LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin are as follows:

Page Revision Number Revision Date

Bulletin

1 Sep.9/14

2 Sep.9/14

3 Sep.9/14

4 Sep.9/14

5 Sep.9/14

6 Sep.9/14

7 Sep.9/14

8 Sep.9/14

9 Sep.9/14

10 Sep.9/14

Appendix 1

1 Sep.9/14

Printed in Great Britain

RB.211−73−AH837

Transmittal - Page 2
1. Planning Information

A. Effectivity

Airbus A330

RB211 TRENT 768-60/15 Engines, with Fuel Tube (FW53576) fitted

RB211 TRENT 768-60/16 Engines, with Fuel Tube (FW53576) fitted

RB211 TRENT 772-60/15 Engines, with Fuel Tube (FW53576) fitted

RB211 TRENT 772-60/16 Engines, with Fuel Tube (FW53576) fitted

RB211 TRENT 772B-60/15 Engines, with Fuel Tube (FW53576) fitted

RB211 TRENT 772B-60/16 Engines, with Fuel Tube (FW53576) fitted

RB211 TRENT 772C-60/16 Engines, with Fuel Tube (FW53576) fitted

NOTE: Fuel Tube (FW53576) is introduced by SB 73-F343.

B. Reason

Low Pressure (LP) fuel leaks from the LP fuel tube run between the Fuel/Oil

Heat Exchanger (FOHE) to the LP/HP fuel pump have occurred in-service in the

Trent 700 fleet. Movement of the FOHE mounts due to wear in conjunction with

engine vibration allows the fuel tubes to move excessively within the clipping

points. This has resulted in excessive wear of the rubber section of the

P-clips, and the subsequent fretting between the exposed metal band and the

fuel tubes. The fretting reduces the fuel tube outer wall thickness, which may

lead to fracture of the fuel tube and the consequent fuel leak. This is

inspected for by Non-Modification Service Bulletin (NMSB) 73-AH522.

However a small number of P-clip tang fractures at clip point 4881 have

resulted in frettage and leaks from the LP Fuel tube between the FOHE to LP/HP

fuel pump prior to the next required inspection in accordance with 73-AH522.

Three of the four of these failures have been confirmed to have broken tangs on

the clips and the other was reported in this condition (but no hardware or

photographs are available to confirm this).

This NMSB is to specifically visually inspect the upper P-clip attaching

feature and the bracket holding this P-clip to the oil tank.

LP FUEL TUBE UPPER CLIP (CP4881) AND BRACKET INSPECTION - NON-MODIFICATION SERVICE

BULLETIN - NON - MOD.73-AH837

Printed in Great Britain

RB.211−73−AH837

Page 1 of 10

Sep. 9/14

Sep. 9/14
C. Description

This NMSB is issued to recommend on-wing visual inspection of the upper P-clip

(CP4881) on the LP fuel tube (FW53576) and the attaching bracket (FW26692).

Advise your local Rolls-Royce representative of NMSB accomplishment and any

significant inspection results in the table provided (Appendix 1) or similar,

and provide to Rolls-Royce.

D. Compliance

ALERT

This Non-Modification Service Bulletin is anticipated to be subject of an

EASA/FAA Airworthiness Directive.

(1) On-wing

Complete the actions detailed in 3.A. Accomplishment Instructions at the

following intervals:

(a) Inspect within the next 800 operating hours from initial issue of this

NMSB.

(b) Following the initial inspection, repeat the inspection at intervals

not exceeding 800 hours.

(2) In-shop

Not applicable, as NMSB 73-AH522 includes replacement of CP 4881 at every

shop visit. Embodiment of 73-AH522 can be used as compliance for NMSB

73-AH837.

E. Approval

The technical content of this Non-Modification Service Bulletin was approved

under the authority of Design Organisation Approval EASA.21J.035 on Aug.29/14.

F. Manpower

(1) On-wing

(a) Time to gain access

0.5 hours (2 persons)

(b) Time to inspect

0.25 hours (1 person)

Printed in Great Britain

RB.211−73−AH837

Page 2

Sep. 9/14

Sep. 9/14
(c) Time to restore to serviceable condition

0.5 hours (2 persons)

(2) In-shop

Not applicable

NOTE: The parts affected by this Non-Modification Service Bulletin are

accessible at in-shop

G. Material Price and Availability

Not affected.

H. Tooling Price and Availability

Special tools are not required.

I. References

(1) Rolls-Royce RB211 Service Bulletin:

73-F343

Fuel - Fuel Tubes - LP Compressor Case - Introduction of revised LP Fuel

Tube Assemblies, Associated Bracketry and Clipstacks

(2) Rolls-Royce RB211 Non-Modification Service Bulletin:

73-AH522

LP Fuel Tubes, Clips, and FOHE Mounting Hardware - Inspection for Frettage

- Non-Modification Service Bulletin

(3) Airbus A330 Aircraft Maintenance Manuals

(a) 71-13-00-010-805-A, Open the Fan Cowl Doors

(b) 71-13-00-410-805-A, Close the Fan Cowl Doors

(4) Aircraft Illustrated Parts Catalogue:

(a) 73-12-41, Pump - Fuel

(b) 79-21-41, Pump - Lubrication and Scavenge Oil

Printed in Great Britain

RB.211−73−AH837

Page 3

Sep. 9/14

Sep. 9/14
2. Material Information

A. The following parts may be required if rejected during inspection:

73-11-47

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

05100 FW53576 1 Tube, Assy Fuel-FCOC to

Line Disconnect

- FW26590/

FK30382

05108 AS43013-

134

1 Ring - -

05116 AS43013-

127

1 Ring, 36.17 mm I/D x 2.62

mm

- -

05125 AS48409 3 Bolt, 0.190 in. dia x

0.562 in.

- -

05126 K8831 3 Washer, 0.190 in. Dia x

0.51 mm thk

- -

05128 AS62424 3 Clip, 38.10 mm (1.500 in.) - AS62426

05131 AS12943 3 Washer, 0.190 in. Dia - -

05132 AS20624 3 Nut, 0.190 in.dia - -

79-11-11

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

01035 FW26692 1 Bracket, clipping oil

tank top - flange

- -

Printed in Great Britain

RB.211−73−AH837

Page 4

Sep. 9/14

Sep. 9/14
3. Accomplishment Instructions

A. On-wing

Inspect the P-clip CP4881 and the bracket supporting the P-clip CP4881.

WARNING: YOU MUST BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE

ENGINE IS SHUTDOWN. THE ENGINE PARTS CAN STAY HOT FOR ALMOST 1 HOUR.

WARNING: YOU MUST NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN

CAUSE AN INJURY. IF YOU GET AN INJURY PUT IT IN COLD WATER FOR 10

MINUTES AND GET MEDICAL AID.

CAUTION: IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE ENGINE IN FLIGHT SHUTDOWN,

POWER LOSS OR OTHER ANOMALIES DUE TO MAINTENANCE ERROR, ROLLS-ROYCE

RECOMMENDS THAT OPERATORS AVOID PERFORMING MAINTENANCE ON MULTIPLE

ENGINES INSTALLED ON THE SAME AIRCRAFT AT THE SAME TIME. IF IT IS NOT

POSSIBLE TO AVOID MAINTENANCE ON MORE THAN ONE ENGINE AT THE SAME TIME,

ROLLS-ROYCE RECOMMENDS THAT ADDITIONAL CONTROLS ARE APPLIED IN ORDER TO

ENSURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED.

MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE

THIS RECOMMENDATION.

(1) Get access:

(a) Open the fan cowl doors in accordance with Aircraft Maintenance Manual

(AMM) Task 71-13-00-010-805-A.

(i) For 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG 1): 415AL 416AL

(ii) For 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG 2): 425AL 426AR

(b) Put suitable access platform into a safe position.

(2) Visually inspect without removing any parts, the upper most clipstack

(CP4881) on the FOHE to HP fuel pump fuel pipe upper section (FW53576) and

the bracket that this P-clip is attached to for damage. Refer to Fig.1,

Fig.2 and Fig.3.

NOTE: If one or more P-clips are removed then refit using only new

P-clips, do not refit previously installed P-clips.

(a) Visually check this clip for obvious evidence that the visible metal

bands through which the bolt (AS48409) is inserted are cracked or

fractured. Refer to Fig.3a.

(i) If the clip is not cracked - Do not disturb the assembly, go to

step 3.A.(2)(b).

Printed in Great Britain

RB.211−73−AH837

Page 5

Sep. 9/14

Sep. 9/14
(ii) If the clip is cracked/fractured remove the clip and inspect

the fuel tube in accordance with step 3.A.(2)(c).

(1) If the fuel tube is found to be unserviceable, remove and

replace fuel tube(s) in accordance with Aircraft Maintenance

Manual 70-12-01.

(b) Visually check the bracket (FW26692) for obvious evidence of wear or

damage, specifically check that the P-clip (CP4881) bolt area is in

good condition. Refer to Fig.3b.

(i) If the bracket is not cracked - Do not disturb the assembly, go

to step 3.A.(3).

(ii) If the bracket is cracked/fractured remove and replace the

bracket and inspect the fuel tube in accordance with step

3.A.(2)(c). This may be carried out within the next 100

operating hours if the clip is not damaged.

(1) If the fuel tube is found to be unserviceable, remove and

replace fuel tube(s) in accordance with Aircraft Maintenance

Manual 70-12-01.

(c) Fuel tube acceptance and rejection criteria:

Contact frettage under clip location to a depth of

greater than 0.2 mm (0.008 in.)

Reject

NOTE: 1. Use AMM Limits for any other damage on the tube.

2. Take particular care to inspect the entire exposed surface

of the tube, a mirror may be used in areas where direct

line of sight access is difficult.

(d) If a clip or fuel tube is rejected, remove and replace it in

accordance with Aircraft Maintenance Manual 70-12-01. If one or more

P-clips are removed then refit using only new P-clips, do not refit

previously installed P-clips.

(e) Refer to Service Bulletin 73-F343 for specific installation

instructions, the Standard Practices Manual (SPM) 70-51-00 for bolt

torque details and Fig.3 for tube and clipping point details.

NOTE: During removal of the clip look for any significant relaxation

of strain that suggests poor alignment of the tube and

stressing of certain clipping positions. If necessary, loosen

adjacent clips and carefully manipulate the tube alignment to

minimise any strain in the system. Make a note on the proforma

(Appendix 1) if alignment issues are seen.

Printed in Great Britain

RB.211−73−AH837

Page 6

Sep. 9/14

Sep. 9/14
(3) Close the fan cowl doors; refer to Aircraft Maintenance Manual (AMM) Task

71-13-00-410-805-A.

(a) For 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG1): 415AL 416AL

(b) For 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG2): 425AL 426AR

(4) Remove the access platform.

(5) If any fuel tube was replaced then do a fuel and oil leak test in

accordance with Aircraft Maintenance Manual, 71-00-00, Test No.2, The Fuel

and Oil Leak Test.

B. In Shop

Not applicable

C. A record of accomplishment is required, Refer to Appendix 1.

Printed in Great Britain

RB.211−73−AH837

Page 7

Sep. 9/14

Sep. 9/14
General Fuel Tube Arrangement

Fig.1

Printed in Great Britain

RB.211−73−AH837

Page 8

Sep. 9/14

Sep. 9/14
Arrangement of Fuel Tubes FW53577 and FW53576

Fig.2

Printed in Great Britain

RB.211−73−AH837

Page 9

Sep. 9/14

Sep. 9/14
Arrangement and Example of Fracture of Clip Position CP4881

Fig.3

Printed in Great Britain

RB.211−73−AH837

Page 10

Sep. 9/14

Sep. 9/14
This form (or similar) to be completed for every engine/component inspected. Results

to be sent to Rolls-Royce via your Service Representative

Feedback Sheet NMSB 73-AH837

Date: Operator:

Engine Serial No. Aircraft:

Hours Cycles

Engine Life:

Life Since Last Shop Visit:

Fuel Tubes Condition Observations (material transfer/fretted/dented/worn -

please specify depth)

FW53576

FW53577

Clips Condition

Observations (material transfer/dust/worn/cracked/metal

band exposed)

4881

2607

2427

Bracket Condition

Observations (material transfer/dust/worn/cracked)

FW26692

Notes:

NOTE: Only those components which are inspected need to be reported on this form.

APPENDIX 1

Printed in Great Britain

RB.211−73−AH837

Appendix 1 - Page 1 of 1

Sep. 9/14

Sep. 9/14