Airworthiness directives › 95-13-10
AD 95-13-10 Airworthiness Directives; Costruzioni Aeronautiche Giovanni Agusta S.p.A. Model A109A, A109AII, and A109C Helicopters
Models named: A109A, A109AII, A109C. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model A109A, A109AII, and A109C helicopters, serial number (S/N) 7670 and lower, excluding S/N 7630, 7633, 7645, 7651, 7654, 7663, 7665, 7666, 7667, 7668, and 7669, 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 helicopter from the applicability of this AD.
Compliance
Required as indicated, unless accomplished previously. To prevent failure of the vertical fin attachment caused by cracks in the tail boom vertical fin rear spar attachment area, and subsequent loss of control of the helicopter, accomplish the following: (a) Within the next 100 hours time-in-service (TIS), modify the tail boom vertical fin and perform a visual inspection for cracks in the vertical fin rear spar attachment area in accordance with Part I of the Accomplishment Instructions of Agusta Bollettino Tecnico No. 109-96, dated March 30, 1994. (1) For helicopters with tail boom, part number (P/N) 109-0370- 01, perform the modification using modification kit, P/N 109-0822- 38-101, in accordance with steps 5 through 8 of Part I of the Accomplishment Instructions of Agusta Bollettino Tecnico No. 109-96, dated March 30, 1994. (2) For helicopters with tail boom, P/N 109-0370-17, perform the modification using modification kit, P/N 109-0822-38-103, in accordance with steps 9 through 12 of Part I of the Accomplishment Instructions of Agusta Bollettino Tecnico No. 109-96, dated March 30, 1994. (b) Thereafter, at intervals not to exceed 300 hours TIS from the last inspection, remove the vertical fin leading edge fairing assembly and visually inspect the vertical fin rear spar attachment area for cracks in accordance with Part II of the Accomplishment Instructions of Agusta Bollettino Tecnico No. 109-96, dated March 30, 1994. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used when 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 2: 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. (e) The inspection and modifications shall be done in accordance with Agusta Bollettino Tecnico No. 109-96, dated March 30, 1994. 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, Direzione Supporto Prodotto E Servizi, 21019 Somma Lombardo (VA), Via per Tornavento, 15. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 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. (f) This amendment becomes effective on August 9, 1995. Issued in Fort Worth, Texas, on June 20, 1995. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 95-15516 Filed 7-3-95; 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