# 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 whichsupports 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