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Copyright (2020) General Electric Company, U.S.A.
TRANSMITTAL INFORMATION
REVISION 6 TO SERVICE BULLETIN 72-0302
Revision 6 is issued to update paragraph 2., MATERIAL INFORMATION.
Revision 5 was issued January 24, 2017. Revision 4 was issued November 17, 2016. Revision 3 was issued September 20, 2016. Revision 2 was issued July 27, 2016. Revision 1 was issued May 31, 2016. The original was issued May 09, 2016. Revision bars in the left margin identify changes.
NOTE:
The original, Revision 1, Revision 2, Revision 3, and Revision 4 of this Service Bulletin had limited distribution. You may not have received the original, Revision 1, Revision 2, Revision 3, and/or Revision 4 of this Service Bulletin.
1.PLANNING INFORMATION
A.Effectivity
* * * FOR GEnx-1B64/P2, -1B67/P2, -1B70/P2, -1B70/75/P2, -1B70C/P2, -1B74/75/P2
This Service Bulletin has been introduced in production to these GEnx-1B engines:
•
GEnx-1B engines, serial numbers 956-794 and up.
These serial numbers are the best available data.
Deleted.
The inner liners P/N 2255M82G06, P/N 2541M22G01, and the combustion chamber assembly P/N 2258M80G10 are affected by this Service Bulletin.
B.Description
This Service Bulletin introduces a new inner liner P/N 2255M82G09 and a new combustion chamber assembly P/N 2258M80G13.
This Service Bulletin also introduces an equivalent repaired inner liner P/N 2735M20G01 to be installed in the combustion chamber assembly P/N 2258M80G13. These configurations contain the new shaped multi-hole cooling pattern and advanced thermal barrier coating applied to the flow path surfaces.
Deleted.
C.Compliance
Category 6
GE recommends that you do this Service Bulletin when the combustor is routed for repair.
Impact E
This recommendation is to improve the cost of ownership, reduce maintenance requirements or is a production improvement.
NOTE:
This Service Bulletin can be accomplished in shop.
This Service Bulletin is offered to improve the reliability or performance of your GE product, or to help prevent the occurrence of the event or condition described in this Service Bulletin. If the operator elects not to participate in the bulletin, that decision will be taken into consideration by GE in evaluating future product performance issues that may arise in the operators fleet.
D.Concurrent Requirements
Do GEnx-1B S/B 72-0293 when or before you do this Service Bulletin.
E.Reason
(1)Objective:
To introduce a new part and improve reliability for limited customers due to hardware availability.
(2)Condition:
The current inner liner does not meet time on-wing expectation due to cracking. Engines in service develop thermal barrier coating (TBC) spallation which leads to early cracking and removal.
(3)Cause:
The cause is due to TBC surface temperatures being above the material bond strength, causing the coating to spall. This condition drives the exposed metal temperatures higher than expected, causing cracks to initiate and propagate in low-cycle fatigue (LCF). The GEnx-1B/P2 combustors spall/crack at a greater rate than entry-into-service (EIS) or PIP1 combustors.
(4)Improvement:
The changes involve improved cooling to the forward nugget and multi-hole region of the inner liner and application of an advanced TBC to the inner liner. These changes will reduce cracking rate on the inner liner, a condition found in service with the current combustor inner liner configuration.
The improvement is achieved through geometry changes, reallocation of cooling air within the inner liner, and the new TBC to reduce coating surface temperatures.
(5)Substantiation:
Substantiation is by analysis and comparative analysis.
F.Approval
The data contained in this Service Bulletin has been reviewed by the FAA or authorized entity representing the FAA and the repair(s) and modification(s) herein comply with the applicable Aviation Regulations and are APPROVED for installation in the model(s) listed in this Service Bulletin.
G.Manpower
No additional man-hours are required to comply with this Service Bulletin.
H.Weight and Balance
The complete compliance with this Service Bulletin increases weight by 0.573 lb (0.260 kg).
I.References (Use the latest version of these documents)
GEK 112862, GEnx-1B Cleaning, Inspection, and Repair Manual (CIR)
GEK 112864, GEnx-1B Engine Illustrated Parts Catalog (EIPC)
GEnx-1B S/B 72-0293, ENGINE - HPT Rotor Assembly (72-53-00) - Introduction of New HPT Stage 1 Blades
GEnx-1B S/B 72-0297, ENGINE - Combustor Diffuser Assembly (72-41-00) - Introduction of Combustion Chamber Assembly P/N 2258M80G10 with Improved Durability Combustor Mixer and Outer Retainer
Repair Document (RD) 124-1340 (P1 or higher), Combustion Chamber Assembly - Combustion Chamber Inner Liner - Alteration - Shaped Multi-hole Liner Panel Weld Replacement with Advanced Hi-Y Thermal Barrier Coating
NOTE:
The reference documents listed below are for the engine manufacturer's internal use only:
CID: 575677, 575804
BPP: 15-72-41-29904
J.Publications Affected
GEK 112862, GEnx-1B Cleaning, Inspection, and Repair Manual (CIR)
GEK 112864, GEnx-1B Engine Illustrated Parts Catalog (EIPC)
K.Interchangeability
Qualified interchangeability.
The new combustion chamber assembly P/N 2258M80G10 that gets the new inner liner P/N 2255M82G09 or the repaired inner liner P/N 2735M20G01 will be reidentified with P/N 2258M80G13, provided it also gets the shaped multihole for the outer liner P/N 2255M81G08 or P/N 2255M81G10 and new parts, radial mixer and outer retainer, post-GEnx-1B S/B 72-0297 as follows:
•
Radial mixers P/N 2647M53G01 and P/N 2647M54G01, and outer retainer P/N 2675M03P01.
L.Software Accomplishment Summary
Not applicable.
2.MATERIAL INFORMATION
A.Material - Price and Availability
(1)Parts necessary to do this Service Bulletin:
 
Part Number
Qty/ Eng
Part Name
Unit ($) Price
Pkg Qty
Lead Time Days
 
2255M82G09
(1)
Liner, Inner
254,300.00
(1)
Quote
NOTE:
Prices are provided for planning purposes and are subject to change.
(2)Other Spare Parts:
 
Part Number
Qty/ Eng
Part Name
Unit ($) Price
Pkg Qty
Lead Time Days
 
2258M80G13
(1)
Assembly, Combustion Chamber
Quote
(1)
Quote
NOTE:
Prices are provided for planning purposes and are subject to change.
(3)Consumables:
None.
B.Industry Support Information
 None.
C.Configuration Chart
 
New Part Number
Qty/ Eng
Part Name
Old Part Number/ IPC Location
Qty/ Eng
Op Code
Chg/ Sprt Code
 
2376M54G03/
G05/G07
(X)
Combustor Diffuser Assembly
2376M54G03/
G05/G07
(X)
RM
-/-
 
.2258M80G13
01-093B, 72-41-00
(1)
Combustion Chamber Assembly
(SIN 12400)
.2258M80G10
01-093A, 72-41-00
(1)
RW/RI
5/A
 
..2255M82G09
01-111B, 72-42-00
(1)
Liner, Inner
(SIN 12400 3)
..2255M82G06
01-111, 72-42-00
(1)
RE/RW/RI
5/B
 
..2735M20G01
01-111C, 72-42-00
(1)
Liner, Inner
(SIN 12400 3)
..2541M22G01
01-111A, 72-42-00
(ALT)
RW/RI/QTC
5/B
Operation Codes
RE=Replace
RI=Reidentify
RM=Remains
RW=Rework
QTC=Quantity Change
Change Codes
5=Qualified interchangeability. Refer to paragraph 1.K., Interchangeability.
Support Codes
A=Old parts will no longer be supplied. B=Old parts will be supplied until all old parts are sold.
D.Parts Disposition
Use serviceable old parts for engines that have not changed.
E.Tooling - Price and Availability
None.
3.ACCOMPLISHMENT INSTRUCTIONS
A.General
(1)Disassemble the combustion chamber assembly (1, Figure 1). Refer to the GEnx-1B CIR, 72-00-42, REPAIR 001.
(2)Replace the inner liner (2, Figure 1). Refer to the GEnx-1B CIR, 72-00-42, REPAIR 002 for the permitted inner liner to assemble and do as follows:
 
NOTICE
 
APPROVAL OF REWORK SOURCES
 
The repair referred to below contains complex processes that could affect engine reliability and/or performance. Therefore it is necessary to substantiate the ability and adequacy of a repair source to successfully accomplish the repair. A Technical License Agreement is also required. Information concerning a Technical License Agreement is available from:
 
ATTN.: Manager, Technical Licensing
GE Aviation
One Neumann Way, M/D RM100
Cincinnati, Ohio 45215-6301
U.S.A.
 
After the repair source has obtained a License Agreement, the Repair Document and the Repair Source Substantiation requirements may be obtained from:
 
ATTN.: Repair Substantiation
GE Aviation
One Neumann Way, M/D S171
Cincinnati, Ohio 45215-6301
U.S.A.
(a)If necessary, rework the inner liner P/N 2541M22G01 to P/N 2735M20G01. Refer to RD 124-1340.
(3)Assemble the combustion chamber assembly (1, Figure 1). Refer to the GEnx-1B CIR, 72-00-42, REPAIR 002.
(4)Reidentify the combustion chamber assembly (1, Figure 1). Refer to the GEnx-1B CIR, 72-00-42, REPAIR 002.
B.Deleted
Inner Liner Location
Figure 1