99-23-10: PS Wire Bundle

99-23-10 RAYTHEON AIRCRAFT COMPANY (Formerly Beech): Amendment 39-11406. Docket 99-NM-156-AD. Applicability: Model Hawker 1000 series airplanes, serial numbers 258151, 258159, and 259003 through 259052 inclusive, 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 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. Compliance: Required as indicated, unless accomplished previously. To prevent a short circuit due to wire chafing, which can cause a fire in the ventral fuel tank area, accomplish the following: Inspection and Modification (a) Within 50 flight hours after the effective date of this AD, perform a detailed visual inspection of the PS wire bundle coming from the bung `DF' for chafing against the front ventral tank transfer/crossfeed actuator, in accordance with Raytheon Aircraft Service Bulletin SB 24-3201, dated October 1998. NOTE 2: For the purposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required." (1) If no chafing is found, prior to further flight, ensure a minimum 0.25-inch clearance exists between the PS wire bundle and valve actuator; and install spiral wrap, as necessary; in accordance with the service bulletin. (2) If any chafing is found on a 22, 20, 16, or 14 gauge (non-shielded) wire, prior to further flight, repair chafed wire by splicing the damaged section using MIL-S-81824/1 splices; ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary; in accordance with the service bulletin. (3) If any chafing is found on a 10 gauge wire, replace the entire wire with a new 10 gauge wire; ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary; in accordance with the service bulletin. (b) Within 50 flight hours after the effective date of this AD, perform a detailed visual inspection of the shielded wires going to the fuel probe `G' for chafing against the wing transfer valve actuator and mounting screws, in accordance with Raytheon Aircraft Service Bulletin SB 24-3201, dated October 1998. (1) If no chafing is found, prior to further flight, ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary; in accordance with the service bulletin. (2) If any chafing is found, prior to further flight, replace the entire shielded wire with a new shielded wire; ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary; in accordance with the service bulletin. (c) Within 50 flight hours after the effective date of this AD, perform a borescope inspection of the entire forward wing spar/forward ventral tank area for chafing of any other wire or wire bundle; and install spiral wrap, as necessary; in accordance with Raytheon Aircraft Service Bulletin SB 24-3201, dated October 1998. (1) If no chafing is found, no further action is required by this AD. (2) If any chafed wire or wire bundle is found, prior to further flight, repair in accordance with a method approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. For a repair method to be approved by the Manager, Wichita ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. Alternative Methods of Compliance (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, Wichita ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE 3: Information concerning the existence of approved alternative methods of compliance with thisAD, if any, may be obtained from the Wichita ACO. Special Flight Permits (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 airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (f) Except as provided by paragraph (c)(2) of this AD, the actions shall be done in accordance with Raytheon Aircraft Service Bulletin SB 24-3201, dated October 1998. 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 Aircraft Company, Manager Service Engineering, Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on December 17, 1999.