AD 2012-26-06 Airworthiness Directives; Sikorsky Aircraft-Manufactured Model S-64F Helicopters

This AD supersedes AD 97-10-15, Amendment 39-10028 (62 FR 28321, May 23, 1997).

(1) Before further flight: (i) Remove from service any part with a number of hours time-in-service (TIS) equal to or greater than the part's retirement life as stated in Table 1 to Paragraph (f) of this AD. Table 1 to Paragraph ( f )—Parts With New or Revised Life Limits Part name Part No. (P/N) Retirement life Main Rotor (M/R) Blade Assembly 6415-20601-045 13,280 hours TIS. Main Transmission Support Beam Assembly, LH 6420-62363-045 9,300 hours TIS. Main Transmission Support Beam Assembly, RH 6420-62363-046 9,300 hours TIS. Left Splice Fitting (Transition Fitting), Rotary, Rudder Boom 6420-66341-101 8,300 hours TIS. Right Splice Fitting (Transition Fitting), Rotary, Rudder Boom 6420-66341-102 8,300 hours TIS. M/R Drive Shaft 6435-20536-101 2,200 hours TIS. Pressure Plate Assembly, Rotary Wing Head 65101-11016-042 8,800 hours TIS. Horn and Liner Assembly 65102-11047-041 1,140 hours TIS. Lower Hub Plate Assembly 65103-11009-041 15,500 hours TIS. Horizontal Hinge Pin, Rotary Wing Head 65103-11020-103 5,100 hours TIS. Damper Bracket Assembly, Rotary Wing Head 65103-11032-043 20,000 hours TIS. Hub Subassembly, Rotary Wing 65103-11310-043 21,600 hours TIS. Shaft Assembly, Pitch Control Tail Gearbox 65358-07035-043 9,400 hours TIS. Rod End Assembly, Primary Servo Assembly 65652-11212-041 20,800 hours TIS. Note 1 to Table 1 to Paragraph (f) of this AD: The list of parts in Table 1 to Paragraph (f) of this AD contains only a portion of the life-limited parts for this model helicopter and is not an all-inclusive list. (ii) Revise the retirement life of each part as shown in Table 1 to Paragraph (f) of this AD by making pen and ink changes or by inserting a copy of this AD into the Airworthiness Limitations section of the maintenance manual. (iii) Record on the component history card or equivalent record the retirement life for each part as shown in Table 1 to Paragraph (f) of this AD. (2) Before further flight, remove from service any part with a P/N listed in Table 2 to Paragraph (f) of this AD, regardless of the part's TIS. The P/Ns listed in Table 2 to Paragraph (f) of this AD are not eligible for installation on any helicopter. Table 2 to Paragraph ( f )—Parts To Be Removed From Service Part name P/N Spindle Assembly, Rotary Rudder 6410-30302-041. Main Gearbox Second Stage Lower Planetary Plate 6435-20516-101 or 6435-20516-102. Bracket Assembly, Main Servo 6435-20527-041 or 6435-20527-042. Primary Servo Link, Tandem Servo, M/R 6465-62161-042. Shoulder Bolt, Tail Rotor (T/R) 65111-07001-102. T/R Blade Assembly 65161-00001-041. (3) Before further flight, if a T/R blade assembly, P/N 65160-00001-048, is installed, remove any of the other three T/R blade assemblies that have a different P/N and replace it with a T/R blade assembly, P/N 65160-00001-048. The T/R blade assembly, P/N 65160-00001-048, must be installed in sets of four only.

(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, Fort Worth, Texas 76137, telephone (817) 222-5170, email 7-avs-asw-170@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 a fatigue crack in a flight critical component. This condition could result in component failure from static overload and subsequent loss of control of the helicopter.