LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin following incorporation of Revision

2 are as follows:

Page Revision Number Revision Date

Bulletin

R 1 2 Jun.13/12

R 2 2 Jun.13/12

R 3 2 Jun.13/12

R 4 2 Jun.13/12

R 5 2 Jun.13/12

R 6 2 Jun.13/12

R 7 2 Jun.13/12

R 8 2 Jun.13/12

R 9 2 Jun.13/12

R 10 2 Jun.13/12

R 11 2 Jun.13/12

R 12 2 Jun.13/12

R 13 2 Jun.13/12

R 14 2 Jun.13/12

R 15 2 Jun.13/12

R 16 2 Jun.13/12

Appendix 1

R 1 2 Jun.13/12

Printed in Great Britain

RB.211−73−AG797

Transmittal - Page 2
1. Planning Information

A. Effectivity

Airbus A340 - 500/600

RB211 TRENT 553-61 Engines

RB211 TRENT 553A2-61 Engines

RB211 TRENT 556-61 Engines

RB211 TRENT 556A2-61 Engines

RB211 TRENT 556B-61 Engines

RB211 TRENT 556B2-61 Engines

RB211 TRENT 560-61 Engines

RB211 TRENT 560A2-61 Engines

This Non-Modification Service Bulletin (NMSB) does not apply to engines which

have been inspected per NMSB 73-G723.

B. Reason

Problem

Low-pressure fuel leaks from the LP fuel tubes which run between the

low-pressure and high-pressure fuel pumps have occurred in-service in the Trent

500 fleet. These have resulted from frettage between the securing clips and the

low-pressure fuel tube outer surface, which reduces the fuel tube wall

thickness, leading to fracture of the fuel tube wall and consequent fuel leak.

This may cause the leakage of significant amounts of fuel and can cause IFSD

and Diversion events. NMSB 73-G723 was issued to inspect the components, gather

data and provide mitigation on engines passing through shop visit.

This NMSB was designed to gather information and provide proactive mitigation

for the condition also for those engines installed on-wing which would not be

covered by NMSB 73-G723.

This NMSB does not apply to engines which have been inspected per NMSB 73-G723.

ENGINE - LP FUEL TUBES AND CLIPS - INSPECTION FOR FRETTAGE - NON-MODIFICATION SERVICE

BULLETIN - NON - MOD.73-AG797

Printed in Great Britain

RB.211−73−AG797

Page 1 of 16

Oct.26/11

R Jun.13/12
Revision 1 of this NMSB is issued add Fig.1 reference to Accomplishment

R Instructions (3.A.(4)), to add reference to SB 73-F738 and to incorporate

reference to clip position 100180 in Accomplishment Instructions (3.A.(4)(a)

and 3.A.(6)) and to correct frettage dimensions in Accomplishment Instructions

(3.A.(5)(c)).

C. Description

This NMSB is issued to recommend on-wing inspection of the low-pressure fuel

tubes and associated hardware.

Advise your Rolls-Royce representative of NMSB accomplishment and inspection

results, regardless of findings. Return Appendix 1 (or similar form) to your

Rolls-Royce service representative.

D. Compliance

ALERT

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

EASA Airworthiness Directive.

On wing:

If the engine has not been inspected to NMSB 73-G723 Initial issue or later

approved version, it is recommended that the actions detailed in section 3.A.

(Accomplishment Instructions, On-wing) be carried out at first opportunity

within 1600 engine flying hours from the effective date for the release of this

NMSB.

E. Approval

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

under the authority of Design Organisation Approval EASA.21J.035 on Oct.25/11

and re-approved on Jan.31/12.

F. Manpower

(1) Time to gain access

0.5 hours

(2) Time to inspect

2 hours

(3) Time to replace tubes (if needed; includes Test 2 Fuel and Oil Leak Test)

3 hours

Printed in Great Britain

RB.211−73−AG797

Page 2

Oct.26/11

R Jun.13/12
(4) Time to restore to serviceable condition

0.5 hours

G. Material Price and Availability

Not applicable

H. Tooling Price and Availability

Not applicable

I. References

(1) Rolls-Royce RB211 Service Bulletins:

SB 73-F737

Engine - Fuel and Control - Fuel Tubes - LP Compressor Case - Introduction

of a revised LP Fuel Tube Incorporating Rigid End Fittings

SB 73-F738

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

LP Fuel Tubes Incorporating Rigid End Fittings

SB 79-AG346

Oil - Fuel Oil Heat Exchanger - Introduction of a Fuel Oil Heat Exchanger

Featuring a revised Cooler Matrix

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

NMSB 73-G723

Engine - LP Fuel Tubes, Clips and FOHE Mounts - Inspection for Frettage -

Non-Modification Service Bulletin

(3) Aircraft Maintenance Manual:

(a) 24-41-00, Deactivation/Reactivation, AC External Power Control

(b) 71-13-00, Maintenance Practices, Opening/Closing Fan Cowl Doors

(c) 70-20-01, Maintenance Processes - Stripping and Cleaning, Maintenance

Practices, Non - Aqueous Liquid Degreasing

(d) 73-11-00, Inspection/Check, Inspection of the Fuel Distribution Tubes

(e) 73-11-00, Plumbing, Maintenance Practices, Draining of the LP Fuel

Supply from the Fuel Oil Heat Exchanger Drain Point

Printed in Great Britain

RB.211−73−AG797

Page 3

Oct.26/11

R Jun.13/12
(f) 73-11-00, Plumbing, Maintenance Practices, Draining of the LP Fuel

Supply from the Fuel Pump Drain Point

(g) 70-12-01, Removal/Installation, Removal of Rigid Tubes

(h) 70-12-01, Removal/Installation, Installation of Rigid Tubes

(i) 71-00-00, Adjustment/Test, Test No.2, The Fuel and Oil Leak Test

Printed in Great Britain

RB.211−73−AG797

Page 4

Oct.26/11

R Jun.13/12
2. Material Information

A. Consumable

OMat 2-101 Lint-free Cloth

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

73-11-47

FIG

ITEM

NO.

PART

NO.

QTY PART TITLE MAT

04100 FK30710 1 Tube, assy fuel - LP pump to line

disconnect,

Pre SB 73-F738

-

04100A FW57604 1 Tube, assy fuel - LP pump to line

disconnect,

SB 73-F738 PT01

-

04104 RR188C 3 Ring, V80756,

Pre SB 73-F738

-

04106 BLT5529 3 Bolt, 0.25 in. dia x 1.028,

x 1.028, Pre SB 73-F738

-

04106A AS48516 3 Bolt, 0.25 in. dia x

1.000, SB 73-F738 PT01

-

04107 AS43013-129 2 Ring,

Pre SB 73-F738

-

04108 AS43013-134 1 Ring -

04500 FW17689 1 Tube, assy fuel pump to FCOC,

Pre SB 73-F738

-

04500A FW57605 1 Tube, assy fuel pump to FCOC,

SB 73-F738 PT01

-

04502 AS20625 4 Nut, 0.25 in. dia -

04504 AS12944 4 Washer, 0.25 in. dia -

04506 AS48516 4 Bolt, 0.25 in. dia x 1 -

04508 AS43013-130 1 Ring -

Printed in Great Britain

RB.211−73−AG797

Page 5

Oct.26/11

R Jun.13/12
FIG

ITEM

NO.

PART

NO.

QTY PART TITLE MAT

04512 RR188C 3 Ring, V80756,

Pre SB 73-F738

-

04514 BLT5529 3 Bolt, 0.25 in. dia x

1.028, Pre SB 73-F738

-

04514A AS48516 3 Bolt, 0.25 in. dia x

1.000, Pre SB 73-F738 PT01

-

04515 AS43013-129 2 Ring,

Pre SB 73-F738

-

04516 AS43013-134 1 Ring -

04525 AS48408 1 Bolt, 0.190 in. dia x 0.50 -

04526 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

-

04528 AS62426 1 Clip, 41.27 mm - 1.625 in. -

04532 AS20624 1 Nut, 0.190 in. dia -

04533 AS48408 1 Bolt, 0.190 in. dia x 0.50 -

04534 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

-

04536 AS62426 1 Clip, 41.27 mm - 1.625 in. -

04540 AS20624 1 Nut, 0.190 in. dia -

04541 AS48408 1 Bolt, 0.190 in. dia x 0.50 in. -

04542 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

-

04544 AS62426 1 Clip, 41.27 mm - 1.625 in. -

04548 AS20624 1 Nut, 0.190 in. dia -

04549 AS48434 1 Bolt, 0.190 in. dia x

2.125 in.

-

04550 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

-

Printed in Great Britain

RB.211−73−AG797

Page 6

Oct.26/11

R Jun.13/12
FIG

ITEM

NO.

PART

NO.

QTY PART TITLE MAT

04552 AS62426 1 Clip, 41.27 mm - 1.625 in. -

04554 UP10482 1 Spacer, 25 mm -

04555 UP10480 1 Spacer, 15 mm -

04556 AS20624 1 Nut, 0.190 in. dia -

73-11-47

FIG

ITEM

NO.

PART

NO.

QTY PART TITLE MAT

05100 FK30713 1 Tube, assy fuel - LP

filter to line disconnect,

Pre SB 73-F737

-

05100A FW57578 1 Tube, assy fuel -

LP filter to HP pump,

SB 73-F737

-

05104 RR188C 3 Ring, V80756,

Pre SB 73-F737

-

05107 AS43013-129 2 Ring,

Pre SB 73-F737

-

05108 AS43013-134 1 Ring -

05112 RR188C 3 Ring, V80756,

Pre SB 73-F737

-

05114 BLT5529 3 Bolt, 0.25 in. dia

x 1.028, Pre SB 73-F737

-

05114A AS48516 3 Bolt, 0.25 in. dia

x 1.000, SB 73-F738 PT01

-

05115 AS43013-129 2 Ring,

Pre SB 73-F737

-

05116 AS43013-134 1 Ring -

05125 AS48408 1 Bolt, 0.190 in. dia x

0.500 in.

-

Printed in Great Britain

RB.211−73−AG797

Page 7

Oct.26/11

R Jun.13/12
FIG

ITEM

NO.

PART

NO.

QTY PART TITLE MAT

05126 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

-

05128 AS62426 1 Clip, 41.27 mm (1.625 in.) -

05132 AS20624 1 Nut, 0.190 in. dia -

05133 AS48409 1 Bolt, 0.190 in. dia x

0.500 in. pre SB 73-F737

-

05134 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

pre SB 73-F737

-

05136 AS62426 1 Clip, 41,27 mm (1.625 in.)

pre SB 73-F737

-

05149 AS48408 1 Bolt, 0.190 in. dia x

0.500 in.

-

05150 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

-

05152 AS62426 1 Clip, 41,27 mm (1.625 in.) -

05157 AS48412 1 Bolt, 0.190 in. dia x

0.750 in.

-

05158 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

-

05160 AS62426 1 Clip, 41,27 mm (1.625 in.) -

05162 UP10478 1 Spacer, 5mm -

05164 AS20624 1 Nut, 0.190 in. dia -

05165 AS48410 1 Bolt, 0.190 in. dia x

0.620 in. SB 73-F737 PT01

-

05166 K8831 1 Washer, 0.190 in. dia x 0.51 in.

thk

SB 73-F737 PT01

-

05167 AS12943 1 Washer, 0.190 in. dia

SB 73-F737 PT01

-

Printed in Great Britain

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Page 8

Oct.26/11

R Jun.13/12
FIG

ITEM

NO.

PART

NO.

QTY PART TITLE MAT

05168 AS62426 1 Clip, 41,27 mm (1.625 in.)

SB 73-F737 PT01

-

05172 AS20624 1 Nut, 0.190 in. dia

SB 73-F737 PT01

-

Printed in Great Britain

RB.211−73−AG797

Page 9

Oct.26/11

R Jun.13/12
3. Accomplishment Instructions

A. On-wing:

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

SHUTDOWN. THE ENGINE CAN STAY HOT FOR ALMOST ONE HOUR.

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

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

MINUTES. THEN GET MEDICAL AID.

WARNING: YOU MUST NOT LET ENGINE OIL STAY ON YOUR SKIN. FLUSH THE OIL FROM YOUR

SKIN WITH WATER. THE OIL IS POISONOUS AND CAN BE ABSORBED INTO YOUR

BODY.

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

POWER LOSS, OR OTHER ANOMALY 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.

CAUTION: YOU MUST NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR

OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT-FREE CLOTH. THE FUEL

OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

(1) Energize the aircraft electrical, refer to Aircraft Maintenance Manual

(AMM) 24-41-00, Maintenance Practices.

(2) Get access to the avionics compartment, then open, safety and tag this

(these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION

For 4040 EM1:

722VU FADEC B ENG 1 13KS1 K46

722VU FUEL LP MOT 2 ENG 1 2QG1 U44

742VU FUEL LP MOT 1 ENG 1 1QG1 K75

742VU FADEC A ENG 1 12KS1 N74

For 4040 EM2:

722VU FADEC B ENG 2 13KS2 D43

722VU FUEL LP MOT 2 ENG 2 2QG2 U45

742VU FUEL LP MOT 1 ENG 2 1QG2 K76

742VU FADEC A ENG 2 12KS2 Q73

For 4040 EM3:

722VU FADEC B ENG 3 13KS3 K47

722VU FUEL LP MOT 2 ENG 3 2QG3 Q43

742VU FUEL LP MOT 1 ENG 3 1QG3 K77

Printed in Great Britain

RB.211−73−AG797

Page 10

Oct.26/11

R Jun.13/12
742VU FADEC A ENG 3 12KS3 Q74

For 4040 EM4:

722VU FADEC B ENG 4 13KS4 D44

722VU FUEL LP MOT 2 ENG 4 2QG4 Q44

742VU FUEL LP MOT 1 ENG 4 1QG4 K78

742VU FADEC A ENG 4 12KS4 N75

(3) Get access: open the Fan Cowl Doors, refer to AMM 71-13-00, Maintenance

Practices

For 4040EM1: 415AL 416AR

For 4040EM2: 425AL 426AR

For 4040EM3: 435AL 436AR

For 4040EM4: 445AL 446AR

CAUTION: YOU MUST NOT PUT OIL THAT HAS COME FROM THE ENGINE BACK INTO THE

OIL SYSTEM. CONTAMINATION IN THE OIL CAN CAUSE DAMAGE TO SOME

PARTS OR FAILURE OF THE OIL.

CAUTION: YOU MUST NOT PUT FUEL THAT HAS COME FROM THE ENGINE BACK INTO

THE FUEL SYSTEM. CONTAMINATION IN THE FUEL CAN CAUSE DAMAGE TO

SOME PARTS.

(4) Remove and check the clips holding the LP fuel tube run from the LP fuel

pump to the FOHE (AIPC 73-11-47, 72-160/72-160A and 73-11-47,

72-150/72-150A) and the clips holding the LP fuel tube run from the LP

filter to the HP fuel pump (73-11-47, 73-140/73-140A). See Fig.1 and

Fig.2.

(a) Visually check each of the clips for obvious evidence of damage that

may have affected the fuel tubes (e.g. significant damage to rubber

and/or dust/debris at location of clip):

Pre SB 73-F737 and pre SB 73-F738: Engines Inspect the clipping points

100181, 102321, 100282, 100187, 102252, 100178, 100180, 102259,

102321, 100186 and 102260

Post SB 73-F737 and SB 73-F738: Engines Inspect the clipping points

100181, 102321, 100282, 102374, 102252, 100178, 100180, 102259,

102321, 100186 and 102260

Printed in Great Britain

RB.211−73−AG797

Page 11

Oct.26/11

R Jun.13/12
(b) Remove, inspect and replace (as necessary) each retaining clip one at

a time, start from either top or bottom of the tube run.

NOTE: This is to prevent alteration to the system alignment and

stressing of the tube and clips.

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

or strain that suggests poor alignment of the tubes and

stressing of certain clipping positions. If necessary loosen

adjacent clips and carefully manipulate the tube alignment to

minimize any strain in the system. Make a note if alignment

issues are seen.

(c) Visually inspect the clips:

Obvious excessive damage Take a photo and reject

Cracked Distressed Rubber Take a photo and reject

Worn/damaged internal diameter of

rubber

Take a photo and reject

Evidence of internal

corrosion/wear/material transfer

to the tube surface (powdery

deposits at ends of rubber

section)

Take a photo and reject

(5) Inspect the LP fuel tube run from the LP fuel pump to the FOHE and the LP

fuel tube run from the LP filter to the HP fuel pump (see Fig.2).

(a) Clean the fuel tubes in accordance with AMM Task 70-20-01-100-805.

(b) Dry the tubes with a clean Material No OMat 2-101 (lint-free cloth) .

(c) Visually check the fuel tubes surface near p-clips location for

evidence of damage/wear in accordance with AMM Task

73-11-00-200-802-A.

NOTE: 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.

Reject and replace the tube if evidence of contact frettage to

a depth of greater than 0.1 mm (0.004 in.) on the outer surface

of a bend or 0.2 mm (0.008 in.) in any other area is evident.

Printed in Great Britain

RB.211−73−AG797

Page 12

Oct.26/11

R Jun.13/12
(d) If the fuel tube is rejected, remove it in accordance with AMM Task

70-12-01-000-801-A and replace it with new in accordance with AMM Task

70-12-01-400-801-A.

(6) Fit clips back to each of the following locations:

Pre SB 73-F737 and pre SB 73-F738: Engines Inspect the clipping points

100181, 102321, 100282, 100187, 102252, 100178, 100180, 102259, 102321,

100186 and 102260

Post SB 73-F737 and SB 73-F738: Engines Inspect the clipping points

100181, 102321, 100282, 102374, 102252, 100178, 100180, 102259, 102321,

100186 and 102260

(7) Get access to the avionics compartment, then remove safety clips(s) and

the tag(s) and close this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION

For 4040 EM1:

722VU FADEC B ENG 1 13KS1 K46

722VU FUEL LP MOT 2 ENG 1 2QG1 U44

742VU FUEL LP MOT 1 ENG 1 1QG1 K75

742VU FADEC A ENG 1 12KS1 N74

For 4040 EM2:

722VU FADEC B ENG 2 13KS2 D43

722VU FUEL LP MOT 2 ENG 2 2QG2 U45

742VU FUEL LP MOT 1 ENG 2 1QG2 K76

742VU FADEC A ENG 2 12KS2 Q73

For 4040 EM3:

722VU FADEC B ENG 3 13KS3 K47

722VU FUEL LP MOT 2 ENG 3 2QG3 Q43

742VU FUEL LP MOT 1 ENG 3 1QG3 K77

742VU FADEC A ENG 3 12KS3 Q74

For 4040 EM4:

722VU FADEC B ENG 4 13KS4 D44

722VU FUEL LP MOT 2 ENG 4 2QG4 Q44

742VU FUEL LP MOT 1 ENG 4 1QG4 K78

742VU FADEC A ENG 4 12KS4 N75

(8) If any tube is replaced, do a leak check of the fuel oil heat exchanger

installation in accordance with AMM, 71-00-00, Adjustment/Test, Test

No.2, The Fuel and Oil Leak Test.

(9) Close Access:

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

items.

Printed in Great Britain

RB.211−73−AG797

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(b) Close the fan cowl doors in accordance with AMM 71-13-00, Maintenance

Practices.

For 4040EM1: 415AL 416AR

For 4040EM2: 425AL 426AR

For 4040EM3: 435AL 436AR

For 4040EM4: 445AL 446AR

(10) De-energise the aircraft electrical circuit in accordance with AMM

24-41-00, Maintenance Practices.

B. Reporting evidences

If any p-clip or a pipe is rejected then quarantine the pipe and record the

results in Appendix 1 or similar form. Send the recorded results to Rolls-Royce,

via your local Field Service representatives, for onward transmittal to Service

Engineering. The proforma attached as Appendix 1 to this NMSB shows the

information required and may be used to return data to Rolls-Royce.

C. Record of accomplishment.

Accomplishment of this Non-Modification Service Bulletin should be recorded in

accordance with local SB tracking system procedures.

Printed in Great Britain

RB.211−73−AG797

Page 14

Oct.26/11

R Jun.13/12
Fuel Tubes LP Compressor Case

Fig.1

Printed in Great Britain

RB.211−73−AG797

Page 15

Oct.26/11

R Jun.13/12
Fuel Tubes LP Compressor Case

Fig.2

Printed in Great Britain

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Page 16

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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-AG797

Date: Operator:

Engine Serial Number: Aircraft:

Hours Cycles

Engine Life:

Life since last shop visit:

Life since embodiment of SB

79-AG346:

Life since embodiment of SB 73-F737

(if applicable):

Life since embodiment of SB 73-F738

(if applicable):

Fuel Tubes Condition Observations (material transfer from

clips/fretted/dented/worn-please specify

depth)

FW57605 (SB 73-F738)

FW17689 (pre SB 73-F738)

FW57604 (SB 73-F738)

FK30710 (pre SB 73-F738)

FW57578 (SB 73-F737)

FK30713 (pre SB 73-F737)

Clips Condition Observations (material

transfer/dust/worn/cracked/metal band

exposed)

102252

100178

100180

102259

102321

100186

102260

100181

102321

100282

102374 (SB 73-F737)

100187 (pre SB 73-F737)

NOTES:

APPENDIX 1

Printed in Great Britain

RB.211−73−AG797

Appendix 1 - Page 1 of 1

Oct.26/11

R Jun.13/12