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CF34-8C Service Bulletins (SBs) SB 72-A0225 R03 ENGINE - Fan Rotor Assembly (72-21-00) - Introduction of Fan Blade Bushing Repair Date Printed:
2016/12/19 GE PROPRIETARY INFORMATION - Not to be used, disclosed to others or reproduced without the express written consent of GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG authorization, is strictly prohibited.
Page 1 of 5 CF34-8C ALERT SERVICE BULLETIN - 72- A0225 R03 Revised:12/09/2016 SB 72-A0225 R03 ENGINE - FAN ROTOR ASSEMBLY (72-21-00) -
INTRODUCTION OF FAN BLADE BUSHING REPAIR Issued:
11/05/2010
GE PROPRIETARY INFORMATION The information contained in this document is GE proprietary information and is disclosed in confidence. It is the property of GE and shall not be used, disclosed to others or reproduced without the express written consent of GE, including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of any repairs, modifications, spare parts, designs, or configuration changes or to obtain FAA or any other government or regulatory approval to do so. If consent is given for reproduction in whole or in part, this notice and the notice set forth on each page of this document shall appear in any such reproduction in whole or in part.
This technical data is considered EAR controlled pursuant to 15 CFR Parts 730-774 respectively. Transfer of this data by any means to a Non-US Person, whether in the United States or abroad, without the proper U.S. Government authorization (e.g., License, exemption, NLR, etc.), is strictly prohibited.
Copyright (2016) General Electric Company, U.S.A.
TRANSMITTAL INFORMATION REVISION 3 TO SERVICE BULLETIN 72-0225 Revision 3 is issued to update paragraphs 1.I., and 3., References ACCOMPLISHMENT INSTRUCTIONS.
Revision 2 was issued June 15, 2016. Revision 1 was issued April 09, 2012. The original was issued November 05, 2010. Revision bars in the left margin identify changes.
1. PLANNING INFORMATION A. Effectivity * * * CF34-8C1 * * * CF34-8C5, -8C5B1, -8C5A1, -8C5A2, -8C5A3 * * * CF34-8C5/M, -8C5B1/M, -8C5A1/M, -8C5A2/M * * * CF34-8C5/B, -8C5B1/B, -8C5A1/B, -8C5A2/B, -8C5A3/B This Service Bulletin is applicable to all CF34-8C engines.
There is no production introduction point for this hardware.
The fan blades P/N are affected by this Service4114T15P02 Bulletin.
B. Description This Service Bulletin introduces a fan blade bushing repair by a controlled cold expansion process, approved by GE Aviation, that
CF34-8C Service Bulletins (SBs) SB 72-A0225 R03 ENGINE - Fan Rotor Assembly (72-21-00) - Introduction of Fan Blade Bushing Repair Date Printed:
2016/12/19 GE PROPRIETARY INFORMATION - Not to be used, disclosed to others or reproduced without the express written consent of GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG authorization, is strictly prohibited.
Page 2 of 5 extends the allowable fan blade operation by an additional 28,000 engine cycles from the time of the repair.
C. Compliance Category 2 GE recommends that you do this Service Bulletin before the fan blades accumulate 41,000 cycles since new (CSN).
NOTE:This Service Bulletin can be accomplished on wing or in shop.
NOTE:CF34-8C S/B is no longer required after completing this Service72-0137 Bulletin.
D. Concurrent Requirements Do CF34-8C S/B when you do this Service Bulletin.72-0227 E. Reason
(1) Objective:
To introduce a repair procedure for the pin holes of the fan blade bushing.
The repair will allow the reuse of the fan blade(s) for an additional 28,000 maximum engine cycles of service limit from the time of the repair.
An unbushed fan blade can be repaired anytime up to the service time limit.
The fan blade(s) can also be repaired if the pin holes are found to be worn up to the maximum repairable limit and within the allowable service limit of the fan blade(s). After the reworked fan blade(s) accumulates 28,000 cycles, it needs to be removed and discarded.
(2) Condition:
On the issue date of this bulletin, a repair does not currently exist for fan blades that have reached the maximum service time limit or pin hole wear limits. Once the fan blade(s) allowable service limit is reached, the current requirement is that they be either scrapped or continue in service with the ECI program as detailed in CF34-8C S/B and CF34-8C Engine72-0137 Maintenance Program, Chapter 05-31-00. Similarly, if the pin hole serviceable wear limits are reached, the current requirement is to scrap the fan blade(s).
(3) Cause:
Fan blades that have reached the maximum allowable service limit, per CF34-8C S/B have been required to undergo ECI of pin holes every72-0137 1,500 to 3,000 cycles.
(4) Improvement:
The fan blade bushing repair extends the allowable fan blade operating limits by an additional 28,000 engine cycles from the time of the bushing repair. ECI of the fan blade pinholes per CF34-8C S/B is no longer72-0137 required after completing the fan blade bushing repair.
(5) Substantiation:
Substantiation is by analysis and test.
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, if accomplished at an approved repair facility.
H. Weight and Balance Weight and balance are not changed.
I. References (Use the latest version of these documents) GEK 9250, Commercial Engine Standard Practices Manual (SPM) GEK 105091, CF34-8C Engine Manual (EM) GEK 105092, CF34-8C Illustrated Parts Catalog (IPC)
CF34-8C Service Bulletins (SBs) SB 72-A0225 R03 ENGINE - Fan Rotor Assembly (72-21-00) - Introduction of Fan Blade Bushing Repair Date Printed:
2016/12/19 GE PROPRIETARY INFORMATION - Not to be used, disclosed to others or reproduced without the express written consent of GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG authorization, is strictly prohibited.
Page 3 of 5 CF34-8C S/B , ENGINE - Fan Rotor Assembly (72-00-21) -72-0137 Inspection of Fan Blades CF34-8C S/B , ENGINE - Fan Rotor Assembly and A-Sump72-0227 Components (72-21-00) - Introduction of Redesigned Fan Blade Retaining Pin P/N 4114T06P03 Repair Document (RD) 830-623 (P2 or higher), Fan Rotor Assembly - Fan Blade - Alteration - Tang Pinhold Bushing Installation NOTE:The reference documents listed below are for the engine manufacturer's internal use only:
CID: 891748 J. Publications Affected GEK 105092, CF34-8C Illustrated Parts Catalog (IPC) K. Interchangeability The repaired fan blades (with bushing) P/N are4114T31G01 interchangeable with fan blades P/N , only when the4114T15P02 repaired fan blades P/N are used with solid fan blade4114T31G01 retaining pins P/N and when the repaired fan blades4114T06P03 are installed in the fan rotor in pairs, 180 degrees apart. The new solid fan retaining pin P/N is introduced by4114T06P03 CF34-8C S/B .72-0227 NOTE:Do not install fan blades with bushings P/N with hollow pins P/N 4114T31G01 or P/N .4114T06P01 4114T06P02 L. Software Accomplishment Summary Not applicable.
2. MATERIAL INFORMATION A. Material - Price and Availability
(1) Parts necessary to do this Service Bulletin:
None.
(2) Other Spare Parts:
Part Number Qty/ Eng Part Name Unit ($) Price Pkg Qty Lead Time Days 4114T06P03 (AR) Pin, Fan Blade Retaining (Solid)
456.00 (1) 5
(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 (FIELD ONLY) 4129T36G01/ G02/G03 (X) Rotor Assembly, Fan (SIN 83000) 4129T36G01/ G02/G03 (X) RM -/- 4923T72G01 (X) Rotor Assembly, Fan (SIN 83000) 4923T72G01 (X) RM -/- . *4114T31G01 (AR) Blade, Unbushed Fan (SIN 83100) (Old Name) Blade, Bushed Fan . 4114T15P02 05-070,72-21-00
(28) RW/RI 5/-
CF34-8C Service Bulletins (SBs) SB 72-A0225 R03 ENGINE - Fan Rotor Assembly (72-21-00) - Introduction of Fan Blade Bushing Repair Date Printed:
2016/12/19 GE PROPRIETARY INFORMATION - Not to be used, disclosed to others or reproduced without the express written consent of GE. Technical data is considered ITAR and/or EAR controlled;
transfer of this data to a Non-US Person, without USG authorization, is strictly prohibited.
Page 4 of 5 (SIN 830A0) (New Name) *Part not provisioned by GE.
Operation Codes RI=Reidentify RM=Remains RW=Rework Change Codes 5=Qualified interchangeability. Refer to paragraph 1.K., .Interchangeability Support Codes None.
D. Parts Disposition None.
E. Tooling - Price and Availability None.
3. ACCOMPLISHMENT INSTRUCTIONS A. General
(1) Remove the affected fan blades Refer to GEK 105091,(1, Figure 1).
72-00-21, REMOVAL.
(2) Send the removed fan blades to an approved repaired source(1, Figure 1) to be reworked per RD 830-623. Refer to the APPROVAL OF REWORK SOURCES NOTICE below for contact information.
NOTICE
APPROVAL OF REWORK SOURCES The repair referred to above 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 a Technical 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.
OR Phone: (513) 552-9563
(3) Install the reworked fan blades Refer to GEK 105091,(1, Figure 1).
72-00-21, INSTALLATION.
(4) After you comply with this Service Bulletin, do as follows:
(a) Once the reworked fan blades reach 28,000 engine cycles(1, Figure 1) since fan blade (1) bushing repair, replace it as follows:
1 Remove the affected reworked fan blades (1) Refer to GEK 105091, 72-00-21, REMOVAL.
2 Discard the removed reworked fan blades (1, Figure 1).
3 Install new fan blades (1) of the same part number (P/N ).4114T15P02
CF34-8C Service Bulletins (SBs) SB 72-A0225 R03 ENGINE - Fan Rotor Assembly (72-21-00) - Introduction of Fan Blade Bushing Repair Refer to GEK 105091, 72-00-21, INSTALLATION.
FAN DISK LEGEND:
1. FAN BLADE
REWORK OLD PART TO P/N 4114T31G01 5034319-00 Fan Blade Location Figure 1 GE PROPRIETARY INFORMATION - Subject to the restrictions on the media.
GE PROPRIETARY INFORMATION - Not to be used, disclosed to Date Printed: others or reproduced without the express written consent of Page 2016/12/19 GE. Technical data is considered ITAR and/or EAR controlled; 5 of 5 transfer of this data to a Non-US Person, without USG authorization, is strictly prohibited.