2012-23-13: Engine Oil Cooler, Main Rotor Blades, Tail Rotor Head, Tail Rotor Blades, Tail Rotor Control System, Main Landing Gear Strut/Axle/Truck, Fuel Transfer Valve, and Fasteners

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 adding the following new airworthiness directive (AD): 2012-23-13 Sikorsky Aircraft Corporation: Amendment 39-17269; Docket No. FAA-2012-1206; Directorate Identifier 2012-SW-021-AD. (a) Applicability This AD applies to Model S-70, S-70A, and S-70C helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as fatigue failure of a main rotor blade, tail rotor blade, planetary carrier assembly, tail rotor servo, elastomeric sleeve bearing, main landing gear shock strut piston cylinder, crossfeed valve, oil cooler axial fan ball bearing assembly, dowelpin, main rotor hub, or right tie attach bolt remaining in service beyond its life limit. This condition could result in loss of control of the helicopter. (c) Effective Date This AD becomes effective December 14, 2012. (d) 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. (e) Required Action Before further flight: (1) Establish or reduce the retirement life of the following parts listed in Table 1-1 of the Sikorsky Technical Manual TM 1-70- 23AW-2, change 3, section 1.1, Airworthiness Limitations, by inserting a copy of Table 1-1 into the Airworthiness Limitations section of TM 1-70-23AW-2 or by making the following pen and ink changes to the Airworthiness Limitations of the maintenance manual: (i) For each dowel pin on the main transmission housing, part number (P/N) NAS607-10-12P, NAS607-12-14P, and NAS607-12-18P, establish a life limit of 3,000 hours time-in-service (TIS). (ii) For elastomeric sleeve bearing, P/N SB5203-202, establish a life limit of 720 hours TIS. (iii) For right tie rod attach bolt, P/N SS5025-04H010, establish a life limit of 3,500 hours TIS. (iv) For right tie rod attach bolt, P/N SS5025-04H10, establish a life limit of 5,000 hours TIS. (v) For oil cooler axial fan ball bearing, P/N 210SFFC, installed in oil cooler axial fans, P/N 70361-03005-103 through - 106, establish a life limit of 2,000 hours TIS; and for bearings installed in oil cooler axial fan, P/N 70361-03005-107, establish a life limit of 2,500 hours TIS. (vi) For oil cooler axial fan ball bearing, P/N 210SFFC-0129, installed in oil cooler axial fan, 70361-03005-103 through -106, establish a life limit of 2,000 hours TIS; and for bearings installed in oil cooler axial fan, P/N 70361-03005-107, establish a life limit of 2,500 hours TIS. [[Page 71089]] (vii) For main rotor hub, P/N 70070-10046-055, establish a life limit of 5,100 hours TIS. (viii) For main rotor blade, P/N 70080-15001-041, establish a life limit of 5,000 hours TIS. (ix) For tail rotor blade, P/N 70080-15002-041, establish a life limit of 5,000 hours TIS. (x) For main rotor blade, P/N 70080-15003-041, establish a life limit of 5,000 hours TIS. (xi) For tail rotor blades, P/N 70080-15004-041 and P/N 70080- 15005-041, establish a life limit of 5,000 hours TIS. (xii) For main landing gear shock strut piston assembly, P/N 70250-12067-102, establish a life limit of 9,000 hours TIS. (xiii) For Number 2 crossfeed breakaway valve, P/N 70307-03006- 103, establish a life limit of 1,500 hours TIS. (xiv) For main module planetary carrier assembly, P/N 70351- 08175-043, -044, and -045, establish a life limit of 1,400 hours TIS; and for P/N 70351-08175-046 establish a life limit of 12,000 hours TIS. (xv) For dowel pins, P/N 70351-08404-101, -102, and -103 on main transmission housings, P/N 70351-08110-044 and -045, establish a life limit of 3,000 hours TIS; for dowel pins, P/N 70351-08404-101, -102, -103, and -104 on main transmission housings, P/N 70351-28110- 043 and -044, establish a life limit of 7,300 hours TIS; for dowel pins, P/N 70351-08404-101, -103, and -104, on main transmission housings, P/N 70351-38110-043, -044, and -045, establish a life limit of 11,000 hours TIS. (xvi) For dowel pin, flight control support mounting to main transmission housing, P/N 70531-04805-101, 70531-04805-102, and 70531-08405-103, establish a life limit of 3,000 hours TIS. (xvii) For dowel pin, flight control support mounting to transmission case, P/N 70351-28404-101, on main transmission housings, P/N 70351-08110-044 and -045, reduce the life limit from 4,300 hours TIS to 3,000 hours TIS. (xviii) For main module planetary carrier assembly, P/N 70351- 38175-041, establish a life limit of 6,500 hours TIS. (xvix) For dowel pin, flight control support mounting to transmission case, P/N 70351-38404-101, on main transmission housings, P/N 70351-38110-043, -044, and -045, reduce the life limit from 20,000 hours TIS to 11,000 hours TIS. (xx) For the tail rotor servo, P/N 70410-06520-044, -045, and - 046, establish a life limit of 15,000 hours TIS. (2) Remove from service any part with a number of hours time-in- service equal to or greater than the part's retirement life as stated in paragraph (e)(1) of this AD. (f) Special Flight Permit Special flight permits to allow flight in excess of life limits will not be issued. (g) Alternative Methods of Compliance (AMOC) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Davison, Flight Test Engineer, New England Regional Office, 12 New England Executive Park, Burlington, MA 01803; phone: (781) 238-7156; email: michael.davison@faa.gov. (2) For operations conducted under 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) Subject Joint Aircraft Service Component (JASC) Codes: 7921 Engine Oil Cooler, 6210 Main Rotor Blades, 6320 Tail Rotor Head, 6410 Tail Rotor Blades, 6720 Tail Rotor Control System, 3213 Main Landing Gear Strut/Axle/Truck, 2824 Fuel Transfer Valve, and 1430 Fasteners.