AD 2008-24-51 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; on which Boeing Alert Service Bulletin 737-28A1206 has been accomplished.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Test (f) Within 48 clock-hours after the effective date of this AD, or prior to further flight, whichever occurs later: Except as provided by paragraphs (g) and (h) of this AD, do the autoshutoff system wiring test specified in paragraphs (f)(1) through (f)(10) of this AD. (1) Remove electrical power from the airplane. (2) Open the following circuit breakers, and install collars and 'DO-NOT-CLOSE' tags on the circuit breakers. (i) Circuit breaker (CB) C3012, XFR BUS 2 SECT 2, on the P92 panel. (ii) CB C3002, XFR BUS 1 SECT 2, on the P91 panel. (iii) CB C1639, Fuel Auto S/O BST PUMP CTR TNK L AC, on the P6-3 panel. (3) Verify continuity between TB5060F in terminal 5 and the bus side terminal of CB C1639 in the P6-3 circuit breaker panel. (4) Check that wire number W0040-6402-14 is installed in terminal 5 of TB5060F. (5) If, during the action required by paragraph (f)(3) of this AD, there is no continuity; or if, during the check required by paragraph (f)(4) of this AD, the wire is found not installed in TB5060F terminal 5: Before further flight, trace wire W0040-6402-14 from CB C1639 and re-terminate the other end of the wire to TB5060F terminal 5. After re-terminating the wire, before further flight, do the actions specified in paragraphs (f)(3) and (f)(4) of this AD. (6) Remove the tags and collars from the following circuit breakers and close the circuit breakers. (i) CB C3012, XFR BUS 2 SECT 2, on the P92 panel. (ii) CB C3002, XFR BUS 1 SECT 2, on the P91 panel. (iii) CB C1639, Fuel Auto S/O BST PUMP CTR TNK L AC, on the P6-3 panel. (7) Supply electrical power to the airplane. (8) Verify the voltage at CB C1639 is 115 volts alternating current +/−5 volts. (9) If the voltage is not within the limits specified in paragraph (f)(8) of this AD, before further flight, repeat the actions required by paragraphs (f)(1) through (f)(8) of this AD. (10) Test the autoshutoff system as follows: (i) On P5-4 panel, switch Bus Transfer to OFF. (ii) Using only one power source (auxiliary power unit (APU) or an engine generator), power only AC Bus 1 with no power to AC Bus 2. (iii) Do the “Center Tank Boost Pump Auto Shutoff Functional Test” in accordance with paragraphs 9.A. through 9.G. of Task 28-22-00-720-805 of the Boeing 737-600/700/800/900 Aircraft Maintenance Manual, Document D633A101, Revision 37, dated October 15, 2008. Accomplishment of paragraphs 9.H. and 9.I. of the functional test should not be accomplished. (iv) If the autoshutoff test fails the test required by paragraph (f)(10)(iii) of this AD: Within 48 clock-hours after the effective date of this AD, or before further flight, whichever occurs later, do either paragraph (f)(10)(iv)(A) or (f)(10)(iv)(B) of this AD. (A) Do all applicable maintenance actions in accordance with Chapter 28, Section 28-22, of the Boeing 737-600/700/800/900 Fault Isolation Manual, Document D633A103, Revision 37, dated October 15, 2008, and repeat the action required by paragraph (f)(10)(iii) of this AD. (B) Deactivate the left-hand fuel pump of the CWT as specified in paragraph (g) of this AD. Optional Deactivation/Reactivation (g) Deactivation of the left-hand fuel pump of the CWT and operation in accordance with Item 28-02, ‘Fuel Boost Pumps (Center Tank), of the Federal Aviation Administration Master Minimum Equipment List for Boeing 737 100/200/300/400/500/600/700/800/900, Revision 52, dated April 29, 2008, may be accomplished in lieu of the requirements of paragraph (f) of this AD until the left-hand fuel pump of the CWT is reactivated. If the pump is deactivated, dispatch under this configuration is allowed for 10 days. For airplanes on which the left-hand fuel pump of the CWT is deactivated under the provision of this paragraph: Prior to further flight after reactivating the pump, do the autoshutoff system wiring test and applicable corrective actions specified in paragraphs (f)(1) through (f)(10) of this AD. Optional Installation (h) Accomplishing the installation of the power failed ‘ON’ protection system ( i.e., uncommanded pump “ON” protection system) for the center tank fuel boost pump in accordance with Boeing Alert Service Bulletin 737-28A1248, dated December 21, 2006; or Revision 1, dated January 9, 2008; terminates the autoshutoff system wiring test required by paragraphs (f) and (g) of this AD. Reporting (i) Submit a report of the findings (both positive and negative) of the actions required by paragraph (f) of this AD to Boeing via e-mail at RSE.BOECOM@BOEING.COM; or via fax at (206) 766-5682; at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include: a description of the test failure; a description of the action taken to correct the failure; the total number of flight cycles/flight hours accumulated on the airplane at the time of inspection; and the date of accomplishment of Boeing Alert Service Bulletin 737-28A1206 and total number of flight hours/flight cycles accumulated on the airplane on the date of accomplishment of that service bulletin. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056. (1) If the test is done after the effective date of this AD: Submit the report within 10 days after accomplishing the test. (2) If the test was accomplished prior to the effective date of this AD: Submit the report within 10 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Samuel Spitzer, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6510; fax (425) 917-6590; has the authority to approve AMOCs for this AD, if requested using 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 (k) You must use the documents specified in Table 1 of this AD, as applicable, to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional actions specified by this AD, you must use the documents specified in Table 2 of this AD, as applicable, to do the optional actions specified by this AD, unless the AD specifies otherwise. Table 1—Documents Incorporated by Reference for the Required Actions Specified in This AD Document Page title/description Page number(s) Revision level Date Task 28-22-00-720-805 of the Boeing 737-600/700/800/900 Aircraft Maintenance Manual (AMM), Document AMM Part II, Practices and Procedures Title Page None shown None noted* October 15, 2008. D633A101, Revision 37, dated October 15, 2008 AMM Part II, Practices and Procedures Transmittal Letter 1 37 October 15, 2008.   AMM Part II, Practices and Procedures Effective Pages 1-3 None noted* October 15, 2008.   AMM Chapter 28, 28-Effective Pages 1-10 None noted* October 15, 2008.   Task 28-22-00-702-805 of AMM Section 28-22 531-536 None noted* February 15, 2008. Chapter 28, Section 28-22, of the Boeing 737-600/700/800/900 Fault Isolation Manual (FIM), Document D633A103, Revision 37, dated October 15, 2008 FIM Title Page None shown None noted* October 15, 2008.   FIM Transmittal Letter 1 37 October 15, 2008.   FIM Effective Pages 1-3 None noted* October 15, 2008.   FIM Chapter 28 Effective Pages 1-2 None noted* October 15, 2008.   FIM Section 28-22 201-292 None noted* February 15, 2008. (*Only the Transmittal Letters for Boeing 737-600/700/800/900 AMM, Document D633A101, Revision 37; and Boeing 737-600/700/800/900 FIM, Document D633A103, Revision 37; contain the revision level of these documents.) Table 2—Documents Incorporated by Reference for the Optional Actions Specified in This AD Document Page title/description Page number(s) Revision level Date Boeing Alert Service Bulletin 737-28A1248, dated December 21, 2006 All 1-115 Original December 21, 2006. Boeing Alert Service Bulletin 737-28A1248, Revision 1, dated January 9, 2008 All 1-119 1 January 9, 2008. Department of Transportation, Federal Aviation Administration Master Minimum Equipment List (MMEL) for Boeing 737 100/200/300/400/500/600/700/800/900, Revision 52, dated April 29, 2008 MMEL Title Page None shown 52 April 29, 2008.   MMEL Contents I 52 April 29, 2008.   MMEL Item 28-02, ‘Fuel Boost Pumps (Center Tank)' 28-2, 28-3 52 April 29, 2008. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For Boeing 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 . For the Federal Aviation Administration Master Minimum Equipment List for Boeing 737 100/200/300/400/500/600/700/800/900 specified in this AD, contact the FAA, Flight Standards Division, Seattle Aircraft Evaluation Group, 1601 Lind Avenue, SW., Renton, Washington 98057. For information on the availability of this material at the FAA, call 425-917-6600 or fax 425-917-6638. (3) 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. (4) You may also review copies of the service information 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 December 18, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-3823 Filed 2-23-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of a failure of the left-hand fuel pump of the center wing tank (CWT) to shut off after being selected “OFF” by the flightcrew during flight on a Boeing Model 737-700 series airplane. Subsequent to that report, the failure was found on two additional airplanes. The failure condition results in continual running of the pump without indication to the flightcrew. We are issuing this AD to prevent extended dry-running of the fuel pump, which could lead to localized overheating of parts inside the fuel pump, and which could produce an ignition source inside the fuel tank.