Service Bulletin

Aerostructures

850 Lagoon Drive

Chula Vista, California 91910-2098

SUMMARY

Summary 1 of 1

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NUMBER: DATE: ATA SYSTEM: A318/A319/A320/A321

RA32071-160 September 18, 2014 71-00-00 CFM56-5A/5B

SUBJECT: NACELLE - ENGINE MOUNT - REPETITIVE INSPECTION OF 

AFT ENGINE MOUNT INNER RETAINER

BACKGROUND

Operators have reported broken aft engine mount 

inner retainers P/N 238-0252-505.

ACTION

This Service Bulletin tasks operators to perform a 

repetitive detailed visual inspection of the aft 

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

(3 per engine) and replace if necessary.

COMPLIANCE

Category 3

Accomplish within 12 months of: A/C delivery, 

inspection or installation of new retainer per SB 

RA32071-146, or issuance of this service bulletin, 

whichever occurs last. 

Perform repetitive inspection every 12 months

thereafter.

NOTE: THE INTENT OF AOT A71N001-12 

REV 2, SB RA32071-146 REV 2, EASA 

AD 2013-0050 OR FAA AD 2014-14-06 

SHOULD HAVE BEEN COMPLIED 

WITH PRIOR TO IMPLEMENTATION 

OF THIS SERVICE BULLETIN.

EFFECTIVITY

All Aft Engine Mounts on A318/A319/A320/A321 

aircraft operated with CFM56-5A/5B engines.

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 Retainers 0.50 M/HRS

(c) Replace Retainer(s) if necessary 1.00 M/HRS

(d) Put Nacelle to Service 0.50 M/HRS

Total 2.50 M/HRS
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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: RA32071-160

DATE: September 18, 2014 PAGE: 1 of 13

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

NACELLE - ENGINE MOUNT – REPETITIVE INSPECTION OF AFT ENGINE MOUNT INNER 

RETAINER

1. PLANNING INFORMATION

A. Effectivity

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

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

(3) All three inner retainers P/N 238-0252-505 on the Aft Engine 

Mount

NOTE: THE INTENT OF AOT A71N001-12 REV 2, SB RA32071-146 REV 2, 

EASA AD 2013-0050 OR FAA AD 2014-14-06 SHOULD HAVE BEEN 

COMPLIED WITH PRIOR TO IMPLEMENTATION OF THIS SERVICE 

BULLETIN.

B. Reason

(1) Problem:

Aft engine mount inner retainers have been reported failed 

in service at the bend radius. 

(2) Cause:

A metallurgical evaluation found the retainers have failed 

by a fatigue cracking mechanism.

(3) Background:

Some cases of failed retainers have been reported.

(4) Objective:

Inspect the aft engine mount inner retainers for cracks or 

failures. 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: RA32071-160

DATE: September 18, 2014 PAGE: 2 of 11

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C. Description

This Service Bulletin provides the instructions to inspect the 

aft engine mount inner retainers P/N 238-0252-505 for cracks or 

failures every 12 months and replace as necessary. 

D. Compliance 

Category 3

Accomplish within 12 months of: A/C delivery, inspection or 

installation of new retainer per SB RA32071-146, or issuance of 

this service bulletin, whichever occurs last. 

Perform repetitive inspection every 12 months thereafter.

NOTE: THE INTENT OF AOT A71N001-12 REV 2, SB RA32071-146 REV 2, 

EASA AD 2013-0050 OR FAA AD 2014-14-06 SHOULD HAVE BEEN 

COMPLIED WITH PRIOR TO IMPLEMENTATION OF THIS SERVICE 

BULLETIN.

E. Approval

The technical content of this document is approved under the 

authority of DOA ref. EASA.21J.031.

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 Retainers 0.50

Replace Retainer(s) 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.
Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-160

DATE: September 18, 2014 PAGE: 3 of 11

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H. Electrical Load Data

Not affected.

I. References

The following information was used in preparation of this Service 

Bulletin: 

Data Identification Change Chapter/Section Type Data

AI-CFM56S-140038 June 2014 71-20-00 Engineering 

Coordination Memo

EASA AD 2013-0050 March 2013 -

Airworthiness 

Directive

FAA AD 2014-14-06 July 2014 -

Airworthiness 

Directive

Airbus AOT A71N001-12

Revision 2 February 2013 -

Alert Operators 

Transmission

238-0252 ADCN F -

Engineering 

Drawing

QN 2063462 - -

Quality 

Notification

A318/A319/A320/A321 

CFM56-5A/5B Component 

Maintenance Manual

Jul 15/12 71-22-07 Publication

A319/A320 CFM56-5A 

Aircraft Maintenance 

Manual

Aug 01/11

71-13-00

71-22-11

78-36-00

Publication

A318/A319/A320/A321 

CFM56-5B 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: RA32071-160

DATE: September 18, 2014 PAGE: 4 of 11

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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 3 RFQ

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.

E. Parts Affected by the Service Bulletin

Part Number Qty Nomenclature Old P/N Qty Operation CHG 

Code

SPRT 

Code

238-0252-505 (3) Inner Retainer 238-0252-505 (3) Inspect A 6

Note 2: Change Codes

 A = New and Old Parts are directly interchangeable.

Note 3: 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: RA32071-160

DATE: September 18, 2014 PAGE: 5 of 11

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

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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 Inner Retainers (3 locations)

NOTE: PAY CLOSE ATTENTION TO THE INNER BEND OF THE RETAINER.

NOTE: THE CENTER RETAINER MAY BE DIFFICULT TO INSPECT. IN 

CASE OF DOUBT, REMOVE THE RETAINER AS PER SECTION 

3.A.(4). FOR INSPECTION.

a) Clean any dirt or unwanted material from the aft engine 

mount with a lint-free cotton cloth. 

b) Without the removal of any hardware, do a visual 

inspection of the 238-0252-505 inner retainer for cracks

using 10x magnification, mirror and light. Refer to 

Figure 1. 

i) For retainers which are cracked or failed, replace 

the retainer as per 3.A.(4). Return cracked or 

failed hardware before next flight and the Data 

Collection and Reporting Sheet (Sheet 1) back to

Goodrich. 

ii) For retainers without cracks and not failed, no 

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

(4) Removal of Outer Retainers (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. for CFM56-5B and AMM 71-22-11-000-042 

section 4.A. 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 2. Retain the hardware for 

installation.
Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-160

DATE: September 18, 2014 PAGE: 6 of 11

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b) Remove the outer retainers 238-0253-509 and 238-0253-511

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

Refer to Figure 2 and AMM 71-22-11-000-043 section 4.A.

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

CFM56-5A.

c) Inspect for a gap between the pin head and anti-rotation 

bracket. Refer to Figure 2 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 Inner Retainers (3 locations)

a) Inspect the nuts P/N 83642-918 and P/N 83642-1420 for any 

looseness or wear. If loose or worn, replace. Record the 

condition of nuts in Sheet 1.

b) Apply torque on large nut P/N 83642-1420 in the 

tightening direction with an open end type adapter or a 

torque wrench at 80 lbf.ft. Record if there is any 

movement of the nut in Sheet 1.

c) Apply torque on small nut P/N 83642-918 in the tightening 

direction with a torque wrench set at 35 lbf.ft. Record 

if there is any movement of the nut in Sheet 1.

d) Remove the following parts in accordance with AMM 71-22-

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

000-042 section 4.A. for CFM56-5A: the nuts P/N 83642-918 

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

e) Remove and replace the inner retainer P/N 238-0252-505. 

Refer to Figure 2 and section 4.G. of AMM 71-22-11-000-

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

4.G. of AMM 71-22-11-000-042 and AMM 71-22-400-042 for 

CFM56-5A.
Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-160

DATE: September 18, 2014 PAGE: 7 of 11

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(7) Installation of Outer Retainers (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.

(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 RA32071-160 has been incorporated.

(11)Reinspect all retainers P/N 238-0252-505 every 12 months in 

accordance with this service bulletin.

(12)If cracked or failed retainers are found, populate the data 

collection and reporting sheet (Sheet 1) and return with the 

failed retainers to Goodrich through your Aerostructures 

Airline Support Manager. 

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 RA32071-160 has been 

accomplished.

(3) If cracked or failed retainers are found, populate the data 

collection and reporting sheet (Sheet 1) and return with the 

failed retainers to Goodrich through your Aerostructures 

Airline Support Manager.

(4) Reinspect all retainers P/N 238-0252-505 every 12 months in 

accordance with this service bulletin.
Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-160

DATE: September 18, 2014 PAGE: 8 of 11

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

 

Inspection of Retainer Bend for Cracks

Figure 1
Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-160

DATE: September 18, 2014 PAGE: 9 of 11

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Assembly and Disassembly of Retainer

Figure 2
Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-160

DATE: September 18, 2014 PAGE: 10 of 11

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Typical Engine Attach Hardware – Gap Test

Figure 3
Goodrich Aerostructures Service Bulletin

EFFECTIVITY: CFM56-5A/5B NUMBER: RA32071-160

DATE: September 18, 2014 PAGE: 11 of 11

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DATA COLLECTION SHEET FOR SERVICE BULLETIN RA32071-160

OPERATOR DATA

OPERATOR:_________________

DATE INSPECTED: ___________

A/C MSN: ___________________ 

A/C MODEL: _________________

ENGINE MODEL: _____________

TSN:________________________

CSN: ________________

TSO: ________________

CSO:________________

ENGINE 1

S/N _____________

PLEASE INDICATE THE CONDITION OF RETAINERS AT EACH 

LOCATION:

BRIGHT 

OR DULL

INTACT, CRACKED 

OR FAILED

IF CRACKED, 

CRACK LENGTH

LEFT: 

CENTER:

RIGHT: 

HISTORY OF RETAINER MAINTENANCE, IF ANY:

CONDITION OF ALL NUTS (WORN, LOOSE, ETC):

LARGE NUT SMALL NUT

LEFT: 

CENTER:

RIGHT: 

ENGINE 2

S/N _____________

PLEASE INDICATE THE CONDITION OF RETAINERS AT EACH 

LOCATION:

BRIGHT 

OR DULL

INTACT, CRACKED 

OR FAILED

IF CRACKED, 

CRACK LENGTH

LEFT: 

CENTER:

RIGHT: 

HISTORY OF RETAINER MAINTENANCE, IF ANY:

CONDITION OF ALL NUTS (WORN, LOOSE, ETC):

LARGE NUT SMALL NUT

LEFT: 

CENTER:

RIGHT: 

Data Collection and Reporting Sheet

Sheet 1