Airworthiness directives › 99-01-02
AD 99-01-02 Airworthiness Directives; Westland Helicopters Ltd. 30 Series 100 and 100-60 Helicopters
Applicability*9
Westland 30 Series 100 and 100-60 Helicopters, 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 (c) 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 rotorcraft from the applicability of this AD.
Compliance
Required as indicated unless accomplished previously. To prevent failure of the conformal pinion quill shafts installed in certain Westland 30 series helicopters main rotor gearboxes that could result in a subsequent forced landing or loss of control of the helicopter, accomplish the following: (a) Prior to further flight, determine if the installed main rotor gearbox (MRGB) has a serial number included in the following list or has a history of shock loading. Shock loading is defined as a slam engagement of the No. 1 engine free wheeling unit that can occur when the No. 1 engine condition lever is at ``GND'' or ``FLT'' position and the engine is driving accessories but the main rotor is not turning. If the No. 1 engine freewheel is then engaged, the No. 1 engine power turbine will abruptly stop, causing potential damage to the MRGB and other drive system components. ------------------------------------------------------------------------ AAT 4440........................ ABL 5602.......... ACD 2875 AAX 4726........................ ABN 8930.......... ACN 7996 ABC 9438........................ ABP 3947.......... ADE 6100 ABD 7294........................ ABP 9028.......... WAG 397 ABG 5056........................ ABT 3965.......... WAG 410 ABH 5075........................ ABW 0547.......... WAK 525 ABJ 9595........................ ACA 3707.......... WAK 561 ABK 9484........................ .................. .................. [[Page 71743]] (b) If the installed MRGB has a serial number listed in paragraph (a) of this AD or has a history of shock loading, perform a magnetic drain plug inspection. (1) If the magnetic drain plug passes inspection, the MRGB may remain in service a maximum of 100 additional hours time in service (TIS) after the effective date of this AD with a repetitive magnetic drain plug inspection at intervals not to exceed 25 hours TIS. The MRGB must then be removed from service and the conformal pinion quill shafts replaced. (2) If the magnetic drain plug fails inspection, remove the MRGB from service prior to further flight and replace the conformal pinion quill shafts. Note 2: Westland Helicopters, Ltd. Service Bulletin No. W30-63- 75, dated November 29, 1995 (SB) pertains to the subject of this AD. (c) 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. 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, Rotorcraft Directorate. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. (f) This amendment becomes effective on January 14, 1999. Note 4: The subject of this AD is addressed in Civil Aviation Authority (United Kingdom) AD 012-11-95. Issued in Fort Worth, Texas, on December 21, 1998. Henry A. Armstrong, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-34502 Filed 12-29-98; 8:45 am] BILLING CODE 4910-13-U
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