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Agusta Emergency AD


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Airworthiness Directives

 

Header Information

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

Docket No. 2002-SW-35-AD; AD 2002-14-51 E

 

Augusta S.p.A. Model A109E and A119 Helicopters

 

PDF Copy (If Available):

 

 

 

Preamble Information

 

Regulatory Information

 

2002-14-51 AGUSTA S.p.A: Docket No. 2002-SW-35-AD.

 

Applicability: Model A109E and A119 helicopters, with tail rotor blade, part number (P/N) 109-8132-01-111, 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 (e) 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 the tail rotor blade and subsequent loss of control of the helicopter, accomplish the following:

 

(a) Before each flight, visually check each tail rotor blade on both sides for a crack as shown in Figure 1 of this AD. Paint irregularities may be due to a crack. If irregularities are found, consult with a mechanic. The pilot must enter compliance with this paragraph in accordance with 14 CFR 43.11 and 91.417(a)(2)(v).

 

(B) Within 5 hours time-in-service (TIS) and thereafter at intervals not to exceed 5 hours TIS, using a 5X or higher magnifying glass, visually inspect each tail rotor blade for a crack in accordance with the Compliance Instructions, Part II, paragraphs 1 through 5, of Agusta Bollettino Tecnico (BT) Nos. 109EP-30 for Model A109E or 119-6 for Model 119-6, both dated June 21, 2002.

 

© If you are unable to determine by the visual inspection whether there is a crack, dye penetrant inspect the tail rotor blade for a crack in accordance with the Compliance Instructions, Part II, paragraphs 6 through 7, of Agusta BT Nos. 109EP-30 for Model A109E or 119-6 for Model 119-6, both dated June 21, 2002.

 

(d) If a crack is found, before further flight, replace any cracked tail rotor blade with an airworthy tail rotor blade.

 

(e) 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.

 

(f) Special flight permits will not be issued.

 

(g) Copies of the applicable service information 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

 

(h) Emergency AD 2002-14-51, issued July 9, 2002, becomes effective upon receipt.

 

Note 3: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile AD Nos. 2002-340 and 2002-341, both dated June 28, 2002.

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