AD 2009-16-06 Airworthiness Directives; Boeing Model 767 Airplanes

Models named: 767-200, -300, -300F, -400ER series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Boeing Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Installation (f) For Model 767 airplanes with line numbers 1 through 940 inclusive: Within 36 months after the effective date of this AD, install an automatic shutoff system for the center tank fuel pump, in accordance with Boeing Service Bulletin 767-28A0083, Revision 2, dated February 12, 2009 (for Model 767-200, -300, and -300F airplanes); or Boeing Service Bulletin 767-28A0084, Revision 1, dated April 26, 2007 (for Model 767-400ER airplanes); as applicable. Installation According to Previous Issue of Service Bulletin (g) Installing an automatic shutoff system is also acceptable for compliance with the requirements of paragraph (f) of this AD if done before the effective date of this AD in accordance with service information identified in Table 1 of this AD. Table 1—Previous Issues of Service Bulletins Boeing service information Revision level Date Alert Service Bulletin 767-28A0083 Original May 3, 2006. Alert Service Bulletin 767-28A0084 Original May 3, 2006. Service Bulletin 767-28A0083 1 April 26, 2007. Revision of Airplane Flight Manual (AFM) (h) For Model 767 airplanes with line numbers 1 through 940 inclusive: Concurrently with accomplishing the actions required by paragraph (f) of this AD, revise Section 1, Certificate Limitations, of the Boeing 767 AFM to include the following: “CENTER TANK FUEL PUMPS Center tank fuel pump switches must not be “ON” unless personnel are available in the flight deck to monitor low PRESS lights. For ground operations prior to engine start: The center tank fuel pump switches must not be positioned ON unless the center tank contains usable fuel. With center tank fuel pump switches ON, verify both center tank fuel pump low PRESS lights are illuminated and EICAS CTR L FUEL PUMP and CTR R FUEL PUMP messages are displayed. For ground operations after engine start and flight operations: The center tank fuel pump switch must be selected OFF when the respective CTR L FUEL PUMP or CTR R FUEL PUMP message displays. Both center tank fuel pump switches must be selected OFF when either the CTR L FUEL PUMP or CTR R FUEL PUMP message displays if the center tank is empty. During cruise flight, both center tank pump switches may be reselected ON whenever center tank usable fuel is indicated. DE-FUELING AND FUEL TRANSFER When transferring fuel or de-fueling center or main wing tanks, the fuel pump low PRESS lights must be monitored and the respective fuel pump switches positioned to “OFF” at the first indication of low pressure. Prior to transferring fuel or de-fueling, conduct a lamp test of the respective fuel pump low PRESS lights. Intentional dry running of a center tank fuel pump (CTR L FUEL PUMP or CTR R FUEL PUMP message displayed on EICAS) is prohibited. Do not reset a tripped fuel pump or fuel pump control circuit breaker.” This may be done by inserting a copy of this AD into the AFM. Note 1: When statements identical to those in paragraph (h) of this AD have been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. Placard Installation (i) For Model 767-200, -300, or -300F airplanes that meet the conditions of paragraphs (i)(1) and (i)(2) of this AD: Within 30 days after the effective date of this AD, install a placard in the flight deck adjacent to each pilot's primary flight display, to alert the flightcrew to follow the procedures required by paragraph (b) of AD 2001-15-08. The placard must include the following statement: “AD 2001-15-08 fuel usage restrictions required.” Alternative placard wording may be used if approved by an appropriate FAA Principal Operations Inspector. Alternative placard methods and alternative methods of mixed fleet configuration control may be used if submitted for review in accordance with the procedures specified in paragraph (m) of this AD. (1) The airplane is operated in a fleet of airplanes on which the actions specified in paragraph (f) of this AD have been done on at least one of the fleet's airplanes. (2) The actions specified in paragraph (i) of AD 2001-15-08 (installation of modified center tank override and override/jettison fuel pumps that are not subject to the unsafe condition described in this AD) or paragraph (f) of this AD have not been done on the airplane. Note 2: If the actions specified in paragraph (f) of this AD have been done on all airplanes operated within an operator's fleet, or if operation according to the fuel usage restrictions of AD 2001-15-08 is maintained until automatic shutoff systems are installed on all airplanes in an operator's fleet: No placard is necessary before removal of the wet shutoff restrictions of AD 2001-15-08. Optional Terminating Action for Paragraphs (f), (h), and (i) of this AD: Deactivation of Center Fuel Tanks (j) Deactivation of the center fuel tanks, in accordance with Boeing Alert Service Bulletin 767-28A0050, dated December 18, 1997; or Boeing Service Bulletin 767-28A0050, Revision 1, dated December 22, 1999; terminates the requirements of paragraphs (f), (h), and (i) of this AD, except as provided by paragraph (k) of this AD. Reactivation of Center Fuel Tanks (k) For any airplane on which the center fuel tank is reactivated, the center fuel tank must be reactivated in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. For any airplane on which the center fuel tank is reactivated, the requirements of paragraphs (f), (h), and (i) of this AD must be done before further flight following the reactivation, or within 36 months after the effective date of this AD, whichever occurs later. For a reactivation method to be approved, the reactivation method must meet the certification basis of the airplane, and the approval must specifically reference this AD. Terminating Action for AD 2001-15-08 (l) For airplanes that have automatic shutoff systems installed: Accomplishing paragraphs (f) and (i) of this AD terminates the requirements of paragraphs (b) and (c) of AD 2001-15-08. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle ACO, 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: Douglas Bryant, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6505; 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. Material Incorporated by Reference (n) You must use Boeing Service Bulletin 767-28A0083, Revision 2, dated February 12, 2009; or Boeing Service Bulletin 767-28A0084, Revision 1, dated April 26, 2007; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating action specified by this AD, you must use Boeing Alert Service Bulletin 767-28A0050, dated December 18, 1997; or Boeing Service Bulletin 767-28A0050, Revision 1, dated December 22, 1999; to perform those actions, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-28A0083, Revision 2, dated February 12, 2009; and Boeing Service Bulletin 767-28A0084, Revision 1, dated April 26, 2007; under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Boeing Alert Service Bulletin 767-28A0050, dated December 18, 1997; and Boeing Service Bulletin 767-28A050, Revision 1, dated December 22, 1999; on September 4, 2001 (66 FR 39417, July 31, 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 July 24, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-18423 Filed 8-4-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent an overheat condition outside the center tank fuel pump explosion-resistance area that is open to the pump inlet, which could cause an ignition source for the fuel vapors in the fuel tank and result in fuel tank explosions and consequent loss of the airplane.