Service Bulletin No. 107/57-005
MITSUBISHI MU 2B · Service Bulletins
Overview
This service bulletin outlines the inspection and replacement procedures for the wing spacer plates of the Mitsubishi MU-2B aircraft. It aims to ensure the airworthiness of the wing structures by addressing potential fatigue cracks found in the spacer plates.
- Mandatory compliance for specified MU-2B models.
- Inspection required for wing spacer plates due to fatigue cracks.
- Fluorescent penetrant inspection is necessary.
- Replacement of spacer plates is required if cracks exceed 0.6 inches.
- Inspection intervals vary based on flight hours.
- No special tools are required for the inspection.
- Negligible weight and balance change expected.
- Logbook entry required after compliance.
Document
Source
Originally published by mhi.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Service Bulletins
- Year ·
- 2016
- File size ·
- 1.0 MB
- Publisher ·
- mhi.com
- Language ·
- en
What is the Service Bulletin No. 107/57-005?
The Service Bulletin No. 107/57-005 is a service bulletins for the MITSUBISHI MU 2B, dated 2016.
Where does the Service Bulletin No. 107/57-005 come from?
This copy of the Service Bulletin No. 107/57-005 was originally published by mhi.com and is hosted on Sprinkle as a free, searchable reference copy.
What year was the Service Bulletin No. 107/57-005 published?
The Service Bulletin No. 107/57-005 — the MITSUBISHI MU 2B service bulletins on file — is dated 2016.
Most owners only have the POH. Here's the essential set for the MITSUBISHI MU 2B.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More MITSUBISHI MU 2Bmanuals & documents
- Mitsubishi MU-2B Service LetterService Bulletins
- Mitsubishi MU-2B Service PublicationService Bulletins
- Mitsubishi MU-2B Service LetterService Bulletins
- Mitsubishi Service Publications TransmittalService Bulletins
- MU-2 Service Bulletin No. 243Service Bulletins
- Mu-2b-60 Pilot'S Operating ManualPilot's Operating Handbook
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In this document
Purpose
To ensure the continued airworthiness of the wing structures through inspection and potential replacement of wing spacer plates.
Compliance
Mandatory compliance is required for specified aircraft serial numbers within defined timeframes based on flight hours.
Inspection Procedure
Detailed steps for conducting a fluorescent penetrant inspection on the wing spacer plates, including preparation and restoration.
Replacement Procedure
Instructions for replacing the spacer plates, including preparation, removal, and installation of new parts.
Recurring Inspection
Guidelines for future inspections based on findings from the initial inspection.
Logbook Entry
Instructions for documenting compliance with the service bulletin in the aircraft's logbook.
Safety notes
- Inspection personnel must be certified as Level II or higher.
- Cracks of 0.6 inches or greater require immediate replacement.
- If cracks are found, monitor growth at specified intervals.
- Ensure proper grounding of the aircraft before inspection.
- Follow all maintenance manual instructions for removal and installation.
Full document text
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 14 No. 107/57-005 DATE: May 3, 2016 Subject: Wing Spacer Plate – Inspection and Replacement of Effectivity: MU-2B-25/-26/-26A/-40: S/N 313SA, 321SA, 348SA through 459SA MU-2B-36A/-60: S/N 661SA, 697SA through 1569SA Purpose: To ensure the continued airworthiness of the wing structures, conduct a one-time fluorescent penetrant inspection for the wing spacer plates and replace them, if necessary. Background: As part of aging aircraft program, one-piece and three-piece main wings were subject of detailed teardown inspections, and cracks were found in the wing spacer plates attached to the forward lower spar at W.STA580. The cracks resulted from fatigue to be caused by flight load. Compliance: Mandatory Approval: Engineering aspects of this Service Bulletin are FAA Approved Time of Compliance: a) For aircraft with flight time 7,500 hours or over - within 200 hours, or 12 months whichever comes first after receipt of this Service Bulletin. b) For aircraft with flight time less than 7,500 hours - to be include in 7,500 hours inspection. Responsible Agency of Compliance: MU-2 Owners/Operators Disposition of Removed Parts: Scrap Spare Parts Affected: Replacement Kit (P/N 035A-900021-101/-102) Required Man Hours: Inspection ~approximately 4 man hours for each side Replacement ~approximately 40 man hours for each side excluding preparation and restoration Special Tools Required: None Weight and Balance Change: Negligible Flight Manual Revision: None MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 2 of 14 INSTRUCTIONS Refer to applicable Maintenance Manual, Illustrated Parts Catalog and Structural Repair Manual to comply with this Service Bulletin. 1. INSPECTION PROCEDURE NOTE Identify and store all removed parts and attaching hardware. If it is necessary to remove further parts for access, inspection and replacement, you can remove those parts beyond following process. If you can access, inspect and replace without removing the parts instructed in following process, it is not necessary to remove the parts. 1.1 PREPARATION (1) Electrically ground the aircraft. (2) Remove the wing center lower fillet and the inner wing leading edge in accordance with applicable Maintenance Manual. (3) Remove sealant and primer from the inspection area between the spacer plate and the skin with a nonmetallic scraper. See Figure 1 and 2. (4) Clean and expose the inspection surface. 1.2 INSPECTION (1) Conduct a fluorescent penetrant inspection to the inspection area shown in Figure 1 and 2 on both left and right sides of wing in accordance with applicable Maintenance Manual. NOTE Personnel performing fluorescent penetrant inspection must be qualified and certified as a Level II or higher based on the requirements of National Aerospace Standard NAS410 or equivalent standard. (a) When a crack of 0.6 inches or greater is found Replace the discrepant spacer plate with a new improved spacer plate (P/N 017A-11102-13/-14) and scrap the discrepant spacer plate. Replacement procedure is instructed in Section 2. (b) When a crack of less than 0.6 inches is found It is allowed to monitor the crack growth by repetitive inspection at the interval of 600 hours. However, the spacer plate must be replaced when the crack length grows beyond 0.6 inches. 1.3 RESTORATION (1) Clean up the inspection area and apply Alodine and zinc chromate primer. (2) Apply sealant to fill the gaps between the spacer plates and the skin in accordance with applicable Maintenance Manual. (3) Restore the inner leading edge. (4) Restore the wing center lower fillet. MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 3 of 14 2. REPLACEMENT PROCEDURE NOTE Replacement Kit may be purchased from Mitsubishi Heavy Industries America, Inc. (MHIA) through Mitsubishi MU-2 Authorized Service Center Network. Replacement of the spacer plate should be conducted in accordance with the installation drawing contained in Replacement Kit. 2.1 PREPARATION NOTE Removal of the engines, each system, the wing and the other attaching hardware should be accomplished in accordance with applicable Maintenance Manual. (1) Electrically ground the aircraft. (2) Drain fuel and purge fuel tanks. (3) Remove all wing-fuselage fillets, the fuel system, the engines, the air conditioning and wing de-icer system, the electrical and instrument system, and the flight control system from the wing. (4) Remove the wing and set appropriate support. (5) Remove the inner wing leading edge. (6) Remove the shut off valves. (7) Remove the fuel tank access doors. 2.2 REPLACEMENT (1) Remove sealant inside the integral tank with a nonmetallic scraper. (2) Remove the outer wing-fuselage fitting and the inner support fitting. If shims are installed, record thickness and location, and store. (3) Drill out and cut off the fasteners on and around the spacer plate. NOTE Several tack rivets and a nut plate are hidden under the skin and sealant as shown in Figure 4. Be careful not to damage adjacent structural components when removing the spacer plate. (4) Peel up the skin and slide out the spacer plate from the wing. (5) Remove remaining sealant inside of the integral tank. Clean up the integral tank and the outer wing-fuselage fitting and the inner support fitting. (6) Duplicate all fastener holes to a new spacer plate from the removed spacer plate. Do not apply countersink to the holes for tack rivets and nut plate installing rivets. (7) Temporary locate the new spacer plate and drill out the holes for tack rivets to the skin by picking up the existing tack rivet holes on spar through the new spacer plate. (8) Drill out the holes for nut plate installing rivets to the skin by picking up the existing holes on spar through the new spacer plate. (9) Remove the new spacer plate and clean up. MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016
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Page 4 of 14 (10) Apply sealant to the new spacer plate and the existing structure where sealant should be applied before fastening in accordance with the installation drawing (refer to Figure 5), and locate the spacer plate. (11) Install all fasteners to the spacer plate, a nut plate and tack rivets in accordance with the installation drawing (refer to Figure 3 and 4). (12) Adjust the gap between the outer wing-fuselage fitting and the spacer plate with laminated shim within 0.005 inches (refer to Figure 3). (13) Touch up the laminated shim with zinc chromate primer. (14) Install the outer wing-fuselage fittings and the inner support fitting. (15) Clean up inside and outside of the integral tank. (16) Apply integral tank sealant and dry in accordance with applicable Maintenance Manual and the installation drawing (refer to Figure 5). (17) Apply sealant to fill the gaps between the spacer plate and the skin shown by the hatched area in Figure 2 in accordance with applicable Maintenance Manual. 2.3 FUEL LEAKAGE CHECK (1) Conduct the integral tank leakage test in accordance with applicable Maintenance Manual. (2) If fuel leakage is found, rework sealing. 2.4 RESTORATION NOTE Restoration of the disrupted systems, including rigging and operational tests, should be accomplished in accordance with applicable Maintenance Manual. (1) Install the fuel tank access doors. (2) Install the fuel shut off valves. (3) Install the inner wing leading edge. (4) Install the wing. (5) Install the flight control system, the electrical and instrument system, the air conditioning and wing de-icer system, the engines, the fuel system and all wing-fuselage fillets. (6) Refuel full and check no leakage. 3. RECURRING INSPECTION (1) If no crack is found during the inspection, repeat the inspection in accordance with the revised Maintenance Requirement Manual at the interval of 2,000 hours. (2) If the crack of less than 0.6 inches is found, repeat the inspection at the interval of 600 hours for crack growth monitoring in accordance with this Service Bulletine. When the crack length exceeds 0.6 inches, replace the cracked spacer plate with a new improved spacer plate. (3) Once the spacer plate is replaced with a new improved spacer plate (P/N 017A-11102-13/-14), recurring (repetitive) inspection is not required. MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 5 of 14 4. LOGBOOK ENTRY Upon completion of this Service Bulletin, make an appropriate maintenance entry in the logbook similar to “Service Bulletin No. 107/57-005 complied with on (date) by (name), number/stamp.” 5. COMPLETION Complete the enclosed compliance card and mail back to Mitsubishi Heavy Industries America, Inc. in care of Turbine Aircraft Services, Inc. Turbine Aircraft Services, Inc. 4550 Jimmy Doolittle Drive Addison, Texas 75001 Attention: Manager, Publications Phone: (972) 248-3108 X 209 Fax: (972) 248-3321 MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 6 of 14 Parts and Material Required The following parts and material are required to comply with this Service Bulletin. Replacement Kit may be purchased from Mitsubishi Heavy Industries America, Inc. (MHIA) through Mitsubishi MU-2 Authorized Service Center Network. All the parts and material except for Replacement Kit may be procured locally. PART NUMBER DESCRIPTION QTY/SHIP REMARKS LH (-101) RH (-102) KIT number 035A-900021-101 to replace LH spacer plate KIT number 035A-900021-102 to replace RH spacer plate 035A-11076 DRAWING 1 1 017A-11102-13 SPACER PLATE 1 017A-11102-14 SPACER PLATE 1 017A-11102-15 LAMINATED SHIM 1 1 800-0115-10 LOCK-O-SEAL 14 14 change PN of 800-015-10 NAS1149D0363H WASHER 14 14 NAS1149D0316H WASHER 4 4 MS20002C7 WASHER 2 2 MS20002-7 WASHER 2 2 NAS679A3W NUT 16 16 H20-7 NUT 2 2 NAS1473A3 DOME NUT 1 1 MS20426AD3-10 RIVET 4 4 not contained in the KIT MS20426AD4-5 RIVET 6 6 not contained in the KIT MS20426AD5-12 RIVET 9 9 not contained in the KIT MS20426AD5-7 RIVET 3 3 not contained in the KIT MS20470AD3-10 RIVET 2 2 not contained in the KIT MS20470AD3-11 RIVET 2 2 not contained in the KIT MS20470AD3-7 RIVET 1 1 not contained in the KIT MS20470AD4-5 RIVET 15 15 not contained in the KIT MS20470AD5-12 RIVET 11 11 not contained in the KIT MS20470AD5-13 RIVET 6 6 not contained in the KIT MS20470AD5-7 RIVET 9 9 not contained in the KIT MS20470AD5-9 RIVET 6 6 not contained in the KIT NAS1097AD4-9 RIVET 16 16 not contained in the KIT AMS-S-8802 Class A or equivalent SEALANT AR AR not contained in the KIT AMS-S-8802 Class B or equivalent SEALANT AR AR not contained in the KIT TT-P-1757 or equivalent PRIMER AR AR not contained in the KIT MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 7 of 14 Figure 1: LOCATION OF SPACER PLATE INSPECTION (Typical, LH side shown, RH side opposite.) OUT B/D (LH) FWD LKG UP Spacer plate OUT B/D (LH) FWD LWR Web Outer wing-fuselage fitting Spar Skin Skin Sealant Crack Spacer plate Inspection area Crack MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 8 of 14 Figure 2: DETAILED INSPECTION AREA OF SPACER PLATE (Typical, LH side shown, RH side opposite.) Skin Skin Skin Spacer plate Spacer plate Outer wing-fuselage fitting Spar Spar Crack Hatched area is filled with sealant A A SECTION A-A Crack Inspection area FWD OUT B/D (LH) LKG UP UPR OUT B/D (LH) W.S. 580 W.S. 520 MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 9 of 14 Figure 3: INSTALLATION OF NEW SPACER PLATE (1/2) (Typical, LH side shown, RH side opposite.) Spacer plate MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 10 of 14 Figure 3: INSTALLATION OF NEW SPACER PLATE (2/2) (Typical, LH side shown, RH side opposite.) Spacer plate Laminated shim Outer wing-fuselage fitting Inner support fitting Shim MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 11 of 14 Figure 4: INSTALLATION OF TACK RIVET AND NUT PLATE (Typical, LH side shown, RH side opposite.) Tack rivet Tack rivet Nut plate 7 8 9 Note: Tack rivets and a nut plate are installed under the skin originally. MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 12 of 14 Figure 5: SEALING INSTRUCTION (1/3) (Typical, LH side shown, RH side opposite.) MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 13 of 14 Figure 5: SEALING INSTRUCTION (2/3) (Typical, LH side shown, RH side opposite.) MU-2 Service Bulletin No. 107/57-005 DATE: May 3, 2016 Page 14 of 14 Figure 5: SEALING INSTRUCTION (3/3) (Typical, LH side shown, RH side opposite.)