2013-20-15: Tail Rotor Drive 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 Airworthiness Directive (AD) 97-19-10, Amendment 39-10130 (62 FR 47933, September 12, 1997), and adding the following new AD: 2013-20-15 SIKORSKY AIRCRAFT CORPORATION-MANUFACTURED (SIKORSKY) MODEL HELICOPTERS (TYPE CERTIFICATE CURRENTLY HELD BY ERICKSON AIR- CRANE INCORPORATED): Amendment 39-17621; Docket No. FAA-2013-0454; Directorate Identifier 2009-SW-81-AD. (a) Applicability This AD applies to Sikorsky Model CH-54A helicopters, now under the Erickson Air-Crane Incorporated (Erickson) Model S-64E type certificate, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as fatigue cracking in a flight critical component, failure of the component, and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 97-19-10, Amendment 39-10130 (62 FR 47933, September 12, 1997). [[Page 65165]] (d) Effective Date This AD becomes effective December 5, 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, for each part listed in Table 1 to paragraph (f) of this AD: (i) Remove any part that has reached or exceeded its newly established or revised retirement life. (ii) Record the newly established or revised retirement life for each part on the component history card or equivalent record. (iii) Make pen and ink changes or insert a copy of this AD into the Airworthiness Limitations section of the maintenance manual to establish or revise the retirement life for each part that is listed in Table 1 to paragraph (f) of this AD. Table 1 to Paragraph (f) of This AD--Parts With New or Revised Life Limits ------------------------------------------------------------------------ Part name Part No. (P/N) Retirement life ------------------------------------------------------------------------ Rod and bushing assembly, 6410-21090-012...... 5,700 hours time-in- main rotor (M/R). service (TIS) or 60 months since the initial installation on any helicopter, whichever occurs first. Rod and bushing assembly, M/ 6410-21090-013 or - 5,700 hours TIS. R. 014. Lower plate, M/R hub........ 6410-23009-102...... 3,000 hours TIS. Upper plate, M/R hub........ 6410-23011-102...... 3,000 hours TIS. Swashplate, rotating, M/R... 6410-24002-101...... 12,860 hours TIS. Piston rod.................. 6410-26005-104...... 10,500 hours TIS. Cylinder, damper assembly... 6410-26215-101...... 7,300 hours TIS. M/R blade................... 6415-20201-045 or - 3,300 hours TIS. 047. M/R blade................... 6415-20201-048, - 20,000 hours TIS. 049, -050, or -051. Truss assembly, stabilizer.. 6420-66250-041...... 4,720 hours TIS. M/R shaft assembly (includes 6435-20078-014 or - 2,600 hours TIS. shaft, P/N 6435-20078-104). 015. M/R shaft assembly (includes 6435-20078-016...... 5,000 hours TIS. shaft, P/N 6435-20078-105). Second stage planetary plate 6435-20231-012, - 1,300 hours TIS. assembly, main gearbox 014, or -015. assembly. Second stage planetary plate 6435-20231-016...... 2,600 hours TIS. assembly, main gearbox assembly. Oil cooler and support 6435-60050-044...... 9,885 hours TIS. assembly. Tail rotor (T/R) blade...... 65160-00001-042, - 23,300 hours TIS. 045, or -048. T/R blade................... 65161-00001-042..... 23,300 hours TIS. Hub, M/R.................... S1510-23001-005..... 3,000 hours TIS. Spindle assembly, M/R....... S1510-23027-5....... 5,675 hours TIS. Horn assembly, M/R.......... S1510-23350-4, -6, 9,710 hours TIS. or -8. Sleeve, M/R................. S1510-23351-2....... 12,930 hours TIS. Sleeve lockwasher, M/R...... S1510-23458-0....... 2,700 hours TIS. Cuff, M/R blade............. S1515-20320-0....... 6,410 hours TIS. Cuff, M/R blade............. S1515-20320-001 or - 12,930 hours TIS. 002. Piston assembly, M/R tandem S1565-20443-0 or 8,100 hours TIS. servo. S1565-20443-301. Fork assembly, M/R tandem S1565-20449 or S1565- 8,100 hours TIS. servo. 20449-301. Bearing, T/R drive shaft.... SB1111-004 or -601.. 1,000 hours TIS or 12 months while installed on any helicopter, whichever occurs first. ------------------------------------------------------------------------ Note 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. (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 part numbers listed in Table 2 to paragraph (f)(2) of this AD are not eligible for installation on any helicopter. Table 2 to Paragraph (f) of This AD--Parts To Be Removed From Service ------------------------------------------------------------------------ Part name P/N ------------------------------------------------------------------------ Rod and bushing assembly, M/R 6410-21090-011. M/R blade.................... 6415-20001-013, -014, or -015. Pylon stabilizer............. 6420-66201-010, -014, or -015. M/R shaft assembly........... 6435-20078-013. Oil cooler and support 6435-60050-043. assembly. Pitch change link, rotary 65113-07100-046. rudder. Spindle, M/R blade........... S1510-23070-3. ------------------------------------------------------------------------ (3) Within 20 hours TIS, and thereafter at intervals not to exceed 20 hours TIS, visually inspect each M/R servo and control arm assembly, P/N S1565-20421-10, -11, -041, or -043, and determine if there is any oil leaking from the M/R tandem servo housing assembly (servo housing), P/N S1565-20252-2. If there is any oil leaking from the servo housing, before further flight, replace the M/R servo and control arm assembly. (4) Within 20 hours TIS or before reaching 1,120 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 200 hours TIS or 12 months, whichever occurs first, ultrasonic (UT) inspect each M/R hub horizontal hinge pin (hinge pin), P/N S1510- 23099-1 or P/N S1510-23099-001, for a crack in accordancewith the [[Page 65166]] Accomplishment Instructions, paragraphs 2.A through 2.C, of Erickson Service Bulletin No. 64B10-3, Revision D, dated October 15, 2007, except you are not required to contact Erickson nor send hinge pins to them. A non-destructive testing (NDT) UT Level I Special, Level II, or Level III inspector who is qualified under the guidelines established by ASNT SNT-TC-1A, ISO 9712, or an FAA-accepted equivalent qualification standard for NDT inspection and evaluation, must perform the UT inspection. (5) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, perform a fluorescent-magnetic particle inspection (MPI) of each second stage planetary plate assembly, P/N 6435-20231-016, for a crack. (6) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 650 hours TIS, perform an MPI of each M/R shaft, P/N 6435-20078-104, for a crack, paying particular attention to thelower spline area. (7) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 1,450 hours TIS, perform an MPI of each M/R shaft, P/N 6435-20078- 105, for a crack, paying particular attention to the lower spline area. (8) Within 150 hours TIS or before reaching 3,375 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 3,375 hours TIS, perform a fluorescent penetrant inspection of each housing lug on each servo housing, P/N S1565-20252-2, for a crack. (9) At each overhaul of the main gearbox assembly, P/N 6435- 20400-053, -054, -058, -060, -062, -063, -064, -065, or -066, perform an MPI of the entire shaft of each M/R shaft assembly, P/N 6435-20078-014, -015, or -016, for a crack, paying particular attention to the rotating swashplate spherical bearing ball travel area, which is located approximately ten inches above the upper roller bearing journal shoulder. (10) If there is a crackin any part, before further flight, replace the cracked part. (11) At each overhaul of the damper assembly, P/N 6410-26200- 042, replace the following parts with airworthy parts that have zero (0) hours TIS: (i) All Air Force-Navy Aeronautical Standard (AN), Aerospace Standard (AS), Military Standard (MS), and National Aerospace Standard (NAS) nuts, bolts, washers, and packings, except packing, P/N MS28775-011, installed on stud, P/N SHF111-11SN-12A; (ii) Lock washer, P/N SS5073-2; (iii) Nut, P/N SS5081-05; (iv) Felt seal, P/N S1510-26017; (v) Retaining ring, P/N UR106L; and (vi) Nut, P/N 6410-26214-101. (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, Aerospace Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 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. 64B General-1, Revision 19, dated September 15, 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, Director of Regulatory Compliance, 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: 6200: Main Rotor System; 6300: Main Rotor Drive System; 6410: Tail Rotor Blades; 6500: Tail Rotor Drive System. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Erickson Service Bulletin No. 64B10-3, Revision D, dated October 15, 2007. (ii) Reserved. (3) For Erickson service information identified in this AD, contact Erickson Air-Crane Incorporated, ATTN: Chris Erickson, Director of Regulatory Compliance, 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. (4) You may view this service information that is incorporated by reference at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (5) You may also view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.