2021-07-15: Tail Rotor Drive Shaft

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by: 0 a. Removing Airworthiness Directive (AD) 82-20-05, Amendment 39-4466 (47 FR 43018, September 30, 1982); and 0 b. Adding the following new AD: \n\n2021-07-15 Airbus Helicopters: Amendment 39-21492; Docket No. FAA- 2020-0912; Product Identifier 2015-SW-071-AD. \n\n(a) Applicability \n\n\n\tThis airworthiness directive (AD) applies to Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, certificated in any category, with a tail rotor (TR) drive shaft bearing (bearing) part number (P/N) 593404, 6007- 2RS1MT47CA, P9107NPP7, 83A851BC3, or 83A851B-1C3, or manufacturer part number (MP/N) 704A33-651-010, 704A33-651-111, 704A33-651-143, or 704A33-651-181, installed. \n\n(b) Unsafe Condition \n\n\n\tThis AD defines the unsafe condition as failure or seizure of a TR bearing, which if not corrected could result in loss of the TR drive and subsequent loss of control of the helicopter. \n\n(c) Affected ADs \n\n\n\tThis AD replaces AD 82-20-05, Amendment 39-4466 (47 FR 43018, September 30, 1982). \n\n(d) Effective Date \n\n\n\tThis AD becomes effective May 7, 2021. \n\n(e) Compliance \n\n\n\tYou 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. \n\n(f) Required Actions \n\n\n\t(1) For helicopters with TR bearing P/N 593404 or MP/N 704A33- 651-181 installed, within 100 hours time-in-service (TIS) and thereafter at intervals not to exceed 165 hours TIS: \n\t(i) Inspect each bearing holder damper bushingfor wear, a crack, tears, and play between each bushing and support plate. If there is any wear, a crack, tears, or play between the bushing and support plate, remove the bearing holder damper bushing from service. \n\t(ii) Inspect each bearing holder for a crack, fretting, and corrosion around the attachment holes. If there is a crack, fretting, or corrosion, remove the bearing holder from service. \n\t(iii) Inspect each rubber sleeve for rotation, crazing, play between the inner races and the rubber sleeve, and lack of integrity of the elastomer. For the purposes of this inspection, lack of integrity may be indicated by brittle or cracked rubber. If there is any rotation, crazing, play between the inner races and the rubber sleeve, or lack of integrity of the elastomer, remove the rubber sleeve from service. \n\t(2) Within 100 hours TIS: \n\t(i) Make a mark with white paint on the rubber sleeves and on the shaft. \n\t(ii) For helicopters with TR shaft bearing P/N 6007-2RS1MT47CA, P9107NPP7, 83A851BC3, or 83A851B-1C3, or MP/N 704A33-651-010, 704A33-651-111, or 704A33-651-143 installed, remove the affected bearings from service and replace with bearing P/N 593404 or MP/N 704A33-651-181. \n\t(3) After the effective date of this AD, do not install bearing P/N 6007-2RS1MT47CA, P9107NPP7, 83A851BC3, or 83A851B-1C3, or MP/N 704A33-651-010, 704A33-651-111, or 704A33-651-143 on any helicopter. \n\n(g) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of: Bang Nguyen, Aerospace Engineer, Structures Certification Section, Fort Worth ACO Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; Information may be emailed to: [email protected]. \n\t(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. \n\n(h) Additional Information \n\n\n\t(1) Airbus Helicopters Alert Service Bulletin (ASB) No. AS355- 01.00.57, Revision 2, dated January 19, 2016, and Airbus Helicopter ASB No. AS350-01.00.70, Revision 1, dated September 21, 2015, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972-641-0000 or 800-232-0323; fax 972- 641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may view a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. \n\t(2) The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2015-0195, dated September 23, 2015. You may view the EASA AD on the internet at https://www.regulations.gov in Docket FAA-2020-0912. \n\n(i) Subject \n\n\n\tJoint Aircraft Service Component (JASC) Code: 6510, Tail Rotor Drive Shaft. \n\n\n\tIssued on March 25, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2021-06783 Filed 4-1-21; 8:45 am) BILLING CODE 4910-13-P