AIRBUS INDUSTRIE 

CUSTOMER SERVICES DIRECTORATE aA300-600 

1 Rond Point Maurice BELLONTE 

31707 BLAGNAC CEDEX FRANCE SERVICE BULLETIN 

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

Telex : AIRBU 530526 F SUMMARY 

This summary is for information only and is not approved for 

modification on the aircraft. 

TITLE : NACELLES/PYLONS - MODIFY RIB 5 IN THE PYLON BOX (RETROFIT 

SOLUTION). 

MODIFICATION No, 11109820987 ATA SYSTEM : 54 

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES 

Two operators of A300 A/C fitted with GE engine pylons have reported 

cracks on the Lower side of rib 5 in the pylon box. The concerned area 

is similar on A300/600 A/C fitted with GE engine pylons. The cracks were 

encountered on aircraft which have Logged between 16,000 and 

27,000 flight hours approximately. 

Investigations disclosed that these cracks are due to the stresses 

resulting from the pressure applied by the thrust reverser cowl bumpers. 

This Service Bulletin recommends the replacement of the stiffeners made 

out of bent extrusion by new thicker machined stiffeners. 

Accomplishment of this Service Bulletin is recommended on GE CF6-8OC 

pylons at 15,000 flight hours, or at the next C-check for aircraft 

having reached 15,000 flight hours. 

Accomplishment of this Service Bulletin cancels requirements of 

Inspection Service Bulletin No. A300-54-6034. 

EFFECTIVITY 

This Service Bulletin is applicable to the following customer(s) : AAL, 

CCA, CNW, DLH, FDX, IRA, KAC, MON, OAL, THA, UAE, XF and X0. 

SERVICE BULLETIN TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY 

None. 

5 DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 1 of 4 

Printed in France 
REFERENCES/REPERCUSSIONS 

TFU 

OEB 

AOT 

SIL 

LIFE LIMIT 

LINE MAINTENANCE AFFECTED 

OTHER 

NATURE OF THE WORK 

AIRCRAFT : YES 

EQUIPMENT : NO 

HARD : NO 

SOFT : NO 

OBRM : NO 

COMPLIANCE 

Recommended. 

MANPOWER 

Per pylon 

TOTAL MANHOURS 

SERVICE BULLETIN 

SUMMARY 

: 54-51-16-001 

: None 

: None 

: None 

: None 

: NO 

: None 

ELAPSED TIME (HOURS) 

32.0 

26.0 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 2 

Printed in France 
t$ A300-600 

SERVICE BULLETIN 

SUMMARY 

MATERIAL INFORMATION 

AIRCRAFT DATA 

Qty per engine pylon : 

3 fittings. 

EQUIPMENT DATA 

None. 

APPENDICES 

None. 

DATE : Nay 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 3 

Printed in France 
SERVICE BULLETIN 

SUMMARY 

GE PYLON 

DATE : May 30% 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 4 

Printed in France 
AIRBUS INDUSTRIE 

CUSTOMER SERVICES DIRECTORATE G &30@600 

1 Rond Point Maurice BELLONTE 

31707 BLAGNAC CEDEX FRANCE SERVICE BULLETIN 

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

Telex : AIRBU 530526 F 

TITLE : NACELLES/PYLONS - MODIFY RIB 5 IN THE PYLON BOX (RETROFIT 

SOLUTION). 

MODIFICATION No. 11109S20987 ATA SYSTEM : 54 

1. PLANNING INFORMATION 

A. EFFECTIVITY 

(1) Aircraft models : B4-601, B4-603, B4-605R, F4-605R. 

(2) Aircraft 

Customer and 

Fleet No. 

AAL050-084 

CCA601-607 

651-653 

CNWOOI-003 

DLH601-611 

FDX650-661 

663-665 

667-669 

IRA601,602 

KAC601-605 

MONOOI-004 

OAL001,002 

5 DATE : May 30/96 

REVISION No. : 

MSN 

423,455',460,420,461,462 

463,465,466,469,470,471 

474,506,507,508,509,510 

511,512,513,514,515,516 

517,606,610,612,615,619 

626,639,643,645,675 

521,525,532,707,732,746 

754 

709,713,715 

725,741,763 

380,391,401,405,408,411 

414,546,553,618,623 

726,728,735,736,738,742 

745,748,752,757,759,760 

766,768,769 

771,772,774 

723,727 

673,694,699,719,721 

540,556,604,605 

632,696 

Kit No. Qty 

546031 of Kits 

A01 70 

A01 14 

A01 06 

A01 06 

A01 22 

A01 24 

A01 06 

A01 06 

A01 04 

A01 IO 

A01 08 

A01 04 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 1 of 23 

Printed inFrance 
9A300-600 

c 

SERVICE BULLETIN 

Customer and MSN Kit No. Qty 

Fleet No. 546031 of Kits 

THA051-058 368,371,377,384,395,398 A01 16 

464,518 

IJAEIOI-105 505,558,563,608,701 A01 IO 

151 747 A01 02 

XF 501 744 A01 02 

503,504 749,764 A01 04 

x0 001,002 584,603 A01 04 

This modification (Retrofit SoLution) is applicable by Service 

Bulletin only. 

The modification No. 11110820983 (Production Solution) is embodied 

before delivery on A/C MSN 761, 767, 773, 775 and subsequent. 

NOTE 1 : This Service Bulletin is applicable on aircraft equipped 

with GEE and GEG engines. 

NOTE 2 : Modification of one aircraft requires 2 Kits 546031AOl. 

(3) Spares 

None. 

B. REASON 

(I) History 

Two operators of A300 A/C fitted with GE engine pylons have 

reported cracks on the lower side of rib 5 in the pylon box. The 

concerned area is similar on A300/600 A/C fitted with GE engine 

pylons. The cracks were encountered on aircraft which have logged 

between 16,000 and 27,000 flight hours approximately. 

Investigations disclosed that these cracks are due to the stresses 

resulting from the pressure applied by the thrust reverser cowl 

bumpers. 

(2) Objective/Action 

This Service Bulletin recommends the replacement of the stiffeners 

made out of bent extrusion by new thicker machined stiffeners. 

DATE : May 30/96 SERVICE BULLETIN No. : A300-54-6031 

REVISION No. : PAGE : 2 
GA3000600 

w 

SERVICE BULLETIN 

(3) Advantages 

The replacement of the stiffeners cancels requirements of 

Inspection Service Bulletin No. A300-54-6034. 

(4) Operational/Maintenance Consequences 

None. 

(5) Accomplishment Timescale 

Accomplishment of this Service Bulletin is recommended on 

GE CF6-80C pylons at 15,000 flight hours. 

C, DESCRIPTION 

To accomplish this Service Bulletin, it is necessary to : 

On the two pylons, in zones 415-416 (left pylon) and 425-426 

(right pylon) 

(1) Gain access to the working area. 

(21 Remove the ventilation duct between rib 2 and rib 7. 

(3) Lift the external mating strips between rib 3 and rib 5. 

(4) Remove the fittings and the shims at rib 5. 

(5) Install.the fitting and the shim at rib 5, left side. 

(6) Install the fitting and the shim at rib 5, right side. 

(7) Install the external mating strips between rib 3 and rib 5. 

(8) Install the ventilation duct between rib 2 and rib 7. 

DATE : May 30196 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 3 

Printed in France 
GA3C?U-600 

SERVICE BULLETIN 

D. APPROVAL 

The design data contained in this Service Bulletin has been approved 

under the authority of DGAC Design Organisation Approval No. C 01. 

The changes specified in this Service Bulletin have been approved by the 

DGAC when they are major , or under the authority of DGAC Design 

Organisation Approval No. C 01, when they are minor. 

E. MANPOWER 

This Service Bulletin is written for an aircraft in a maintenance 

condition. The manhours/elapsed time estimates do not include the time 

to prepare for the modification, non-productive elapsed time or 

administration. 

Kit No. 546031AOl is valid for one pylon. 

Gain access 

Remove/install the thrust reverser cowls 

Remove/install the ventilation duct 

Lift/install the mating strips 

Remove the fittings and the shims 

Install the fitting and the shims 

Tests 

Close-up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

DATE : May 30/96 

REVISION No. : 

5.0 

6.0 

2.5 

4.0 

3.5 

6.0 

1.0 

4.0 

32-O 

26.0 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 4 

Printed in France 
$411300-600 

SERVICE BULLETIN 

F. 

G. 

H. 

I. 

MATERIAL - COST AND AVAILABILITY 

(1) Material 

Customers with aircraft shown in paragraph l.A.iZ) should send a 

purchase order to Airbus Industrie. Quote the number of this 

Service Bulletin. The address is : 

AIRBUS INDUSTRIE 

MATERIEL SUPPORT CENTER 

P-0. BOX 63 02 62 

22312 HAMBURG 

GERMANY 

(2) Cost and availability 

Kit No. cost Availability : Calendar 

(US Dollars) days from receipt of order 

546031AOl 2450 150 

NOTE : The sales terms (costs and availability) are estimated in 

relation to economic conditions at the issue date of the 

Service Bulletin. 

TOOLING - PRICE AND AVAILABILITY 

Accomplishment of this Service Bulletin entails use of tools described 

in AMM 71-13-03, P. Block 401. 

WEIGHT AND BALANCE 

Manufacturers Empty Weight : + 0.832 kg (+ 1.834 Lb) 

Effect on balance : + 22.107 kgm (+ 159.899 Lb.ft) 

REFERENCES 

Aircraft Maintenance Manual (AMM) : 06-41-54, 20-21-12, 24-00-00, 

24-41-00, 36-11-00, 36-11-15, 

71-13-03 

Structural Repair Manual (SRM) : 51-40-21, 51-40-44, 51-40-47 

Consumable Material List (CML) 

Service Bulletin : A300-54-6034 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 5 

Printed in France 
SERVICE BULLETIN 

J. PUBLICATIONS AFFECTED 

Structural Repair Manual (SRM> : 54-51-16 

DATE : May 30/96 

REVISION No, : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 6 

Printed in France 
9A300-600 

SERVICE BULLETIN 

2. ACCOMPLISHMENT INSTRUCTIONS 

A. GENERAL 

(I) Preparation 

(a) De-energize the aircraft electrical circuits 

(Refer to AMM 24-41-00, P. Block 301). 

(b) Electrically ground the aircraft (Refer to AMM 24-00-00, 

P. Block 301). 

(c) Put the access platforms in position to get access to the 

engine pylons. 

Cd) Remove the access doors 413BL, 415AL, 416AR (Left pylon) and 

access doors 423BL, 425AL, 426AR (right pylon) (Refer 

to AMM 06-41-54). 

(e> Remove the thrust reverser cowls (Refer to AMM 71-13-03, 

P. Block 401). 

(f) Remove the bleed air precooler (Refer to AMM 36-11-15, 

P. Block 401). 

(g) Remove the bleed air precooler cold air inlet duct 

(Refer to AMM 36-11-00, P. Block 401). 

(2) Standard Practices 

(a) To clean the surfaces to be sealed with Methyl-Ethyl-Ketone, 

Mat. No. II-003 (Refer to CML). 

(b) To torque standard threaded fasteners (Refer to AMM 20-21-12). 

(c) To remove and install the fasteners (Refer to SRM 51-40-21). 

Cd) To drill and deburr holes (Refer to SRM 51-40-44). 

(e) To countersink the holes (Refer to SRM 51-40-47). 

(f) To shorten the rivets as required. 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 7 

Printed in France 
SERVICE BULLETIN 

B. MODIFICATION 

On-the two pylons, in zones 415-416 Cleft pylon) and 425-426 (right 

Won), reinforce the fittings at rib 5. 

NOTE : The description is given for the left engine pylon. The procedure 

is the same for right engine pylon. 

(I) Remove the ventilation duct between rib 2 and rib 7. 

Refer to Figure 1 

(a) Remove : 

2 screws Item (20) (retain) 

2 washers Item (IO) (discard) 

2 clamps Item (21) (retain> 

1 duct Item (22) (retain) 

(2) Lift the external mating strips between rib 3 and rib 5. 

Refer to Figure 2 

(a) From the outside of the pylon, lift : 

1 + I mating strip Item (16) 

To do this, remove : 

2 + 2 rivets 

18 + 18 rivets 

Item (14) (discard) 

Item (15) (discard) 

NOTE 1 : It is necessary to lift the mating strips to make it 

possible to remove the two upper fasteners of fittings 

Items 2 and 3 and to countersink these holes. 

Remove more rivets, if necessary to prevent damage of 

the part. 

NOTE 2 : Install wedges to keep the mating strips lifted. 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

1 PAGE : 8 

Printed in France 
SERVICE BULLETIN 

(3) Remove the fittings and the shims at rib 5. 

Refer to Figure 3 

(a) From the outside of the pylon, remove : 

1 + 1 shim 

2 + 2 screws 

1 + 1 screw 

1 screw, L side 

1 screw; R side 

2 + 2 washers 

1 + 1 washer. 

1 washer, L side 

1 washer, R side 

2 + 2 nuts 

1 + 1 nut 

1 nut, L side 

1 nut, R side 

(b) From the inside of the pylon, remove : 

1 fitting 

1 fitting 

1 fitting 

15 rivets 

22 rivets 

17 screws 

17 washers 

17 nuts 

1 screw 

1 washer 

1 nut 

Item (23) (retain) 

Item (24) (retain) 

Item (25) (retain) 

Item (26) (retain) 

Item (7) (discard) 

Item (27) (retain) 

Item (281 (retain) 

Item (28) (retain) 

Item (11) (discard) 

Item (8) (discard) 

Item (13) (discard) 

Item (13) (discard) 

Item (9) (discard) 

Item (I) (discard) 

Item (2) (discard) 

Item (3) (discard) 

Item (121 (discard) 

Item (5) (discard) 

Item (61 (discard) 

Item (29) (discard> 

Item (8) (discard> 

Item (7) (discard) 

Item (11) (discard) 

Item (9) (discard) 

NOTE : Be careful when you remove the rivets Item (121, not to 

damage the rivet holes as rivets of the same dimension 

will be installed. 

(4) Install the fitting and the shim on the left side of the pylon at 

rib 5. 

Refer to Figure 4 

(a) From the inside of the pylon at rib 5, on the lateral panel and 

in front of the stiffener, put in position and temporarily 

attach : 

1 fitting A5461277820000 Item 3 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 9 

Printed in France 
~6300-600 

SERVICE BULLETIN 

(b) Drill the fitting Item 3 to match the holes in the 

pane 1. 

lateral 

Use the table given in Figure 4 and countersink the 1 holes as 

written in Para. 2.A.C2)(e). 

(cl Clean the drilled area. 

(d> Attach the fitting Item 3 with : 

8 screws NAS1153E3 Item 16 

3 screws NAS1153E4 Item 5 

11 nuts NASlf26C3E Item 8 

(e) Drill the fitting Item 3 to match the holes in the stiffener. 

Use the table given in Figure 4. 

(f) Produce a 0.3 mm CO.0118 in.) to 0.5 mm (0.0197 in.) chamfer at 

45” on the holes. 

(g) Clean the drilled area. 

(h) Attach the fitting Item 3 with : 

17 screws NAS6703U3X Item 6 

17 nuts NAS1726C3E Item 8 

(i> From the outside of the pylon at.rib 5, on the lateral panel, 

put in position and attach : 

1 shim 

2 screws 

1 screw 

1 screw 

2 washers 

2 washers 

2 nuts 

2 nuts 

NASl726C3E 

ASNA2021C4E 

Item (23) 

Item (24) 

Item (25) 

Item (26) 

Item (27) 

Item (28) 

Item 8 

Item 13 

NOTE : Items (231, (241, (251, (261, (271 and (28) were 

retained at removal. 

(5) Install the fittings and the shim on the right side of the pylon at 

rib 5. 

Refer to Figure 5 

(a) From the inside of the pylon at rib 5, on the lateral panel, in 

front of the upper stiffener, put in position and temporarily 

attach : 

1 fitting A5461277620000 Item 2 

DATE : Nay 30/96 SERVICE BULLETIN No. : A300-54-6031 

REVISION Noi : PAGE : 10 < 

Printed in France 
SERVICE BULLETIN 

(b> Drill the fitting Item 2 to match the holes in the 

panel. 

Latera 

Use the table given in Figure 5 and countersink the 

written in Para. 2.A.l2>(e>. 

holes as 

(c) Clean the drilled area. 

Cd) Attach the fitting Item 2 with : 

11 screws NAS1153E4 Item 5 

11 nuts NAS1726C3E Item 8 

(e) Drill the fitting Item 2 to match the holes in the upper 

stiffener. 

Use the table given in Figure 5. 

(f) Clean the drilled area. 

(g) Attach the fitting Item 2 with : 

5 rivets NSA5415-40-11 Item 12 

(h) From the inside, on the lateral panel, behind the lower 

stiffener and the fitting Item 2, put in position and 

temporarily attach : - 

1 fitting A5461277220000 Item 1 

(i) Drill the fitting Item 1 to match the holes in the 

panel and in the lower stiffener. 

Use the table given in Figure 5. 

Cj) Clean the drilled area. 

(k) Attach the fitting Item 1 with : 

5 screws NAS6703U4 Item 4 

1 screw NAS6704U15X Item 7 

5 washers NSA5379-3C Item 10 

1 washer ASNA2394EW4 Item 11 

5 nuts NAS1726C3E Item 8 

1 nut NAS1727C4E Item 9 

Latera 

1 

1 

(1) Drill the fitting Item 1 to match the hole in the fitting 

Item 2 and drill the fitting Item 2 to match the holes in the 

fitting Item 1. 

Use the table given in Figure 5. 

(rn) Clean the drilled area. 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 11 

Printed in France 
63 A3000600 

SERVICE BULLETIN 

(n> Attach the fittings Items 1 and 2 with : 

5 rivets NSA5415-40-11 Item 12 

(01 From the outside of the pylon at rib 5, on the lateral panel, 

put in position and attach : 

1 shim 

2 screws 

1 screw 

1 screw 

2 washers 

1 washer 

1 washer 

2 nuts 

1 nut 

1 nut 

NAS6707UlSX 

ASNA2394EW4 

NASl726C3E 

ASNA2021C4E 

NAS1727C4E 

Item (23) 

Item (24) 

Item (25) 

Item 7 

Item (27) 

Item (28) 

Item 11 

Item 8 

Item 13 

Item 9 

NOTE : Items (231, (241, (251, (27) and (28) were retained at 

removal. 

(6) Install the external mating strips between rib 3 and rib 5. 

Refer to Figure 2 

(a> From the outside of the pylon, drill the mating strips 

Item (16) and the lateral panels. 

Use the table given in Figure 2. 

(b1 Countersink the holes as written in Para. 2.A.(Z)(e). 

(c) Attach the mating strips Item (16) with : 

2 + 2 rivets NSA5414-48-11 Item 14 

18 + 18 rivets NSA5414-32-07 Item 15 

(7) Install the ventilation duct between rib 2 and rib 7. 

Refer to Figure 1 

(a> Install : 

2 screws Item (20) 

2 washers NSA5379-SC Item 10 

2 clamps Item (21) 

1 duct Item (22) 

NOTE : Items (201, (21) and (22) were retained at removal. 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 12 

Printed in France 
$2 A300-600 * 

SERVICE BULLETIN 

C. TESTS 

(1) Preparation for the tests 

(a> Install the bleed air precooler cold air inlet duct 

(Refer to AMM 36-11-00, P. Block 401). 

lb) Install the bleed air precooler (Refer to AMM 36-11-15, 

P. Block 401). 

(c) Install the thrust reverser cowls (Refer to AMM 71-13-03, 

P. Block 301). 

(d) Disconnect the aircraft electrical ground connection 

(Refer to AMM 24-00-00, P. Block 301) and energize the aircraft 

electrical circuits (Refer to AMM 24-41-00, P. Block 301). 

(2) Tests 

(a> Do the Leakage check of the pneumatic duct and precooler 

connections (Refer to AMM 36-11-00, P. Block 601). 

(b) Do the adjustment/test of the thrust reverser cowl (Refer to 

AMM 71-13-03, P. Block 501). 

D. CLOSE-UP 

(I) Make sure that the work areas are clean and clear of tools and 

other items of equipment. 

(2) Install the access doors 413BL, 415AL, 416AR (left pylon) and the 

access doors 423BL, 425AL, 426AR (right pylon) (Refer to 

AMM 06-41-54). 

(3) Remove the access platform(s). 

E. DOCUMENTATION 

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

given in this Service Bulletin. 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 13 

Printed in France 
SERVICE BULLETIN 

3 

m LEFT SIDE SHOWN 

RIGHT SIDE IDENTICAL 

Removal/Installation of the Ventilation Duct between Rib 2 and Rib 7 

Figure 1 

DATE : Nay 30196 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 14 

Printed in France 




$2 A300-600 * 

SERVICE BULLETIN 

3. MATERIAL INFORMATION 

A. LIST OF COMPONENTS 

ITEM NEW PART No. QTY KEYWORD ITEM OLD PART No. INT INST 

DISP 

Kit No. 546031AOl 

: 

3 

4 

5 

6 

7 

8 

9 

10 

II 

12 

13 

14 

15 

16 

A5461277220000 1 Fitting (I) A5461100521000 * 

A5461277620000 1 Fitting (2) A5461176950200 * 

A5461277820000 1 Fitting (3) A5461176950000 * 

NAS6703U4 5 Screw 

NAS1153E4 14 Screw 

NAS6703U3X 17 Screw 

NAS6704UlSX 2 Screw 

NAS1726C3E 48 Nut 

NAS1727C4E 2 Nut 

NSA5379-3C 7 Washer 

ASNA2394EW4 2 Washer 

NSA5415-40-11 10 Rivet 

ASNA2021C4E 3 Nut 

NSA5414-48-11 4 Rivet 

NSA5414-32-07 36 Rivet 

NAS1153E3 8 Screw 

NOTE * : Discard 

B. SPECIAL TOOLS 

None. 

C. LIST OF MATERIALS - OPERATOR'SUPPLIED 

DESCRIPTION REFERENCE TO CML QTY PER A/C 

Methyl-Ethyl-Ketone Mat. No. II-003 As required 

D. PARTS TO BE RE-IDENTIFIED BY OPERATOR 

None. 

. 

DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 23 

Printed in France 
AIRBUS INDUSTRIE 

CUSTOMER SERVICES DIRECTORATE ~A30&6~~ 

1 Rond Point Maurice BELLONTE 

31707 BLAGNAC CEDEX FRANCE SERVICE BULLETIN 

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

Telex : AIRBU 530526 F 

TITLE : NACELLES/PYLONS - MODIFY RIB 5 IN THE PYLON BOX (RETROFIT 

SOLUTION). 

MODIFICATION No. 11109820987 ATA SYSTEM : 54 

IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW 

Please fill : I.. REJECTED 

.I. WILL BE EMBODIED 

1.1 EFFECTIVITY 

This SB can only be incorporated in your "customized" documentation within 

the agreed time schedule if this sheet is returned to us on purchase date 

and signed by a duly authorized and empowered officer or representative. 

FROM : Please return to : 

AIRLINE : 

. . . . . . . . . . . . . . . . ..~. 

NAME : 

AIRBUS INDUSTRIE 

CUSTOMER SERVICES DIRECTORATE 

1 Rond Point Maurice BELLONTE 

31707 BLAGNAC CEDEX FRANCE 

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

Telex : AIRBU 530526 F ..1..1.........11... 

DATE: 

. . . . . . . . . . . . . ...19.. 

5 DATE : May 30/96 

REVISION No. : 

SERVICE BULLETIN No. : A300-54-6031 

PAGE : 1 of 1 

Printed in France