AD 2003-03-01 Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes

Models named: 737-600, -700, -700C, -800, -900 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model 737-600, -700, -700C, -800, and -900 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 (g) 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 increased structural loads on the aft engine mount, which could result in failure of the aft engine mount and consequent separation of the engine from the airplane, accomplish the following: Review of Maintenance Records (a) Within 90 days after the effective date of this AD, review the airplane maintenance records to determine whether either engine has been removed since the airplane's date of manufacture. If neither engine has been removed since the airplane's date of manufacture, no further action is required by this paragraph. Inspection To Determine if Center Link Assembly is Installed Correctly (b) For any installed engine that is found to have been removed from the airplane since the airplane's date of manufacture: Within 90 days after the effective date of this AD, do a one-time general visual inspection to determine if the center link assembly of the aft engine mount is installed correctly, per the Accomplishment Instructions of Boeing Alert Service Bulletin 737-71A1462, Revision 1, dated November 7, 2002. If the center link assembly is installed correctly, as specified in the service bulletin, no further action is required by paragraphs (b), (c), or (d) of this AD for that engine. However, paragraph (f) of this AD continues to apply. Note 2: 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.” Follow-on and Corrective Actions (c) For any center link assembly that is found installed incorrectly during the inspection required by paragraph (b) of this AD: Before further flight, do the actions in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, per the Accomplishment Instructions of Boeing Alert Service Bulletin 737-71A1462, Revision 1, dated November 7, 2002, except that it is not necessary to submit a report of findings to the airplane manufacturer. (1) Remove the center link assembly and install it correctly. (2) Perform a detailed inspection of the engine mounting lugs and engine turbine rear frame for cracking, yielding, buckling, or wear damage. (3) Perform a detailed inspection of the hardware for the aft engine mount; including the center link assembly, right link assembly, aft mount hanger assembly, and link pins; for cracking, yielding, buckling, or wear damage. Note 3: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” Repair (d) If any cracking, yielding, buckling, or wear damage is found during the inspections required by paragraphs (c)(2) and (c)(3) of this AD: Before further flight, replace the discrepant part with a new or serviceable part per the applicable section of the airplane maintenance manual, or repair per a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or per data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved, the approval must specifically reference this AD. Credit for Actions Accomplished Previously (e) Inspections and correction of the installation of the center link assembly accomplished before the effective date of this AD per the Accomplishment Instructions of Boeing Alert Service Bulletin 737-71A1462, dated August 29, 2002, are acceptable for compliance with the requirements of paragraphs (b) and (c) of this AD. Parts Installation (f) As of the effective date of this AD, no person may install an engine on any airplane unless the inspection specified by paragraph (b) of this AD is accomplished and the center link assembly of the aft engine mount is found to be installed correctly. Alternative Methods of Compliance (g) 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 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (h) 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. Incorporation by Reference (i) Unless otherwise specified in this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 737-71A1462, Revision 1, dated November 7, 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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date (j) This amendment becomes effective on February 13, 2003. Issued in Renton, Washington, on January 21, 2003. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-1815 Filed 1-28-03; 8:45 am] BILLING CODE 4910-13-P