AD 2000-22-22 Airworthiness Directives; Raytheon Model Hawker 800XP and Hawker 800 (U-125A) Series Airplanes

Makes named: raytheon. Models named: Hawker 800XP series. Read the applicability below — it usually turns on serial or part numbers too.

Model Hawker 800XP series airplanes, as listed in Raytheon Service Bulletin SB 24-3212, dated August 1999; and Hawker 800 (U-125A) series airplanes, as listed in Raytheon Service Bulletin SB 24-3213, dated February 2000; 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.

Required as indicated, unless accomplished previously. To detect and correct chafing of the wire bundle exiting panel “JA” due to insufficient clearance from the fuel cross-feed valve operating lever, which could result in a fire in the area of the fuel system in a confined space, accomplish the following: Inspection and Corrective Actions (a) Within 50 flight hours or 6 months after the effective date of this AD, whichever comes first, conduct a one-time detailed visual inspection of the panel “JA” wire bundle in accordance with the Accomplishment Instructions of Raytheon Aircraft Service Bulletin SB 24-3212, dated August 1999 (for Model 800XP series airplanes); or SB 24-3213, Revision 1, dated February 2000 (for Model 800 (U-125A) series airplanes; as applicable. (1) Ensure that the wire bundle is routed correctly, in accordance with Figure 1 of the applicable service bulletin. (2) Ensure that a minimum clearance of 0.25-inch exists between the wire bundle from relay “KT” and the fuel cross-feed valve operating lever throughout its range of travel. 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.” (b) If the wire bundle is routed correctly and sufficient clearance exists, no further action is required by this AD. (c) If the wire bundle is not routed correctly or if sufficient clearance does not exist, prior to further flight, perform a detailed visual inspection of the wire bundle to relay “KT” for chafing, in accordance with the Accomplishment Instructions of Raytheon Aircraft Service Bulletin SB 24-3212, dated August 1999 (for Model 800XP series airplanes); or SB 24-3213, Revision 1, dated February 2000 (for Model 800 (U-125A) series airplanes); as applicable. (1) If no chafing is detected, prior to further flight, ensure that the wire bundle is routed correctly and ensure that a minimum clearance of 0.25-inch exists between the wire bundle and the fuel cross-feed valve operating valve throughout its range of travel, in accordance with the applicable service bulletin. (2) If any chafing is detected, prior to further flight, repair the chafed wire, ensure that the wire bundle is routed correctly and ensure that a minimum clearance of 0.25-inch exists between the wire bundle and the fuel cross-feed valve operating valve throughout its range of travel, in accordance with the applicable service bulletin. 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 Aircraft Certification Office (ACO), FAA. 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 this AD, 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) The actions shall be done in accordance with Raytheon Aircraft Service Bulletin SB 24-3212, dated August 1999; or Raytheon Aircraft Service Bulletin SB 24-3213, Revision 1, dated February 2000; as applicable. 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, 9709 East Central, Wichita, Kansas 67206. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, 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. Effective Date (g) This amendment becomes effective on December 19, 2000. Issued in Renton, Washington, on November 1, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00-28479 Filed 11-13-00; 8:45 am] BILLING CODE 4910-13-P