97-09-12: Upper Fuselage Skin

97-09-12 RAYTHEON AIRCRAFT COMPANY (Formerly Beech, Raytheon Corporate Jets, British Aerospace, Hawker Siddeley, et al.): Amendment 39-10008. Docket 96-NM-190-AD. Applicability: All Model DH 125-1A, -3A, and -400 series airplanes, 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. NOTE 2: Raytheon Model DH 125-1B, -3B, and -400B series airplanes are similar in design to the airplanes that are subject to the requirements of this AD and, therefore, also may be subject to the unsafe condition addressed by this AD. However, as of the effective date of this AD, those models are not type certificated for operation in the United States. Airworthiness authorities of countries in which the Model DH 125-1B, -3B, and -400B series airplanes are approved for operation should consider adopting corrective action, applicable to those models, that is similar to the corrective action required by this AD. Compliance: Required as indicated, unless accomplished previously. To detect and correct scoring of the upper fuselage skin around the periphery of the cockpit canopy blister interface, which could result in reduced structural integrity of the fuselage skin, and consequent cabin depressurization; accomplish the following: (a) Within 90 days afterthe effective date of this AD, perform a one-time detailed visual inspection to detect scoring of the upper fuselage skin around the periphery of the cockpit canopy blister interface, in accordance with Raytheon Aircraft Service Bulletin SB.53-93, dated May 16, 1996. (b) If no scoring is detected during the inspection required by paragraph (a) of this AD, no further action is required by this AD. (c) If any scoring is detected during the inspection required by paragraph (a) of this AD, prior to further flight, determine the maximum location and details of each score, including the edge distance and material thickness, in accordance with Raytheon Aircraft Service Bulletin SB.53-93, dated May 16, 1996. (1) If any scoring is found that is within the limits specified in the service bulletin, prior to further flight, repair in accordance with the service bulletin. (2) If any scoring is found that is outside the limits specified in the service bulletin, prior to furtherflight, repair in accordance with a method approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. (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 this AD, if any, may be obtained from the Wichita ACO. (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. (f) The actions shall be done in accordance with Raytheon Aircraft Service Bulletin SB.53-93, datedMay 16, 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, Commercial Service 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, Wichita Aircraft Certification Office, Small Airplane Directorate, 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 June 6, 1997.