Airworthiness directives › 2001-22-51
AD 2001-22-51 Airworthiness Directives; Agusta S.p.A. Model A119 Helicopters
Models named: A119. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model A119 helicopters, with a tail rotor blade (blade), part number 109-8132-01-107, installed, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise 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 request approval for an alternative method of compliance in accordance with paragraph (g) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance
Required as indicated, unless accomplished previously. To prevent failure of a blade and subsequent loss of control of the helicopter, accomplish the following: (a) Remove any blade on or before accumulating 50 hours time-in-service (TIS). (b) Before each flight, visually check both sides of each blade for a crack. An owner/operator (pilot) holding at least a private pilot certificate may perform the visual check required by this paragraph, and must enter compliance into the helicopter maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). (c) Within 10 hours TIS and thereafter at intervals not to exceed 10 hours TIS or before the next flight after any abnormal increase in the vibratory level of the helicopter, inspect each blade for a crack using a 5-power or higher magnifying glass in accordance with the Compliance Instructions, Part II, paragraphs 1 through 6, of Agusta Bollettino Tecnico No. 119-1, Revision A, dated August 22, 2001 (ABT). (d) Within 25 hours TIS and thereafter at intervals not to exceed 25 hours TIS, dye penetrant inspect each blade for a crack in accordance with the Compliance Instructions, Part III, paragraphs 1 through 4.5, of the ABT. (e) Before further flight, remove any blade in which a crack is found. (f) This AD revises the Limitations section of the maintenance manual by establishing a 50-hour life limit for each blade, P/N 109-8132-01-107. (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, Regulations Group, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Regulations Group. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (h) Special flight permits will not be issued. (i) The inspections shall be done in accordance with the Compliance Instructions, Part II, paragraphs 1 through 6 and Part III, paragraphs 1 through 4.5, of Agusta Bollettino Tecnico No. 119-1, Revision A, dated August 22, 2001. 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, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (j) This amendment becomes effective on December 26, 2001, to all persons except those persons to whom it was made immediately effective by Emergency AD 2001-22-51, issued October 30, 2001, which contained the requirements of this amendment. Note 3: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy) ADs 2001-124, dated March 30, 2001; 2001-348, dated August 20, 2001; and 2001-374, dated August 29, 2001. Issued in Fort Worth, Texas, on November 27, 2001. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 01-30211 Filed 12-7-01; 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