81-14-51 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4190 as amended by amendment 39-5801. Applies to Model SA 360C, SA 365C, and SA 365N helicopters certificated in any category (Airworthiness Docket No. 81-ASW-32);
Compliance required as indicated.
To detect possible cracks in the tail rotor internal and external rotating fairing and in the tail rotor hub, accomplish the following:
a. Within 5 hours time in service after receipt of this AD for Model SA 360C and SA 365C helicopters which have 45 hours or more total time in service on the effective date of this AD, inspect in accordance with paragraphs (c) and (d) unless already accomplished, and thereafter at intervals not to exceed 50 hours from the last inspection.
b. Before reaching 50 hours total time in service for those Model SA 360C and SA 365C helicopters which have less than 45 hours total time in service on the effective date of this AD, inspect in accordance with paragraphs (c) and (d), unless already accomplished, and thereafter at intervals not to exceed 50 hours from the last inspection.
c. Inspect visually for cracks in the tail rotor internal and external rotating fairings in the area of each blade clearance hole.
d. Inspect visually for cracks in the flange of the rotor hub body at the attaching points of the external fairing after removing the external fairing access door.
e. Following initial compliance with this AD, visually check the tail rotor internal and external rotating fairing for cracks before the first flight of each day. The pilot may conduct the check required by this paragraph.
NOTE: For the requirements regarding the listing of compliance with the AD in the aircraft's permanent maintenance record, see FAR 91.173(a)(2)(V).
f. If a crack is found in the tail rotor fairing or in the rotor hub body, remove the affected part before further flight. Install a serviceable part and continue the inspections and checks.
g. Equivalent means of compliance must be approved by the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium.
h. Within 50 hours time in service after the effective date of this amendment and thereafter at intervals not to exceed 150 hours time in service, inspect for cracks at the mating surfaces of the rotor hub and the external or outer fairing, after removing the fairing from the hub. Use a dye penetrant or equivalent inspection method.
i. This AD does not apply to Model SA 365N helicopters that comply with Section 2, Accomplishment Instructions, Service Bulletin 64.04, approved November 28, 1985, and to Model SA 360C and SA 365C helicopters that comply with Section 2, Accomplishment Instructions, Service Bulletin 65.17, dated December 17, 1985, which concerns the tail rotor head with dual hub body.
NOTE: Model SA 365N, S/N 6215 and onward, may have the tail rotor head with dual hub body installed at the factory.
Amendment 39-4190 became effective August 27, 1981 to all persons except those persons to whom it was made immediately effective by telegraphic AD T81-14-51 issued June 30, 1981.
This amendment 39-5801 amends Amendment 39-4190 (46 FR 42254), AD 81-14-51.
This amendment 39-5801 becomes effective January 15, 1988.