AD 2004-08-02 Airworthiness Directives; McDonnell Douglas Model 717-200 Airplanes

Models named: 717-200. Read the applicability below — it usually turns on serial or part numbers too.

Model 717-200 airplanes, as listed in Boeing Service Bulletin 717-55-0003, dated June 18, 2002; certificated in any category.

Required as indicated, unless accomplished previously. To detect and correct corrosion of the left- and right-hand horizontal stabilizer hinge fitting bolts, barrel nuts, and associated holes in the horizontal stabilizer structure, and the left- and right-hand elevator sector pinch bolts and associated holes, which could lead to loss of a hinge fitting and reduced structural integrity of the horizontal stabilizer; accomplish the following: Service Bulletin References (a) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Boeing Service Bulletin 717-55-0003, dated June 18, 2002. Initial Inspection (b) Prior to the accumulation of 18,000 total flight cycles, or within 15 months after the effective date of this AD, whichever is later: Perform the general visual inspections specified in paragraphs (c) and (d) of this AD, as applicable, in accordance with the service bulletin. Note 1: For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.” Horizontal Stabilizer Hinge Fitting Bolt Inspection (c) For Group 1 and Group 2 airplanes identified in paragraph 1.A.1. of the service bulletin: Perform a general visual inspection of the left- and right-hand horizontal stabilizer hinge fitting bolts, barrel nuts, and the associated holes in the horizontal stabilizer for corrosion in accordance with the service bulletin. (1) If no corrosion is found, before further flight, install bolts and barrel nuts with applicable corrosion protection, in accordance with the service bulletin. (2) If any corrosion is found, before further flight, remove the corrosion and do the actions specified in paragraph (c)(2)(i) or (c)(2)(ii) of this AD, as applicable, in accordance with the service bulletin. (i) If corrosion rework is within tolerance limits, before further flight, perform the corrective actions in accordance with the service bulletin, as applicable. (ii) If corrosion rework exceeds the tolerance limits and the service bulletin specifies to contact Boeing for repair: Before further flight, repair in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA; or in accordance with data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative (DER) who has been authorized by the Manager, Los Angeles ACO, to make such findings. For a repair method to be approved, the approval must specifically reference this AD. Elevator Sector Pinch Bolt Inspection (d) For Group 1 airplanes identified in paragraph 1.A.1. of the service bulletin: Perform a general visual inspection of the left- and right-hand elevator sector pinch bolts and associated holes for corrosion in accordance with the service bulletin. (1) If no corrosion is found, before further flight, install bolts and barrel nuts with applicable corrosion protection in accordance with the service bulletin. (2) If any corrosion is found, before further flight, remove the corrosion and do the actions specified in paragraph (d)(2)(i) or (d)(2)(ii) of this AD, as applicable, in accordance with the service bulletin. (i) If corrosion rework is within tolerance limits, before further flight, perform the corrective actions in accordance with the service bulletin, as applicable. (ii) If corrosion rework exceeds the tolerance limits and the service bulletin specifies to contact Boeing for repair: Before further flight, repair in accordance with a method approved by the Manager, Los Angeles ACO, FAA; or in accordance with data meeting the type certification basis of the airplane approved by a Boeing Company DER who has been authorized by the Manager, Los Angeles ACO, to make such findings. For a repair method to be approved, the approval must specifically reference this AD. Alternative Methods of Compliance (e) In accordance with 14 CFR 39.19, the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD. Incorporation by Reference (f) Unless otherwise specified in this AD, the actions shall be done in accordance with Boeing Service Bulletin 717-55-0003, dated June 18, 2002. 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 Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; 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 May 19, 2004. Issued in Renton, Washington, on April 6, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-8299 Filed 4-13-04; 8:45 am] BILLING CODE 4910-13-P