98-25-10: Seat Restraint Systems

98-25-10 AIRCRAFT BELTS, INC.: Amendment 39-10936. Docket No. 98-SW-33-AD. \n\n\tApplicability: Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems 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. \n\n\tNOTE 1: This AD applies to each seat restraint system 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 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 use the authority provided in paragraph (c) 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 seat restraint system from the applicability of this AD. \n\n\tCompliance: Required within 10 hours time-in-service after the effective date of this AD, unless accomplished previously. \n\n\tTo 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: \n\n\tNOTE 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. \n\n\t(a)\tVisually inspect all affected seat restraint systems to determine if the locking mechanism is engaging properly in accordance with the following: \n\n\t\t(1)\tOpen 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. \n\n\t\t(2)\tAllow the spring to close the lift lever slowly until the lift lever is back to its at-rest position. \n\n\t\t(3)\tAfter 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. \n\n\t(b)\tIf the locking mechanism does not seat properly, replace the buckle with an airworthy buckle. \n\n\t(c)\tAn 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 an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Airplane Certification Office. \n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Airplane Certification Office. \n\n\t(d)\tSpecial 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. \n\n\t(e)\tThis amendment becomes effective on December 24, 1998. \n\n\t\n\nFIGURE 1 \nAD 98-25-10