G500-G550 MTM V1

FlightSafetyinternational

FlightSafety International, Inc.Marine Air Terminal, LaGuardia Airport

Flushing, New York 11371(718) 565-4100

www.flightsafety.com

GULFSTREAM G500/G550MAINTENANCE

TRAINING MANUALVOLUME 1

Courses for the G500/G550 and other Gulfstream aircraft are taught at thefollowing FlightSafety learning centers:

FlightSafety InternationalGulfstream Learning Center301 Robert B. Miller RoadSavannah, Georgia 31408(912) 644-1000(800) 625-9369

FlightSafety InternationalLong Beach Learning CenterLong Beach Municipal Airport4330 Donald Douglas DriveLong Beach, CA 90808(562) 938-0100(800) 487-7670

FlightSafety InternationalGreater Philadelphia/Wilmington Learning CenterNew Castle County Airport155 North duPont HighwayNew Castle, Delaware 19720(302) 221-5100

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

Copyright 2005 by FlightSafety International, Inc.All rights reserved.

Printed in the United States of America.

FOR TRAINING PURPOSES ONLY


NOTICEThe material contained in this training manual is based on informationobtained from the aircraft manufacturers Pilot Manuals andMaintenance Manuals. It is to be used for familiarization and trainingpurposes only.

At the time of printing it contained then-current information. In the eventof conflict between data provided herein and that in publications issuedby the manufacturer or the FAA, that of the manufacturer or the FAAshall take precedence.

We at FlightSafety want you to have the best training possible. Wewelcome any suggestions you might have for improving this manual orany other aspect of our training program.

CONTENTSVOLUME 1

ATAChapter Title Number

INTRODUCTION

ATA 100

AIRCRAFT GENERAL 512

AIR CONDITIONING 21

AUTOFLIGHT 22

COMMUNICATIONS 23

ELECTRICAL POWER 24

EQUIPMENT AND FURNISHINGS 25FIRE PROTECTION 26

FLIGHT CONTROLS 27

FUEL 28

HYDRAULIC POWER 29

ICE AND RAIN PROTECTION 30

INDICATING AND RECORDING SYSTEMS 31

Revision 2 LEP-1

LIST OF EFFECTIVE PAGES

Dates of issue for original and changed pages are:Original ......0 ....... January 2005

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.


FlightSafety international

GULFSTREAM G500/G550 MAINTENANCE TRAINING MANUAL

Page *RevisionNo. No.Cover6 ................................................ 0LEP.......................................................... 01-2 .......................................................... 02-i2-24 .................................................. 05-i12-46 ................................................ 021-i21-90 .............................................. 023-i23-14 .............................................. 024-i24-150 ............................................ 025-i25-20 .............................................. 026-i26-50 .............................................. 027-i27-112 ............................................ 028-i28-62 .............................................. 029-i29-50 .............................................. 030-i30-46 .............................................. 031-i31-64 .............................................. 0

GENERALIn addition to the basic Maintenance TrainingManual, FlightSafety provides a supplementalMaintenance Schematic Manual (MSM) to beused concurrently. The MSM, commonly calledthe flat manual, is printed in an 11 x 17-inchformat and contains schematics to be used onlyas a tool in understanding a system. They are notkept current. The corresponding schematic(s) inthe manufacturers Maintenance Manual mustbe used when performing maintenance.

The second chapter of this manual, ATA100/Publications, is an introduction to the AirTransport Association format for aircraft main-tenance manuals. It is intended to describe sim-ply the basic format for all ATA 100 maintenancemanual chapters and also to explain where vari-ations may exist from one manufacturer to an-other. In addition, it includes information onvarious Gulfstream Aerospace publications use-ful to the maintenance technician.

1-1FOR TRAINING PURPOSES ONLY

INTRODUCTION

INTRODUCTIONThis training manual provides a description of the major airframe and engine systemsinstalled in the Gulfstream G500/G550. This information is intended as an instructionalaid only; it does not supersede, nor is it meant to substitute for, any of the manufacturersmaintenance or operating manuals. This material has been prepared from the basic de-sign data, and all subsequent changes in airplane appearance or system operation willbe covered during academic training and by subsequent revisions to this manual.



Following ATA 100/Publications, each chap-ter of this book has listed on the divider tabthe ATA chap te r i nc luded , such a s 24Electrical Power. In some cases it was ap-propriate, for training purposes, to includemore than one ATA chapter in one chapter ofthis book, such as Chapter 5157, Structures,wh ich i nc ludes i n fo rma t ion f rom ATAChapters 51 through 57.

The goal of this course is to provide the verybest training possible for the clients in ourmaintenance initial program. So that there isno uncertainty about what is expected of theclient, the following basic objectives are pre-sented for this course.

Given the Gulfstream G500/G550 AircraftMaintenance Manual (AMM), class notes, andthis 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 of mainte-nance documentation, including themajor chapter headings and symbology.

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

Perform routine servicing.

Outline the recommended maintenanceschedule applicable options and locateroutine procedures in the manufacturersMaintenance Manual.

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 selected normal and emergencycockpit procedures as required for en-gine start/run-up, APU start, batterycheck, airplane taxiing, etc. (requiresuse of a simulator).

The FlightSafety instructor will modify thestated overall objective conditions and crite-ria to satisfy selected performance require-ments, when appropriate. The performancelevels specified will not vary from those di-r ec t ed by t he F l i gh tSa fe ty D i r ec to r o fMaintenance Training.

FOR TRAINING PURPOSES ONLY1-2



2-i

CHAPTER 2ATA 100/PUBLICATIONS

CONTENTSPage

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

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

AIR TRANSPORT ASSOCIATION (ATA) NUMBERING SYSTEM .................................. 2-3General ............................................................................................................................. 2-3

Aircraft Maintenance Manual Format.............................................................................. 2-3

Revisions and Service Bulletins....................................................................................... 2-5

AIRCRAFT MAINTENANCE MANUAL............................................................................. 2-9

General ............................................................................................................................. 2-9

Types of Information........................................................................................................ 2-9

Fault Isolation Manual ................................................................................................... 2-13

WIRING DIAGRAM MANUAL.......................................................................................... 2-15

General........................................................................................................................... 2-15

Equipment Locator ........................................................................................................ 2-15

Schematic Diagrams ...................................................................................................... 2-19

Wire Lists....................................................................................................................... 2-21

Termination Lists ........................................................................................................... 2-21

ADDITIONAL PUBLICATIONS...........................................................................................2-21

Illustrated Parts Catalog................................................................................................. 2-21

Operating Manual .......................................................................................................... 2-21

Airplane Flight Manual.................................................................................................. 2-21




Structural Repair Manual............................................................................................... 2-21

Weight and Balance Manual .......................................................................................... 2-22

Master Minimum Equipment List.................................................................................. 2-22

Configuration Deviation List ......................................................................................... 2-22

OPERATOR COMMUNICATIONS..................................................................................... 2-23

2-ii FOR TRAINING PURPOSES ONLY



2-iii

ILLUSTRATIONSFigure Title Page2-1 ATA System Code Example ..................................................................................... 2-2

2-2 System Description................................................................................................... 2-8

2-3 Adjustment/Test Example ...................................................................................... 2-102-4 Fault Isolation Manual Example ............................................................................ 2-12

2-5 Equipment Locator Example (System-Referenced)............................................... 2-142-6 Equipment Locator Example (Aircraft Assembly-Referenced)............................. 2-162-7 Schematic Diagram Example................................................................................. 2-18

2-8 Schematic Symbols ................................................................................................ 2-19

2-9 Wire List Example ................................................................................................. 2-20

2-10 Termination List Example...................................................................................... 2-20






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-format manual, the main-tenance technician must become thoroughly familiar with the outline and contents pre-sented for any given airplane. In addition, the various types of publications and operatorcommunications for the Gulfstream G500/G550 aircraft are discussed.

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CHAPTER 2ATA 100/PUBLICATIONS


GENERALATA Specification No. 100 is issued by the AirTransport Association of America as theSpecification for Manufacturers TechnicalData . I t es tab l i shes a s tandard for the presentation of certain data produced by aircraft,engine, and component manufacturers requiredfor the support of their respective products.

Under this format, the Aircraft MaintenanceManual is broken down into standard chaptersas defined by ATA 100. Each chapter coversa specific area of maintenance information,such as Chapter 10, Parking and Mooring,or a specific system, such as Chapter 32,Landing Gear. All data pertaining to a givensystem is located within its chapter, regardlessof whether it is mechanical, hydraulic, or elec-trical in nature. The chapters are arranged inalphabetical order.

2-2 FOR TRAINING PURPOSES ONLY



27 . 51 . 05

CHAPTER/SYSTEMFLIGHT CONTROLS

SUBSYSTEM/SECTIONFLAPS

UNIT/SUBJECTREMOVAL/INSTALLATION

Figure 2-1. ATA System Code Example

Besides the Aircraft Maintenance Manual, themaintenance technician uses many other pub-lications and communiqus, such as the WiringManual, the Illustrated Parts Catalog,FaultIsolation Manual, and Service Bulletins, toperform aircraft maintenance and keep hisknowledge up to date.

AIR TRANSPORTASSOCIATION (ATA)NUMBERING SYSTEMGENERALAll maintenance publications are formatted ac-cording to the Air Transport Association (ATA)numbering system, which identifies chap-ter/system, subsystem/section, and unit/sub-ject for each assigned item of equipment(Figure 2-1). The following information is ageneral discussion of the ATA 100 system andis not specific to Gulfstream Aerospace pub-lications.

The Aircraft Maintenance Manual (AMM) isprepared from the manufacturers technicaldata in accordance with the Air TransportAssociation and conforms to ATA 100 Revision32.

The AMM provides sufficient information toenable a mechanic who is unfamiliar with theairplane to service, test, adjust, and repairsystems and to remove and install any unitnormally requiring such action on the line orin the maintenance hangar.

AIRCRAFT MAINTENANCEMANUAL FORMATDivision of Subject MatterThe introduction to the AMM lists the chap-ters from the ATA 100 format which are in-cluded in the manual. Each chapter has the

following items (as applicable) filed at thefront:

Effectivity code cross-reference list Highlights page(s) for each normal

revision List of effective pages List of effective temporary revisions List of service bulletins Table of contents

Standard Numbering SystemThe numbering system identifies and segre-gates subject matter by chapter (system), sec-tion (subsystem), and subject (unit) (Figure2-1). The system is a conventional dash-num-ber breakdown, and each number is composedof three elements consisting of two digits each.

When referred to as a unit, the three-elementnumber (chapter/section/subject) is called thechapter/section number. The chapter/sec-tion number is located in the lower-right cor-ner of each page with the page number anddate. Each system, subsystem, and unit is al-located a block number.

A page numbering system allows rapid loca-tion of information for retrieval. All mainte-nance information is separated into specifictypes of information (topics), and blocks ofpage numbers are assigned to each.

Chapter Numbering SystemThe chapter numbering system provides afunctional breakdown of the entire aircraft.

It uses a three-element number, with the ele-ments separated by dashes. Each element con-tains two digits, corresponding to chapter/system, section/subsystem, and subject/unit.




Chapter/SystemThe first pair of digits is assigned by ATASpecification 100 and designates thechapter/system. For example, 21-xx-xx identifiesthe air-conditioning system.

Section/SubsystemThe second pair of digits designates the sec-tion/subsystem. Only the first digit will beassigned by ATA Specification 100.

When the second pair is -00-, it shows thematter will be treated in general and appliesto the chapter/system as a whole. The seconddigit of the pair is used when it is convenientto break down the section/subsystem.

For example, 21-20-xx identifies the airdistribution subsystem, and 21-22-xx identifiesthe passenger cabin distribution subsystem.

Subject/UnitThe third pair of digits designates a compo-nent or functions of chapters and sections cov-ered by the previous elements.

When the third pair is -00-, it shows that thematter will be dealt with in general and appliesto the section as a whole, without treatingspecifics concerning components or functions.

As an example, 21-24-01 identifies the recir-culation fans of the air-conditioning distri-bution subsystem.

EffectivityIn the lower left corner of each page is infor-mation on effectivity. When a page applies toall aircraft, the word ALL is printed in theeffectivity box. If the information does notapply to all aircraft, the particular aircraft towhich the information does apply are specified.

Effectivity differences are reflected withinthe text or figures through references, call-outs, or even by adding specific page blocks.

When applicable, the effectivities of servicebulletins are differentiated through the fol-lowing indications:

Pre-Mod SBAircraft covered by theservice bulletin effectivity that do nothave the relevant modification(s) in-corporated

Post-Mod SBAircraft whose opera-tor has accomplished the service bul-l e t i n o r t ha t have t he r e l evan tmodification(s) factory-incorporated

The following page number blocks are used inthe AMM:

1 to 99 .... Description and Operation 201 to 299 .... Maintenance Practices 301 to 399 ............................ Servicing 401 to 499 ........ Removal/Installation 501 to 599 ................ Adjustment/Test 601 to 699 .............. Inspection/Check 701 to 799 ............ Cleaning/Painting 801 to 899 .............. Approved Repairs

Each new topic of information starts with page001, 101, 201, 301, etc., and continues withinthe page numbering block as necessary; unusedpage number blocks are omitted.

Illustrations and tables use the same num-bering system as the page block in whichthey appearfor example, Figure 403 is thethird figure in the Removal/Installation topic.If an illustration requires more than one pageunit, whether it is a foldout or multiple-sheetpresentation, each page unit is assigned asheet number.




REVISIONS AND SERVICEBULLETINSGeneralATA 100 allows the manufacturer a great dealof leeway or freedom in the area of AMM re-visions and their dissemination. Virtuallyevery aircraft manufacturer has a system dif-ferent from any other manufacturer; some dif-ferences are great while others are barelynoticeable, but all are intended to get main-tenance information, routine or vital, to thefield in a timely manner.

Because changes, particularly new temporarychanges, may be vital to ground and/or air-borne safety, the maintenance technicianshould be thoroughly familiar with the method-ology used by a particular manufacturer to in-co rpo ra t e changes i n to an AMM . Themanufacturers methods are listed in detail inthe AMM Introduction for a given airplane.

Two types of revisions are issued for the AMM:permanent and temporary. Service bulletins arealso issued and disseminate information whichmay be of a routine nature or require specialhandling and prompt compliance.

When text or art in illustrations is revised, ablack bar appears on the page outside the mar-gin beside the revised, added, or deleted ma-terial.

A bar beside the page number or the sectiontitle and the printing date indicates that nei-ther the text nor the illustration has beenchanged but that the material has been relo-cated to a different page or a totally new pagehas been added.

Temporary RevisionsGeneralTemporary revisions are urgent in nature.Theyare printed on yellow paper and notify operatorsof changes or provide advance information onsome equipment or modifications. A temporaryrevision is filed in the manual as instructed in the

temporary revision. The changes in thetemporary revisions will be incorporated in thefirst permanent revision following their release.

List of Effective TemporaryRevisionsTemporary revisions are recorded on the list of effective temporary revisions. The page has columns for writing in the temporary revision number and issue date.

Permanent RevisionsGeneralPermanent revisions are printed on white paperand are issued to qualified holders as required toupdate the AMM. Additions, deletions, orrevisions to the text are identified on the textpage by a black bar in the left margin of the pageadjacent to the revision.

Letter of TransmittalA letter of transmittal accompanies eachpermanent revision published by themanufacturer. The letter gives filing instructionsand the reason for issue. Listed in the filinginstructions are the temporary revisions whichare incorporated in the permanent revision.Those temporary revisions are removed from themanual.

List of Effective PagesA new list of effective pages is issued with eachpermanent revision. The AMM uses three codesto identify pages for update:

RRevised (to be replaced) DDeleted (to be removed) NNew (to be added)




Effectivity Code Cross-Reference ListThe aircraft serial number effectivity for anAMM page is listed in the lower-left corner ofthe page. It says ALL or gives a specificeffectivity code. The code is listed on theeffectivity code cross-reference list, which isprinted on green paper and lists the specificaircraft serial numbers affected by that code.

HighlightsA highlights page is printed on white paper andis issued with each permanent revision. It liststhe pages in each chapter which are changed andthe reasons for change. It also states No revisedpage for this revision if a permanent changedoes not affect that particular chapter.

Record of RevisionsThe record of revisions is filed in the front ofthe AMM and provides a place for the re-sponsible individual to record the successiverevision numbers, dates inserted, and his ini-tials against the appropriate revision number.If the revision is inserted by the factory for areprint of the manual, the revision recordshows the revisions already incorporated.

Service BulletinsGeneralService bulletins are printed on either white or blue paper. White paper indicates routine handling with a specified time limit forcompliance. Blue paper indicates specialhandling with a specified time limit forcompliance, which may be immediate. Thisinformation is incorporated in the normalrevisions.

Service Bulletin ListThe service bulletin list has columns whichgive the service bulletin number, the revisionin which it is incorporated, and the service bul-letin subject.

Record of Service BulletinsThe record of service bulletins is filed in thefront of the AMM and provides columns whichlist the service bulletin identification numberand the subject.

NOTES




NOTES NOTES







Figure 2-2. System Description

AIRCRAFTMAINTENANCE MANUALGENERALThe primary publication used for maintenanceis the Aircraft Maintenance Manual (AMM).The purpose of the AMM is to acquaint main-tenance technicians with the systems and com-ponents of the Gulfstream G500/G550 and todirect them in the proper procedures for main-taining the aircraft in an airworthy condition.All Gulfstream G500/G550 maintenance pub-lications are also available as electronic man-uals (CD ROM).

NOTEOnly the installations made in theaircraft during manufacture havebeen reflected in this manual.

TYPES OF INFORMATIONThe AMM provides two types of information:system description, fault isolation, and main-tenance practices.

NOTEThe Engine Maintenance Manualwi l l be i nco rpo ra t ed i n t heGulfs tream G500/G550 Aircraf tMaintenance Manual. The StructuralRepair Manual also contains the pro-cedures for corrosion prevention andcorrosion treatment.

System DescriptionThe first type of information contained in theAMM is System Description. This informa-tion is located in page block 1 to 99 and isused by maintenance technicians to quicklygain an overview knowledge of any particularsystem.

The System Description section is provided foreach airframe and powerplant system and de-scribes the system on multiple levels neces-sitated by the system. It provides a centrallocation for the description of all the aircraftsystems, including location, configuration,function, operation, and control of the com-plete system and its subsystems.

As an example of the function of this section,the nosewheel steering system description in-cludes its purpose and a general description,the major subsystems, outstanding system fea-tures, and a description of system operation,as well as an operational summary.

NOTES







Figure 2-3. Adjustment/Test Example

Maintenance ProceduresThe second type of information is MaintenanceProcedures, which are located in page block201 to 299. The Maintenance Procedures areused by maintenance technicians to performdaily aircraft maintenance and servicing.

Page block 201 to 299 is used when a l lsubtopics of Maintenance Procedures are rel-atively brief. When individual subtopics be-come so lengthy as to require a number ofpages, the following page number blocks areused (Figure 2-3):

301 to 399 ............................ Servicing 401 to 499 ........ Removal/Installation 501 to 599 ................ Adjustment/Test 601 to 699 .............. Inspection/Check 701 to 799 ............ Cleaning/Painting 801 to 899 ................................ Repairs

NOTES







Figure 2-4. Fault Isolation Manual Example

FAULT ISOLATION MANUALEven though the Gulfstream G500/G550 FaultIsolation Manual is a stand-alone publica-tion, it is a vital part of the AMM and has beenp repa red i n a cco rdance w i th A i rTranspo r t a t i on Assoc i a t i on (ATA)Specification No. 100, Revision 32.

The Fault Isolation Manual provides a centrallocation for the detailed breakdown of the var-ious aircraft systems fault isolation proce-dures; it also includes AMM references toassist the technician in the resolution of sys-tem malfunctions. Figure 2-4 is an example ofa fault isolation index for AC electrical loaddistribution, for an AC crosstie bus failure.

The Fault Isolation Manual is written for useby experienced technicians and contains trou-bleshooting trees needed to isolate systemproblems to the LRU level. Fault isolation isused by maintenance personnel to locate anddetermine the cause of any particular mainte-nance malfunctions and the possible solution.

NOTES




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ELECTRICAL POWER SOURCE

Aircraft: 5001-9999

1A

1C

1D1E

2A

2A

2B

2D 4E

4D

4C

4B

4A 5A

5B

5C

5E 6E

6C

6B

6A 7A

7B

7C

7E

8D

8C

8B

8A 9A

9B

9C

9D

9E

10A

10B

10C

10D

10E

11A

11B

11C

11D

11E

12A

12B

12C

12D

12E

14A

14B

14C14E

14D

14F

14K

14J

14H

8E

7D5D 6D

3E3D

3C

3B

3A1F

1G

2C

Detail C

LEFT ELECTRONICEQUIPMENT RACK (LEER)

REF DES NOMENCLATUREa) LEER-G11 APU GCU PWR c/bb) LEER-G16 L GCU PWR c/bc) 031A5 Left Bus Power Control Unitd) 031A4 Left Generator Control Unite) 155A1 Modular Avionics Unit #1

A9+10 Dual Generic I/O 1 Modulef) 035A1 Left Power Distribution Boxg) 181K6EL APU Ready to Load Relay

(347 Pnl)

Detail A

COCKPIT OVERHEAD PANEL(COP)

REF DES NOMENCLATUREa) 031DS1 APU Generator Switchb) 031DS2 Right Generator Switchc) 031DS3 Left Generator Switch

RIGHT ELECTRONICEQUIPMENT RACK (REER)

REF DES NOMENCLATUREa) REER-C27 R GCU PWR c/bb) 140A1 Annun Lights Dim & Test Boxc) 155A2 Modular Avionics Unit #2

A7+8 Dual Generic I/O 2 Moduled) 031A1 APU Generator Control Unite) 031A2 Right Generator Control Unitf) 031A3 Right Bus Power Control Unitg) 035A2 Right Power Distribution Box

Detail D

PEDESTAL AREA

REF DES NOMENCLATUREa) 053S1 Left Fire Handle Switchb) 053S2 Right Fire Handle Switchc) 292DS5 Left Fuel Shutoff Switchd) 292DS6 Right Fuel Shutoff Switch

Detail B

RIGHT ENGINE

REF DES NOMENCLATUREa) 031G2 Right Integrated Drive Generator

Detail HRIGHT MAIN WHEEL STRUT

REF DES NOMENCLATUREa) 112S2 Right Main Gear Downlock Sw

Detail F

Detail E

LEFT MAIN WHEEL STRUT

REF DES NOMENCLATUREa) 112S1 Left Main Gear WOW Switch

Detail I

APU ENCLOSURE (TAIL)REF DES NOMENCLATURE

a) 031G3 APU Generator

Detail G

LEFT ENGINE

REF DES NOMENCLATUREa) 031G1 Left Integrated Drive Generator

WIRING DIAGRAM

Equipment Locator

24-00-00Figure 1, Sheet 1 of 1

Figure 2-5. Equipment Locator Example (System-Referenced)

WIRING DIAGRAMMANUALGENERALMany factors have influenced the design ofthe Gulfstream G500/G550 Aircraft WiringManual, among them page size, system com-plexity, and system design.The requirementto provide the maintenance technician withan efficient and precise set of informationaltools resulted in an electrical system pre-sentation unlike any that Gulfstream has pre-sented in the past. This manual is formattedto ATA 100 specifications and provides de-tailed illustrations of the aircraft electricalsystems and how they interface with other air-craft systems.

The purpose of the Gulfstream G500/G550Aircraft Wiring Manual is to provide all the air-craft systems wiring information needed toperform troubleshooting, fault isolation of theelectrical circuits and the repair of specificelectrical systems and components. The com-plexity of Gulfstream G500/G550 electri-c a l / av ion i c s sy s t ems ha s p romp tednon-conventional methods of presentation.Systems are represented in four complemen-tary drawing types:

1. Equipment Locator2 Schematic Diagram3. Wire List4. Te r m i n a t i o n L i s t ( r e p r e s e n t e d i n

Chapter 91)Each of these drawing types is designed toprovide the maintenance technician with in-formation essential to maintain the wiring andcomponent integrity of the aircraft systems.

All drawing types contained within the wiringmanual are designed for ease of use and un-derstanding. Symbology is included to clearlyindicate the logic states (ON/OFF, ener-gized/de-energized, etc) and the intercon-nections of all included systems. Refer to theillustrations through the remainder of this sec-tion for specific examples.

EQUIPMENT LOCATORThe equipment locators (EL) are designed toprovide navigation to component locationsthroughout the aircraft. The locator indicatesan approximate area, such as cockpit overheador tail compartment. Equipment locators fallinto two general categories: system-referencedand aircraft assembly-referenced.

System-ReferencedThe system-referenced equipment locators(Figure 2-5) precede system schematics. Theylist those components, which by virtue of theirreference designation and function are es-sential components of the system. Also con-ta ined on the sys tem- leve l loca tors a rereferences and general locations of separatesystem major components, which interfacewith the system being presented. An often-in-cluded example is the Annunciator Lights Dimand Test Box, which appears on the locator ofeach system providing input to, or receivingoutput from, this component (most systemdrawings are of this category).




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Figure 2-6. Equipment Locator Example (Aircraft Assembly-Referenced)

1) Left Junction and RelayPanel 347A1

LEFT JUNCTION AND RELAYPANELS

Aircraft: 5001-9999

WIRING DIAGRAM

Equipment Locator


Aircraft Assembly-ReferencedAircraft assembly-referenced equipment lo-cators (Figure 2-6) include all junctions andconnections, which are not specific to any onesystem. Aircraft interconnections are refer-enced by the junction/relay panel or connec-tor cluster into which they are installed. Allassembly-referenced equipment locators arelocated in Chapter 91 of the GulfstreamG500/G550 Aircraft Wiring Manual.

Panel Assembly EquipmentLocatorThe panel assembly locator serves to providea visual presentation of panel components andconnectors. Components such as relays whichhave a system designation are identified bynomenclature and the drawing(s) upon whichthey appear. Full reference designation is pro-vided for those components whose decal doesnot provide such. Schematic diagrams and theelectrical equipment list do not include therelay socket designation X which is insertedin the relay reference designation.

Example:

032K3 = Relay032XK3 = Relay Socket

NOTES




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1) Left Battery Bus Control2) Battery Contactor #13) Left Battery Charger4) Left Battery

DC POWER SOURCE

Aircraft: 5001-9999

D

E1P127-00

FP128-00

35

+

-

032K1 Loc: 385A1

BATTERYCONTACTOR #1

1P119-22

1P118-22N

13111715141620182119

1P116-22N

1P330-221P108-20/221P109-22/24

P112-22P114-22

P111-22P113-22

1P110-221P117-22N

A

A

A

A

1

3

42

5781011131416

L MAIN BATTSWITCH

032DS1 Loc: COP

ON

W154-22

1P156-22

P143-20

From 33-11-00ANNUNCIATOR LIGHTS

P1CTESTDIM

CH 122

O/GNDO/GND

140A1P1C39

64ANNUN LTS DIM & TEST

1P110-22

1P153-20/22P146-20

1P154-20N

P82-20

P101-22

Q182-20

1P151-22/24

140A1 Loc: REER

OFF

ON318A1E5C

5

L BATT CONTLEER - G15

L BATT BUS ATo 24-60-00

DC PWR DISTP82-16

3

L BATT CHGR CONTLEER - J14

L ESS 28 VDCTo 24-60-00

DC PWR DISTP101-22

385A1E1A

D

E

F

G

032K7 Loc: 385A1

L BATT CHGRCONTACTOR

P102-10

385A1E1A

385A1E3C

LEFT BATTERY

POS

NEG

1P127-00

1P140-00N

032BT1

E4159A

98

12

11THERMISTOR

OVERTEMPSWITCH

1P132-20 (WHT)

1P131-20 (BLU)1P129-20

1P130-20

FAIL ANNUN OUT

CHGR MODE CONT

GROUND

THERMISTOR INPUT

THERMISTOR RETURN

OVERTEMP SWITCH

OVERTEMP SWITCH RTN

L BATTERY CHARGER032BC1 Loc: Tail

POS

NEG1P124-8BATT CHARGER OUTPUT +

ON

546

111012P82-20 P143-20

P145-22/24 P143-20OFF

032S1EXTERNAL BATTERY SWITCH

Loc: RadomeP82-16

035A1P1A5

T3

T4

18

L POWER DISTRIBUTION BOX

P114-20/22

P234-22 (WHT)P235-22 (BLU)

R POWER DISTRIBUTION BOX

P123-00

P128-00

15E

15F LEDBC AUX

LEDBC AUX RTN

LEFT BUS POWERCONTROL UNIT

031A5P1A

031A5 Loc: LEER

C1C2C3

181K2APU PILOT RELAY

Loc: 381A1 (Ref: 49-60-00)

P143-20 1P119-20

APU STARTERNOT ENGAGED

APU STARTERENGAGED

A1A2

A3

085K3AUX HYD PUMP CONT RELAY #1

Loc: 381A1 (Ref: 29-21-00)

P143-20 P144-20

PUMP OFF

PUMP ON

G H J

35

+

-

1P153-20/22

1P121-22N

1921 1P115-22N

1P330-22

385A1E3C

385A1E1A

032K7P1

X2Y1

X1

A2A1

A3

032K5L BATT CONTROL

RELAYLoc: 347A1P144-22

P322-20NP82-16

P82-16 1P119-16/20

1211

312

98

Loc: Tail

1P134-20N

1P135-22/24

1P108-20/22

1P132-20 (WHT)1P131-20 (BLU)

1P129-20

1P130-20

X1

X2

P143-20

P120-20N 032K3L BATT BUSB RELAY

Loc: 347A1

P107-12

1P108-20/22

347A1E3A

1P330-22

10 P96-14LEFT BAT BUS A

385 PNL (Tail)

15 P97-12LEFT BAT BUS B

385 PNL (Tail)

A1A2A3

347A1E3A

To 24-60-00DC POWER

DISTRIBUTION

AF

BG

AF

BG

P81-20

P88-20

P87-20

P80-20 P112-20

P112-20

P111-20

P111-20

385TJ1B

385TJ1C

3

3

L ESS DC CONT #1PILOT - G7L BAT BUS BTo 24-60-00

DC PWR DISTL ESS DC CONT #2

COPILOT - G7R BAT BUS BTo 24-60-00

DC PWR DIST R ESS DC CONT #1COPILOT - G8

L BAT BUS BTo 24-60-00

DC PWR DIST

R ESS DC CONT #2PILOT - G8

1713

1511

032K2P1032K2P1

032K2

BATTERYCONTACTOR #2

RELAXED

ENERGIZED

P112-22

P111-22

J C F

032BT1P2

6

4

Q182-22

381TJ1KLoc: Tail

385TJ1LLoc: TAIL

032K1P1

SHEET 6BATT TIE BUSLoc: 385A1

SHEET 6

032BC1P1

P143-20

032BT1P1

C

P143-20

A

B

H

H

GA

FBATT CHARGER OUTPUT -

155A1A10P4155A1A10P4E1

14EXT BATT SW ON

29LEFT BATT SW OFF

1P109-22/24

1P135-22/24

035A1P1B6035A2 Loc: REER

A2

DUAL GENERIC I/O 1155A1A9+10Loc: LEER155A1

27L BATT CHARGER FAIL

28L BATT CONTACTOR STAT

P113-22P114-22

A3

B6

P143-22

P144-22

035A1P1A6

P143-22

P111-22

P143-20

P113-20

035A2P1A5

23P113-20

24

23

P144-20

P143-20

035A2P1A6

16P199-20NE2166A

035A2P1A5 REDCBR ESS DC

Battery BusContactor

A1+

A9-

12NC3

REDXC

21NC1

REDC

12NC1

12NC2

RELAXED

T2P123-00

035A2P1A5

2520

P279-22 (WHT)P280-22 (BLU)

12NC4

R ESSDC BUS A1 A2

A1P167-20NE2165A

035A1 Loc: LEER

LEDCBL ESS DC

BatteryContactor

12NC4

LEDCLEDXC RELAXED

ENERGIZED

A1+

A9-

A2 A1L ESS

DC BUS

P143-20

21

NC2

21NC1

12NC1

12NC3

ENERGIZED

C

G

1

1

2 Q182-20

MAU

1PROC2

PS1B

PS 1ACH A

PS 1BCH B

To 24-60-00DC POWER

DISTRIBUTION

035A1P1B6

3

3

6

9

12

15

Loc: 385A1

Loc: 385A1

AD C B

HALL EFFECTSENSOR

032HE7P1

032HE7

SHEET 7F

P133-20

H797-20

H797-20FROM 49-60-00

APU CONTROL28 VDC FROM APU CONT #1AND/OR APU CONT #2 WHENSTARTER ENGAGED SIGNAL IS

OUTPUT BY APU ECU385TJ1C

EKP133-20 2Q182-20

Loc: 385A1

H797-20

P133-20 D

SHEET 6E

SHEET 6

P133-20

CB369

CB368

E4121D

1P125-8N E4120A

FROM 29-21-00AUXILIARY HYDRAULIC

PUMP CONTROL28 VDC WHEN AUXILIARYHYDRAULIC PUMP IS ON

15E15F REDBC AUX

REDBC AUX RTN

RIGHT BUS POWERCONTROL UNIT

031A3P1A

031A3 Loc: REER

P112-22

L M K

385TJ1LLoc: TAIL

To 49-60-00APU CONTROL

WIRING DIAGRAM

Schematic


Figure 2-7. Schematic Diagram Example

SCHEMATIC DIAGRAMSSchematic diagrams (Figure 2-7) represent allGulfstream G500/G550 systems. The schemat-ics are designed to functionally describe the sys-tems wi th a min imum of o ff - shee t o roff-drawing reference. Entire circuits are re-peated on different system drawings when cir-cuit function and operation is significant tomore than one system.

The schematic diagrams are designed to beused in conjunction with their respective wirelists. Schematics do not show the wires seg-ment letters. These are found on the wire listsonly. Schematics function primarily to performinitial system troubleshooting, though in manycases they will be all that is necessary to faultisolate the system. Due to the compact natureof the system schematics, they are also highlyeffective teaching aids.

The schematics depict all active components(switches, relays, circuit breakers, etc.) withinthe subject system (Figure 2-8). All terminaljunctions are also illustrated. With the excep-tion of vendor-supplied disconnects and cables,no aircraft assembly-referenced connectorsare shown. Aircraft assembly connectors arepurposely omitted so that entire system func-tions can be shown on a single sheet.

All G500/G550 Wiring Manual schematic cir-cuits and relays are shown in the de-energized(relaxed) state. Annunciator switches are de-picted in the extended position. Toggle typeswitches are shown in the OFF position. Three-position switches are ordinarily shown in thecenter-resting position.




L BATT BUS ATO: 24-60-00

DC PWR DIST

L BATT CONTLEER-G15

5

G TO SHEET 6032BT2P2-4TO SHEET 5032BT1P2-4

All circuit breakers presented indicate the electrical bus which provides primary power and the source's system drawing. All circuit breakers are presented with the names as they appear on the circuit breaker panel, the circuit breaker panel name, and the grid location of the circuit breaker.

CIRCUIT BREAKERS

Relays may be depicted in several alignments, thought their logic (de-energized, relaxed) remains constant throughout the schematics. Energized and de-energized coil and contact logic states (on/off, air/gnd, etc.) are included to minimize the need to consult other drawings.When partial relays are shown, as is the case with relay 181K2A above, the system schematic number for the relay is indicated.

RELAYS

On-sheet references are sometimes used to reduce the clutter of wires on complex drawings. The on-sheet reference is a triangular figure with a number in it. The corresponding, matching reference is the same shape and number. The point of the triangle always points in the direction of the matching reference.

Off-drawing references point to another system drawing. These references include, at a minimum, the drawing ATA designation and name of the system.If the referenced wire provides logic to the circuit being depicted, a text block will explain the source of the signal and what controls the logic states. Ann Lts Pwr and Warn Lts Pwr references include circuit breaker and location. The majority of off-drawing references include the system ATA and sheet number of the corresponding drawing.

Off-sheet references are indicated by this symbol. The continuation of the signal path on the indicated sheet is the same symbol and letter.

ON-SHEET, OFF-SHEET & OFF-DRAWING REFERENCES

1 TO; 032K1P1-20(THIS SHEET) 1TO: 105A3P1A-15

(THIS SHEET)

H797-20

FROM 181K2-D1 (APU PILOT RELAY): 28VDCFROM APU CONT NO. 1 AND/OR APU CONT NO. 2

WHEN STARTER ENGAGED SIGNAL IS OUTPUT BYTHE APU ECU (SEE 49-80-00): APU CONTROL

X1

X2P120-20N

P143-20

P37-12 A1

A3 A2

032K3RL BATT BUS

B RELAYLOC: 347A1

P107-12

APU STARTERNOT ENGAGED

APU STARTERENGAGED

C3C1C2

181K2AAPU PILOT RELAY

LOC: 381A1 (REF: 49-60-00)

G

Figure 2-8. Schematic Symbols




328CB354-2 2F15A22 2 2F15B22 30-30-00 328CB11-2 L230A20 3 L230B20 33-30-00 328CB50-2 G50A20 4 5G0B20 32-50-00 328CB280-2 P33A22 5 P33B22 24-40-00 328CB262-2 2F27A20 7 2F27B20 30-30-00 328CB296-2 F10A22 8 F10B22 30-30-00 328CB34-2 2H177A20 9 2H177AB20 21-60-00 328CB335-2 2C44A20 10 2C44B20 27-50-00 328CB333-2 1C44A20 11 1C44B20 27-50-00 328CB332-2 C48A20 12 C48B20 27-50-00 328CB328-2 W172A22 13 W172B22 31-50-00 328CB326-2 W170A22 14 W170B22 31-51-00 328CB24-2 2SA2A20 16 2SA2820 34-43-00 328CB306-2 E104A22 17 E104B22 77-31-00 328CB198-2 1E20A22 18 1E20B22 28-40-00 328CB197-2 1E21A22 19 1E21B22 28-40-00 328CB73-2 W140A22 20 W140B22 52-70-00 328CB277-2 2X238B22(WHT) 21 2X238C22(WHT) 24-20-00 328CB278-2 2X239B22(BLU) 22 2X239C22(BLU) 24-20-00 328CB279-2 2X240B22(ORN) 23 2X240C22(ORN) 24-20-00 328A1E3B 2X241B22(GRN) 24 2X241C22(GRN) 24-20-00 328CB340-2 FD59A22 25 FD59B22 31-60-00 328CB20-2 2L90A22 26 2L90B22 31-41-00 328CB321-2 2E20A22 27 2E20B22 28-40-00 328CB320-2 2E21A22 28 2E21B22 28-40-00 328CB323-2 2Q280A22 29 2Q280AB20 28-26-00 328CB365-2 FR51A22(WHT)

30 2Q281AB20 28-26-00

328C B315-2 2Q281A20 FR52B22(WHT) 31-31-00

Wire No.From To

Item Item Ref ATAPinNo.

Figure 2-10. Termination List Example

X9A20 SOCKET 040XKT A2 STUD, GND E4018E NOPIN 5001-99991P108A22 CONN, PLUG 032K1P1 16 CONN, RCPT 385A1J1 D* 5001-9999 1P108B20 CONN, PLUG 032BC1P1 8 CONN, PLUG 385A1P1 * 5001-9999 1P109A22 CONN, PLUG 032K1P1 20 CONN, RCPT 385A1J1 C* 5001-9999 1P109B22 CONN, PLUG 385A1P1 C* CONN, PLUG 4000P9 35 5001-9999 1P109C22 CONN, PLUG 2000P9 35 CONN, RCPT 4000J9 35 5001-9999 1P109D22 CONN, RCPT 2000J9 35 CONN, PLUG 331A1P35 10 5001-9999 1P109E24 CONN, PLUG 155A1A10P4 28 CONN, RCPT 331A1J35 10 5001-9999

Wire Number Effectivity RemarksFrom

Item Ref Des. Pin No.

From CableNumberItem Ref Des. Pin No.

Figure 2-9. Wire List Example

WIRE LISTSEach individual wire belonging to a systemis found on the wire list. The graphical point-to-point wire list displays the source, all in-te r im d isconnec ts (connec tors ) and thedestination. All junctions (splices and termi-nal junction modules) are also shown. Twistedor twisted-shielded wires are indicated by spe-cific symbols, and the cable name (i.e., 2/203,3S1, etc.) is provided for each segment. Allcomponents which terminate a wire are shown,with the components reference designationand nomenclature clearly indicated. Figure2-9 provides a sample wire list.

TERMINATION LISTSThe termination lists (Figure 2-10) graphicallydepict wire connections for connector and panelassembly components. Wires that terminate atinterim or panel assembly-designated connec-tions are found in Chapter 91 of the GulfstreamG500/G550 Aircraft Wiring Manual.

ADDITIONALPUBLICATIONSAs an aid to the Aircraft Maintenance Manual,Gulfstream Aerospace also publishes otherdocumentation.

ILLUSTRATED PARTSCATALOGThe Illustrated Parts Catalog provides a picto-rial/part number breakdown of the aircraft andground support equipment. The Illustrated PartsCatalog is the only approved part number list-ing for the aircraft. Part effectivity is providedvia aircraft serial number ranges or by notes atthe bottom of the particular parts list page.

Maintenance technicians use the IllustratedParts Catalog to locate and determine theproper part number when replacing and/or in-specting hardware and components. TheIllustrated Parts Catalog can also be used inconjunction with the AMM system descrip-tions to better understand a particular system.

OPERATING MANUALThe purpose of the Operating Manual is to pro-vide the flight crew with the aircrafts neces-sa ry opera t ing l imi ta t ions , p rocedures ,performance, and systems information re-quired for safe and efficient operation..

The Operating Manual serves as a compre-hensive reference for use during transitionand recurrency training and proficiency checkson the aircraft. The manual provides necessaryoperational data from the FAA-approvedGulfs tream G500/G550 Airplane Fl ightManual and standardized procedures and prac-t i c e s t o enhance a i rp l ane ope ra t i on .Maintenance technicians use the OperatingManual for engine run-up and taxi operations.

AIRPLANE FLIGHT MANUALThe Gulfstream G500/G550 Airplane FlightManual (AFM) serves as a comprehensive ref-erence for all flight operations. The AFM pro-vides operators with numbered sections thatcontain limitations, procedures, and perfor-mance data for the aircraft and aircraft systems.

All performance limitations and informationlisted are in compliance with FAA regula-tions, Part 25, and must be on board the air-craft for all flight operations.

STRUCTURAL REPAIRMANUALThe Structural Repair Manual provides in-formation for general repairs of simple andcommon structural components, repair mate-rials, and their specifications and processes.

The Structural Repair Manual includes gen-eral repair procedures that must be performedconcurrently with structural repairs (such assheet metal forming, fastener installation, cor-rosion treatment, and sealing), along with re-quired skin thickness diagrams, detailedillustrations, and part number identification.




WEIGHT AND BALANCEMANUALThe purpose of the aircraft Weight and BalanceManual is to provide the operator with guide-lines to ensure that the maximum weight andcenter-of-gravity limits are not exceeded dur-ing operation.

The Weight and Balance Manual providesweight and balance data, loading graphs andCG envelopes, manufacturers bare emptyweight, operating gross weight (in pounds),typical loading summary, outfitting weightallowance, and aircraft weighing procedures.

MASTER MINIMUMEQUIPMENT LISTThe Mas t e r Min imum Equ ipmen t L i s t(MMEL) is initiated by Gulfstream on theirequipment and the number of components al-lowed to be inoperative to release an aircraftfor fl ight operations. All manufacturersMMELs are approved by the FAA, per the op-erating FAR.

The maintenance activity then reviews theMMEL and submits a Minimum EquipmentList (MEL) to the local FSDO for approval. TheMEL then becomes a legal means to release theaircraft with an inoperative system or compo-nent. The MEL must remain with the aircraftat all times and will include instructions on itsuse by the maintenance technicians.

The Maintenance Operational Placarding(MOP) procedures manual is a supplement tothe MEL that contains maintenance, opera-tional, and placarding procedures. The MMELfrom the aircraft manufacturer provides guide-lines for operators to develop an individual air-craft MEL.

NOTEThe MEL is intended to permit safeaircraft operation with inoperativeitems for a period of time until repairscan be accomplished. Absolute com-pliance is required.

CONFIGURATION DEVIATIONLISTThe Configuration Deviation List (CDL) al-lows the aircraft to maintain safe flight oper-ations without certain parts, as listed. TheCDL provides an additional certification lim-itations listing of the type and number of com-ponents allowed to be inoperative for safeflight operations and lists required placardingand logbook entry information for mainte-nance technicians and aircrews when operat-ing under CDL limitations.

The CDL is used to determine operating lim-itations due to missing or removed aircraftequipment and imposes performance penaltieson the aircraft. The CDL does not includeparts which do not affect the airworthiness ofthe aircraft and is based on the aircrafts con-figuration as originally manufactured.

NOTEAll Configuration Deviation Listpenalties and limitations are ap-proved by the FAA and must be fol-l owed when ope ra t i ng w i th aconfiguration deviation. The CDL isl oca t ed i n Append ix B o f t heGulfstream G500/G550 AirplaneFlight Manual.




OPERATORCOMMUNICATIONSThe purpose of Gulfstream G500/G550 oper-a to r communica t ions i s fo r Gul f s t reamAerospace Corporation to provide continu-ous written communication with Gulfstreamaircraft operators concerning aircraft main-tenance and operations. Operator communi-cations are relayed via the following:

Service News Maintenance and Operations Letters Service Bulletins Gulfstream Intercom

Service News provides general service news,information on improved parts, and operatorexperiences.

Maintenance and Operations Letters providegeneral information and items of interest con-cerning the aircraft.

Service Bulletins provide aircraft feature or de-sign changes, incorporating a statement ofimportance, inspection requirements, main-tenance not covered in maintenance manuals,a strict time compliance, and timely informa-tion of major importance. Response to aService Bulletin is accomplished via a ServiceReply Card.

Gulfstream Intercom (provided on websitewww.Gulfstream.com) provides a weekly com-munication of topics to Gulfstream owners, op-erators, and employees and include currentevents, upcoming events, and technical up-dates.

NOTEThe technical content of operatorcommunications is for informationonly and is not to be used in the main-tenance or service of any Gulfstreamaircraft.

The application of operator communicationsenables operators and maintenance techni-cians to maintain the aircraft to the latestGulfstream-suggested configuration, contin-ually improve maintenance practices, and re-duce maintenance downtime.

NOTES




5-i

CHAPTER 512AIRCRAFT GENERAL

CONTENTSCHAPTER 5 ............................................................................................................................ 5-1

INTRODUCTION ................................................................................................................... 5-1

GENERAL............................................................................................................................... 5-1

DESIGN CHARACTERISTICS ............................................................................................. 5-2

Aircraft Performance..........................................................................................................5-2

G500 Aircraft Weights ..................................................................................................... 5-2

G550 Aircraft Weights ..................................................................................................... 5-2

Cabin Standards ............................................................................................................... 5-3

Differences from Previous Gulfstream Aircraft............................................................... 5-7

AIRCRAFT SYSTEMS........................................................................................................... 5-9

Airframe Innovations ....................................................................................................... 5-9

Engines............................................................................................................................. 5-9

Auxiliary Power Unit ..................................................................................................... 5-11

Hydraulics...................................................................................................................... 5-13

Flight Controls....................................................................................................................... 5-13

Landing Gear ................................................................................................................. 5-13

Environmental Control System...................................................................................... 5-15

Fuel System.................................................................................................................... 5-15

Electrical Power ............................................................................................................. 5-17

G500/G550 Avionics Equipment Functions .................................................................. 5-19

AIRCRAFT PLACARDS...................................................................................................... 5-21

General........................................................................................................................... 5-21

Caution and Warning Placards....................................................................................... 5-21




Instruction and Information Placards............................................................................. 5-21

Locator Placards ............................................................................................................ 5-21CHAPTER 12SERVICING............................................................................................... 12-1INTRODUCTION ................................................................................................................. 12-1GENERAL ............................................................................................................................ 12-1JACKING, LIFTING, AND SHORING ............................................................................... 12-3

Operational Requirements ............................................................................................. 12-3Individual Nose and Main Gear Jacking........................................................................ 12-5Fuselage Jacking ............................................................................................................ 12-7Lifting and Shoring........................................................................................................ 12-9

PARKING, STORAGE, AND MOORING ........................................................................ 12-11Parking Procedures ...................................................................................................... 12-11Storage ......................................................................................................................... 12-13Mooring ....................................................................................................................... 12-15

LEVELING AND WEIGHING .......................................................................................... 12-17Leveling ....................................................................................................................... 12-17Weighing...................................................................................................................... 12-19

TOWING............................................................................................................................. 12-19SERVICING........................................................................................................................ 12-25

Fuel System Servicing ................................................................................................. 12-25Oil System Servicing .................................................................................................. 12-27Hydraulic System Servicing ........................................................................................ 12-35Pneumatic System Servicing ....................................................................................... 12-39Oxygen System Servicing ........................................................................................... 12-43Anti-Icing/Deicing....................................................................................................... 12-44Aircraft Washing.......................................................................................................... 12-45

5-ii FOR TRAINING PURPOSES ONLY



5-iii

ILLUSTRATIONSFigure Title Page5-1 Aircraft Dimensions ................................................................................................. 5-4

5-2 Emergency Exits....................................................................................................... 5-6

5-3 Rolls-Royce Deutschland BR710 Engine ................................................................ 5-8

5-4 Engine Instrument Displays ..................................................................................... 5-9

5-5 Auxiliary Power Unit ............................................................................................. 5-10

5-6 APU Synoptic Page............................................................................................... 5-11

5-7 2/3 Hydraulic Synoptic Page.................................................................................. 5-12

5-8 Flight Control Locations ........................................................................................ 5-12

5-9 Flight Control Synoptic Page ................................................................................. 5-13

5-10 ECS/PRESS Synoptic Page.................................................................................... 5-14

5-11 Fuel System Synoptic Page.................................................................................... 5-14

5-12 Gulfstream G500/G550 Electrical Schematic........................................................ 5-16

5-13 AC and DC Synoptic Pages.................................................................................... 5-17

5-14 PlaneView System Overview ................................................................................. 5-18

5-15 Flight Displays ....................................................................................................... 5-19

5-16 Locator PlacardEmergency Window Exits ........................................................ 5-20

12-1 Aircraft Jacking...................................................................................................... 12-2

12-2 Axle Jack Provisions .............................................................................................. 12-4

12-3 Main Landing Gear With Jack Adapter ................................................................. 12-5

12-4 Fuselage Jack Point Locations ............................................................................... 12-6

12-5 Locations of Pneumatic Bags and Stabilizing Line Attachments .......................... 12-8

12-6 Landing Gear Pins................................................................................................ 12-10

12-7 Protective Covers ................................................................................................. 12-12




12-8 Tire Covers........................................................................................................... 12-13

12-9 Battery Disconnect............................................................................................... 12-13

12-10 Mooring Rings ..................................................................................................... 12-14

12-11 Longitudinal Leveling Brackets........................................................................... 12-16

12-12 Lateral Leveling Brackets .................................................................................... 12-17

12-13 Torque Link Disconnect....................................................................................... 12-18

12-14 Nose Strut Extension............................................................................................ 12-20

12-15 Nosewheel Steering Collar................................................................................... 12-21

12-16 Nose Wheel Well Parking Brake Accumulator Gage .......................................... 12-22

12-17 Tow Bar Attachment ............................................................................................ 12-23

12-18 Single-Point Pressure Refueling .......................................................................... 12-24

12-19 Overwing Fueling ................................................................................................ 12-24

12-20 Ground Service Control Panel ............................................................................ 12-26

12-21 Engine Oil Tank Location .................................................................................... 12-26

12-22 Oil Tank Sight Gage............................................................................................. 12-28

12-23 APU Gearbox....................................................................................................... 12-28

12-24 Remote Oil Replenishment System ..................................................................... 12-30

12-25 Air Turbine Starter ............................................................................................... 12-32

12-26 Hydraulic System Schematic ............................................................................... 12-34

12-27 Hydraulic Reservoir ............................................................................................. 12-35

12-28 Remote Hydraulic Replenishing System ............................................................. 12-36

12-29 Landing Gear Strut Filler Valves ......................................................................... 12-38

12-30 Emergency Extension Blowdown Bottles............................................................ 12-40

12-31 Oxygen Service Panel .......................................................................................... 12-42

5-iv FOR TRAINING PURPOSES ONLY



INTRODUCTIONThis training manual presents a description of the major airframe systems and enginesinstalled on the Gulfstream G500/G550 aircraft. The information contained herein is in-tended only as an instructional aid. This material does not supersede, nor is it meant asa substitute for, any of the manufacturers operating manuals. The material presentedhas been prepared from the basic design data. All subsequent changes in aircraft appearanceor system operation will be covered during academic training and subsequent revisionsto this manual.

GENERALThe Gulfstream G500/G550 is a low-wing,twin fan-jet, pressurized transport categoryairplane, specifically designed for all-weatheroperations and certified to fly at altitudes upto 51,000 feet.

The minimum crew required is a pilot and copi-lot.

Many aircraft systems and standards, alongwith their effect on aircraft performance, areunique to the Gulfstream G500/G550.

This chapter describes the design character-istics of the Gulfstream G500/G550 aircraftand identifies the major aircraft systems, air-craft placards, interior furnishings and equip-ment, and outfitting options. It covers materialfrom the following ATA chapters:

6Dimensions and Areas

11Placards and Markings

25Equipment/Furnishings

CHAPTER 5AIRCRAFT GENERAL




DESIGNCHARACTERISTICSThe mission for which the Gulfstream G550is designed is to provide executive travelerswith the longest-range non-stop capabilityavailable.

AIRCRAFT PERFORMANCEThe Gulfstream G550 has been designed to arange specification of 6,750 nm. This criteriondictated fuselage size, wing, engines, fuel ca-pacity, and weight.The normal cruising speedof the Gulfstream G550 is 459 knots true air-speed (KTAS)/0.80 Mach, which is also thelong-range cruise airspeed. Initial cruisingaltitude is 41,000 feet and will be achieved in21 minutes. Maximum cruising speed is 499KTAS (maximum operating Mach 0.885).Maximum cruising altitude is 51,000 feet witha climb rate of 4,188 fpm, and total flight timeis approximately 14 hours. This is based onmaintaining 0.80 Mach, 99% Boeing stan-dardized winds, and ATC airway routing. Withthe aircraft at 51,000 feet, the cabin altitudewould be equivalent to 6,000 feet (1,829 me-ters) with 10.17 psid.

G550 AIRCRAFT WEIGHTS Ma x imum r am p91 , 400 l b s

(41,458 kg) (Allows 400 lbs of fuel forengine run-up and taxi)

Max imum t akeo ff91 ,000 l b s(41,277 kg)

Ma x imum l and ing75 , 300 l b s(34,227 kg)

Maximum zero fue l54,500 lbs(24,721 kg) (Maximum allowable weightof a loaded aircraft without fuel).

The basic operating weight of the GulfstreamG550 includes the manufacturers bare emptyweight and the typical operating items listedbelow:

Flight crewthree (3) at 170 lbs each = 510Flight attendantone (1) at 170 lbs = 170Crew baggagefour (4) at 30 lbs = 120Engine oil = ........................................123Unusable/Undrainable fuel ................189Supplies ................................................688

Maximum payload for the Gulfstream G550with maximum fuel on board is 1,600 lbs (727kg), including passengers (8) and baggage.The maximum useable fuel weight for theGulfstream G550 is 41,300 lbs (18,773 kg).




CABIN STANDARDS SeatsAll passenger compartment seats must meetregulatory requirements. The maximum num-ber of passengers the Gulfstream G500/G550can carry is 19 (13 is typical). All seats are se-cured to the aircraft structure, have three pointrestraints, and may be configured as follows:

Single forward facing seats are designedto meet a 16-g requirement. Seats havevarious levels of foam options (soft tofirm) and various seat coverings fromwhich to choose. Side facing seats mustalso meet a 16-g requirement. Seat beltsare lever or push-button release type.

Double seats are available with the samestandards as the single seats.

Triple (divan) style seats 37 to 39 incheswide are available and include stowageunderneath.

NOTES







96.40 ft

25.86 ft

35.17 ft

93.45 ft

Figure 5-1. Aircraft Dimensions

Interior Dimensions andCapacitiesCabin length .................. 43 ft 11 in. (13.4 m)Cabin height ...................... 6 ft 2 in. (1.9 m)Cabin width ........................ 7 ft 4 in. (2.2 m)Cabin volume .......... 1,669 cu ft (47.3 cu m)Baggage compartmentlength .................................... 6 ft 2 in. (1.9 m)Baggage compartmentvolume ............................ 226 cu ft (6.4 cu m)Baggage compartment capacity .......................... 2,500 lb (1,134 kg)

Exterior DimensionsWing span ........................ 93 ft 6 in. (28.5 m)Wing area (each wing) .............. 1,136.5 sq ftHeight (top of verticalstabilizer to ground) ...... 25 ft 10 in. (7.9 m)Horizontalstabilizer span .............. 35 ft 2 in. (10.72 m)Horizontal stabilizer area ...... 260.85 sq ft (24.23 sq m) Total length(tip of nose to end ofhorizontal stabilizer) .... 96 ft 5 in. (29.4 m)Fuselage stations (FS) represent edges of ver-tical planes perpendicular to the horizontalreference plane and show measurement oflength along the longitudinal (X) axis. Thestations locate points along the fuselage fromFS 0.00 located 4 inches aft of the forward tipof the nose radome (Figure 5-1).

NOTES







ENTRANCE DOOR

EMERGENCY ESCAPEWINDOWS (2 PER SIDE)

EXTERNALBAGGAGECOMPARTMENTDOOR

PRIMARY ESCAPE ROUTES

SECONDARY ESCAPE ROUTES TO BE USEDONLY ON INSTRUCTIONS FROM FLIGHT CREW

Figure 5-2. Emergency Exits

DIFFERENCES FROM PREVIOUSGULFSTREAM AIRCRAFTDatum LineThe datum line is an imaginary vertical planefrom which all horizontal measurements aretaken. On the Gulfstream G500/G550 aircraftthe datum line is located at FS 4.00. Thismeans that the datum line is located 4 inchesin front of the tip of the nose radome, whichis FS 0.00.

Water Line (WL)The water lines represent edges of planes par-allel to the horizontal reference plane. Thisplane is parallel to the fuselage centerline andlocates points, components, and distancesabove a theoretical datum line (WL 0.00). Forthe Gulfstream V, WL 0.00 is 100 inches belowthe centerline of the fuselage datum.

Buttock (Butt) Line (BL)The butt line shows measurement of width tothe left and right of the aircraft centerline.Measurements, in inches, to the left of BL0.00 are designated left buttock line (LBL), andmeasurements to the right of BL 0.00 are des-ignated right buttock line (RBL). Wing stationsrepresent planes perpendicular to the wingreference plane and parallel to the fuselagecenterline and are measured from WS 50.00(FS 397.513 BL 0.00 WL 39.982) to WS531.000 (BL 531.000).

DoorsThe baggage compartment door is a 40 x 36-inch plug-type door on the left side of the air-plane. The main entrance door is a 36 x 60-inchpassenger entrance door. An unpressurizedtail compartment houses the auxiliary powerunit (APU), the air-conditioning units, andother equipment. The entrance to this com-partment is from the ground, through an ac-cess (ventral) door with a self-containedfolding ladder. There are also several servicedoors located all over the aircraft; these are dis-cussed in Chapter 5157, Structures.

WindowsThere are fourteen windows in the passengercabin (seven per side) (Figure 5-1). They arelocated 49 inches apart on center and are el-liptical in shape (19 x 26 inches), water tight,and electrically heated.

Emergency ExitsOf the fourteen windows in the passenger com-partment, four are removabletwo on the leftand two on the right side located over the wing.The removable windows are capable of beingopened from either inside or outside for emer-gency egress. The main entrance door is cer-tified as an emergency exit, and the baggagecompartment door may also be used as an aux-iliary emergency exit (Figure 5-2).

NOTES




5-8FOR T

RAIN

ING P

URPOSES O

NLY

FlightSafety

international

GU

LFSTR

EA

M G

500/G

55

0 M

AIN

TENAN

CE TR

AIN

ING

MAN

UAL

Figure 5-3. Rolls-Royce Deutschland BR710 Engine

AIRCRAFT SYSTEMS AIRFRAME INNOVATIONSInnovations in the airframe include an en-larged cockpit, relocated airstair, new trail-ing-edge components, new wing technology,nacelle and thrust reversers, and newly de-signed winglets.

ENGINESThe Gulfstream G500/G550 has two aft fuse-lage-mounted Rol ls-Royce DeutschlandBR700-710C4-11 engines (Figure 5-3) witha static thrust of 15,385 pounds each at ISA+15C (86F). Each engine is a high bypassturbofan with a bypass ratio of 4.0:1 and iscontrolled by a full authority digital enginecontrol (FADEC).Control of the BR710 engine is electronic, viadual-channel engine electronic controllers(EECs). Nothing mechanical connects thepilots power levers and the engines. Thepower levers send electronic signals to theEECs microprocessors, which command en-gine power. This system protects against en-gine overspeed and overtemperature.

NOTES







PRIMARY ENGINE ALTERNATE ENGINE

SECONDARY ENGINE COMPACTED ENGINE

Figure 5-4. Engine Instrument Displays

Primary Engine IndicationsThe normal configuration format at initial ap-plication of full electrical power places the pri-mary engine display 1/6 window in the topright section of DU No. 2 with the secondaryengine display 1/6 window directly below inthe bottom right of DU No. 2. In this config-uration, the primary engine contains analogdial representations for EPR, TGT and LP rpmand digital indications for HP rpm and fuelflow (FF) with a split arrow icon showing dif-ferences in engine FF.

The secondary engine display 1/6 window willdisplay only digital indications for the fol-lowing engine parameters: oil pressure, oiltemperature, LP and HP EVM, hydraulic pres-sures, fuel tank temperature and fuel quantity(a split arrow icon representing differences intank quantities).If for any reason the flight crew chooses to re-arrange the default display format, the fol-lowing options are available:

1. If the secondary engine 1/6 window iseliminated from display, the primaryengine 1/6 window format will changeto an alternate engine 1/6 window dis-play where the digital indications of HPrpm and fuel flow (and split arrow dif-ference icon) are replaced with digitalreadings of fuel quantity including atotal fuel indication and a split arrowtank difference icon.

2. A compacted engine 1/6 window may beelected for display during normal en-gine operations. If only battery power isavailable for the aircraft electrical sys-tem, and engines are operating, the 1/6compacted engine display is the defaultpresentation. The compacted windowcontains digital indications for EPR,TGT, LP and HP rpm, FF, oil pressure,oil temperature and fuel quantity.

NOTES







Figure 5-5. Auxiliary Power Unit

AUXILIARY POWER UNITThe auxiliary power unit (APU) is the RE220,developed by Honeywell. The APU is a gas tur-bine engine that starts with aircraft or groundDC power and then operates on aircraft-sup-plied fuel. The APU is to provide an alternatesource of pneumatic power for the main enginestart system and the environmental controlsystem, and provide shaft power to drive theauxiliary AC generator. Engine operation iscontrolled by four systems: fuel, lubrication,electrical and pneumatic. The control systemconsists of an electronic control unit (ECU)and sensors that measure APU operating pa-rameters, which the ECU uses to control theengine. The ECU ensures the APU and all ofits subsystems operate correctly in responseto all environmental and load conditions.

The APU provides pneumatic power in theform of compressed air for operation of air-craft main engine starters and environmentalcontrol. The engine has five basic operatingmodes: ready to load (full rpm with no shaftor bleed load), main engine starting (bleedload), environmental control (bleed load),electrical power generation (shaft load) andcombination operation (simultaneous shaftand bleed loads). The APU can be started upto 43,000 feet, although 39,000 feet is guar-anteed. The auxiliary AC generator is rated at40 kVa electrical load up to 45,000 feet. APUoperations can be monitored from the APUcontrol panel located on the cockpit overheadpanel or using the 1/6 synoptic page APUBLEED (Figure 5-6).




APU

Bleed Air Pressure

EGT RPM%C

LPsi Psi

R

495

45 45

101.1

Open

Figure 5-6. APU Synoptic Page




LATERAL AXIS

VERTICAL AXIS

AILERON

AILERON

FLAP

ELEVATORTRIM TAB

ELEVATORTRIM TAB

RUDDER

ELEVATOR

LONGITUDINAL AXIS

SPOILERS

AILERON TRIM TAB

Figure 5-8. Flight Control Locations

NWS

Main Door

FlapsGnd Spl Ctrl

Brakes

Ldg Gear

3000 3100 psi

psi

psi

psi

3000 psiLeft

psiRight

0

L T/R R T/R

AileronElev

Flt SplGnd SplStl Bar

Rudder

1.5g4.7g

12

Full

Low

Full

Low

C 24 C

3000

Aux

PTU

HMG

HYDRAULICS

YD2YD1

ACCUM

BOTTLE

Left Right

Figure 5-7. 2/3 Hydraulic Synoptic Page

HYDRAULICSHydraulic power is supplied to the aircraft bythree independent systems designated as leftsystem, right system, and auxiliary system.All systems operate at 3,000 psi nominal pres-sure. The left hydraulic system is powered byone variable displacement pump mounted onthe left engine. This system powers the flightcontrols, ground spoiler control, wing flaps,brakes, nose wheel steering, landing gear, andhydraulic motor generator. The right hydraulicsystem is powered by one variable displacementpump mounted on the right engine. This sys-tem powers the flight controls and through thepower transfer unit; ground spoiler control,wing flaps, brakes, nose wheel steering, land-ing gear, and hydraulic motor generator. A DCelectrically-driven pump is provided for op-eration of the main entrance door, alternatepower for flaps, brakes, steering, rudder, yaw

damper, and for ground operation of the land-ing gear. The 2/3 HYDRAULICS synopticpage displays system operation and indicatesany abnormal condition (Figure 5-7).

FLIGHT CONTROLSGulfstream G500/G550 flight controls fea-ture conventional mechanical linkages withdual servo hydraulic boost for all axes. Rollauthority is augmented by combined aileronand spoiler action (Figures 5-8 and 5-9). Anaileron and elevator disconnect is providedin case of jammed controls and both electricand manual pitch trim is available. Roll andyaw trim are manually operated, and dual-channel yaw dampers are provided. The 2/3 ora 1/6 FLIGHT CONTROL synoptic page de-picts system operation and indicates any ab-normal condition in the system (Figure 5-9)




1 1

1/6 PAGE

2/3 PAGE

Figure 5-9. Flight Control Synoptic Page




6200 6200

12,400

3843

21 14

Figure 5-11. Fuel System Synoptic Page

1/6 PAGE

2/3 PAGE

Figure 5-10. ECS/PRESS Synoptic Page

LANDING GEARThe Gulfstream G500/G550 landing gears arefully retractable, tricycle landing gear withstandard dual wheels. Oil-pneumatic shockstruts provide support of the aircraft duringlanding and while on the ground. The gear iselectrically controlled and hydraulically ac-tuated and is normally pressurized from the lefthydraulic system. The landing gear incorpo-rates an electronically controlled antiskidbraking system and a nose wheel steering sys-tem. The FLIGHT CONTROL synoptic pagecan be displayed as 1/6 or 2/3, and depictslanding gear position with weight on wheelsinformation (Figure 5-9).

ENVIRONMENTAL CONTROLSYSTEMThe environmental control system (ECS) cansustain a maximum pressure differential of10.17 psi. This allows a 6,000-foot cabin al-titude at FL 510. The ECS consists of dual aircycle machines, a three-zone temperature con-trol, water separators, and ozone filters. Dualdigital controls that are tied into the flightmanagement system normally govern cabinpressurization. The 2/3 or a 1/6 ECS/PRESSsynoptic page depicts operation of the pneu-matic system and indicates any abnormal con-ditions within the system (Figure 5-10).

FUEL SYSTEMThe fuel system consists of two integral wingtanks with a total usable capacity of 41,300pounds (Figure 5-11). Cross-flow capabilityby way of a cross-feed valve allows fuel fromeither tank manifold to feed the opposite tankmanifold. Fuel transfer between tanks is pro-vided through the intertank valve. This pro-vides for fuel balancing.

Refueling is accomplished by gravity or pres-sure fueling. Automatic or manual refuel-ing capability is available in the pressurefueling mode.

Documents

G500-G550 MTM V1