AD 2011-18-03 Airworthiness Directives; The Boeing Company 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 the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD. (1) The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes, identified in Boeing Alert Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009. (2) The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes, identified in Boeing Alert Service Bulletin 737-28A1248, Revision 2, dated August 28, 2009. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, 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 (u) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane.

Comply with this AD within the compliance times specified, unless already done. Installation of Automatic Shutoff System for the Center Tank Fuel Boost Pumps (g) For airplanes identified in paragraph 1.A.1. of Boeing Alert Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009: Within 36 months after the effective date of this AD, install an automatic shutoff system for the center tank fuel boost pumps, by accomplishing all of the actions specified in Part 1 and Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009, except that Figure 1 of this AD must be used in lieu of Sheet 2 of Figure 11 of Boeing Alert Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009. If a placard has been previously installed on the airplane in accordance with paragraph (h) of this AD, the placard may be removed from the flight deck of only that airplane after the automatic shutoff system has been installed. Installing automatic shutoff systems on all airplanes in an operator's fleet, in accordance with this paragraph, terminates the placard installation required by paragraph (h) of this AD for all airplanes in an operator's fleet. Note 2: Boeing Alert Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009, refers to Boeing Component Service Bulletin 233A3202-28-03, dated January 12, 2006, as an additional source of guidance for replacing the left and right center boost pump switches of the P5-2 fuel control module assembly with new switches and changing the wiring of the P5-2 fuel control module assembly. BILLING CODE 4910-13-P ER26AU11.015 BILLING CODE 4910-13-C Placard Installation for Mixed Fleet Operation (h) Prior to or concurrently with installing an automatic shutoff system on any airplane in an operator's fleet, as required by paragraph (g) of this AD, install a placard adjacent to the pilot's primary flight display on all airplanes in the operator's fleet that are not equipped with an automatic shutoff system for the center tank fuel boost pumps. The placard must read as follows (unless alternative placard wording is approved by an appropriate FAA Principal Operations Inspector): “AD 2002-24-51 fuel usage restrictions required.” Installing an automatic shutoff system, in accordance with paragraph (g) of this AD, terminates the placard installation required by this paragraph for only that airplane. Installing automatic shutoff systems on all airplanes in an operator's fleet, in accordance with paragraph (g) of this AD, terminates the placard installation required by this paragraph for all airplanes in an operator's fleet. If operation according to the fuel usage restrictions of AD 2002-24-51, Amendment 39-12992 (68 FR 10, January 2, 2003), and AD 2001-08-24, Amendment 39-12201 (66 FR 20733, April 25, 2001), is maintained until automatic shutoff systems are installed on all airplanes in an operator's fleet, the placard installation specified in this paragraph is not required. Installation of a placard in accordance with paragraph (e) of AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30, 2002), is acceptable for compliance with the placard installation requirements of this paragraph; however, terminating action specified in paragraph (g) of AD 2002-19-52 and installation of an automatic shutoff system required by paragraph (g) of this AD must be accomplished on the airplane before the placard is removed from the airplane. Airplane Flight Manual (AFM) Revision (i) For airplanes on which Boeing Alert Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009, has been accomplished: At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, do the actions specified in paragraphs (i)(3) and (i)(4) of this AD. (1) For airplanes on which the terminating action specified in paragraph (g) of AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30, 2002), has been done: Concurrently with accomplishing the actions required by paragraph (g) of this AD. (2) For airplanes on which the terminating action specified in paragraph (g) of AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30, 2002), has not been done: Concurrently with accomplishing the terminating action specified in paragraph (g) of AD 2002-19-52. (3) Revise Section 1 of the Limitations section of the Boeing 737-600/-700/-700C/-800/-900 AFM to include the following statement. This may be done by inserting a copy of this AD into the AFM. “Center Tank Fuel Pumps Intentional dry running of a center tank fuel pump (low pressure light illuminated) is prohibited.” Note 3: For clarification purposes, the AFM limitations required by AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30, 2002), continue to be required until the optional terminating actions specified in paragraph (g) of AD 2002-19-52 have been done. (4) Revise Section 3 of the Normal Procedures section of the Boeing 737-600/-700/-700C/-800/-900 AFM to include the following statements. This may be done by inserting a copy of this AD into the AFM. Alternative statements that meet the intent of the following requirements may be used if approved by an appropriate FAA Principal Operations Inspector. “CENTER TANK FUEL PUMPS Alternative Method of Compliance (AMOC) to AD 2001-08-24 and AD 2002-24-51 for Aircraft With the Automated Center Tank Fuel Pump Shutoff Center tank fuel pumps must not be “ON” unless personnel are available in the flight deck to monitor low pressure lights. For ground operation, center tank fuel pump switches must not be positioned “ON” unless the center tank fuel quantity exceeds 1000 pounds (453 kilograms), except when defueling or transferring fuel. Upon positioning the center tank fuel pump switches “ON” verify momentary illumination of each center tank fuel pump low pressure light. For ground and flight operations, the corresponding center tank fuel pump switch must be positioned “OFF” when a center tank fuel pump low pressure light illuminates [1]. Both center tank fuel pump switches must be positioned “OFF” when the first center tank fuel pump low pressure light illuminates if the center tank is empty. [1] When established in a level flight attitude, both center tank pump switches should be positioned “ON” again if the center tank contains usable fuel. Defueling and Fuel Transfer When transferring fuel or defueling center or main tanks, the fuel pump low pressure lights must be monitored and the fuel pumps positioned to “OFF” at the first indication of the fuel pump low pressure [1]. Defueling the main tanks with passengers on board is prohibited if the main tank fuel pumps are powered [2]. Defueling the center tank with passengers on board is prohibited if the center tank fuel pumps are powered and the auto-shutoff system is inhibited [2]. [1] Prior to transferring fuel or defueling, conduct a lamp test of the respective fuel pump low pressure lights. [2] Fuel may be transferred from tank to tank or the aircraft may be defueled with passengers on board, provided fuel quantity in the tank from which fuel is being taken is maintained at or above 2000 pounds (907 kilograms).” Note 4: When statements identical to those in paragraphs (i)(3) and (i)(4) of this AD have been included in the general revisions of the Boeing 737-600/-700/-700C/-800/-900 AFM, the general revisions may be inserted into that AFM, and the copy of this AD may be removed from that AFM. Installation of Secondary Pump Control Relays (j) For airplanes identified in paragraph 1.A.1. of Boeing Alert Service Bulletin 737-28A1248, Revision 2, dated August 28, 2009: Within 60 months after the effective date of this AD, install one secondary control relay for the electrical control circuit of each of the two center tank fuel boost pumps, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-28A1248, Revision 2, dated August 28, 2009. Airworthiness Limitations (AWL) Revision for AWL No. 28-AWL-23 (k) For airplanes identified in paragraph 1.A.1. of Boeing Alert Service Bulletin 737-28A1248, Revision 2, dated August 28, 2009: Concurrently with accomplishing the actions required by paragraph (j) of this AD, or within 30 days after the effective date of this AD, whichever occurs later, revise the maintenance program by incorporating AWL No. 28-AWL-23 of Subsection E, AWLs—Fuel Systems, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), of the Boeing 737-600/700/800/900 MPD Document, D626A001-CMR, Revision March 2011. The initial compliance time for the actions specified in AWL No. 28-AWL-23 is within 1 year after accomplishing the installation required by paragraph (j) of this AD, or within 1 year after the effective date of this AD, whichever occurs later. No Alternative Inspections or Inspection Intervals (l) After accomplishing the applicable actions specified in paragraph (k) of this AD, no alternative inspections or inspection intervals may be used unless the inspections or inspection intervals are approved as an AMOC in accordance with the procedures specified in paragraph (u) of this AD. Terminating Action for AD 2001-08-24, Amendment 39-12201 (66 FR 20733, April 25, 2001) (m) Accomplishing the actions required by paragraphs (g), (h), and (i) of this AD, or accomplishing the actions specified in paragraph (s) of this AD, terminates the requirements of paragraph (a) of AD 2001-08-24, Amendment 39-12201 (66 FR 20733, April 25, 2001), for Model 737-600, -700, -700C, -800, and -900 series airplanes that have the automatic shutoff system, or a TDG Aerospace, Inc., universal fault interrupter (UFI), installed. After accomplishing the actions required by paragraphs (g), (h), and (i) of this AD, or accomplishing the actions specified in paragraph (s) of this AD, the AFM limitation required by paragraph (a) of AD 2001-08-24 may be removed from the AFM for those airplanes. Terminating Action for AD 2002-24-51, Amendment 39-12992 (68 FR 10, January 2, 2003) (n) Accomplishing the actions required by paragraphs (g), (h), and (i) of this AD, or accomplishing the actions specified in paragraph (s) of this AD, terminates the requirements of paragraph (b) of AD 2002-24-51, Amendment 39-12992 (68 FR 10, January 2, 2003), for Model 737-600, -700, -700C, -800, and -900 series airplanes that have the automatic shutoff system, or a TDG Aerospace, Inc., UFI, installed. After accomplishing the actions required by paragraphs (g), (h), and (i) of this AD, or accomplishing the actions specified in paragraph (s) of this AD, the AFM limitations required by paragraph (b) of AD 2002-24-51 may be removed from the AFM for those airplanes. Terminating Action for AWL Revision (o) Incorporating AWL No. 28-AWL-23 into the maintenance program in accordance with paragraph (g)(3) of AD 2008-10-10 R1, Amendment 39-16164 (75 FR 1529, January 12, 2010), terminates the corresponding action required by paragraph (k) of this AD. Terminating Action for AD 2008-24-51, Amendment 39-15781 (74 FR 8155, February 24, 2009) (p) Accomplishing the actions required by paragraph (g) of this AD terminates the requirements of paragraph (f) of AD 2008-24-51, Amendment 39-15781 (74 FR 8155, February 24, 2009). Credit for Actions Accomplished in Accordance With Previous Service Information (q) Actions accomplished before the effective date of this AD in accordance with Boeing Alert Service Bulletin 737-28A1248, dated December 21, 2006; or Boeing Alert Service Bulletin 737-28A1248, Revision 1, dated January 9, 2008; are considered acceptable for compliance with the corresponding actions specified in paragraph (j) of this AD. (r) Actions accomplished before the effective date of this AD in accordance with Boeing Alert Service Bulletin 737-28A1206, dated January 11, 2006; or Revision 1, dated January 30, 2008; are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD, provided one of the actions specified in paragraph (r)(1) or (r)(2) of this AD have been done. (1) The procedures specified in paragraph (f) of AD 2008-24-51, Amendment 39-15781 (74 FR 8155, February 24, 2009), have been accomplished. (2) The actions specified in Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-28A1206, Revision 2, dated May 21, 2009, have been accomplished. Optional Terminating Action (s) Installing TDG Aerospace, Inc., UFI, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, within 36 months after the effective date of this AD, terminates the actions required by paragraphs (g) through (k) of this AD; provided that, concurrently with installing a UFI on any airplane in an operator's fleet, a placard is installed adjacent to the pilot's primary flight display on all airplanes in the operator's fleet not equipped with a UFI or an automatic shutoff system. The placard must read as follows (unless alternative placard wording is approved by an appropriate FAA Principal Operations Inspector): “AD 2002-24-51 fuel usage restrictions required.” Installation of a placard in accordance with paragraph (h) of this AD is acceptable for compliance with the placard installation required by this paragraph. Installing a TDG Aerospace, Inc., UFI in accordance with this paragraph on an airplane terminates the placard installation required by this paragraph for only that airplane. Installing TDG Aerospace, Inc., UFIs in accordance with this paragraph, or automatic shutoff systems in accordance with paragraph (g) of this AD, on all airplanes in an operator's fleet terminates the placard installation required by this paragraph for all airplanes in an operator's fleet. If operation according to the fuel usage restrictions of AD 2002-24-51, Amendment 39-12992 (68 FR 10, January 2, 2003), and AD 2001-08-24, Amendment 39-12201 (66 FR 20733, April 25, 2001), is maintained until UFIs or automatic shutoff systems are installed on all airplanes in an operator's fleet, the placard installation specified in this paragraph is not required. Installation of a placard in accordance with paragraph (e) of AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30, 2002), is acceptable for compliance with the placard installation requirements of this paragraph; however, terminating action specified in paragraph (g) of AD 2002-19-52 and installation of a UFI specified by this paragraph must be accomplished on the airplane before the placard is removed from the airplane. Note 5: Guidance on installing a TDG Aerospace, Inc., UFI can be found in TDG Aerospace, Inc., Supplemental Type Certificate (STC) ST02076LA. Credit for Actions Accomplished in Accordance With Previous Service Information (t) Revising the maintenance program by incorporating AWL No. 28-AWL-23 of a revision specified in paragraphs (t)(1) through (t)(12) of this AD of Subsection G, Airworthiness Limitations—Fuel System AWLs, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), of the Boeing 737-600/700/800/900 MPD Document, D626A001-CMR; or Subsection E, AWLs—Fuel Systems, of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), of the Boeing 737-600/700/800/900 MPD Document, D626A001-CMR, Revision February 2011; before the effective date of this AD is considered acceptable for compliance with the corresponding actions specified in paragraph (k) of this AD. (1) Revision March 2008. (2) Revision April 2008. (3) Revision June 2008. (4) Revision February 2009. (5) Revision March 2009. (6) Revision August 2009. (7) Revision September 2009. (8) Revision November 2009. (9) Revision January 2010. (10) Revision May 2010. (11) Revision July 2010. (12) Revision August 2010. Alternative Methods of Compliance (AMOCs) (u)(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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. Related Information (v) For more information about this AD, contact Tak Kobayashi, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Ave., SW., Renton, Washington 98057-3356; phone: (425) 917-6499; fax (425) 917-6590; e-mail: Takahisa.Kobayashi@faa.gov. Material Incorporated by Reference (w) You must use the service information contained in table 1 of this AD, as applicable, to do the actions required by this AD, unless the AD specifies otherwise. Table 1—All Material Incorporated by Reference Document Revision Date Boeing Alert Service Bulletin 737-28A1206 2 May 21, 2009. Boeing Alert Service Bulletin 737-28A1248 2 August 28, 2009. AWL No. 28-AWL-23 of Subsection E, AWLs—Fuel Systems of Section 9, Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), of the Boeing 737-600/700/800/900 Maintenance Planning Data Document, D626A001-CMR March 2011 March 2011. (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in table 1 of this AD 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. (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 an NARA facility, 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 12, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011-21617 Filed 8-25-11; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent center tank fuel pump operation with continuous low pressure, which could lead to friction sparks or overheating in the fuel pump inlet that could create a potential ignition source inside the center fuel tank. These conditions, in combination with flammable fuel vapors, could result in a center fuel tank explosion and consequent loss of the airplane.