Airworthiness directives › 2015-04-05
AD 2015-04-05 Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters
Applicability*9
This AD becomes effective March 12, 2015.
Compliance
(1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Schwetz, Aviation Safety Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238-7761; email michael.schwetz@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
Required actions
Joint Aircraft Service Component (JASC) Code: 6510 Tail Rotor Drive Shaft.
Unsafe condition
Within 30 hours time-in-service: (1) Inspect each TDS flange attachment hardware at all four locations for looseness and torque stripe misalignment as depicted in Figure 1 and shown in Figure 2 of Sikorsky Aircraft Corporation Alert Service Bulletin ASB 76-66-52, Basic Issue, dated April 1, 2014 (ASB). Inspect each nut to determine whether it can be rotated by hand. Determine whether the hardware is assembled correctly by following the Accomplishment Instructions, paragraph B.(3)(a) through B.(3)(b) of the ASB. Determine the torque of each nut. (2) If there is no looseness, torque stripe misalignment, incorrect hardware assembly, and if no nut can be rotated by hand and the torque of any nut is not less than 105 inch-pounds, no further action is required by this AD. (3) If there is looseness, torque stripe misalignment, incorrect hardware assembly, a nut rotated by hand, or the torque of any nut is less than 105 inch-pounds, do the following: (i) Apply an index mark to the flange and shaft to make sure the flange is reinstalled in the same position and to maintain shaft balance, unbolt and remove the flange from the shaft, and visually inspect each radius washer for wear or fretting. Replace any washer with wear or fretting. (ii) Inspect the flange and shaft for a crack, fracture, wear on the mounting hole, and diameter by following the Accomplishment Instructions, paragraph 3.D.(5)(a) through 3.D.(5)(e), of the ASB. If the flange and shaft fail any of the inspection criteria, before further flight, replace the TDS with an airworthy TDS. (iii) Align index marks, install the flange on the shaft, and coat the grip length of each bolt and the contact surfaces on each radius washer and washer with epoxy polyamide primer. (iv) Torque each nut by following either paragraph D.(9) or D.(10) of the Accomplishment Instructions of the ASB.
Affected ADs
This AD defines the unsafe condition as loose or fractured TDS flange-to-shaft attachment hardware. This condition could result in loss of a tail rotor drive and subsequent loss of control of the helicopter.
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