LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin are as follows:

Page Revision Number Revision Date

Bulletin

1 Sep.28/12

2 Sep.28/12

3 Sep.28/12

4 Sep.28/12

5 Sep.28/12

6 Sep.28/12

7 Sep.28/12

8 Sep.28/12

9 Sep.28/12

10 Sep.28/12

11 Sep.28/12

12 Sep.28/12

13 Sep.28/12

14 Sep.28/12

15 Sep.28/12

16 Sep.28/12

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18 Sep.28/12

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Appendix 1

Printed in Great Britain

RB.211−73−AG948

Transmittal - Page 2
1 Sep.28/12

Printed in Great Britain

RB.211−73−AG948

Transmittal - Page 3
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

B. Reason

Problem

Low Pressure (LP) fuel leaks from the LP fuel tubes between the combined LP/HP

(Low Pressure/High Pressure) Fuel Pump and the Fuel/Oil Heat Exchanger (FOHE)

have occurred in-service in the Trent 500 fleet. Movement of the FOHE mounts

due to wear 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 frettage between the exposed metal band and the

fuel tubes. The frettage reduces the fuel tube outer wall thickness, leading to

fracture of the fuel tube and the consequent fuel leak. This may cause the

leakage of significant amounts of fuel and can cause In-Flight Shut Down (IFSD)

and diversion events. This Non-Modification Service Bulletin (NMSB) is designed

to address the condition for both in-shop engines and those installed on-wing.

NMSB 73-AG797 and NMSB 73-G723 were used to gather information and to define

the inspection interval that is instructed in this document.

C. Description

This NMSB is issued to recommend on-wing and in-shop inspection of LP fuel

tubes, P-clips and FOHE mounts.

ENGINE - LP FUEL TUBES, CLIPS AND FOHE MOUNTS - INSPECTION FOR FRETTAGE -

NON-MODIFICATION SERVICE BULLETIN - NON - MOD.73-AG948

Printed in Great Britain

RB.211−73−AG948

Page 1 of 43

Sep.28/12

Sep.28/12
Advise your local Rolls-Royce representative of NMSB accomplishment. Record

inspection results in the table provided (Appendix 1) or similar and provide to

Rolls-Royce if any rectification action was required.

D. Compliance

ALERT

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

EASA Airworthiness Directive.

(1) On-wing

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

following intervals:

(a) Inspect within 6000 hours from either (which ever was accomplished

most recently):

(i) The embodiment of SB 73-F737 or SB 73-F738 (which ever was

embodied first)

(ii) The last fuel tube inspection in accordance with NMSB 73-AG797

or NMSB 73-G723 (which ever was embodied last)

(b) Following initial inspection, repeat the inspection at intervals not

exceeding 6000 engine flying hours.

(2) In-shop

Complete the actions detailed in 3.B. Accomplishment Instructions.

Inspect at all shop visits, post the issue of this bulletin.

E. Approval

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

under the authority of Design Organisation Approval EASA.21J.035 on Sep.27/12.

F. Manpower

(1) On-wing

(a) Time to gain access

0.5 man hours

(b) Time to inspect

4 man hours

Printed in Great Britain

RB.211−73−AG948

Page 2

Sep.28/12

Sep.28/12
(c) Time to replace tubes (if needed; includes Test 2 - The Fuel and Oil

Leak Test)

6 man hours if replacing with the same part

10 man hours if embodiment of SB 73-F737 is required

30 man hours if embodiment of SB 73-F738 is required

(d) Time to restore to serviceable condition

0.5 man hours

(2) In-shop

(a) Time to inspect

4 man hours

(b) Time to replace tubes (if needed; includes Test 2 - The Fuel and Oil

Leak Test)

6 man hours if replacing with the same part

10 man hours if embodiment of SB 73-F737 is required

30 man hours if embodiment of SB 73-F738 is required

G. Material Price and Availability

Not affected.

H. Tooling Price and Availability

Special tools are not required.

I. References

(1) Rolls-Royce RB211 Service Bulletins:

(a) 73-F737

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

Introduction of a revised LP Fuel Tube Incorporating Rigid End

Fittings

(b) 73-F738

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

revised LP Fuel Tubes Incorporating Rigid End Fittings

Printed in Great Britain

RB.211−73−AG948

Page 3

Sep.28/12

Sep.28/12
(2) Rolls-Royce RB211 Non-Modification Service Bulletins:

(a) 73-G723

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

Frettage - Non-Modification Service Bulletin

(b) 73-AG797

Engine - LP Fuel Tubes and Clips - Inspection for Frettage -

Non-Modification Service Bulletin

(3) Engine Manual:

72-00-34, LP Compressor Case Module, Removal and Installation

72-34-00, LP Compressor Case Module, Assembly and Disassembly

(4) Engine Illustrated Parts Catalogue:

72-34-15, LP Compressor Rear Case

72-35-16, LP Compressor Case Accessories Mounts

73-11-47, Fuel Tubes, LP Compressor Case

79-21-11, Fuel Oil Heat Exchanger

(5) Aircraft Maintenance Manual

70-12-01, Removal/Installation of Rigid Tubes

71-00-00, Power Plant - General

71-13-00, Fan Cowl - Maintenance Practices

79-22-41, Heat Exchanger Fuel/Oil, Removal/Installation

Printed in Great Britain

RB.211−73−AG948

Page 4

Sep.28/12

Sep.28/12
2. Material Information

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

72-34-15

FIG/ITEM

NO.

PART

NO.

QTY PART TITLE MAT

05070 FW22292 1 Bracket, assy support,

front

-

05085 FK31365 1 Bracket, top mounting assy

FCOC mounting - upper

-

05180 FK32651 1 Bracket, assy accessory

mounting

-

05215 FK31492 1 Bracket -

05230 FK31375 1 Bracket, bottom mount, assy

FCOC brace mounting

-

05245 FK17275 1 Bracket -

05260 FK12473 1 Bracket, assy -

72-34-15

FIG/ITEM

NO.

PART

NO.

QTY PART TITLE MAT

06102 AS20626 7 Nut, 0.3125 in. dia -

06108 B485850 14 Washer -

06119 AS48619 1 Bolt, 0.3125 in.dia x 1.188-

06125 AS48625 4 Bolt, 0.3125-24UNJF x 1.562-

06131 AS48631 2 Bolt, 0.3125-24UNJF x 1.938-

72-35-16

FIG/ITEM

NO.

PART

NO.

QTY PART TITLE MAT

05094 AS48512 2 Bolt, Bihex HD, 0.250

in.dia x 0.748

-

05095 FEB5031 1 Strap, bonding upper - FCOC

to rear fancase, VU5082

-

05096 AS20625 2 Nut, 0.250 in.dia -

05097 AS12944 5 Washer, 0.250 in.dia -

05098 AS48520 1 Bolt, 0.250 in.dia x 1.250 -

05099 SP124G 1 Washer -

05445 FEB5032 1 Strap, bonding lower - FCOC

to rear fancase, VU5082

-

05446 AS20624 1 Nut, 0.190 in.dia -

05447 AS12943 1 Washer, 0.190 in.dia -

05448 AS48409 1 Bolt, 0.190 in.dia x 0.562

in.

-

Printed in Great Britain

RB.211−73−AG948

Page 5

Sep.28/12

Sep.28/12
73-11-47

FIG/ITEM

NO.

PART

NO.

QTY PART TITLE MAT

04100 FK30710 1 Tube, assy fuel - LP pump

to line disconnect, pre

SB73-F738

-

04100A FW57604 1 Tube, assy fuel - LP pump

to line disconnect,

SB73-F738 PT01

-

04104 RR188C 3 Ring, V80756, pre SB73-F738 -

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

pre SB73-F738

-

04106A AS48516 3 Bolt, 0.25 in.dia x 1.000,

SB73-F738 PT01

-

04107 AS43013-

129

2 Ring, pre SB73-F738 -

04108 AS43013-

134

1 Ring -

04117 K16738 1 Connector, pre SB73-F738 -

04125 AS48410 1 Bolt, 0.190 in.dia x 0.625,

pre SB73-F738

-

04126 K8831 1 Washer, 0.190 in.dia x 0.51

thk

-

04127 AS12943 1 Washer, 0.190 in. dia -

04128 AS62426 1 Clip, 41.27mm (1.625) -

04132 AS20624 1 Nut, 0.190 in.dia -

04133 AS48415 1 Bolt, 0.190 in. dia x 0.938 -

04134 K8831 1 Washer, 0.190 in.dia x 0.51

thk

-

04136 AS62426 1 Clip, 41.27mm (1.625) -

04138 UP10479 1 Spacer, 10mm -

04140 AS20624 1 Nut, 0.190 in. dia -

04202 LK30233 1 Ferrule, Seal Carrier, Pre

SB73-F738

-

04202A FW57169 1 Adaptor, Flanged SB73-F738

PT01

-

04208 LK29963 1 Retainer, Ferrulem Pre

SB73-F738

-

04242 UP10968 1 Adaptor, Flanged -

04500 FW17689 1 Tube, assy fuel pump to

FCOC, pre SB73-F738

-

04500A FW57605 1 Tube, assy fuel pump to

FCOC, SB73-F738 PT01

-

04502 AS20625 4 Nut, 0.190 in. dia -

04504 AS12944 4 Washer, 0.25 in.dia -

04506 AS48516 4 Bolt, 0.25 in.dia x 1.000 -

04508 AS43013-

130

1 Ring -

04512 RR188C 3 Ring, V80756, pre SB73-F738 -

Printed in Great Britain

RB.211−73−AG948

Page 6

Sep.28/12

Sep.28/12
04514 BLT5529 3 Bolt, 0.25 in.dia x 1.028,

pre SB73-F738

-

04514A AS48516 3 Bolt, 0.25 in.dia x 1.000,

pre SB73-F738 PT01

-

04515 AS43013-

129

2 Ring, pre SB73-F738 -

04516 AS43013-

134

1 Ring -

04517 K16738 1 Connector, pre SB73-F738 -

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

04526 K8831 1 Washer, 0.190 in. dia x

0.51 thk

-

04528 AS62426 1 Clip, 41.27mm (1.625) -

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 thk

-

04536 AS62426 1 Clip, 41.27 mm (1.625) -

04540 AS20624 1 Nut, 0.190 in. dia -

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

04542 K8831 1 Washer, 0.190 in.dia x 0.51

thk

-

04544 AS62426 1 Clip, 41.27 mm (1.625) -

04548 AS20624 1 Nut, 0.190 in. dia -

04549 AS48434 1 Bolt, 0.190 in. dia x 2.125 -

04550 K8831 1 Washer, 0.190 in. dia x

0.51 thk

-

04552 AS62426 1 Clip, 41.27 mm (1.625) -

04554 UP10482 1 Spacer, 25 mm -

04555 UP10480 1 Spacer, 15 mm -

04556 AS20624 1 Nut, 0.190 in. dia -

04602 UP10969 1 Adapter, Flanged-recessed -

04614 UP11132 1 Adapter, 1.625 in. dia tube -

04638 LK29963 1 Retainer, Ferrule, pre

SB73-F738

-

04642 LK30233 1 Ferrule, Seal carrier, pre

SB73-F738

-

04642A FW57169 1 Adapter, Flanged, SB73-F738

PT01

-

73-11-47

FIG/ITEM

NO.

PART

NO.

QTY PART TITLE MAT

05070 FW11124 1 Bracket -

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

-

Printed in Great Britain

RB.211−73−AG948

Page 7

Sep.28/12

Sep.28/12
05104 RR188C 3 Ring, V80756, pre SB

73-F737

-

05106 BLT5529 3 Bolt, 0.250 in. dia x 1.028

in. pre SB 73-F737

-

05106A AS48516 3 Bolt, 0.250 in. dia x 1.000

in. SB 73-F737 PT01

-

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 -

05117 K16738 2 Connector, pre SB 73-F737 -

05125 AS48408 1 Bolt, 0.190 in. dia x 0.500-

05126 K8831 1 Washer, 0.190 in. dia x

0.51 thk

-

05128 AS62426 1 Clip, 41.27 mm (1.625) -

05132 AS20624 1 Nut, 0.190 in. dia -

05133 AS48409 1 Bolt, 0.190 in. dia x 0.500

pre SB 73-F737

-

05134 K8831 1 Washer, 0.190 in. dia x

0.51 thk, pre SB73-F737

-

05136 AS62426 1 Clip, 41,27 mm (1.625) pre

SB 73-F737

-

05149 AS48408 1 Bolt, 0.190 in. dia x 0.500-

05150 K8831 1 Washer, 0.190 in. dia x

0.51 thk

-

05152 AS62426 1 Clip, 41.27 mm (1.625) -

05156 AS20624 1 Nut, 0.190 in. dia -

05157 AS48412 1 Bolt, 0.190 in. dia x 0.750-

05158 K8831 1 Washer, 0.190 in. dia x

0.51 thk

-

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

05162 UP10478 1 Spacer, 5 mm -

05164 AS20624 1 Nut, 0.190 in. dia -

05165 AS48410 1 Bolt, 0.190 in. dia x 0.620

SB 73-F737 PT01

-

05166 K8831 1 Washer, 0.190 in. dia x

0.51 thk SB 73-F737 PT01

-

05167 AS12943 1 Washer, 0.190 in. dia SB

73-F737 PT01

-

05168 AS62426 1 Clip, 41,27 mm (1.625) SB

73-F737 PT01

-

Printed in Great Britain

RB.211−73−AG948

Page 8

Sep.28/12

Sep.28/12
05172 AS20624 1 Nut, 0.190 in. dia SB

73-F737 PT01

-

05202 LK30233 1 Ferrule, Seal carrier, pre

SB 73-F737

-

05202A FW57169 1 Adapter, Flanged, SB

73-F737 PT01

-

05208 LK29963 1 Retainer, Ferrule, pre SB

73-F737

-

05238 LK29963 1 Retainer, Ferrule, pre SB

73-F737

-

05242 LK30233 1 Ferrule, Seal carrier, pre

SB 73-F737

-

05242A FW57169 1 Adapter, Flanged, SB

73-F737

-

79-21-11

FIG/ITEM

NO.

PART

NO.

QTY PART TITLE MAT

01015 FK19654 1 Bracket, angle bonding lead -

01030 55027001-1 1 Cooler, Oil-Fuel Cooled

(5002EN), VSG215, pre SB

79-E371

-

01030A 55027001-

11

1 Cooler, Oil-Fuel Cooled

(5002EN), VSG215, SB

79-E371 PT01, pre SB

79-G346

-

01030B 55027001-

21

1 Cooler, Oil-Fuel Cooled

(5002EN), VSG215, SB

79-G346 PT01

-

01031 AS20626 1 Nut, 0.3125 in. dia -

01035 AS54722 1 Bolt -

01036 BLT5477 2 Bolt, 0.3125 in. dia x

1.240

-

01037 AS12945 2 Washer -

01070 AS20626 1 Nut, 0.3125 in. dia -

01072 AS12945 1 Washer -

01074 AS54746 1 Bolt -

01280 FK10141 1 Bracket, assy of FCOC

support strut

-

01282 BLT5477 2 Bolt, 0.3125 in. dia x

1.240

-

01284 AS12945 2 Washer -

01300 FK19290 1 Strut, assy FOHE support -

Front

-

01302 AS20626 1 Nut, 0.3125 in. dia -

01306 AS54722 1 Bolt -

01310 UP11630 3 Spacer -

01330 FK11165 1 Bracket, assy front upper

mounting - oil tank

-

Printed in Great Britain

RB.211−73−AG948

Page 9

Sep.28/12

Sep.28/12
01334 AS20626 2 Nut, 0.3125 in. dia -

01336 AS48618 2 Bolt, 0.3125 in. dia x

1.125

-

01338 B485850 4 Washer -

01400 FK19924 1 Plate, assy FCOC support -

01402 AS20626 1 Nut, 0.3125 in. dia -

01404 AS54722 1 Bolt -

01500 FK19264 1 Strut, assy FOHE support -

Lower

-

01502 AS20626 2 Nut, 0.3125 in. dia -

01504 AS54722 2 Bolt -

01560 FK31369 1 Link, upper assy support -

FCOC

-

01562 AS20626 1 Nut, 0.3125 in. dia -

01564 AS54722 1 Bolt -

01580 FK31371 1 Link, upper assy FOHE

support

-

01615 FW11126 1 Bracket -

01620 FW11164 1 Strut, assy FCOC support -

Lower

-

01622 AS20626 2 Nut, 0.3125 in. dia -

01624 AS48618 1 Bolt, 0.3125 in. dia x

1.125

-

01626 B485850 4 Washer -

02058 0F28-021 1 Ring, sealing -

02068 0F25-021 1 Ring, sealing -

02110 0F25-021 1 Ring, sealing -

Printed in Great Britain

RB.211−73−AG948

Page 10

Sep.28/12

Sep.28/12
3. Accomplishment Instructions

A. On-wing - Inspect the fuel tubes (Part Nos.: FW57605/FW17689, FW57604/FK30710

and FW57578/FK30713), P-clips and FOHE mounting hardware for

wear/damage/frettage. Refer to Fig.1 thru Fig.21.

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.

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

DOWN, 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.

(1) Get access

(a) Open the fan cowl doors; refer to Aircraft Maintenance Manual (AMM)

Task 71-13-00.

(i) For 4040EM1: 415AL 416AR

(ii) For 4040EM2: 425AL 426AR

(iii) For 4040EM3: 435AL 436AR

(iv) For 4040EM4: 445AL 446AR

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

Printed in Great Britain

RB.211−73−AG948

Page 11

Sep.28/12

Sep.28/12
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 BEEN DRAINED FROM THE ENGINE BACK

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

TO SOME PARTS.

(3) Visually inspect fuel tubes (EIPC 73-11-47, Fig/Item No.04-500A/04-500,

04-100A/04-100 and 05-100A/05-100) and the relevant clipstacks for

damage/wear. Refer to Fig.1 thru Fig.16. Record inspection results in the

table provided (Appendix 1) or similar and provide to Rolls-Royce if any

rectification action was required.

CAUTION: INSPECTION OF THE CLIPS MUST BE DONE ONE AT A TIME TO PREVENT

ALTERATION TO THE SYSTEM ALIGNMENT AND STRESSING OF THE TUBES

AND CLIPS

(a) During removal of the clips look for any significant relaxation of

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 minimise any strain in the

system. Make a note on the proforma (Appendix 1) or similar if

alignment issues are seen.

(b) Visually inspect all the clips for obvious evidence of wear that may

have damaged the fuel tubes (for example, significant wear to rubber

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

(i) Remove any obviously damaged clip(s) first (one at a time) and

inspect fuel tube(s) in accordance with criteria as specified

in steps 3.A.(3)(f) and 3.A.(3)(g).

(ii) If clip(s) and/or fuel tube(s) are found to be unserviceable,

remove and replace in accordance with step 3.A.(3)(h).

(c) Remove and inspect each remaining clip one at a time (positions

specified in steps 3.A.(3)(c)(i) and 3.A.(3)(c)(ii)) in accordance

with the criteria as specified in step 3.A.(3)(f). Start from either

the top or bottom of the tube run.

(i) LP - FOHE tube run clipping positions: CP102252, CP100178,

CP100180, CP102259, CP102321, CP102373 (SB 73-F738) / CP100186

(pre SB 73-F738), CP102260.

(ii) FOHE - HP tube run clipping positions: CP100181, CP102321,

CP100282, CP102374 (SB 73-F737) / CP100187 (pre SB 73-F737).

Printed in Great Britain

RB.211−73−AG948

Page 12

Sep.28/12

Sep.28/12
(d) Inspect the fuel tube around the area which the clip was fitted in

accordance with the criteria as specified in step 3.A.(3)(g).

(i) If fuel tube is found to be serviceable, reinstall or replace

clip in accordance with step 3.A.(3)(h).

(ii) If fuel tube is found to be unserviceable, replace in

accordance with step 3.A.(3)(h).

(e) Make sure clip and tube are returned to an acceptable condition before

moving to the next clipping point.

(f) P-clip acceptance and rejection criteria

Obvious excessive damage Reject

Cracked Distressed Rubber Reject

Worn/damaged internal diameter

of rubber

Reject

Metal band exposure Reject

Evidence of corrosion/wear/

material transfer to the tube

surface (powder/dust deposits at

ends of rubber section)

Reject

(g) Fuel tube acceptance and rejection criteria

Contact frettage to a depth

greater than 0.1 mm (0.004 in.)

on the outer surface of a bend on

the tube

Reject

Contact frettage to a depth

greater than 0.2 mm (0.008 in.)

in any other area of the tube

Reject

NOTE: Take particular care to inspect the entire exposed surface of

the tube. A mirror can be used in areas where direct line of

sight access is difficult.

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

accordance with Aircraft Maintenance Manual 70-12-01. Refer to Service

Bulletins 73-F737 and SB73-F738 for specific installation instructions

and Fig.1 thru Fig.16 for tube and clipping point details.

Printed in Great Britain

RB.211−73−AG948

Page 13

Sep.28/12

Sep.28/12
(4) Inspect all FOHE mounts and associated hardware for signs of obvious

damage and excessive wear. Refer to Fig.17 thru Fig.21. Record inspection

results in the table provided (Appendix 1) or similar and provide to

Rolls-Royce if any rectification action was required.

NOTE: It is not necessary to remove the FOHE from the engine or

disconnect the oil and fuel tubes. It is acceptable to inspect the

FOHE mounts and associated hardware when the FOHE is installed on

the engine

NOTE: The FOHE mounts, links and brackets can be removed, inspected and

replaced one at a time.

NOTE: The purpose of this inspection is to identify noticeable play in

the spherical bearing of the FOHE mounts. In most cases this can be

done in situ without removing hardware, by manipulating the FOHE

and mounts. If wear is suspected then remove the bolt at one end of

the link/strut for more detailed assessment.

(a) Disconnect the following FOHE mounts and links one at a time in

accordance with Aircraft Maintenance Manual 79-22-41 and examine by

manipulation and visual inspection in accordance with the criteria as

specified in step 3.A.(4)(b).

EIPC Ref Part No. Description

79-21-11,

01-280

FK10141 Bracket, assy of FCOC support strut

79-21-11,

01-300

FK19290 Strut, assy FOHE support - Front

79-21-11,

01-330

FK11165 Bracket, assy front upper mounting -

Oil tank

79-21-11,

01-400

FK19924 Plate, assy FCOC support

79-21-11,

01-500

FK19264 Strut, assy FCOC support - Lower

79-21-11,

01-620

FK11164 Bracket, assy FCOC mounting - Lower

72-34-15,

05-085

FK31365 Bracket, top mounting assy FCOC

mounting - Upper

72-34-15,

05-230

FK31375 Bracket, bottom mount assy, FCOC

brace mounting

NOTE: If replacement of damaged parts is not possible during

inspection then they can be replaced within 800 flight hours.

(b) FOHE mounting hardware acceptance and rejection criteria:

Bearings tight but not seized Accept

Low friction but no play in

bearings

Accept

Printed in Great Britain

RB.211−73−AG948

Page 14

Sep.28/12

Sep.28/12
Minor scratches/score marks Accept

Play in spherical bearings Replace within 800 flight hours

Spherical bearings seized Replace within 800 flight hours

Bent or twisted Replace within 800 flight hours

(5) If fancase mounting bracket, 72-34-15, 05-230, 79-21-11, 01-330 or 01-620

(FK31375, FK11165 or FK11164) are found to be unserviceable, remove and

replace in accordance with the following instructions. Refer to Fig.20 and

Fig.21.

(a) Remove and install the bracket (79-21-11, 01-330). Refer to Fig.20.

(i) Remove the brackets at location A.

(1) Release and remove the bolts, washers and nuts that attach

the bracket to the LP compressor case flange FD.

(2) Remove the bracket.

(3) Attach the bracket (79-21-11, 01-330) to the rear of the LP

compressor case flange FD with the bolts (79-21-11, 01-336),

the washers (79-21-11, 01-338) and the nuts (79-21-11,

01-334).

(ii) Torque the nuts (79-21-11, 01-334) to 32,2 Nm (285 lbfin).

(b) Remove and install the brackets (79-21-11, 01-620) and (79-21-11,

01-615). Refer to Fig.20.

(i) Remove the brackets at location A.

(1) Release and remove the bolts, washers and nuts that attach

the brackets to the LP compressor case flange FD.

(2) Remove the brackets.

(3) Attach the bracket (79-21-11, 01-620) to the rear of the LP

compressor case flange FD and the bracket (79-21-11, 01-615)

to the front of the LP compressor case flange FD, with the

bolts (79-21-11, 01-624), the washers (79-21-11, 01-626) and

the nuts (79-21-11, 01-622).

(ii) Torque the nuts (79-21-11, 01-622) to 32,2 Nm (285 lbfin).

Printed in Great Britain

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(c) Remove and install the brackets (72-34-15, 05-260), (72-34-15,

05-245), (72-34-15, 05-230), (72-34-15, 05-215) and (72-34-15, 05-180)

at position A. Refer to Fig.21.

(i) Remove the brackets at position A.

(1) Release and remove the bolts, washers and nuts that attach

the brackets to the LP compressor case flange FE.

(2) Remove the brackets.

(3) Attach the brackets (72-34-15, 05-260), (72-34-15, 05-245),

(72-34-15, 05-230), (72-34-15, 05-215) and (72-34-15, 05-180)

to the LP compressor case flange FE with the four bolts

(72-34-15, 06-125), eight washers (72-34-15, 06-108) and four

nuts (72-34-15, 06-102).

(ii) Torque the four nuts (72-34-15, 06-102) to 32,2 Nm (285 lbfin).

(6) Reassemble the FOHE mounts and links in accordance with Aircraft

Maintenance Manual 79-22-41.

(7) Remove the access platform.

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

installation in accordance with Aircraft Maintenance Manual 71-00-00, Test

No.2, The Fuel and Oil Leak Test.

(9) For each fuel tube, make sure there is a 5 mm minimum clearance from any

adjacent tubes and hardware. If necessary loosen adjacent clips and

carefully manipulate the tube alignment to achieve the necessary

clearance.

(10) Close access:

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

items.

(b) Close the fan cowl doors in accordance with Aircraft Maintenance

Manual (AMM) 71-13-00.

(i) For 4040EM1: 415AL 416AR

(ii) For 4040EM2: 425AL 426AR

(iii) For 4040EM3: 435AL 436AR

(iv) For 4040EM4: 445AL 446AR

Printed in Great Britain

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Sep.28/12
B. At shop visit - Inspect the fuel tubes (EIPC 73-11-47, 04/500A/04-500,

04-100A/04-100 and 05-100A/05-100) P-clips and FOHE mounting hardware for

wear/damage/frettage. Refer to Fig.1 thru Fig.21.

(1) Visually inspect the fuel tubes (EIPC 73-11-47, Fig/Item Nos.

04/500A/04-500, 04-100A/04-100 and 05-100A/05-100) P-clips and FOHE

mounting hardware for damage/wear. Refer to Fig.1 thru Fig.16. Record

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

provide to Rolls-Royce if any rectification action was required.

CAUTION: INSPECTION OF THE CLIPS MUST BE DONE ONE AT A TIME TO PREVENT

ALTERATION TO THE SYSTEM ALIGNMENT AND STRESSING OF THE TUBES

AND CLIPS

(a) During removal of the clips look for any significant relaxation of

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 minimise any strain in the

system. Make a note on the proforma (Appendix 1) or similar if

alignment issues are seen.

(b) Visually inspect all the clips for obvious evidence of wear that may

have damaged the fuel tubes (for example, significant wear to rubber

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

(i) Remove any obviously damaged clip(s) first and inspect fuel

tube(s) in accordance with the criteria as specified in steps

3.B.(1)(f) and 3.B.(1)(g).

(ii) If clip(s) and/or fuel tube(s) are found to be unserviceable,

remove and replace in accordance with step 3.B.(1)(h).

(c) Remove and inspect each remaining clip one at a time (positions

specified in 3.B.(1)(c)(i) and 3.B.(1)(c)(ii)) in accordance with the

criteria as specified in step 3.B.(1)(f). Start from either the top or

the bottom of the tube run.

(i) LP - FOHE tube run clipping positions: CP102252, CP100178,

CP100180, CP102259, CP102321, CP102373 (SB 73-F738) / CP100186

(pre SB 73-F738), CP102260.

(ii) FOHE - HP tube run clipping positions: CP100181, CP102321,

CP100282, CP102374 (SB 73-F737) / CP100187 (pre SB 73-F737).

(d) Inspect the fuel tube around the area which the clip was fitted in

accordance with criteria as specified in step 3.B.(1)(g).

(i) If fuel tube is found to be serviceable, reinstall or replace

clip in accordance with step 3.B.(1)(h).

Printed in Great Britain

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Page 17

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Sep.28/12
(ii) If fuel tube is found to be unserviceable, replace in

accordance with step 3.B.(1)(h).

(e) Make sure clip and tube are returned to an acceptable condition before

moving to the next clipping point.

(f) P-clip acceptance and rejection criteria

Obvious excessive damage Reject

Cracked Distressed Rubber Reject

Worn/damaged internal diameter

of rubber

Reject

Metal band exposure Reject

Evidence of corrosion/wear/

material transfer to the tube

surface (powder/dust deposits at

ends of rubber section)

Reject

(g) Fuel tube acceptance and rejection criteria

Contact frettage to a depth

greater than 0.1 mm (0.004 in.)

on the outer surface of a bend on

the tube

Reject

Contact frettage to a depth

greater than 0.2 mm (0.008 in.)

in any other area of the tube

Reject

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.

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

accordance with Engine Manual 72-00-34. Refer to Fig.1 thru Fig.16 for

tube and clipping point details.

Printed in Great Britain

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Page 18

Sep.28/12

Sep.28/12
(2) Inspect all FOHE mounts and associated hardware for signs of obvious

damage and excessive wear. Refer to Fig.17 thru Fig.21. Record inspection

results in the table provided (Appendix 1) or similar and provide to

Rolls-Royce if any rectification action was required.

NOTE: It is not necessary to remove the FOHE from the engine or

disconnect the oil and fuel tubes. It is acceptable to inspect the

FOHE mounts and associated hardware whilst the FOHE is assembled to

the engine.

NOTE: FOHE mounts/links/brackets can be removed, inspected and replaced

one at a time

NOTE: The purpose of this inspection is to identify noticeable play in

the spherical bearing of the FOHE mounts. In most cases this can be

done without removing hardware, by manipulating the FOHE and

mounts. If wear is suspected then remove the bolt at one end of the

link/strut for more detailed assessment.

(a) Disconnect the following FOHE mounts and links one at a time in

accordance with Engine Manual 72-00-34 and 72-34-00 and examine by

manipulation and visual inspection in accordance with the criteria as

specified in step 3.B.(2)(b).

EIPC Ref Part No. Description

79-21-11,

01-280

FK10141 Bracket, assy of FCOC support strut

79-21-11,

01-300

FK19290 Strut, assy FOHE support - Front

79-21-11,

01-330

FK11165 Bracket, assy front upper mounting -

Oil tank

79-21-11,

01-400

FK19924 Plate, assy FCOC support

79-21-11,

01-500

FK19264 Strut, assy FCOC support - Lower

79-21-11,

01-620

FK11164 Bracket, assy FCOC mounting - Lower

72-34-15,

05-085

FK31365 Bracket, top mounting assy FCOC

Mounting - Upper

72-34-15,

05-230

FK31375 Bracket, bottom mount, assy FCOC

brace mounting

(b) FOHE mounting hardware acceptance and rejection criteria:

Bearings tight but not seized Accept

Low friction but no play in

bearings

Accept

Minor scratches/score marks Accept

Play in spherical bearings Reject

Spherical bearings seized Reject

Printed in Great Britain

RB.211−73−AG948

Page 19

Sep.28/12

Sep.28/12
Bent or twisted Reject

(3) Re-assemble the FOHE mounts and links in accordance with Engine Manual

72-00-34 and 72-34-00.

(4) For each fuel tube, make sure there is a 5 mm minimum clearance from any

adjacent tubes and hardware. If necessary loosen adjacent clips and

carefully manipulate the tube alignment to achieve the necessary

clearance.

C. A record of accomplishment is required.

Printed in Great Britain

RB.211−73−AG948

Page 20

Sep.28/12

Sep.28/12
SB73-F737 and SB73-F738 Fuel Tubes and LP Compressor Case

Fig.1

Printed in Great Britain

RB.211−73−AG948

Page 21

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Sep.28/12
Pre SB73-F738 LP Fuel Pump to FOHE Supply Tube Run

Fig.2

Printed in Great Britain

RB.211−73−AG948

Page 22

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Sep.28/12
SB73-F738 LP Fuel Pump to FOHE Supply Tube Run

Fig.3

Printed in Great Britain

RB.211−73−AG948

Page 23

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Sep.28/12
Pre SB73-F737 and SB73-F737 Fuel Tubes LP Compressor Case

Fig.4

Printed in Great Britain

RB.211−73−AG948

Page 24

Sep.28/12

Sep.28/12
Pre SB73-F737 and SB73-F737 FOHE to HP Fuel Pump Tube Run

Fig.5 (sheet 1 of 2)

Printed in Great Britain

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Sep.28/12
Pre SB73-F737 and SB73-F737 FOHE to HP Fuel Pump Tube Run

Fig.5 (sheet 2 of 2)

Printed in Great Britain

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Page 26

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Sep.28/12
Pre SB73-F738 and SB73-F738 Clipstack Assembly CP102252

Fig.6

Printed in Great Britain

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Page 27

Sep.28/12

Sep.28/12
Pre SB73-F738 and SB73-F738 Clipstack Assembly CP100178

Fig.7

Printed in Great Britain

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Sep.28/12
Pre SB73-F738 and SB73-F738 Clipstack Assembly CP100180

Fig.8

Printed in Great Britain

RB.211−73−AG948

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Sep.28/12
Pre SB73-F738 and SB73-F738 Clipstack Assembly CP102259

Fig.9

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RB.211−73−AG948

Page 30

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Sep.28/12
Pre SB73-F738 and SB73-F738 Clipstack Assemblies CP102373 and 100186

Fig.10

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Sep.28/12
Pre SB73-F738 and SB73-F738 Clipstack Assembly CP102260

Fig.11

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Sep.28/12
Pre SB73-F737 and SB73-F737 Clipstack Assembly CP100181

Fig.12

Printed in Great Britain

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Page 33

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Sep.28/12
Pre SB73-F737 and SB73-F737 Clipstack Assembly CP102321

Fig.13 (sheet 1 of 2)

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RB.211−73−AG948

Page 34

Sep.28/12

Sep.28/12
Pre SB73-F738 and SB73-F738 Clipstack Assembly CP102321

Fig.13 (sheet 2 of 2)

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Page 35

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Sep.28/12
Pre SB73-F737 and SB73-F737 Clipstack Assembly CP100282

Fig.14

Printed in Great Britain

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Page 36

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Sep.28/12
SB73-F737 Clipstack Assembly CP102374

Fig.15

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Sep.28/12
Pre SB73-F737 Clipstack Assembly CP100187

Fig.16

Printed in Great Britain

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Sep.28/12
FOHE Mounting Hardware

Fig.17

Printed in Great Britain

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Sep.28/12
FOHE Mounting Hardware

Fig.18

Printed in Great Britain

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Sep.28/12
Arrangement of bonding leads

Fig.19

Printed in Great Britain

RB.211−73−AG948

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Sep.28/12

Sep.28/12
Arrangement of Brackets Mounted on Fancase Flange FD

Fig.20

Printed in Great Britain

RB.211−73−AG948

Page 42

Sep.28/12

Sep.28/12
Arrangement of Brackets Mounted on Fancase Flange FE

Fig.21

Printed in Great Britain

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Page 43

Sep.28/12

Sep.28/12
This form (or similar) to be completed for every inspection where rectification

action was required. Results to be sent to Rolls-Royce via your Service

Representative

Feedback Sheet NMSB 73-AG948

Date: Operator:

Engine Serial Number: Aircraft:

Hours Cycles

Engine Life:

Life since last shop visit:

Life since embodiment of NMSB

73-G723/NMSB 73-AG797*:

Fuel Tubes Condition Observations (material transfer from

clips/fretted/dented/worn-please specify)

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 - please specify)

102252

100178

100180

102259

102321

102373 (SB 73-F738)/

100186 (pre SB 73-F738)*

102260

100181

102321

100282

102374 (SB 73-F737)/

100187 (pre SB 73-F737)*

FOHE Mounts Condition

Observations (tight/seized/play in

spherical bearings/sperical bearings

seized/bent or twisted/minor cosmetic

damage - please specify)

FK10141

FK19290

FK11165

FK19924

FK19264

FK11164

FK31365

FK31375

NOTES:

* delete as appropriate

APPENDIX 1

Printed in Great Britain

RB.211−73−AG948

Appendix 1 - Page 1 of 1

Sep.28/12

Sep.28/12