Service Bulletin Aerostructures 850 Lagoon Drive Chula Vista, California 91910-2098 REVISION SUMMARY Revision Summary 1 of 1 Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098 These commodities, technology or software are controlled by the US Export Administration Regulations (EAR). Diversion contrary to US law is prohibited. ECCN: 9E991 NUMBER: DATE: ATA SYSTEM: A318/A319/A320/A321 RA32071-164 Rev 1 July 19, 2017 71-20-00 CFM56-5A/5B SUBJECT: NACELLE - POWER PLANT - INTRODUCTION OF AN IMPROVED AFT ENGINE MOUNT RETAINER ASSEMBLY Subject: Nacelle Service Bulletin No. RA32071-164 Revision No. 1, dated July 19, 2017 List of Effective Pages: PAGE NO. REVISION NO. DATE All 0 October 6, 2016 Summary, 1-5, 8-14, 18-20 1 July 19, 2017 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) Corrected references throughout Accomplishment Instructions of Service Bulletin (2) Removed AMM subtask and subtask-section references due to operator compatibility (3) Included reference to PAD 2017-036 in Compliance sections (4) Revised Figure 1 to illustrate Nut P/N 83642-918 removal location and include omitted washer P/N VN936NP3 (5) Updated Kit Pricing for 2017 Calendar Year (6) Added recommended tooling for on wing marking (7) Included In-Shop manpower estimates and completed section 3.B ‘Shop Instructions’ to include omitted sections 3.A.(6)c) – 3.A.(6)d, 3.A.(8)a, and 3.A.(10) (8) Added Caution to inform Operators to ensure A/C electrical network is de-energized (9) Added instruction during the re-identification of the Aft Engine Mount Assembly to electrically ground the aircraft (10) Added note in section 3.A.(9) and figure 5 to clarify retainer orientation (LHS vs RHS) (11) Removed specified -5A engines from the effectivity that have the 4 lug mounting flange configuration (12) Added reference to AMM chapter 12-34-24 to section 1.K ‘References’ (13) Added Figure 6 and 7 showing incorrect and correct retainer configurations (14) Added additional step 3.A.(5) to verify 4 mounting flange configuration (15) Added Figure 8 showing old LPT Assembly, 4 mounting flange configuration Effect of Change on Prior Compliance: None.
Transcript
Service Bulletin Aerostructures 850 Lagoon Drive Chula Vista, California 91910-2098
REVISION SUMMARY
Revision Summary 1 of 1
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098 These commodities, technology or software are controlled by the US Export Administration Regulations (EAR).
Diversion contrary to US law is prohibited. ECCN: 9E991
NUMBER: DATE: ATA SYSTEM: A318/A319/A320/A321 RA32071-164 Rev 1 July 19, 2017 71-20-00 CFM56-5A/5B
SUBJECT: NACELLE - POWER PLANT - INTRODUCTION OF AN IMPROVED AFT ENGINE MOUNT RETAINER ASSEMBLY
Subject: Nacelle Service Bulletin No. RA32071-164 Revision No. 1, dated July 19, 2017
List of Effective Pages:
PAGE NO. REVISION NO. DATE
All 0 October 6, 2016
Summary, 1-5, 8-14, 18-20 1 July 19, 2017
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) Corrected references throughout Accomplishment Instructions of Service Bulletin (2) Removed AMM subtask and subtask-section references due to operator compatibility (3) Included reference to PAD 2017-036 in Compliance sections (4) Revised Figure 1 to illustrate Nut P/N 83642-918 removal location and include omitted
washer P/N VN936NP3 (5) Updated Kit Pricing for 2017 Calendar Year (6) Added recommended tooling for on wing marking (7) Included In-Shop manpower estimates and completed section 3.B ‘Shop Instructions’ to
include omitted sections 3.A.(6)c) – 3.A.(6)d, 3.A.(8)a, and 3.A.(10) (8) Added Caution to inform Operators to ensure A/C electrical network is de-energized (9) Added instruction during the re-identification of the Aft Engine Mount Assembly to
electrically ground the aircraft (10) Added note in section 3.A.(9) and figure 5 to clarify retainer orientation (LHS vs RHS) (11) Removed specified -5A engines from the effectivity that have the 4 lug mounting flange
configuration (12) Added reference to AMM chapter 12-34-24 to section 1.K ‘References’ (13) Added Figure 6 and 7 showing incorrect and correct retainer configurations (14) Added additional step 3.A.(5) to verify 4 mounting flange configuration (15) Added Figure 8 showing old LPT Assembly, 4 mounting flange configuration
Effect of Change on Prior Compliance:
None.
Service Bulletin Aerostructures 850 Lagoon Drive Chula Vista, California 91910-2098
SUMMARY
Revision Summary 1 of 1
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098 These commodities, technology or software are controlled by the US Export Administration Regulations (EAR).
Diversion contrary to US law is prohibited. ECCN: 9E991
NUMBER: DATE: ATA SYSTEM: A318/A319/A320/A321
RA32071-164 Rev 1 DRAFT 71-00-00 CFM56-5A/5B
SUBJECT: NACELLE - POWER PLANT - INTRODUCTION OF AN IMPROVED AFT ENGINE MOUNT RETAINER ASSEMBLY
BACKGROUND Operators have reported broken Aft Engine Mount inner retainers P/N 238-0252-505.
ACTION This Service Bulletin introduces an improved Aft Engine Mount retainer assembly consisting of redesigned inner, middle, and outer retainers.
COMPLIANCE
Category 3 – Mandatory Service Bulletin must be accomplished. EASA has issued PAD 2017-036 in support of a future Airworthiness Directive associated to this Service Bulletin.
Replace at next maintenance opportunity no later than 48 months of the initial publication date of this Service Bulletin.
Incorporation of this Service Bulletin is the terminating action for the latest revision of UTAS Service Bulletins RA32071-146, RA32071-160, and RA32071-165.
EFFECTIVITY All Aft Engine Mounts on A318/A319/A320/A321 aircraft operated with CFM56-5A/5B engines delivered with Quick Engine Change (QEC) Kits and Engine Build-Up (EBUs) prior to EBU S/Ns 13515001.
NOTE: UTAS has issued an All Operators Letter (reference PUB0002362) to inform Operators this Service Bulletin is NOT applicable on CFM56-5A1, -5A3, -5A4, -5A4/F, -5A5, and -5A5/F engines with the Low Pressure Turbine (LPT) Assembly, 4 mounting flange configuration. Refer to Figure 8.
MANPOWER
The estimated time to incorporate the full intent of this Service Bulletin on one (1) Nacelle with two (2) required mechanics (without bootstrap use): On-Wing
In-Shop
MATERIAL INFORMATION
The parts to accomplish this Service Bulletin are available from UTC Aerospace Systems as Kit RA32071-164-551.
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
These commodities, technology or software are controlled by the US Export Administration Regulations (EAR). Diversion contrary to US law is prohibited. ECCN: 9E991
NACELLE - ENGINE MOUNT - INTRODUCTION OF AN IMPROVED AFT ENGINE MOUNT RETAINER ASSEMBLY
1. PLANNING INFORMATION
A. Effectivity
(1) Airplane: A318/A319/A320/A321
(2) Engine: CFM56-5A/5B
(3) All Aft Engine Mounts on A318/A319/A320/A321 aircraft operated with CFM56-5A/5B engines delivered with Quick Engine Change (QEC) Kits and Engine Build-Up (EBUs) prior to EBU S/Ns 13515001.
NOTE UTAS has issued an All Operators Letter (reference PUB0002362) to inform Operators this Service Bulletin is NOT applicable on CFM56-5A1, -5A3, -5A4, -5A4/F, -5A5, and -5A5/F engines with the Low Pressure Turbine (LPT) Assembly, 4 mounting flange configurations. Refer to Figure 8.
B. Concurrent Requirements
None
C. Reason
(1) Objective:
Remove all existing configuration Aft Engine Mount Retainer Assemblies and replace with the new improved design.
(2) Problem:
Cracks have been reported on the Aft Engine Mount inner retainers at the bend radius.
(3) Cause:
Metallurgical evaluation identified fatigue cracking as the failure mechanism of the retainer.
(4) Background:
Some cases of failed retainers have been reported.
(5) Substantiation:
This Service Bulletin has been substantiated by engineering analysis and test.
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
D. Description
This Service Bulletin provides the instructions to remove the currently installed Aft Engine Mount inner, middle, and outer retainers, including the associated hardware, and replace with the improved design.
E. Compliance
Category 3 – Mandatory
Service Bulletin must be accomplished. EASA has issued PAD 2017-036 in support of a future Airworthiness Directive associated to this Service Bulletin.
Replace at next maintenance opportunity no later than 48 months of the initial publication date of this Service Bulletin.
Incorporation of this Service Bulletin is the terminating action for the latest revision of UTAS Service Bulletins RA32071-146 and RA32071-160.
F. Approval
The technical content of this document is approved under the authority of DOA Ref. EASA.21J.031.
G. Manpower
The estimated time to incorporate the full intent of this Service Bulletin on one Nacelle with two (2) required mechanics (without bootstrap use):
On-Wings Task Hours Elapsed Hours (a) Gain Access 1.00 1.00
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
K. References
This Service Bulletin is subject to aircraft modification N° 158435 P14799 (classified major) and is covered by Airbus Service Bulletin N° A320-71-1071.
Under no circumstances shall the modified equipment, resulting from the application of this Service Bulletin, be installed on the aircraft type unless its aircraft Service Bulletin is approved.
The following information was used in preparation of this Service Bulletin:
Data Identification Change Chapter/Section Type Data
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
2. MATERIAL INFORMATION
A. Material Price and Availability
Parts required to accomplish this Service Bulletin are available from UTAS as follows:
NOTE: Quantities listed are per Nacelle.
This bulletin contains industry initiative pricing available to all Operators. Depending on the age of the Operator’s aircraft at the time of Service Bulletin kit delivery, the following discount to the ‘then year kit price’ will be provided: MONTHS Discount % from then yr. kit price 0 to 60 months 60% 61 to 84 months 50% 85 to 120 months 40% Greater than 120 months 25% Operators should submit a purchase order for the kit quantities required and the aircraft number and age since initial aircraft delivery. Operators may list on their purchase order separate pricing for each batch of parts covered under the discount groupings above, or if it is simpler in the Operator system to have one line item, Operators may calculate a single price at the weighted average of the Operator’s fleet at the time of requested delivery. If Rohr Inc. is unable to achieve the requested delivery schedule under this managed service bulletin program an alternate delivery schedule will be provided at time of order acknowledgment.
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
Direct the purchase order to:
UTC Aerospace Systems – Aerostructures Group 850 Lagoon Drive Chula Vista, CA 91910-2098 Attn: Direct Airline Sales (Service Bulletin No. RA32071-164) [email protected]
NOTE: Please do not submit purchase orders for kit via Spec 2000 Ordering System or Internet Portal. Purchase Orders for kits should be submitted via email attachment to [email protected].
B. Industry Support Information
See above paragraph 2.A.
C. Material Necessary to Implement SB
DESCRIPTION DESIGNATION MANUFACTURER
High Temperature Ink, Sermetel
No409 (Black) Praxair Surface Technologies Indianapolis
Cloth, Cotton Commercially Available
Solvent Commercially Available
Abrasive Paper 180 Grit Aluminum oxide Commercially Available
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
3. ACCOMPLISHMENT INSTRUCTIONS
A. On-Wing
These instructions are written on the condition that the Power Plant is installed on the airplane.
(1) Open the fan cowl doors. Refer to AMM Task 71-13-00-010-040-A for CFM56-5A and AMM Task 71-13-00-010-040-B for CFM56-5B.
(2) Make sure the thrust reverser is unserviceable. Refer to A318/A319/A320/A321 AMM Task 78-30-00-481-041-A for CFM56-5A and AMM Task 78-30-00-481-041-B for CFM56-5B.
(3) Open the thrust reverser doors. Refer to AMM Task 78-36-00-010-040-A for CFM56-5A and AMM Task 78-36-00-010-040-B for CFM56-5B.
(4) Prior to the incorporation of this Service Bulletin, verify the engine is not fitted with the Low Pressure Turbine (LPT) four mounting flange configuration and proceed to step 3.A.(5). If the engine is fitted with the four mounting flange, then the new Aft Engine Mount Retainer Assembly must not be installed. Refer to section 1.A.(3) and Figure 8 for additional details.
(5) Inspect the Aft Engine Mount to identify the location of the Part Number then proceed to step 3.A.(6). If the Part Number cannot be located on-wing, the unit must be taken into the shop to locate the Part Number prior to incorporating the Service Bulletin. Refer to paragraph 3.B for shop instructions. Refer to Figure 5 for typical existing marking location.
(6) Removal of the outer and middle retainers 238-0253-509 and 238-0253-511 (alternative 238-0253-507) (3 locations).
NOTE: Although clearance is tight, this task can be accomplished on wing, using the following procedures: 3.A.(6).a) through 3.A.(6).d).
a) Without the use of the engine bootstrap system, remove the following parts in accordance with AMM Task 71-22-11-000-042-A for CFM56-5A and AMM Task 71-22-11-000-043-A for CFM56-5B: The NAS6303U5 (or NAS6203-5) bolts, the VN936NP3C washers, the VN936NP3 washers, and the NAS1805-3 nuts that attach the outer, middle, and inner retainers together. Discard the bolts, nuts, and washers. Refer to Figure 1.
b) Remove the outer retainers 238-0253-509 and middle retainers 238-0253-511 (alternative 238-0253-507). Discard the hardware. Refer to AMM Task 71-22-11-000-042-A without removing the nuts 83642-1420, nuts 83642-918, and inner retainers 238-0252-505 for CFM56-5A. Refer to AMM 71-22-11-000-043-A without removing the nuts P/N 83642-1420, nuts P/N 83642-918, and the inner retainer P/N 238-0252-505 for CFM56-5B. Refer to Figure 1.
c) Inspect the nut P/N 83642-1420 and nuts P/N 83642-918 for any looseness or wear.
d) If nuts P/N 83642-1420 and nuts P/N 83642-918 are loose or worn, inspect for a gap between the pin head and anti-rotation bracket. Refer to Figure 4.
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
i. If there is a gap of more than 0.001 inch (0.025mm), then proceed to step 3.A.(7) because the engine weight must be supported per the AMM, Chapter 71-22-11.
ii. If the gap is less than 0.001 inch (0.025mm), proceed to step 3.A.(8).
(7) 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 71-22-11-000-042-A for CFM56-5A and AMM Task 71-22-11-000-043-A, for CFM56-5B and proceed to step 3.A.(8).
(8) Removal of the Inner Retainers 238-0252-505 (3 locations)
CAUTION: THE REMOVAL OF THE FOLLOWING HARDWARE MUST BE PERFORMED AT ONLY ONE LINK LOCATION AT A TIME.
a) Do a torque test of the nuts P/N 83642-1420. Torque the nuts to a minimum value of between 80 lbf.ft (108.5 N.m), not to exceed the maximum value of 95 lbf.ft (128.8 N.m). If there is any movement of the nuts, discard and replace with new.
b) Reworking one link at a time, remove nuts P/N 83642-918 and P/N 83642-1420 in accordance with AMM 71-22-11-000-042-A for CFM56-5A and AMM 71-22-11-000-043-A for CFM56-5B. Retain the P/N 83642-1420 nut for installation and discard the P/N 83642-918 nut.
c) Examine the nut P/N 83642-1420 for corrosion and damaged threads. Replace any damaged parts as necessary.
d) Remove and discard the inner retainer P/N 238-0252-505. Refer to Figure 1 and AMM 71-22-11-000-042-A for CFM56-5A and AMM 71-22-11-000-043-A for CFM56-5B.
(9) Installation of the Retainers (3 locations)
CAUTION: AFT ENGINE MOUNT RETAINERS ARE HANDED. EXTRA CARE MUST BE TAKEN TO ENSURE THE CORRECT RETAINERS ARE INSTALLED AT EACH LINK LOCATION. REFER TO FIGURE 2, 3, AND 6 FOR FURTHER INFORMATION ON THE CONFIGURATION AND LOCATION OF THESE DETAILED PARTS.
CAUTION: REPLACE ALL OLD CONFIGURATIONS WITH THE NEW IMPROVED DESIGN. PERFORM OPERATION ONE LINK AT A TIME.
NOTE: Retainers to be aligned between beam and link. Refer to Figures 6 and 7 for correct and incorrect alignment of retainer.
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
i. Install the inner retainer P/N 238-0252-507 following AMM Task 71-22-11-400-042-A for CFM56-5A and AMM Task 71-22-11-400-043-A for CFM56-5B. Refer to Figures 2 & 3.
ii. Install the following parts in accordance with AMM Task 71-22-11-400-042-A for CFM56-5A and AMM Task 71-22-11-400-043-A for CFM56-5B: The 83642-1420 nut, CR 9458 locking nut, 238-0253-515 middle retainer, 238-0253-513 outer retainer, NAS6303U5 bolts, S700W1501D301 washers, and NAS1805-3 nuts. Refer to Figures 2 & 3.
NOTE: The CR 9458 lock nut can only be used one time. If the CR 9458 locking nut has been uninstalled, it must be discarded and replaced with new.
b) For Center and Right Hand Links of Aft Engine Mount:
i. Install the inner retainer P/N 238-0252-508 following AMM Task 71-22-11-400-042-A for CFM56-5A and AMM Task 71-22-11-400-043-A for CFM56-5B. Refer to Figures 2 & 3.
NOTE: Due to limited clearance between the link and the center retainer, it is necessary to loosely position the NAS6303U5 bolt on the leg of the center retainer which is parallel to the link prior to installing the retainer.
ii. Install the following parts in accordance with AMM Task 71-22-11-400-042-A for CFM56-5A and AMM Task 71-22-11-400-043-A for CFM56-5B: The 83642-1420 nut, CR 9458 locking nut, 238-0253-516 middle retainer, 238-0253-514 outer retainer, NAS6303U5 bolts, S700W1501D301 washers, and NAS1805-3 nuts. Refer to Figures 2 & 3.
c) If installed, remove the Bootstrap system. Refer to AMM Task 71-22-11-400-042-A, for CFM56-5A and AMM Task 71-22-11-400-043-A, for CFM56-5B.
NOTE: Odd retainer dash numbers are installed on the LHS while even retainer dash numbers are installed on the Center and RHS.
(10) Re-identify the Aft Engine Mount Assembly using electro etch.
CAUTION: DO NOT USE METAL STAMP OR VIBROETCH ON ENGINE MOUNT.
WARNING: ENSURE AIRCRAFT ELECTRICAL NETWORK IS DE-ENERGIZED PER AMM TASK 12-34-24-869-002.
a) Make sure that the aircraft is electrically grounded. Refer to AMM Task 12-34-24-869-002 (These instructions are provided in aircraft cover Service Bulletin 71-1071.)
b) Use aluminum oxide 180 grit sand paper to abrade the existing part number, maintain 125 ra.
c) Clean the surface using a clean lint free cloth and solvent.
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
d) Using high temperature ink, cross out the existing part number.
e) Using electro etch, re-identify part number of the Aft Engine Mount Assembly per CMM 71-22-07 Repair No. 06 for CFM56-5A/5B following Paragraph 2.E. Copy all of the data below the existing part number to the new part number location. Refer to Figure 5 for suggested re-identification location.
NOTE: For on-wing part number re-identification of aft engine mount assembly, Agicom ME3000S or equivalent tooling can be used per section 2.F.
(11) Close the thrust reverser doors. Refer to A318/319/A320/A321 AMM Task 78-36-00-410-040-A for CFM56-5A or 78-36-00-410-040-B for CFM56-5B.
(12) Make sure the thrust reverser is serviceable. Refer to A318/A319/A320/A321 AMM Task 78-30-00-081-041-A for CFM56-5A or AMM Task 78-30-00-081-041-B for CFM56-5B.
(13) Close the fan cowl doors. Refer to A318/A319/A320/A321 AMM Task 71-13-00-410-040-A for CFM56-5A or AMM Task 71-13-00-410-040-B for CFM56-B.
(14) Write in engine log and/or other records that Goodrich Service Bulletin RA32071-164 has been incorporated.
B. Shop (QEC Instructions)
The following instructions are for spare engines with engine mounts installed, QEC Kits, and engine mounts in the shop.
(1) Follow the instructions of § 3.A.(6).a)-3.A.(6).b), 3.A.(8).b)-3.A.(8).d), 3.A.(9).a)-3.A.(9).b), 3.A.(10).
(2) Mark in the engine log that SB RA32071-164 has been accomplished.
(3) All retainers P/N 238-0252-505, 238-0253-511 (alternative 238-0253-507), 238-0253-509, nuts P/N 83642-918, and washers P/N VN936NP3 and VN936P3C in inventory must be removed and replaced with the new parts introduced in section 2.E of this Service Bulletin.
Rohr, Inc., a subsidiary of The Goodrich Corporation, operating as Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098
This document is subject to the controls and restrictions on the first page.
NOTE: FOR SOME MOUNT ASSEMBLIES, THE PART NUMBER MAY BE LOCATED IN
AN ALTERNATE LOCATION. IF THE PART NUMBER CANNOT BE LOCATED ON-WING, THE UNIT MUST BE TAKEN INTO THE SHOP TO LOCATE THE PART NUMBER PRIOR TO INCORPORATING THE SERVICE BULLETIN.
