Airbus A330

The content of this document is the property of Airbus Industrie. It issupplied in confidence and commercial security on its contents must bemaintained.It must not be used for any purpose other than that for which it is supplied,nor may information contained in it be disclosed to unauthorized persons.It must not be reproduced in whole or in part without permission inwriting from the owners of the copyright. Requests for reproduction ofany data in this document and the media authorized for it must beaddressed to Airbus Industrie.

© Airbus Industrie 1990. All rights reserved.

Airbus IndustrieCustomer Services DirectorateTechnical Data And Documentation

31707 Blagnac CedexFRANCE

Reference : E. ARM Issue : Jan 98

Page 1 of 1JAN 30/98

REVISION TRANSMITTAL SHEET

TO : ALL HOLDERS OF A330 AIRCRAFT RECOVERY MANUAL

The revision, dated JAN 30/98 is attached and covers all the Aircraft RecoveryManual data identified in the Highlights.

FILING INSTRUCTIONS

NOTE : Before introducing this revision make certain that previous revisions areincorporated.

– affected pages are listed on the ″List of Effective Pages″ anddesignated as follows :

R = revised (to be replaced)D = deleted (to be removed)N = new (to be introduced)

– make certain that the content of the manual is in compliance withthe List of Effective Pages.

– file the Revision Transmittal Sheet separately.

– remove and destroy the pages which are affected by thisrevision.

REASON FOR ISSUE

The attached Highlights detail the reasons for issue.

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AIRCRAFT RECOVERY MANUAL

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HIGHLIGHTSPage 1 of 1JAN 30/98

HIGHLIGHTS

REV. 07 – JAN 30/98

Description of change :

1-70 P 1 : Updated page : ″Cargo Compartment – Loading and Unloading″1-70 P 2 : Updated page : ″Lower Deck Compartments – Cargo – A330-300″1-70 P 3 : Updated page : ″Lower Deck Compartments – Cargo – A330-200″1-70 P 4 : Updated page : ″Lower Deck Compartments – Cargo Hold Volume″1-70 P 5 : Updated page : ″Lower Deck Compartments – Loading Combinations″1-70 P 6 : Updated page : ″Different Types of Containers and Pallets″2-33 P 19A : New page : ″Aircraft Reference Axis (A330-200)″2-33 P 20A : New page : ″Type and Position of Loads Acting on Aircraft

A330 with Center Tank″2-34 P 1 to 21 : Updated All Chapters : ″Defueling″3-27 P 3 : Updated page : ″Landing Gear and Jacking Point Location″4-10 P 1 to 17 : Updated All Chapter : ″Moving Damaged Aircraft on Its Landing

Gear″4-10 P 1A : Deleted page in Chapter : ″Moving Damaged Aircraft on Its Landing

Gear″

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LIST OF EFFECTIVE PAGES

CHAPTER/SECTION

C PAGES DATE

List of R 1 JAN 30/98Effective R 2 JAN 30/98Pages

R 3 JAN 30/98

Record of R 1 JAN 30/98Revisions

Table of R 1 JAN 30/98Contents R 2 JAN 30/98

Alphabetical 1 JAN 30/93Index

1-00 1 SEP 30/92

1-10 1 MAY 30/971-10 2 MAY 30/97

1-10 3 MAY 30/971-10 3A MAY 30/97

1-10 4 MAY 30/971-10 4A MAY 30/97

1-20 1 MAY 30/971-20 2 MAY 30/97

1-20 2A MAY 30/971-20 3 MAY 30/97

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1-60 3 OCT 30/931-60 4 0CT 30/93

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1-60 5 OCT 30/931-60 6B FEB 01/95

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1-60 7A OCT 30/931-60 8A OCT 30/93

1-60 7B JUL 01/941-60 8B JUL 01/94

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1-60 15 JUL 01/941-60 16 OCT 30/93

1-70 R 1 JAN 30/981-70 R 2 JAN 30/98

1-70 R 3 JAN 30/981-70 R 4 JAN 30/98

1-70 R 5 JAN 30/981-70 R 6 JAN 30/98

2-05 1 SEP 30/922-05 2 SEP 30/92

2-10 1 SEP 30/922-10 2 SEP 30/92

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2-31 11 OCT 30/932-31 12 OCT 30/93

2-31 13 OCT 30/932-31 14 OCT 30/93

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2-31 19 OCT 30/932-31 20 OCT 30/93

2-31 21 OCT 30/932-31 22 OCT 30/93

2-31 23 OCT 30/932-31 24 OCT 30/93

2-31 25 JUL 01/942-31 26 JUL 01/94

2-31 27 MAY 30/972-31 28 JAN 01/96

2-31 27A MAY 30/972-31 28A JUL 01/94

2-31 27B MAY 30/972-31 28B JUL 01/94

2-31 29 OCT 30/932-31 30 JAN 01/96

2-31 31 OCT 30/932-31 32 OCT 30/93

2-33 1 JAN 01/962-33 2 JAN 01/96

2-33 3 JAN 01/962-33 4 JAN 01/96

2-33 5 JAN 01/962-33 6 JAN 01/96

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2-33 9 JAN 01/962-33 10 JAN 01/96

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3-27 R 3 JAN 30/983-27 4 JUL 01/95

3-27 5 JUL 01/943-27 6 JUL 01/94

3-28 1 MAY 30/973-28 2 JAN 01/96

3-28 3 JAN 01/963-28 4 JAN 01/96

4-10 R 1 JAN 30/984-10 D 1A JAN 30/98

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RECORD OF REVISIONS

REVISIONINSERTED

DATE SIGNATURE

PRELIMINARY (ISSUE 1) SEP 30/92

PRELIMINARY (ISSUE 2) JAN 30/93

ISSUE JUL 30/93

REVISION N°. 1 OCT 30/93

REVISION N°. 2 JUL 01/94

REVISION N°. 3 FEB 01/95

REVISION N°. 4 JUL 01/95

REVISION N°. 5 JAN 01/96

REVISION N° 6 MAY 30/97

REVISION N° 7 JAN 30/98

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CONTENTSPage 1

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TABLE OF CONTENTS

SUBJECT CH/SE PAGE

ALPHABETICAL INDEX 1

INTRODUCTION 1-00 1General Aircraft Characteristics 1-10 1 to 4AFuselage Frame Stations 1-20 1 to 4AWing Rib Stations 1-30 1 to 2Door Clearances 1-40 1 to 8Ground Clearances 1-50 1 to 5Ground Service Connections and Locations 1-60 1 to 16Cargo Load Arrangements 1-70 1 to 6

SURVEY AND PREPARATION 2-00Quick Reference Guideline for A/C Recovery 2-05 1 to 2Damage and Terrain 2-10 1 to 2Damage Control and Safety 2-20 1 to 2Weight and H-Arm Management 2-30 1Empty Weight Revision and H-Arm Location 2-30 1ComputationEffect of the Nose Gear, Flap and Slat positionon the Aircraft CG

2-31 1

Weight and Aircraft CG Variations due to anyFluids aboard other than Fuel

2-31 2

Weight and Aircraft CG Variations due to Cargoaboard

2-31 3 to 12

Net Recoverable Weight (NRW) and H-Arm Location 2-31 13Component Removal – CG Shifts 2-31 14Mass, H-Arm and Moment Concerning VariousComponents of Engines

2-31 15 to 32

Weight and Aircraft CG Variations due to any Fuelaboard

2-33 1 to 20A

Defueling 2-34 1 to 21Removal of Payload 2-40 1 to 4

STABILIZE AIRCRAFT 3-00Tethering 3-10 1 to 8Lifting Damaged Aircraft 3-20 1Nose Gear Retracted, Collapsed or Lost 3-21 1 to 8Main Gears Retracted, Collapsed or Lost 3-22 1 to 2One Main Gear Retracted, Collapsed or Lost 3-23 1 to 2Nose Gear and either Left or Right Hand MainGear Retracted, Collapsed or Lost

3-24 1 to 2

All Gears Retracted, Collapsed or Lost 3-25 1 to 2Lifting Using Inflatable Bags 3-26 1 to 3Lifting with Hydraulic Jacks 3-27 1 to 6Auxiliary Jacking Points 3-28 1 to 4

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CONTENTSPage 2

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SUBJECT CH/SE PAGE

MOVING AIRCRAFT 4-00Moving Damaged Aircraft 4-10 1 to 17Towing 4-21 1 to 6Taxiing and Towing of Aircraft with Deflated Tires 4-22 1 to 4Returning Undamaged Aircraft to Runway 4-30 1 to 2

TOOLING AND EQUIPMENT 5-00General Recovery Equipment 5-10 1Equipment Peculiar to the Aircraft 5-20 1Specialized Recovery Equipment 5-20 2

PREVIOUS AIRCRAFT RECOVERY EXPERIENCE 6-00

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ALPHABETICAL INDEX

SUBJECT CH/SE

Aircraft on its Landing Gear 4-10Aircraft with Landing Gear Collapsed 4-11All Gears Retracted, Collapsed or Lost 3-25Auxiliary Jacking Points 3-28Cargo Load Arrangements 1-70Component Removal - CG Shifts 2-31Damage and Terrain 2-10Damage Control and Safety 2-20Defueling 2-34Door Clearances 1-40Effect of the Nose Gear, Flap andSlat position on the Aircraft CG

2-31

Empty Weight Revision and H-Arm Location Computation 2-30Equipment Peculiar to the Aircraft 5-20Escape Slide Removal 2-35Fuselage Frame Stations 1-20General Aircraft Characteristics 1-10General Recovery Equipment 5-10Ground Clearances 1-50Ground Service Connections and Locations 1-60Lifting Damaged Aircraft 3-20Lifting Using Inflatable Bags 3-26Lifting with Hydraulic Jacks 3-27Main Gears Retracted, Collapsed or Lost 3-22Mass, H-Arm and Moment Concerning 2-31Various Components of EnginesMoving Damaged Aircraft 4-10Net Recoverable Weight (NRW) and H-Arm Location 2-31Nose Gear Retracted, Collapsed or Lost 3-21Nose Gear and either LH or RH Hand Main Gear 3-24Retracted, Collapsed or LostOne Main Gear Retracted, Collapsed or Lost 3-23Quick Reference Guideline for A/C Recovery 2-05Removal of Payload 2-40Returning Undamaged Aircraft to Runway 4-30Specialized Recovery equipment 5-20Tethering 3-10Towing 4-21Towing an Aircraft with Tires Deflated 4-22Weight and H-Arm Management 2-30Weight and Aircraft CG Variations due to any Fuel aboard 2-33Weight and Aircraft CG Variations due to any 2-31Fluids aboard other than FuelWeight and Aircraft CG Variations due to Cargo aboard 2-31Wing Rib Stations 1-30

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INTRODUCTION

1. Purpose of Manual

The AIRCRAFT RECOVERY MANUAL is intended to provide Airlines and AirportAuthorities with optimum planning, preparation and accomplishment data forthe Lifting and moving of a disabled aircraft which may be obstructingairport traffic.

2. Scope of Manual

The Manual contains general information covering the different aircraftmodels. Of course, it will not be easy in every instance to locate all therequisite data in the Manual within a very short time ; it is hence advisiblefor Airport Authorities and Airlines to use this Manual to jointly draw upone or more schemes based on their specific requirements, equipment availableas well as on recommendations contained in publications, such as the U.S.Federal Aviation Agency circular AC 150/5200-13 of August 27, 1970, entitled″Removal of Disabled Aircraft″, and the specification written by the ″ATAAircraft Recovery Subcommittee″. Endeavours are made for the information inthis Manual to comply with that in the Aircraft Technical Specifications ;however, in case of conflict, the Aircraft Technical Specification shallprevail.

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GENERAL AIRPLANE CHARACTERISTICS

BASIC DEFINITIONS

The weight terms used throughout this manual are given below together with theirrespective definitions.

MAXIMUM RAMP WEIGHT

Maximum weight authorized for ground maneuver by the applicable governmentregulations, including taxi and run-up fuel.

MAXIMUM LANDING WEIGHT (MLW)

The maximum landing weight shall be the maximum weight at which the aircraftmeets the appropriate landing certification requirements.

MAXIMUM TAKEOFF WEIGHT (MTOW)

The maximum takeoff weight shall be the maximum permissible weight of theaircraft when the brakes are released for takeoff, or at the start of thetakeoff roll.

OPERATING WEIGHT EMPTY (OWE)

The operational weight empty shall be the manufacturer's weight empty plus theoperator's items weight. The operator's items weight shall be the flight andcabin crew and their baggage, unusable fuel, oil for engines, APU, IDG,emergency equipment, toilet, chemicals and fluids, galley structure, cateringequipment, seats, documents, pallets and baggage containers, emergency equipment(as detailed in the WBM).

MAXIMUM ZERO FUEL WEIGHT (MZFW)

The total maximum Operating Weight Empty (OWE) plus the maximum payload. It isalso the maximum operational weight without usable fuel.

MAXIMUM STRUCTURAL PAYLOAD

Consists of the maximum design payload weight of passengers, passenger baggageand/or cargo.

STANDARD SEATING CAPACITY

The maximum number of passengers specifically certified or anticipated forcertification.

MAXIMUM CARGO VOLUME

The maximum usable volume available for cargo.

USABLE FUEL CAPACITY

The volume of fuel carried for a particular operation, less drainable unusablefuel and trapped fuel remaining after a fuel runout test has been accomplished.

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GENERAL AIRPLANE CHARACTERISTICS DATA

WEIGHTS USABLE FUEL CAPACITY

WEIGHTVARIANTS

MAXRAMPWEIGHT

MAXTAKEOFFWEIGHT

MAXLANDINGWEIGHT

MAXZERO FUELWEIGHT

OPERATINGWEIGHTEMPTY

MAXSTRUCTURALPAYLOAD

Engines US Pounds at15.6°C (60°F)

Kilograms at15.6°C (60°F)

Designation lb kg lb kg lb kg lb kg lb kg lb kg GALLONS LITERS JP1D=0.790

JP1D=0.790

A330/300

Basic WV OOO 469360 212900 467375 212000 383600 174000 361554 164000 255813 116036 105741 47964 all 25859.8 97885 170480 77329.15

ReinforcedWV 010 480382 217900 478398 217000 394623 179000 372577 169000 279246 126665 GE CF6-80E1 25859.8 97885 170480 77329.15

A330/200

WV20 509039 230900 507055 230000 396825 180000 370370 168000 275458 124948 108139 49052 * 36872 139560

VOLUME

STDSEATINGCAPACITY

PAX

* Engines : – GE CF6-80E1A4– PW 4174– RR TRENT 775

TotalFUSELAGEVOLUME

PassengerCABINVOLUME

COCKPIT

VOLUME

AVIONICSCOMPARTMENT

VOLUME

MAXCARGOVOLUME

ft3 m3 ft3 m3 ft3 m3 ft3 m3 ft3 m3

A330/300 37292 1056 13773 390 424 12 1540 43.6 5685 161 335 REMARKS

A330/200 424 12 1540 43.6 293all : GE CF6-80 E1A2

PW4164 & 4168RR TRENT 768 & 772

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AIRCRAFTRECOVERYMANUAL

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AIRPLANE DIMENSIONSModel 300

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FUSELAGE FRAMES/STATIONS

"This section gives the fuselage frame stations measured along X datum 6382 mmfrom the nose.

The stations (STA) are given in millimeters without conversion.

Fuselage frame stations are shown on

– pages 2 thru 4 for A330-300– pages 2A thru 4A for A330-200.

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FUSELAGE FRAMES/STATIONSNOSE SECTION (FR 1 to FR 37.1)

MODEL 300

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FUSELAGE FRAMES/STATIONSNOSE SECTION (FR 1 to FR 38)

MODEL 200

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FUSELAGE FRAMES/STATIONSFORWARD SECTION (FR 37.1 to FR 58)

MODEL 300

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FUSELAGE FRAMES/STATIONSFORWARD SECTION (FR 38 to FR 58)

MODEL 200

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FUSELAGE FRAMES/STATIONSFORWARD SECTION (FR 58 to FR 106A)

MODEL 300

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FUSELAGE FRAMES/STATIONSFORWARD SECTION (FR 58 to FR 106A)

MODEL 200

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WING RIB STATIONS

Wing rib stations are shown on page 2.

NOTE : All dimensions of stations in this section are in millimeters.

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Wing Ribs/Stations

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DOOR CLEARANCES

Location, shape and dimensions of passenger/crew and cargo compartment doors andof emergency exits are shown on pages 2 thru 8.

Ground clearances of door sills are shown in Section 1-50.

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DOOR CLEARANCESFORWARD PASSENGER/CREW DOOR

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DOOR CLEARANCESMID PASSENGER/CREW DOOR

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DOOR CLEARANCESEMERGENCY EXIT

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DOOR CLEARANCESAFT PASSENGER/CREW DOOR

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DOOR CLEARANCESFORWARD CARGO COMPARTMENT DOOR

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DOOR CLEARANCESAFT CARGO COMPARTMENT DOOR

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DOOR CLEARANCESBULK CARGO COMPARTMENT DOOR

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GROUND CLEARANCES

The heights of the doors, fuselage, wing tip, stabilizer, nacelle and mainlanding gear door above the ground are given on pages 2 to 5.Dimentions in the tables are approximate and will vary with tire type andconditions.

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MRW212 900 kg469 360 lb

OPERATING WEIGHTEMPTY CG 26.8 %

MAXIMUM RAMPWEIGHT CG 15 %

MAXIMUM RAMPWEIGHT CG 36.5 %

AC ON JACKS*FDL at 6500 mm

m ft m ft m ft m ftA 4.55 14.92 4.41 14.46 4.55 14.92 6.32 20.7B 2.70 8.85 2.55 8.36 2.66 8.72 4.14 13.5

FR 26 C1 7.74 25.4 7.58 24.86 7.67 25.16 9.32 30.5FR 72 C2 8.53 28 8.31 27.26 8.19 26.87 9.32 30.5

D 4.83 15.84 4.67 15.32 4.73 15.51 6.32 20.7FR 20 E1 2.10 6.89 1.95 6.39 2.03 6.66 3.68 12.FR 37 E2 2.28 7.48 2.10 6.88 2.14 7.02 3.68 12.FR 56 E3 2.74 8.99 2.54 8.33 2.45 8.03 3.68 12.FR 45 H 2.04 6.7 1.86 6.10 1.85 6.07 3.26 10.7

K 3.43 11.25 3.22 10.56 3.13 10.27 4.24 13.9L 5.77 18.93 5.55 18.20 5.41 17.75 6.53 21.4M 17.18 56.36 16.94 55.58 16.72 54.85 17.62 57.8N 6.46 21.20 6.13 20.11 6.06 19.88 7.55 24.7O 8.33 27.32 8.09 26.54 7.88 25.85 9.23 30.2P 8.05 26.41 7.70 25.26 7.61 24.96 8.96 29.4

GE = R 0.94 3.08 0.76 2.49 0.79 2.59 2.34 7.67PW = R 0.90 2.95 0.72 2.36 0.75 2.46 2.29 7.51RR = R 0.87 2.85 0.69 2.26 0.72 2.36 2.21 7.25

S 3.87 12.70 3.68 12.07 3.64 11.94 5.25 17.2T 4.33 14.20 4.13 13.55 4.11 13.48 5.70 18.7U 4.64 15.22 4.41 14.46 4.37 14.33 6.00 19.6V 4.97 16.30 4.72 15.48 4.67 15.32 6.30 20.6X 7.48 24.54 7.24 23.76 7.03 23.06 8.10 26.5Y 3.68 12.07 3.46 11.35 3.35 11 4.39 14.4

* See Section 3.28 page 3

GROUND CLEARANCESModel 300 (212 tonnes)

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MRW230 900 kg509 042 lb

OPERATING WEIGHTEMPTY CG 27.9 %

MAXIMUM RAMPWEIGHT CG 21 %

MAXIMUM RAMPWEIGHT CG 37.5 %

AC ON JACKS*FDL at 6500 mm

m ft m ft m ft m ftA 4.63 15.19 4.44 14.56 4.63 15.19 6.32 20.7B 2.78 9.12 2.58 8.46 2.74 8.99 4.14 13.5

FR 26 C1 7.75 25.42 7.56 24.80 7.69 25.23 9.32 30.5FR 72 C2 8.54 28.02 8.31 27.26 8.16 26.77 9.32 30.5

D 6.32 20.7FR 20 E1 2.04 6.7 1.84 6.03 2.01 6.59 3.68 12.FR 37 E2 2.23 7.31 2.03 6.66 2.12 6.95 3.68 12.FR 56 E3 2.70 8.86 2.48 8.13 2.40 7.87 3.68 12.FR 45 H 2.02 6.63 1.81 5.93 1.83 6.00 3.26 10.7

K 3.50 11.48 3.27 10.73 3.16 10.36 4.24 13.9L 5.74 18.83 5.51 18.07 5.35 17.55 6.53 21.4M 18.23 59.80 17.98 58.98 17.71 58.10 18.67 61.25N 6.48 21.26 6.14 20.14 6.05 19.85 7.55 24.7O 8.30 27.23 8.05 26.41 7.77 25.49 9.23 30.2P 8.08 26.51 7.71 25.29 7.61 24.96 8.96 29.4

GE = R 0.94 3.08 0.74 2.42 0.79 2.59 2.34 7.67PW = R 0.90 2.95 0.70 2.29 0.75 2.46 2.29 7.51RR = R 0.87 2.85 0.67 2.19 0.72 2.36 2.21 7.25

S 3.89 12.76 3.67 12.04 3.64 11.94 5.25 17.2T 4.35 14.27 4.13 13.55 4.11 13.48 5.70 18.7U 4.63 15.19 4.42 14.50 4.37 14.33 6.00 19.6V 4.95 16.24 4.73 15.52 4.67 15.32 6.30 20.6X 7.47 24.51 7.23 23.72 6.97 22.86 8.10 25.5Y 3.66 12.01 3.43 11.25 3.30 10.82 4.39 14.4Z 5.41 17.75 5.22 17.12 5.43 17.81

* See Section 3.28 page 3

GROUND CLEARANCESModel 200 (230 tonnes)

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MAIN LANDING GEAR

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RADOME TRAVEL

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SEP 30/92

GROUND SERVICE CONNECTIONS

AND LOCATIONS

The ground service connections and locations are specified on pages 1 thru 12A.

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OCT 30/93

1 – OXYGEN SYSTEM

2 – EXTERNAL POWER (ELECTRICAL)

3 – POTABLE WATER DRAIN

4 – LOW PRESSURE PRE-CONDITIONING

5 – HIGH PRESSURE AIR PRE-CONDITIONING AND ENGINE STARTING

6 – IDG OIL FILLING

7 – ENGINE OIL FILLING

8 – PRESSURE REFUEL

9 – OVERWING REFUEL

10 – HYDRAULIC GROUND POWER SUPPLY (YELLOW)

11 – HYD RESERVOIR FILLING AND GROUND POWER SUPPLY (GREEN)

12 – HYD RESERVOIR AIR PRESSURIZATION & GROUND POWER SUPPLY (BLUE)

13 – NITROGEN CHARGING FOR HYDRAULIC ACCUMULATORS

14 – REFUEL/DEFUEL PANEL

15 – POTABLE WATER FILLING

16 – TOILET SERVICING

17 – APU OIL FILLING

GROUND SERVICE CONNECTIONSSYMBOLS USED ON GROUND

SERVICE CONNECTIONS DIAGRAMS

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OCT 30/93

GROUND SERVICE CONNECTIONSGROUND SERVICE CONNECTIONS LAYOUT

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OCT 30/93

HYDRAULIC SYSTEM

A. Ground service panel for :

– Green System

– Yellow System

– Blue System

B. Reservoir Pressurization

One 1/4 in. self sealingconnection common to the 3reservoirs.(Blue System Ground Service Panel)

C. Accumulator Chargingfive connections(one for each accumulator) for :

1 – Yellow system accumulator

1 – Green system accumulator

1 – Blue system accumulator

2 – Blue system brakeaccumulator

D. Reservoir Filling, 2 Connections :One self-sealing connection forpressurized supply on theGreen system ground service panel.

One handpump filling connection.

DISTANCEMeters

(ft – in.)MEANHEIGHTFROMGROUND

AFT OFNOSE

FROM AIRPLANECENTERLINE

R SIDE L SIDE

41.3(135-6)

1.34(4-5)

2.23(7-4)

35.4(116-2)

1.30(4-3)

1.95(6-5)

34.41(112-11)

1.28(4-2)

1.94(6-4)

34.47(113-1)

1.41(4-8)

1.89(6-2)

35.55(116-8)

1.43(4-8)

1.91(6-3)

41.52(136-3)

1.33(4-4)

2.19(7-2)

34.54(113-4)

1.38(4-6)

1.9(6-3)

34.54(113-4)

1.24(4-1)

1.9(6-3)

34.54(113-4)

1.18(3-10)

1.9(6-3)

41.31(135-6)

1.3(4-3)

2.11(6-11)

GROUND SERVICE CONNECTIONSHYDRAULIC SYSTEM

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OCT 30/93

DISTANCEMeters


AFT OFNOSE


R SIDE L SIDE

E. Reservoir DrainOne 3/8 in. self-sealing connectionon reservoir for :

– Yellow system

– Green system

– Blue system

29.03( 95.24)

2.12(6.95) – 2.40

( 7.87)

33.17(108.82) – 0.70

(2.29)3.80

(12.46)

29.03( 95.24) – 2.12

(6.95)2.40

( 7.87)

F. Ground test

Three 1 in. self-sealing connectionsand three 1-1/2 in.self-sealing connections (one pairper system)

– Green system ground service panel

– Yellow system ground service panel

– Blue system ground service panel

34.92(114.56) – 1.35

(4.42)2.2

( 7.21)

29.03( 95.24)

1.30( 4.26) – 2.0

( 6.56)

28.03( 91.96) – 1.28

(4.19)2.0

( 6.56)

GROUND SERVICE CONNECTIONSHYDRAULIC SYSTEM

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FEB 01/95

OIL SYSTEM

A. Engine oil replenishment :One gravity filling cap andone pressure filling connectionper engine

ENGINE OILFILLING

DISTANCE FT – IN (Meters)MEANHEIGHTFROMGROUNDAFT OF NOSE

FROM AIRPLANE CENTERLINE

ENGINE 1 (Left) ENGINE 2 (Right)

84 ft 5 in(25,729 m)

34 ft 11 in(10,661 m)

26 ft 6 in(8,079 m)

88 in(2,232 m)

Tank capacity :– Full level : 8.00 US GAL (30.3 liters)– Usable : 5.75 US GAL (21.7 liters)

B. IDG oil replenishment :

One pressure filling connection per engine

IDG OILPRESSUREFILLINGCONNECTION




85 ft 10 in(26,167 m)

33 ft 1 in(10,078 m)

28 ft 5 in(8,662 m)

59 in(1,50 m)

Max delivery pressure required : 40 Psi (2.75 bar)Max OIL capacity of the IDG : 1.1 US GAL (4.1 liters)

Ground Service ConnectionsEngine Oil Tank and IDG.

PW4000 – Engine

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FEB 01/95

OIL SYSTEM

A. Engine oil replenishment :One gravity filling capOne Ozone self sealing pressure fill and overfill connector per engine

ENGINE OILFILLING

DISTANCE FT - IN (Meters)MEANHEIGHTFROMGROUNDAFT OF NOSE



78ft 5ins(23,901m)

26ft Oins(7,925m)

35ft 6ins(10,820m)

81.0ins(2,057m)



One ozone self sealing pressure fill and overfill connector per engine


DISTANCE FT - IN (Meters)MEANHEIGHTFROMGROUNDAFT OF NOSE



80ft Oins(24,384m)

31ft 8ins(9,652m)

29ft 10ins(9,093m)

33.0ins(838mm)


Ground Service ConnectionsEngine Oil Tank and IDG.RR RB211 Trent - Engine

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FEB 01/95

OIL SYSTEM

A. Engine oil replenishment :One gravity filling cap andone pressure filling connectionper engine

ENGINE OILFILLING




81 ft 9 in(24,936 m)

32 ft 9 in(10,00 m)

28 ft 7 in(8,732 m)

67 in(1,716 m)



One pressure filling connection per engine





75 ft 6 in(23,036 m)

26 ft 1 in(7,962 m)

35 ft 4 in(10,778 m)

92 in(2,354 m)


Ground Service ConnectionsEngine Oil Tank and IDG.GE CF6-80E1 – Engine

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OCT 30/93

GROUND SERVICE CONNECTIONSENGINE OIL TANKPW4000 ENGINE

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OCT 30/93

Ground Service ConnectionsEngine Oil Tank

RB211 – Trent Engine

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JUL 01/94

Ground Service ConnectionsEngine Oil Tank

GE CF6-80E1-Engine

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OCT 30/93

Ground Service ConnectionsIDG

PW4000 ENGINE

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OCT 30/93


RB211 – Trent Engine

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JUL 01/94


GE CF6-80E1 Engine

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OCT 30/93

ELECTRICAL SYSTEM

Two standard 6 pin connectorsISO R 461 specification

Supply :115/200 Volt, 3-Phase, 400 HzPower required : 2 – (90 KVA)

DISTANCEMeters

(ft – in.) MEANHEIGHTFROMGROUND

AFT OFNOSE

AIRPLANECENTERLINE

7.01(22-12)

1.98(6-6)

GROUND SERVICE CONNECTIONSELECTRICAL SYSTEM

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OCT 30/93

OXYGEN SYSTEM

0 – BASIC

1 – OPTION

2 – OPTION

NOTE : INTERNAL CHARGING CONNECTIONPROVIDED

DISTANCEMeters


AFT OFNOSE


R SIDE L SIDE

OPTION 1 2.5(8-2)

0.53(1-8) – 3.2

(10-6)

OPTION 2 2.5(8-2)

0.68(2-2) – 3.2

(10-6)

Zero, one or two service connections (external charging in the avionicscompartment) MS22066 Std

GROUND SERVICE CONNECTIONSOXYGEN SYSTEM

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ENGINE OIL REPLENISHMENTPW4000 ENGINE

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IDG Oil REPLENISHIMENTPW4000 ENGINE

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STARTER OIL REPLENISHMENTPW4000 ENGINE

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OCT 30/93

FUEL SYSTEM

Four Standard 2.5 in.connections – ISO R45 SPEC.

LEFT SIDE OPTION

Two service connections(gravity refuel)

DISTANCEMeters


AFT OFNOSE


R SIDE L SIDE

30.00(98-5)

12.6(41-4)

12.6(41-4)

5.00(16-5)

34.50(113-3)

17.2(56-5)

17.2(56-5)

5.80(19-0)

Flow Rate :1580 l/min (348 Imp. gal/min) (417 U.S. gal/min) per connectionMaximum Pressure :– 50 psig (3.45 bars)

GROUND SERVICE CONNECTIONSFUEL SYSTEM

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OCT 30/93

PNEUMATIC SYSTEM

A330

Two standard 3 in.TC20 connections for enginestarting and cabin airconditioning (HP)

Two standard 8 in. connections(MS33562) for preconditionedair (LP)

DISTANCEMeters


AFT OFNOSE


R SIDE L SIDE

30.57(100-4) – 0.84

(2-9)1.79(5-10)

30.92(101-5) – 0.84

(2-9)1.79(5-10)

29.03(95-3) – 0.31

(1-0)1.86(6.1)

29.03(95-3) – 0.76

(2-6)1.89(6-2)

GROUND SERVICE CONNECTIONSPNEUMATIC SYSTEM

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OCT 30/93

POTABLE WATER SYSTEM

A330

Service panel, located between frame69–70, comprising :– one heated 3/4 in. quick releasefilling connection

– one heated 3/4 in. overflow anddischarge connection

– one ground pressurization connection

Fwd drainage panel, located betweenframe 28–29 comprising :– one standard 3/4 in. drain connectionwith back-up mechanical control

Aft drainage panel, located betweenframe 55–56 for A340-200 and 51.1–57.2for A330, comprising :– one standard 3/4 in. drain connectionwith back-up mechanical control

– one standard 3/4 in. overflow anddischarge connection with back-upmechanical control

Usable capacity :– 700 liters (154 Imp. gal) (185 US gal) standard– 1050 liters (231 Imp. gal) (277 US gal) standard option

Fill rate :

– pressure

– flow

DISTANCEMeters


AFT OFNOSE


R SIDE L SIDE

48.15(157-9)

0.51(1-7) – 3.15

(10-3)

14.70(48-2) – 0.60

(2-0)1.90(6-2)

40.18(131-7)

0.72(2-4) – 2.46

(8-1)

Installation of ... in aircraft

Fwd-tank (and opt-tank)[sect.15/16]

aft-tank [sect.18]

50 PSI3.45 bars

125 PSI8.62 bars

50 PSI3.45 bars

125 PSI8.62 bars

45 l/min10 Imp. gal/min12 US gal/min




GROUND SERVICE CONNECTIONSPOTABLE WATER SYSTEM

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OCT 30/93

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JUL 01/94

VACUUM TOILET SYSTEM

Waste Service panel comprising :

Standard : One standard 4 in. drainconnection and two 1 in.flushing connections

Standard option : One standard 4 in.drain connection andthree 1 in. flushingconnections

DISTANCEMeters


AFT OFNOSE


R SIDE L SIDE

50.65(166-1) – 0.09

(0-3)3.6

(10-8)

Capacity waste tanks :

standard : 700 liters (153.9 Imp. gal) (184.9 US gal.)standard option : 1050 liters (231.0 Imp. gal) (277.4 US gal.)

Chemical fluid :standard : 36 liters (7.9 Imp. gal.) ( 9.5 US gal.)standard option : 54 liters (11.9 Imp. gal.) (14.3 US gal.)

GROUND SERVICE CONNECTIONSVACUUM TOILET SYSTEM

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OCT 30/93

AIRCRAFT GROUNDING LOCATION

The aircraft must be grounded in these conditions– when it is Refueled/Defueled– maintenance– bad weather conditions.

NOTE : In all other conditions, the electrostatic discharge through the tyre issufficient.

The Main Landing Gear and the Nose Landing Gear grounding Studs (1) take aclip-on connector, such as Appleton TGR (2).

– connect ground end of static electric ground connection to approved connectionon ramp or in hangar.

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1-70Page 1

JAN 30/98

CARGO COMPARTMENT

LOADING AND UNLOADING

1. General

Cargo and baggage may be containerized or palletized or loaded in bulk. It isloaded in three underfloor compartments (forward cargo compartment, aft cargocompartment and bulk cargo compartment).

2. Forward Cargo Compartment

A. Capacity

The FWD compartment can be loaded with different types of contaners :

– half size containers, full size contianers, pallets (see example ofcombinations page 5)

B. Access Door (Ref. Section 1-40, page 5)

3. Aft Cargo Compartment

A. Capacity

The aft compartment can be loaded with different types of containers :

halt size containers, full size containers, pallets (see example ofcombinations page 5)


4. Bulk Cargo Compartment

A. Capacity

The volume of the bulk cargo compartment is 19.7 m3 (695 cu.ft). Thecompartment extends from FR 65 to FR 73. It can accommodate up to 3 468 kg(7 645 lb) of baggage or freight (based on an average density of 11 lb/Ft3

(176 kg/m3)


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LOWER DECK COMPARTMENTSCARGO - A330-300

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SEP 30/92

Cargo Compartment Palletized volume− 300

Containerized volume− 300

Forward

Door size (h × w)

66.89 in × 106.34 in(1.699 m × 2.701 m)

2 430 cu.ft.(68.8 cu.m)

based on 96 in × 125 inpallets loaded to height

of 64 in (1.625 m)

2 808 cu.ft.(79.5 cu.m)

based on LD3(IATA E NAS 3610-2K2C)

container volume

Aft

Door size (h × w)

66.61 in × 107.68 in(1.692 m × 2.735 m)

1 620 cu.ft.(45.87 cu.m)


of 64 in (1.625 m)

2 184 cu.ft.(61.8 cu.m)


container volume

Bulk

Door size (h × w)

37.3 in × 37.3 in(0.95 m × 0.95 m)

695 cu.ft = 19.7 cu.m

LOWER DECK COMPARTMENTSCARGO HOLD VOLUME

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JAN 30/98

LOWER DECK COMPARTMENTSCARGO - A330-200

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A330-300



Forward

Door size (h × w)

66.89 in × 106.34 in(1.699 m × 2.701 m)

2 442 cu.ft.(69.1 cu.m)


of 64 in (1.625 m)

2 844 cu.ft.(80.5 cu.m)


container volume

Aft

Door size (h × w)

66.3 in × 107.1 in(1.683 m × 2.721 m)

1 628 cu.ft.(46.0 cu.m)


of 64 in (1.625 m)

2 212 cu.ft.(62.6 cu.m)


container volume

Bulk

Door size (h × w)

37.3 in × 37.3 in(0.95 m × 0.95 m)

695 cu.ft = 19.7 cu.m

A330-200



Forward

Door size (h × w)

66.89 in × 106.34 in(1.699 m × 2.701 m)

1 628 cu.ft.(46.0 cu.m)

2 212 cu.ft.(62.6 cu.m)

Aft

Door size (h × w)

66.3 in × 107.1 in(1.683 m × 2.721 m)

1 628 cu.ft.(46.0 cu.m)

1 896 cu.ft.(53.6 cu.m)

Bulk

Door size (h × w)

37.3 in × 37.3 in(0.95 m × 0.95 m)

695 cu.ft = 19.7 cu.m

LOWER DECK COMPARTMENTSCARGO HOLD VOLUME

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Cargo flexibility – loading combinations

Typical Loading combinations – standard aircraftA330-300 A330-200

FWD AFT FWD AFT

– Half-size containers NAS 3610-2K2C as per IATAcontour E or 60.4 in × 61.5 in palletsNAS 3610-2K3P limited to max gross weight 3 500 lb(1 587 kg) each

18 14 14 12

– Half-size containers NAS 3610-2K2C as per IATAcontour C limited to max gross weight 3 500 lb(1 587 kg) each

9 7 7 6

– Full-size containers NAS 3610-2L2C as per IATAcontour F or 60.4 in × 61.5 in pallets NAS3610-2L3P, 2L4P limited to max gross weight7 000 lb (3174 kg) each

9 7 7 6

– 96 in × 125 in pallets NAS 3610-2M1P, 2P, 3Plimited to max gross weight 10 200 lb (4 626 kg)each (with potential for extension to 11 250 lb(5 103 kg)

6 4 4 4

Plus Half-size containers NAS 3610-2K2C as per IATAcontour E or N limited to max gross weight 3 500 lb(1 587 kg) each. Or 60.4 in × 61.5 in pallets NAS 3610-2K3P limitedto max gross weight 3 500 lb (1 587 kg) each

. Or 60.4 in × 125 in pallets NAS 3610-2L3P, 2L4Plimited to max gross weight 7 000 lb (3 174 kg)each

. Or full-size containers NAS 3610-2L2C as per IATAcontour P limited to max gross weight 7 000 lb(3174 kg) each

– 2 2

– 2 2

– 1 1

– 1 1

LOWER DECK COMPARTMENTSLOADING COMBINATIONS

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DIFFERENT TYPES OF CONTAINERS AND PALLETS

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SEP 30/92

QUICK REFERENCE GUIDELINE FOR A/C RECOVERY

1. OBTAIN INITIAL INFORMATION ABOUT INCIDENT.

2. ESTABLISH COMMUNICATION WITH LOCAL AIRLINE/AGENT/OWN REPRESENTATIVE.

3. DISPATCH DESIGNATED PERSON FROM RECOVER TEAM TO MAKE A DETAILED SURVEY ONSITE.

4. PREPARATION AND SELECTION OF PERSONNEL/EQUIPMENT/MANUALS.

5. CHECK AVAILABILITY FOR IATP-KITS AND ORDER IF REQUIRED.

ON THE SITE

1. ESTABLISH NECESSARY CONTACT WITH LOCAL SECURITY/FIRE FIGHTING BRIGADE TOSECURE THE SITE, AND PROVIDE AREA MAP.

2. FORMULATE DETAILED A/C RECOVERY PLAN.

3. OBTAIN NECESSARY CLEARANCE FROM LOCAL AUTHORITIES TO PROCEED WITH RECOVERYOPERATION.

4. A) ESTABLISH COMMUNICATION TO/FROM AND ON SITE.

B) ESTABLISH TRANSPORTATION TO/FROM SITE.

C) ESTABLISH ACCOMODATION AND FACILITIES AS NECESSARY ON SITE.

5. CONTACT LOCAL AIRLINES, AIRPORT AUTHORITIES AND LOCAL SUPPLIERS FORASSISTANCE.

A) HEAVY MACHINERY/CRANES, ETC.

B) ACCESS ROADS – BUILDING MATERIALS.

C) TIMBER/GRAVEL/SAND/STEEL PLATES, ETC.

D) LIGHTING EQUIPMENT.

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SEP 30/92

6. MAKE ACCESS TO BAGGAGE/CARGO FOR REMOVAL.

A) CHECK MANIFESTS FOR RESTRICTED ARTICLES.

B) REMOVE REF. RESP. REC. MANUAL.

7. WEIGHT AND BALANCE CALCULATION.

8. CAUTION : CHECK THAT RECOVERY PLAN DETAILED IN ITEM 2IS STILL VALID AND ALL SAFETY PRECAUTIONS ARE TAKEN.

9. REMOVAL OF MAJOR COMPONENTS AS NECESSARY.

A) TO LIGHTEN A/C.

B) DUE TO WIND FORCES.

C) DUE AUTHORITY REQUEST (VERT. FIN).

10. MAKE PREPARATION FOR :

A) TETHERING

B) LIFTING REF. RESP. REC. MANUAL

C) MOVING

11. PREPARE FOR HANGARING AND PARKING.

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SEP 30/92

DAMAGE AND TERRAIN

1. The exact condition of a damaged aircraft must be ascertained in order toprepare for its recovery and make arrangements for its repair at the earliestopportunity.

WARNING : PRIOR TO STARTING RECOVERY PROPER, DISCONNECT AND REMOVE ALLAIRCRAFT BATTERIES ; IF REMOVAL IS NOT POSSIBLE, DISCONNECT ANDINSULATE THE BATTERY GROUND TO AVOID ACCIDENTS WHICH MAY ARISEBECAUSE OF SHORT CIRCUITS.

2. After the obvious damage has been observed, the structural condition of theaircraft should be determined and an attempt made to visualize how the impactmight have been transmitted to other members. To this effect, throughly checkthe external structure to the aircraft, panel by panel ; joggles, bulges inthe skin or at structural joints are indications of structure internaldamage ; rivets, bolts or other fasteners that are torn off or damaged arealso signs of damage and justify an internal inspection of the zonesconcerned.

3. If the accident has been caused by any malfunction of the landing gear, it isoften possible to tow the aircraft after it has been lifted. It should bedetermined whether the structure is capable of supporting the weight of theaircraft lowered on to the gear. Several cases may occur :

A. The gears were up locked when the aircraft landed ; the aircraft rests onthe engines and on the aft fuselage. It is very probable the gears may beextended and downlocked, after the aircraft has been jacked, and used fornormal towing.

B. When landing, the aircraft touched the runway violently or got bogged. Thegears or the gear struts have been damaged ; in certain cases, it will bepossible to strengthen the damaged parts temporarily by means of braces inorder to downlock the gear for towing.

C. If the gears have collapsed after touchdown because of a malfunction ofthe landing gear locking, it is possible, if the condition of the aircraftso allows, to strengthen the damaged parts, temporarily, as describedabove.

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SEP 30/92

4. The violence of the shock, the position of the damaged aircraft and theconditions of the terrain on which it landed, are major factors to beconsidered in determining the method of recovery.The other factors are :

A. Immediate availability of lifting equipment

B. Urgency of removal

C. The necessity of reducing the weight of the aircraft to ensure a safelifting operation.

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SEP 30/92

DAMAGE CONTROL AND SAFETY

1. General

All necessary precautions must be taken when carrying out recovery operationson crashed aircraft to avoid injury to personnel or damage to equipment.

WARNING : IT IS STRICTLY FORBIDDEN TO SMOKE OR EXPOSE NAKED LIGHTS.

2. Batteries

WARNING : PRIOR TO STARTING RECOVERY PROPER, DISCONNECT AND REMOVE ALLAIRCRAFT BATTERIES ; IF REMOVAL IS NOT POSSIBLE, DISCONNECT ANDINSULATE THE BATTERY GROUND TO AVOID ACCIDENTS WHICH MAY ARISEBECAUSE OF SHORT CIRCUITS.

3. Oxygen

WARNING : A WARNING NOTICE SHALL BE INSTALLED IN THE WORK AREA. PERSONNELSHALL CLEAN TOOLS AND ENSURE THAT THEIR HANDS ARE CLEAN TO AVOIDCONTAMINATION.STRICTLY PROHIBIT ANY ELECTRICAL POWER SUPPLY ON THE AIRCRAFT.PROHIBIT ANY OPERATION ON THE AIRCRAFT.USE ONLY TOOLS AND EQUIPMENT SPECIFICALLY ALLOCATED FOR HANDLINGOXYGEN.GROUND THE AIRCRAFT ELECTROSTATICALLY AND EFFECT A GROUNDCONNECTION BETWEEN THE EQUIPMENT AND THE AIRCRAFT.PERSONNEL IN CHARGE OF CARRYING OUT THE ACTIONS BELOW MUST BE AWAREOF THE RISKS INVOLED IN HANDLING OXYGEN WHICH ENHANCES COMBUSTIONIN THE PRESENCE OF FUEL, AND BECOMES EXPLOSIVE IN THE PRESENCE OFHYDROCARBONS (FUELS, LUBRICANTS).

4. Fuel Tank Defueling

WARNING : BEFORE PROCEEDING WITH MAINTENANCE WORK ON OR NEAR MECHNICAL FLIGHTCONTROLS OR PRIMARY FLIGHT CONTROL SURFACES, LANDING GEARS,ASSOCIATED DOORS OR ANY MOVING COMPONENT, MAKE CERTAIN THAT GROUNDSAFETIES AND/OR WARNING NOTICES ARE IN CORRECT POSITION TO PREVENTINADVERTENT OPERATION OF CONTROLS.BEFORE POWER IS SUPPLIED TO THE AIRCRAFT MAKE CERTAIN THATELECTRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS ARE ISOLATED.BEFORE PRESSURIZING FUEL SYSTEMS, MAKE CERTAIN THAT FUEL SYSTEMUNDER MAINTENANCE HAS BEEN ISOLATED.CHECK THAT THE LANDING GEAR GROUND SAFETIES INCLUDING WHEEL CHOCKSARE IN POSITION.

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SEP 30/92

BEFORE UNDERTAKING MAINTENANCE OPERATIONS ON THE FUEL SYSTEM, MAKECERTAIN THAT FIRE FIGHTING EQUIPMENT IS READILY AVAILABLE AND INPROXIMITY TO THE WORK AREA.BEFORE CONNECTING THE TANKER'S REFUELING HOSE TO THE AIRCRAFT, MAKECERTAIN THAT BOTH THE TANKER AND THE AIRCRAFT ARE CORRECTLYCONNECTED TO AN APPROVED GROUND AND THAT ELECTRICAL BONDING BETWEENTHE AIRCRAFT AND THE TANKER IS EFFECTED.

5. External Power

WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT, MAKE CERTAIN THATELECTRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS ARE ISOLATED.

WARNING : IT IS FORBIDDEN TO DISCONNECT THE GROUND POWER UNIT CONNECTOR WHENTHE CIRCUIT IS ENERGIZED AS THIS COULD CAUSE ARCING WHICH WOULD BEDANGEROUS FOR PERSONNEL, OR DAMAGE TO EQUIPMENT. CUT OFF THEELECTRICAL SUPPLY BEFORE DISCONNECTING THE GROUND POWER UNITCONNECTOR.

WARNING : WITH ELECTRICAL NETWORK ENERGIZED AND NLG SHOCK ABSORBER EXTENDEDTHE BLUE HYD. SYS. ELECTRIC PUMP WILL AUTOMATICALLY RUN.OPEN, SAFETY AND TAG C/B 2701 GJ AND 2702 GJ TO ISOLATE THE PUMP.

6. Towing

WARNING : BEFORE POSITIONING THE LOCKING DEVICES, MAKE CERTAIN THAT THELANDING GEAR IS DOWNLOCKED.

CAUTION : THE LANDING GEAR BRACE STRUT LOCKING DEVICES MUST ALWAYS BE FITTEDWHEN THE AIRCRAFT IS ON THE GROUND OR BEING TOWED.USE ONLY TOWING EQUIPMENT DESIGNED OR APPROVED BY THE AIRCRAFTMANUFACTURER.

Printed in France


2-30Page 1

SEP 30/92

WEIGHT AND H-ARM MANUAL

1. General

An accurate knowledge of the weight and horizontal arm from station 0 (zero)(h-arm) location of a damaged aircraft is essential to determine the requiredcapacity of lifting and transportation facilities. In practically all cases,it is advisable to reduce the weight of the aircraft as much as possible byremoving fuel and water, cargo and in certain cases some major aircraftcomponents : engines, flight surfaces etc...

2. Lifting weight of the Aircraft

A. Definition

The aircraft lifting weight (REW = Recoverable Empty Weight) is theaircraft empty weight (MEW = Manufacturer's Empty Weight) plus the weightof various items of operational equipment that are an integral part of theaircraft.

The Manufacturer's Empty Weight is the dry weight (without fuel)guaranteed by the manufacturer. The H-arm is given with the aircraftconsidered in gears extended, flaps and slats retracted configuration.

B. Determination of the Lifting Weight

Obtain from the Weight and Balance Manual (WBM) the MEW of the consideredaircraft.

Obtain from this WBM supplement the weight of particular items ofequipment.

The sum of these different weights is the REW (Recoverable Empty Weight).

Printed in France


2-30Page 2

OCT 30/93

EMPTY WEIGHT REVISION AND H-ARM LOCATION COMPUTATION

1. Revised REW

With the REW having been computed as per page 1, subtract from the weightobtained, the weight of the various components or items or equipment of theaircraft in question which have been removed to reduce the weight of theaircraft or which have been torn off or lost during the accident.The weights of such equipment are given in the Weight and Balance Manual(WBM).The weights of major components of the aircraft which may be removed or tornoff in the accident are given in section 2-31 fig. 1 and 1A.

2. H-arm Location Computation

Using the data of the Weight and Balance Manual (WBM)Compute the moments of :

a) The Manufacturer's Empty Weight (MEW)

b) The various items of equipment remaining on board.

– Sum up these momentsMoment = Weight × H-arm Location

– Sum up the aircraft empty weight and the weight of the equipmentremaining on board.

– Determine the location

H-arm = Sum of the momentsSum of the weights

– Convert H-arm into %RC (Reference Chord).

%RC = H-arm − 34.5320.0727

With the RC percentage obtained for the complete aircraft :

– Using section 2-31, note any variations in H-arm location caused bycomponents having been torn off in the accident or removed.

– Using the table in section 2-31, note any variations in H-arm locationdue to the position of the nose gear, the flaps and the slats.

– Compute the algebraic sum of these values.

– Add or subtract, according to the sign, this sum to the %RC previouslyobtained ; the H-arm location is obtained in percentage of RC of theconsidered aircraft.

Printed in France


2-31Page 1

OCT 30/93

EFFECTS OF MOVING COMPONENTS ON THE AIRCRAFT CG

Balance effects caused by operation of slats, flaps, thrust reverser andlanding gears are given below.

A. Slats and flaps extension

COCKPIT INDICATION (°) MOMENTS

SLATSINBOARD/OUTBOARD

FLAPS SLATS FLAPS TOTAL

Kgm FtLb Kgm FtLb Kgm FtLb

14/16 0 − 498 − 3602 0 0 − 498 − 3602

14/16 8 − 498 − 3602 + 823 + 5953 + 325 + 2351

17.7/20 14 − 638 − 4615 + 966 + 6987 + 328 + 2372

19.6/23 22 − 719 − 5201 + 1087 + 7862 + 368 + 2662

19.6/23 32 − 719 − 5201 + 1195 + 8643 + 476 + 3443

B. Thrust reverser extension

Thrust reverser = Negligeable

C. Landing gear retraction

MOMENTS

NLG MLG

Kgm FtLb Kgm FtLb

− 974 − 7045 − 3372 − 24390

Printed in France


2-31Page 2

OCT 30/93

WEIGHT AND AIRCRAFT CG VARIATIONS DUE TO ANY FLUIDSABOARD OTHER THAN FUEL

1. Waste tanks

ITEMWEIGHT H-ARM MOMENTS

(kg) (lb) (m) ft Kgm FtLb

Tank No 1 350 771.61 56.914 186.723 19 920 144 077

Tank No 2 350 771.61 57.696 189.289 20 194 146 057

2. Potable water

ITEMWEIGHT H-ARM MOMENTS


Tank No 1 350 771.61 44.470 145.897 15 565 112 576

Tank No 2 350 771.61 57.021 187.074 19 957 144 346

3. Hydraulic system fluid

LOCATIONWEIGHT H-ARM MOMENTS


Tanksa) Greenb) Yellowc) Blue

282417

61.7352.9137.48

39.56535.40735.407

129.804116.163116.163

1 108850602

8 0006 1464 354

Systems 426 939.16 38.242 125.464 16 291 117 833

Aircraft total 495 1 091.27 38.082 124.939 18 851 136 349

Printed in France


2-31Page 3

OCT 30/93

WEIGHT AND AIRCRAFT CG VARIATIONS DUE TO CARGO ABOARD

1. Establish the mass of the containers or pallets remaining in each cargocompartment.

2. In order to determine the effect of this cargo on the aircraft CG locationproceed as mentioned in section 2-33, pages 1 to 3 (read ″cargo″ instead of″fuel″ in the corresponding applicable text and formula).

Using the following tables the masses of each container or pallet arespecified in increments of 250 kg (551 lb) or 500 kg (1 102 lb) for easyinterpolation. The values in column ″H-ARM″ represent the distance of the CGof each container or pallet to the point about which the resulting "MOMENTS"are being taken.

Adjusting the masses of the cargo load can reduce the lifting load by theCARGO MOMENTS listed in the following tables :

Printed in France


2-31Page 4

OCT 30/93

CARGO MOMENTS

1. FWD Cargo CompartmentA. Half Size Containers (NAS 3610.2K1C, 2K2C) 60.4 × 61.5 in MAX IATA

contour E, G.

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11 R+L

1 5871 2501 000750500250

15.43215.43215.43215.43215.43215.432

24 49119 29015 43211 5747 7163 858

3 5002 7562 2051 6531 102551

50.62950.62950.62950.62950.62950.629

177 201139 534111 63783 69055 79327 897

---------------------------------------------- ----------------------------------

12 R+L

1 5871 2501 000750500250

17.21817.21817.21817.21817.21817.218

27 32521 52217 21812 9138 6094 304

3 5002 7562 2051 6531 102551

56.48956.48956.48956.48956.48956.489

197 711155 684124 55893 37662 25131 125

---------------------------------------------- ----------------------------------

13 R+L

1 5871 2501 000750500250

18.80118.80118.80118.80118.80118.801

29 83723 50118 80114 1019 4004 700

3 5002 7562 2051 6531 102551

61.68261.68261.68261.68261.68261.682

215 887169 996136 009101 96067 97433 987

---------------------------------------------- ----------------------------------

21 R+L

1 5871 2501 000750500250

20.56320.56320.56320.56320.56320.563

32 63325 70420 56315 42210 2815 141

3 5002 7562 2051 6531 102551

67.46367.46367.46367.46367.46367.463

236 120185 928148 756111 51674 34437 172

---------------------------------------------- ----------------------------------

22 R+L

1 5871 2501 000750500250

22.14622.14622.14622.14622.14622.146

35 14627 68222 14616 60911 0735 536

3 5002 7562 2051 6531 102551

72.65772.65772.65772.65772.65772.657

254 300200 242160 209120 10280 06840 034

---------------------------------------------- ----------------------------------

23 R+L

1 5871 2501 000750500250

23.72823.72823.72823.72823.72823.728

37 65629 66023 72817 79611 8645 932

3 5002 7562 2051 6531 102551

77.84777.84777.84777.84777.84777.847

272 464214 546171 653128 68185 78742 894

---------------------------------------------- ----------------------------------

24 R+L

1 5871 2501 000750500250

25.49125.49125.49125.49125.49125.491

40 45431 86425 49119 11812 7456 373

3 5002 7562 2051 6531 102551

83.63183.63183.63183.63183.63183.631

292 708230 487184 406138 24292 16146 081

---------------------------------------------- ----------------------------------

25 R+L

1 5871 2501 000750500250

27.07327.07327.07327.07327.07327.073

42 96533 84127 07320 30513 5366 768

3 5002 7562 2051 6531 102551

88.82188.82188.82188.82188.82188.821

310 873244 791195 850146 82197 88148 940

---------------------------------------------- ----------------------------------

26 R+L

1 5871 2501 000750500250

28.65528.65528.65528.65528.65528.655

45 47535 81928 65521 49114 3277 164

3 5002 7562 2051 6531 102551

94.01194.01194.01194.01194.01194.011

329 038259 094207 294155 400103 60051 800

Printed in France


2-31Page 5

OCT 30/93

CARGO MOMENTS

B. Half Size Containers (NAS 3610.2K1C, 2K2C) 60.4 × 61.5 in MAX IATAcontour C, H.

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11R or L

1 5871 2501 000750500250

15.43215.43215.43215.43215.43215.432

24 49119 29015 43211 5747 7163 858

3 5002 7562 2051 6531 102551

50.62950.62950.62950.62950.62950.629

177 201139 534111 63783 69055 79327 897

---------------------------------------------- ----------------------------------

12R or L

1 5871 2501 000750500250

17.21817.21817.21817.21817.21817.218

27 32521 52217 21812 9138 6094 304

3 5002 7562 2051 6531 102551

56.48956.48956.48956.48956.48956.489

197 711155 684124 55893 37662 25131 125

---------------------------------------------- ----------------------------------

13R or L

1 5871 2501 000750500250

18.80118.80118.80118.80118.80118.801

29 83723 50118 80114 1019 4004 700

3 5002 7562 2051 6531 102551

61.68261.68261.68261.68261.68261.682

215 887169 996136 009101 96067 97433 987

---------------------------------------------- ----------------------------------

21R or L

1 5871 2501 000750500250

20.56320.56320.56320.56320.56320.563

32 63325 70420 56315 42210 2815 141

3 5002 7562 2051 6531 102551

67.46367.46367.46367.46367.46367.463

236 120185 928148 756111 51674 34437 172

---------------------------------------------- ----------------------------------

22R or L

1 5871 2501 000750500250

22.14622.14622.14622.14622.14622.146

35 14627 68222 14616 60911 0735 536

3 5002 7562 2051 6531 102551

72.65772.65772.65772.65772.65772.657

254 300200 242160 209120 10280 06840 034

---------------------------------------------- ----------------------------------

23R or L

1 5871 2501 000750500250

23.72823.72823.72823.72823.72823.728

37 65629 66023 72817 79611 8645 932

3 5002 7562 2051 6531 102551

77.84777.84777.84777.84777.84777.847

272 464214 546171 653128 68185 78742 894

---------------------------------------------- ----------------------------------

24R or L

1 5871 2501 000750500250

25.49125.49125.49125.49125.49125.491

40 45431 86425 49119 11812 7456 373

3 5002 7562 2051 6531 102551

83.63183.63183.63183.63183.63183.631

292 708230 487184 406138 24292 16146 081

---------------------------------------------- ----------------------------------

25R or L

1 5871 2501 000750500250

27.07327.07327.07327.07327.07327.073

42 96533 84127 07320 30513 5366 768

3 5002 7562 2051 6531 102551

88.82188.82188.82188.82188.82188.821

310 873244 791195 850146 82197 88148 940

---------------------------------------------- ----------------------------------

26R or L

1 5871 2501 000750500250

28.65528.65528.65528.65528.65528.655

45 47535 81928 65521 49114 3277 164

3 5002 7562 2051 6531 102551

94.01194.01194.01194.01194.01194.011

329 038259 094207 294155 400103 60051 800

Printed in France


2-31Page 6

OCT 30/93

CARGO MOMENTS

C. Full Size Containers (NAS 3610-2L1C, 2L2C) 60.4 × 125 in MAX IATA contour F.

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11

3 1742 5002 0001 5001 000500

15.43215.43215.43215.43215.43215.432

48 98138 58030 86423 14815 4327 716

7 0005 5114 4093 3072 2051 102

50.62950.62950.62950.62950.62950.629

354 403279 016223 223167 430111 63755 793

---------------------------------------------- ----------------------------------

12

3 1742 5002 0001 5001 000500

17.21817.21817.21817.21817.21817.218

54 65043 04534 43625 82717 2188 609

7 0005 5114 4093 3072 2051 102

56.48956.48956.48956.48956.48956.489

395 423311 311249 060186 809124 55862 251

---------------------------------------------- ----------------------------------

13

3 1742 5002 0001 5001 000500

18.80118.80118.80118.80118.80118.801

59 67447 00237 60228 20118 8019 400

7 0005 5114 4093 3072 2051 102

61.68261.68261.68261.68261.68261.682

431 774339 929271 956203 982136 00967 974

---------------------------------------------- ----------------------------------

21

3 1742 5002 0001 5001 000500

20.56320.56320.56320.56320.56320.563

65 26751 40741 12630 84420 56310 281

7 0005 5114 4093 3072 2051 102

67.46367.46367.46367.46367.46367.463

472 241371 789297 444223 100148 75674 344

---------------------------------------------- ----------------------------------

22

3 1742 5002 0001 5001 000500

22.14622.14622.14622.14622.14622.146

70 29155 36544 29233 21922 14611 073

7 0005 5114 4093 3072 2051 102

72.65772.65772.65772.65772.65772.657

508 599400 489320 345240 277160 20980 068

---------------------------------------------- ----------------------------------

23

3 1742 5002 0001 5001 000500

23.72823.72823.72823.72823.72823.728

75 31359 32047 45635 59223 72811 864

7 0005 5114 4093 3072 2051 102

77.84777.84777.84777.84777.84777.847

544 929429 015343 227257 440171 65385 787

---------------------------------------------- ----------------------------------

24

3 1742 5002 0001 5001 000500

25.49125.49125.49125.49125.49125.491

80 90863 72750 98238 23625 49112 745

7 0005 5114 4093 3072 2051 102

83.63183.63183.63183.63183.63183.631

585 417460 890368 729276 568184 40692 161

---------------------------------------------- ----------------------------------

25

3 1742 5002 0001 5001 000500

27.07327.07327.07327.07327.07327.073

85 93067 68254 14640 60927 07313 536

7 0005 5114 4093 3072 2051 102

88.82188.82188.82188.82188.82188.821

621 747489 493391 612293 731195 85097 881

---------------------------------------------- ----------------------------------

26

3 1742 5002 0001 5001 000500

28.65528.65528.65528.65528.65528.655

90 95171 63757 31042 98228 65514 327

7 0005 5114 4093 3072 2051 102

94.01194.01194.01194.01194.01194.011

658 077518 095414 494310 894207 294103 600

Printed in France


2-31Page 7

OCT 30/93

CARGO MOMENTS

D. Full Size Containers (NAS 3610-2A2C, 2A6C) 88 × 125 in MAX IATAcontour F.

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11P

4 6264 0003 5003 0002 5002 0001 5001 000500

15.78315.78315.78315.78315.78315.78315.78315.78315.783

73 01263 13255 24047 34939 45731 56623 67415 7837 891

10 2008 8187 7166 6145 5114 4093 3072 2051 102

51.78151.78151.78151.78151.78151.78151.78151.78151.781

528 166456 605399 542342 480285 365228 302171 240114 17757 063

---------------------------------------------- ----------------------------------

12P

4 6264 0003 5003 0002 5002 0001 5001 000500

18.45018.45018.45018.45018.45018.45018.45018.45018.450

85 35073 80064 57555 35046 12536 90027 67518 4509 225

10 2008 8187 7166 6145 5114 4093 3072 2051 102

60.53160.53160.53160.53160.53160.53160.53160.53160.531

617 416533 762467 057400 352333 586266 881200 176133 47166 705

---------------------------------------------- ----------------------------------

21P

4 6264 0003 5003 0002 5002 0001 5001 000500

20.91420.91420.91420.91420.91420.91420.91420.91420.914

96 74883 65673 19962 74252 28541 82831 37120 91410 457

10 2008 8187 7166 6145 5114 4093 3072 2051 102

68.61568.61568.61568.61568.61568.61568.61568.61568.615

699 873605 047529 433453 820378 137302 523226 910151 29675 614

---------------------------------------------- ----------------------------------

22P

4 6264 0003 5003 0002 5002 0001 5001 000500

23.37723.37723.37723.37723.37723.37723.37723.37723.377

108 14293 50881 81970 13158 44246 75435 06523 37711 688

10 2008 8187 7166 6145 5114 4093 3072 2051 102

76.69576.69576.69576.69576.69576.69576.69576.69576.695

782 289676 296591 779507 261422 666338 148253 630169 11284 518

---------------------------------------------- ----------------------------------

23P

4 6264 0003 5003 0002 5002 0001 5001 000500

25.84125.84125.84125.84125.84125.84125.84125.84125.841

119 540103 36490 44377 52364 60251 68238 76125 84112 920

10 2008 8187 7166 6145 5114 4093 3072 2051 102

84.77984.77984.77984.77984.77984.77984.77984.77984.779

864 746747 581654 155560 728467 217373 791280 364186 93893 426

---------------------------------------------- ----------------------------------

24P

4 6264 0003 5003 0002 5002 0001 5001 000500

28.30528.30528.30528.30528.30528.30528.30528.30528.305

130 939113 22099 06784 91570 76256 61042 45728 30514 152

10 2008 8187 7166 6145 5114 4093 3072 2051 102

92.86392.86392.86392.86392.86392.86392.86392.86392.863

947 203818 866716 531614 196511 768409 433307 098204 763102 335

Printed in France


2-31Page 8

OCT 30/93

CARGO MOMENTS

E. Full Size Containers (NAS 3610-2M1C, 2M3C) 96 × 125 in MAX IATA contour F

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

15.88515.88515.88515.88515.88515.88515.88515.88515.88515.885

81 06171 48263 54055 59747 65539 71231 77023 82715 8857 942

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

52.11552.11552.11552.11552.11552.11552.11552.11552.11552.115

586 294516 981459 550402 119344 689287 206229 775172 344114 91457 431

------------------------------------------------- ------------------------------------

12P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

18.34818.34818.34818.34818.34818.34818.34818.34818.34818.348

93 63082 56673 39264 21855 04445 87036 69627 52218 3489 174

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

60.19660.19660.19660.19660.19660.19660.19660.19660.19660.196

677 205597 144530 808464 472398 136331 740265 404199 068132 73266 336

------------------------------------------------- ------------------------------------

21P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

20.81220.81220.81220.81220.81220.81220.81220.81220.81220.812

106 20493 65483 24872 84262 43652 03041 62431 21820 81210 406

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

68.28068.28068.28068.28068.28068.28068.28068.28068.28068.280

768 150677 338602 093526 848451 604376 291301 046225 802150 55775 245

------------------------------------------------- ------------------------------------

22P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

23.27623.27623.27623.27623.27623.27623.27623.27623.27623.276

118 777104 74293 10481 46669 82858 19046 55234 91423 27611 638

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

76.36376.36376.36376.36376.36376.36376.36376.36376.36376.363

859 084757 521673 369589 217505 065420 836336 684252 532168 38084 152

------------------------------------------------- ------------------------------------

23P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

25.74025.74025.74025.74025.74025.74025.74025.74025.74025.740

131 351115 830102 96090 09077 22064 35051 48038 61025 74012 870

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

84.44884.44884.44884.44884.44884.44884.44884.44884.44884.448

950 040837 724744 662651 601558 539465 393372 331279 269186 20893 062

------------------------------------------------- ------------------------------------

24P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

28.20328.20328.20328.20328.20328.20328.20328.20328.20328.203

143 920126 913112 81298 71084 60970 50756 40642 30428 20314 101

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

92.52892.52892.52892.52892.52892.52892.52892.52892.52892.528

1 040 940917 878815 912713 946611 980509 922407 956305 990204 024101 966

Printed in France


2-31Page 9

OCT 30/93

CARGO MOMENTS

F. Half Size Pallets (NAS 3610-2K3P) 60.4 × 61.5 in

PALLETPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11 R + L

1 5871 2501 000750500250

15.43215.43215.43215.43215.43215.432

24 49119 29015 43211 5747 7163 858

3 5002 7562 2051 6531 102551

50.62950.62950.62950.62950.62950.629

177 201139 534111 63783 69055 79327 897

---------------------------------------------- ----------------------------------

12 R + L

1 5871 2501 000750500250

17.21817.21817.21817.21817.21817.218

27 32521 52217 21812 9138 6094 304

3 5002 7562 2051 6531 102551

56.48956.48956.48956.48956.48956.489

197 711155 684124 55893 37662 25131 125

---------------------------------------------- ----------------------------------

13 R + L

1 5871 2501 000750500250

18.80118.80118.80118.80118.80118.801

29 83723 50118 80114 1019 4004 700

3 5002 7562 2051 6531 102551

61.68261.68261.68261.68261.68261.682

215 887169 996136 009101 96067 97433 987

---------------------------------------------- ----------------------------------

21 R + L

1 5871 2501 000750500250

20.56320.56320.56320.56320.56320.563

32 63325 70420 56315 42210 2825 141

3 5002 7562 2051 6531 102551

67.46367.46367.46367.46367.46367.463

236 120185 928148 756111 51674 34437 172

---------------------------------------------- ----------------------------------

22 R + L

1 5871 2501 000750500250

22.14622.14622.14622.14622.14622.146

35 14627 68222 14616 60911 0735 536

3 5002 7562 2051 6531 102551

72.65772.65772.65772.65772.65772.657

254 300200 242160 209120 10280 06840 034

---------------------------------------------- ----------------------------------

23 R + L

1 5871 2501 000750500250

23.72823.72823.72823.72823.72823.728

37 65629 66023 72817 79611 8645 932

3 5002 7562 2051 6531 102551

77.84777.84777.84777.84777.84777.847

272 464214 546171 653128 68185 78742 894

---------------------------------------------- ----------------------------------

24 R + L

1 5871 2501 000750500250

25.49125.49125.49125.49125.49125.491

40 45431 86425 49119 11812 7456 373

3 5002 7562 2051 6531 102551

83.63183.63183.63183.63183.63183.631

292 708230 487184 406138 24292 16146 081

---------------------------------------------- ----------------------------------

25 R + L

1 5871 2501 000750500250

27.07327.07327.07327.07327.07327.073

42 96533 84127 07320 30513 5366 768

3 5002 7562 2051 6531 102551

88.82188.82188.82188.82188.82188.821

310 873244 791195 850146 82197 88148 940

---------------------------------------------- ----------------------------------

26 R + L

1 5871 2501 000750500250

28.65528.65528.65528.65528.65528.655

45 47535 81928 65521 49114 3277 164

3 5002 7562 2051 6531 102551

94.01194.01194.01194.01194.01194.011

329 038259 094207 294155 400103 60051 800

Printed in France


2-31Page 10

OCT 30/93

CARGO MOMENTS

G. Full Size Pallets (NAS 3610-2L3, 2L4P) 60.4 × 125 in

PALLETPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11

3 1742 5002 0001 5001 000500

15.43215.43215.43215.43215.43215.432

49 98238 58030 86423 14815 4327 716

7 0005 5114 4093 3072 2051 102

50.62950.62950.62950.62950.62950.629

354 403279 016223 223167 430111 63655 793

---------------------------------------------- ----------------------------------

12

3 1742 5002 0001 5001 000500

17.21817.21817.21817.21817.21817.218

54 65048 04534 43625 82717 2188 609

7 0005 5114 4093 3072 2051 102

56.48956.48956.48956.48956.48956.489

395 423311 311249 060186 809124 55862 251

---------------------------------------------- ----------------------------------

13

3 1742 5002 0001 5001 000500

18.80118.80118.80118.80118.80118.801

59 67447 00237 60228 20118 8019 400

7 0005 5114 4093 3072 2051 102

61.68261.68261.68261.68261.68261.682

431 774339 929271 956203 982136 00967 974

---------------------------------------------- ----------------------------------

21

3 1742 5002 0001 5001 000500

20.56320.56320.56320.56320.56320.563

65 26751 40741 12630 84420 56310 281

7 0005 5114 4093 3072 2051 102

67.46367.46367.46367.46367.46367.463

472 241371 789297 444223 100148 75674 344

---------------------------------------------- ----------------------------------

22

3 1742 5002 0001 5001 000500

22.14622.14622.14622.14622.14622.146

70 29155 36544 29233 21922 14611 073

7 0005 5114 4093 3072 2051 102

72.65772.65772.65772.65772.65772.657

508 599400 413320 345240 277160 20980 068

---------------------------------------------- ----------------------------------

23

3 1742 5002 0001 5001 000500

23.72823.72823.72823.72823.72823.728

75 31359 32047 45635 59223 72811 824

7 0005 5114 4093 3072 2051 102

77.84777.84777.84777.84777.84777.847

544 929429 015343 227257 440171 65385 787

---------------------------------------------- ----------------------------------

24

3 1742 5002 0001 5001 000500

25.49125.49125.49125.49125.49125.491

80 90863 72750 98238 23625 49112 745

7 0005 5114 4093 3072 2051 102

83.63183.63183.63183.63183.63183.631

585 417460 890368 729276 568184 40692 161

---------------------------------------------- ----------------------------------

25

3 1742 5002 0001 5001 000500

27.07327.07327.07327.07327.07327.073

85 93067 68254 14640 60927 07313 536

7 0005 5114 4093 3072 2051 102

88.82188.82188.82188.82188.82188.821

621 747489 493390 730293 731195 85097 881

---------------------------------------------- ----------------------------------

26

3 1742 5002 0001 5001 000500

28.65528.65528.65528.65528.65528.655

90 95171 63757 31042 98228 65514 327

7 0005 5114 4093 3072 2051 102

94.01194.01194.01194.01194.01194.011

658 077518 095414 494310 894207 294103 600

Printed in France


2-31Page 11

OCT 30/93

CARGO MOMENTS

H. Full Size Pallets (NAS 3610-2A1, 2A2, 2A3, 2A4, 2A6P) 88 × 125 in

PALLETPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11P

4 6264 0003 5003 0002 5002 0001 5001 000500

15.78315.78315.78315.78315.78315.78315.78315.78315.783

73 01263 13255 24047 34939 45731 56623 67415 7837 891

10 2008 8187 7166 6145 5114 4093 3072 2051 102

51.78051.78051.78051.78051.78051.78051.78051.78051.780

528 156456 596399 534342 473285 360228 298171 236114 17557 062

---------------------------------------------- ----------------------------------

12P

4 6264 0003 5003 0002 5002 0001 5001 000500

18.45018.45018.45018.45018.45018.45018.45018.45018.450

85 35073 88064 57555 35046 12536 90027 67518 4509 225

10 2008 8187 7166 6145 5114 4093 3072 2051 102

60.53060.53060.53060.53060.53060.53060.53060.53060.530

617 406533 754467 049400 345333 581266 877200 173133 46966 704

---------------------------------------------- ----------------------------------

21P

4 6264 0003 5003 0002 5002 0001 5001 000500

20.91420.91420.91420.91420.91420.91420.91420.91420.914

96 74883 65673 19962 74252 28541 82831 37120 91410 457

10 2008 8187 7166 6145 5114 4093 3072 2051 102

68.61468.61468.61468.61468.61468.61468.61468.61468.614

699 863605 038529 426453 813378 132302 519226 906151 29475 613

---------------------------------------------- ----------------------------------

22P

4 6264 0003 5003 0002 5002 0001 5001 000500

23.37723.37723.37723.37723.37723.37723.37723.37723.377

108 14293 50881 81970 13158 44246 75435 06523 37711 688

10 2008 8187 7166 6145 5114 4093 3072 2051 102

76.69576.69576.69576.69576.69576.69576.69576.69576.695

782 289676 297591 779507 261422 666338 148253 630169 11284 518

---------------------------------------------- ----------------------------------

23P

4 6264 0003 5003 0002 5002 0001 5001 000500

25.84125.84125.84125.84125.84125.84125.84125.84125.841

119 540103 36490 44377 52364 60251 68238 76125 84112 920

10 2008 8187 7166 6145 5114 4093 3072 2051 102

84.77984.77984.77984.77984.77984.77984.77984.77984.779

864 746747 581654 155560 728467 217373 791280 364186 93893 426

---------------------------------------------- ----------------------------------

24P

4 6264 0003 5003 0002 5002 0001 5001 000500

28.30528.30528.30528.30528.30528.30528.30528.30528.305

130 939113 22099 06784 91570 76256 61042 45728 30514 152

10 2008 8187 7166 6145 5114 4093 3072 2051 102

92.86392.86392.86392.86392.86392.86392.86392.86392.863

947 203818 866716 531614 196511 768409 433307 098204 763102 335

Printed in France


2-31Page 12

OCT 30/93

CARGO MOMENTS

I. Full Size Pallets (NAS 3610-2M1, 2M2, 2M3P) 96 × 125 in

PALLETPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

11P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

15.88515.88515.88515.88515.88515.88515.88515.88515.88515.885

81 06171 48263 54055 59747 65539 71231 77023 82715 8857 942

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

52.11552.11552.11552.11552.11552.11552.11552.11552.11552.115

586 294516 981459 550402 119344 689287 258229 775172 344114 91457 431

---------------------------------------------- ----------------------------------

12P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

18.34818.34818.34818.34818.34818.34818.34818.34818.34818.348

93 63082 56673 39264 21855 04445 87036 69627 52218 3489 174

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

60.19660.19660.19660.19660.19660.19660.19660.19660.19660.196

677 205597 144530 808464 472398 136331 740265 404199 068132 73266 336

---------------------------------------------- ----------------------------------

21P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

20.81220.81220.81220.81220.81220.81220.81220.81220.81220.812

106 20493 65483 24872 84262 43652 03041 62431 21820 81210 406

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

68.28068.28068.28068.28068.28068.28068.28068.28068.28068.280

768 150677 338602 093526 848451 604376 291301 047225 802150 55775 245

---------------------------------------------- ----------------------------------

22P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

23.27623.27623.27623.27623.27623.27623.27623.27623.27623.276

118 777104 74293 10481 46669 82658 19046 55234 91423 27611 638

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

76.36476.36476.36476.36476.36476.36476.36476.36476.36476.364

859 095757 531673 378589 225505 071420 842336 689252 536168 38384 153

---------------------------------------------- ----------------------------------

23P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

25.74025.74025.74025.74025.74025.74025.74025.74025.74025.740

131 351115 830102 96090 09077 22064 35051 48038 61025 74012 874

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

84.44884.44884.44884.44884.44884.44884.44884.44884.44884.448

950 040837 724744 662651 601558 539465 393372 331279 270186 20893 062

---------------------------------------------- ----------------------------------

24P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

28.20328.20328.20328.20328.20328.20328.20328.20328.20328.203

143 920126 913112 81298 71084 60970 50756 40642 30428 20314 101

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

92.52892.52892.52892.52892.52892.52892.52892.52892.52892.528

1 040 940917 878815 912713 946611 980509 922407 956305 990204 024101 956

Printed in France


2-31Page 13

OCT 30/93

CARGO MOMENTS

2. AFT Cargo Compartment

A. Half Size Containers (NAS 3610-2K1C, 2K2C) 60.4 × 61.5 in MAX IATAContour E.G.

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31 R + L

1 5871 2501 000750500250

40.88940.88940.88940.88940.88940.889

64 89151 11140 88930 66720 44410 222

3 5002 7562 2051 6531 102551

134.149134.149134.149134.149134.149134.149

469 521369 715295 799221 748147 83273 916

---------------------------------------------- ----------------------------------

32 R + L

1 5871 2501 000750500250

43.35243.35243.35243.35243.35243.352

68 80054 19043 35232 51421 67610 838

3 5002 7562 2051 6531 102551

142.229142.229142.229142.229142.229142.229

497 801391 983313 615235 105156 73678 368

---------------------------------------------- ----------------------------------

33 R + L

1 5871 2501 000750500250

44.93544.93544.93544.93544.93544.935

71 31256 16944 93533 70122 46711 234

3 5002 7562 2051 6531 102551

147.423147.423147.423147.423147.423147.423

515 980406 298325 068243 690162 46081 230

---------------------------------------------- ----------------------------------

34 R + L

1 5871 2501 000750500250

46.51746.51746.51746.51746.51746.517

73 82258 14646 51734 88823 25811 629

3 5002 7562 2051 6531 102551

152.613152.613152.613152.613152.613152.613

534 145420 601336 512252 269168 18084 090

---------------------------------------------- ----------------------------------

41 R + L

1 5871 2501 000750500250

48.07748.07748.07748.07748.07748.077

76 29860 09648 07736 05825 00012 019

3 5002 7562 2051 6531 102551

157.731157.731157.731157.731157.731157.731

552 058434 707347 797260 729178 82086 910

---------------------------------------------- ----------------------------------

42 R + L

1 5871 2501 000750500250

49.65949.65949.65949.65949.65949.659

78 80962 07449 65937 24424 82912 415

3 5002 7562 2051 6531 102551

162.921162.921162.921162.921162.921162.921

570 223449 010359 241269 308179 53989 769

---------------------------------------------- ----------------------------------

43 R + L

1 5871 2501 000750500250

51.24151.24151.24151.24151.24151.241

81 31964 05151 24138 43125 62012 810

3 5002 7562 2051 6531 102551

168.111168.111168.111168.111168.111168.111

588 388463 314370 685277 887185 25892 629

Printed in France


2-31Page 14

OCT 30/93

CARGO MOMENTS

B. Half Size Containers (NAS 3610-2K1C, 2K2C) 60.4 × 61.5 in MAX IATAContour C.H.

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31R or L

1 5871 2501 000750500250

40.88940.88940.88940.88940.88940.889

64 89151 11140 88930 66720 44410 222

3 5002 7562 2051 6531 102551

134.149134.149134.149134.149134.149134.149

469 521369 715295 799221 748147 83273 916

---------------------------------------------- ----------------------------------

32R or L

1 5871 2501 000750500250

43.35243.35243.35243.35243.35243.352

68 80054 19043 35232 51421 67610 838

3 5002 7562 2051 6531 102551

142.229142.229142.229142.229142.229142.229

497 801391 983313 615235 105156 73678 368

---------------------------------------------- ----------------------------------

33R or L

1 5871 2501 000750500250

44.93544.93544.93544.93544.93544.935

71 31256 16944 93533 70122 46711 234

3 5002 7562 2051 6531 102551

147.423147.423147.423147.423147.423147.423

515 980406 298325 068243 690162 46081 230

---------------------------------------------- ----------------------------------

34R or L

1 5871 2501 000750500250

46.51746.51746.51746.51746.51746.517

73 82258 14646 51734 88823 25811 629

3 5002 7562 2051 6531 102551

152.613152.613152.613152.613152.613152.613

534 145420 601336 512252 269168 18084 090

---------------------------------------------- ----------------------------------

41R or L

1 5871 2501 000750500250

48.07748.07748.07748.07748.07748.077

76 29860 09648 07736 05825 00012 019

3 5002 7562 2051 6531 102551

157.731157.731157.731157.731157.731157.731

552 058434 707347 797260 729178 82086 910

---------------------------------------------- ----------------------------------

42R or L

1 5871 2501 000750500250

49.65949.65949.65949.65949.65949.659

78 80962 07449 65937 24424 82912 415

3 5002 7562 2051 6531 102551

162.921162.921162.921162.921162.921162.921

570 223449 010359 241269 308179 53989 769

---------------------------------------------- ----------------------------------

43R or L

1 5871 2501 000750500250

51.24151.24151.24151.24151.24151.241

81 31964 05151 24138 43125 62012 810

3 5002 7562 2051 6531 102551

168.111168.111168.111168.111168.111168.111

588 388463 314370 685277 887185 25892 629

Printed in France


2-31Page 15

OCT 30/93

CARGO MOMENTS

C. Full Size Containers (NAS 3610-2L1C, 2L2C) 60.4 × 125 in MAX IATA Contour F

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31

3 1742 5002 0001 5001 000500

40.88940.88940.88940.88940.88940.889

129 782102 22281 77861 33340 88920 444

7 0005 5114 4093 3072 2051 102

134.149134.149134.149134.149134.149134.149

939 043739 295591 463443 631295 799147 832

---------------------------------------------- ----------------------------------

32

3 1742 5002 0001 5001 000500

43.35243.35243.35243.35243.35243.352

137 599108 38086 70465 02843 35221 676

7 0005 5114 4093 3072 2051 102

142.229142.229142.229142.229142.229142.229

995 603783 824627 088470 351313 615156 736

---------------------------------------------- ----------------------------------

33

3 1742 5002 0001 5001 000500

44.93544.93544.93544.93544.93544.935

142 624112 33789 87067 40244 93522 467

7 0005 5114 4093 3072 2051 102

147.423147.423147.423147.423147.423147.423

1 031 961812 448649 988487 528325 068162 460

---------------------------------------------- ----------------------------------

34

3 1742 5002 0001 5001 000500

46.51746.51746.51746.51746.51746.517

147 645116 29293 03469 77546 51723 258

7 0005 5114 4093 3072 2051 102

152.613152.613152.613152.613152.613152.613

1 068 291841 050672 871504 691336 512168 180

---------------------------------------------- ----------------------------------

41

3 1742 5002 0001 5001 000500

48.07748.07748.07748.07748.07748.077

152 596120 19296 15472 11548 07724 038

7 0005 5114 4093 3072 2051 102

157.731157.731157.731157.731157.731157.731

1 104 117869 256695 436521 616347 797178 820

---------------------------------------------- ----------------------------------

42

3 1742 5002 0001 5001 000500

49.65949.65949.65949.65949.65949.659

157 617124 14799 31874 48849 65924 829

7 0005 5114 4093 3072 2051 102

162.921162.921162.921162.921162.921162.921

1 140 447897 858718 319538 780359 241179 539

---------------------------------------------- ----------------------------------

43

3 1742 5002 0001 5001 000500

51.24151.24151.24151.24151.24151.241

162 639128 102102 48276 86151 24125 620

7 0005 5114 4093 3072 2051 102

168.111168.111168.111168.111168.111168.111

1 176 777926 460741 201555 943307 685185 258

Printed in France


2-31Page 16

OCT 30/93

CARGO MOMENTS

D. Full Size Containers (NAS 3610-2A2C, 2A6C) 88 × 125 in MAX IATA contour F.

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31P

4 6264 0003 5003 0002 5002 0001 5001 000500

41.23941.23941.23941.23941.23941.23941.23941.23941.239

190 772164 956144 336123 717103 09782 47861 85841 23920 619

10 2008 8187 7166 6145 5114 4093 3072 2051 102

135.297135.297135.297135.297135.297135.297135.297135.297135.297

1 380 0291 193 0491 043 952894 854745 622596 524447 427298 330149 097

---------------------------------------------- ----------------------------------

32P

4 6264 0003 5003 0002 5002 0001 5001 000500

43.70343.70343.70343.70343.70343.70343.70343.70343.703

202 170174 812152 960131 109109 25787 40665 55443 70321 851

10 2008 8187 7166 6145 5114 4093 3072 2051 102

143.380143.380143.380143.380143.380143.380143.380143.380143.380

1 462 2761 264 3251 106 320948 315790 167632 162474 158316 153158 005

---------------------------------------------- ----------------------------------

33P

4 6264 0003 5003 0002 5002 0001 5001 000500

46.16746.16746.16746.16746.16746.16746.16746.16746.167

213 569184 668161 584138 501115 41792 33469 25046 16723 083

10 2008 8187 7166 6145 5114 4093 3072 2051 102

151.465151.465151.465151.465151.465151.465151.465151.465151.465

1 544 9431 335 6181 168 7041 001 790834 724667 809500 895333 980166 914

---------------------------------------------- ----------------------------------

41P

4 6264 0003 5003 0002 5002 0001 5001 000500

48.42748.42748.42748.42748.42748.42748.42748.42748.427

224 023193 708169 494145 281121 06796 85472 64048 42724 213

10 2008 8187 7166 6145 5114 4093 3072 2051 102

158.879158.879158.879158.879158.879158.879158.879158.879158.879

1 620 5661 400 9951 225 9101 050 826875 582700 498525 413350 328175 085

---------------------------------------------- ----------------------------------

42P

4 6264 0003 5003 0002 5002 0001 5001 000500

50.68850.68850.68850.68850.68850.68850.68850.68850.688

234 483202 752177 408152 064126 720101 37676 03250 68825 344

10 2008 8187 7166 6145 5114 4093 3072 2051 102

166.297166.297166.297166.297166.297166.297166.297166.297166.297

1 696 2291 466 4071 283 1481 099 888916 463733 203549 944366 685183 259

Printed in France


2-31Page 17

OCT 30/93

CARGO MOMENTS

E. Full Size Containers (NAS 3610-2M1C, 2M3C) 96 × 125 in MAX IATA Contour F

CONTAINERPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

41.34141.34141.34141.34141.34141.34141.34141.34141.34141.341

210 963186 034165 364144 693124 023103 35282 68262 01141 34120 670

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

135.632135.632135.632135.632135.632135.632135.632135.632135.632135.632

1 525 8601 345 4691 196 0031 046 537897 070747 468598 001448 535299 069149 466

---------------------------------------------- ----------------------------------

32P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

43.80543.80543.80543.80543.80543.80543.80543.80543.80543.805

223 537197 122175 220153 317131 415109 51287 61065 70743 80521 902

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

143.715143.715143.715143.715143.715143.715143.715143.715143.715143.715

1 616 7941 425 6531 267 2791 108 905950 531792 013633 639475 265316 892158 374

---------------------------------------------- ----------------------------------

41P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

48.32648.32648.32648.32648.32648.32648.32648.32648.32648.326

246 608217 467193 304169 141144 978120 81596 65272 48948 32624 163

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

158.548158.548158.548158.548158.548158.548158.548158.548158.548158.548

1 783 6651 572 7961 398 0761 223 3561 048 636873 758699 038524 318349 598174 720

---------------------------------------------- ----------------------------------

42P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

50.78950.78950.78950.78950.78950.78950.78950.78950.78950.789

259 176228 550203 156177 761152 367126 972101 57876 18350 78925 394

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

166.629166.629166.629166.629166.629166.629166.629166.629166.629166.629

1 874 5761 652 9601 469 3351 285 7091 102 084918 292734 667551 042367 417183 625

Printed in France


2-31Page 18

OCT 30/93

CARGO MOMENTS

F. Half Size Pallets (NAS 3610-2K3P) 60.4 × 61.5 in

PALLETPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31 R + L

1 5871 2501 000750500250

40.88940.88940.88940.88940.88940.889

64 89151 11140 88930 66720 44410 222

3 5002 7562 2051 6531 102551

134.149134.149134.149134.149134.149134.149

469 521369 715295 799221 748147 83273 916

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32 R + L

1 5871 2501 000750500250

43.35243.35243.35243.35243.35243.352

68 80054 19043 35232 51421 67610 838

3 5002 7562 2051 6531 102551

142.229142.229142.229142.229142.229142.229

497 801391 983313 615235 105156 73678 368

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33 R + L

1 5871 2501 000750500250

44.93544.93544.93544.93544.93544.935

71 31256 16944 93533 70122 46711 234

3 5002 7562 2051 6531 102551

147.423147.423147.423147.423147.423147.423

515 980406 298325 068243 690162 46081 230

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34 R + L

1 5871 2501 000750500250

46.51746.51746.51746.51746.51746.517

73 82258 14646 51734 51723 25811 629

3 5002 7562 2051 6531 102551

152.613152.613152.613152.613152.613152.613

534 145420 601336 512252 269168 18084 090

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41 R + L

1 5871 2501 000750500250

48.07748.07748.07748.07748.07748.077

76 29860 09648 07736 05825 00012 019

3 5002 7562 2051 6531 102551

157.731157.731157.731157.731157.731157.731

552 058434 707347 797260 729178 82086 910

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42 R + L

1 5871 2501 000750500250

49.65949.65949.65949.65949.65949.659

78 80962 07449 65937 24424 82912 415

3 5002 7562 2051 6531 102551

162.921162.921162.921162.921162.921162.921

570 223449 010359 241269 308179 53989 769

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43 R + L

1 5871 2501 000750500250

51.24151.24151.24151.24151.24151.241

81 31964 05151 24138 43125 62012 810

3 5002 7562 2051 6531 102551

168.111168.111168.111168.111168.111168.111

588 388463 314370 685277 887185 25892 629

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2-31Page 19

OCT 30/93

CARGO MOMENTS

G. Full Size Pallets (NAS 3610-2L3, 2L4P) 60.4 × 125 in

PALLETPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31

3 1742 5002 0001 5001 000500

40.88940.88940.88940.88940.88940.889

129 782102 22281 77861 33340 88920 444

7 0005 5114 4093 3072 2051 102

134.149134.149134.149134.149134.149134.149

939 043739 295591 463443 631295 799147 832

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32

3 1742 5002 0001 5001 000500

43.35243.35243.35243.35243.35243.352

137 599108 38086 70465 02843 35221 676

7 0005 5114 4093 3072 2051 102

142.229142.229142.229142.229142.229142.229

995 603783 824627 088470 351313 615156 736

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3 1742 5002 0001 5001 000500

44.93544.93544.93544.93544.93544.935

142 624112 33789 87067 40244 93522 467

7 0005 5114 4093 3072 2051 102

147.423147.423147.423147.423147.423147.423

1 031 961812 448649 988487 528325 068162 460

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34

3 1742 5002 0001 5001 000500

46.51746.51746.51746.51746.51746.517

147 645116 29293 03469 77546 51723 258

7 0005 5114 4093 3072 2051 102

152.613152.613152.613152.613152.613152.613

1 068 291841 050672 871504 691336 512168 180

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41

3 1742 5002 0001 5001 000500

48.07748.07748.07748.07748.07748.077

152 596120 19296 15472 11548 07724 038

7 0005 5114 4093 3072 2051 102

157.731157.731157.731157.731157.731157.731

1 104 117869 256695 436521 616347 797178 820

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42

3 1742 5002 0001 5001 000500

49.65949.65949.65949.65949.65949.659

157 617124 14799 31874 48849 65924 829

7 0005 5114 4093 3072 2051 102

162.921162.921162.921162.921162.921162.921

1 140 447897 858718 319538 780359 241179 539

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43

3 1742 5002 0001 5001 000500

51.24151.24151.24151.24151.24151.241

162 639128 102102 48276 86151 24125 620

7 0005 5114 4093 3072 2051 102

168.111168.111168.111168.111168.111168.111

1 176 777926 460741 201555 943307 685185 258

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OCT 30/93

CARGO MOMENTS

H. Full Size Pallets (NAS 3610-2A1, 2A2, 2A3, 2A4, 2A6P) 88 × 125 in.

PALLETPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31P

4 6264 0003 5003 0002 5002 0001 5001 000500

41.23941.23941.23941.23941.23941.23941.23941.23941.239

190 772164 956144 336123 717103 09782 41861 85841 23990 619

10 2008 8187 7166 6145 5114 4093 3072 2051 102

135.297135.297135.297135.297135.297135.297135.297135.297135.297

1 380 0291 193 0491 043 952894 854745 622596 524447 427298 330149 097

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32P

4 6264 0003 5003 0002 5002 0001 5001 000500

43.70343.70343.70343.70343.70343.70343.70343.70343.703

202 170174 812152 960131 109109 25787 40665 55443 70321 851

10 2008 8187 7166 6145 5114 4093 3072 2051 102

143.380143.380143.380143.380143.380143.380143.380143.380143.380

1 462 2761 264 3251 106 320948 315790 167632 162474 158316 153158 005

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33P

4 6264 0003 5003 0002 5002 0001 5001 000500

46.16746.16746.16746.16746.16746.16746.16746.16746.167

213 569184 668161 584138 501115 41792 33469 25046 16723 083

10 2008 8187 7166 6145 5114 4093 3072 2051 102

151.465151.465151.465151.465151.465151.465151.465151.465151.465

1 544 9431 335 6181 168 7041 001 790834 724667 809500 895333 980166 914

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41P

4 6264 0003 5003 0002 5002 0001 5001 000500

48.42748.42748.42748.42748.42748.42748.42748.42748.427

224 023193 708169 494145 281121 06796 85472 64048 42724 213

10 2008 8187 7166 6145 5114 4093 3072 2051 102

158.879158.879158.879158.879158.879158.879158.879158.879158.879

1 620 5661 400 9951 225 9101 050 826875 582700 498525 413350 328175 085

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42P

4 6264 0003 5003 0002 5002 0001 5001 000500

50.68850.68850.68850.68850.68850.68850.68850.68850.688

234 483202 752177 408152 064126 720101 37676 03250 68825 344

10 2008 8187 7166 6145 5114 4093 3072 2051 102

166.297166.297166.297166.297166.297166.297166.297166.297166.297

1 696 2291 406 4071 283 1481 099 888916 463733 203549 944366 685183 259

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OCT 30/93

CARGO MOMENTS

I. Full Size Pallets (NAS 3610-2M1, 2M2, 2M3P) 96 × 125 in

PALLETPOSITION

MASSKg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt. Lb

31P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

41.34141.34141.34141.34141.34141.34141.34141.34141.34141.341

210 963186 034165 364144 693124 023103 35282 68262 01141 34120 670

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

135.632135.632135.632135.632135.632135.632135.632135.632135.632135.632

1 525 8601 345 4691 196 0031 046 537897 070747 468598 001448 535299 069149 466

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32P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

43.80543.80543.80543.80543.80543.80543.80543.80543.80543.805

223 537197 122175 220153 317131 415109 51287 61065 70743 80521 902

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

143.715143.715143.715143.715143.715143.715143.715143.715143.715143.715

1 616 7941 425 6531 267 2791 108 905950 531792 013633 639475 265316 892158 374

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41P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

48.32648.32648.32648.32648.32648.32648.32648.32648.32648.326

246 608217 467193 304169 141144 978120 81596 65272 48948 32624 163

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

158.548158.548158.548158.548158.548158.548158.548158.548158.548158.548

1 783 6651 572 7961 398 0761 223 3561 048 636873 758699 038524 318349 598174 720

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42P

5 1034 5004 0003 5003 0002 5002 0001 5001 000500

50.78950.78950.78950.78950.78950.78950.78950.78950.78950.789

259 176228 550203 156177 761152 367126 972101 57876 18350 78925 394

11 2509 9208 8187 7166 6145 5114 4093 3072 2051 102

166.629166.629166.629166.629166.629166.629166.629166.629166.629166.629

1 874 5761 652 9601 469 3351 285 7091 102 084918 292734 667551 042367 417183 625

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OCT 30/93

3. BULK CARGO COMPARTMENT

LOADPOSITION

MASSkg

H-ARMm

MOMENTKgm

MASSLb

H-ARMFt

MOMENTFt.Lb

51 329 52.755 17 356 726 173.078 125 655

52 1 387 53.195 73 781 3 058 174.522 533 688

53 1 752 55.330 96 938 3 861 181.526 700 872

TOTAL 3 468 54.335 188 434 7 645 178.262 1 362 813

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OCT 30/93

NET RECOVERABLE WEIGHT (NRW) AND H-ARM LOCATION

1. Net Recoverable Weight (NRW)

The NRW is the weight obtained in section 2-30 (revised REW) plus :– the weight of the different fluids remaining aboard (sections 2-31 and2-33).

– the weight of the cargo which may still be on the aircraft, (section 2-31).

2. H-arm Location

– Determine the location

H-arm =Sum of the momentsSum of the weights

– Convert H-arm into %RC (Reference Chord).

%RC =H-arm – 34.532

0.0727

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OCT 30/93

ITEM COMPONENT WEIGHT H-ARM MOMENTSKg Lb m Ft Kgm Ft.lb

1 NOSE LANDING GEAR(complete)

764 1 684 12.957 42.51 9 899 71 587

2 MAIN LANDING GEAR(1 Side Complete)

3 875 8 543 38.217 125.38 148 091 1 071 121

3 RUDDER 183 404 66.897 219.47 12 242 88 6664 ELEVATOR (1 Side) 270 595 67.482 221.39 18 220 131 7275 GE ENGINE (1 Side) 5 400 11 905 31.111 102.07 167 999 1 215 1435 PW = TBD5 RR = TBD6 SLAT 1 (1 Side) 163 360 31.547 103.49 5 142 37 2567 SLAT 2 (1 Side) 73 160 34.771 114.07 2 538 18 2518 SLAT 3 (1 Side) 62 137 36.783 120.67 2 281 16 5329 SLAT 4 (1 Side) 64 141 38.705 126.98 2 477 17 90410 SLAT 5 (1 Side) 58 128 40.948 134.34 2 375 17 19611 SLAT 6 (1 Side) 45 99 43.078 141.33 1 938 13 99212 SLAT 7 (1 Side) 38 83 44.558 146.18 1 693 12 13313 INNER FLAP (1 Side) 262 579 39.149 128.44 10 257 74 36714 OUTER FLAP (1 Side) 383 843 41.521 136.22 15 903 114 83315 INNER AILERON (1 Side) 92 203 44.136 144.80 4 060 29 39416 OUTER AILERON (1 Side) 78 172 45.871 150.49 3 578 25 884

Component Removal (Figure 1)

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2-31Page 25

JUL 01/94

ITEM COMPONENTWEIGHT H-ARM MOMENTS

Kg Lb m Ft Kgm Ft.lb17 SPOILER 1 (1 Side) 25 55 38.346 125.80 959 6 91918 SPOILER 2 (1 Side) 23 51 38.879 127.55 894 6 50519 SPOILER 3 (1 Side) 26 56 39.666 130.13 1 031 7 28720 SPOILER 4 (1 Side) 26 56 40.476 132.79 1 052 7 43621 SPOILER 5 (1 Side) 26 56 41.316 135.55 1 074 7 59122 SPOILER 6 (1 Side) 23 50 42.326 138.86 973 6 94323 WING TIP 61 134 47.390 155.47 2 891 20 83324 APU 250 551 67.028 219.90 16 757 121 16525 Horizontal Tail 1 337 2 948 65.335 214.35 87 353 631 90426 Vertical Tail 519 1 145 64.010 210 33 221 240 45027 Pylon 1 230 2 712 33.045 108.41 40 652 293 167

Component Removal (Figure 1A)

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JUL 01/94

REMOVAL OF POWER PLANT

1. General

When a power plant is damaged or removed it is necessary to calculate thechange in CG location for airplane recovery.

The loss of an airplane power plant (engine nacelle) will cause a lateralshift in the airplane center of gravity (CG) (along the wing mean aerodynamicchord) as well as aft (along the fuselage longitudinal centerline).

Removal of the remaining power plant may be necessary to facilitate liftingthe airplane. Such removal will cause the CG to return to its originallateral position (as with both power plants installed) but will cause it tomove further aft. If the airplane can be supported and towed on its landinggear, removal of the remaining power plant may not be necessary.

To aid in the computation of the airplane CG shift due to loss of the powerplant, the weights and CG locations of the complete power plant and of itsmajor components are given in Tables :

– PW 4000 : Page 28– RR RB211 TRENT : Page 28A– GE CF6 80E1 : Page 28B

The CG locations are given by Nacelle Stationline, Nacelle Waterline, andNacelle Buttline as shown in Figure :

– PW 4000 Engine : Page 27– RR RB 211 TRENT Engine : Page 27A– GE CF6.80E1 Engine : 27B

The power plant (nacelle) CG locations must be converted to the airplanestation system of space coordinates before they can be used to compute theshift of airplane CG.

The new CG location could make it necessary to use different hoisting,jacking, and shoring procedures to recover the airplane.

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MAY 30/97

Nacelle Station LinesPW 4000 – Engine

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2-31Page 27AMAY 30/97

Nacelle Station LinesR.R, RB211 – Trent Engine

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2-31Page 27BMAY 30/97

Nacelle Station LinesGE. CF6 80E1 Engine

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JAN 01/96

P.W. 4164/68 :

COMPOMENTWEIGHT H-ARM MOMENTS

(kg) (lb) (m) ft Kgm ft.lb

INLET COWL 216 476 28.533 93.61 6 163 44 558

FAN COWL 143 315 29.780 97.70 4 259 30 776

THRUST REVERSER 778 1 716 31.180 102.30 24 258 175 547

EXHAUST NOZZLEAND PLUG

80 177 33.466 109.79 2 277 19 433

PYLON 1 260 2 778 33.041 108.40 41 632 301 135

BARE ENGINE 5 867 12 934 30.979 101.63 181 754 1 314 482

Mass, H-ARM, and Moment ConcerningVarious Components of Engines

P.W. 4000 - Engine

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2-31Page 28AJUL 01/94

R.R. RB211 TRENT :



INLET COWL 227 500 28.494 93.483 6 468 46 742

FAN COWL 136 300 29.849 97.929 4 059 29 379

THRUST REVERSER 816 1 800 31.444 103.161 25 658 185 690

COMMON NOZZLEASSEMBLY

247 545 33.508 109.933 8 276 59 913

PYLON 1 310 2 888 32.947 108.093 43 161 312 173

BARE ENGINE 5 286 11 653 30.913 101.419 163 406 1 181 836

Mass, H-ARM, and Moment ConcerningVarious Components of EnginesR.R. RB211 – Trent – Engine

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2-31Page 28BJUL 01/94

GE. CF6-80E1 :



INLET COWL 281 620 28.365 93.06 7 971 57 692

FAN COWL 159 350 29.806 97.79 4 739 34 227

THRUST REVERSER 703 1 550 31.062 101.91 21 837 157 960

CORE COWL 61 134 32.726 107.37 1 996 14 388

PRIMARY NOZZLE 79 175 33.686 110.52 2 661 19 341

PYLON 1 230 2 712 33.069 108.49 40 675 294 225

BARE ENGINE 5 596 12 337 31.198 102.35 174 584 1 262 692

Mass, H-ARM, and Moment ConcerningVarious Components of Engines

G.E. CF6-80E1 - Engine

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2-31Page 29

OCT 30/93

2. Analysis of Airplane CG Change Because of Power PlantRemoval or Damage

A. Look at the damage to each power plant to see what items are not there.

B. See Tables TBD (page 30) for the weights of the removed or lost componentand their CG locations in the nacelle. Convert nacelle component CGlocations to airplane station locations and calculate the arm for eachitem from airplane CG.

C. Calculate the lateral and longitudinal change in the airplane CG becauseof a removed power plant or components. See paragraph 3.

D. Put together the CG change because of damaged or removed power plantswith the CG change because of damaged or removed aircraft components andcalculate the total airplane CG change.

E. Decide if it is necessary to remove the remaining power plants so theresulting CG change will make airplane recovery easier.

WARNING : DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRPLANE FALLS ON RECOVERYPERSONNEL. VERIFY THAT ALL PERSONNEL ARE AWAY FROM AIRPLANE WHEN POWERPLANT IS REMOVED. REMOVAL OF POWER PLANT WEIGHT FROM WING MAY CAUSEAIRPLANE TO CHANGE POSITION BECAUSE OF CHANGE OF AIRPLANE CENTER OFGRAVITY.

CAUTION : VERIFY THAT THE DENSITY OF THE GROUND IS ABLE TO HOLD THE WEIGHT OFREMOVED ENGINE AND SUPPORT EQUIPMENT.

F. If it is necessary to remove one or more power plant, see removalinstructions in the Airbus Industrie A330 Aircraft Maintenance Manual.

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JAN 01/96

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OCT 30/93

3. Calculation of Center of Gravity (CG) Location with one or more Power PlantRemoved

Use the weight and CG data from Table (Page 24 and 25) to calculate theairplane CG changes because of power plant or component removal. The CGlocations are given by Nacelle Stationline, Waterline, and Buttline. SeeFigure 2.

The power plant CG locations must be converted from the nacelle locations toairplane station locations before they can be used to calculate the change inairplane CG.

The change in CG location is calculated as follows :

1. The equation for the new location of the airplane CG is :

Airplane moment minus power plant momentAirplane weight minus power plant weight = airplane CG

2. The equation for percent of CG change of the airplane is :

Change in CGPower Plant Arm × 100 = percent of CG change

Airplane and power plant weight and arm values have been assigned as followsfor use in the examples. The true values may be different.

Recoverable Empty Weight (REW) = 340,000 lbAircraft arm from CG (AA) = 0Power Plant Weight (PPW) = 10,500 lbPower Plant Arm (PPA) laterally from CG = 25 ftPower Plant Arm forward of CG = 20 ft

Calculation Example A :

Calculate the lateral change in CG because of removal of one power plant :

(REW × AA) – (PPW × PPA)REW – PPW = CG change in feet

340,000 × 0 − 10,500 × 25340,000 − 10,500 = 0 − 262,500

329,500 = − 0.796

In this example the calculation shows that when one power plant is removed,the CG of this airplane moves laterally 0.796 feet from its initial CGlocation toward the remaining power plants.

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OCT 30/93

Calculation Example B :

Calculate the percent of lateral change in CG due to removal of one power plant

Change in CGPPA × 100 = percent of CG change

− 0.79625 × 100 = − 3.19 percent

The computation shows that the percentage of airplane CG change is 3.19 percent.

Calculation Example C :

Calculate the longitudinal change in CG because of removal of one power plant :

(REW × AA) − (PPW × PPA)REW − PPW = CG change in feet

(340,000 × 0) − (10,500 × 20)340,000 − 10,500 = 0 − 210,000

329,500 = − 0.637

In this example the calculation shows that when one power plant is removed, theCG of this airplane moves longitudinally aft 0.637 feet from its initial CGlocation.

Calculation Example D :

Calculate the percent of longitudinal change in CG because of removal of onepower plant :

Change in CGPPA × 100 = percent of CG change

− 0.63720 × 100 − 3.19 percent

The computation shows that the percentage of airplane CGT change is − 3.19percent.

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2-33Page 1

JAN 01/96

WEIGHT AND CG CHANGES DUE TO THE FUEL IN THE AIRCRAFT FUEL TANKS

1. General

The weight and CG position of the aircraft will change due to fuel quantitiesin each tank.

To find the changes in weight and CG position, calculate :– the H-arm dimension along the longitudinal plane from nose to tail– the Y-arm dimension along the lateral plane from wing tip to wing tip.

The H-arm is a dimension from the CG of an item/component to the horizontalarm reference datum plane.

The Y-arm is a dimension from the CG of an item/component to the lateral armreference datum plane.

2. H-arm Calculations (Ref. Fig.1)

To calculate the H-arm, establish the following :– the aircraft weight empty (Ref. 1-10 page 2)– the aircraft H-arm at 25% Reference Chord (RC). This is the H-arm designref.

– the total fuel moment– the total fuel weight.

To calculate the total weight and moment of the fuel in the tanks :– find the remaining fuel quantities in each tank– use the mass and moment data on pages 9 thru 17.

Use this information in Equation 1 to determine the effect of the fuel on theH-arm.

Equation 1 :

H-arm from position X0 =

(Aircraft Wt Empty x Aircraft H-arm) + Total Fuel MomentAircraft Wt Empty + Total Fuel Wt

After Equation 1 is complete, calculate the change in the percentageReference Chord in Equation 2.

Equation 2 :

% RC =H-arm – 34.532

0.0727 is used for (A330-300)

An example of how to calculate the H-arm from position X0 and the change inthe percentage RC is shown.

The example used is for an A330-300 aircraft.

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JAN 01/96

To find the Operating Weight Empty (OWE) refer to section 1-10 page 2. Thisgives the OWE as 12 638 kg.

To find the H-arm at this weight refer to the Weight and Balance Manual.In this manual the aircraft H-arm at 25 % RC is 36.3495 m aft of the X0position (Ref. Fig.1).

The aircraft is to be recovered with fuel in the tanks as follows :– Inner tank LH Wing 42194 l– Inner tank RH Wing 42194 l– Outer tank LH Wing 3688 l– Outer tank RH Wing 3688 l– Trim tank 6121 l

Look at the mass and moment data on pages 9 thru 17 for the information thatfollows :

Inner tank LHMoment of 42194 l 1096338.2 m.kgMass of 42194 l 33122.0 kg

Inner tank RHMoment of 42194 l 1096338.2 m.kgMass of 42194 l 33122.0 kg

Outer tank LHMoment of 3688 l 114804.4 m.kgMass of 3688 l 2895.0 kg

Outer tank RHMoment of 3688 l 114804.4 m.kgMass of 3688 l 2895.0 kg

Trim tankMoment of 6121 l 292719.69 m.kgMass of 6121 l 4805.3 kg

Total Fuel Moment = 2715004.9 m.kgTotal Fuel Mass = 76839.3 kg

Now enter the Total Fuel Moment and Total Fuel Mass into equation 1.

H-arm from position X0 =(126381 x 36.3495) + 2715004.9

126381 + 76839.3

H-arm = 35.965 m

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JAN 01/96

Enter this H-arm in equation 2 and calculate the % RC :

% RC =35.965 - 34.532

0.0727

% RC = 19.716%

3. Y-Arm Calculations

When the aircraft is in level flight the Y-arm dimension is usually loadedequally about the centerline. That is, the Y-arm dimension about the RH wingis equal to the Y-arm dimension about the LH wing.

In this configuration all the moments and loads are equal about thecenterline.

To calculate the Y-arm for an aircraft on a recovery, establish thefollowing :– the aircraft weight empty– the dimension from the aircraft centerline to the MLGs– the dimension from the aircraft centerline to the jacking point– the total fuel weight– the total fuel moment.

To find the total fuel weight and moment of the fuel in the tanks :– find the remaining fuel quantities in each tank– use the mass and moment data on pages 9 thru 17.

The example shows how to calculate :– the Y-arm moment with an allowance– the total fuel mass and moments– the lifting load, for an aircraft on a recovery with a MLG failure.

If the aircraft, has a LH MLG failure, it will rest on the LH engine withthe fuselage horizontal. The aircraft will be recovered from this position.

The loads acting on the aircraft with a LH MLG failure are shown in Fig.2.

To calculate the load needed to lift the LH wing, take moments about the RHMLG.

Also put the lifting load at the beginning of this equation :

Lifting load x Dim. to RH MLG = Aircraft Wt x Dim. to RH MLG + Total fuelMoment

This will give :

Equation 3 :

Lifting load =Aircraft Wt x Dim. to RH MLG + Total Fuel Moment

Dim. to RH MLG

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The example used is for a (A330-300) aircraft with the fuel tanks full,when the MLG failure happens.

To take moments about the RH MLG :– make an allowance to the moment arm shown in the mass and data sheets(because the moment arm is taken about the aircraft centerline)

– compile a table to record the calculations made.

To make the allowance add together these figures :– the dimension from the RH MLG to the centerline of the aircraft– the Y-moment arm which is found in pages 9 thru 17.

The table to compile will include all the remaining fuel in the tanks withmass and moment calculations.

The table compiled in this example is shown in Table 4.

In the table all moments about the RH MLG in a clockwise direction areshown with a positive sign. All moments about the RH MLG in the oppositedirection are shown with a negative sign.

To compile Table 4, read the correct mass and data for the remaining fuelin the tank. These figures are found in the data sheets, pages 9 thru 17.Enter these figures for the fuel mass and the Y-arm moment in columns 3and 4, of Table 4.

Calculate the values of the Y-arm in column 5. To do this revise themoment arm so that it equals the dimension of the Y-arm of the fuel ineach tank. The new moment arm will now equal the dimension between thesepositions :– the remaining fuel in each tank– and the point about which the moments are taken.

To get the fuel moment in each tank multiply together the information thatfollows :– the fuel mass in each tank– the Y-arm dimension in column 5.

Now put together all the figures in column 6 to get a Total Fuel Moment.Make sure that both the positive and negative signs are used before thefigures.

In the Maintenance Facility Planning Manual (MFP Section 3-10, 3-14)A330-300, the information that follows is given:– the dimension from the aircraft centerline to the Jacking Point= 8.511 m

– the dimension from the aircraft centerline to the MLG centerline= 5.342 m.

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Now calculate the lifting load which should be applied by pneumatic liftingbags. These are fitted adjacent to the LH Jacking Point.

Use equation N°3 to calculate this load.

Lifting load = Aircraft Wt x Dim. from RH MLG to Aircraft C/L + Total Fuel MomentDim. from RH MLG to LH Jacking Point

= 126381 × 5.342 + 410473.9413.853

Lifting load = 78365.79 kg

4. Calculations for Removed Fuel

When fuel is drained from the tanks, the load needed to lift the aircraft isdecreased. The fuel moment will also be decreased.

The fuel to be drained in the tanks has a mass moment sign of a minus.The fuel loads in these tanks act directly against the lifting load.

Because the aircraft has a MLG failure, there is a quantity of fuel that willremain in the tanks (Ref. Table 3). Include this fuel to make the fuel momentcalculations.

There are two methods which can be used to drain fuel from the tanks. Theseare :– by a pressure defuel– by a suction defuel.

In Table 1, information is given on :– the refuel/defuel pumps in use– the position of the crossfeed valves– the defuel rates in liters/min.

Table 2 provides information on the defuel rates for each type of fuel tank.

The defuel rates in Tables 1 and 2 are those when one hose is connected to arefuel/defuel coupling.

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PUMP(S) CROSSFEED VALVES DEFUEL RATESl/min

MAIN 1 AND 2 CLOSED 366.8

MAIN 2 AND 3 CLOSED 365.6

MAIN 1, 2, 3 AND 4 CLOSED 406.8

Pressure Defuel InformationTable 1

The suction defuel uses the pumps of the fuel tanker to give the necessarynegative pressure of 0.76 bar (11 psi).

The defuel rates, in Table 2 are those, when :– a negative pressure of 0.76 bar (11 psi) is applied at the refuel/defuelcoupling

– the fuel flows through one defuel hose– the appropriate tank refuel/defuel valve is open.

FUEL TANK DEFUEL RATEl/min

INNER 288.0

OUTER 89.0

TRIM 72.0

Suction Defuel InformationTable 2

When a Pressure Defuel or a Suction Defuel is finished, there will still be aquantity of remaining fuel in the tanks.

The quantity of the remaining fuel is given in Table 3. It gives differentpositions of the aircraft attitudes.

The fuel quantities in the table are calculated when :– the fuel pumps are available and not damaged– the fuel tank drains have also been used to drain the fuel.

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In the columns at the top of Table 3 the abbreviations that follow are used :

CC – Collector Cells (Total, i.e. 2)LF – Left Forward InnerLA – Left Aft InnerRF – Right Forward InnerRA – Right Aft InnerTRM – Trim TankRO – Right Outer TankLO – Left Outer Tank.

AIRCRAFTCONFIGURATION CC LF LA RF RA TRM RO LO TOTAL

QTY

1. NLG COLLAPSE 12 253 34 253 34 70 42 42 740

2. 1 RH or LH MLGCOLLAPSE

12 78 20 83 10 6 921 0 1130

3. 1 NLG and 1 RH orLH MLG COLLAPSE

12 167 29 180 24 11 45 18 486

4. ALL MLGsCOLLAPSE

12 90 19 90 19 33 0 0 263

5. ALL GEARSCOLLAPSE

12 85 16 85 16 25 6 6 251

6. OVERBALANCEDTAIL ON GROUND

12 245 95 245 95 276 821 821 2610

7. NORMAL ATTITUDE 12 84 16 84 16 9 7 7 235

All quantities are in liters

The Remaining Fuel Quantities that you Cannot DrainTable 3

You must now calculate the decreased Total Fuel Moment to find the decreasedlifting load needed to lift the wing.

The table that has been compiled in this example is shown in Table 5.

When the decreased Total Fuel Moment has been calculated (Ref. Table 5) useEquation 3 again.

Lifting Load =126381 x 5.342 + (-8646.58)

13.853

= 48110.93 kg

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The lifting load needed is therefore decreased, if all the fuel from thetanks in the LH wing is drained.

The decreased lifting load will be :

78365.79 – 48110.93 = 30254.86 kg

That is a decrease of 38.61% in the lifting load required to lift theaircraft with the fuel removed.

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5. FUEL DATA FOR INNER TANK, LEFT OR RIGHT HAND WING

A. H-ARM

Fuel specific gravity 0.785

CAPACITY MASS H-ARM MOMENT MASS H-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lbx103)400 314 33.869 10634.86 692.244 111.12 76.92800 628 33.818 21237.70 1384.488 110.95 153.611200 942 33.743 31785.91 2076.733 110.70 229.891600 1256 33.710 42339.76 2768.977 110.59 306.222000 1570 33.698 52905.86 3461.222 110.55 382.632400 1884 33.694 63479.49 4153.466 110.54 459.122800 2198 33.695 74061.61 4845.711 110.55 535.693200 2512 33.696 84644.35 5537.955 110.55 612.223600 2826 33.701 95239.03 6230.199 110.56 688.814000 3140 33.706 105836.8 6922.444 110.58 765.484400 3454 33.709 116430.9 7614.688 110.59 842.104800 3768 33.716 127041.9 8306.933 110.61 918.825200 4082 33.722 137653.2 8999.177 110.64 995.675600 4396 33.727 148263.9 9691.421 110.65 1072.356000 4710 33.733 158882.4 10383.666 110.67 1149.166400 5024 33.741 169514.8 11075.91 110.69 1225.996800 5338 33.748 180146.8 11768.155 110.72 1302.977200 5652 33.754 190777.6 12460.399 110.74 1379.867600 5966 33.761 201418.1 13152.644 110.76 1456.788000 6280 33.770 212075.6 13844.888 110.79 1533.878400 6594 33.778 222732.1 14537.132 110.82 1611.008800 6908 33.785 233386.8 15229.377 110.84 1688.029200 7222 33.791 244038.6 15921.621 110.86 1765.079600 7536 33.800 254716.8 16613.866 110.89 1842.3110000 7850 33.808 265392.8 17306.110 110.92 1919.5910400 8164 33.816 276073.8 17998.354 110.94 1996.7410800 8478 33.823 286751.4 18690.599 110.96 2073.9111200 8792 33.830 297433.4 19382.843 110.99 2151.3011600 9106 33.839 308137.9 20075.088 111.02 2228.7412000 9420 33.847 318838.74 20767.33 111.05 2306.2112400 9734 33.854 329534.84 21459.58 111.07 2383.5212800 10048 33.862 340245.38 22151.82 111.09 2460.8513200 10362 33.868 350940.22 22844.06 111.11 2538.2013600 10676 33.876 361660.18 23536.31 111.14 2615.8314000 10990 33.884 372385.16 24228.55 111.16 2693.2514400 11304 33.892 383115.17 24920.80 111.19 2770.9414800 11618 33.899 393828.58 25613.04 111.26 2849.7115200 11932 33.906 404566.39 26305.29 111.24 2926.2015600 12246 33.912 415286.35 26997.53 111.26 3003.7516000 12560 33.920 426035.2 27689.78 111.28 3081.3216400 12874 33.928 436789.07 28382.02 111.31 3159.20

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CAPACITY MASS H-ARM MOMENT MASS H-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lbx103)16800 13188 33.935 447534.78 29074.26 111.33 3236.8417200 13502 33.942 458284.88 29766.51 111.36 3314.8017600 13816 33.949 469039.38 30458.75 111.38 3392.4918000 14130 33.955 479784.15 31151.00 111.40 3470.2218400 14444 33.963 490561.57 31843.24 111.43 3548.2918800 14758 33.970 501329.26 32535.49 111.45 3626.0819200 15072 33.977 512101.34 33227.73 111.47 3703.8919600 15386 33.984 522877.84 33919.98 111.49 3781.7420000 15700 33.991 533658.7 34612.22 111.52 3859.9520400 16014 33.997 544427.96 35304.46 111.54 3937.8620800 16328 34.004 555217.31 35996.71 111.56 4015.7921200 16642 34.012 566027.7 36688.95 111.59 4094.1221600 16956 34.020 576843.12 37381.20 111.61 4172.1622000 17270 34.028 587663.56 38073.44 111.64 4250.5222400 17584 34.035 598471.44 38765.69 111.66 4328.5822800 17898 34.042 609283.72 39457.93 111.68 4406.6623200 18212 34.050 620118.6 40150.17 111.71 4485.1723600 18526 34.059 630977.03 40842.42 111.74 4563.7324000 18840 34.069 624825.46 41534.66 111.77 4642.3324400 19154 34.078 652730.01 42226.91 111.80 4720.9724800 19468 34.087 663430.5 42919.15 111.83 4799.6525200 19782 34.096 674487.07 43611.40 111.86 4878.3725600 20096 34.104 685353.98 44303.64 111.89 4957.1326000 20410 34.119 696368.79 44995.89 111.94 5036.8426400 20724 34.134 707393.02 45688.13 111.99 5116.6126800 21038 34.149 718426.66 46380.37 112.04 5196.4627200 21352 34.163 729448.38 47072.62 112.08 5275.9027600 21666 34.177 740478.88 47764.86 112.13 5355.8828000 21980 34.193 751562.14 48457.11 112.18 5435.9228400 22294 34.213 762744.62 49149.35 112.25 5517.0128800 22608 34.233 773939.66 49841.60 112.31 5597.7129200 22922 34.252 785124.34 50533.84 112.37 5678.4929600 23236 34.271 796320.96 51226.09 112.44 5759.8630000 23550 34.291 807553.05 51918.33 112.50 5840.8130400 23864 34.315 818893.16 52610.57 112.58 5922.9030800 24178 34.338 830224.16 53302.82 112.66 6005.0131200 24492 34.360 841545.12 53995.06 112.73 6086.8631600 24806 34.382 852879.89 54687.31 112.80 6168.7332000 25120 34.407 864303.84 55379.55 112.88 6251.2432400 25434 34.433 875768.92 56071.80 112.97 6334.4332800 25748 34.459 887250.33 56764.04 113.05 6417.1733200 26062 34.484 898722.01 57456.28 113.14 6500.6033600 26376 34.511 910262.14 58148.53 113.22 6583.5834000 26690 34.539 921845.91 58840.77 113.32 6667.8434400 27004 34.566 933420.26 59533.02 113.40 6751.0434800 27318 34.593 945011.57 60225.26 113.49 6834.96

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CAPACITY MASS H-ARM MOMENT MASS H-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lbx103)35200 27632 34.623 956702.74 60917.50 113.59 6919.6235600 27946 34.653 968412.74 61609.75 113.69 7004.4136000 28260 34.683 980141.58 62301.99 113.79 7089.3436400 28574 34.713 991889.26 62994.24 113.89 7174.4136800 28888 34.745 1003713.6 63686.48 113.99 7259.6237200 29202 34.777 1015558.0 64378.73 114.10 7345.6137600 29516 34.808 1027392.9 65070.97 114.20 7431.1038000 29830 34.843 1039366.7 65763.22 114.31 7517.3938400 30144 34.877 1051332.3 66455.46 114.42 7603.8338800 30458 34.910 1063288.8 67147.71 114.53 7690.4339200 30772 34.947 1075389.1 67839.95 114.65 7777.8539600 31086 34.982 1087450.5 68532.19 114.77 7865.4440000 31400 35.021 1099659.4 69224.44 114.90 7953.8940400 31714 35.059 1111861.1 69916.68 115.02 8041.8240800 32028 35.097 1124086.7 70608.93 115.15 8130.6241200 32342 35.135 1136336.2 71301.17 115.27 8218.8941600 32656 35.175 1148674.8 71993.42 115.40 8308.0442000 32970 35.215 1161038.6 72685.66 115.53 8397.3742194 33122 35.234 1167031.1 73021.42 115.60 8441.28

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6. FUEL DATA FOR INNER TANK, LEFT OR RIGHT HAND WING

A. Y-ARM


CAPACITY MASS Y-ARM MOMENT MASS Y-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lbx103)400 314 3.140 985.96 692.244 10.30 7.13800 628 3.195 2006.46 1384.488 10.48 14.511200 942 3.254 3065.27 2076.733 10.66 22.141600 1256 3.305 4151.08 2768.977 10.84 30.162000 1570 3.357 5270.49 3461.222 11.01 34.652400 1884 3.405 6415.02 4153.466 11.17 46.392800 2198 3.454 7591.89 4845.711 11.33 54.903200 2512 3.493 8774.41 5537.955 11.46 63.463600 2826 3.541 10006.86 6230.199 11.62 72.394000 3140 3.582 11247.48 6922.444 11.75 81.344400 3454 3.617 12493.12 7614.688 11.87 90.384800 3768 3.660 13790.88 8306.933 12.01 99.775200 4082 3.697 15091.15 8999.177 12.13 109.165600 4396 3.730 16397.08 9691.421 12.24 118.626000 4710 3.764 17728.44 10383.666 12.35 128.246400 5024 3.800 19091.12 11075.91 12.46 138.016800 5338 3.832 20455.21 11768.155 12.57 147.937200 5652 3.861 21822.37 12460.399 12.67 157.877600 5966 3.892 23219.67 13152.644 12.77 167.968000 6280 3.924 24642.72 13844.888 12.87 178.188400 6594 3.954 26072.68 14537.132 12.97 188.558800 6908 3.982 27507.66 15229.377 13.06 198.899200 7222 4.007 28938.55 15921.621 13.15 209.379600 7536 4.038 30430.37 16613.866 13.25 220.1310000 7850 4.066 31918.10 17306.110 13.34 230.8610400 8164 4.093 33415.25 17998.354 13.43 241.7210800 8478 4.117 34903.93 18690.599 13.51 252.5111200 8792 4.141 36407.67 19382.843 13.59 263.4111600 9106 4.169 37962.91 20075.088 13.68 274.6312000 9420 4.196 39526.32 20767.33 13.77 285.9712400 9734 4.220 41077.48 21459.58 13.85 297.2112800 10048 4.244 42643.71 22151.82 13.92 308.3513200 10362 4.266 44204.29 22844.06 14.00 319.8213600 10676 4.291 45810.72 23536.31 14.08 331.3914000 10990 4.317 47443.83 24228.55 14.16 343.0814400 11304 4.342 49081.97 24920.80 14.25 355.1214800 11618 4.365 50712.57 25613.04 14.32 366.7815200 11932 4.388 52357.62 26305.29 14.40 378.8015600 12246 4.409 53992.61 26997.53 14.46 390.3816000 12560 4.435 55703.60 27689.78 14.55 402.8916400 12874 4.461 57430.91 28382.02 14.64 415.51

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CAPACITY MASS Y-ARM MOMENT MASS Y-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lb×103)16800 13188 4.485 59148.18 29074.26 14.71 427.6817200 13502 4.509 60880.52 29766.51 14.79 440.2517600 13816 4.531 62600.30 30458.75 14.87 452.9218000 14130 4.553 64333.89 31151.00 14.94 465.4018400 14444 4.578 66124.63 31843.24 15.02 478.2918800 14758 4.605 67960.59 32535.49 15.11 491.6119200 15072 4.630 69783.36 33227.73 15.19 504.7319600 15386 4.654 71606.44 33919.98 15.27 517.9620000 15700 4.677 73428.90 34612.22 15.34 530.9520400 16014 4.699 75249.79 35304.46 15.42 544.3920800 16328 4.724 77133.47 35996.71 15.50 557.9521200 16642 4.752 79082.78 36688.95 15.59 571.9821600 16956 4.779 81032.72 37381.20 15.68 586.1422000 17270 4.805 82982.35 38073.44 15.76 600.0422400 17584 4.830 84930.72 38765.69 15.85 614.4422800 17898 4.854 86876.90 39457.93 15.93 628.5623200 18212 4.880 88874.56 40150.17 16.01 642.8023600 18526 4.911 90981.19 40842.42 16.11 657.9724000 18840 4.941 93088.44 41534.66 16.21 673.2824400 19154 4.970 95195.38 42226.91 16.31 688.7224800 19468 4.999 97320.53 42919.15 16.40 703.8725200 19782 5.026 99424.33 43611.40 16.49 719.1525600 20096 5.053 101545.09 44303.64 16.58 734.5526000 20410 5.091 103907.31 44995.89 16.70 751.4326400 20724 5.128 106272.67 45688.13 16.82 768.4726800 21038 5.165 108661.27 46380.37 16.95 786.1527200 21352 5.20 111030.40 47072.62 17.06 803.0627600 21666 5.235 113421.51 47764.86 17.14 818.6928000 21980 5.272 115878.56 48457.11 17.30 838.3128400 22294 5.317 118537.20 49149.35 17.44 857.1628800 22608 5.361 121201.49 49841.60 17.59 876.7129200 22922 5.403 123847.57 50533.84 17.73 895.9629600 23236 5.444 126496.78 51226.09 17.86 914.9030000 23558 5.488 129242.40 51918.33 18.00 934.5330400 23864 5.538 132158.83 52610.57 18.16 955.4130800 24178 5.586 135058.31 53302.82 18.33 977.0431200 24492 5.633 137963.44 53995.06 18.48 997.8331600 24806 5.679 140873.27 54687.31 18.63 1018.8232000 25120 5.731 143962.72 55379.55 18.80 1041.1432400 25434 5.785 147135.69 56071.80 18.98 1064.2432800 25748 5.837 150291.08 56764.04 19.15 1087.0333200 26062 5.888 153453.06 57456.28 19.32 1110.0533600 26376 5.943 156752.57 58148.53 19.50 1133.9034000 26690 6.000 160140.00 58840.77 19.68 1157.9934400 27004 6.056 163536.22 59533.02 19.86 1182.3334800 27318 6.110 166912.98 60225.26 20.05 1207.52

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CAPACITY MASS Y-ARM MOMENT MASS Y-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lb×103)35200 27632 6.170 170489.44 60917.50 20.25 1233.5835600 27946 6.230 174103.58 61609.75 20.44 1259.3036000 28260 6.289 177727.14 62301.99 20.63 1285.2936400 28574 6.349 181416.33 62994.24 20.83 1312.1736800 28888 6.413 185258.74 63686.48 21.04 1339.9637200 29202 6.476 189112.15 64378.73 21.25 1368.0537600 29516 6.537 192946.09 65070.97 21.45 1395.7738000 29830 6.605 197027.15 65763.22 21.67 1425.0938400 30144 6.672 201120.77 66455.46 21.89 1454.7138800 30458 6.737 205195.55 67147.71 22.10 1483.9639200 30772 6.808 209495.78 67839.95 22.34 1515.5439600 31086 6.878 213809.51 68532.19 22.57 1546.7740000 31400 6.949 218198.60 69224.44 22.80 1578.3240400 31714 7.019 222600.57 69916.68 23.03 1610.1840800 32028 7.093 227174.60 70608.93 23.27 1643.0741200 32342 7.168 231827.46 71301.17 23.52 1677.0041600 32656 7.246 236625.38 71993.42 23.77 1711.2842000 32970 7.324 241472.28 72685.66 24.03 1746.6442194 33122 7.365 243945.67 73021.40 24.16 1764.42

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7. FUEL DATA FOR OUTER TANK, LEFT OR RIGHT HAND WING

A. H-ARM


CAPACITY MASS H-ARM MOMENT MASS H-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lb×103)200 157 40.580 6371.06 346.122 133.13 46.08400 314 40.688 12776.03 692.244 133.49 92.41600 471 40.750 19193.25 1038.367 133.69 138.82800 628 40.804 25624.91 1384.488 133.87 185.341000 785 40.849 32066.47 1730.611 134.02 231.941200 942 40.899 38526.86 2076.733 134.18 278.661400 1099 40.936 44988.66 2422.855 134.30 325.391600 1256 41.000 51496.00 2768.977 134.51 372.461800 1413 41.050 58003.65 3115.100 134.68 419.542000 1570 41.120 64558.40 3461.222 134.91 466.952200 1727 41.180 71117.86 3807.344 135.10 514.372400 1884 41.256 77726.30 4153.466 135.35 562.172600 2041 41.329 84352.49 4499.589 135.59 610.102800 2198 41.406 91010.39 4845.711 135.84 658.243000 2355 41.489 97706.60 5191.833 136.12 706.713200 2512 41.571 104426.35 5537.955 136.39 755.323400 2669 41.657 111182.53 5884.077 136.67 804.183600 2826 41.749 117982.67 6230.199 136.97 853.353688 2895 41.789 120979.16 6382.317 137.10 875.02

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8. FUEL DATA FOR OUTER TANK, LEFT OR RIGHT HAND WING

A. Y-ARM


CAPACITY MASS Y-ARM MOMENT MASS Y-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lb×103)200 157 18.020 2829.14 346.122 59.12 20.46400 314 18.144 5697.22 692.244 59.53 41.21600 471 18.229 8585.86 1038.367 59.81 62.10800 628 18.313 1150.56 1384.488 60.08 83.181000 785 18.390 14436.15 1730.611 60.33 104.411200 942 18.480 17408.16 2076.733 60.63 125.911400 1099 18.547 20383.15 2422.855 60.85 147.431600 1256 18.669 23448.26 2768.977 61.25 169.601800 1413 18.767 26517.78 3115.100 61.57 191.802000 1570 18.898 29669.86 3461.222 62.00 214.602200 1727 19.014 32837.18 3807.344 62.38 237.502400 1884 19.158 36093.67 4153.466 62.85 261.052600 2041 19.295 39381.10 4499.589 63.30 284.822800 2198 19.439 42726.92 4845.711 63.77 309.013000 2355 19.592 46139.16 5191.833 64.28 333.733200 2512 19.745 49599.44 5537.955 64.78 358.753400 2669 19.902 53118.44 5884.077 65.29 384.203600 2826 20.069 56714.99 6230.199 65.84 410.203688 2895 20.142 58312.70 6382.317 66.08 421.76

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9. FUEL DATA FOR TRIM TANK

A. H-ARM


CAPACITY MASS H-ARM MOMENT MASS H-ARM MOMENT(l) (kg) (m) (m.kg) (lb) (ft) (ft.lb×103)200 157 64.144 10070.61 346.122 210.44 72.84400 314 64.122 20134.31 692.244 210.37 145.63600 471 64.152 30215.59 1038.367 210.47 218.55800 628 64.185 40308.18 1384.488 210.58 291.551000 785 64.215 50408.78 1730.611 210.68 364.611200 942 64.240 60514.08 2076.733 210.76 437.691400 1099 64.261 70622.84 2422.855 210.83 510.811600 1256 64.280 80735.68 2768.977 210.89 583.951800 1413 64.297 90851.66 3115.100 210.95 657.132000 1570 64.313 100971.41 3461.222 211.00 730.322200 1727 64.330 111097.91 3807.344 211.05 803.542400 1884 64.348 121231.63 4153.466 211.11 876.842600 2041 64.368 131375.09 4499.589 211.18 950.222800 2198 64.391 141531.42 4845.711 211.25 1023.663000 2355 64.416 151699.68 5191.833 211.34 1097.243200 2512 64.444 161883.33 5537.955 211.43 1170.893400 2669 64.476 172086.44 5884.077 211.53 1244.663600 2826 64.511 182308.09 6230.199 211.65 1318.623800 2983 64.549 192549.67 6582.936 211.77 1394.074000 3140 64.590 202812.60 6922.444 211.91 1466.944200 3297 64.635 213101.60 7268.566 212.05 1541.304400 3454 64.682 223411.63 7614.688 212.21 1615.914600 3611 64.732 233747.25 7960.810 212.37 1690.644800 3768 64.784 244106.11 8306.933 212.54 1765.565000 3925 64.839 254493.08 8653.055 212.72 1840.685200 4082 64.896 264905.47 8999.177 212.91 1916.015400 4239 64.956 275348.48 9345.299 213.11 1991.585600 4396 65.017 285814.73 9691.422 213.31 2067.285800 4553 65.081 296313.79 10037.544 213.52 2143.226000 4710 65.147 306842.37 10383.666 213.73 2219.306121 4805 65.187 313223.54 10593.100 213.86 2265.44

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COLUMN 1 2 3 4 5 6

CELL N° CAPACITY

litres

MASS(From table)

kg

Y-ARM ABOUTAIRCRAFTCENTERLINE(From table)

m

Y-ARM ABOUTRH MAINGEAR

m

MOMENTABOUTRH MAINGEARm.kg

1 42194 33122 7.365 12.707 420881.252 42194 33122 7.365 –2.023 –67005.801A 3688 2895 20.142 25.484 73776.182A 3688 2895 20.142 –14.8 –42846.0Trim 6121 4805 0.0 5.342 25668.31

TOTAL FUEL MOMENT 410473.94 m.kg

Fuel Moment Table with Fuel Remaining in the tanksTable 4

COLUMN 1 2 3 4 5 6

CELL N° CAPACITY

litres

MASS(From table)

kg

Y-ARM ABOUTAIRCRAFTCENTERLINE(From table)

m

Y-ARM ABOUTRH MAINGEAR

m

MOMENTABOUTRH MAINGEARm.kg

1 104 81.64 2.75 8.092 660.632 96 75.36 2.70 –2.642 –199.101A 1 0.785 17.866 23.208 18.212A 921 772.98 18.00 12.658 –9151.48Trim 6 4.71 0.0008 5.342 25.16

TOTAL FUEL MOMENT – 8646.58 m.kg

Fuel Moment Table with Fuel that you Cannot Drain (LH Wing)Table 5

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Aircraft Reference Axis (A330-300)Figure 1

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Aircraft Reference Axis (A330-200)Figure 1A

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Type and Position of Loads Acting on AircraftFigure 2

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Type and Position of Loads Acting on AircraftA330 with Center Tank

Figure 2A

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DEFUELING

1. General

This topic deals with defuelling of the -300 and -200 models of the A330aircraft. It is not possible to provide all the configurations or theconditions of a damaged aircraft. Therefore specific operations to defuel theaircraft before recovery, can not be given. In some conditions it will benecessary to use the procedures given in the Aircraft Maintenance Manual(AMM).

The preparation and description that follows is made at Post Mod. 40176. Thisoptional modification introduces a refuel/defuel coupling in the LH wing.

The A330-200 model is fitted with an optional center tank in the centersection of the aircraft.

2. Precautions

Before you start to defuel the aircraft you must make sure that :– the safety zone (Ref. Fig. 1) is identified to prevent the entry of personsthat are not necessary to the defuel operation

– all equipment and materials that are not necessary for the defuel operationare moved out of the safety zone

– the safety and the fire fighting equipment, and the personnel approved tooperate it, are in place

– the fuel tankers are in the correct position– the escape lanes for the fuel tankers are clear– the fuel tankers have sufficient capacity to defuel the aircraft– the aircraft and fuel tankers are grounded correctly– you use only the electrical equipment necessary for the defuel operation– you do not operate the aircraft main engines or the APU during the defueloperation

– the electrical equipment that you use will not cause a spark– caps are installed on all damaged fuel pipes– damaged electrical wiring and fuel pumps are isolated– you use only fuel pumps that are serviceable– do not do a defuel procedure in bad weather conditions, lightning isdangerous

– do not operate radio or radar equipment during the defuel operation– immediately flush away with water, or remove, fuel spillage.

3. Preparation (Ref. Figs. 2 and 3)

A. Put the access platforms in position, below the access panels 522HB and622HB.

B. Open the panels 522HB and 622HB.C. Remove the refuel/defuel coupling caps from the refuel/defuel couplings.D. Make sure that the couplings of the fuel supply hoses are clean.E. Connect the fuel supply hoses to the refuel/defuel couplings.

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F. Open the access panel 198DB in the RH belly fairing.

CAUTION : THE GROUND POWER UNIT (GPU) MUST NOT BE CONNECTED TO THEAIRCRAFT IF THE DEFUEL OPERATION IS TO BE DONE WITHOUTELECTRICAL POWER.

CAUTION : THE AIRCRAFT ELECTRICAL SYSTEM MUST NOT BE ENERGIZED, IF THEDEFUEL OPERATION IS TO BE DONE WITHOUT ELECTRICAL POWER.

G. If necessary, and if it is safe to do so, put the GPU in a position asfar from the aircraft as possible. The GPU must have 3 phases, with 115volts at 400 Hz and supply 20 KVA.

H. If necessary, and if it is safe to do so, connect the GPU to the aircraftand energize the aircraft electrical system.

I. If necessary, start the Electronic Instrument System (EIS) and theElectronic Centralized Aircraft Monitoring (ECAM).

4. Defuel (Ref. Figs. 2 and 3)

In the leading edge of both LH and RH wings there is a refuel/defuelcoupling. This is the interface between the refuel/defuel system and theexternal source.Each refuel/defuel coupling can have two refuel/defuel hoses connected to it.The aircraft can then be defueled through one or more of the refuel/defueladaptors.

CAUTION : IF ONLY ONE REFUEL/DEFUEL COUPLING IS USED IT MUST BE THE ONEIDENTIFIED – USE THIS ADAPTOR TO DEFUEL.

There are two ways to defuel an aircraft. These are :– with a pressure defuel (the aircraft fuel-pumps supply the fuel pressurefor the defuel)

– with a suction defuel (the external defuel source supplies the suction toremove the fuel).

These two ways can be used at the same time to increase the defuel rate.

When the aircraft is at the usual lateral and longitudinal angles, gravitywill act upon the fuel in the tanks. At these angles most of the fuel in thetanks can be removed.Fuel will move from the trim tank into the fuel gallery. From the fuelgallery it will move to the refuel/defuel couplings and out of the aircraft.

The defuel can be done in these electrical conditions :– an electrical GPU connected to the aircraft electrical system– the aircraft batteries or the APU connected to the aircraft electricalsystem

– no aircraft electrical power available.

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In the condition of, when no aircraft electrical power is available, you mustremove the electrical actuators and operate the fuel valves manually. You canthen power the fuel pumps with an independent electrical supply and a wiringharness.

You cannot start a pressure defuel unless all the wing inlet valves are closed.This prevents the possibility of a tank overflow, because the inner tanks haveno fuel hi-level sensor protection during a defuel. It is only possible topressure defuel the inner fuel tanks and the optional center tank. To defuel theother fuel tanks, the fuel must first be moved to the inner tanks or theoptional center tank.

To fully defuel the trim tank in the Trimmable Horizontal Stabilizer it must beset to the zero position. The Fuel Control and Monitoring System (FCMS) preventsa defuel of the wing tanks until the trim tank is empty.

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Safety Area and Fueling ZoneFigure 1

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Refuel/Defuel CouplingFigure 2

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Refuel/Defuel Control Panel 990VU – Component LocationFigure 3

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5. Defuel Procedures

There are four procedures you can use to remove fuel from an aircraft.These are :– a pressure defuel with electrical power– a suction defuel with electrical power– a pressure defuel without electrical power– a suction defuel without electrical power.

A. Pressure Defuel with Electrical Power (Ref. Fig.3,4 and 5)

NOTE : The pressure defuel is controlled from the cockpit overhead panel245VU.

(1) In the Cockpit

(a) Push in the FUEL pushbutton switch (P/BSW) and make sure thatthe ECAM system Display Unit shows the FUEL page.

(b) Read and make a record of the fuel quantities.

(2) On the Refuel/Defuel Control Panel 990VU :

(a) Make sure that the REFUEL-DEFUEL-VALVES (switches 5QU1, 5QU2,6QU1, 6QU2 and 8QU) are in the NORM (guarded) position (7QUalso, on the -200 model).

(b) Set the MODE SELECT switch (3QU) to the DEFUEL position.

(c) Lift the guard and set the TRANSF VALVE switch (11QU) to OPEN.

(3) Defuel of the trim tank and the trim pipe until empty.

(a) On the overhead panel 245VU, push in the T TANK MOSE P/BSW(21QL) and put the T TANK FEED (fuel isolation) switch (13QN) tothe open position. Make sure that :

1 The FWD light comes on

2 The FUEL page shows :– the trim-tank isolation valve symbol is in-line (valve open)– the forward-transfer triangular symbol is in view (fueltransfer in operation).

(b) Monitor the fuel contents, and make sure that the trim tank fuelcontents figure decreases.

(c) Continue the defuel until the trim-tank fuel quantity indicationis zero and the inner-tank fuel quantity indications are stable.

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(d) Release out the T TANK MODE P/BSW and put the T TANK FEED switchto the AUTO position. Make sure that :

1 The FWD light goes off.

2 The FUEL page shows :– the trim-tank isolation valve symbol is cross-line (valveclosed)

– the forward-transfer triangular symbol is not in view(fuel-transfer not in operation).

(4) Defuel of the Center Tank until it is empty (-200 model).

(a) Push in the L TRANSFER and R TRANSFER switches. Make sure that :– the OFF lights go off– on the ECAM, the FUEL page shows the L and R TRANSFERfuel-pump symbols are in-line (pumps in operation).

(b) Operate the pumps until a pump FAULT light comes on.

(c) Release out the L and R TRANSFER P/BSWs. Make sure that :– the OFF light comes on– the FUEL page shows that the L and R TRANSFER fuel pumpsymbols are cross-line (pumps not in operation)

– the FAULT light goes off.

(5) Defuel the wing tanks until they are empty.

(a) Push in the L1, L2, R1, R2 P/BSWs to start the pumps. Make surethat :– the OFF lights go off– the FUEL page shows the related fuel pump symbol is in-line(pump in operation).

NOTE : During a defuel the fuel pumps can empty the fuelcollector cell faster than the collector cell can fill.You must let the collector cell fill again before thedefuel can continue.

(b) Operate the pump until a TANK pump FAULT-light comes on.

CAUTION : DO NOT LET THE FUEL PUMPS OPERATE FOR MORE THAN 15MINUTES WITH THE FAULT LIGHT ON. THIS PREVENTS DAMAGETO THE FUEL PUMPS.

(c) Release out the TANK P/BSW. Make sure that :– the related FAULT light goes off– the related TANK P/BSW OFF light comes on– the FUEL page shows the related fuel pump symbol is cross-line(pump not in operation)

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(d) Repeat this operation for each of the fuel pumps as necessary.

(e) On the ECAM make sure that the FUEL page shows :– the trim-tank isolation valve symbol is cross-line (valveclosed)

– the forward fuel-transfer symbol is not in view (fuel-transfernot in operation)

– the fuel pump symbols are cross-line (pumps not in operation).

B. Suction Defuel with Electrical Power (Ref. Fig.3)

NOTE : A suction defuel is controlled from the Refuel/Defuel ControlPanel 990VU.

(1) On the Refuel/Defuel Control Panel 990VU :

(a) Set the TRIM TK REFUEL-DEFUEL-VALVES switch (8QU) to the OPENposition.

(b) Set the REFUEL-DEFUEL-VALVES switches (5QU1, 5QU2, 6QU1 and6QU2) to the OPEN position (on -200 models set 7QU to the OPENposition).

(c) Set the MODE SELECT switch 3QU to the DEFUEL position.

(2) Defuel the trim tank, the wing tanks and the center tank until empty.

(a) At the fuel tanker :

1 Operate the tanker suction motor.

2 Set the applicable REFUEL VALVE switches to SHUT when eachfuel tank becomes empty.

3 Stop the tanker suction motors.

4 Put the MODE SELECT switch to the OFF position.

5 Put the REFUEL VALVE switch(es) to the NORM position.

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C. Pressure Defuel without Aircraft Electrical Power (Ref. Figs. 2, 6, 7 and8)

WARNING : THE AIRCRAFT ELECTRICAL SYSTEM MUST BE SWITCHED OFF ANDISOLATED

When you pressure defuel an aircraft without electrical power you willfind that the fuel quantity instruments do not operate. You must then :– manually operate all the defuel related valves– isolate the fuel pumps from the aircraft electrical system– use an External Wiring Harness (EWH) control box and power source tooperate the aircraft fuel pumps

– use the aircraft Manual Magnetic Indicators (MMIS) to give anindication of the aircraft fuel contents.

When you pressure defuel without aircraft electrical power you must not :– energize the aircraft electrical system– connect a GPU to the aircraft.

CAUTION : WHEN YOU DEFUEL WITHOUT ELECTRICAL POWER YOU MUST;– KEEP THE BALANCE OF THE AIRCRAFT CORRECT– DEFUEL THE TRIM TANK BEFORE YOU DEFUEL THE WING TANKS– REMOVE AN EQUAL QUANTITY OF FUEL FROM EACH WING.

(1) Aircraft Preparation

(a) Open the MLG doors and access panels to locate the refuel/defuelvalves.

(b) Write down the position of the valves, so that you can returnthem to the original position after the defuel.

(c) Remove the electrical actuators and manually set these valves tothe closed position :– fuel inlet, trim-tank 5705QA– fuel inlet, inner tank 5603QA1 and (5603QA2)– fuel inlet, outer tank 5600QA1 and (5500QA2)– fuel inlet, center tank (5501QA) (-200 Model)– auxiliary forward fuel transfer 5703QA– fuel trim pipe isolation, center section 5701QA.

(d) If necessary, set these valves to the open position :– the fuel crossfeed (5300QA)– the fuel trim-tank isolation (5702QA).

NOTE : The fuel crossfeed valve will allow you to defuel thecomplete aircraft from one wing. That is from either theLH wing or the RH wing refuel/defuel couplings. When youopen the fuel trim pipe isolation valve 5701QA, you canremove the fuel in the transfer pipe.

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(e) Disconnect the electrical actuators from the LH and RH STBY fuelpumps and connect the EWH plugs P1 and P2.

NOTE : You can control the pumps from the switches on the EWHcontrol box.

(f) Push and hold in the Manual Command Button (MCB) on therefuel/defuel isolation valves 502QU1 and (502QU2).

NOTE : The MCBs must be held in all the time the defuel is inprogress.

(2) Defuel the trim tank

(a) Manually open these valves :

– the trim-tank isolation valve 5705QA– the auxiliary FWD transfer valve 5703QA

(b) Push and hold in the MCB on the refuel/defuel isolation valves502QU1 and (502QU2).

(c) Set the pump switches on the EWH to ON.

CAUTION : DO NOT LET THE PUMPS OPERATE FOR MORE THAN 15 MINUTESWITH NO FUEL IN THE TANKS. THIS WILL PREVENT DAMAGE TOTHE PUMPS.

(d) Monitor the fuel quantity receiver at the tanker until the trimtank is empty.

NOTE : There are no Manual Magnetic Indicators (MMIs) in thetrim tank.To monitor the fuel in the trim tank you must record thefuel quantity that is received at the tanker.

(e) To complete the defuel you must next :

1 Remove the fuel from the outer tanks.2 Remove the fuel from the inner tanks.

(3) Defuel the outer tanks then the inner tanks.

NOTE : The inner tank high level protection does not function withoutpower. You must use the MLIs to monitor the fuel levels.

(a) Manually open the outer tank inlet valves 5500QA1 and 5500QA2.

(b) Push and hold in the MCB on the refuel/defuel isolation valves502QU1 and 502QU2.

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(c) On the control box of the EWH, set the pump switches to on.

CAUTION : DO NOT LET THE PUMPS OPERATE FOR MORE THAN 15 MINUTESWITH NO FUEL IN THE TANKS. THIS WILL PREVENT DAMAGE TOTHE PUMPS.

(d) Monitor the fuel quantities in the outer tanks with the MMIswhen the flow to the tanker has become stable.

(e) To complete the defuel you must next remove the fuel from theinner tanks.

(f) To remove fuel from these tanks you must :– manually set the inlet valves 5603QA1 and 5603QA2 to open– set the pump switches on the control box to on.

(g) Monitor the fuel quantities in all the tanks until they areempty.

NOTE : The aircraft MMIs can be used to give an indication ofthe fuel contents in the wing tanks.

(h) When the defuel is complete you must :– return all the valves that you manually closed to the originalposition and install the electrical actuators

– release out the MCB which will return the refuel/defuelisolation valves to the normal position.

D. Suction Defuel Without Aircraft Electrical Power (Ref. Fig. 6 and 8)

WARNING : THE AIRCRAFT ELECTRICAL SYSTEM MUST BE SWITCH OFF ANDISOLATED.

NOTE : When you suction defuel an aircraft without electrical poweryou will find that the fuel quantity instruments do notoperate.

You must manually operate all the defuel related valves.

CAUTION : WHEN YOU SUCTION DEFUEL WITHOUT AIRCRAFT ELECTRICAL POWERYOU MUST NOT :– ENERGIZE THE AIRCRAFT ELECTRICAL SYSTEM– CONNECT A GPU TO THE AIRCRAFT.

CAUTION : WHEN YOU DEFUEL WITHOUT ELECTRICAL POWER YOU MUST :– KEEP THE BALANCE OF THE AIRCRAFT CORRECT– DEFUEL THE TRIM TANK BEFORE YOU DEFUEL THE WING TANKS– REMOVE AN EQUAL QUANTITY OF FUEL FROM EACH WING

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(1) Aircraft Preparation

(a) Open the MLG doors and access panels to locate the refuel/defuelvalves.

(b) Write down the positions of the valves, so that you can return themto the original position after the defuel.

(c) Remove the electrical actuators and manually set these valves to theopen position :– fuel inlet valve, trim tank 5705QA– fuel inlet inner valve, tank 5603QA1 and (5603QA2)– fuel inlet outer valve, tank 5500QA1 and (5500QA2)– auxiliary forward fuel transfer valve 5703QA– trim tank isolation valve 5702QA– trim-pipe isolation valve 5701QA– APU isolation valve 5204QA

NOTE : The fuel trim-tank isolation valve 5702QA is used only if thetransfer pipe to the trim-tank is to be defuelled.

(2) Defuel all tanks together

(a) Start the suction pumps on the fuel tanker. This will supply thenecessary negative pressure of 0.76 bar (11 psi). This pressure isthe maximum negative pressure allowed.

(b) Push and hold in the MCB on the refuel/defuel isolation valves 505QU1and 502QU2.

NOTE : The MCB must be held in all the time the defuel is inprogress.

(c) Use the MMIs to monitor the fuel contents in the tanks. You can alsouse the gauges in the tanker to monitor the fuel quantity removed.

(d) When each tank becomes empty, set the applicable fuel valve to theclosed position.

(e) When the defuel is complete you must :– stop the suction motors on the fuel tanker– release out the MCB which will return the refuel/defuel isolationvalves to the normal position

– return all the valves that you manually opened to the originalpositions and install the elelctrical actuators.

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Cockpit Fuel ControlsFigure 4

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Cockpit Fuel IndicationFigure 5

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Refuel/Defuel Component LocationsFigure 6

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External Electrical Wiring Harness and Control BoxFigure 7

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Manual Magnetic Indicator LocationsFigure 8

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6. Procedure to Drain the Remaining Fuel (Ref. Fig. 9)

When you have defueled an aircraft you will still have a quantity of fuelin the tanks. This fuel is the remaining fuel (unusable) that you cannotremove with a defuel.

A. Drain the unusable fuel that you cannot remove with a defuel

WARNING : AIRCRAFT FUEL IS POISONOUS.DO NOT GET THE FUEL IN YOUR EYES OR MOUTH.DO NOT GET THE FUEL ON YOUR SKIN FOR A LONG TIME.

(1) Make sure that the fuel tank to be drained has been defuelled tothe unusable fuel level.

(2) If necessary, put an access platform below the applicable waterdrain valve.

(3) Put a container with a minimum capacity of 200l (53 US gal) belowthe water drain valve.

(4) Put the hose in the container and install the drain tool in thewater drain valve.

(5) Operate the drain tool to open the water drain valve.

(6) To prevent any leakage, continuously monitor the fuel flow intothe container.

(7) When the fuel flow stops, operate the drain tool to close thewater drain valve.

(8) Remove the drain tool from the water drain valve.

(9) Discard the drained fuel, (you must refer to your local disposalregulations).

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Water Drain Positions and Drain ToolFigure 9

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7. Close-up

A. Stop the EIS and the ECAM if they have been used.

B. De-energize the aircraft electrical system and disconnect the GPU fromthe aircraft if it is has been used.

C. Remove the GPU from its position near the aircraft, if it has been used.

D. Close the access panel 198DB.

E. Disconnect the hoses from the aircraft refuel/defuel couplings and refitthe refuel/defuel coupling caps.

F. Close both access panels 522HB and 622HB and remove the access platformsfrom below the panels.

G. Disconnect all the ground cables from the tanker and the aircraft.

H. Move the fuel tankers away from the safety area and the fueling zone.

J. Remove all the ground support equipment, maintenance equipment, tools andother items from the area.

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REMOVAL OF PAYLOAD

01. General

Removal of the payload is necessary to reduce aircraft weight for recovery.In passenger aircraft, the removal of baggage/cargo containers, cargopallets and bulk cargo must be considered. It is assumed, for the purposesof this publication, that the total payload is to be removed. This sectionincludes removal of containers/pallets and other Unit Load Devices (ULD)from the aircraft.

If the aircraft has come to rest on an unpaved or soft surface, access tothe aircraft with normal loaders, transporters and other vehicles with smallwheels and low ground clearances may be a major difficulty. In thisparticular case, Pierced Steel Plank (PSP) type surfaces may be anadvantage.

With the aircraft in a nose-down attitude, the AFT cargo compartment doormay be higher than the type of loader available can reach. For access inthis instance, fork-lift type vehicles may be of use.

If the aircraft attitude is such that the cargo compartment doors are lowerthan normal container and pallet transporter vehicles may be close enough tothe desired height to permit direct unloading. Alternatively, standardcontainer or pallet conveyor equipment may be used.

Removal of containers and/or pallets from the aircraft will in most caseshave to be done manually, due to lack of electrical power supply for thecargo loading system. Upward or downward movement of the aircraft about thelongitudinal or lateral axes, or a combination of both, may be expectedduring unloading, dependent on the at-rest attitude of the aircraft and onthe location of a specific container or pallet in the cargo compartment.

A block and tackle or other tensioning equipment may be used to pullcontainers upwards or to restrain them when being lowered. If a rope isused, it can be looped around the container and the opposite end anchoredaround the side guide tie-down attachment. Pallets may also be removed bythis method, provided that they can withstand the strain of a rope loop. Ifnot, it is advisable to unload the pallet piece by piece. If there is aconsiderable height difference between the door threshold and the loadingequipment, restraint from inside and a pulling force from outside may benecessary. Pulling may be achieved by means of a block and tackle anchoredto the loading vehicle, a tractor with a rope of suitable strength or bymeans of a vehicle equipped with a winch. It is possible that damage tocontainers may result when using this method.

Bulk cargo may be removed from any of the cargo compartments by any of themethods previously mentioned or by manhandling, if the weight of these itemspermits. For aircraft which have ″load thru capability″, large items of bulkcargo which have been loaded thru the AFT cargo compartment into the Bulkcargo compartment must be unloaded the same way. The divider net must firstbe released and any latches lowered which are in the way of cargo.

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2. FWD, AFT and Bulk Cargo Compartment Doors – Operating Instructions

A. General

The following instructions detail various methods of gaining access tothe FWD, AFT and Bulk cargo compartments. For this purpose it must beassumed that electrical and hydraulic power is not available and that thedoors cannot be opened in the normal way. If access can be gained to theright-hand side of the belly fairing, it may be possible to open the FWDand AFT cargo compartment doors using the hand pump.

B. Open the FWD and AFT cargo compartment door using the hand pump (Ref. AMMTASK 52-30-00-010-802).

C. Open the FWD or AFT cargo compartment door when the hydraulic system isdefective (Ref. AMM TASK 52-30-00-010-804).

D. Open the Bulk cargo compartment door (Ref. AMM TASK 52-30-00-010-803).

3. Manual Unloading of the FWD and AFT Cargo Compartment (Fig. 1 and 2)

A. The following instructions refer to the unlatching and positioning ofcontainers and pallets prior to their removal from the cargocompartments. No attempt is made to provide firm rules for removalprocedures, as these will largely depend on the attitude of the aircraftat rest. However, the notes contained in Paragraph 1. General, should beof assistance in determining the method to be employed.

WARNING : CONTAINERS AND PALLETS MUST BE RESTRAINED BEFORE RELEASINGLATCHES IF CARGO COMPARTMENT FLOOR IS NOT LEVEL. SEE 1.GENERAL.

Refer to the Cargo Loading Manual (CLS) for the method of raising andlowering the latches used in the cargo loading system.

Floor plans with procedures detailing the unloading steps for the ULD areprovided in Fig. 1 and 2.

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Manual Unloading – FWD Cargo CompartmentFigure 1

MODEL 200 & 300

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Manual Unloading – Aft Cargo CompartmentFigure 2

MODEL 200 & 300

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TETHERING

1. General

A. During lifting operations of a damaged aircraft, in which cranes, jacks,and/or inflatable bags are used, the aircraft should be tethered toprevent horizontal shifting due to lifting side forces, (weight of theaircraft, wing forces, etc...). Tethers can be attached to fabric slingspassed around the fuselage or the engine pylons or to different fittiangssuch as pylon hoist fittings, fuselage fittings and vertical stabilizefittings.

B. To ensure satisfactory horizontal stability, aircraft tethering cablesshould be secured to heavy vehicles or to deadmen fixed firmly in theground ; the tethers should lead at various angles to the fuselage centerline so that aircraft shifting in any direction is prevented. Figure 1shows a typical installation which might be used.

C. A tensioning device should be provided for each tethering line so that asteady but no excessive tethering action is maintained throughout thelifting operation.

D. The number of tethers will vary with the type of recovery operation andaccording to wind strength and direction. Figure 2 shows approximately theforces exerted on the aircraft according to their magnitude and direction.

2. Tethering

A. Using straps and/or cablesIf tethering fittings are not availablem or if it is impossible to installthem, the aircraft can be tethered with straps or cables passed around theengine pylons and the fuselage main frames on which the slings secured tothe ground will be fitted. In this case, it is necessary to protect thefuselage with pylwood sheets covered with thick padding at places wherecables or straps are in contact with the fuselage. The fuselage framescapable of bearing these loads are frames 17, 36, 59 and 76.

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B. By means of tethering fittings (For P/N Ref. See chapter 5.20 § 3)

Figure 3 shows positions on the airplane at which fittings can beinstalled.On the fuselage, fitting attachment points are blanked off by screws whichmust be removed.

WARNING THE SAME FITTING MUST NOT BE USED TO TETHER AND LIFT THE AIRPLANEAT THE SAME TIUME ; THE STRESSES IMPOSED ON THE STRUCTURE WOULD BETOO SEVERE.

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Example of TetheringFigure 1

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Ground Wind LoadsFigure 2

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Location of Tethering FittingsFigure 3

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Tethering Fittings at FR36Figure 4

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Tethering Fittings at FR59-FR76Figure 5

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LIFTING DAMAGED AIRCRAFT

This section describes the ways and means to lift the aircraft by means ofeither inflatable bags (3-26) or hydraulic jacks (3-27) or by using theauxiliary jacking points (3-28) in the various configuration listed below :

– Nose gear retracted, collapsed or lost (3-21)

– Main gear retracted, collapsed or lost (3-22)

– One main gear retracted, collapsed or lost (3-23)

– Nose gear and either left or right hand main gear retracted, collapsed or lost(3-24)

– All gears retracted, collapsed or lost (3-25)

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NOSE GEAR RETRACTED, COLLAPSED OR LOST

01. General

In all probability, the aircraft will be resting on the main gears, theengine nacelles, and on the nose gear door area at the lower forward part ofthe fuselage, the front jack pad being probably damaged (ref. Figure 1). Themost obvious lifting methods consist in :– Lifting the aircraft at FR17 with a strap, a cross bar and crane,– Lifting the aircraft at FR17 by means of 2 special fittings either withjacks, or with a crane, a cross bar and 2 slings,

– Lifting the aircraft with inflatable bags placed under the fuselage.– Any combination of the above 3 methods.

The choice of the lifting method depends on the weight and the aircraftH-arm as computed in section 2 and the lifting means available.

It is obviously advisable to locate the H-arm as far back as possible in theaircraft, but without tilting the aircraft on to the aft fuselage. Thetables included in this section give the reactions and lifting limitationsversus aircraft CG and weight. If the reaction is above the limitation, theaircraft H-arm location can be moved by :– Reducing the weight of the aircraft by removing removable equipment.

WARNING : IN NO CIRCUMSTANCES MUST THE AIRCRAFT H-ARM LOCATION BE FURTHERBACK THAN TBD.

02. Lifting

A. Using a strap aft of FR17, a cross bar and a crane.

Figure 2 gives the reactions at FR17 according to the weight, theaircraft H-arm location and the lifting limitation by one strap.Figure 3 gives the minimum dimensions of the strap and the approximateheight to which the aircraft must be lifted. The strap must obligatorilybe positioned immediately aft of FR17.

B. By means of two special fittings installed at FR17

Figure 4 shows a drawing of the fittings

(1) Using hydraulic jacks

Figure 5 gives ground clearances of the fitting jack pads, aircrafton the ground and aircraft lifted.

Figure 2 gives the reactions at FR17 according to the weight andaircraft H-arm and the lifting limitation by 2 jacks.It is advisable to use jacks provided with a loadmeter.

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NOTE : When the lifting is achieved by jacks, the variation of thehorizontal projection of the distance between the restingpoints of the aircraft on the ground is 0.1 m (0.33 ft)maximum ; if special articulated jacks are not available, itis advisable to carry out the lifting operation in incrementsby blocking and moving the jacks.

(2) Using two slings, a cross bar and a crane

Figure 6 gives the measurements of the cross bar, the slings and theheight from the ground of the Reference Fuselage Datum (RFD) of theaircraft when lifted.

Figure 2 gives the reaction at FR17 according to the weight andaircraft H-arm and the limitation of lifting with two slings.

It is advisable to use slings provided with a loadmeter.

C. Using inflatable bags

Using of inflatable bags is covered in section 3-26. As the zones whichrest on the bags will be practically touching the ground, it will benecessary to pre-lift using one of the methods mentioned above, in orderto be able to slide the bags under the fuselage ; however, if consistencyof the ground so allows, a trench may be dug out under the aircraft.

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Nose Gear CollapsedFigure 1

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Reactions at FR 17Figure 2

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Hoisting by a Strap at FR17Figure 3

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Fittings at FR17Figure 4

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Jack Pads at FR17Figure 5

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Hoisting by 2 slings at FR17Figure 6

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MAIN GEARS RETRACTED, COLLAPSED OR LOST

01. General

The aircraft rests on the engine nacelles and the aft fuselage (Fig. 1).The most obvious methods of lifting the aircraft consist in :– Using hydraulic jacks,– Using inflatable bags.

Whatever the method used, a jack will be placed at the front jack pad ; thenose gear is not necessarily in contact with the ground as its positiondepends on the damage to the engine nacelles.

02. Lifting

A. Using hydraulic jacks

Section 3-27 covers lifting with hydraulic jacks and gives theinformation required for their utilisation ; it also gives thepermissible loads and the location of the jacking points.The height of the wing jack pads from the ground when the aircraft is onthe ground can vary from 2.30 m (7.5 ft) to 3.30 m (10.8 ft)this height depends on the degree of damage to the engine nacelles.

The height of the wing jack pads when the aircraft is lifted is about5.8 m (19.0 ft).

B. Using inflatable bags

Section 3-26 covers utilisation of inflatable bags and gives thenecessary instructions for use.For aircraft lifting, it is preferable to place 2 bags on each side ofthe aircraft between the fuselage and the engine pylon taking care not toplace bags under the jack pads.

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Main Gears Retracted, Collapsed or LostFigure 1

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ONE MAIN GEAR RETRACTED, COLLAPSED OR LOST

01. General

In all probability, the aircraft will be resting on the nose gear, on one ofthe main gears and the engine nacelles of the damaged side (Fig. 1). Theaircraft may be in an unstable condition, depending on aircraft H-armlocation, with a risk of tilting backwards on to the aft fuselage. The firststep is therefore to place inflatable bags under the aft fuselage (Ref.section 3-26).These bags must be deflated as the down wing is raised, to avoid excessivestress on the aircraft skin.Lifting methods consist in :

– using hydraulic jacks under the lifting points.– using inflatable bags.

02. Lifting


Section 3-27 covers lifting with hydraulic jacks and gives theinformation required for this process. A jack will be placed under thedamaged wing jack pad. The height of the jack pad from the ground, whenthe aircraft is on the ground, is about 3.6 m (11.8 ft), this heightdepends on the degree of damage to the engine nacelles. The height of thewing jack pad when the aircraft is lifted is about 5.8 m (19.0 ft) toallow extension of the gear, if this is possible. The maximum load a wingjack pad can bear is 73 700 daN. It is advisable to place jacks under thetwo remaining jack pads.


Section 3-26 covers utilisation of inflatable bags and gives thenecessary instructions for use. Two bags should be placed between thefuselage and the engine the pylon ; two more should be placed beyond thepylon.

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One Main Gear RetractedFigure 1

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NOSE GEAR AND EITHER LEFT OR RIGHT HANDMAIN GEAR RETRACTED, COLLAPSED OR LOST

01. General

The aircraft rests on the front lower part of the fuselage on the nose geardoors, on the engine nacelles, and on the opposite main gear (Fig. 1) ; theforward jack pad is probably damaged.

02. Lifting

For reason of structural resistance, the lifting operation must be done intwo stages :

1°) Lift the aircraft under the wing of the damaged side, following theprocedure described in section 3-23.

The height of the wing jack pad from the ground when the aircraft is onthe ground, is about 4.30 m (14.1 ft).

2°) Lift the aircraft by the forward fuselage, following the proceduredescribed in section 3-21.

Note : By using this method, further damage to the aircraft will be avoided,and less personnel will be required for the lifting operation than ifthe aircraft was lifted under the wing and forward fuselagesimultaneously.

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Nose Gear and Either Left or Right HandMain Gear Retracted

Figure 1

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ALL GEARS RETRACTED, COLLAPSED OR LOST

01. General

The aircraft rests on the engine nacelles and on the aft lower part of thefuselage (ref. Figure 1).The most obvious lifting methods consist in :

– Using hydraulic jacks– Using inflatable bags.

02. Lifting


Section 3-27 covers lifting with hydraulic jacks and gives theinformation required for their utilisation ; it also gives thepermissible loads and the position of the jacking points. It is advisableto use jacks provided with loadmeters.

The height of the wing jack pads from the ground when the aircraft is onthe ground is about 2.9 m (9.5 ft), the height of the forward jack padfrom the ground is about 3.40 m (11.1 ft) These dimensions are given onlyas an indication since they depend on the degree of damage to the enginenacelles.

The height of the jack pads when the aircraft is lifted, is about 4.37 m(14.3 ft) for the forward jack pad and 5.8 m (19 ft) for the wing jackpads ; these heights allow the gears to be extended if this is possible.


Section 3-26 covers utilisation of the inflatable bags and gives thenecessary instructions for use.

– Place 2 bags under the forward fuselage aft of FR26.– Place two bags on each side of the aircraft, under the wings, betweenthe fuselage and the internal engine pylon.Depending on the weight of the aircraft, one or two more bags can beplaced under each wing outboard of the engine pylons ; in nocircumstances must the bags be placed under the jack pads, as thiswould prevent positioning of the jacks.

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All Gears RetractedFigure 1

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LIFTING USING INFLATABLE BAGS

01. General

Lifting a damaged aircraft with inflatable bags is subject to a certainnumber of specifications which must be scrupulously observed ; thesespecifications are given in the "Specifications For Use" delivered by thevendors with the equipment.

02. Use of Inflatable Bags

Figure 1 shows those undersurfaces of the aircraft capable of withstandingon bagloads ; with bags inflated between 3.5 and 7 psi.Figure 2 shows the positions at which bags may be placed (for example).All bags are capable of lifting : See Page 3.As this means of lifting is not stable, avoid covering the jack pads underthe wing in order to allow positioning of hydraulic jacks at the earliestopportunity.

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ALLOWABLE Bearing SurfaceFigure 1

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Example Of Location For Inflatable BagsFigure 2

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LIFTING WITH HYDRAULIC JACKS

01. General

Positioning of the jacks under the aircraft jack pads, shown in page 2, isdefinitely the safest procedure for lifting a damaged aircraft. However somegeneral rules are to be observed.

The ground must be suitably prepared in order to provide a firm base for thejacks.

When the aircraft is not level with the ground, the jack head moves throughan arc during lifting and generates side forces on the ball pads which couldcause accidents. In such cases, it is advisable to lift in increments,shoring the aircraft and repositioning the jacks each time. However jacksnow exist with rams articulated on the base thus removing the risk ofaccidents.

02. Lifting by Means of Jacks

– The dimensions of the jacks pads are shown on page 4.– The aircraft height when it is on jacks are shown on page 5.

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Landing Gear and Jacking Point Location

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JACKING DESIGN

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Forward Jacking Point A, Underwing Jacking Points BSafety Stay Point C

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Load at the Aircraft Jacking Points

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AUXILIARY JACKING POINTS

1. General

For certain types of accidents, foreseeable or not, the aircraft jack padsare unusable, the lifting procedure with inflatable bags is not applicableand it is advisable to provide for adapters under the wings and the fuselagefor an alternative means of lifting.

CAUTION : Aircraft must not be lifted or supported by the wings or fuselagealone without adequate support of the other.

2. Auxiliary Jacking Points (Ref. page 3)

A. Under the fuselage

Frames which are capable of supporting loads are noted below as well asthe maximum permissible loads for each frame.

– Shoring fittings : (each side)

– FR 7– FR 17– FR 261

– FR 32– FR 36– FR 391

– FR 538

– FR 59– FR 76

– Shoring cradles :

– FR 17– FR 18 to 37– FR 532

– FR 56 to 72

– Safety stay pad :

– FR 85

A330-300 A330-2001 000 daN 1 000 daN8 250 daN 8 250 daN3 750 daN3 750 daN 3 750 daN2 950 daN 2 950 daN11 450 daN 11 450 daN11 000 daN 11 000 daN3 950 daN 3 950 daN7 450 daN 7 450 daN

15 000 daN 15 000 daN5 000 daN 5 000 daN each12 000 daN 12 000 daN5 000 daN 5 000 daN each

4 500 daN 4 500 daN

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B. Under the wings

Shoring cradles positioned under the wings can be used in the operationto recover a damaged aircraft.

Typical recovery action may require the aircraft to be supported whilst areplacement/retracted/collapsed landing gear is made functional.Functional landing gear is necessary in the recovery, to permit theaircraft to be moved from the accident area.

The shoring cradles, each with two adjustable pads, 152.4 mm (6.0 in)square, may be positioned at locations under each wing. These locationsare detailed in Table 1 and shown on page 3.

The adjustable pads are faced with thin rubber and contact the wingprofile at the datum intersections of the ribs and the front and rearspars (F/S and R/S).

Table 1 shows the maximum load limit allowed at each jack pad when thewings are supported by the cradles. These load limits apply to all A330aircraft and variants.

It is important that the loads at each rib position are not exceeded ordamage to the aircraft may occur.

RIBPOSITION SPAR

MAXIMUM ALLOWABLE LOAD

daN lbf

6 F/S 7651 172006 R/S 7651 17200

15 F/S 4782 1075015 R/S 4782 10750

22 F/S 5600 1259022 R/S 5600 12590

27 F/S 4650 1045427 R/S 4650 10454

31 F/S 3899 876531 R/S 3899 8765

Table 1 - Maximum Allowable Load at each Jack Pad

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Location auxiliary Jacking Points

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MOVING DAMAGED AIRCRAFT ON ITS LANDING GEAR

1. General (Ref. Figure 1)

This topic deals with moving damaged aircraft on its landing gears.

To move the aircraft the landing gears must be functional.This may require the aircraft to be lifted.

The information contained in this topic provides details of the following :– manual extension of the landing gears– jacking loads required to lift the aircraft at the wing and fuselagejacking points

– jacking loads and heights required to lift the aircraft at the landinggears.

There are two designs of nose landing gear (NLG) used on this aircraft.These are as follows :– single stage shock-absorber – Model 300 (up to 218T)– two stage shock-absorber – Model 300 (up to 218T)

– Model 300 (230T)– Model 200 (230T)

After the aircraft has been lifted, it is possible to extend and lock themain and nose landing gears down. The aircraft can then be towed to therepair area.

WARNING : BEFORE YOU EXTEND THE LANDING GEAR(S) MAKE SURE THAT :– ALL PERSONS ARE IN A SAFE POSITION– THE AIRCRAFT IS SUPPORTED AND MOORED CORRECTLY– ALL EQUIPMENT IS REMOVED FROM THE AREA WHERE THE LANDING GEAR(S)WILL EXTEND (REF. FIG. 1).

2. Manual Extension of the Landing Gear(s) (Ref. Figures 2 and 3)

A. Remove all damaged gear-doors. If the doors are badly damaged, you canbreak them to remove them.

B. The nose and main landing gear(s) can be extended by the free fall system.The system is operated electrically by switches on panel 312VU in thecockpit (Ref. Fig. 2). The switches must only be used if it is safe toenergise the aircraft electrical network.

If it is not safe to energise the electrical network, the landing gear(s)can be extended :– by the connection of an external power supply through control unit, PartN°.98F32001001000, to each of the electrical actuators 5GF, 6GF and7GF, (Ref. Fig. 3)

– manually, by removal of the applicable electrical actuator(s) 5GF, 6GFand 7GF, and the use of a ratchet and splined drive, Part N°.98F32104022000 (Ref. Fig 3).

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The main landing gears lock down by their own weight and the springs on thelock links.

Install the Landing Gear Ground locking pins when the landing Gears areextended.

Visually inspect all the Landing Gear and their attachments for damage andcorrect attachment before the aircraft is moved.

3. Jacking Loads at Wing and Fuselage

Loads of the wing and fuselage jacking points are shown in the graphs infigures 4 and 5.

4. Jacking Loads and Heights at Landing Gears

Loads at the main landing gear and nose landing gear jacking points are shownin figures 6 and 7. Important heights when jacking for damaged wheels andtires are shown in figures 8 and 9.

5. Moving the Aircraft

Refer to chapter 4-21 for the procedure to move the aircraft on its landinggear.

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C. The main landing gears lock down by their own weight and the springs onthe lock links.

Install the landing gear ground locking pins when the landing gears areextended.

D. Visually inspect all the landing gears and their attachments for damageand correct attachment before the aircraft is moved.

3. Jacking Loads at Wing and Fuselage

Loads of the wing and fuselage jacking points are shown in the graphs (Ref.Figs. 4 and 5).

NOTE : Load at Jacking Point is the load required to give 25.4 mm (1.10 in.)clearance between wheel and ground.

4. Jacking Loads and Heights at Landing Gears

Loads at the main landing gear and nose landing gear jacking points are shown(Ref. Figs. 6 and 7). Important heights when jacking for damaged wheels andtires are shown (Ref. Figs 8 and 9).

NOTE : Load at Jacking Point is the load required to give 25.4 mm (1.0 in.)clearance between wheel and ground.

5. Moving the Aircraft

Refer to chapter 4-21 for the procedure to move the aircraft on its landinggear.

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Landing Gear FootprintFigure 1

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Free-Fall Selector SwitchesFigure 2

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Free-Fall ActuatorsFigure 3

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Wing Jacking Point LoadsFigure 4 (Sheet 1)

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Wing Jacking Point LoadsFigure 4 (Sheet 2)

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Fuselage Jacking Point LoadsFigure 5 (Sheet 1)

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Fuselage Jacking Point LoadsFigure 5 (Sheet 2)

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MLG Bogie Jacking Point LoadsFigure 6 (Sheet 1)

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MLG Bogie Jacking Point LoadsFigure 6 (Sheet 2)

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NLG Axle Jacking Point LoadsFigure 7 (Sheet 1)

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NLG Axle Jacking Point LoadsFigure 7 (Sheet 2)

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MLG Jacking Point HeightsFigure 8 (Sheet 1)

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NLG Jacking Point HeightsFigure 9

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TOWING

1 – General

The A330 is designed with means for conventional tractor towing.

It is possible to tow or push the aircraft, at maximum ramp weight withengines at zero or up to idle thrust, using a tow bar attached to the nosegear leg. The two bar fitting is installed at the front of the leg.

The main gears have attachments points for towing and debogging. Theseattachment points are be able to be used to restrain the aircraft when theengines are running at up to maximum thrust.

2 – Approximate Towing Loads

Aircraft towing forces cannot be accurately calculated.

They can only be established through experience or testing.

For the A330 as for most aircraft, the following maximum values have beenset :

– Breakaway on dry level concrete : 6 % x MTW– To maintain rolling on level surface : 3 % x MTW– Breakaway on slope : 6 % x MTW

+ 1 % x MTW per1 % slope

– To maintain rolling on slope : 3 % x MTW+ 1 % x MTW per1 % slope

Note :

– In all above formula, MTW = Maximum Taxi Weight.

– When the aircraft is pushed rearward with the engines idling, the enginethrust resistance must be added to the above formulae values.

Moreover, the following coefficients of friction between the tow tractor tiresand the ground have been adopted :

– Dry concrete or asphalt : 0.80– Wet asphalt : 0.75– Wet concrete : 0.57– Hard snow : 0.20– Ice : 0.05

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3 – Limit Loads and Angles

The limit towing loads and angles are shown in page 4.

Whatever the towing arrangement used, the steering angle allowed on eachside of the aircraft centerline is 83° only when the nose wheel steeringdesactivation electrical-box towing lever in towing position and locked witha special pin.

The steering angle is limited to 40° during rearward pushing with theengines at idle to avoid the possibility of NLG tire slippage.

4 – Towing by Main Gears (Ref. page 5)

Forward of rearward towing by the main landing gears uses two fork-shapedfittings and a cable. The two fittings, which are specific tools, areattached to lug provided at each end of the gear.The two fitting/cable set is provided with a safety shear pin calibrated to51300 daN (115322 lbf).

5 – Landing Gear Downlock Ground Safety Pins

If required the landing gear may be mechanically locked in the "down"position during towing by inserting a ground safety pin in the nose geartelescopic drag strut (Ref. page 6) and a ground safety sleeve around theMLG Lock Link actuator ram.

NOTE : If gear braces are damaged they may be replaced with steel juryrigging to permit towing to the maintenance area.

6 – Nose Gear Tow Bar

Towing by Nose Gear FWD Fitting (Ref. page 3)

A conventional type tow bar designed in accordance WITH SAE ARP 915 isrequired, and should be equipped with a damping system to protect the nosegear against jerks and with towing shear pins :

– (calibrated to 28620 daN) (64337 lbf) for gear protection againstexcessive loads.

– (calibrated to 3130 m.daN) (23100 lbf.ft) for gear protection againstexcessive torque.

The towing head is designed according to SAE AS 1614 cat I.

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Nose Gear TowingFittings

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MAX GEAR LOADS

daN lbf

A 28620 64337

B 51300 115322

Limit Towing angles

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Main Landing Gear Cable Towing

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Downlock GroundSafety Pin

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TAXIING AND TOWING OF AIRCRAFT WITH DEFLATED TIRES

1. General

When you have deflated tires on an aircraft it will limit the movement youcan make on the ground.

The deflated tires can be on one or more of the Landing Gears. They canlimit the movement in these ways :– they limit the aircraft from being moved at taxiing speed on certainnose-wheel steering angles

– they limit the aircraft from being towed at the maximum towing angles.

There are two methods which you can use to move an aircraft these are :– with its own power (taxiing)– with a tow (towing).

2. Taxiing Using Two Engines (Ref. Figure 1).

In figure 1, you will find three different Landing Gear configurations withdeflated tires. These are found on Curves A, B and C. Figure 1 also showsthese configurations with the maximum nose-wheel steering angle at differentaircraft speeds.

A. Yous must look at Curve A, if any one tire is deflated on one or morelanding Gears.

You are permitted a maximum of three deflated tires for each aircraft,this is a maximum of one for each Landing Gear.

If you have more than three deflated tires you must look at anothercurve.

When you look at Curve A, the maximum steering angle that you arepermitted is 65 deg.

B. You must look at Curve B if you have one deflated tire on each axle ofone or both Main Landing Gears together with :– one Nose Gear deflated tire.

You are permitted a maximum of five deflated tires for each aircraft.There must not be more than one deflated tire on any axle.

If you have more than five deflated tires you must look at a differentcurve.

When you look at Curve B the maximum steering angle that you arepermitted is 65 deg.

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C. You must look at Curve C, if you have three deflated tires on one or bothMain Landing Gears together with :– one Nose Gear deflated tire.

You are permitted a maximum of seven deflated tires, but there must be atleast one inflated tire on each Landing Gear.

When you look at Curve C, the maximum steering angle that you arepermitted is 50 deg.

NOTE : You must not use the nose wheel steering if all four tires on thesame Main Gear are deflated.

In these configurations you must also limit the aircraft speed to2.5 m/s.

3. Towing

When you tow an aircraft with deflated tires you must refer to theconfigurations that follow.

These configurations prevent the aircraft from being towed as usual.

A. You can tow an aircraft by the Nose Gear if any one tire is deflated onone or more Landing Gears.

You are permitted a maximum of three deflated tires for each aircraft.

You can tow an aircraft by the Nose Gear when :– one of the Nose Gear tires is deflated (the maximum angular movement ofthe towbar is ± 10 deg.).

– both Nose Gear tires are inflated (the maximum angular movement of thetowbar is ± 40 deg.).

B. You can also tow an aircraft by the Nose Gear when :

– any one tire or two tires (one on each axle) is deflated on any one MainGear

– both Nose Gear tires are inflated (the maximum angular movement of thetow bar is ± 10 deg).

C. You must tow an aircraft by the Main Gear if :

– two tires on the same axle are deflated– or three tires on the same Main Gear are deflated.

When you tow an aircraft by the Main Gear, both Nose Gear tires must beinflated.

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JUL 30/93

In this configuration you must steer the aircraft by the Nose Gear or bythe normal steering-control. The maximum nose-wheel steering angle thatyou are permitted is ± 50 deg.

D. You must tow the aircraft by the Main Gear if all four tires on the sameMain Gear are deflated

When you tow an aircraft by the Main Gear, both Nose Gear tires must beinflated.

You must limit the aircraft speed to 1.3 m/s. When you tow the aircraftin this configuration no angular movement of the towbar is permitted.

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JUL 30/93

Allowable Nose-Wheel Steering Angle Against Forward Speed

Figure 1

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JUL 30/93

RETURNING UNDAMAGED AIRCRAFT TO RUNWAY

1. General

A. When, as a result of various circumstances, an aircraft has left therunway, it may be partially or completely bogged. Probably there will beno damage to the aircraft but other than normal towing is necessary toturn the aircraft to the runway.

B. If only the main gear of one side is off the runway all fuel should beremoved or transferred from wing with bogged gear to opposite wing tank.Refer to Aircraft Maintenance Manual for applicable fuel transferprocedures.

C. Aircraft weight should be reduced as near as possible to the emptyequipped weight except for fuel in the case mentioned above.

D. In practically all cases, the runway or a major taxiway will be blockednecessitating rapid clearance in order that the airport may resumeoperations. Valuable time will be saved by planning the job to completionbefore starting the operation.

2. Job Planning

Job Planning to completion should include the weight to be removed, conditionof terrain, direction aircraft is to be towed, equipment available to installan emergency runway, tractors, hoists and towing vehicles available.

A. Determine whether it is necessary to lift the aircraft to strengthen theground under the wheels, and start digging to prepare ramps gentlyinclined up to the ground level.

B. If the accident has been caused by malfunction of the brakes or of thenose gear steering, take the necessary steps to free seized brakes orlocked steering.

C. Ensure that available vehicles are capable of towing the aircraft on theramps.

D. Prepare the ground in the direction chosen for towing. Fill the holes withcrushed rock or gravel. If the equipment necessary for an emergency runwayis not available, a track is to be constructed with timbers covered withsteel plates or plywood sheets.

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JUL 30/93

E. Make sure that the method used is adapted to the nature of the terrain.

F. Ensure that a sufficient quantity of material is available to constructfoundations for ramps.

3. Return of Aircraft to Runway

Note : If the wheels have bogged down only to a depth of less than center ofaxle and if they do not sink any further, it will not be necessary tolift the airplane to strengthen the ground under the landing gear.

A. Starting from the gear, construct gently inclined ramps in the directionchosen for towing ; these ramps should extend approximately one meter oneach side of the landing gear.The depth an length of these ramps depend on the depth that gear is boggeddown.

Note : On extremely soft ground the channel will require additionalexcavation and filling with resistant material (crushed rock orgravel) to provide sufficient bearing strength.

B. Lay heavy timbers or railroad crossties crosswise in each channel. Covertimbers or crossties with thick plywood sheets, steel sheets at least 6 mmthick or 20 mm thick light alloy sheets.

Note : To have a firm channel bottom, two layers of plywood will beplaced, one accross the ramp, the other one lengthwise ; ifplywood isused in this manner, joints must be straggered to avoidsteps under load.

Station towing and winching vehicles on a concrete surface.

Tow airplane form main gear. See chapter 4-21 for towing procedures.

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5-10Page 1

OCT 30/93

GENERAL RECOVERY EQUIPMENT

1. Jacks.

2. Work lights, floodlights.

3. Engine Removal Equipment (tools, slings, shipping trailers etc).

4. On-site communication equipment.

5. Ballast bags.

6. Sheets of plywood, steel plate, planking, etc...

7. Cribbing timber (railroad ties) to make platform for bags.

8. Bulldozers, forklift, cranes, winching vehicles, bucket loader forexcavating (as required).

9. Aircraft towing tractor.

10. Cables, pulley blocks, ladder.

11. Miscellaneous tools : shovels, picks, crowbars, sledge hammers, hoes,chainsaws, hammers and nails, handsaw, small hydraulic jacks, shackles,etc ...

12. Miscellaneous materials : Crushed rock, steel beams, padding to protectaircraft.

13. Mobile shelter-trailer; etc ...

14. Copperloy coated steel grounding rod with cable and clips.

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JAN 01/96

EQUIPMENT PECULIAR TO THE AIRCRAFT

1. Towing

Bar-steering nose wheel P/N 98F 09101003 000

Cable-Towing, main landing gear P/N 98F 09101002 000

2. Lifting and Shoring

– Jacks

Front Jack – Point A TR 470000 P/N 98F 07101000 000

Main Jack LH – Point B1 TR 090000 P/N 98F 07101001 000

Main Jack RH – Point B2 TR 090000 P/N 98F 07101001 000

Safety (FR85) – Point C TR 120000 P/N 98F 07101002 000

Fitting – FR7 LH P/N 98F 07203000 100

Fitting – FR7 RH P/N 98F 07203000 101

Fitting – FR17 LH P/N 98A 07003903 100

Fitting – FR17 RH P/N 98A 07003903 101

A/C Lifting Assy FR17comprising : P/N 98A 07003900 000

– Sling assy P/N 98A 07003900 001

– Hoisting beam P/N 98A 07003900 002

– Upper slings P/N 98A 07003900 003

– Sling fitted with ring P/N 98A 07003900 004

Fitting – FR26-1, 32, 36 LH P/N 98F 07203000 102

Fitting – FR26-1, 32, 36 RH P/N 98F 07203000 103

Fitting – FR39-1 LH P/N 98F 07203000 104

Fitting – FR39-1 RH P/N 98F 07203000 105

Fitting – FR53-8 LH P/N 98F 07203000 108

Fitting – FR53-8 RH P/N 98F 07203000 109

Fitting – FR59 LH P/N 98F 07203000 110

Fitting – FR59 RH P/N 98F 07203000 111

Fitting – FR76 LH P/N 98F 07203000 112

Fitting – FR76 RH P/N 98F 07203000 113

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JAN 01/96

Shoring Cradles - Damaged Aircraft Repair

Shall be placed under each wing and fuselage as necessary :

– Under FuselageFR : 11, 17, 26 to 58, 532, 72 and 80.

– Under WingRIB 6, 12, 22, 31

3. LIFTING USING INFLATABLE BAGS

– 30000 kg (66138 lb) and 6000 kg (13228 lb) high stability inflatable bagswith related hoses, valves and protectives pads.

– A Compressor delivering oil-free air at 3,5 and 7 PSI.

4. TETHERING

Tethering fitting at Frame 17 LH P/N 98A 07003903 100

Tethering fitting at Frame 17 RH P/N 98A 07003903 101

Tethering fitting at Frame 36 LH P/N 98F 07203000 102

Tethering fitting at Frame 36 RH P/N 98F 07203000 103





5. LANDING GEAR, Manual Extension

CONTROL UNIT P/N 98F 32001001 000

SPLINED DRIVE P/N 98F 32104022 000

SHORING ASSY, Under fuselage P/N 98F 07203001

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Airbus A330