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Copyright (2019) General Electric Company, U.S.A.
TRANSMITTAL INFORMATION
REVISION 6 TO SERVICE BULLETIN 72-0315
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, -1B64/P1, -1B64/P2, -1B67, -1B67/P1, -1B67/P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, -1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -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 outer liner P/N 2255M81G08 is affected by this Service Bulletin.
B.Description
This Service Bulletin releases a new outer liner P/N 2255M81G10.
Deleted.
Also, this Service Bulletin introduces an equivalent reworked outer liner P/N 2257M50G02 for installation in the combustion chamber assembly P/N 2258M80G08 or P/N 2258M80G13. These configurations contain the new shaped multi-hole cooling pattern and advanced thermal barrier coating applied to the flow path surfaces.
C.Compliance
Category 7
GE recommends that you do this Service Bulletin at customer's convenience/option.
Impact E
This recommendation is to improve the cost of ownership, reduce maintenance requirements or is a product improvement.
NOTE:
This Service Bulletin can be accomplished in shop.
D.Concurrent Requirements
None.
E.Reason
(1)Objective:
To introduce a new part and improve reliability for limited customers due to hardware availability.
(2)Condition:
The current outer liner does not meet time on wing capability requirements due to thermal barrier coating (TBC) surface temperatures being above the design expectation. Engines in service develop thermal barrier coating spallation that results in early cracking which leads to early engine 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.
(4)Improvement:
The improvement to the outer liner is achieved through the application of advanced high yttrium TBC in order to reduce surface temperatures and increase coating temperature capability.
(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 0.895 lb (0.406 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 72-0302, ENGINE - Combustion Chamber Assembly (72-42-00) - Introduction of New Inner Liner for GEnx-1B/P2 Engines
GEnx-1B S/B 72-0110, ENGINE - Combustion Chamber Assembly (72-42-00) - Introduction of Reworked Inner and Outer Liners with T800 Coated Aft Seal Leg
Repair Document (RD) 124-1344 (P1 or higher), Combustion Chamber Assembly - Combustion Chamber Outer 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 combustion chamber assembly change from P/N 2258M80G10 to P/N 2258M80G13 is qualified interchangeable. The combustion chamber assembly P/N 2258M80G10 can be reworked to a P/N 2258M80G13 by the replacement of the current outer liner P/N 2255M81G08 with the new outer liner P/N 2255M81G10 or reworked outer liner P/N 2257M50G02 hardware defined herein provided it also contains the new inner liner P/N 2255M82G09 or P/N 2735M20G01 introduced by the GEnx-1B S/B 72-0302. The existing outer liner P/N 2255M81G08 or P/N 2541M17G04 introduced by the GEnx-1B the S/B 72-0110 are permitted as an alternate to the field for the combustion chamber assembly P/N 2258M80G08.
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
 
2255M81G10
(1)
Liner, Outer
Past configuration. Refer to the GEnx-1B IPC for latest part number.
(-)
--
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)
Combustion Chamber Assembly
Past configuration. Refer to the GEnx-1B IPC for latest part number.
(-)
--
NOTE:
Prices are provided for planning purposes and are subject to change.
(3)Consumables:
None.
B.Industry Support Information
Contact your Customer Support Manager (CSM).
C.Configuration Chart
 
New Part Number
Qty/ Eng
Part Name
Old Part Number/ IPC Location
Qty/ Eng
Op Code
Chg/ Sprt Code
 
(PRODUCTION)
 
2376M54G08
(X)
Combustor Diffuser Assembly
2376M54G08
(X)
RM
-/-
 
.2258M80G13
01-093B, 72-41-00
(1)
Combustion Chamber Assembly
(SIN 12400)
.2258M80G10
01-093A, 72-41-00
(1)
RE/RW/RI
5/A
 
..2255M81G10
01-101E, 72-42-00
(1)
Liner, Outer
(SIN 12400 2)
..2255M81G08
01-101A, 72-42-00
(1)
RE
5/A
 
(FIELD)
 
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)
RE/RW/RI
5/A
 
..2255M81G10
01-101E, 72-42-00
(1)
Liner, Outer
(SIN 12400 2)
..2255M81G08
01-101A, 72-42-00
(1)
RE/RW/RI
5/A
 
..2255M81G08
01-101F, 72-42-00
(ALT)
Liner, Outer
(SIN 12400 2)
--
(-)
AD
5/A
 
..2257M50G02
01-101G, 72-42-00
(ALT)
Liner, Outer
(SIN 12400 2)
..2541M17G04
01-101C, 72-42-00
(ALT)
RE/RW/RI
5/A
 
2376M54G01/
G02/G04/G06
(X)
Combustor Diffuser Assembly
2376M54G01/
G02/G04/G06
(X)
RM
-/-
 
.2258M80G08
01-091A, 72-41-00
(1)
Combustion Chamber Assembly
(SIN 12400)
.2258M80G08
01-091A, 72-41-00
(1)
RM
-/-
 
..2255M81G10
01-101E, 72-42-00
(1)
Liner, Outer
(SIN 12400 2)
..2255M81G08
01-101A, 72-42-00
(1)
RE/RW/RI
5/A
 
..2255M81G08
01-101F, 72-42-00
(ALT)
Liner, Outer
(SIN 12400 2)
--
(-)
AD
5/A
 
..2257M50G02
01-101G, 72-42-00
(ALT)
Liner, Outer
(SIN 12400 2)
..2541M17G04
01-101C, 72-42-00
(ALT)
RE/RW/RI
5/A
Operation Codes
AD=Add
RE=Replace
RI=Reidentify
RM=Remains
RW=Rework
Change Codes
5=Qualified interchangeability. Refer to paragraph 1.K., Interchangeability.
Support Codes
A=Old parts will no longer be supplied.
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 (Figure 1). Refer to the GEnx-1B CIR, 72-00-42, REPAIR 001.
(2)Replace the outer liner. 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 License Agreement is also required. Information concerning a License Agreement is available from:
 
ATTN.: Manager, 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 outer liner P/N 2541M17G04 to P/N 2257M50G02. Refer to RD 124-1344.
(3)Assemble the combustion chamber assembly (Figure 1). Refer to the GEnx-1B CIR, 72-00-42, REPAIR 002.
(4)If necessary, reidentify the combustion chamber assembly (Figure 1). Refer to the GEnx-1B CIR, 72-00-42, REPAIR 002.
B.Deleted
Combustion Chamber Assembly Location
Figure 1