AD 98-05-16 Airworthiness Directives; Raytheon Model DH 125-1A and -3A Series Airplanes

Makes named: raytheon. Models named: DH 125-1A, -3A series. Read the applicability below — it usually turns on serial or part numbers too.

Model DH 125-1A and -3A series airplanes; equipped with a main entry door having part numbers 25FC3559A, 25FC3559A/B, or 25FC3559A/C; and on which Raytheon Modification 251429 has not been accomplished; 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 (b) 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 fatigue cracking of the main entry door/ frame pressing area, which could result in loss of structural integrity of the door and consequent decompression of the cabin, accomplish the following: (a) Within the next 150 landings or 90 days after the effective date of this AD, whichever occurs earlier, perform an eddy current inspection to detect fatigue cracking of the main entry door/frame pressing, in accordance with Raytheon Aircraft Service Bulletin SB.52-48, including Appendix A, dated June 19, 1996. (1) If no cracking is detected during the inspection, repeat the inspection thereafter at intervals not to exceed 1,000 flight hours. (2) If any cracking is detected during the inspection, prior to further flight, repair the cracking in accordance with the service bulletin. (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, Wichita Aircraft Certification Office (ACO), FAA, Small 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, Wichita ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (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) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The actions shall be done in accordance with Raytheon Aircraft Service Bulletin, SB.52-48, including Appendix A, dated June 19, 1996. 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, Technical Services--Beech, 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. (e) This amendment becomes effective on April 10, 1998. Issued in Renton, Washington, on February 26, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-5588 Filed 3-5-98; 8:45 am] BILLING CODE 4910-13-P