95-21-17: Electrical Cable Loom

95-21-17 RAYTHEON CORPORATE JETS, INC. (Formerly de Havilland; Hawker Siddeley; British Aerospace, plc): Amendment 39-9404. Docket 95-NM-42-AD. Applicability: Model Hawker 1000 and BAe 125-1000A series airplanes; as listed in Raytheon Service Bulletin SB 24-313, dated December 19, 1994; certificated in any category. NOTE 1: This AD applies to each airplane 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 airplanes 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 (b) of this AD 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 airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent incorrect fault displays in the cockpit and possible electrical systems failures, accomplish the following: (a) Within 6 months after the effective date of this AD, perform a detailed visual inspection to detect chafing damage of the electrical cable loom (wire bundle) behind the right-hand throttle box cover, and perform continuity and insulation checks and system functional tests, in accordance with Raytheon Service Bulletin SB 24-313, dated December 19, 1994. (1) If no damage is found, prior to further flight, verify that the arrangement of the cable loom is correct and, using a cable tie, tie back the loom to the cable loom support bracket, in accordance with the service bulletin. (2) If any damage is found, prior to further flight, repair the damaged loom, in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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) tooperate the airplane to a location where the requirements of this AD can be accomplished. (d) The actions shall be done in accordance with Raytheon Service Bulletin SB 24-313, dated December 19, 1994. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Raytheon Corporate Jets, Inc., Customer Support Department, Adams Field, P.O. Box 3356, Little Rock, Arkansas 72203. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 17, 1995.