2012-26-06: Main Rotor Drive System and Tail Rotor System

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 removing Amendment 39-10028 (62 FR 28321, May 23, 1997) and adding the following new airworthiness directive (AD): 2012-26-06 ERICKSON AIR-CRANE INCORPORATED: Amendment 39-17301; Docket No. FAA-2012-0689; Directorate Identifier 2009-SW-065-AD. (a) Applicability This AD applies to Sikorsky Aircraft Corporation-manufactured Model S-64F helicopters, now under the Erickson Air-Crane Incorporated Model S-64F type certificate, certificated in any category. (b) Unsafe Condition 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. (c) Other Affected ADs This AD supersedes AD 97-10-15, Amendment 39-10028 (62 FR 28321, May 23, 1997). (d) Effective Date This AD becomes effective April 16, 2013. (e) Compliance 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. (f) Required Actions (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), 6420-66341-101 8,300 hours TIS. Rotary, Rudder Boom. Right Splice Fitting (Transition Fitting), 6420-66341-102 8,300 hours TIS. Rotary, Rudder Boom. 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 historycard 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. ---------------------------------------------------------------------------------------------------------------- [[Page 15602]] (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. (g) Alternative Methods of Compliance (AMOCs) (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. (h) Additional Information Erickson Service Bulletin No. 64F General-1, Revision 17, dated August 17, 2010, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance Officer, 3100 Willow Springs Rd, P.O. Box 3247, Central Point, OR 97502, telephone (541) 664-5544, fax (541) 664-2312, email address cerickson@ericksonaircrane.com. You may review a copy of this information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.(i) Subject Joint Aircraft Service Component (JASC) Code: 6300: Main Rotor Drive System and 6400: Tail Rotor System.