Airworthiness Directives; The Boeing Company Model 737-600, -700, -700C, -800, and -900 Series Airplanes, 53317-53324 [2011-21617]

Download as PDF Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at http:// www.eurocopter.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or 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. (f) This amendment becomes effective on September 12, 2011. Note: The subject of this AD is addressed in European Aviation Safety Agency (France) Emergency AD No. 2009–0109–E, dated May 7, 2009. Issued in Fort Worth, Texas, on July 21, 2011. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–21477 Filed 8–25–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28661; Directorate Identifier 2007–NM–013–AD; Amendment 39–16785; AD 2011–18–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 737–600, –700, –700C, –800, and –900 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installation of an automatic shutoff system for the center tank fuel boost pumps, and installation of a placard in the airplane flight deck if necessary. This AD also requires revisions to the Limitations and Normal Procedures sections of the airplane flight manual to advise the flightcrew of certain operating restrictions for airplanes equipped with an automated center tank fuel pump shutoff control. This AD further requires installation of a secondary control relay for the electrical control circuit of each of the two center tank fuel boost pumps. Additionally, this AD requires a revision to the maintenance program to incorporate Airworthiness Limitation (AWL) No. 28–AWL–23. This AD also provides an mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 15:41 Aug 25, 2011 Jkt 223001 option of installation and maintenance of universal fault interrupters using a certain supplemental type certificate, which terminates certain requirements of this AD. 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. DATES: This AD is effective September 30, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 30, 2011. ADDRESSES: 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 TDG Aerospace information identified in this AD, contact TDG Aerospace, Inc., 545 Corporate Drive, Escondido, California 92029; telephone 760–466– 1040; fax 760–466–1038; Internet http:// www.tdgaerospace.com; e-mail info@tdgaerospace.com. You may review copies of the referenced 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Tak Kobayashi, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 53317 Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: (425) 917–6499; fax: (425) 917–6590; e-mail: Takahisa.Kobayashi@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That SNPRM published in the Federal Register on March 8, 2011 (76 FR 12634). The original NPRM (72 FR 37479, July 10, 2007) proposed to require installation of an automatic shutoff system for the center tank fuel boost pumps, installation of a placard in the airplane flight deck if necessary, and concurrent modification of the P5–2 fuel control module assembly. The original NPRM also proposed to require revisions to the Limitations and Normal Procedures sections of the airplane flight manual (AFM) to advise the flightcrew of certain operating restrictions for airplanes equipped with an automated center tank fuel pump shutoff control. Additionally, the original NPRM proposed to require a revision to the Airworthiness Limitations (AWL) section of the Instructions for Continued Airworthiness (ICA) to incorporate AWL No. 28–AWL–19 and No. 28–AWL–23. The original NPRM further proposed to require installation of a secondary control relay for the electrical control circuit of each of the two center tank fuel boost pumps. The SNPRM proposed to revise the original NPRM by adding airplanes, adding additional operational testing of the automatic shutoff system for certain airplanes, removing the requirement for incorporating AWL No. 28–AWL–19 into the AWL section of the ICA, and adding an option of installation and maintenance of universal fault interrupters using a certain supplemental type certificate. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. Support for SNPRM Delta Airlines (Delta) stated that it has no objections to the SNPRM. Request To Correct Service Information Citation Boeing requested that we revise the fifth paragraph under the ‘‘Explanation E:\FR\FM\26AUR1.SGM 26AUR1 53318 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations of Additional Changes Made to this Supplemental NPRM’’ section of the SNPRM to correct the model designation portion of the document citation provided in that paragraph. Although we agree that there was a typographical error in the document citation specified in the ‘‘Explanation of Additional Changes Made to this Supplemental NPRM’’ section of the SNPRM, we do not agree to revise this AD in this regard, as that section is not restated in the final rule. No change to the AD is necessary in this regard. mstockstill on DSK4VPTVN1PROD with RULES Request To Include Definition in Paragraph (b) of the SNPRM Boeing requested that we revise paragraph (b) of the SNPRM to properly define ‘‘2001–08–24’’ as an airworthiness directive. We agree and have revised paragraph (b) of this AD accordingly. Request To Revise Conditions Specified in Paragraph (h) of the SNPRM Boeing requested that we revise paragraph (h) of the SNPRM to remove the last sentence of the paragraph, which specifies the conditions when a placard is not necessary. Boeing stated that this sentence is confusing and possibly contradictory, and that the placard requirement provided in those paragraphs is well defined without the use of this sentence. We agree partially. We agree to remove the first condition specified in the second to last sentence of paragraph (h) of this AD, which states, ‘‘If automatic shutoff systems are installed concurrently on all airplanes in an operator’s fleet in accordance with paragraph (g) of this AD * * *, the placard installation specified in this paragraph is not necessary.’’ If the automatic shutoff system is concurrently installed on all airplanes, there will be no airplanes on which a placard would be required to be installed. Therefore, this condition is unnecessary. We have revised paragraph (h) of this AD to remove this condition. We do not agree to remove the second condition in the second to last sentence of paragraph (h) of this AD. That condition provides an option to operators that prefer not to install a placard on any airplane in their fleet. If an operator intends to maintain fuel usage restrictions specified in 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), for all airplanes in the fleet until the automatic shutoff systems are installed on all of those airplanes, the operator is not required to install a placard, even after installing VerDate Mar<15>2010 15:41 Aug 25, 2011 Jkt 223001 the automatic shutoff system on any airplane in its fleet. We have determined that this option should remain available to operators, and have not revised paragraph (h) of this AD to remove this condition. We also have not revised paragraph (s) of this AD to remove the same condition specified in the second to last sentence of paragraph (h) of this AD. Also, we acknowledge that a reference to AD 2001–08–24, Amendment 39– 12201 (66 FR 20733, April 25, 2001), was inadvertently omitted in the last sentence of paragraph (h) of the SNPRM. We have added a reference to AD 2001– 08–24 in paragraph (h) of this AD, and provided additional clarification in the ‘‘Additional Changes Made to this AD’’ section of this AD. Request To Revise Proposed Wording of Placard in Paragraph (h) of the SNPRM Southwest Airlines (Southwest) requested that the SNPRM be revised to allow alternative wording for the placard required by paragraph (h) of the SNPRM. Southwest stated that it has a placard adjacent to the pilot’s primary flight display on all of its airplanes that are not equipped with an automatic shutoff system, which reads, ‘‘AD 2002– 19–52 fuel usage restrictions required.’’ Southwest reported that it is unable to find any language in either AD 2002– 19–52, Amendment 39–12900 (67 FR 61253, September 30, 2002), or AD 2002–24–51, Amendment 39–12992 (68 FR 10, January 2, 2003), that requires the placard text proposed in paragraph (h) of the SNPRM. We agree partially. We have determined that clarification of paragraph (h) of this final rule is necessary to prevent inadvertent removal of the placard required by paragraph (h) of this AD and by paragraph (e) of AD 2002–19–52, Amendment 39–12900 (67 FR 61253, September 30, 2002). As discussed in the preamble of the SNPRM, AD 2002– 19–52 requires installation of a placard, and provides an optional terminating action that allows removal of that placard. The intent of the placard installation required by AD 2002–19–52 is to address mixed operation of the airplanes with and without the optional terminating action accomplished within an operator’s fleet. After issuance of AD 2002–19–52, we issued AD 2002–24–51, Amendment 39–12992 (68 FR 10, January 2, 2003), to mandate fuel usage restrictions identical to those required by AD 2002–19–52, to address an unsafe condition not related to AD 2002–19– 52. Airworthiness Directive 2002–24–51 did not require installation of a placard, because terminating action for that AD PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 was not available at the time, and, therefore, there was no concern about mixed fleet operation. We do not agree to revise the placard wording required by paragraph (h) of this AD. However, if a placard that refers to AD 2002–19–52, Amendment 39–12900 (67 FR 61253, September 30, 2002), already exists on an airplane, we have determined that use of that placard does meet the placard installation requirement of paragraph (h) of this AD. Therefore, we have revised paragraph (h) of this AD to state that installation of a placard in accordance with paragraph (e) of AD 2002–19–52 is acceptable for compliance with the requirements of paragraph (h) of this AD, and that the placard may be removed from an airplane only once the 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 have been accomplished. Request To Reference Latest AWL Revision in Paragraph (k) of the SNPRM Boeing requested that we revise paragraph (k) of the SNPRM to reference the latest revision of the maintenance planning data (MPD) document. Boeing stated that the document specified in paragraph (k) of the SNPRM has been revised, and that the applicable subsection has changed from ‘‘G’’ to ‘‘E.1.’’ in Revision February 2011. We agree that this AD should refer to the current revision of the MPD document specified in paragraph (k) of this AD. Therefore, we have revised paragraph (k) of this AD to refer to 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. We have also added new paragraph (t) to this AD (and re-identified subsequent paragraphs accordingly) to give credit to operators that accomplish the AWL revision required by paragraph (k) of this AD before the effective date of this AD using any of the following revisions 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: • Revision March 2008 • Revision April 2008 • Revision June 2008 • Revision February 2009 • Revision March 2009 • Revision August 2009 E:\FR\FM\26AUR1.SGM 26AUR1 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations • • • • • • Revision September 2009 Revision November 2009 Revision January 2010 Revision May 2010 Revision July 2010 Revision August 2010 Paragraph (t) of this AD also provides credit to operators that accomplish the AWL revision required by paragraph (k) of this AD before the effective date of this AD using 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. mstockstill on DSK4VPTVN1PROD with RULES Request To Clarify Terminating Action for Paragraphs (m) and (n) of SNPRM Delta requested that we revise paragraphs (m) and (n) of the SNPRM to clarify that accomplishing the actions specified in paragraph (s) of the SNPRM terminates the actions required in paragraphs (m) and (n) of the SNPRM. Delta pointed out that paragraph (s) of the SNPRM terminates only paragraphs (g) through (k) of the SNPRM, and not paragraphs (m) and (n) of the SNPRM. Delta stated that operators planning to comply with the proposed requirements by installing universal fault interrupters (UFIs) in accordance with paragraph (s) of the SNPRM will not accomplish paragraphs (g), (h), and (i) of the SNPRM. Therefore, Delta asserted that, as the SNPRM is currently written, operators that do not do the actions specified in paragraphs (g), (h), and (i) of the SNPRM will not be able to comply with the requirements of paragraphs (m) and (n) of the SNPRM. We agree. Accomplishing the optional terminating action specified in paragraph (s) of this AD terminates the requirements of paragraphs (g) through (k) of this AD, making the optional terminating action specified in paragraph (s) of this AD equivalent to the actions required by paragraphs (g) through (k) of this AD. Therefore, complying with paragraph (s) of this AD meets the condition required to terminate the requirements of paragraph (a) of AD 2001–08–24, Amendment 39– 12201 (66 FR 20733, April 25, 2001), and paragraph (b) of AD 2002–24–51, Amendment 39–12992 (68 FR 10, January 2, 2003). We have revised paragraphs (m) and (n) of this AD to state that accomplishing the actions (i.e., optional terminating action) specified in paragraph (s) of this AD terminates the requirements of paragraph (a) of AD 2001–08–24 and paragraph (b) of AD 2002–24–51. VerDate Mar<15>2010 15:41 Aug 25, 2011 Jkt 223001 Request To Provide Credit for Aerospace Supplemental Type Certificate (STC) Continental Airlines (Continental) requested that we revise the SNPRM to give credit for incorporating universal fault interrupters (UFIs) using TDG Aerospace STC ST02076LA before the effective date of the AD. Continental pointed out that paragraphs (q) and (r) of the SNPRM provide credit for actions done before the effective date of the AD using other service information. While we do agree that installing TDG Aerospace UFIs before the effective date of this AD is acceptable for terminating certain actions required by this AD, we do not agree to revise the AD to provide specific credit for those actions. Installing TDG Aerospace UFIs, as specified in paragraph (s) of this AD, is acceptable both before and after the effective date of this AD. Operators are always permitted to accomplish the requirements of an AD at a time earlier than the specified compliance time. We have not changed the AD in this regard. Request To Revise Paragraph (v) of the SNPRM To Add Contact Information Delta requested that we revise paragraph (v) of the SNPRM to add contact information for TDG Aerospace. Delta pointed out that contact information for the other service information identified in the SNPRM is provided, but not for TDG Aerospace. We agree partially. We do not agree to revise paragraph (v) of the SNPRM, because that paragraph is not restated in this final rule. However, we do agree to provide contact information for TDG Aerospace. We have revised the ADDRESSES section of this AD to include this contact information. Additional Changes Made to This AD We have revised paragraph (h) of this AD to clarify when a placard is not necessary. We have determined that the second to last sentence of paragraph (h) of this AD should also refer to AD 2001– 08–24, Amendment 39–12201 (66 FR 20733, April 25, 2001), for clarity. Operators that choose to maintain the fuel usage restrictions of AD 2002–24– 51, Amendment 39–12992 (68 FR 10, January 2, 2003), for all airplanes in their fleet do not meet the condition to terminate AD 2002–24–51 and AD 2001–08–24 until the actions required by paragraphs (g) and (i) of this AD are accomplished on all airplanes in their fleet. Therefore, those operators are otherwise required to comply with the requirements of AD 2001–08–24, regardless of whether that AD is mentioned in paragraph (h) of this AD. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 53319 Therefore, this change does not increase the burden on operators. We have revised paragraph (s) of this AD to specify that installation of TDG Aerospace UFIs, as provided in that paragraph, must be done in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, because referring to the STC now violates Office of the Federal Register (OFR) policies for approval of optional materials ‘‘incorporated by reference’’ in rules. We have added Note 5 to this AD to specify that additional guidance on installing TDG Aerospace UFIs can be found in TDG Aerospace STC ST02076LA. We have also revised paragraph (s) of this AD to clarify the time limit for doing the optional terminating action. Since paragraph (s) of this AD terminates the actions required by paragraphs (g) through (k) of this AD, if done, paragraph (s) of this AD must be accomplished within the earliest time specified among those paragraphs to be considered terminating action; that earliest time is 36 months. Additionally, we have revised paragraph (s) of this AD to allow the use of alternative placard wording that is approved by an appropriate FAA Principal Operations Inspector, instead of requiring approval of alternative placard wording as an alternative method of compliance in accordance with paragraph (u) of this AD. We have also revised paragraph (s) of this AD by adding a statement to allow installation of a placard in accordance with paragraph (e) of AD 2002–19–52, Amendment 39–12900 (67 FR 61253, September 30, 2002). Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously— and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD affects 685 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\26AUR1.SGM 26AUR1 53320 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations ESTIMATED COSTS Number of U.S.-registered airplanes Action Labor cost Parts cost Cost per product Installation of the automatic shutoff system (Boeing Alert Service Bulletin 737– 28A1206). Between 94 and 117 (depending on airplane configuration) work-hours × $85 per hour = Between $7,990 and $9,945. 1 work-hour × $85 per hour = $85. 1 work-hour × $85 per hour = $85. 68 work-hours × $85 per hour = $5,780. Between $22,994 and $30,197 (depending on airplane configuration). Between $30,984 and $40,142. 538 Between $16,669,392 and $21,596,396. $10 .............................. $95 .............................. 685 $65,075. None ............................ $85 .............................. 538 $45,730. $3,274 ......................... $9,054 ......................... 685 $6,201,990. 1 work-hour × $85 per hour = $85. None ............................ $85 .............................. 685 $58,225. Placard installation, if necessary. AFM revision ................. Installation of secondary pump control relays (Boeing Alert Service Bulletin 737– 28A1248). AWL revision to add 28–AWL–23. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. mstockstill on DSK4VPTVN1PROD with RULES Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and VerDate Mar<15>2010 15:41 Aug 25, 2011 Jkt 223001 (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2011–18–03 The Boeing Company: Amendment 39–16785; Docket No. FAA–2007–28661; Directorate Identifier 2007–NM–013–AD. Effective Date (a) This AD is effective September 30, 2011. Affected ADs (b) Accomplishing certain requirements of this AD terminates certain requirements of AD 2001–08–24, Amendment 39–12201 (66 FR 20733, April 25, 2001); AD 2002–24–51, Amendment 39–12992 (68 FR 10, January 2, 2003); and AD 2008–24–51, Amendment 39– 15781 (74 FR 8155, February 24, 2009). Airworthiness Directive 2002–19–52, Amendment 39–12900 (67 FR 61253, September 30, 2002), is affected by this AD. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Cost on U.S. operators Applicability (c) 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. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 28, Fuel. Unsafe Condition (e) 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. E:\FR\FM\26AUR1.SGM 26AUR1 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations (f) 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 mstockstill on DSK4VPTVN1PROD with RULES 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 VerDate Mar<15>2010 15:41 Aug 25, 2011 Jkt 223001 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. 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 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 BILLING CODE 4910–13–P E:\FR\FM\26AUR1.SGM 26AUR1 ER26AU11.015</GPH> Compliance 53321 53322 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 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. mstockstill on DSK4VPTVN1PROD with RULES ‘‘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. VerDate Mar<15>2010 15:41 Aug 25, 2011 Jkt 223001 ‘‘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. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 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. E:\FR\FM\26AUR1.SGM 26AUR1 53323 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 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-ANMSeattle-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 mstockstill on DSK4VPTVN1PROD with RULES Document Revision Boeing Alert Service Bulletin 737–28A1206 ............................................................................................ Boeing Alert Service Bulletin 737–28A1248 ............................................................................................ 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. 2 ............................ 2 ............................ March 2011 ........... (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in table 1 VerDate Mar<15>2010 15:41 Aug 25, 2011 Jkt 223001 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 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 Date May 21, 2009. August 28, 2009. March 2011. Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax E:\FR\FM\26AUR1.SGM 26AUR1 53324 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0823; Directorate Identifier 2011–SW–018–AD; Amendment 39–16765; AD 2011–17–01] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Model A109A, A109A II, A109C, and A109K2 Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: This amendment supersedes an existing emergency airworthiness directive (EAD) for the specified Agusta S.p.A. (Agusta) model helicopters. That EAD currently requires inspecting the main rotor scissor fitting assembly to determine if there are 2 washers installed under the head of each main rotor scissor fitting assembly fixing bolt (fixing bolt). If there are not 2 washers installed under the head of each fixing bolt, that EAD requires replacing each fixing bolt and installing 2 washers under the head of each fixing bolt. This superseding airworthiness directive (AD) is prompted by the determination that a wrong part number (P/N) for the main rotor scissor fitting assembly was listed in the EAD. This AD retains the requirements of the EAD and corrects a P/N for the main rotor scissor fitting assembly. The actions specified by this AD are intended to prevent a crack in a fixing bolt, failure of a fixing bolt, and mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 15:41 Aug 25, 2011 Jkt 223001 subsequent loss of control of the helicopter. DATES: Effective September 12, 2011. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 12, 2011. Comments for inclusion in the Rules Docket must be received on or before October 25, 2011. ADDRESSES: Use one of the following addresses to submit comments on this AD: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this AD from Agusta Westland, Customer Support & Services, Via Per Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone 39- 0331–711133; fax 39 0331 711180; or at http:// www.agustawestland.com/technicalbullettins. Examining the Docket: You may examine the docket that contains the AD, any comments, and other information on the Internet at http:// www.regulations.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647– 5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Sharon Miles, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, ASW–111, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Discussion On January 13, 2010, we issued EAD 2010–02–51 for the Agusta Model A109A, A109A II, A109C, and A109K2 PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 helicopters, which requires, within 5 hours time-in-service (TIS), inspecting the main rotor scissor fitting assembly, P/N 109–0110–67 and P/N 109–0110– 58, to determine if there were 2 washers installed under the head of each fixing bolt, P/N 109–0101–78–5. That action was prompted by an incident where 2 of the 3 installed fixing bolts on a Model A109K2 helicopter had cracked in flight. The manufacturer’s investigation revealed that the crack was caused by inadequate information in the technical publication for installing the fixing bolts. This condition, if not detected and corrected, could result in failure of a fixing bolt and subsequent loss of control of the helicopter. Since issuing EAD 2010–02–51, we have determined that the EAD contains an incorrect P/N for the main rotor scissor fitting assembly as listed in paragraph (a) of the Compliance section. The EAD states P/N ‘‘109–0110–58’’ and the correct P/N is ‘‘109–0101–58’’. Therefore, we are issuing this superseding AD to correct a P/N for the main rotor scissor fitting assembly. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Emergency AD 2009–0274–E, dated December 18, 2009 (EAD 2009–0274–E) to correct an unsafe condition for the Agusta Model A109A, A109A II, A109C, and A109K2 model helicopters. EASA states that failure of the fixing bolt ‘‘might lead to loss of control of the helicopter.’’ Related Service Information Agusta has issued Mandatory Alert Bollettino Tecnico (BT) No. 109K–53 for Model A109K2 helicopters and Mandatory Alert BT No. 109–131 for Model A109A, A109A II, and A109C helicopters, both dated December 18, 2009. The BTs specify a one-time inspection for correct installation of the main rotor scissor fitting assembly by determining if 2 washers are installed under the head of each fixing bolt. If 2 washers are not installed under the head of each fixing bolt, the BTs specify replacing each fixing bolt with an airworthy fixing bolt and installing 2 washers under the head of each fixing bolt. EASA classified this service bulletin as mandatory and issued EAD No. 2009–0274–E to ensure the continued airworthiness of these helicopters. FAA’s Evaluation and Unsafe Condition Determination These helicopters have been approved by the aviation authority of Italy, and are approved for operation in the United States. Pursuant to our bilateral E:\FR\FM\26AUR1.SGM 26AUR1

Agencies

[Federal Register Volume 76, Number 166 (Friday, August 26, 2011)]
[Rules and Regulations]
[Pages 53317-53324]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-21617]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28661; Directorate Identifier 2007-NM-013-AD; 
Amendment 39-16785; AD 2011-18-03]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 737-600, -700, 
-700C, -800, and -900 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD requires installation of an automatic 
shutoff system for the center tank fuel boost pumps, and installation 
of a placard in the airplane flight deck if necessary. This AD also 
requires revisions to the Limitations and Normal Procedures sections of 
the airplane flight manual to advise the flightcrew of certain 
operating restrictions for airplanes equipped with an automated center 
tank fuel pump shutoff control. This AD further requires installation 
of a secondary control relay for the electrical control circuit of each 
of the two center tank fuel boost pumps. Additionally, this AD requires 
a revision to the maintenance program to incorporate Airworthiness 
Limitation (AWL) No. 28-AWL-23. This AD also provides an option of 
installation and maintenance of universal fault interrupters using a 
certain supplemental type certificate, which terminates certain 
requirements of this AD. 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.

DATES: This AD is effective September 30, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of September 30, 
2011.

ADDRESSES: 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 TDG 
Aerospace information identified in this AD, contact TDG Aerospace, 
Inc., 545 Corporate Drive, Escondido, California 92029; telephone 760-
466-1040; fax 760-466-1038; Internet http://www.tdgaerospace.com; e-
mail info@tdgaerospace.com.
    You may review copies of the referenced 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Tak Kobayashi, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: 
(425) 917-6499; fax: (425) 917-6590; e-mail: 
Takahisa.Kobayashi@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to include an airworthiness directive (AD) that 
would apply to the specified products. That SNPRM published in the 
Federal Register on March 8, 2011 (76 FR 12634). The original NPRM (72 
FR 37479, July 10, 2007) proposed to require installation of an 
automatic shutoff system for the center tank fuel boost pumps, 
installation of a placard in the airplane flight deck if necessary, and 
concurrent modification of the P5-2 fuel control module assembly. The 
original NPRM also proposed to require revisions to the Limitations and 
Normal Procedures sections of the airplane flight manual (AFM) to 
advise the flightcrew of certain operating restrictions for airplanes 
equipped with an automated center tank fuel pump shutoff control. 
Additionally, the original NPRM proposed to require a revision to the 
Airworthiness Limitations (AWL) section of the Instructions for 
Continued Airworthiness (ICA) to incorporate AWL No. 28-AWL-19 and No. 
28-AWL-23. The original NPRM further proposed to require installation 
of a secondary control relay for the electrical control circuit of each 
of the two center tank fuel boost pumps. The SNPRM proposed to revise 
the original NPRM by adding airplanes, adding additional operational 
testing of the automatic shutoff system for certain airplanes, removing 
the requirement for incorporating AWL No. 28-AWL-19 into the AWL 
section of the ICA, and adding an option of installation and 
maintenance of universal fault interrupters using a certain 
supplemental type certificate.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Support for SNPRM

    Delta Airlines (Delta) stated that it has no objections to the 
SNPRM.

Request To Correct Service Information Citation

    Boeing requested that we revise the fifth paragraph under the 
``Explanation

[[Page 53318]]

of Additional Changes Made to this Supplemental NPRM'' section of the 
SNPRM to correct the model designation portion of the document citation 
provided in that paragraph.
    Although we agree that there was a typographical error in the 
document citation specified in the ``Explanation of Additional Changes 
Made to this Supplemental NPRM'' section of the SNPRM, we do not agree 
to revise this AD in this regard, as that section is not restated in 
the final rule. No change to the AD is necessary in this regard.

Request To Include Definition in Paragraph (b) of the SNPRM

    Boeing requested that we revise paragraph (b) of the SNPRM to 
properly define ``2001-08-24'' as an airworthiness directive. We agree 
and have revised paragraph (b) of this AD accordingly.

Request To Revise Conditions Specified in Paragraph (h) of the SNPRM

    Boeing requested that we revise paragraph (h) of the SNPRM to 
remove the last sentence of the paragraph, which specifies the 
conditions when a placard is not necessary. Boeing stated that this 
sentence is confusing and possibly contradictory, and that the placard 
requirement provided in those paragraphs is well defined without the 
use of this sentence.
    We agree partially. We agree to remove the first condition 
specified in the second to last sentence of paragraph (h) of this AD, 
which states, ``If automatic shutoff systems are installed concurrently 
on all airplanes in an operator's fleet in accordance with paragraph 
(g) of this AD * * *, the placard installation specified in this 
paragraph is not necessary.'' If the automatic shutoff system is 
concurrently installed on all airplanes, there will be no airplanes on 
which a placard would be required to be installed. Therefore, this 
condition is unnecessary. We have revised paragraph (h) of this AD to 
remove this condition.
    We do not agree to remove the second condition in the second to 
last sentence of paragraph (h) of this AD. That condition provides an 
option to operators that prefer not to install a placard on any 
airplane in their fleet. If an operator intends to maintain fuel usage 
restrictions specified in 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), for all airplanes in the fleet until the automatic 
shutoff systems are installed on all of those airplanes, the operator 
is not required to install a placard, even after installing the 
automatic shutoff system on any airplane in its fleet. We have 
determined that this option should remain available to operators, and 
have not revised paragraph (h) of this AD to remove this condition. We 
also have not revised paragraph (s) of this AD to remove the same 
condition specified in the second to last sentence of paragraph (h) of 
this AD.
    Also, we acknowledge that a reference to AD 2001-08-24, Amendment 
39-12201 (66 FR 20733, April 25, 2001), was inadvertently omitted in 
the last sentence of paragraph (h) of the SNPRM. We have added a 
reference to AD 2001-08-24 in paragraph (h) of this AD, and provided 
additional clarification in the ``Additional Changes Made to this AD'' 
section of this AD.

Request To Revise Proposed Wording of Placard in Paragraph (h) of the 
SNPRM

    Southwest Airlines (Southwest) requested that the SNPRM be revised 
to allow alternative wording for the placard required by paragraph (h) 
of the SNPRM. Southwest stated that it has a placard adjacent to the 
pilot's primary flight display on all of its airplanes that are not 
equipped with an automatic shutoff system, which reads, ``AD 2002-19-52 
fuel usage restrictions required.'' Southwest reported that it is 
unable to find any language in either AD 2002-19-52, Amendment 39-12900 
(67 FR 61253, September 30, 2002), or AD 2002-24-51, Amendment 39-12992 
(68 FR 10, January 2, 2003), that requires the placard text proposed in 
paragraph (h) of the SNPRM.
    We agree partially. We have determined that clarification of 
paragraph (h) of this final rule is necessary to prevent inadvertent 
removal of the placard required by paragraph (h) of this AD and by 
paragraph (e) of AD 2002-19-52, Amendment 39-12900 (67 FR 61253, 
September 30, 2002). As discussed in the preamble of the SNPRM, AD 
2002-19-52 requires installation of a placard, and provides an optional 
terminating action that allows removal of that placard. The intent of 
the placard installation required by AD 2002-19-52 is to address mixed 
operation of the airplanes with and without the optional terminating 
action accomplished within an operator's fleet. After issuance of AD 
2002-19-52, we issued AD 2002-24-51, Amendment 39-12992 (68 FR 10, 
January 2, 2003), to mandate fuel usage restrictions identical to those 
required by AD 2002-19-52, to address an unsafe condition not related 
to AD 2002-19-52. Airworthiness Directive 2002-24-51 did not require 
installation of a placard, because terminating action for that AD was 
not available at the time, and, therefore, there was no concern about 
mixed fleet operation.
    We do not agree to revise the placard wording required by paragraph 
(h) of this AD. However, if a placard that refers to AD 2002-19-52, 
Amendment 39-12900 (67 FR 61253, September 30, 2002), already exists on 
an airplane, we have determined that use of that placard does meet the 
placard installation requirement of paragraph (h) of this AD. 
Therefore, we have revised paragraph (h) of this AD to state that 
installation of a placard in accordance with paragraph (e) of AD 2002-
19-52 is acceptable for compliance with the requirements of paragraph 
(h) of this AD, and that the placard may be removed from an airplane 
only once the 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 have been accomplished.

Request To Reference Latest AWL Revision in Paragraph (k) of the SNPRM

    Boeing requested that we revise paragraph (k) of the SNPRM to 
reference the latest revision of the maintenance planning data (MPD) 
document. Boeing stated that the document specified in paragraph (k) of 
the SNPRM has been revised, and that the applicable subsection has 
changed from ``G'' to ``E.1.'' in Revision February 2011.
    We agree that this AD should refer to the current revision of the 
MPD document specified in paragraph (k) of this AD. Therefore, we have 
revised paragraph (k) of this AD to refer to 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.
    We have also added new paragraph (t) to this AD (and re-identified 
subsequent paragraphs accordingly) to give credit to operators that 
accomplish the AWL revision required by paragraph (k) of this AD before 
the effective date of this AD using any of the following revisions 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:

 Revision March 2008
 Revision April 2008
 Revision June 2008
 Revision February 2009
 Revision March 2009
 Revision August 2009

[[Page 53319]]

 Revision September 2009
 Revision November 2009
 Revision January 2010
 Revision May 2010
 Revision July 2010
 Revision August 2010
    Paragraph (t) of this AD also provides credit to operators that 
accomplish the AWL revision required by paragraph (k) of this AD before 
the effective date of this AD using 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.

Request To Clarify Terminating Action for Paragraphs (m) and (n) of 
SNPRM

    Delta requested that we revise paragraphs (m) and (n) of the SNPRM 
to clarify that accomplishing the actions specified in paragraph (s) of 
the SNPRM terminates the actions required in paragraphs (m) and (n) of 
the SNPRM. Delta pointed out that paragraph (s) of the SNPRM terminates 
only paragraphs (g) through (k) of the SNPRM, and not paragraphs (m) 
and (n) of the SNPRM. Delta stated that operators planning to comply 
with the proposed requirements by installing universal fault 
interrupters (UFIs) in accordance with paragraph (s) of the SNPRM will 
not accomplish paragraphs (g), (h), and (i) of the SNPRM. Therefore, 
Delta asserted that, as the SNPRM is currently written, operators that 
do not do the actions specified in paragraphs (g), (h), and (i) of the 
SNPRM will not be able to comply with the requirements of paragraphs 
(m) and (n) of the SNPRM.
    We agree. Accomplishing the optional terminating action specified 
in paragraph (s) of this AD terminates the requirements of paragraphs 
(g) through (k) of this AD, making the optional terminating action 
specified in paragraph (s) of this AD equivalent to the actions 
required by paragraphs (g) through (k) of this AD. Therefore, complying 
with paragraph (s) of this AD meets the condition required to terminate 
the requirements of paragraph (a) of AD 2001-08-24, Amendment 39-12201 
(66 FR 20733, April 25, 2001), and paragraph (b) of AD 2002-24-51, 
Amendment 39-12992 (68 FR 10, January 2, 2003). We have revised 
paragraphs (m) and (n) of this AD to state that accomplishing the 
actions (i.e., optional terminating action) specified in paragraph (s) 
of this AD terminates the requirements of paragraph (a) of AD 2001-08-
24 and paragraph (b) of AD 2002-24-51.

Request To Provide Credit for Aerospace Supplemental Type Certificate 
(STC)

    Continental Airlines (Continental) requested that we revise the 
SNPRM to give credit for incorporating universal fault interrupters 
(UFIs) using TDG Aerospace STC ST02076LA before the effective date of 
the AD. Continental pointed out that paragraphs (q) and (r) of the 
SNPRM provide credit for actions done before the effective date of the 
AD using other service information.
    While we do agree that installing TDG Aerospace UFIs before the 
effective date of this AD is acceptable for terminating certain actions 
required by this AD, we do not agree to revise the AD to provide 
specific credit for those actions. Installing TDG Aerospace UFIs, as 
specified in paragraph (s) of this AD, is acceptable both before and 
after the effective date of this AD. Operators are always permitted to 
accomplish the requirements of an AD at a time earlier than the 
specified compliance time. We have not changed the AD in this regard.

Request To Revise Paragraph (v) of the SNPRM To Add Contact Information

    Delta requested that we revise paragraph (v) of the SNPRM to add 
contact information for TDG Aerospace. Delta pointed out that contact 
information for the other service information identified in the SNPRM 
is provided, but not for TDG Aerospace.
    We agree partially. We do not agree to revise paragraph (v) of the 
SNPRM, because that paragraph is not restated in this final rule. 
However, we do agree to provide contact information for TDG Aerospace. 
We have revised the ADDRESSES section of this AD to include this 
contact information.

Additional Changes Made to This AD

    We have revised paragraph (h) of this AD to clarify when a placard 
is not necessary. We have determined that the second to last sentence 
of paragraph (h) of this AD should also refer to AD 2001-08-24, 
Amendment 39-12201 (66 FR 20733, April 25, 2001), for clarity. 
Operators that choose to maintain the fuel usage restrictions of AD 
2002-24-51, Amendment 39-12992 (68 FR 10, January 2, 2003), for all 
airplanes in their fleet do not meet the condition to terminate AD 
2002-24-51 and AD 2001-08-24 until the actions required by paragraphs 
(g) and (i) of this AD are accomplished on all airplanes in their 
fleet. Therefore, those operators are otherwise required to comply with 
the requirements of AD 2001-08-24, regardless of whether that AD is 
mentioned in paragraph (h) of this AD. Therefore, this change does not 
increase the burden on operators.
    We have revised paragraph (s) of this AD to specify that 
installation of TDG Aerospace UFIs, as provided in that paragraph, must 
be done in accordance with a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA, because referring to the STC 
now violates Office of the Federal Register (OFR) policies for approval 
of optional materials ``incorporated by reference'' in rules. We have 
added Note 5 to this AD to specify that additional guidance on 
installing TDG Aerospace UFIs can be found in TDG Aerospace STC 
ST02076LA.
    We have also revised paragraph (s) of this AD to clarify the time 
limit for doing the optional terminating action. Since paragraph (s) of 
this AD terminates the actions required by paragraphs (g) through (k) 
of this AD, if done, paragraph (s) of this AD must be accomplished 
within the earliest time specified among those paragraphs to be 
considered terminating action; that earliest time is 36 months.
    Additionally, we have revised paragraph (s) of this AD to allow the 
use of alternative placard wording that is approved by an appropriate 
FAA Principal Operations Inspector, instead of requiring approval of 
alternative placard wording as an alternative method of compliance in 
accordance with paragraph (u) of this AD.
    We have also revised paragraph (s) of this AD by adding a statement 
to allow installation of a placard in accordance with paragraph (e) of 
AD 2002-19-52, Amendment 39-12900 (67 FR 61253, September 30, 2002).

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously--and minor editorial 
changes. We have determined that these minor changes:
     [Agr]re consistent with the intent that was proposed in 
the SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 685 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 53320]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
           Action                Labor cost       Parts cost        Cost per       registered      Cost on U.S.
                                                                    product         airplanes       operators
----------------------------------------------------------------------------------------------------------------
Installation of the           Between 94 and   Between $22,994  Between $30,984             538  Between
 automatic shutoff system      117 (depending   and $30,197      and $40,142.                     $16,669,392
 (Boeing Alert Service         on airplane      (depending on                                     and
 Bulletin 737-28A1206).        configuration)   airplane                                          $21,596,396.
                               work-hours x     configuration).
                               $85 per hour =
                               Between $7,990
                               and $9,945.
Placard installation, if      1 work-hour x    $10............  $95............             685  $65,075.
 necessary.                    $85 per hour =
                               $85.
AFM revision................  1 work-hour x    None...........  $85............             538  $45,730.
                               $85 per hour =
                               $85.
Installation of secondary     68 work-hours x  $3,274.........  $9,054.........             685  $6,201,990.
 pump control relays (Boeing   $85 per hour =
 Alert Service Bulletin 737-   $5,780.
 28A1248).
AWL revision to add 28-AWL-   1 work-hour x    None...........  $85............             685  $58,225.
 23.                           $85 per hour =
                               $85.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2011-18-03 The Boeing Company: Amendment 39-16785; Docket No. FAA-
2007-28661; Directorate Identifier 2007-NM-013-AD.

Effective Date

    (a) This AD is effective September 30, 2011.

Affected ADs

    (b) Accomplishing certain requirements of this AD terminates 
certain requirements of AD 2001-08-24, Amendment 39-12201 (66 FR 
20733, April 25, 2001); AD 2002-24-51, Amendment 39-12992 (68 FR 10, 
January 2, 2003); and AD 2008-24-51, Amendment 39-15781 (74 FR 8155, 
February 24, 2009). Airworthiness Directive 2002-19-52, Amendment 
39-12900 (67 FR 61253, September 30, 2002), is affected by this AD.

Applicability

    (c) 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.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 28, Fuel.

Unsafe Condition

    (e) 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.

[[Page 53321]]

Compliance

    (f) 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
[GRAPHIC] [TIFF OMITTED] TR26AU11.015

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

[[Page 53322]]

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.

[[Page 53323]]

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-        2.................................  May 21, 2009.
 28A1206.
Boeing Alert Service Bulletin 737-        2.................................  August 28, 2009.
 28A1248.
AWL No. 28-AWL-23 of Subsection E, AWLs-- March 2011........................  March 2011.
 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.
----------------------------------------------------------------------------------------------------------------

    (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

[[Page 53324]]

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