.6"

121.7 CUBIC'

17'8"

5'9"

5'9"

465.0 CUBIC'

25 CUBIC'

53.85"

39.40" MIN49.10" MAX

38.20" MIN48.35" MAX

55 CUBIC' EXTERNAL25 CUBIC' INTERNAL

1.37 METERS

0.71 CUBIC METERS

13.17 CUBIC METERS

1.75 METERS

1.75 METERS

5.4 METERS

3.45 CUBIC METERS

1.79 METERS

1.40 METERS

1.75 METERS

16.94 METERS

5.93 METERS

17.30 METERS

1.00 METERS MIN1.25 METERS MAX

0.97 METRES MIN1.23 METERS MAX

1.56 METERS EXTERNAL0.71 CUBIC INTERNAL

LENGTH

HEIGHT

WIDTH

VOLUME

LENGTH

HEIGHT

WIDTH

VOLUME

LENGTH

HEIGHT

WIDTH

VOLUME

BAGGAGE VOLUME

Table 6-1. DIMENSIONS

AREASAircraft areas are measured in planes paral-lel and perpendicular to the fuselage referenceplane.

Aircraft areas are expressed in square feet,square inches and square meters.



KEY AREA SIZE

WING AREAFLAP AREASPOILER AREAAILERON AREAWINGLET AREAVERTICAL STABILIZER AREARUDDER AREAHORIZONTAL STABILIZER AREAELEVATOR AREA

337.2 SQ FT44.8 SQ FT12.7 SQ FT12.9 SQ FT5.56 SQ FT99.03 SQ FT12.6 SQ FT150.67 SQ FT21.7 SQ FT

Table 6-2. AREAS

ZONESAircraft zones are provided to standardize di-vision of the aircraft, facilitate inspection,job instructions, maintenance planning and

simplify location of work areas, access doors,access panels, ports, removable fairings andcomponents.



MAJORZONE

DESCRIPTIONLOCATION

INCHES MILLIMETERSLOWER FUSELAGE

AFT FUSELAGE/EMPANNAGE

POWERPLANT, PYLONS AND NACELLES

LEFT WING

RIGHT WING

LANDING GEAR

DOORS

100

200

300

400

500

600

800

700

UPPER FUSELAGE

FS 0FS 426.14 0FRAME 43

FS 21.89FS 353 1FRAME 35

FS 0FS 10824 0FRAME 43

FS 556FS 3531FRAME 35

APPROX FS 463-FS578

Table 6-3. ZONES



SEE DETAIL BSEE DETAIL A

DETAIL BDETAIL A

WINGJACKINGPAD

NOSEJACKING

PAD

Figure 7-1. Jacking Pads

LIFTING AND SHORINGLifting and shoring includes the necessaryprocedures to lift and shore the aircraft underany condit ion. This includes lif t ing andshoring procedures employed during main-tenance.

AIRCRAFT JACKINGThe fuselage contains one jacking point lo-cated at FS 140.9 (3580 mm). The wings con-tain two jacking points at FS 367.4 (9332mm), BL 103.7 (2633 mm).The three jacking points (Figure 7-1) are ca-pable of supporting the aircraft at the designramp gross weight and also enable lifting ofthe aircraft for weighing by electronic loadcells. Jack pads must be installed to accept thejacks.

It is mandatory to place a cradleunder the tail at frame 45 or 1,550 lbs(700 KG) ballast at FS 19 to preventthe aircraft from tipping.

When jacking the complete structure, the max-imum gross weight must not be exceeded.Jacking individual gear units for wheel chang-ing is done using the main gear shock strutslocking links and axle jacks.Chapter 7 in the Maintenance Manual lists theapproved jacking equipment and the proce-dures to be used to safely jack the aircraft.

NOTEBefore the aircraft is jacked, the fol-lowing circuit breakers must beopened:

ST BY GYRO (overhead panelSYSTEMS)

AOA PROBE HEAT (overhead panelICE PROTECTION)

PITOT STATIC HEAT (overhead panelICE PROTECTION)

SAT/TAS PROBE HEAT (overheadpanelICE PROTECTION)

HOUR METER (overhead panelSYSTEMS)

HEAT POWER (overhead panelwindshield)

EMERGENCY LIFTINGThis procedure provides instructions for emer-gency lifting of aircraft using hoist and slingassembly.

This procedure may be used for lifting adowned aircraft in case of two or more of thelanding gear has collapsed (retracted).A lifting sling is positioned at fuselage pro-duction splices located just aft of entrancedoor FS 221.8 (5633 mm) and main landinggears FS 452.0 (11483 mm) and nylon strapsaround the fuselage.

SHORINGThe aircraft may be supported with props,beams and shoring, when required.

If required, shoring is accomplished usingcontour boards that conform to the lower sur-faces of the wing and fuselage. Contour boardsare fabricated from two thicknesses of one-inch plywood, laminated together and securedby bolts. The contour surface is then coveredwith one-half-inch felt, followed by heavycanvas.

CAUTION





FS 200

FS 200

SEAT TRACKS

SEAT TRACKS

AIRCRAFTCENTERLINE

AIRCRAFTCENTERLINE

CABIN FLOOR

NOTE:TO LEVEL, PLACE GAUGE

ON SEAT TRACK AT FS 200 AT 90 TO AIRCRAFT CENTERLINE.

NOTE:TO LEVEL, PLACE GAUGE

ON EITHER SEAT TRACK AT FS 200 PARALLEL WITH AIRCRAFT CENTERLINE.

DETAIL ALATERAL LEVELING PROCEDURE

SEE DETAIL A SEE DETAIL B

DETAIL BLONGITUDINAL LEVELING PROCEDURE

CABIN FLOOR

FWD

FWD

GAUGE PLATE

Figure 8-1. Aircraft Leveling

LEVELING ANDWEIGHINGLeveling of the aircraft is required to carry outmaintenance practices such as weighing, sym-metry checks, etc. Lateral and longitudinalleveling of the aircraft is accomplished byadjusting the height of the jacks which sup-port the aircraft. All weight and balance com-putations are based on measurements takenwhen the aircraft is in a level position. Thisposition is when the longitudinal axis of theaircraft is in a horizontal plane. Weighing ofthe aircraft is accomplished whenever modi-fications or repairs are accomplished and cal-culated or actual weight and moment data arenot available. When unsatisfactory flight char-acteristics are reported by the pilot, whichcannot be traced to flight control systems mal-functions, improper load or error in weight andbalance data.

AIRCRAFTWEIGHT ANDBALANCINGOne of the basic elements of aircraft designis weight. The weight of an aircraft is used indetermining such design criteria as engine re-quirements, wing area, landing gear require-ments and payload capacity. Weight changes,whether in modification or maintenance, canhave distinct effects on aircraft performanceand payload capability. All aircraft are de-signed with a number of weight limits. Theselimits are determined by performance, controland structural restrictions. If the aircraft ac-tual weight exceeds the design weight, reduc-tions in performance and payload result. Anincrease in gross weight increases takeoffspeed, stalling speed and landing ground roll.Rate-of-climb, ceiling and range decreasewith increasing gross weight. If the operatingweight increases while performance require-ments remain the same, then the payload orfuel may decrease.

Aircraft weight and balance can be used to de-termine the following:

Basic operating weightBasic aircraftweight plus the operating items

Zero fuel weightBasic operat ingweight plus payload

Ramp weightZero fuel weight plususable fuel

Takeoff weightWeight at brake re-lease for takeoff

Usable fuelWeight of fuel remainingin the aircraft when fuel level is belowpump delivery level

Usable/drainable fuelUsable fuel(weight) that may be drained from theaircraft using standard drain valves

Unusable/undrainable fuelUnusablefuel (weight) remaining in the aircraftafter draining

AIRCRAFT LEVELINGAll weight and balance computations are basedon measurements taken when the aircraft is ina level position. This position is when the lon-gitudinal axis of the aircraft is in a horizon-tal plane.

Leveling is accomplished using a spirit levelon the seat tracks (Figure 8-1) and adjustingthe jacks accordingly. The aircraft is approx-imately level when the landing gear struts areextended normally and the tires are properlyinflated.





FWD

9

9

32FT 10IN 4IN(10M 1M)

BACKWARD

LINK

MLG WHEELSLING

SLING ATTACHMENTTO MLG

SEE DETAIL A

DETAIL A

CABLE13,860 LBS(6,300 KG) MAXTENSION FORCEIN EACH CABLE

Figure 9-1. Main Landing Gear Towing

TOWING AND TAXIINGTowing procedures are basically the same forthis aircraft as the procedures for any aircraftwith tricycle landing gear. The aircraft can betowed forward or be pushed backward on hardsurfaces, using a Gulfstream approved towbaror towbarless tug. To tow the aircraft fromsoft sand, earth or mud, steel cables or a nylontowing harness must be attached to the maingears and two tow vehicles must be used.Taxiing the aircraft for maintenance purposesshould be limited to qualified individuals only.

Towing and taxiing the aircraft witha flat tire is prohibited except whena hazardous condition arises. Towor taxi the aircraft the minimum dis-tance necessary to clear the runway.Avoid sharp turns and abrupt startsand stops.

MAIN LANDING GEAR TOWINGWhen the aircraft is to be towed out of softsand, mud or earth, the aircraft must be towedaft from the main landing gear (Figure 9-1).Steel cables (3/4 inch) or a nylon towing har-ness is attached to each main landing gearand two tow vehicles are used. The nose geartowbar shall be used only for steering whilethe aircraft is being towed.

Towing the aircraft without brakes oremergency brake accumulator etc.,will require special handling and ad-ditional personnel.

NOTES

CAUTION

CAUTION





NOSELANDING GEARSAFETY PIN

REMOVE

BEFORE

FLIGHT

TOWINGDEVICE

SPARESHEAR PINS

NOSE LANDING GEAR

TOWINGADAPTER

JACKINGPAD

2950

TOWING DEVICE TRAVEL

PIP PIN

TOWHEADADAPTER

Figure 9-2. Nose Landing Gear Towing

NOSE LANDING GEAR TOWINGTowing the aircraft on hard surfaces is ac-complished by using a tow bar connected tothe towing adapter, which is part of the noselanding gear (Figure 9-2). There is a portabletow bar that comes with the aircraft as part ofthe loose equipment. When using the portabletow bar it is important that the bar be fully ex-tended and all pip pins are properly installed.

The towing adaptor has a shear pin installedto protect the aircraft from excessive loads dur-ing towing. There are two spare shear pinsinstalled on the towing adaptor in case themain pin shears.

The towing vehicle should have a minimumdrawba r pu l l o f 12 ,000 pounds and beequipped with a torque converter to minimizeacceleration and deceleration loads on thenose gear for dry conditions.

Towing the aircraft without brakes oremergency brake accumulator etc.,will require special handling and ad-ditional personnel.

Nose wheel scissors must be discon-nected, and the nose landing gearsafety pin installed, prior to towingthe aircraft. Failure to comply mayresult in damage to the steering sys-tem support brackets.

The maximum towing limit with thenose scissors disconnected is 100 ei-ther side from center.

Always inspect the towing adaptersheer pin; ensure that the shear pinis installed and that the cotter pin isinstalled.

NOTES

CAUTION

CAUTION

CAUTION

CAUTION





12FT

40 FT

NOTE:IF BLAST DEFLECTOR IS NOT AVIALABLE,

AREA MUST BE CLEAR 100 FT AFT OF AIRCRAFT.

Figure 9-3. Engine Danger Zones

TAXIINGThe purpose of taxiing is to move an aircraftusing its own power to another location. Thrustrequirements for taxiing depend on the slope,condition of the ramp and the gross weight ofthe aircraft. Prior to taxiing, check indica-tions of main and auxiliary hydraulic systemsto ensure the systems are filled to the properquantity. Advance throttles evenly and do notattempt to engage nose wheel steering until air-craft is in motion. Check for positive brakingaction immediately after aircraft starts tomove. Smooth directional control during taxi-ing is accomplished by using nose wheel steer-ing, application of asymmetrical thrust isineffective and differential braking may causeoverheating of the brakes. The use of throttlesand braking action to set taxi speed and stopthe aircraft is preferred.

The aircraft turning radius is 60 either sideof center using the steering tiller set to maxdeflection. The nose wheel steering uses rud-der input for a max of 3 input either side ofcenter using the rudder pedals; this input isadded to any tiller input.

Make sure that personnel and equip-ment are clear of the engine inletand exhaust (Figure 9-3).

Do not operate the engines with theemergency exits removed or the leftengine above idle with the cabin en-trance door open. Personnel shouldwear ear protectors during engineoperation.

NOTES

WARNING

WARNING





60

34' 2" (10.41 m)

43'2"

(13.15

m)

29' 2

" (8.89 m)

36'1"

(10.99

m)

21' 0"

(6.40 m)

49' 7"

(15.11 m)

Figure 9-4. G150 Turning Radius

Figure 9-4 shows the turning radius of theG150.

The maximum turning angle using the nosewheel steering is 60 and enables the aircraftto preform a u-turn in 497, thus keeping thelanding gear on the hard runway/taxiway.

NOTEThe wings require at least a 109 ra-dius during the u-turn. Make sureadequate clearance is available be-fore initiating the u-turn.

NOTES





Figure 10-1. Mooring Attachment Points

PARKING ANDMOORINGThe aircraft is normally parked or moored ona hard-surface apron where mooring accom-modations are available. The aircraft shouldalways be parked with the nosewheel cen-tered.

PARKING AND STORAGEParking aircraft involves use of ground safetylocks, parking brakes, chocks and protectivecovers. To prevent inadvertent retraction oflanding gear while on ground, safety locksshould be installed during parking and moor-ing. The parking brake is utilized to applymain landing gear wheel brakes during park-ing. A gust lock is provided to lock all flightcontrols without use of external locking de-vices. During parking and mooring, chocksand protective covers are needed.

Outside storage procedures are based on ahumid tropical atmosphere. Based on thissomewhat severe climate, an aircraft remain-ing inoperative for a period of 15 days or moreis considered as having the aircraft in storage.The requirements for inside storage is thesame as outside. Electronic equipment may re-main installed in aircraft, but must be oper-ated at least 1 hour every week up to 90 days,unless otherwise specified by manufacturer.Inside storage is considered to be a placewhere humidity and temperature are con-stantly controlled. A hangar area where thedoors are continuously opened is not consid-ered as constant temperature, even when it isair conditioned.

MOORINGThe aircraft should be moored when parked inthe open for any length of time or during ex-isting or expected bad weather conditions.

Provisions are incorporated on the main andnose landing gear for mooring. A spring-loaded ring is mounted on each main landing

gear and two rings are mounted, one on eachside, on the nose landing gear just below taxilights (Figure 10-1). All mooring rings areheld down by torsion springs. The springs po-sition rings against the strut in order to clearlines and structure in wheel wells when thelanding gear is retracted.

When winds up to 60 knots are forecast, theaircraft must be moored when outdoors. Inwinds up to 20 knots, secure the main land-ing gear and tail with 3/4-inch manila or nylonrope, tied in a clove hitch or other antislipknot. In 20- to 60-knot winds, secure the nosegear also. If winds over 60 knots are forecast,the aircraft must be hangared or flown out ofthe area.

NOTELeave sufficient slack in the ropes toavoid causing damage to the aircraftif the ropes shrink.

For extended mooring, every 30 days accom-plish the following:

Service tires. Connect electrical power, and motoreach engine for 30 seconds.

Check and service, if required, all fluidlevels.

Check the security and condition of allprotective covers.





1620165516851720175017851820

FILLINGPRESSP.S.I.G.

0102030405060

INITIALTEMPDEG F

13

11

GRAVITY REFUEL CAPACITY IS LESS THANPRESSURE REFUEL CAPACITY BY655 lb (300 kg) - 98 US gal (82.0 lmg. gal)

FUEL JET A JET B, JET A-1, JP-5 OR EQUIV.PER A.F.M. SECT I CAPACITY10380 lb (4708 kg) - 1549 US gal (5864 liters)

1 OXYGEN CHARGING PER MAINT MANUAL2 TABLE OF FILLING PRESSURES

CAUTION

HYDRAULIC RESERVOIRSEXTERNAL PRESSURIZATION POINTUSE ONLY DRY NITROGEN

GRAVITY REFUEL

THERMAL RELIEFOXYGEN BOTTLE

1850188019151950198020152050

FILLINGPRESSP.S.I.G.

708090

100110120130

INITIALTEMPDEG F

1415 4

578910

1213

5

14

12

11

CLEAN ADAPTERPER AMM 20-70-13PRIOR TO USE

7

PITOTSTATIC

15

STATIC38

STATIC49

10

STATICSOURCES

5

OXYGEN REFILL4

Figure 11-1. Placards and Markings

PLACARDS ANDMARKINGSNumerous placards, nameplates, and markingsare listed in Chapter 11 of the MaintenanceManual, and their locations are shown. Theyare used for various purposes, including:

Operating or installation instructions Directional movements Servicing instructions Part or position identification Rescue and escape instructions Safety precautions

Where ambiguity might exist as to the exactlocation for a decal,

Documents

G150 MTM