Airworthiness Directive · Amendment 39-15290 · Eurocopter France Model SA-365 N1, AS-365 N2, AS-365 N3, SA-366G1, EC 155B, and EC155B1 Helicopters
Eurocopter France Model SA-365 N1, AS-365 N2, AS-365 N3, SA-366G1, EC 155B, and EC155B1 Helicopters
Superseded. A later AD replaced this one: AD 2016-23-05. Comply with the one in force.
Model SA-365N1, AS-365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters, with a tail rotor (T/R) pitch control rod assembly double bearing (bearing) installed, certificated in any category.
This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. That AD currently requires a onetime inspection for end play in the pitch control rod assembly double bearing (bearing) using the tail rotor (T/ R) hub control plate, and before further flight, replacing the bearing if end play is present. This amendment requires checking the T/R gearbox (TGB) oil level before the first flight of the day and maintaining the oil at the maximum level for certain helicopters. Also, this action requires, during each required inspection or at certain specified intervals, ensuring the oil is at the maximum level for certain other model helicopters. This action also requires inspecting the magnetic plug for chips at specified intervals. Depending on the quantity of chips found, this action requires either replacing the TGB before further flight or further inspecting for axial play in the T/R hub pitch change control spider (spider). If axial play is found in the spider, before further flight, this AD requires replacing the bearing. This amendment is prompted by the finding that metal chips were not detected on the magnetic plug due to insufficient oil flow because the oil in the TGB was being maintained at the minimum level. The actions specified by this AD are intended to detect metal chips on the magnetic plug, to prevent damage to the bearing resulting in end play, loss of T/R pitch control, and subsequent loss of control of the helicopter.
Required as indicated.
To detect metal chips on the magnetic plug to prevent damage to the bearing resulting in end play, loss of T/R pitch control, and subsequent loss of control of the helicopter, do the following:
(a) Before the first flight of each day for Model SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters, check the T/R gearbox (TGB) oil level. An owner/operator (pilot) holding at least a private pilot certificate may perform the visual check of the oil level but must enter compliance into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v).
(b) If the oil level is not at maximum during the check in paragraph (a) of this AD, before further flight, a qualified mechanic must fill it to the maximum level.
(c) During each required inspection not to exceed 15 hours time-in-service (TIS) or 7 days, whichever occurs first, if the oil level is not at the maximum level, fill it to the maximum level for Model EC 155B and EC155B1 helicopters.
(d) Inspect the magnetic plug of the TGB for any chips as follows:
(1) At intervals not to exceed 25 hours TIS for helicopters with a magnetic plug without a chip electrical indication in the cockpit, or
(2) At intervals not to exceed 100 hours TIS and after any illumination of the TGB “CHIP” warning light for helicopters with a chip electrical indication in the cockpit.
(e) If you find any chips during the inspection in paragraph (d) of this AD, before further flight, follow the Accomplishment Instructions, paragraph 2.B.2.b), of Eurocopter Alert Service Bulletin No. 05.00.54 for Model SA-365N1, AS-365N2, AS 365 N3; No. 05A015 for Model EC 155B and EC155B1; or No. 05.37 for Model SA-366G1, all dated August 25, 2006 (ASBs), as appropriate for your model helicopter.
(1) If the quantity of chips on the magnetic plug, as referenced in the Operational Procedures, paragraph 2.B.2.b)1) of the ASBs is at or above the removal criteria, before further flight, replace the TGB with an airworthy TGB.
(2) If the quantity of chips on the magnetic plug is below the removal criteria, as referenced in the Operational Procedure, paragraph 2.B.2.b)2) of the ASBs.
(i) Inspect for axial play in the T/R hub pitch control change spider (spider) by following the additional steps in the Operational Procedure, paragraph 2.B.2.b)2) of the ASBs.
(ii) If there is axial play in the spider, before further flight, replace the bearing with an airworthy bearing.
(f) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, ATTN: Uday Garadi, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193-0110, telephone (817) 222-5123, fax (817) 222-5961.
(g) Special flight permits will not be issued.
(h) Do the inspections by following the specified portions of Eurocopter Alert Service Bulletin No. 05.00.54 for Model SA-365N1, AS-365N2, AS 365 N3; No. 05A015 for Model EC 155B and EC155B1; or No. 05.37 for Model SA-366G1 helicopters, all dated August 25, 2006, as applicable. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or 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/code_of_federal_regulations/ibr_locations.html.
(i) This amendment becomes effective on January 14, 2008.
Note: The subject of this AD is addressed in European Aviation Safety Agency Revised Emergency AD No. 2006-0258 R1-E on August 29, 2006, which replaced AD No. 2006-0051-E, dated February 20, 2006.
