Service Bulletin

Aerostructures

850 Lagoon Drive 

Chula Vista, California 91910-2098

REVISION SUMMARY

 Revision Summary 1 of 1 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR). 

NUMBER: DATE: ATA SYSTEM: A318/A319/A320/A32

RA32071-146 Rev. 2 July 26, 2012 71-00-00 CFM56-5A/5B

SUBJECT: NACELLE - ENGINE MOUNT - INSPECTION OF AFT ENGINE 

MOUNT RETAINER 

Subject: Nacelle Service Bulletin No. RA32071-146 

Revision No. 2, dated July 26, 2012. 

List of Effective Pages: 

PAGE NO. 

REVISION 

NO. DATE 

ALL Original 19 March 2012 

Summary, 1, 8, and 11 1 June 14, 2012 

Summary, 1, 3, 4, 6, 

7, 8, and 11 2 July 26, 2012 

Note: A copy of this notice should be filed as a permanent record with 

each copy of subject bulletin revision and with any future revisions. 

Reasons for Revision: 

The Bulletin has been revised to incorporate the following changes: 

(1) Updated Effectivity; provided additional information in the 

Cause and Objective. 

(2) Added Airbus AOT A71N001-12 to References. 

(3) Update Accomplishment Instructions. 

(4) Updated Figure 3. 

Effect of Change on Prior Compliance: 

N/A
Service Bulletin

Aerostructures

850 Lagoon Drive 

Chula Vista, California 91910-2098

SUMMARY

Summary 1 of 1 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

NUMBER: DATE: ATA SYSTEM: A318/A319/A320/A32

RA32071-146 Rev. 2 July 26, 2012 71-00-00 CFM56-5A/5B

SUBJECT: NACELLE - ENGINE MOUNT - INSPECTION OF AFT ENGINE 

MOUNT RETAINER 

BACKGROUND

Multiple operators have reported broken aft 

engine mount inner retainers P/N 238-0252-505. 

ACTION 

This Service Bulletin tasks operators to inspect 

the aft engine mount inner retainers (3 per 

engine) and replace if necessary. 

COMPLIANCE 

Category 3 

Accomplish when the Nacelle is disassembled 

sufficiently to afford access to the affected 

subassembly. Accomplish within 6 months of 

the original revision issue date of this Service 

Bulletin. 

NOTE: Refer to Airbus AOT A71N001-12 for 

extended compliance timescale. 

EFFECTIVITY 

Aft Engine Mounts on Engine Build Up units 

prior to S/N 11025001 and all aft engine mounts 

that have been removed or replaced since entry 

into service or have had the inner retainers, P/N 

238-0252-505, replaced since entry into service. 

MANPOWER 

The estimated time to incorporate the full intent of 

this Service Bulletin on one Nacelle (without 

bootstrap use): 

MATERIAL INFORMATION 

No kit is associated with this Service Bulletin. 

 

(a) Gain Access 0.50 M/HRS 

(b) Inspect Bracket 0.50 M/HRS 

(c) Replace Bracket if necessary 1.00 M/HRS 

(e) Put Nacelle to Service 0.50 M/HRS 

Total 2.50 M/HRS 
This Page Intentionally 

 

Left Blank
Service Bulletin

Aerostructures

850 Lagoon Drive 

Chula Vista, California 91910-2098

A318/A319/A320/A321

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 1 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

NACELLE - ENGINE MOUNT - INSPECTION OF AFT ENGINE MOUNT RETAINER BRACKETS 

1. PLANNING INFORMATION 

A. Effectivity 

(1) Airplane: A318/A319/A320/A321 

(2) Engine: CFM56-5B/5A 

(3) All three Aft Engine Mount Retainers, P/N 238-0252-505, on 

EBU prior to S/N 11025001 and all retainers that have been 

replaced since entry into service or are on an aft engine 

mount that has been removed or replaced since entry into 

service. EBU S/N 11025001 was delivered with Aft Engine 

Mount S/N 5804 and was delivered on Aircraft MSN 4942. 

B. Reason 

(1) Problem: 

Aft engine mount retainers have been failing in service. 

(2) Cause: 

 A metallurgical evaluation found surface pitting on the 

surface of the failed bracket. The surface pitting 

adversely affected the strength of the retainer in 

fatigue. There are two types of material finishes: “D” 

dull or “B” bright. The dull finish has the pitted surface 

and is subject to cracking. The bright finish has a smooth 

finish free of pits. Some brackets were manufactured from 

dull finish material. 

(3) Background: 

 Multiple cases of failed retainer brackets have been 

reported, and retainers have been found with surface 

pitting. 

(4) Objective: 

 Inspect the aft engine mount retainer for surface finish 

(dull or bright), cracks or failures and remove and 

replace as necessary. 

(5) Substantiation: 

 This Service Bulletin has been substantiated by 

engineering analysis. 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 2 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

C. Description 

This Service Bulletin provides the instructions to inspect the 

aft engine mount retainers P/N 238-0252-505 and replace as 

necessary. 

D. Compliance 

Category 3 

Accomplish when the Nacelle is disassembled sufficiently to 

afford access to the affected subassembly. Accomplish within 6 

months of the original revision issue date of this Service 

Bulletin. 

E. Approval 

The inspection procedures described in this SB are reviewed and 

technically accepted by Airbus Design Office to apply to the 

Airbus fleet affected. 

This SB does not contain any change information that revises the 

equipment definition covered by Airbus approved modifications. 

F. Manpower 

Estimated man-hours to incorporate the intent of this bulletin 

to a Nacelle using trained personnel (without bootstrap use): 

In-Shop M-HRS 

 

Gain Access 0.50 

Inspect Bracket 0.50 

Replace Bracket if necessary 1.00 

Put Nacelle into Service 0.50 

Total 2.50 

NOTE: Estimated labor hours are for planning purposes only. 

Labor reimbursement is not provided under the terms of 

this service bulletin. 

G. Weight and Balance 

None. 

H. Electrical Load Data 

Not affected. 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 3 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

I. References 

The following information was used in preparation of this 

Service Bulletin: 

Data Identification Change Chapter/Section Type Data 

A71N001-12 Airbus July 2012 - Alert Operators 

Transmission 

QN 2063462 - - Quality 

Notification 

IR027509 Sept 7/11 - Information 

Request 

A318/A319/A320/A321 

CFM56-5B Component 

Maintenance Manual 

Jul 15/12 71-22-07 Publication 

A318/A319/A320/A321 

CFM56-5B Aircraft 

Maintenance Manual 

Aug 01/11 

71-13-00 

71-22-11 

78-36-00 

Publication 

A318/A319/A320/A321 

CFM56-5A Aircraft 

Maintenance Manual 

Aug 01/11 

71-13-00 

71-22-11 

78-36-00 

Publication 

J. Other Publications Affected 

None. 

K. Interchangeability or Intermixability of Parts 

Pre and post service bulletin EBUs are interchangeable. 

Interchangeability and intermixability of the Aft Engine Mount 

Assembly is not affected. 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 4 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

2. MATERIAL INFORMATION 

A. Material Price and Availability 

(1) No kits are provided to accomplish this Service Bulletin. 

The following part may be required and may be purchased 

from Goodrich. 

Part Number Nomenclature 

QTY 

(per engine) 

EST’D UNIT 

PRICE 

238-0252-505 Inner Retainer 

Bracket 3 RFQ 

(2) For up to one year from the Service Bulletin original 

issue date, Inner Retainer Bracket purchases for 

replacements made as a result of this Service Bulletin 

will receive a refund of the price paid after receipt of 

the removed retainer bracket by Goodrich. Return all 

removed Inner Retainer Brackets to the Goodrich address 

below: 

Goodrich Aerostructures Group 

850 Lagoon Drive 

Chula Vista, CA 91910-2098 

Attn: Bldg 29 Service Bulletin RA34071-146 

Operators should submit a charge purchase order for the 

applicable quantities. The purchase order must specify 

this service bulletin number and only the parts herein. A 

delivery schedule will be provided at time of order 

acknowledgment. 

Direct charge purchase order to: 

Goodrich Corporation – Aerostructures Group 

850 Lagoon Drive 

Chula Vista, CA 91910-2098 

Attn: Direct Airline Sales 

(Service Bulletin No. RA32071-146) 

Ordering website: parts.asg.goodrich.com 

B. Industry Support Information 

No industry support is provided for this service bulletin. 

C. Material Necessary to Implement SB 

 None. 

D. Materials Necessary for each Spare 

Refer to sections 2.A. and 2.C. 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 5 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

E. Parts Affected by the Service Bulletin 

New P/N Qty Nomenclature Old P/N Qty Operation CHG 

Code

SPRT 

Code

238-0252-505 (3) Inner Retainer 

Bracket 238-0252-505 (3) Inspect A 6 

Note 1: Change Codes 

 A = New and Old Parts are directly interchangeable. 

Note 2: Support Codes 

 6 = New part currently available. 

F. Tooling 

Reference Nomenclature 

S487ETT2 Engine Trolley 

S686CR56-5 Engine Cradle 

98D27803500001 Tool-Zero Locking, Flap 

Slat CTL Lever 

98D71203500000 Bootstrap-System 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 6 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

3. ACCOMPLISHMENT INSTRUCTIONS 

A. Airplane 

These instructions are written on the condition that the Power 

Plant is installed on the airplane. 

(1) Open the fan cowl doors. Refer to A318/A319/A320/A321 

CFM56-5A/5B Aircraft Maintenance Manual (AMM) Task 71-13-00-

010-040. 

(2) Open the thrust reverser doors. Refer to A318/319/A320/A321-

CFM56-5A/5B Aircraft Maintenance Manual (AMM) Task 78-36-00-

010-040. 

(3) Inspection of the Retainer Brackets (3 locations) 

a) Identify the most visible surfaces of the inner 

retainers P/N 238-0252-505 and clean these areas before 

the inspection. 

b) Visually inspect the 238-0252-505 inner retainer for 

surface finish, dull or bright, using 10x 

magnification, mirror and light. Refer to Figures 1 

and 2. 

NOTE: The center retainer may be difficult to inspect. 

In case of doubt, remove the retainer as per 

section 3.A.(4). for inspection. 

i. For conforming brackets (bright surface finish), no 

further action is required. Proceed to 3.A.(8). 

ii. For non-conforming brackets (dull surface finish) 

without cracks and not failed, a 50 Flight Cycle 

grace period is allowed with an inspection at 25 

Flight Cycles. After this period, replace the 

bracket as per section 3.A.(4). and contact 

Goodrich. 

iii. For non-conforming brackets which are cracked or 

failed, proceed to step 3.A.(4). and contact 

Goodrich. 

(4) Removal of Retainer Brackets (3 locations) 

NOTE: This task can be accomplished on wing, even though 

clearance is tight, using the following procedures 

3.A.(4).a through 3.A.(4).c. 

a) Without the use of the engine bootstrap system, remove 

the following parts in accordance with AMM 71-22-11-

000-043 section 4.A.3 for CFM56-5B and AMM 71-22-11-

000-042 section 4.A.3 for CFM56-5A: The NAS6303U5 

bolts, the VN936NP3C washers, the VN936NP3 washers, and 

the NAS1805-3 nuts that attach the outer retainers to 

the inner retainers. Refer to Figure 1. Retain the 

hardware for installation. 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 7 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

b) Remove the outer retainers 238-0253-509 and 238-0253-

511 (or 238-0253-507). Retain the hardware for 

installation. Refer to Figure 1 and AMM 71-22-11-000-

043 section 4.A.3 for CFM56-5B and AMM 71-22-11-000-042 

section 4.A.3 for CFM56-5A. 

c) Inspect for a gap between the pin head and antirotation bracket. Refer to Figure 1 and 3. 

i. If there is a gap of more than 0.001 inch 

(0.025mm), then proceed to step 3.A.(5) because the 

engine weight must be supported per the Aircraft 

Maintenance Manual, Chapter 71-22-11. 

ii. If the gap is less than 0.001 inch (0.025mm), 

proceed to step 3.A.(6). 

(5) Installation of Bootstrap 

NOTE: Bootstrap installation is necessary only if a gap is 

found between the pin head and anti-rotation bracket 

a) Install the Bootstrap system to take the engine weight 

off of the aft engine mount. Refer to AMM Task 71-22-

11-000-043, subtask 71-22-11-480-051 for CFM56-5B and 

AMM Task 71-22-11-000-042, subtask 71-22-11-480-050 for 

CFM56-5A. 

(6) Replacement of the Retainer Brackets (3 locations) 

a) Remove the following parts in accordance with AMM 71-

22-11-000-043 section 4.A.3 for CFM56-5B and AMM 71-22-

11-000-042 section 4.A.3 for CFM56-5A: The nuts P/N 

83642-918 and P/N 83642-1420. Retain for installation. 

Refer to Figure 1. 

b) Remove and replace the inner retainer bracket, P/N 238-

0252-505, with a conforming bracket. Refer to Figure 1 

and AMM 71-22-11-000-043 section 4.A.3 for CFM56-5B and 

AMM 71-22-11-000-042 section 4.A.3 for CFM56-5A. 

Return non-conforming retainers per the instructions in 

Section 2. 

(7) Installation of the Retainer Brackets (3 locations) 

a) Install the following parts in accordance with AMM 71-

22-11-400-043 section 4.G.11 for CFM56-5B and AMM 71-

22-11-400-042 section 4.G.11 for CFM56-5A: The 83642-

1420 nut, 83642-918 nut, 238-0253-511 (or 238-0253-507) 

outer retainer, 238-0253-509 outer retainer, NAS6303U5 

bolts, VN936NP3C washers, VN936NP3 washers, and 

NAS1805-3 nuts. 

b) If installed, remove the Bootstrap system. Refer to AMM 

Task 71-22-11-400-043, subtask 71-22-11-080-050 for 

CFM56-5B and AMM Task 71-22-11-400-042, subtask 71-22-

11-080-051 for CFM56-5A. 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 8 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

(8) Close the thrust reverser doors. Refer to 

A318/319/A320/A321-CFM56-5A/5B Aircraft Maintenance Manual 

(AMM) Task 78-36-00-410-040. 

(9) Close the fan cowl doors. Refer to A318/A319/A320/A321 

CFM56-5A/5B Aircraft Maintenance Manual (AMM) Task 71-13-00-

410-040. 

(10) Write in engine log and/or other records that Goodrich 

Service Bulletin RA32071-146 Rev. 2 has been incorporated. 

(11) All P/N 238-0252-505 in inventory must be inspected. Refer 

to Figure 2. 

(12) Report Accomplishment of this service bulletin and findings 

to Goodrich. 

B. Shop (QEC Instructions) 

The following instructions are for when the engine is in the shop. 

(1) Follow the instructions of sections 3.A.(3), 3.A.(4).a.-

3.A.(4).b., 3.A.(6)., 3.A.(7). 

(2) Mark in the engine log that SB RA32071-146 Rev. 2 has been 

accomplished. 

(3) All P/N 238-0252-505 in inventory must be inspected. Refer 

to Figure 2. 

(4) Report Accomplishment of this service bulletin and findings 

to Goodrich. 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 9 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

Assembly and Disassembly of Retainer 

Figure 1 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 10 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

 

 

Normal Smooth Surface Nonconforming Pitted Surface 

(Good Part) (Discrepant Part)

 

Examples of non-conforming Inner Retainer Brackets due to surface pitting 

Figure 2 
Goodrich Aerostructures Service Bulletin 

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-146 Rev. 2 

DATE: July 26, 2012 PAGE: 11 of 11 

The information contained in this document is Goodrich proprietary and shall not be used, disclosed, or reproduced without Goodrich consent. 

This document is subject to the controls and restrictions of the U.S. Export Administration Regulations (EAR).

Typical Engine Attach Hardware – Gap Test 

Figure 3