AD 2010-14-08 Airworthiness Directives; The Boeing Company Model 747-400, 747-400D, and 747-400F Series Airplanes

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

This AD applies to The Boeing Company Model 747-400, 747-400D, and 747-400F series airplanes, certificated in any category; as identified in Boeing Service Bulletins 747-28A2280, Revision 1, dated November 25, 2009, and 747-28A2281, Revision 1, dated November 25, 2009. Note 1: This AD requires revisions to certain operator maintenance documents to include a new inspection. Compliance with this inspection is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this inspection, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance (AMOC) according to paragraph (p)(1) of this AD. The request should include a description of changes to the required inspection that will ensure the continued operational safety of the airplane.

Comply with this AD within the compliance times specified, unless already done. Installations and Wiring Changes (g) Within 60 months after the effective date of this AD, do the actions in paragraphs (g)(1) and (g)(2) of this AD, as applicable. (1) For Model 747-400, 747-400D, and 747-400F series airplanes: Install new pump control and time delay relays and do related investigative and all applicable corrective actions, and change the wiring for the center and main fuel tanks override/jettison fuel pumps, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-28A2280, Revision 1, dated November 25, 2009. Do all related investigative and applicable corrective actions before further flight. (2) For Model 747-400 series airplanes: Install new relays and wiring for the horizontal stabilizer override/jettison fuel pumps in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-28A2281, Revision 1, dated November 25, 2009. Prior/Concurrent Requirements (h) Prior to or concurrently with the actions required by paragraph (g) of this AD, do the applicable actions in paragraphs (h)(1) and (h)(2) of this AD. (1) For Model 747-400, 747-400D, and 747-400F series airplanes identified in paragraphs (h)(1)(i), (h)(1)(ii), and (h)(1)(iii) of this AD: Install new integrated display system (IDS) software in accordance with the Accomplishment Instructions of the applicable service bulletin listed in paragraph (h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD. (i) For Model 747-400, 747-400D, and 747-400F series airplanes that have General Electric engines, except airplanes having variable numbers (V/Ns) RL429, RL430, RL473, RL511, and RL521: Boeing Service Bulletin 747-31-2376, dated September 5, 2006. (ii) For Model 747-400 and 747-400F series airplanes that have Pratt & Whitney engines except airplanes having V/Ns RL456, RL492, and RL502: Boeing Service Bulletin 747-31-2377, dated September 5, 2006. (iii) For Model 747-400 and 747-400F series airplanes that have Rolls Royce engines: Boeing Service Bulletin 747-31-2378, dated September 5, 2006. (2) For Model 747-400 series airplanes except V/Ns RM403, RM441 through RM443 inclusive, and RM445: Install a new automatic shutoff system for the horizontal stabilizer tank (HST) fuel pumps in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-28A2262, Revision 2, dated August 13, 2009. Credit for Actions Done According to Previous Issues of Service Bulletins (i) Actions done before the effective date of this AD in accordance with the applicable service information contained in Table 1 of this AD are acceptable for compliance with the corresponding actions required by paragraphs (g) and (h) of this AD. Table 1—Credit Service Information Document Revision Date Boeing Alert Service Bulletin 747-28A2280 Original August 7, 2008. Boeing Alert Service Bulletin 747-28A2281 Original December 13, 2007. Boeing Service Bulletin 747-28A2262 Original March 15, 2007. Boeing Service Bulletin 747-28A2262 1 May 8, 2008. Maintenance Program Revision (j) Concurrently with accomplishing the actions required by paragraph (g) of this AD, revise the maintenance program by incorporating Airworthiness Limitation (AWL) No. 28-AWL-24 and No. 28-AWL-26 of Section 9, “Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs),” of the Boeing 747-400 Maintenance Planning Data (MPD) Document D621U400-9, Revision April 2008. The inspection interval for AWL No. 28-AWL-24 and AWL No. 28-AWL-26 starts on the date the modification is incorporated. No Alternative Inspections or Inspection Intervals (k) After accomplishing the action specified in paragraph (j) of this AD, no alternative actions or intervals may be used unless the inspections or inspection intervals are approved as an AMOC in accordance with the procedures specified in paragraph (p)(1) of this AD. Acceptable Action for Certain ADs (l) For Model 747-400, -400D, and -400F series airplanes: Installing new IDS software in accordance with paragraph (h)(1) of this AD is an acceptable method of compliance for the action in the applicable AD paragraph listed in Table 2 of this AD. Table 2—Actions for Which Paragraph (h)(1) of This AD Is an Acceptable Method of Compliance (No Certificate Limitations) The action in— Of— (1) Paragraph E AD 90-09-06, amendment 39-6581. (2) Paragraph (b) AD 91-13-10 R1, amendment 39-8158. (3) Paragraph (d)(1) AD 96-07-09, amendment 39-9558. (4) Paragraph (a)(3)(iii) AD 2000-02-22, amendment 39-11540. (5) Paragraph (a)(2)(ii) AD 2000-12-21, amendment 39-11799. (6) Paragraph (d)(2)(iv) AD 2003-16-16, amendment 39-13269. (7) Paragraph (d)(1) AD 2004-10-05, amendment 39-13635. (m) For Model 747-400 series airplanes with a horizontal stabilizer fuel tank and with horizontal stabilizer tank fuel pump auto-shutoff installed: Installing new IDS software in accordance with paragraph (h)(1) of this AD is an acceptable method of compliance for the action in the applicable AD paragraph listed in Table 3 of this AD, provided the certificate limitations included in the following statement are incorporated into the Limitations Section of the applicable airplane flight manual (AFM) in place of the certificate limitation required by the AFM revision specified in the applicable AD listed in Table 3 of this AD. This may be done by inserting a copy of this AD in the AFM. CERTIFICATE LIMITATIONS Center Wing Tank: The center wing tank (CWT) fuel quantity indication system must be operative to dispatch with CWT mission fuel. If the FUEL LOW CTR L or R message is displayed, both CWT override/jettison pump(s) must be selected OFF. If the FUEL PRESS CTR L or R message is displayed, the corresponding CWT override/jettison pump must be selected OFF. Horizontal Stabilizer Tank: The following additional limitations must be followed if the horizontal stabilizer tank (HST) is fueled and used: The HST fuel quantity indication system must be operative to dispatch with HST mission fuel. If either the FUEL PMP STB L or R message is displayed while on the ground, both HST pumps must be selected OFF. If either the FUEL PRES STB L or R message is displayed, both HST pumps must be selected OFF. Defueling: Prior to defueling any fuel tanks, perform a lamp test of the respective Fuel Pump Low Pressure indication lights. When defueling, the Fuel Pump Low Pressure indication lights must be monitored and the fuel pumps positioned to OFF at the first indication of fuel pump low pressure. When defueling with passengers on board, fuel pump switches must be selected OFF at or above approximately 7,000 pounds (3,200 kilograms) for the CWT, 3,000 pounds (1,400 kilograms) for main tanks, and 2,100 pounds (1,000 kilograms) for the HST. (These requirements apply for defueling or transferring between tanks.) Warnings and Notes Applicable to All Fuel Operations Warning Do not reset a tripped fuel pump circuit breaker. Warning Do not cycle CWT and HST pump switches from ON to OFF to ON with any continuous low pressure indication present. Note In a low fuel situation, both CWT override/jettison pumps may be selected ON and all CWT fuel may be used. Note In a low fuel situation, both HST transfer pumps may be selected ON and all HST fuel may be used. Note The limitations contained in these certificate limitations supersede any conflicting basic airplane flight manual limitations.” Note 2: When a statement identical to that in paragraph (m) of this AD has 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. Note 3: The certificate limitations in paragraph (m) of this AD are also included as an enclosure to FAA Letter 140S-09-191, dated June 23, 2009. Table 3—Actions for Which Paragraph (h)(1) of This AD Is an Acceptable Method of Compliance (With Certificate Limitations) The action in— Of— (1) Paragraph (a) AD 2001-12-21, amendment 39-12277. (2) Paragraph (a) AD 2001-21-07, amendment 39-12478. (3) Paragraph (c)(2) AD 2002-19-52, amendment 39-12900. (4) Paragraph (a) AD 2002-24-52, amendment 39-12993. Optional Terminating Action for Paragraphs (g)(2), (h)(2), and (m) of this AD: Deactivation of the HST (n) Deactivation of the HST, in accordance with the applicable Boeing service information in Table 4 of this AD, terminates the requirements of paragraphs (g)(2), (h)(2), and (m) of this AD, except as provided by paragraph (o) of this AD. Deactivation of the HST before the effective date of this AD in accordance with the applicable service information in Table 5 of this AD also terminates the requirements of paragraphs (g)(2), (h)(2), and (m) of this AD, except as provided by paragraph (o) of this AD. Table 4—Deactivation Service Information Boeing Service Information Revision Date Service Bulletin 747-28-2247 Original November 26, 2002. Service Bulletin 747-28-2265 Original February 22, 2006. Service Bulletin 747-28-2272 Original February 21, 2006. Service Bulletin 747-28-2274 1 May 21, 2008. Service Bulletin 747-28-2275 4 February 2, 2009. Service Bulletin 747-28-2279 2 October 16, 2007. Service Bulletin 747-28-2285 3 August 30, 2007. Service Bulletin 747-28-2293 2 March 4, 2008. Service Bulletin 747-28-2295 2 January 19, 2009. Service Bulletin 747-28-2296 Original July 13, 2007. Service Bulletin 747-28-2300 1 June 2, 2008. Service Bulletin 747-28-2310 Original December 18, 2008. Service Bulletin 747-28-2314 Original December 9, 2008. Table 5—Deactivation Credit Service Information Boeing Service Information Revision Date Service Bulletin 747-28-2274 Original March 13, 2006. Service Bulletin 747-28-2275 Original June 12, 2006. Service Bulletin 747-28-2275 1 March 16, 2007. Service Bulletin 747-28-2275 2 July 2, 2007. Service Bulletin 747-28-2275 3 March 11, 2008. Service Bulletin 747-28-2279 Original June 12, 2006. Service Bulletin 747-28-2279 1 May 25, 2007. Service Bulletin 747-28-2285 Original January 23, 2007. Service Bulletin 747-28-2285 1 May 9, 2007. Service Bulletin 747-28-2285 2 August 3, 2007. Service Bulletin 747-28-2293 Original May 9, 2007. Service Bulletin 747-28-2293 1 August 29, 2007. Service Bulletin 747-28-2295 Original November 17, 2006. Service Bulletin 747-28-2295 1 March 20, 2008. Service Bulletin 747-28-2300 Original January 16, 2008. Reactivation of the HST (o) For any airplane on which the HST is reactivated, the HST must be reactivated in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. For any airplane on which the HST is reactivated, the requirements of paragraphs (g)(2), (h)(2), and (m) of this AD must be done before further flight following the reactivation, or within 60 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. Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, Seattle Aircraft Certification Office (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 Aircraft Certification Office, 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 (q) You must use the service information contained in Table 6 of this AD, as applicable, to do the actions required by this AD, unless the AD specifies otherwise. Table 6—Required Material Incorporated by Reference Boeing Service Information Revision Date Service Bulletin 747-28A2280 1 November 25, 2009. Service Bulletin 747-28A2281 1 November 25, 2009. Section 9, “Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs),” of the 747-400 Maintenance Planning Data (MPD) Document D621U400-9 April 2008 April 2008. Service Bulletin 747-28A2262 2 August 13, 2009. Service Bulletin 747-31-2376 Original September 5, 2006. Service Bulletin 747-31-2377 Original September 5, 2006. Service Bulletin 747-31-2378 Original September 5, 2006. If you accomplish the optional actions specified in this AD, you must use the service information specified in Table 7 of this AD, as applicable, to perform those actions unless the AD specifies otherwise. Table 7—Optional Material Incorporated by Reference Boeing Service Information Revision Date Service Bulletin 747-28-2247 Original November 26, 2002. Service Bulletin 747-28-2265 Original February 22, 2006. Service Bulletin 747-28-2272 Original February 21, 2006. Service Bulletin 747-28-2274 1 May 21, 2008. Service Bulletin 747-28-2275 4 February 2, 2009. Service Bulletin 747-28-2279 2 October 16, 2007. Service Bulletin 747-28-2285 3 August 30, 2007. Service Bulletin 747-28-2293 2 March 4, 2008. Service Bulletin 747-28-2295 2 January 19, 2009. Service Bulletin 747-28-2296 Original July 13, 2007. Service Bulletin 747-28-2300 1 June 2, 2008. Service Bulletin 747-28-2310 Original December 18, 2008. Service Bulletin 747-28-2314 Original December 9, 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 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. (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. (4) 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 June 17, 2010. Robert D. Breneman, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-15935 Filed 7-1-10; 8:45 am] BILLING CODE 4910-13-P

This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent uncommanded operation of certain override/jettison pumps which could cause overheat, electrical arcs, or frictional sparks, and could lead to an ignition source inside a fuel tank. This condition, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.