2016-08-19: Landing Gear

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new AD: 2016-08-19 Mitsubishi Heavy Industries, Ltd.: Amendment 39-18496; Docket No. FAA-2016-1363; Directorate Identifier 2015-CE-040-AD. (a) Effective Date This airworthiness directive (AD) becomes effective June 6, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Mitsubishi Heavy Industries, Ltd. Models MU- 2B-30, MU-2B-35, and MU-2B-36 airplanes, serial numbers 502 through 696, except 652 and 661, and Models MU-2B-36A and MU-2B-60 airplanes, serial numbers 661SA, and 697SA through 1569SA, certificated in any category. (d) SubjectAir Transport Association of America (ATA) Code 32: Landing Gear. (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as reports of cracks found in the upper attach fittings of the main landing gear oleo strut. We are issuing this AD to prevent failure of the main landing gear oleo strut attach fitting, which could cause the landing gear to fail and result in loss of control. (f) Actions and Compliance Unless already done, do the following actions: (1) Within the next 100 hours time-in-service (TIS) after June 6, 2016 (the effective date of this AD) or within the next 6 months after June 6, 2016 (the effective date of this AD), whichever occurs first, do a visual inspection of the main landing gear oleo upper attach fittings for cracks. Do the inspection following the INSTRUCTIONS section in Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin No. 243, dated June 30, 2015, and the INSTRUCTIONS section in Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin No. 105/32-017, dated September 29, 2015, as applicable. (2) Before further flight after the inspection required in paragraph (f)(1) of this AD, if no signs of cracks are found, lubricate the pin assembly attached to the main landing gear oleo attach fitting as specified in Mitsubishi Heavy Industries, Ltd. MU- 2 Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated April 27, 2012. (3) Within the next 100 hours TIS after doing the initial visual inspection required in [[Page 26099]] paragraph (f)(1) of this AD or within the next 12 months after doing the initial visual inspection required in paragraph (f)(1) of this AD, whichever occurs first, do an ultrasound inspection of the main landing gear oleo upper attach fittings for cracks as specified in Mitsubishi Heavy Industries, Ltd. MU-2 Service News JCAB T.C.: No. 176, FAA T.C.: No. 128/32-013, dated July 18, 2013. This ultrasound inspection may also be done in place of the visual inspection required in paragraph (f)(1) of this AD if done within the next 100 hours TIS after June 6, 2016 (the effective date of this AD) or within the next 6 months after June 6, 2016 (the effective date of this AD), whichever occurs first. Repetitively thereafter ultrasound inspect the attach fittings every 600 hours TIS or 36 months, whichever occurs first, and any time a hard landing or overweight landing occurs. (4) Before further flight after any inspection required in paragraph (f)(3) of this AD, if no signs of cracks are found, lubricate the pin assembly attached to the main landing gear oleo attach fitting as specified in Mitsubishi Heavy Industries, Ltd. MU- 2 Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated April 27, 2012, and Mitsubishi Heavy Industries, Ltd. MU-2 Service News JCAB T.C.: No. 176, FAA T.C.: No. 128/32-013, dated July 18, 2013. (5) Before further flight after any inspection required in paragraph (f)(1) and (f)(3) of this AD where cracks are found, replace the main landing gear oleo upper attach fittings following the INSTRUCTIONS section in Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin No. 243, dated June 30, 2015, and the INSTRUCTIONS sections in Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin No. 105/32-017, dated September 29, 2015, as applicable. After replacement, continue with the repetitive ultrasound inspection requirements of paragraph (f)(3) and lubrication requirements of paragraph (f)(4) of this AD. (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Andrew McAnaul,Aerospace Engineer, FAA, ASW- 143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; email: andrew.mcanaul@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (h) Related Information Refer to MCAI Japan Civil Aviation Bureau (JCAB) AD No. TCD- 8585-2015, dated July 1, 2015, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2016-1363. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin No. 105/32-017, dated September 29, 2015. (ii) Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin No. 243, dated June 30, 2015. (iii) Mitsubishi Heavy Industries, Ltd. MU-2 Service News JCAB T.C.: No. 176, FAA T.C.: No. 128/32-013, dated July 18, 2013. (iv) Mitsubishi Heavy Industries, Ltd. MU-2 Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated April 27, 2012. (3) For Mitsubishi Heavy Industries, Ltd service information identified in this AD, contact Mitsubishi Heavy Industries America, Inc., c/o Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; telephone: (972) 248-3108, ext. 209; fax: (972) 248-3321; Internet: http://mu-2aircraft.com. (4) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. In addition, you can access this service information on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-1363. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.