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Copyright (2016) General Electric Company, U.S.A.
TRANSMITTAL INFORMATION
REVISION 2 TO SERVICE BULLETIN 72-0089
Revision 2 is issued to update paragraphs 1., PLANNING INFORMATION, 2., MATERIAL INFORMATION, and 4., APPENDIX A.
Revision 1 was issued May 10, 2013. The original was issued June 04, 2012. Revision bars in the left margin identify changes.
1.PLANNING INFORMATION
A.Effectivity
* * * FOR GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1
This Service Bulletin is applicable to all GEnx-1B engines.
This Service Bulletin has been introduced in production to these GEnx-1B engines:
•
GEnx-1B engines, serial numbers 956-158 and up.
These serial numbers are the best available data.
 Refer to paragraph 4., APPENDIX A for GEnx-1B Engine Illustrated Parts Catalog (EIPC) model apply coding.
B.Description
This Service Bulletin releases a new HPT rotor assembly P/N 2305M57G08 which incorporates a new HPT stage 1 blade P/N 2305M26P08.
C.Compliance
Category 7
GE recommends that you do this Service Bulletin at customer's convenience.
NOTE:
This Service Bulletin can be accomplished in shop.
D.Concurrent Requirements
None.
E.Reason
(1)Objective:
To introduce new parts.
(2)Condition:
 The GEnx-1B, with 75,000 lb thrust capability incorporates a new HPT stage 1 blade P/N 2305M26P08, which has additional air plasma spray (APS) thermal barrier coating (TBC) on the convex airfoil. This new blade is part of the HPT rotor assembly P/N 2305M57G08. To enable GEnx-1B engines to be rated at 75,000 lb thrust, the HPT rotor assembly P/N 2305M57G08 must be incorporated.
 Additionally, this Service Bulletin allows the use of HPT stage 2 blades P/N 2305M35G06 and P/N 2305M35G07 with TBC on the airfoil, or HPT stage 2 blades P/N 2305M35G05 and P/N 2305M35G08 without TBC on the airfoil.
(3)Cause:
Due to the more severe operating conditions that the HPT stage 1 blade P/N 2305M26P08 is exposed at 75,000 lb thrust, the additional patch of TBC is required to reduce metal temperature and ensure that the blade has sufficient creep rupture capability.
(4)Improvement:
The new HPT stage 1 blade P/N 2305M26P08 is required for 75,000 lb of thrust operation. The new HPT stage 1 blade P/N 2305M26P08 on engines rated below 75,000 lb of thrust will increase the robustness of the blade and make the HPT rotor assembly the same with the 75,000 lb of thrust engine HPT assembly. Also, this document lets the use of HPT stage 2 blade with or without TBC, which are both certified on the GEnx-1B engine to reduce spare parts inventory for customers.
(5)Substantiation:
Substantiation is by analysis and comparative analysis.

F.Approval
This Service Bulletin has been reviewed by the FAA and the repair(s) and modification(s) herein comply with the applicable Federal Aviation Regulations and are FAA 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
Weight and balance are not changed.
I.References (Use the latest version of this document)
GEK 112864, GEnx-1B Engine Illustrated Parts Catalog (EIPC)
NOTE:
The reference documents listed below are for the engine manufacturer's internal use only:
 
CID: 573202, 573899
 
BPP: 11-72-53-03, 12-72-53-02
J.Publication Affected
GEK 112864, GEnx-1B Engine Illustrated Parts Catalog (EIPC)
K.Interchangeability
The new HPT stage 1 blade P/N 2305M26P08 and the old HPT stage 1 blade P/N 2305M26P06 must be introduced in complete engine sets in order to upgrade to PIP1 configuration at a later date.
The mixture of the proposed and superseded hardware in the field is permitted for the 70.000 lb thrust power and below applications.
There is no restriction on the mixing of stage 2 blade part numbers within the same HPT rotor.
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
 
2305M26P08
(62)
Blade, HPT Stage 1
23,140.00
(1)
5
NOTE:
Prices are provided for planning purposes and are subject to change.
(2)Other Spare Parts:
None.
(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
 
2376M20G05/G06
(X)
Propulsor Module Assembly
2376M20G05/G06
(X)
RM
-/-
 
.2305M57G08034-020C, 72-00-02
(1)
Rotor Assembly, HPT (SIN15000)
.2305M57G04034-020B, 72-00-02
(1)
RE
5/E
 
..2305M26P0801-211, 72-53-00
(62)
Blade, HPT
(Stage 1) (SIN 150A0)
..2305M26P0601-210, 72-53-00
(62)
RE
5/E
 
.2305M57G08
(X)
Rotor Assembly, HPT
.2305M57G08
(X)
RM
-/-
 
..2305M35G0501-112, 72-53-00
(62)
Blade, Stage 2 (SIN150B0)
..2305M35G0501-112, 72-53-00
(62)
RM
-/-
 
..2305M35G0801-112A, 72-53-00
(ALT)
Blade, Stage 2 (SIN150B0)
..2305M35G0801-112A, 72-53-00
(ALT)
RM
-/-
 
..2305M35G0601-113, 72-53-00
(62)
Blade, Stage 2 (SIN 150B0)
--
(-)
AD
5/-
 
..2305M35G0701-113A, 72-53-00
(ALT)
Blade, Stage 2 (SIN 150B0)
--
(-)
AD
5/-
 
Operation Codes
AD=Add
RE=Replace
RM=Remains
Change Code
5=Qualified interchangeability. Refer to paragraph 1.K., Interchangeability.
Support Code
E=Old parts will be supplied, and can be used at other engine locations.
D.Parts Disposition
None.
E.Tooling - Price and Availability
None.
3.ACCOMPLISHMENT INSTRUCTIONS
A.General
(1)Removal and installation instructions for the HPT blades have not changed. Refer to the GEnx-1B EM, 72-53-00, DISASSEMBLY 001 and ASSEMBLY 001.
(2)The removal and installation instructions for the HPT stage 2 blades have not changed. Refer to the GEnx-1B EM, 72-50-00, DISASSEMBLY 001 and ASSEMBLY 001.
4.APPENDIX A - Model Applicability
 
Part Number
IPC Code Model Apply
 
2305M57G04
AA
 
2305M57G08
AA and BB
 
2305M26P06
AA
 
2305M26P08
AA and BB