AD 2002-21-04 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.

Model A119 helicopters with hub and tail rotor blades assembly, part number (P/N) 109-8131-02-149, or tail rotor blades, 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 (i) 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.

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 further flight, install a placard in the helicopter and mark the airspeed indicator at 122 knots indicated airspeed (KIAS) to indicate a reduction in the helicopter never exceed speed (Vne) by 30 KIAS. Make and install the placard in accordance with the Compliance Instructions, Part I, of Agusta Alert Bollettino Tecnico No. 119-6, Revision A, dated July 12, 2002 (BT). On the glass of the airspeed indicator, apply a red mark over the value of 122 KIAS. (b) Before each start of the helicopter engine, visually check both sides of each tail rotor blade for a crack in the area depicted in Figure 1 of this AD. An owner/operator (pilot) holding at least a private pilot certificate may perform this visual check and must enter compliance with this paragraph into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). See Figure 1: ER16OC02.010 Note 2: Paint irregularities on the tail rotor blade may be due to a crack. (c) Within 25 hours time-in-service (TIS), and thereafter at intervals not to exceed 25 hours TIS, and any time an increase in vibration levels occur, using a 5x or higher magnifying glass, visually inspect each tail rotor blade for a crack in accordance with the Compliance Instructions, Part III, paragraphs 1. through 5., of the BT. Reporting to Agusta Service Engineering is not required. 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 III, paragraph 6., of the BT. (d) Replace any cracked tail rotor blade with an airworthy blade before further flight. (e) Not later than October 30, 2002, in accordance with the Compliance Instructions, Part IV, and Figure 2 of the BT: (1) Install a new grip and bushing assembly, P/N 109-8131-02-147, into tail rotor hub and blade assembly, P/N 109-8131-02-149; (2) Reidentify the modified tail rotor hub and grips assembly, P/N 109-8131-02-141, as P/N 109-8132-01-153; and (3) Reidentify the modified tail rotor hub and blade assembly, P/N 109-8131-02-149, as P/N 109-8131-02-155. Returning the grips to the manufacturer is not required by this AD. (f) After completing the actions required by paragraph (e) of this AD, remove the Vne placard and the airspeed indicator marking at 122 KIAS that were installed in accordance with paragraph (a) of this AD. Modifying and reidentifying the parts as required by paragraph (e) of this AD is terminating actions for the requirements of paragraph (a) of this AD and restores the original Vne. (g) After completing the actions required by paragraph (e) of this AD, establish a retirement life of 1,000 hours TIS for tail rotor control rod, P/N 109-0135-02-101. (h) After completing the actions required by paragraph (e) of this AD, revise the helicopter Airworthiness Limitations Section of the Agusta Model A119 helicopter maintenance manual by inserting a 1,000 hour TIS retirement life for each tail rotor control rod, P/N 109-0135-02-101. (i) 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, 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, Regulations Group. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (j) Special flight permits will not be issued. (k) Installing the placard, inspecting for cracks, modifying and reidentifying the tail rotor hub and blade assembly, and reidentifying the tail rotor hub and grip assembly shall be done in accordance with the Compliance Instructions, Part I, Part III, paragraphs 1 through 6, and Part IV, of Agusta Alert Bollettino Tecnico No. 119-6, Revision A, dated July 12, 2002. 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. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (l) This amendment becomes effective on October 31, 2002. Note 4: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy) AD No. 2002-367, dated July 16, 2002. Issued in Fort Worth, Texas, on October 8, 2002. Larry M. Kelly, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 02-26071 Filed 10-15-02; 8:45 am] BILLING CODE 4910-13-P