Airworthiness directives › 99-03-10
AD 99-03-10 Airworthiness Directives; Agusta S.p.A. (Agusta) Model A109E Helicopters
Models named: A109E. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model A109E helicopters, serial numbers up to and including 11036, 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 (d) 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 prevent loss of the metallic clamp or the engine exhaust ejector which could result in damage to the main or tail rotor system and subsequent loss of control of the helicopter, accomplish the following for each engine: (a) Prior to further flight, in accordance with Part I of the Compliance Instructions in Agusta Bollettino Tecnico No. 109EP-3, dated December 22, 1998 (Technical Bulletin), inspect the exhaust ejector to ejector saddle locking system, the dampers at the bottom of the ejector saddle, and the torque of the metallic clamp, and install safety wire on the metallic clamp. If any damage is found as a result of the inspection, accomplish Part II of the Compliance Instructions in the Technical Bulletin prior to further flight. (b) Within the next 10 hours time-in-service (TIS), inspect the dampers and metallic clamps, and reposition and modify the ejector saddle and the locking metallic clamp in accordance with Part II of the Compliance Instructions in the Technical Bulletin. (c) Thereafter, at intervals not to exceed 25 hours TIS, inspect the metallic clamp, locking mechanism, and dampers in accordance with Part III of the Compliance Instructions in the Technical Bulletin. (d) 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 Directorate, Rotorcraft Standards Staff, 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (e) 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) The inspections and modification shall be done in accordance with Agusta Bollettino Tecnico No. 109EP-3, dated December 22, 1998. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Agusta S.p.A., 21017 Cascina Costa di Samarate (VA), Via Giovanni Agusta 520, telephone (0331) 229111, fax (0331) 229605-222595. 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 Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on April 5, 1999, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 99-03-10, issued January 28, 1999, which contained the requirements of this amendment. (h) The subject of this AD is addressed in Registro Aeronautico Italiano (Italy) AD No. 98-465, dated December 24, 1998. Issued in Fort Worth, Texas, on March 10, 1999. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 99-6556 Filed 3-18-99; 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