A A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BeLLonte

31707 BLAGNAC CEDEX FRANCE

TeL : (33) 5 61 93 33 33

TeLex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - INSPECTION OF THE OUTER SHROUD BOX HINGE BRACKET

MODIFICATION No : None

This page transmits revision No. 05 of Service BuLLetin A300-57-6010.

ADDITIONAL WORK

No additional work is required by this revision for aircraft inspected by any

previous revision.

REASON

This Service BuLLetin has been issued to inform Operators that Flight Hours (FH)

conversion figures have been added to the AccompLishment TimescaLe. In addition a

maximum crack Length has been included.

CHANGES

SUMMARY

AIRBUS address has been amended.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Text has been amended.

- EFFECTIVITY

. Effectivity has been updated.

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

REVISION No. : 05 Feb 21/11 PAGE : 1

Printed in France
A300-6OO

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

SERVICE BULLETIN:

- AIRBUS address has been amended.

• Copyright statement has been moved below TITLE and Airbus Industrie has

been changed to AIRBUS.

PLANNING INFORMATION

EFFECTIVITY

. Para. (2)(a) Effectivity has been updated.

Para. (2)(b) Effectivity has been updated.

• Para. (2)(c) Effectivity by MSN and

kit/configuration has been added.

- REASON

. Para. B.(5) Text has been amended.

- APPROVAL

. ApprovaL statement has been amended

MATERIAL-COST AND AVAILABILITY

. AIRBUS address has been amended.

ACCOMPLISHMENT INSTRUCTIONS

INSPECTION

. Para. (4)(a) and (b) FH conversion figures have been added-

. Para. (4)(b) and (c) ALLowabLe criticaL crack Length Limit has been added.

. AI/SE-A has been changed to AIRBUS.

- CLOSE UP

- Para. (6) Airbus Industrie and AI/SE-A have been changed to AIRBUS.

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57.6010

REVISION No. : 05 Feb 21/11 PAGE : 2

Printed in France
A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

ACCEPTANCE/REJECTION SHEET:

. AIRBUS address has been amended.

FILING INSTRUCTIONS

1. Remove and destroy pages 1, 2 and 3 of the Summary and pages 1, 2, 3, 4, 5, 6,

7, 8 and 9 of the Service BuLLetin and page 1 of the Acceptance/Rejection sheet.

2. Insert pages 1, 2, 3 and 4 of the Summary and pages 1, 2, 3, 4, 5, 6, 7, 8, 8A,

88 and 9/10 of the Service BuLLetin and page 1 of the Acceptance/Rejection

sheet.

Put this Revision TransmittaL Sheet in front of the Service BuLLetin.

HISTORY OF PREVIOUS REVISIONS

This is only appLicabLe for Revision 05 and subsequent. If information is required

for revisions issued previous to this, please check your copies of Revision

TransmittaL Sheet or contact AIRBUS.

REVISION SEQUENCE

ORIGINAL : Dec

REVISION No.

REVISION No.

REVISION No.

REVISION No.

REVISION No.

17

01

02

03

04

05

/86

- Dec 14/90

- Mar 30/98

- Sep 16/98

- Feb 22/99

- Feb 21/11

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

REVISION No. : 05 Feb 21/11 PAGE : 3/4

Printed in France
A300-600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

TeL : (33) 5 61 93 33 33

TeLex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information onLy

and is not approved for modification of the aircraft

MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57

TITLE : WINGS — INSPECTION OF THE OUTER SHROUD BOX HINGE BRACKET

MODIFICATION No. : NONE

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

An ALL Operator TeLex (AOT) 57/86/01 has been issued to aLL A300 Operators requesting

inspection of the aft hinge brackets of the outer shroud box. This inspection revealed

that approximately half of aLL the brackets inspected were cracked.

This Inspection Service BuLLetin introduces a visuaL inspection of the forward and aft

outer shroud box hinge brackets for cracks or complete fracture of the bracket.

AccompLishment of this Service BuLLetin wiLL Lead to the early detection of the cracks in

the shroud box hinge brackets and wiLL prevent the fracture of the brackets. Fracture of

a bracket wouLd allow verticaL movement of the inner shroud box structure in the

immediate area which couLd result in damage to the top skin of the inboard flap.

AdditionaLLy, the Loads carried through the brackets wiLL be transferred to the remaining

supports which may aLso crack and cause extensive structural damage.

A detaiLed visuaL inspection is necessary of the shroud box hinge brackets.

The inspection thresholds and repeat intervaLs are given in this Service BuLLetin. In

addition a maximum crack Length is incLuded.

The inspection of the forward and aft brackets is onLy appLicabLe to aircraft which are

pre production Mod. No.06661H1033.

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57.6010

I REVISION No. : 05 Feb 21/11 PAGE : 1

Printed in France
A300-600

SERVICE BULLETIN

SUMMARY

NOTE : The originaL issue of this Service BuLLetin did not specify an inspection of

the forward hinge brackets. If the inspection of the forward hinge brackets,

in accordance with this Service BuLLetin at Revision 01 or any Later approved

revision, was not done before accompLishment of Service BuLLetin A300-57-6011

(Mod. 06661) you must do an inspection of the forward hinge brackets within

18 months from accompLishment of the modification.

AccompLishment of this Service BuLLetin has been rendered mandatory by the issue of an

Airworthiness Directive (AD) pubLished by the European Aviation Safety Agency (EASA). The

AD must be used as the reference document for the mandatory accompLishment timescaLe.

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

I REVISION No. : 05 Feb 21/11 PAGE : 2

Printed in France
© A300-600

SERVICE BULLETIN

SUMMARY

EFFECTIVITY

This Service BulLetiin is appLicabLe to these customers

AAL, AAW, DLH, F21, FDX, IRM, KAC, THA

SERVICE BULLETIN TO BE ACCOMPLISHED

PREVIOUSLY OR SIMULTANEOUSLY

None

REFERENCES/REPERCUSSIONS

TFU : 572200001

OEB : None

AOT : 57/86/01

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : None

OTHER : None

NATURE OF THE WORK

AIRCRAFT Yes

EQUIPMENT No

HARD No

SOFT No

OBRM No

COMPLIANCE

Mandatory

MANPOWER

Aircraft

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

MATERIAL INFORMATION

AIRCRAFT DATA

None

EQUIPMENT DATA

None

APPENDICES

None

DATE : Dec 17/86 SERVICE BULLETIN No. : A300 -57-6010

REVISION No. : 05 - Feb 21/11 PAGE : 3

Printed in France
© A300-600

SERVICE BULLETIN

SUMMARY

JOINT LINE USUAL STARTING POINT

OF CRACKS

CRACK IN VERTICAL

WEB RADIUS f /,

CRACK IN VERTICAL FLANGE

UNDER BEARING ASSY. NUT

EXAMPLE 'A'

EXAMPLE 'B'

DATE : Dec 17/S6 SERVICE BULLETIN No. : A300-57-6010

REVISION No. : 05 -- Feb 21/11 PAGE : 4

Printed in France
A3O0-600

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - INSPECTION OF THE OUTER SHROUD BOX HINGE BRACKET

MODIFICATION No. : NONE

This document contains AIRBUS PROPRIETARY INFORMATION and shatL at aLL times remain

the property of AIRBUS; no inteLLectuaL property right or License is granted by

AIRBUS in connection with any information contained in it. It is deLivered on the

express condition that said document and the information contained in it shall be

treated as confidentiaL, shaLL not be used for any purpose other than that for which

it is hereby deLivered. It shall not be disclosed in whole or in part to third

parties and shall not be duplicated in any manner (except for the purposes of

performing the tasks described hereunder and provided that any recipient of such

document shall comply with the conditions herein), without AIRBUS prior written

consent.

1. PLANNING INFORMATION

A.EFFECTIVITY

(1) Models

B4-601, B4-603, B4-605R, B4-620, B4-622, C4-620

(2) Aircraft

(a) Effectivity by MSN

The Service Bulletin is appLicabLe to aircraft MSN:

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348

0351 0354 0358 0361 0365 0368 0380 0398 0401 0405

0408 0411 0414 0423

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57.6010

I REVISION No. : 05 Feb 21/11 PAGE : 1

Printed in France
A300-600

SERVICE BULLETIN

NOTE : This Service BuLLetin is onLy appLicabLe to aircraft which

are pre production Modification No. 0661H1033. Modification

No. 06661H1033 has been embodied on aircraft MSN 388, 417,

420, 459 and subsequent.

(b) The Operator MSN relationship is provided for information onLy and

is correct at the time of issue in accordance with the information

available to AIRBUS. Any further changes resuLting from transfer

of an aircraft from one Operator to another wiLL not be refLected

in this List unless the Service BuLLetin is revised for another

reason.

OPERATOR MSN

AAL 0423

AAW 0354

DLH 0380 0401 0405

F21 0284 0294 0301 0307 0312 0317

0321 0336 0348 0351 0408

FDX 0358 0361 0365

IRM 0411 0414

KAC 0344

THA 0368 0398

Cc) Effectivity by MSN and Kit/Configuration

None

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

I REVISION No. : 05 Feb 21/11 PAGE : 2

Printed in France
S A300-600

SERVICE BULLETIN

(3) Spares

None

B. REASON

(1) History

An All Operator Telex (AOT) 57/86/01 has been issued to all A300

Operators requesting inspection of the aft hinge brackets of the

outer shroud box. This inspection revealed that approximately half

of all the brackets inspected were cracked or completely fractured.

Fracture of the bracket would alLow vertical movement of the inner

shroud box structure in the immediate area which couLd result in

damage to the top skin of the inboard flap. Additionally, the Loads

carried through the brackets will be transferred to the remaining

supports which may aLso crack and cause extensive structural

damage.

There is aLso some evidence of un— reported fractures of the forward

hinge bracket of the outer shroud box.

Pre production and retro Modification No. 06661H1033 (Service

Bulletin A300-57-6011) have been introduced which replace the

aluminium alloy aft bracket with a steel bracket.

(2) Objective/Action

A mandatory detailed visual inspection is required of the LH and RH

outer shroud box hinge brackets to detect any cracks or complete

fracture of the brackets on aircraft pre production

Mod.No.06661H1033.

NOTE: The original issue of this Service BuLLetin did not specify

an inspection of the forward hinge brackets. If the

inspection of the forward hinge brackets, in accordance

with this Service BuLLetin at Revision 01 or any later

approved revision, was not done before accompLishment of

Service Bulletin A300-57-6011 (Mod.06661) you must do an

inspection of the forward hinge brackets within 18 months

from accomplishment of the modification.

(3) Advantages

Accomplishment of this Service BuLLetin wiLL lead to the early

detection of the cracks in the shroud box hinge brackets and will

prevent the fracture of the brackets.

(4) OperationaL/Maintenance Consequences

None.

DATE : Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

D REVISION No. : 05 — Feb 21/1 PAGE : 3
A300-600

SERVICE BULLETIN

(5) AccompLishment TimescaLe

AccompLishment of this Service BuLLetin has been rendered mandatory by

the issue of an Airworthiness Directive (AD) pubLished by the European

Aviation Safety Agency (EASA). The AD must be used as the reference

document for the mandatory accomplishment timescaLe.

For those aircraft that are pre Modification No. 06661H1033 a

detaiLed visuaL inspection is to be done on the forward and aft

hinge brackets of the outer shroud box not Later than 5,000 FC or

10,400 FH. For aircraft already within the inspection program, the

inspection must be compLeted within the next interval period. However,

where the FH Limit only has been exceeded the inspection may be extended

to the previously planned FC inspections.

The repeat visuaL inspection intervaLs are as follows:

- If no cracks are found on either the forward or aft hinge

brackets, do the repeat inspection every 1,000 FC or 2,000 FH

untiL the Service BuLLetin A300-57-6011 (Mod- 06661H1033) is

embodied.

- If a crack not more than 8 mm in Length is found in one haLf bracket,

do the repeat inspection every 50 FC or 100 FH untiL repLacement of the

damaged hinge bracket.

If the crack Length is more than 8 mm or both haLf brackets are cracked

or a hinge bracket has fractured, repLace the bracket before the next

fLight.

I The inspection threshoLds and repeat inspection intervals are the same

1 for aircraft subject to normal range or short range operation.

NOTE : Each hinge bracket (forward and aft) is manufactured from two

half brackets joined at the verticaL face of the fLange which

supports its bearing assembLyC. DESCRIPTION

To accomplish this Service Bulletin it is necessary to:

(1) Get access to both the LH and RH inner and outer shroud boxes, forward

and aft hinge brackets.

(2) Do a detaiLed visual inspection of the hinge brackets.

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

I

REVISION No. : 05 Feb 21/11 PAGE : 4

Printed in France
A300 - 600

SERVICE BULLETIN

(3) Repair by repLacement, as necessary.

(4) If a bracket is cracked do additional visual inspections for secondary

damage of the support structure, attachment brackets and the top skin of

the inboard fLap in the area of the inner and outer shroud boxes.

(5) CLose-up after the work is accomplished.

D. APPROVAL

Approved under EASA Design Organisation Approval No. EASA.21J.031.

If an aircraft Listed in the effectivity has a modification or repair that is not

of AIRBUS origin, and which effects the content of this Service BuLLetin, the

operator is responsibLe for obtaining approvaL by its airworthiness authority for

any adaptation necessary before incorporation of the Service BuLLetin.

E. MANPOWER

This Inspection Service BuLLetin is written for an aircraft in a maintenance

condition. The manhours/eLapsed time does not include time to prepare for the

inspection, non-productive eLapsed time, repair or administration.

On aircraft

Get access 2.0

Inspection 4.0

Close-up 2.0

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

F. MATERIAL - COST AND AVAILABILITY

If repLacement brackets are required send a Spares Purchase Order, quoting this

Service BuLLetin number, to:

AIRBUS

MATERIAL SUPPORT CENTER

P.O. BOX 630262

22312 HAMBURG

GERMANY

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

REVISION No. 05 Feb 21/11 PAGE : 5

Printed in France
A3Oo-600

SERVICE BULLETIN

G. TOOLING - PRICE AND AVAILABILITY

None

H. WEIGHT AND BALANCE

Not changed

I. REFERENCES

Aircraft Maintenance ManuaL (AMM)

Service BuLLetin (SB)

J. PUBLICATIONS AFFECTED

None

06-41-57, 24-00-00, 27-50.00,

27-61.54

A300-57-6011

DATE: Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

REVISION No. : 05 Feb 21/11 PAGE : 6

Printed in France
© A300-600

SERVICE BULLETIN

2. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE

CAUTIONS IN THE REFERENCED PROCEDURES.

WARNING : PUT THE SAFETY DEVICES AND WARNING NOTICES IN POSITION

BEFORE YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND RELATED DOORS

- COMPONENTS THAT MOVE.

WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL

SURFACES ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A

HYDRAULIC SYSTEM.

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED

BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

(1) Preparation

(a) Make sure that the aircraft is electricaLLy grounded (Refer to

AMM: 24-00-00, P. Block 301).

(b) Put warning notices in the fLight compartment to teLL persons

not to operate the fLight controls.

(c) Put the safety barriers in position.

(d) Extend the flaps (Refer to AMM: 27-50-00, P. BLock 301).

(e) Extend the spoiLers 1 and 2 (Refer to AMM: 27-61-54, P. Block

401).

(f) Remove and retain the access panels 577CT, 57701 (LH) and

677CT, 677DT (RH), (Refer to AMM: 06-41-57, P. BLock 1).

(g) Get access to the Inner Shroud Box forward attachments through

the Main Landing Gear Bays.

(2) Standard Practices

None

B. INSPECTION

The procedure that follows is applicable to the (LH) and (RH) wings.

Refer to Figure 1

(1) Cleaning:

CLean the area to be inspected with Cleaning Agent (Mat. No. 11-026).

(2) Get access from the top surface of the wing through the gap between

the inner and outer shroud boxes. Move the seal between the shroud

boxes, as necessary, to visually inspect the top of the outer

DATE : Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

I REVISION No. : 05 - Feb 21/11 PAGE : 7

 Printed in France
© A300-600

SERVICE BULLETIN

shroud—box hinge brackets.

(3) Do a detailed inspection of the outer shroud—box forward and aft

hinge bracket assemblies, as follows:

(a) Inspect the small radius between the top fLange and the

verticaL fLange, as shown in exampLe 'A' and exampLe 'B' of

Figure 1, for signs of cracks on the hinge bracket.

(b) Get access from the lower surface of the wing and with the use

of an inspection mirror, visually inspect both haLves of the

hinge brackets for signs of cracks or fracture of the bracket.

NOTE 1 :Each hinge bracket (forward and aft) is manufactured

from two haLf brackets joined at the vertical face of

the flange which supports its bearing assembly.

NOTE 2 :The cracks can start in either of the two half brackets

and run down the vertical web radius (exampLe 'A' of

Figure 1), or run through the verticaL fLange under

the bearing assembly attachment nut (exampLe 'B' of

Figure 1).

(4) Use the results of the inspection to do one or more of the worksteps

that folLow:

(a) If no cracks are found on either the forward or aft hinge brackets, do the

repeat inspection every 1,000 FC or 2,000 FH or until Service Bulletin

A300-57-6011 (Modification 06661H1033) is embodied.

(b) If a crack not more than 8 mm in Length is found in one half bracket, do

the repeat inspection every 50 FC or 100 FH (whichever comes first) until

a repair is done, as detailed in Para. C. REPAIR.

(c) If the crack length is more than 8 mm or both haLf brackets are cracked or

a hinge bracket has fractured, do a repair as detailed in Para. C. REPAIR.

(d) If a crack is found in one half bracket or both haLf brackets,

do a visual inspection for secondary damage in the areas that

foLLow:

1 The inner shroud—box forward attachments and the attachment

brackets at the inboard end.

2 The inner and outer shroud—box structure, adjacent to the

fractured bracket.

3 The top skin of the inboard flap.

NOTE : If any damage is found contact AIRBUS for an

applicable repair procedure.

(5) If Service Bulletin A300-57-6011 (Modification 06661H1033) has been

embodied after the fracture of the aft hinge bracket, then visually

inspect the forward hinge bracket for cracks immediately after the

embodiment of the modification.

If this modification was embodied before the receipt of Revision 01

of this Service Bulletin, you must do a once only inspection of

the forward hinge brackets within 18 months from the embodiment

of the modification.

DATE : Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

I REVISION No. : 05 — Feb 21/11 PAGE : 8

Printed in France
© A300-600

SERVICE BULLETIN

C.REPAIR

(1) If a crack is found in one half bracket, Less than 8mm the bracket

should be:

- replaced as soon as a replacement part is available, or

- Service Bulletin A300-57-6011 (Modification 06661H1033) shouLd

be embodied.

(2) If both haLf brackets are cracked or the hinge bracket has fractured

or cracks are greater than 8mm in one half bracket:

- replace the damaged hinge bracket before the next flight or

- embody Service BuLLetin A300-57-6011 (Modification No. 06661H1033)

before the next flight.

D. TEST

None

E. CLOSE—UP

(1) Make sure that the work area is clean and clear of tools and other

items of equipment.

(2) Install the access panels 577CT, 577DT (LH) and 677CT, 677DT (RH),

(Refer to AMM: 06-41-57, P. Block 1).

(3) Retract the spoilers 1 and 2 (Refer to AMM: 27- 61 -54, P. Block 401).

(4) Retract the flaps (Refer to AMM: 27-50-00, P. Block 301).

(5) Remove the safety barriers and the warning notices.

(6) ResuLts of the inspections, including NIL findings, should be sent

immediately to AIRBUS.

NOTE : AIRBUS requests the return of the fractured hinge brackets

for investigation.

F. DOCUMENTATION

Write in the applicable aircraft records that you have done aLL the work

given in this Service BuLLetin.

DATE : Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

I

REVISION No. : 05 — Feb 21/11 PAGE : 8A

Printed in France
Tj A300-600

SERVICE BULLETIN

JOINT LINE USUAL STARTING POINT

OF CRACKS

CRACK IN VERTICAL

WEB RADIUS 

CRACK IN VERTICAL FLANGE

Îf^ \

UNDER BEARING ASSY. NUT

EXAMPLE 'A'

EXAMPLE 'B'

Outer Shroud Box Hinge Brackets — Inspection area

Figure 1 Sheet 1

DATE : Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

REVISION No. : 05 — Feb 21/11 PAGE : 8B

Printed in France
© A300-600

SERVICE BULLETIN

3. MATERIAL INFORMATION

A. LIST OF COMPONENTS

None

B. SPECIAL TOOLS

None

C. LIST OF MATERIAL - OPERATOR SUPPLIED

DESCRIPTION REFERENCE TO CML

CLeaning agent (Mat. No. 11-026)

D. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

QTY PER A/C

As required

DATE : Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

REVISION No. : 05 - Feb 21/11 PAGE : 9/10

Printed in France
S A300-600

SERVICE BULLETIN

ACCEPTANCE/REJECTION SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

TITLE : WINGS — INSPECTION OF THE OUTER SHROUD BOX HINGE BRACKET

MODIFICATION No. : NONE ATA SYSTEM : 57

IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW

PLease fill : ...REJECTED

...WILL BE EMBODIED

...EFFECTIVITY

This SB can only be incorporated in your "customized"

documentation within the agreed time schedule in so far as this

sheet returned to us on purchase date and signed by a duly

authorized and empowered officer or representative.

FROM : PLease return to

AIRLINE : AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

NAME : 31707 BLAGNAC CEDEX FRANCE

Attn : AI/SE—D32 Technical Data

DATE : and Documentation Services

FAX : (+33) 5 61 93 28 06

7 DATE : Dec 17/86 SERVICE BULLETIN No. : A300-57-6010

I REVISION No. . 05 — Feb 21/11 PAGE : 1 of 1

Printed in France