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Copyright (2016) General Electric Company, U.S.A.
TRANSMITTAL INFORMATION
REVISION 1 TO SERVICE BULLETIN 72-0293
Revision 1 is issued to change the original issue of this Service Bulletin from limited distribution to full release. The original was issued April 20, 2016.
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 is applicable to these GEnx-1B engines:
•
GEnx-1B engines, serial numbers 956-102 through 956-738.
This Service Bulletin has been introduced in production to these GEnx-1B engines:
•
GEnx-1B engines, serial numbers 956-739 and up.
These serial numbers are the best available data.
The high pressure turbine (HPT) blades (HPT stage 1 blades) P/N 2305M26P06, P/N 2305M26P08, P/N 2305M26P09, P/N 2305M26P10, P/N 2383M53P02, and P/N 2383M53P05 are affected by this Service Bulletin.
B.Description
This Service Bulletin releases the new HPT stage 1 blades P/N 2305M26P11 and P/N 2383M53P08.
C.Compliance
Category 3
GE recommends that you do this Service Bulletin at the next shop visit of the engine if the HPT case/combustor diffuser nozzle (CDN) case is separated.
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 72-0294 when you do this Service Bulletin.
 
LIFE LIMIT
 
The mandatory inspection requirements for the new HPT stage 1 blades have been added to the GEnx-1B Engine Manual, Section 05-21-00 by Temporary Revision (TR) 05-0061. Refer to the GEnx-1B EM for the mandatory inspection requirements of these parts.
E.Reason
(1)Objective:
To introduce new parts, improve reliability, and reduce significant events.
(2)Condition:
The old HPT stage 1 blades have experienced thermal distress and cracking on the concave and convex areas of the airfoil. This convex cracking has resulted in two in-flight shut down (IFSD) events.
(3)Cause:
The higher operating temperatures and stresses than those which were originally predicted led to the thermal distress and cracking.
(4)Improvement:
The new HPT stage 1 blades have additional cooling holes to reduce the operating temperature of the blade and additional wall thickness on the convex side to reduce the operating stresses of the blade.
(5)Substantiation:
Substantiation is by comparative analysis, analysis, and test.
F.Approval
The data contained in this Service Bulletin has been reviewed by the appropriate governmental authority 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 0.40 lb (0.18 kg).
I.References (Use the latest version of these documents)
GEnx-1B, Boeing 787 Aircraft Maintenance Manual (AMM)
GEK 112851, GEnx-1B Engine Manual (EM)
GEK 112864, GEnx-1B Engine Illustrated Parts Catalog (EIPC)
GEnx-1B S/B 72-0294, ENGINE - High Pressure Turbine Stage 1 Nozzle Assembly (72-51-00) - Introduction of New HPT Support Nozzle
NOTE:
The reference documents listed below are for the engine manufacturer's internal use only:
CID: 573202, 575448, 575643, 575643-1
BPP: 15-72-53-41434
J.Publications Affected
GEnx-1B, Boeing 787 Aircraft Maintenance Manual (AMM)
GEK 112851, GEnx-1B Engine Manual (EM)
GEK 112864, GEnx-1B Engine Illustrated Parts Catalog (EIPC)
K.Interchangeability
Qualified interchangeability.
The HPT stage 1 blades P/N 2305M26P11 and P/N 2383M53P08 must be installed as full sets, and must be installed in an engine which has incorporated a higher flowing HPT support nozzle reference GEnx-1B S/B 72-0294.
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
 
2305M27P01
(62)
Damper, Stage 1
40.50
(1)
5
 
AND
 
2305M26P11
(62)
Blade, HPT
23,140.00
(1)
Quote
 
OR
 
2383M53P08
(62)
Blade, HPT
23,140.00
(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
 
2305M57G09
(1)
Rotor Assembly, HPT
Quote
(-)
Quote
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
 
GEnx-1B/P2 PRODUCTION
 
2447M20G04
(X)
Propulsor Module Assembly
2447M20G04
S/B 72-0290
(X)
RM
-/-
 
.2305M57G09
34-021A, 72-00-02
(1)
Rotor Assembly, HPT
(SIN 15000)
.2305M57G06
34-021, 72-00-02
(1)
RW
5/A
 
..2383M53P08
02-210B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2383M53P05
02-210A, 72-53-00
(62)
RE
5/A
 
 
GEnx-1B/P2 FIELD
 
2447M20G01/
G02/G03
(X)
Propulsor Module Assembly
2447M20G01/
G02/G03
(X)
RM
-/-
 
2447M20G04
(X)
Propulsor Module Assembly
2447M20G04
S/B 72-0290
(X)
RM
-/-
 
.2305M57G06
34-021, 72-00-02
(1)
Rotor Assembly, HPT
(SIN 15000)
.2305M57G06
34-021, 72-00-02
(1)
RM*
-/-
 
..2383M53P08
02-210B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2383M53P05
02-210A, 72-53-00
(62)
RE
5/A
 
..2383M53P08
02-210B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2383M53P02
02-210, 72-53-00
(62)
RE
5/A
 
 
GEnx-1B/EIS FIELD
 
2376M20G05/
G06/G07
(X)
Propulsor Module Assembly
2376M20G05/
G06/G07
(X)
RM
-/-
 
.2305M57G08
34-020C, 72-00-02
(1)
Rotor Assembly, HPT
(SIN 15000)
.2305M57G08
34-020C, 72-00-02
(1)
RM*
-/-
 
..2305M26P11
01-211B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2305M26P10
01-211A, 72-53-00
(62)
RE
5/A
 
..2305M26P11
S/B 72-0293
(62)
Blade, HPT
(SIN 150A0)
..2305M26P08
01-211, 72-53-00
(62)
RE
5/A
 
.2305M57G04
34-290A, 72-00-02
(1)
Rotor Assembly, HPT
(SIN 15000)
.2305M57G04
34-290A, 72-00-02
(1)
RM*
-/-
 
..2305M26P11
01-211B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2305M26P09
01-210A, 72-53-00
(62)
RE
5/A
 
..2305M26P11
S/B 72-0293
(62)
Blade, HPT
(SIN 150A0)
..2305M26P06
01-210, 72-53-00
(62)
RE
5/A
 
.2305M57G05
34-290B, 72-00-02
(1)
Rotor Assembly, HPT
(SIN 15000)
.2305M57G05
34-290B, 72-00-02
(1)
RM*
-/-
 
..2305M26P11
01-211B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2305M26P09
01-210A, 72-53-00
(62)
RE
5/A
 
..2305M26P11
01-211B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2305M26P06
01-210, 72-53-00
(62)
RE
5/A
 
GEnx-1B/P1 FIELD
 
2376M20G08/
G09
(X)
Propulsor Module Assembly
2376M20G08/
G09
(X)
RM
-/-
 
.2305M57G08
34-020C, 72-00-02
(1)
Rotor Assembly, HPT
(SIN 15000)
.2305M57G08
34-020C, 72-00-02
(1)
RM*
-/-
 
..2305M26P11
01-211B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2305M26P10
01-211A, 72-53-00
(62)
RE
5/A
 
..2305M26P11
01-211B, 72-53-00
(62)
Blade, HPT
(SIN 150A0)
..2305M26P08
01-211, 72-53-00
(62)
RE
5/A
NOTE:
*These HPT rotor assemblies are assembled with new HPT stage 1 blades part numbers.
Operation Codes
RE=Replace
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
Discard old parts.
E.Tooling - Price and Availability
None.
3.ACCOMPLISHMENT INSTRUCTIONS
A.General
(1)Removal and installation instructions of the HPT stage 1 blade (1, Figure 1) have not changed. Refer to the GEnx-1B EM, 72-53-00, DISASSEMBLY 001 (CONFIGURATION 01 or CONFIGURATION 02) and ASSEMBLY 001 (CONFIGURATION 01 or CONFIGURATION 02).
HPT Stage 1 Blade Location
Figure 1