Jan.16/98

RBZll-524 SERIES PROPULSION SYSTEM SERVICE BULLETIN This document transmitsRevision 3 to ServiceBulletin RBZll-72-9764, Revision 1 to the Supplement,and the ModificationAcceptance Sheet.
Service Bulletin Revision Status Initial Issue Aug.20/93 Revision 1 Aug.25195 Revision 2 Nov.10/95 SupplementRevision Status Initial Issue Aug.20/93

Bulletin Revision 3 Remove Incorporate Pages 1, 3, 4, Pages 1, 3, 4, 6 and 11 6 and 11 dated Jan.16/98
Supplement Revision 1 Remove Incorporate Page 1 Page 1 Reason for Change To change the compliancecategory

Reason for Change To update prices

NOTE: Additionalwork IS NOT required on enginesmodified toprevious

issues of this Service Bulletin


# RB.211-72-9764 Transmittal Page I of 2LIST OF EFFECTIVE PAGES The effective pages to this ServiceBulletin following the incorporationof R Revision 3 and Revision 1 to the Supplementare as follows: Page Bulletin Rl2 R3 R4 .5 R67 8 9 10 R 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 Supplement Rl Rev. JJ&

3

1 Jan.16/98

Date Jan.16/98 Aug.20/93 Jan.16/98 Jan.16/98 Aug.25/95 Jan.16/98 Aug.20/93 Aug.20/93 Aug.20193 Aug.20/93 Jan.16/98 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93 Aug.20/93



# RB.2 I I-72-97 Transmittal Page 2

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# III ~~O~(il~ Propulsion System !f!, 

# SERVICE

**BULLETIN**

ENGINE - COMBUSTION SECTION - IMPROVEDPHASE 2 COMBUSTION LINER WITH STRENGTHENED HEAD AND IMPROVEDHEATSHIELDS - MOD.72-9764
1. Planning Information A. Effectivity (1) Lockheed L-1011 RB211-524B4-02, -524B4-02/10,-524B4-02/11, -524B4-D-02, -524B4-D-02/10, -524B4-D-02/11 Enginesprior to Serial No.14883 RB211-524 Modules -M04503AE, -MO4$3AF, -M04503AG,-MO4503AH, -MO4503AL, -MO4503AM, -M04578AB, -M04578AD,-MO4579AB, -M04579AD, -MO4586AA, -M04586AB, -MO4589& -M04589AB, -M04708AB, -M04709AB, -MO4719AA, -M04723AA, -M04723AB, -MO4724AA,-M04724AB, -M04725AA, -M04726AA, -MO4727AA, -M04727AB, -MO4728AAprior to SerialNo.CM5607 (2) Boeing 747 RB211-524D4-19, -524D4-19/11,-52404-19/12,-524D4-19/15, -524D4-19/17, -524D4-19/18, -524D4-19/19,-524D4-19/21,-524D4-19/22, -524D4X-19, -524D4X-19/11, -524D4X-19/12,-524D4X-19/15,-524D4X-19/17, -524D4X-19/18, -524D4X-19/19,-524D4X-19/21,-524D4X-19/22Engines prior to Serial No.12790 RB211-524 Modules -M04700AA,-MO4701AA, -MO4702AA,-M04702AB, -MO4703AA, -MO4703AB prior to Serial No.CM7806 RB211-524D4-B-19, -524D4-B-19/11,-524D4-B-19/12,-524D4-B-19/15, -524D4-B-19/17, -524D4-B-19/18,-524D4-B-19/19,-524D4-B-19/21, -524D4-B-19/22, -524D4X-B-19,-524D4X-B-19/11,-524D4X-B-19/12, -524D4X-B-19/15, -524D4X-B-19/17,-5241)4X-B-19/18, -524D4X-B-19/19, -524D4X-B-19/21, -524D4X-B-19/22Engines prior to Serial No.12790 RB211-524 Modules -M04710AA, -M0471OAB, -MO4711AA,-MO4712fi, -M04713AA, -MO4713AB prior to SerialNo.CM7806 RB211-524D4-39, -524D4-B-39Enginesprior to SerialNo.12561 RB211-524 Modules -MO4704AA, -M04704AB, -MO4705AA,-MO4705AB, -MO4714AA, -MO4714AB, -M04715AA, -MO4715ABprior to SerialNo.CM3961 RB211-524G2-19, -524G2-19/11,-524G2-19/15,-52463-19, -524G3-19/15, -52482-19, -524H2-19/11,-524H2-19/15Engines prior to Serial No.13343 RB211-524 Modules -MO4731AA,-MO4732AAprior to Serial No.CM8367
Aug.20193 R Revision 3 Jan.16/98 0 Rolls-Royce plc 

# RB.211-72-9764 Page 1 of 30

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# cl BB.z,flfl Propulsion System !ha 

# SERVICE

**BULLETIN**
(3) Boeing 767 RB211-524H-36, -524H-36/11Engines prior to Serial No.13452 RB211-524Modules -M04731AA, -MO4732AA prior to SerialNo.CM8454 B. Reason 

### (1)

(2)

(3)

(4)

(5) Problem Cracking of the front combustion liner diffuser case bleed struts and front section inner and outer linersmay occur after extendeduse. Additionally, Phase 2 combustion liners have exhibitedburning/holingof the heatshield inner ramp corners which may cause prematureremoval. Evidence There have been a few reported incidents of combustorhead rejection due to crackingwith the Phase 2 combustion liner. In addition there have been several incidentswith the ImprovedPackage 1 combustionliner which has the same basic head assembly. The cracking can result in loss of materialwhich in a small number of cases has led to downstream secondarydistress. Substantiation The changes introducedby this Service Bulletinhave completed over 1,000 cycles of development engine testingat temperatureconditions representativeof those likely to be encounteredby engines in service afterwhich the combustorwas found to be in good condition. Engineeringanalysis confirms a reduction in stresses in the affected area when a strengthenedhead is fitted and the problem is alleviated. Objective Incorporationof the changes introducedby this Service Bulletin (Modification)is designed to maintain reliability. It is anticipated that a significant increase in combustor head and heatshield life will result upon incorporationof this ServiceBulletin (Modification). Effect of Service Bulletin on: Operation Not affected Maintenance Not affected Overhaul Not affected Repair Schemes Affected (see l.K.) Interchangeability Not affected

Aug.20193 @ Rolls-Royce plc 

# RB.2 1I-72-9764 Page 2

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# ElmBOzjfJ Propulsion System !!!k 

# SERVICE

**BULLETIN**

C. Description (1) The changes introduced by this Service Bulletin are as follows:



# 5 G C .- 

### -Ls E ‘C n A revised front combustion liner assembly is introduced similar to the existing item except for the following: 

### (a> (b) 

## cc> Cd) (e> The combustion liner head with diffuser, diffuser walls and bleed offtake struts is produced in C263 material instead of N75 material. Reduced axial length bleed offtake struts with increased leading edge radius. A revised heatshield design featuring a modified cooling hole pattern and aluminised surface finish. The meter panel cooling hole pattern is revised to match the revised heatshield and ensure sufficient cooling air flow. The revised meter panel features an increased cooling flow burner seal ring. (2) Existing front combustion liner assemblies can be reworked, see Fig 1 to 5. (3) A combustion liner, head section assembly is required to accomplish rework of the front combustion liner. (4) For relationship with other Service Bulletins (Modification) see 1.J. D. Compliance R RB211-524H-36 series engines and modules R MANDATORY R This Service Bulletin (Modification) is classified MANDATORY by the United R Kingdom Civil Aviation Authority (C.A.A.) and must be accomplished by 10th R December, 1997. R RB211-524-B4-02, D4-19, D4-B-19, D4-39, D4-B-39, -524-G2-19, G3-19, H2-19

series engines and modules RECOMMENDED (3) Rolls-Royce recommends that this Service Bulletin (Modification) be accomplished, commensurate with Operators experience, when the part involved requires renewal because of its condition.

Aug.20/93 Revision 3 Jan.16/98 0 Rolls-Royce plc 

# RB.2 1l-72-9764 Page 3

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# SERVICE

**BULLETIN**

E. Approval Modification 72-9764 was approvedby a representativeof the United Kingdom Civil Aviation Authority (C.A.A.)on June 3/93. R Rolls-Royceplc Aerospace Group is approved under the authority of J.A.A. R Design OrganisationApprovalNo.CAA.JA.2001. F. Manpower Estimatedmanhours:

G.

H.(1) In service .. .. .. Not applicable (2) At overhaul .. . . . . 20 hours NOTE: The parts affectedby this ServiceBulletin are accessible at

overhaul. Material - Price and Availability Modificationkit not required; parts supplied as single line items. For prices and availabilityof future spares, see supplement to this bulletin. Tooling - Price and Availability For prices and availability,see supplement to this bulletin. Usage Part No. Description Additional tools MD13402 Location Ring A.M.O. Function

Locate combustion sectionand inner tackwelding MH13403/2 Argon Backing Block

MH13406/1 Argon BackingBlock

Aug.20193 Revision 3 Jan.16/98 liner head wall whilst Supply argon backing whilst welding replacement combustion liner head section to combusion liner innerwall Supply argon backing whilst welding replacement combustion liner head section to combusion liner outer wall

0 **Rolls-Royce** plc 

# RB.211-72-9764 Page 4

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# n @#JOzfJfl Propulsion System !!!!L 

# SERVICE

**BULLETIN**

Part No. MH13432/2

MH13434
MH1377512

MH13814 MHf5786/1

HC22892 3405528
HCU5037
HC21740
HC21743
1704302 Description

Location Clamp (innerwall) Ring

Check Gauge (inner wall) Location Clamp Ring (innerwall)

Check Gauge (outer wall) Checking and Welding fixture

Insert tool Tang Removal Tool
Thread Gauge Torque Check Plug Torque Adapter Torquemaster
Usage column abbreviations



### Aug.20/93 R Revision 1 Aug.25/95 Usage A.M.O. *

*
*

*
*

* *
*
*
*
* Function

Locate combustion liner inner wall whilst tackwelding to replacement combustionliner head section. Locate during post weld inspection Post weld inspectposition of inner wall Locate combustion liner outer wall whilst tackwelding to replacement combustionliner head section. Locate during post weld inspection Post weld inspectposition of outer wall Hold combustion liner component parts and tooling components during tackwelding and post weld inspection Insertwire thread insert Remove tang from fittedwire thread insert Inspect fittedwire thread insert threads Check fittedwire thread insert torque Check fittedwire thread insert torque Check fittedwire thread insert torque 'A' - accomplishement 'M' - maintenance '0' - overhaul

0 Roils-Royce plc 

# RB.2 11-72-9764 Page 5R R 

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# ElmBazflfl Propulsion System !!!fi, 

# SERVICE

**BULLETIN**

I. Weight and Balance (1) Weight change
. . . . . . Plus 1,18 kg. (2.6 lb.) (2) Moment Arm . . . . . . . . 1245 mm. (49,Oin.j rearwards (3) Datum . . . . . . . . Engine front mount centreline J. References (1) All engines This Service Bulletin supersedes the following Rolls-Royce RB211 Service Bulletins: 72-8980 Combustion section - Front combustion liner - (Hairpin

standard) stiffened cabin air offtake struts 72-9122 Combustion liners - Front combustion liner assembly with the P4

air transfer pillar bosses in revised material (2) All engines except RB211-524G2-19, -524G3-19, -524H2-19 and -524H-36 This Service Bulletin only applies to engines incorporating the following Rolls-Royce RB211 Service Bulletin: 72-8729 Combustion liners - Improved front combustion liner assembly -

Seventh section outer cooling ring with slotted holes. (3) Engine Manual, 72-41-00, Disassembly/Assembly and 72-41-13, Removal/Instllation (4) Engine Overhaul Processes Manual, T.S.D.594-J, TASK 70-00-00-100-101, 70-00-00-200-210, 70-00-00-200-213 and 70-00-00-300-409 K. Other Publications Affected (1) Illustrated Parts Catalogue, 72-41-13 (2) The following Repair Schemes will be revised to include the new parts introduced by this Service Bulletin: Engine Manual, 72-41-13, FRS2519, 3002, 5596

Aug.20/93 Revision 3 Jan.16/98 0 **Rolls-Royce** plc 

# RB.2 1l-72-9764 Page 62. Accomplishment Instructions

A. The new front combustionliner assemblies introducedby this Service Bulletin are freelyand fully interchangeablewith existing. Remove and install in accordancewith current overhaul procedure (EngineManual, 72-41-00,Disassembly/Assemblyand 72-41-13, Removal/Installation) B. Rework existing front combustion liner assembly (UL27659,UL23992 and UI.22988)(72-41-13Fig/ItemNo.02250) ConsumableMaterials OMat 508 Polishingbuff, hard felt OMat 3/62 Welding fillerwire, nickel C263

Procedure SupplementaryInformation (1) Machine to separateliner head assembly from innerand outer walls Refer to Fig.1 and 2. Pack under front lip as required and clamp to machine table. cut into head section leaving a trim allowance on inner and outerwalls. Discard head assembly. Use vertical lathe (2) Machine inner and outerwalls to length as required for re-fitment (3) Deburr (4) Remove thermalbarrier coating from areas adjacent to weld line on inner and outerwalls

(5) Select replacementcombustion liner head sectionassembly

(6) Cleanweld edges of liner walls and head sectionassembly

Aug.20/93 Refer to Fig.1 and 2. Use vertical lathe

Refer to Fig.1 and 2 and Engine Manual TASK 72-41-13-300-094,Repair Scheme FRS5596. Do not thin parentmaterial below 0,98 mm. (0.039in.). Use portable grinding equipment Refer to Fig.3 and Material Information. Parts: UL36797 - Combustion liner head section assembly Refer to Fig.2 OMat 508, Polishingbuff 

# RB.2 1l-72-9764
@Rolls

-Royce plc Page 7Procedure Supplemantary Information

(7) Locally degrease all weld edges Engine Overhaul ProcessesManual T.S.D.594-J, TASK 70-00-00-100-101 (8) Assemble replacementhead section Refer to Fig.1, 2, 3 and 4. assembly and inner and outer liner Ensure correct radial and walls into welding fixture position Tools: MH13432/2 Location Clamp

(innerwall) MH13775/2 Location Clamp

(outerwall) axial

ring ring ~H14786/1 Checking and welding

fixture MH13402 Location ring (9) Argonarc tackweldaround circumference of combustion liner head assembly and inner and outer wall joints Refer to Fig.1 and 3. Engine Overhaul ProcessesManual T.S.D.594-J, TASK 70-00-00-300-409. Tackweld through location ring slots Group 2 welds 12,7mm. (0.500in.) long Tools: MH13406/1 Outerwall argon backing

block MH13403/2 Innerwall argon backing

block Welding Data Type of Welding Weld Group Filler Material Torch Electrode Current Gas Flow Polarity Argonarc D.C. output Group 2 OMat 3/62 Fillerwire, nickel C263 BOC 200 or any 200 amp water cooled equivalent 2 per cent thoriated tungsten 2.37mm. (0.093in.)dia. 20 - 25 amps 25 CFH for torch 15 CFH for backing Negative The data is given for guidance only. Optimum settingsmust be obtained by trials.

Aug.20/93 

# RB.2 11-72-9764Page 8 @ RolIs-Royce plcAug.20193 Procedure SupplemantaryInformation

(10) Remove tackweldedassembly ’ from fixture (11) Planish joints at inner and outer positions to produce good butt joints (12) Argonarc weld complete inner and Refer to Fig.1 and 3. outer circumferentialjoints Refer to EngineOverhaul Processes Manual T.S.D.594-J,TASK 70-00-00-300-409and WeldingData in operation 2.B.(9) OMat 3/62 Welding fillerwire,

nickel C263 Tools: MH13406/1 Outerwall argon backing

block MH13403/2 Innerwall argon backing

block (13) Fluorescentpenetrant inspect welded areas Engine Overhaul ProcessesManual, T.S.D.594-J, TASK 70-00-00-200-210 or TASK 70-00-00-200-213.Reject if cracked (14) Inspectwelds Engine OverhaulProcessesManual, T.S.D.594-J, TASK 70-00-00-300-409, Fig.70-00-00-990-409-003,004, 005, A06 and B06 butt welded acceptance standards. Group 2 welds (15) Dress excessweld bead flush to parent material Maximum height of weld bead after dressing to be 0,25 mm. (O.OlOin.>. Parent materialmust not be reduced. Use portable grinding equipment



# RB.2 1l-72-9764 Page 9 @Rolls-Royce plcProcedure

(16) Dimensionally inspect

(17) Re-apply thermal barrier coating to areas of weld joints and apply to designated areas in head assembly (18) Select wire thread inserts

(19) Fit wire thread inserts

(20) Check torque of inserts

Aug.2C/93 Supplemantary Information Refer to Fig.1, 3 and 4 and Engine Manual TASK 72-41-13-300-095,Repair Scheme FRS2519 - Basic Repair Data. Locate in check/weld fixture and inspect liner wall positions Tools: MH14786/1 Checking and welding

fixture MB13432/2 Location clamp ring

(innerwall) MH13775/2 Location calmp ring

(outerwall) MB13434 Check gauge*(innerwall) MH13814 Check gauge (outerwall) Refer to Fig.1 and 3 and Engine Manual TASK 72-41-13-300-094,Repair Scheme FRS5596 Refer to Fig.5 and Material Information Parts: AGS3707 Wire thread insert Refer to Fig.5 and Standard PracticesManual TASK 70-42-13-300-001,Repair Scheme FRS3002. Fit wire thread insertsAGS3707, nominal.unified thread size 6,35mm. (0.250in.)dia - 28 threadsper inch Tools: HC22892 Insert tool 3405528 Tang removal tool HCU5037 Thread gauge Tools: HC21740 Torque check plug HC21743 Torque adapter 1704302 Torquemaster 

# RB.2 1l-=72-9764 Page 10 @Rolls-Royce plcR

R 

### (21) (22)

C.

D. 

### -

~ 

### ~~O~~fl Propulsion System !ff~ 

# SERVICE

**BULLETIN**
Procedure Inspect inserts

Cancel existingpart number and adjacent to it re-identify with new part number by vibro-engraving Supplemantary Information Refer to Fig.5. Ensure inserts are installedat correct depth Existing Renumber UL27659 UL33964 UL23992 UL33964 UL22988 UL33964 Use vibro-engraving equipment Front combustion liner assembliesreworked in accordancewith this Service Bulletin are interchangeablewith existing. Re-install in accordancewith current overhaulprocedure (EngineManual 72-41-00,Assembly and 72-41-13, Installation). Whenever this Service Bulletin number appears in or is added to a Log Book record, then all reference to ServiceBulletins 72-8980 and 72-9122 shall be deleted from this record should they already be present. A record of accomplishment is required.

Aug.20/93 Revision 3 Jan.16/98 

# RB.21**l-72-9764**

**0** Rotts-Royce

plc Page 11

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# n mBOafll Propulsion System !!fk 

# SERVICE

**BULLETIN**

REMOVE INNER AND OUTER WALLS TO iNSTRUCTIONS FIT HEAD SECTION UL36797 TO INSTRUCTIONS. WELD TO INSTRUCTIONS. WELDS ARE GROUP 2. APPLY GRADATED METAL/CERAMIC PLASMA DEPOSIT To SURFACES 

# AB TO INSTRUCTIONS. FOR ALL OTHER PARTICULARS REFER TO INSTRUCTIONS. DIMENSIONS ARE IN MILLIMETRES (INCHES) GEOMETRIC SYM@OLS CONFORM TO IS0 RIIOI-1969

Rework of front combustion liner assemblies - All engines Fig.1
Aug.20/93 0 Rolls-Royce plc RB.2 11-72-9764 Page 12CUT ANI TRM OUTER WA ,Y-- REMOVE EXiSTlffi PLASMA

COATNG TO THIS DlMiNSJON TO INSTRUCTIONS TRIMALLO~NCE

,- REMOVE EXISTING PLASMA COATNG TO THIS DIMENSION TO INSTRUClIO(JS.

TRIM ALLOWANCE

+T iiNr! TRM INNER WALL ASSEMBIY TO THIS DMENSION

TYPICAL SECTION THROUGH COMBUSTION LINER SHOWING WALL AND HEAD SEPARATION.

Rework of front combustion liner assemblies - All engines Fig.2
Aug.20/93 

# RB.2 11-72-9764 Page 13 @Rolls~Royce

plcARGON ARC BUTT WELD 

# I SURFACE

## A8?/I-- AC

CHUTE SHOWN THUS FOR CONVENIENCE. FRONT INNER SECONDARY CHUTE SHOWN THUS FOR NEW UL36

I SURF&E 

## AB

I I i BUTT WELD


### I

TYPICAL SECTION THROUGH COMBUSTION LINER SHOWING ADDITION OF NEW HEAD ASSEMBLY

Rework of front combustion liner assemblies - All engines Fig.3
Aug.20/93 

# RB.2 11-72-9764 Page 14 @ Roils .Royce ptcE m =

c STRUT TD.C\ FRONT OUTER SECONDARY

FRONT INNER SECONDARY CHUTES 1 

# +J 36PLUNGED HOLES EQUALLY SPACED

SECTION 

### AC SHOWING THE ANGULAR POS OF THE INNERAND OUTER WALLS RELATIVE TOTHE HEAD ASSY.

Rework of front combustion liner assemblies- All engines Fig.4
Aug.20/93 

# RB.2 1l-72-9764 Page 15 @Rolls-Royce

plc

## v-AM LENGTH OF ASSEMBLED INSERT / : **INSTALL INSERTS** **IN**

**COMB'LINER HEAD**  SECTION 3/4 TO 1112 PITCH BELOW SURFACE. BREAK OFF TANG AT NOTCH,SEE w 7 ACCOMPLISHMENT INSTRUCTIONS. zi TYPICAL 54 POSITIONS 0 a (COMPRISING 18 GROUPS OF 3). 5 MIN 5.66-1 b 0 2 **(.223) 1**  **\ 2**  **m**

THE INSERT MAY.ERANCES

PROTRUDE /y PROTRUSION MUST BE KEPT EXPOSED THREAD AT THIS PO@ TOA MINIMUM BY INSTALLING IN COMB’ LINER HEAD SECTION TO THE INSERT TOA SMALLER BE DEFORMED TO RETAIN INSERTS. PITCH FIGURE QUOTED, TYPICAL 54 POSITIONS. TYPICAL 36 POSITIONS. SECTiON 

## AR

SECTION 

## AP

SECTION 

## AN

Rework of front combustion liner assemblies - All engines Fig.5
Aug.20/93 

# RB.2 **11-72-9764**
@Rolls

-Royce plc Page 163. Material Information

NOTE: For unit list prices, see supplement to this bulletin. I.P.C. Fig./ New Item Part No. Qty Keyword Old Instructions Mat. Part No. Disposition A. The kit required consists of the following parts: All engines and modules 72-41-13 02262 AGS3707 54 Insert, wire thread **QED** AGS3707 (0.250in. dia)(VU1653) 02274 LX36797 1 Head section assy, UL31133 combustion liner B. Parts to be reworked: All engines and modules 72-41-13 02250 UL33964 1 Liner assy, combustion front - UL27659 UL23992 UL22988 C. New production parts: (4) (l)(3)

(l)(2)

The following parts will be made available as future spares in addition to those listed under A. and B.: None. D. Instruction disposition codes: (1) Old and new parts are feely and fully interchangeable. (2) For rework refer to Fig.1 to 5. (3) Not available as a spare for replenishment purposes. (4) Old part destroyed during rework.

Aug.20/93 

# RB.2 1l-72-9764 Page 17 @Rolls.Royce

plcPATH 1

**e** PATH 2 Head Section (full) Meter panel Head Section (partial) Includes features of S.B.RB211-72-4203 and 72-4429 Includes features of S.B.R.B211-72-5769 a= b= **C=** ***r**
**e =:**  72-4068 Pl LK68669 a.LK68780 b.LK68782 P3 

# I 72-4203 Pl LK68625 a.LK68796 b.N/A P6 I I 72-4429 Pl LK80483 * *

A 72-4578 P5

b.LK68840 Pll 72-4578 ~9 LK69704 a.LK70830 b.LK70829 P13 ---F 72-4578 Pl LK69702 a.LK68839 b.LK68840 Pll

This family tree of combustion Path 1 - Combustion liners for liners authorises two paths: fitment in RB211-524B4-02 and -524B4-D-02 engines which Path 2 - feature cross-key location (S.B.72-5769)

Existing combustion liners at present fitted in RB211-524B-02, -534B-B-02 and -524B3-02 engines which can be fitted in RB211-524B4-02 and -52484-D-02 engines which do not feature cross-key location (S.B.72-5769)

ulellJg

leaq UI PalUlJdc QFamily tree - Combustionfront liner, head section and meter panels FWll-524B engines and modules

Sheet 2 of 6 

# RB.211-72-9764 Page 19 Aug.20/93 0 Rolls -Royce plcJ K 72-5862 Pl LK80428 a.LK81376 b.LK71254P4 c.LK81378 

# ____I72-5862 P3 LK83188 a.LK71252 b.LK71254 c.LK81355

I I
, 1

72-5710 PL LK80439 a.LK81419 b.LK81447P3 c.LK81421 

# 7 72-5824 P3 LK84013 a.LK81622 b.LK81654 c.LK81355 P25 72-5824 Pl LK80521 a.LK81652 b.LK81654 c.LK81378P21 H

72-5824 P4 LK84014 a.LK81622 b.LK81654 c.LK81355P25t 

# I 72-5710 P2 UL12091

72-6235 Pl a.LK81711 b.LK81715 r 72-6235P2 LK84830 

# J-l

Q R S

Family tree - Combustion front liner, head section and meter panels RB211-524B engines and modules

Sheet 3 of 6
Aug.20193 

# RB.2 1l-72-9764 Page 20 @_I Rol Is-Royce plcPrmted m Great Brltaln

S 

## k OQ 

### L 0



### . u3 G, 0 P K Q JR L M T

a. UL14472 P25 72-6430 Pl 1 UL10371 a.LK86909 b.LK86911 P24 

# I
c.LK81685 72-6430 P20 UL16104 a.UL14474 P23

a.UL17602 P13 a.UL17596 P15 b.LK81447 72-6630 Pl ULlllOl a.UL14386 Pl b.LK86911 c.UL14388

-r ’ 72-6630 P3 ULl1098 a.UL17602 Pl:!
L b.LK71254 c.UL17604 72-6630 P4

a.UL17594 P16 / ) l.UL17606 Pl71 la.ULl76; Pl81 

## II I 

## I .X

72-7221 PI UL16078 (a) UL14459 P2 (b) N/A (c> N/A

72-7865 UL16885 

# I 72-7998 UL21441 L I I

Family tree - Combustion front liner, head section and meter panels RB211-524B engines and modules

Sheet 5 of 6
Aug.20/93 

# RB.2 1l-72-9764 Page 22 @ Rol Is-Royce plc

# I Al A2 A3 A4 1

i 72-9122 Pl UL27659 

### I 

## 1 72-8952 P4 72-8952 Pl' UL28972 UL26916

f72-9122 Pl UL28974

1 72-9764 Pl UL33964 A5 A6

Family tree - Combustion front liner, head section and meter panels RB211-524B engines and modules

Sheet 6 of 6
Aug.20/93 

# RB.Zll-72-9764 Page 23 @ RolIs.Royce plcPATH 1

* a= Head Section (full) b = Meter panel C' Head section (partial) *I Includes features of S.B.R8211-72-5769


# I 72-4429 Pl LK84810 I 

# I 72-4578 Pl LK84812

A . .

PATH 2 I

Front combustionliner, head sections and meter panels RB211-524D4-19,-524D4X-19, -52404-B-19, -524D4X-B-19series engines and modules only. This family tree of combustion liners autorises two paths: Path 1 -
Path 2 - Combustion liners for fitment in RB211-524D4-19,-524D4X-19,

-524D4-B-19and -524D4X-B-19 engines which feature cross-key location (S.B.72-5769)and deleted stiffening ring (S.B.72-4972) Existing combustion liners at present fitted in RB211-524B2-19, -524B2-B-19,-524C2-19 and -524C2-B-19which do not feature cross-key location (S.B.72-5769). Family tree - Combustion front liner, head section and meter panels RB211-524D4 engines and modules

Sheet 1 of 5
Aug.20/93 

# RB.211-72-9764 Page 24 @Rolls.Royce plcA

t72-5149 Pl LK80469 1 a.LK81376 K b.LK71254 c.LK81378 P4 I 72-5299 Pl LK83299 1 a.LK81376 J b.LK71254 c.LK81378
72-5862 Pl 1 LK80428 a.LK81376 s b.LK71254 L c.LK81378
72-5824 Pl LK80521 a.LK81652 I b.LK81654 M c.LK81378P21
72-5710 Pl - LK80439 a.LK81419 1 b.LK81447 P3 N c.LK81421

I t a.LK81711 b.LK81715 c.LK81685 P3 

# I 72-6235 P2 LK84830

# LP 0 Family tree - Combustion front liner, RJ3211-524D4

engines Sheet 2 of
Aug.20/93 

# 1 I B

t-l 72-5149 Pl LK74221 a.LK71252 b.LK71254 c.LK81355 P4
72-5299 P16 LK80494 a.LK71252 b.LK71254 c.LK81355
72-5862 P4 LK83186 a.LK71252 b.LK71254 c.LK81355

R S T head sectionand meter panels and modules 5 

# RB.2 11-72-9764 Page 25 @Rolls-Royce plcFamily tree

Aug.20/93 - Combustion frdnt liner, head section and meter panels RBZll-524D4engines andmodules

Sheet 3 of 5 

# RB.2 11-72-9764 Page 26 @Rolls-Royce plcX

72-7865 /IILlI t 72-7998 UL21441

72-8980 Pl 72-8980 P2

uL27109 

### 1 Al 72-8517 UL24898

II A2 A3

Family tree - Combustion front liner,head sectionand meter panels RB211-524D4 engines and modules

Sheet 4 of 5
Aug.20/93 

# RB.211972-9764 Page 27 @ RolIs -Royce **plc**-0 1 5 t a. 3

72-9122 Pl A2 A3 /\ 72-8952 P4 UL28972 1 -A4&G-,&,

72-8952 Pl UL26916

I 72-9122 Pl UL28974


# I 72-9764 Pl UL33964 I

Family tree - Combustion front liner, head section and meter panels RB211-524D4engines and modules

Sheet 5,0f 5
Aug.20/93 

# RB.2 1l-72-9764 Page 28 @Rolls-Royce plc*

* = Ref S.B.RB211-72-6630Pl

I 181 172-85 D Pl

# I

A C DIS ULlllOf

Front combustion liner RB211-524D4-39 and -524134-B-39 series engines and modules only. 

# r- 72-8729 UL22988

-I

Aug.20/93 Family tree - Combustion front liner RB211-524D4 engines and modules

Sheet 1 of 2 r 

# I 72-8980 P2 UL27109 I



# RB.2 11-72-9764 Page 29 @ Rol Is-Royce plc
.F

72-9122 Pl D ( 

### c
72-8952 P4 72-8952 P1 UL28972 UL26916"'&,A,

72-9122 Pl UL28974

Aug.20/93 Family tree - Combustion front liner RB211-524D4 engines and modules

Sheet 2 of 2 

# RB.2 1l-72-9764 Page 30 @Rolls-Royce plc

### - 

# n @~,~~fl Propulsion System !fk 

# SERVICE

SUPPLEMENT - PRICES AND AVAILABILITY ENGINE - COMBUSTION SECTION - IMPROVED PHASE 2 COMBUSTIONLINER WITH STRENGTHENEDHEAD AND IMPROVED HEATSHIELDS - MOD.72-9764
;; $ This is a technicaldocumentnot a quotation; any prices and delivery given are g in good faithwithout engagement. % Alternativeparts may be supplied instead of parts listed. See Material

Informationdisposition instructions. c .- cp f 1. m ModificationKit 

# 5 G c ._ u 2 c ‘C a 2.

R R R 3.

R R R R R R R R R R R R R R Not applicable. Parts supplied as single line items. Future spares will be supplied to this Service Bulletin standardwhen existing stocks of parts have been used up; approximatelyDecember 1994. New production or reworkedparts
Part No. QtY AGS3707 54 UL33964 1 UL36797 1 Tools Unit Price U.S. Dollars 1.10 231,003.OO 177,078.OO
Delivery can commence in 20 weeks from receipt of order. Tool No. Unit Price U.S. Dollars MH13402 1043.00 MH13403/2 2630.00 MH13406/1 1764.00 MH13432/2 2328.00 MH13434 520.00 MH13775/2 3055.00 MH13814 467.00 MH14786/1 25472.00 HC22892 395.00 3405528 48.20 HCU5037 172.00 HC21740 180.00 HC21743 179.00 1704302 91.10

Aug.20193 Revision 1 Jan.16/98 RB.2 1 I-72-9764 0 Rolls-Royce plc SupplementPage 1 of 1C ._ co Y 

### G 

# 5 6 c .- 

# x E ‘C a 

### - 

# R iB$JJfl Propulsion System !f!!a 

# SERVICE

**BULLETIN**

MODIFICATION ACCEPTANCE
To: Service Modification Engineer The information on this sheet is given RB211 Propulsion System in good faith based upon the latest Rolls-Royce plc information known to the supplying party, P.O. Box 31 no warranty or representation is given Derby DE24 8BJ concerning such information which must England not be taken as establisning any contractual or other commitment on the part of either party. RB211 Service Bulletin 72-9764 - ENGINE - COMBUSTION COMBUSTION LINER WITH STRENGTHENED HEAD AND IMPROVED revised on Jan.16/98. SECTION - IMPROVED PHASE 2 HEATSHIELDS has been
The Rolls-Royce Recommendation for this Service Bulletin is: Lockheed L-1011 RB211-524 ; RECOMMENDED (3) Boeing 747 RB211-524 ) Boeing 767 RB211-524H-36 MANDATORY CUSTOMER POLICY Is the subject modification standard acceptable for delivery as spares to support equipment ,.....*......*....................... YES/NO (if 'NO' immediate discussion with Rolls-Royce is essential) Is the customers fitment policy commensurate with that implied by the Rolls-Royce recommendation .......................... YES/NO (if 'NO' what policy does the customer intend to follow and from when?) Policy ........................................................................

............................................................................... Date ............................ Signed .......................... Date ........................................ on behalf of ............................... (airline)

Revised 

# RB.211-72-9764 0 **Rolls-Royce** plc Modification Acceptance