# M U

- 2 

# S E R V I C E B U L L E T I N

MITSUBISHI HEAVY INDUSTRIES, LTD.
NAGOYA AEROSPACE SYSTEMS WORKS 10, OYE

- CHO, MINATO

- KU, NAGOYA, JAPAN

Page 1 of 3 No. 105/32

- 017 

### DATE: S eptember 29

, 2015

Subject: Main Landing Gear Oleo Attach Fitting

– Inspection of

Effectivity: MU

- 2B

- 3 6A/

- 60 : S/N 661SA, 697SA through 1569SA

Purpose: Conduct a one

- time visual inspection of the main landing gear oleo attach fitting s to e nsure that no visible crack exist s in lug s of the fitting s

. Background: C rack s were found in the fitting s of the main landing gear oleo

strut on several long body airplanes

. Since the fitting is very important structure for safe landing , a one

- time inspection is required to e nsure continu ed airworthiness.

Compliance: Mandatory

Approval: Engineering aspects of this Service Bulletin are FAA Approved

Time of Compliance: Within 100 flight hours or 6 months

, after receipt of this Service Bulletin, whichever occurs first

Responsible Agency of Compliance: MU

- 2 Owners/Operators

Disposition of Removed
Parts: Scrap

Spare Parts Affected: None

Required Man Hours: Approximately 5 man hours

Special Tools Required: None

Weight and Balance Change: None

Flight Manual Revision: None

# MU

- 2 Service Bulletin

No. 105/32

- 017 DATE: S eptember 29 , 201 5

Page 2 of 3 INSTRUCTION S Refer to the applicable MU

- 2 Maintenance Manual

, Illustrated Parts Catalog and Structural Repair Manual to comply with this Service Bulletin.

1. PREPARATION (1) Turn on electrical power to the airplane and open main landing gear forward doors using the ground open switch in accordance with the applicable m aintenance m anual for easier access to the fittings. If it is necessary to remove more parts for access, those parts m ay be removed

. (2) Pull the circuit breakers “ LG CONT ” and “ LG DOOR MOTOR ”

. (3) Electrically ground the aircraft. (4) Cl ea n the fitting lug surface to be inspected with a solvent damped cloth to remove any
dirt / dust / grease contaminants and make sure that the surface is exposed

.

2. INSPECTION (1) Visual ly inspect the lugs of the oleo attach fitting s on both sides for visible cracks

. (Figure

1 & 2 ) Use a mirror and flashlight to check the entire surface of lugs of the fitting

. If any
cracks are found in the lug

, replace with a new f itting in accordance with the applicable
Maintenance Manual and discard the discrepant fitting

.

NOTE If the visual inspection is inconclusive

, conduct a n on

- destructive inspection in accordance with the applicable maintenance manual

.

3. LUBRICATION (1) Lubricate the pin assemblies with grease “ GP ” (MIL

- PRF

- 23827).

4. RESTORA TION (1) Close main landing gear forward doors.

NOTE For continued airworthiness after completion of this SB, the Maintenance Requirement Manual requires recurring visual and non

- destructive inspection of the fittings, and also, the Maintenance Manual requires

lubrication for the pin assemblies.

5. LOGBOOK ENTRY Upon completion of this Service Bulletin

, m ake an appropriate maintenance entry in the logbook similar to “Service Bulletin No. 105/32

- 017 complied with on (date) by (name)

, number/stamp

. ”

6. COMPLETION Complete the enclosed compliance card and mail back to Mitsubishi Heavy Industries America, Inc. i n care of Turbine Aircraft Services , Inc

.

Turbine Aircraft Services, Inc. 4550 Jimmy Doolittle Drive

, Addison, Texas 75001 Attention: Manager, Publication s Phone: (972) 248

- 3108 X 209 Fax: (972) 248

- 3321

# MU

- 2 Service Bulletin

No. 105/32

- 017 DATE: S eptember 29 , 201 5

Page 3 of 3

Figure 1: LOCATION OF FITTING LUG INSPECTION

( Typically shown for L/H side)

Figure 2 : MOST LIKELY LOCATION OF CRACKS ON FITTING

(Typically shown for L/H side)

FWD

Drag Strut Leg Oleo Strut Oleo Attach Fitting Frame (STA5605)

Pin Assy

Most likely location
of cracks

FWD

UPR

OUTB/D (L/H)