Airworthiness directives › 97-15-15
AD 97-15-15 Airworthiness Directives; Eurocopter France Model SA-365N, SA- 365N1, and SA-366G1 Helicopters
Models named: SA-365N, SA-365N1, SA-366G1. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model SA-365N, SA-365N1, and SA-366G1 helicopters, with main gearbox, part number (P/N) 365A32-6000-00, 365A32-6000-02, 365A32-6001-00, or 366A32-0001-00, installed, but not modified in accordance with MOD 077244, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (g) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD.
Compliance
Required as indicated, unless accomplished previously. To detect cracks in the gear shaft which could lead to failure of the gear shaft, failure of the transmission, and subsequent loss of control of the helicopter, accomplish the following: (a) Following each flight, when the main rotor is stopped, inspect the main gearbox magnetic plug (magnetic plug) for ferrous chips. (b) Following the last flight of each day, or at intervals not to exceed 12 hours time-in-service, whichever occurs first, inspect the main gearbox oil filter (oil filter) for ferrous chips. (c) If the total surface area covered by ferrous chips on the magnetic plug and in the oil filter is equal to or greater than 0.08 in\2\ [[Page 6071]] (50mm\2\), remove the main gearbox before further flight and replace with an airworthy main gearbox. (d) If the inspections specified in paragraph (a) or (b) of this AD reveal the presence of any ferrous chips on either the magnetic plug or in the oil filter, or if abnormal vibrations are reported by the flight crew, then perform main gearbox vibration measurements on the ground. Note 2: MET work card CT 05.53.00.221 describes an appropriate main gearbox vibration measurement technique for model SA-365N and SA-365N1 helicopters. MET work card CT 05.53.00.220 is applicable for model SA-366G1 helicopters. (e) If vibration levels above the helicopter's basic data are identified at a frequency of 26.07HZ, replace the main gearbox with an airworthy gearbox before further flight. Note 3: Interpretation of results is made by comparing the reading with previously obtained data when the aircraft vibration level was acceptable (i.e., reading performed upon aircraft acceptance or when main gearbox was installed). (f) Installation of MOD 077244 constitutes terminating action for the requirements of this AD. (g) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (h) Special flight permits will not be issued. (i) This amendment becomes effective on February 23, 1998, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 97-15-15, issued July 18, 1997, which contained the requirements of this amendment. Note 5: The subject of this AD is addressed in Direction Generale de L'Aviation Civile (France) AD 97-145-042(AB), dated July 10, 1997, and AD 97-164-020(AB), dated July 16, 1997. Issued in Fort Worth, Texas, on January 30, 1998. Henry A. Armstrong, Manager, Rotorcraft Directorate, Aircraft Certification Office. [FR Doc. 98-2969 Filed 2-5-98; 8:45 am] BILLING CODE 4910-13-P
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1