AD 98-25-10 Airworthiness Directives; Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH Seat Restraint Systems

Makes named: cessna, piper, beech. Read the applicability below — it usually turns on serial or part numbers too.

Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems manufactured between March 1997 and November 1998 that are installed on, but not limited to, Beech Aircraft Corp., Bell Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation, Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace, Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp. aircraft, certificated in any category. Note 1: This AD applies to each seat restraint system 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 seat restraint systems 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 (d) 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 within 10 hours time-in-service after the effective date of this AD, unless accomplished previously. To prevent failure of the seat restraint system due to the buckle assembly (buckle) locking mechanism not engaging properly, which could result in the seat restraint system failing to properly secure the occupant during turbulence or landing, accomplish the following: Note 2: The part number (P/N) of the seat restraint system is on the identification label located on each end of the seat restraint system near the anchor point (Example: P/N MD A2626-E010). The model is designated by the first two letters of the P/N. (a) Visually check all affected seat restraint systems to determine if the locking mechanism is engaging properly in accordance with the following: (1) Open the lift lever of the buckle fully until it will not open any further. This will cause the locking mechanism to pivot on the pivot pin. (2) Allow the spring to close the lift lever slowly until the lift lever is back to its at-rest position. (3) After the lever is completely closed, examine the slot in the bottom of the buckle. The locking mechanism should be firmly seated against the edge of the slot as shown in Figure 1. BILLING CODE 4910-13-U [[Page 69187]] [GRAPHIC] [TIFF OMITTED] TR10DE99.022 BILLING CODE 4910-13-C [[Page 69188]] (b) If the locking mechanism does not seat properly, replace the buckle with an airworthy buckle. (c) The requirements of this AD may be performed by an owner/ operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with sections 43.11 and 91.417(a)(2)(v) of the Federal Aviation Regulations (14 CFR sections 43.11 and 91.417(a)(2)(v)). Note 3: If the seat restraint systems' locking mechanisms are found to be functioning properly after the visual check described in paragraph (a) of this AD, the following is an example of a maintenance record entry that may be used: ``AD (number), paragraph (a) complied with by visual check. Seat belt buckle locking mechanism(s) found serviceable. (Date) (Aircraft total time-in-service). (Signature) (Certificate number and type of certificate held)'' If any of the seat restraint systems' locking mechanisms are found to malfunction after the visual check described in paragraph (a), the following is an example of a maintenance record entry that may be used: ``AD (number), paragraphs (a) and (b) complied with by visual check and replacement of seat belt buckle locking mechanism(s) on (seat location(s)) with airworthy buckle(s). (Date) (Aircraft total time-in-service). (Signature) (Certificate number and type of certificate held)'' (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, Airplane Certification Office, FAA. Operators shall submit their requests through a FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Airplane Certification Office. Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Airplane Certification Office. (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 aircraft to a location where the requirements of this AD can be accomplished. (f) This amendment becomes effective on January 14, 2000. Issued in Fort Worth, Texas, on December 3, 1999. Henry A. Armstrong, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 99-32083 Filed 12-9-99; 8:45 am] BILLING CODE 4910-13-U