AD 98-04-41 Airworthiness Directives; Boeing Model 737-200 and -300 Series Airplanes Equipped With a Main Deck Cargo Door Installed in Accordance With Supplemental Type Certificate SA2969SO

Models named: 737-200, -300 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 737-200 and -300 series airplanes equipped with a main deck cargo door installed in accordance with Supplemental Type Certificate (STC) SA2969SO; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 cracking in the upper jamb area of the fuselage and in the main cargo door, which could result in reduced structural integrity of the main cargo door and/or fuselage, and consequent loss or opening of the main cargo door while the airplane is in flight, or reduced controllability of the airplane, accomplish the following: (a) Within 10 days after the effective date of this AD, and thereafter at intevals not to exceed 600 flight cycles, perform a detailed visual inspection to detect cracks in the hinge and lift actuator box area of the main deck cargo door and upper jamb of the fuselage. Pay particular attention to the upper frame of the fuselage and upper jamb frames of the main deck cargo door, primary longeron, and clips of the fuselage, primarily in the hinge and lift actuator box area. If any crack is detected, prior to further flight, replace the cracked part with a new part having the same part number, or repair in accordance with a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small 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, Atlanta ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta 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) This amendment becomes effective on March 10, 1998. Issued in Renton, Washington, on February 12, 1998. Gilbert L. Thompson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-4245 Filed 2-20-98; 8:45 am] BILLING CODE 4910-13-U