AD 2011-20-06 Airworthiness Directives; Agusta S.p.A. Model AB139 and AW139 Helicopters

Models named: AB139, AW139. Read the applicability below — it usually turns on serial or part numbers too.

Model AB139 and AW139 helicopters, with a tail assembly, part number (P/N) 3G5350A00132, 3G5350A00133, 3G5350A00134, or 3G5350A00135, except those with tailboom reinforcement structural retro-modification (MOD), P/N 3G5309P01812, installed, certificated in any category.

Required as indicated. To detect damage to the tailboom to prevent failure of a tailboom and subsequent loss of control of a helicopter, do the following: (a) For all affected helicopters, before further flight, visually check all tailboom panels on both sides of the tailboom for skin bulging or deformation. Pay particular attention to the previously repaired areas. This visual check may be performed by an owner/operator (pilot) holding at least a private pilot certificate and must be entered into the helicopter records showing compliance with paragraph (a) of this AD in accordance with 14 CFR 43.9(a)(1)-(4) and 91.417(a)(2)(v). (b) If there is bulging or deformation of a tailboom panel skin, before further flight, using an aluminum hammer (GF-06-00), P/N 109-3101-58-2 (aluminum hammer), tap inspect the area around the bulge or deformity for debonding. Mark the boundaries of the debond area and measure the size of the marked area. (c) For helicopters with a tailboom assembly, P/N 3G5350A00132, 3G5350A00133, or 3G5350A00134, and a serial number (S/N) with a prefix of “A” up to and including S/N 7/109 for the short nose configuration and a S/N with a prefix of “A” up to and including S/N 7/063 for the long-nose configuration, within 25 hours time-in-service (TIS) from the last inspection or within 7 days, whichever occurs first, unless done previously, and thereafter at intervals not to exceed 25 hours TIS, tap inspect each tailboom panel on both sides of the tailboom in AREAs 3 and 5 for debonding, using an aluminum hammer as depicted in Figure 2 of Agusta Alert Bollettino Tecnico No. 139-195, Revision B, dated February 2, 2010 (ABT). First, inspect AREA 5 then AREA 3. You do not need to tap inspect the longeron area contained in AREA 3. Pay particular attention to previously repaired areas. (d) For all affected helicopters, except those with tailboom assembly part numbers and serial numbers described in paragraph (c) of this AD, within 50 hours TIS, unless done previously, and thereafter at intervals not to exceed 50 hours TIS, tap inspect each tailboom panel on both sides of the tailboom for debonding using an aluminum hammer. Pay particular attention to the previously repaired areas. (e) If there is any debonding, mark the debond area and measure the size of the marked area. (f) Before further flight, install tailboom structural reinforcement per MOD, P/N 3G5309P01812; if: (1) The mathematical area of a single debond is equal to or greater than 320 mm 2 and is wholly within AREA 3 as depicted in Figure 2 of the ABT; (2) The mathematical area of a single debond is equal to or exceeds 150 mm 2 if the debond occurs in area 1, 2, 4, or 5 as depicted in Figure 2 of the ABT; or (3) The distance between the edges of any two debonded areas is less than 3 times the largest debond dimension of the two debonded areas measured on a line between the centers of the two debonded areas; or (4) A debond is within 3 mm from any bond joint edge. (g) If none of the criteria of paragraphs (f)(1) through (f)(4) of this AD are met, before further flight, repair the debonded area of the tailboom using FAA engineering approved data and procedures or replace the tailboom with an airworthy tailboom. (h) Modifying the tailboom per MOD, P/N 3G5309P01812, is terminating action for the requirements of this AD. (i) 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 Manager, Safety Management Group, FAA Attn: Sharon Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Guidance Group, 2601 Meacham Blvd, Fort Worth, Texas 76137, telephone (817) 222-5122, fax (817) 222-5961, for information about previously approved alternative methods of compliance. (j) The Joint Aircraft System/Component (JASC) Code is 5302: Rotorcraft Tailboom. (k) The inspections shall be done on both sides of the tailboom by following the specified portions of Agusta Alert Bollettino Tecnico No. 139-195, Revision B, dated February 2, 2010. 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. Copies may be obtained from Agusta, Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA), Italy, telephone 39 0331-229111, fax 39 0331-229605/222595, or at http://customersupport.agusta.com/technical_advice.php. 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 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. (l) This amendment becomes effective on November 14, 2011. Note: The subject of this AD is addressed in European Aviation Safety Agency AD No. 2011-0019, dated February 3, 2011 . Issued in Fort Worth, Texas, on September 13, 2011. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011-27690 Filed 10-26-11; 8:45 am] BILLING CODE 4910-13-P