AD 98-02-51 Airworthiness Directives; Boeing Model 737-300, -400, and -500 Series Airplanes

Models named: 737-300, -400, -500 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 737-300, -400, and -500 series airplanes having line positions 2765 through 2977 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 (e) 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 prevent reduced structural integrity of the horizontal stabilizer due to loose or missing fasteners of the left- or right- hand horizontal stabilizer, accomplish the following: (a) Within 5 flight cycles or 24 clock hours after the effective date of this AD, whichever occurs later, perform the following inspections of the left- and right-hand sides of the horizontal stabilizer: (1) Perform a general visual inspection to determine if any fasteners are missing on the top and bottom of the leading edge skin where it is attached to the front spar. (2) Perform a detailed visual inspection to detect loose or missing fasteners of the attachment of the elevator hinge plates to the left- and right-hand sides of the horizontal stabilizer rear spar fittings. Ensure torque sealant has not been broken on the fasteners. (b) If no discrepancies are found, no further inspections are required by this AD. (c) If any fastener is loose or missing, or if the torque sealant has been broken on any fastener, prior to further flight, install a new or serviceable fastener. (d) Within 5 days after accomplishing the inspections required by this AD, report inspection results, positive or negative, to the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax (425) 227-1181. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the paperwork reduction act of 1980 (44 U.S.C. 3501 et seq.) have been assigned OMB control number 2120-0056. (e) 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, Seattle ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Seattle ACO. (f) 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. (g) This amendment becomes effective on March 2, 1998, to all persons except those persons to whom it was made immediately effective by telegraphic AD T98-02-51, issued on January 8, 1998, which contained the requirements of this amendment. Issued in Renton, Washington, on February 18, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-4716 Filed 2-24-98; 8:45 am] BILLING CODE 4910-13-U