Airworthiness directives › 2013-22-15
AD 2013-22-15 Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters
Applicability*9
This AD becomes effective December 13, 2013.
Compliance
Special flight permits will not be issued.
Required actions
(1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Nicholas Faust, Aviation Safety Engineer, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238-7763; email nicholas.faust@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.
Unsafe condition
Within 150 hours time-in-service (TIS): (1) For each spindle cuff assembly or blade cuff assembly with 1,900 or more hours TIS, conduct a nondestructive inspection (NDI) by following the Accomplishment Instructions, paragraph 3.B., of Sikorsky S-76 Alert Service Bulletin ASB 76-65-67A, Revision A, dated July 18, 2012 (ASB), except this AD does not require you to contact Sikorsky Aircraft Corporation. This inspection must be done by a level 2 or higher technician with National Aerospace Standard 410 or equivalent certification. (2) For each spindle cuff assembly or blade cuff assembly with less than 1,900 hours TIS, visually inspect the area indicated in Figure 4 of the ASB as “white paint application area” for a crack by using a 5x or higher power magnifying glass. (3) If there is a crack, before further flight, replace the cracked part. (4) If there is no crack, apply white paint by following the Accomplishment Instructions, paragraph 3.D., of the ASB. (5) Do not install an affected spindle cuff assembly or blade fold cuff assembly on any helicopter unless it has been inspected in accordance with paragraphs (e)(1) through (e)(4) of this AD.
Affected ADs
This AD defines the unsafe condition as a crack in a spindle cuff assembly or blade fold cuff assembly. This condition could result in failure of a spindle cuff assembly or blade fold cuff assembly, loss of a rotor blade, and subsequent loss of control of the helicopter.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1