AD 2009-16-07 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.

This AD applies to Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes, certificated in any category; as identified in Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2006-10-17 Inspection/Replacements/Wiring Changes/Corrective Actions (f) Within 36 months after June 22, 2006 (the effective date of AD 2006-10-17), do the applicable actions in paragraphs (f)(1) through (f)(5) of this AD by accomplishing all the applicable actions specified in the Accomplishment Instructions of Boeing Service Bulletin 737-24A1141, Revision 2, dated December 1, 2005, except as provided by paragraph (i) of this AD. Any applicable corrective actions must be done before further flight. (1) Replace the five brackets that hold the P5 panel to the airplane structure with new brackets; (2) Do a general visual inspection for wire length and damage of the connectors and the wire bundles, and applicable corrective actions; (3) Make wiring changes; (4) Replace the standby compass bracket assembly with a new assembly; and (5) Replace the stud assemblies with new assemblies. Note 1: For the purposes of this AD, a general visual inspection is: “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 ensure visual access to all 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.” (g) Actions done before June 22, 2006, in accordance with Boeing Alert Service Bulletin 737-24A1141, Revision 1, dated December 23, 2004, are acceptable for compliance with the requirements of paragraph (f) of this AD. Concurrent Requirements (h) Before or concurrently with the requirements of paragraph (f) of this AD, do the applicable action specified in Table 1 of this AD. Table 1—Concurrent Requirements For airplanes identified in Boeing component Service Bulletin— Action (1) 233A3205-24-01, dated July 26, 2001 Modify the generator drive and standby power module assembly in accordance with the Accomplishment Instructions of Boeing Component Service Bulletin 233A3205-24-01, dated July 26, 2001. (2) 69-37319-21-02, Revision 1, dated August 30, 2001 Modify the air conditioning module assembly in accordance with the Accomplishment Instructions of Boeing Component Service Bulletin 69-37319-21-02, Revision 1, dated August 30, 2001. New Actions Required by This AD New Service Bulletin Revision (i) As of the effective date of this AD, use only the Accomplishment Instructions of Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008, to do all the applicable actions required by paragraph (f) of this AD. Note 2: Accomplishment of the steps specified in the tables of the figures of Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008, is required. Due to the variability of airplane configurations, the illustrations in the figures are provided as examples. Note 3: Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008, refers to “unwanted” wire length. “Unwanted” wire length is any wire length that does not meet the wire length requirements specified in the Standard Wiring Practices Manual (SWPM). Additional Operational Test (j) For airplanes on which the actions required by paragraph (f) of this AD have been done in accordance with Boeing Service Bulletin 737-24A1141, Revision 2, dated December 1, 2005, before the effective date of this AD: Within 12 months after the effective date of this AD, do an operational test of the P5-14 panel in accordance with paragraphs 3.B.92. and 3.B.93., as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Binh Tran, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6485; fax (425) 917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov. (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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) AMOCs approved previously in accordance with AD 2006-10-17 are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (l) You must use the service information contained in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Table 2—All Material Incorporated by Reference Document Revision level Date Boeing Component Service Bulletin 233A3205-24-01 Original July 26, 2001. Boeing Component Service Bulletin 69-37319-21-02 1 August 30, 2001. Boeing Service Bulletin 737-24A1141 3 February 20, 2008. (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. Table 3—New Material Incorporated by Reference Document Revision level Date Boeing Service Bulletin 737-24A1141 3 February 20, 2008. (2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in Table 4 of this AD on June 22, 2006 (71 FR 28766, May 18, 2006). Table 4—Material Previously Incorporated by Reference Document Revision level Date Boeing Component Service Bulletin 233A3205-24-01 Original July 26, 2001. Boeing Component Service Bulletin 69-37319-21-02 1 August 30, 2001. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com ; Internet https://www.myboeingfleet.com. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. (5) You may also review copies of the service information that is incorporated by reference 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/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on August 7, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-19180 Filed 8-17-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of an electrical burning smell in the flight compartment. We are issuing this AD to prevent wire bundles from contacting the overhead dripshield panel and modules in the P5 overhead panel, which could result in electrical arcing and shorting of the electrical connector and consequent loss of several critical systems essential for safe flight; and to ensure proper operation of the passenger oxygen system. If an improperly functioning passenger oxygen system goes undetected, the passenger oxygen mask could fail to deploy and result in possible incapacitation of passengers during a depressurization event.