AD 2007-25-19 Airworthiness Directives; Boeing Model 747-400 Series Airplanes

Models named: 747-400 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Boeing Model 747-400 series airplanes, certificated in any category; as identified in Boeing Service Bulletin 747-21A2439, Revision 2, dated May 24, 2007.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections and Corrective Actions (f) At the applicable times specified in the Table 1 of paragraph 1.E. of Boeing Service Bulletin 747-21A2439, Revision 2, dated May 24, 2007, except as provided by paragraph (g) of this AD, do the actions specified in paragraphs (f)(1) and (f)(2) of this AD by accomplishing all the actions specified in the Accomplishment Instructions of the service bulletin. (1) Do repetitive general visual inspections to detect discrepancies (i.e., cracks, creases, deformation, deflection, and interference with the rudder and/or elevator cables) of the forward and rear heat exchanger shells of the air distribution system of the crew rest area, and do the applicable corrective actions, until the actions required by paragraph (f)(2) of this AD are done. The applicable corrective actions must be done before further flight. (2) Do an inspection to identify the part number, shop code, and build date of the forward and rear heat exchanger shells of the air distribution system of the crew rest area, and before further flight, do the applicable corrective actions. Accomplishing these actions ends the repetitive inspections required by paragraph (f)(1) of this AD. (g) Where Boeing Service Bulletin 747-21A2439, Revision 2, dated May 24, 2007, specifies a compliance time “after the release date of the service bulletin” or “after the date of Revision 02 of the service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD. Actions According to Previous Issues of Service Bulletin or Previously Accomplished Inspections (h) Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin 747-21A2439, dated November 3, 2005; or Boeing Service Bulletin 74721A2439, Revision 1, dated July 24, 2006; are acceptable for compliance with the corresponding actions specified in this AD. (i) If a forward heat exchanger shell, part number 65B41601-52, is found installed during the replacement required by paragraph (c) of AD 2001-18-04, amendment 39-12430, or was installed during the inspection required by paragraph (d)(2) of that AD (AD 2001-18-04 refers to Boeing Alert Service Bulletin 747-21A2412, dated January 20, 2000; or Revision 2, dated November 30, 2000; as the appropriate sources of service information for accomplishing the required actions): Actions required by paragraphs (f)(1) and (f)(2) of this AD are not required for that forward heat exchanger shell only. Parts Installation (j) As of the effective date of this AD, no person may install a heat exchanger shell having a part number identified in the “Existing Part Number” column of the table specified in paragraph 2.C. of Boeing Service Bulletin 747-21A2439, Revision 2, dated May 24, 2007, on any airplane. Special Flight Permits (k) 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 done, except as provided by paragraphs (k)(1) and (k)(2) of this AD. (1) If any forward or rear heat exchanger shell of the air distribution system of the crew rest area is found deflecting or interfering with the rudder and/or elevator control cables ( e.g. , chafing, rubbing, or contacting) during any inspection required by paragraph (f)(1) of this AD, special flight permits are not allowed. (2) If any crack or crease is found on the forward or rear heat exchanger shell of the air distribution system of the crew rest area during any inspection required by paragraph (f)(1) of this AD, the air distribution system in the crew rest area must be inoperative during flight. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (m) You must use Boeing Service Bulletin 747-21A2439, Revision 2, dated May 24, 2007, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on November 30, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-23850 Filed 12-7-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of an uncommanded up and down pitch movement of an airplane in flight and resistance in the elevator controls on the ground during taxi. We are issuing this AD to prevent cracking and buckling of the forward or rear heat exchanger shell of the air distribution system of the crew rest area, which could result in jamming of the rudder and/or elevator control cables and consequent reduced controllability of the airplane.