AD 2001-24-07 Airworthiness Directives; Agusta S.p.A. Model A109C, A109E, and A109K2 Helicopters

Models named: A109C, A109E, A109K2. Read the applicability below — it usually turns on serial or part numbers too.

Model A109C, A109E, and A109K2 helicopters, with main rotor blade (blade), part number (P/N) 709-0103-01—all dash numbers, having a serial number (S/N) up to and including S/N 1428 with a prefix of either “EM-” or “A5-” installed, certificated in any category.

Required within 10 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 25 hours TIS. To prevent failure of a blade tip cap, excessive vibration, and subsequent loss of control of the helicopter, accomplish the following: (a) Tap inspect the upper and lower sides of each tip cap for bonding separation between the metal shells and the honeycomb core using a steel hammer, P/N 109-3101-58-1, or a coin (quarter) in the area indicated as honeycomb core on Figure 1 of Alert Bollettino Tecnico Nos. 109-106, 109K-22, or 109EP-1, all Revision B, and dated December 19, 2000 (ABT), as applicable. Also, tap inspect for bonding separation in the tip cap to blade bond area (no bonding voids are permitted in this area). (b) Visually inspect the upper and lower sides of each blade tip cap for swelling or deformation. (c) Dye-penetrant inspect the tip cap leading edge along the welded joint line of the upper and lower tip cap skin shells for a crack in accordance with the Compliance Instructions, paragraph 3, of the applicable ABT. (d) If any swelling, deformation, crack, or bonding separation that exceeds the prescribed limits in the applicable maintenance manual is found, replace the blade with an airworthy blade. (e) Replacement blades affected by this AD must comply with the repetitive inspection requirements of this AD. Replacing an affected blade with a blade having an airworthy blade tip cap, P/N 709-0103-29-109, is terminating action for the requirements of this AD for that blade. (f) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Office, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (g) The tap inspection and dye-penetrant inspection shall be done in accordance with Agusta Alert Bollettino Tecnico Nos. 109-106, 109K-22, or 109EP-1, all Revision B, and all dated December 19, 2000, as applicable. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of January 7, 2002 (66 FR 60144, December 3, 2001). 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; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_ regulations/ibr_locations.html. (h) This amendment becomes effective on July 30, 2004. Note: The subject of this AD is addressed in Ente Nazionale per l'Aviazionne Civile (Italy) AD Nos. 2000-571, 2000-572, and 2000-573, all dated December 22, 2000. Issued in Fort Worth, Texas, on June 16, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-14316 Filed 6-24-04; 8:45 am] BILLING CODE 4910-13-P