AD 95-01-04 Airworthiness Directives; Boeing Model 747-100 Series Airplanes Equipped With Freighter Conversion Modification Installed in Accordance With Supplemental Type Certificate (STC) SA2322SO

Models named: 747-100 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 747-100 series airplanes equipped with freighter conversion modification installed in accordance with Supplemental Type Certificate (STC) SA2322SO, 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 use the authority provided in paragraph (d) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Required as indicated, unless accomplished previously. To prevent reduced fatigue life of the fuselage, accomplish the following: (a) Within 90 days after the effective date of this AD, perform a detailed close visual inspection of the tee chord and lap joint of stringer 4L from fuselage station (FS) 1660 to FS 2040 to detect discrepancies (such as corrosion, cracking, open holes, misdrilled holes, and any freeze plugs in the fuselage skin and internal stringer or longerons). External structural doublers must be removed to perform this inspection. (1) If no discrepancy is detected, prior to further flight, modify the longitudinal lap joints of the upper body skin at stringer 4L at FS 1689.5 to FS 1741.1, and FS 1961.1 to FS 2010.5, in accordance with GATX/Airlog Service Bulletin 94-MG-1000-009, dated May 4, 1994. Accomplishment of this modification constitutes terminating action for the inspections required by AD 90-15-06, amendment 39-6653. (2) If any discrepancy is detected, prior to further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (b) Within 30 days after the airplane is returned to service subsequent to the completion of the inspection required by paragraph (a) of this AD, submit a report of the findings of that inspection, positive or negative, to the FAA, Transport Airplane Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; or fax the report to (206) 227-1181. The report must include the information contained in paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of this AD. 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.) and have been assigned OMB Control Number 2120-0056. (1) Serial number of the airplane; (2) Date of completion of the modification installed in accordance with STC SA2322S0; (3) Date of the last inspection performed in accordance with the requirements of AD 90-15-06, amendment 39-6653; and (4) Description and location of each discrepancy detected during the inspection required by paragraph (a) of this AD. (c) As of the effective date of this AD, modification of the longitudinal lap joints of the upper body skin at stringer 4L, FS 1689.5 to FS 1741.1, and FS 1961.1 to FS 2010.5, must be accomplished in accordance with GATX/Airlog Service Bulletin 94-MG- 1000-009, dated May 4, 1994, prior to installation of Supplemental Type Certificate (STC) SA2322SO on any airplane in accordance with the STC. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be [[Page 2007]] used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. 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 Seattle 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 modification shall be done in accordance with GATX/ Airlog Service Bulletin 94-MG-1000-009, dated May 4, 1994. 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 GATX/Airlog Company, Tulsa International Airport, P.O. Box 582527, Tulsa, Oklahoma 74158. 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. (g) This amendment becomes effective on January 23, 1995. Issued in Renton, Washington, on December 27, 1994. James V. Devany, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 95-283 Filed 1-5-95; 8:45 am] BILLING CODE 4910-13-U