AD 2018-19-09 Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters

This AD replaces AD 2017-14-03, Amendment 39-18947 (82 FR 34838, July 27, 2017).

(1) Before further flight, remove from service any part that has accumulated the number of landing cycles listed in Table 1 to paragraph (f)(1) of this AD. Thereafter, remove from service any part before accumulating the number of landing cycles listed in Table 1 to paragraph (f)(1) of this AD. For purposes of this AD, a landing cycle is counted anytime the helicopter lifts off into the air and then lands again regardless of the duration of the landing and regardless of whether the engine is shut down. If the number of landing cycles in unknown, multiply the number of hours time-in-service by 4.5 to determine the number of landing cycles. Table 1 to Paragraph ( f )(1) Part name Part No. (P/N) Life limit Main landing gear (MLG) wheel axle 2392-2334-001 22,300 landing cycles. MLG or nose landing gear (NLG) threaded hinge pin 2392-2311-003 26,100 landing cycles. NLG cylinder 2392-4006-005 26,300 landing cycles. NLG hinge pin 2392-4312-003 26,700 landing cycles. Landing gear actuator rod end 2392-0876-901 41,700 landing cycles. MLG cylinder 2392-2006-005 76,300 landing cycles. MLG pin outboard 2392-2312-003 50,300 landing cycles. MLG bulkhead (left-hand side) 92201-08111-105 92201-08111-107 92201-08111-109 58,400 landing cycles. MLG bulkhead (right-hand side) 92201-08111-106 92201-08111-108 92201-08111-110 58,400 landing cycles. (2) For helicopters with 31,600 or more landing cycles and an NLG airframe fitting assembly P/N 92209-01101-041 installed, before further flight and thereafter at intervals not to exceed 1,989 landing cycles: (i) Using a 10X or higher power magnifying glass, inspect each bushing (P/N 92209-01101-102 and P/N 92209-01101-103) and all visible surfaces of mating lug fittings adjacent to each bushing for fretting, corrosion, wear, and scratches. If there is fretting, corrosion, wear, or a scratch more than 0.0005 inch deep, replace the NLG airframe fitting assembly before further flight. (ii) Ultrasonic inspect each NLG actuator fitting P/N 92209-01101-101 in accordance with Sikorsky Ultrasonic Inspection Technique No. UT 5077, Revision 0, dated July 25, 2014 (UT 5077), except you are not required to report to or contact Sikorsky. If there are any anomalies or suspect indications, replace the NLG actuator fitting before further flight. Note 1 to paragraph (f)(2)(ii) of this AD: A copy of UT 5077 is attached to Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-004, Basic Issue, dated January 30, 2015.

(1) The Manager, Boston ACO Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Dorie Resnik, Aviation Safety Engineer, Boston ACO Branch, Compliance and Airworthiness Division, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238-7693; email dorie.resnik@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.

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.

This AD defines the unsafe condition as fatigue failure of the landing gear. This condition could result in failure of the landing gear and subsequent damage to and loss of control of the helicopter.