# 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 Good rich consent. This document is subject to the controls and restrictions of the U.S. Export Admini stration Regulations (EAR). NUMBER: DATE: ATA SYSTEM: 

## A 318/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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration Regulations (EAR). NUMBER: DATE: ATA SYSTEM: 

## A 318/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/HRSThis 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration Regulations (EAR). E. Parts Affected by the Service Bulletin

New P/N Qty Nomenclature Old P/N Qty Operation CHG Code S PRT 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration 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 Good rich consent. This document is subject to the controls and restricti ons of the U.S. Export Admi nistration Regulations (EAR). Typical Engine Attach Hardware – Gap Test Figure 3