AD 98-13-28 Airworthiness Directives; Agusta S.p.A. Model A109C and A109K2 Helicopters

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

Model A109C and A109K2 helicopters, with tail rotor blades (blades), part number (P/N) 109-8132-01-107, serial number A5-all dash numbers, 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 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 [[Page 34800]] requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD.

Required before further flight, unless accomplished previously. To prevent loss of the tip fairing on the blade, which could result in increased vibrations, loss of the tail rotor assembly, and subsequent loss of control of the helicopter, accomplish the following: (a) Perform a one-time inspection of each tail rotor blade for debonds. The area to be inspected is located in a spanwise band from 620.0 mm to 670.0 mm (24.4 to 26.4 inches), as measured outboard from the blade retention bolt centerline. Inspect the entire blade surface on both sides of each blade within this band (see Figure 1). Note 2: Agusta Bollettino Tecnico (Technical Bulletin) Number 109K-15, Revision A, dated April 18, 1997, pertains to the subject of this AD. [GRAPHIC] [TIFF OMITTED] TR26JN98.004 (b) Perform a tapping inspection to detect debonds within the blade surface area identified in paragraph (a) of this AD, using an aluminum hammer, P/N 109-3101-58-2, or equivalent. The presence of paint cracks on the tail rotor blade upper or lower surface in the tip fairing area at the 670.0 mm spanwise location (see Figure 1) may indicate that debonds exist. (c) Any blade that does not meet the allowable debond criteria specified in the applicable maintenance manual must be replaced with an airworthy blade before further flight. (d) 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, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. (f) This amendment becomes effective on July 13, 1998. Note 4: The subject of this AD is addressed in Registro Aeronautico Italiano (Italy) AD 97-124 and AD 97-125, both dated April 30, 1997. Issued in Fort Worth, Texas, on June 15, 1998. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-16612 Filed 6-25-98; 8:45 am] BILLING CODE 4910-13-U