Airworthiness Directives; The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 63229-63235 [2011-26242]

Download as PDF 63229 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Proposed Rules Size standards in millions of dollars NAICS codes NAICS U.S. industry title 515112 ......................................................... 515120 ......................................................... 515210 ......................................................... Radio Stations ............................................................................... Television Broadcasting ................................................................. 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Libraries and Archives ................................................................... * * * 519190 ......................................................... * * * All Other Information Services ....................................................... * * * * Dated: July 22, 2011. Karen G. Mills, Administrator. [FR Doc. 2011–26208 Filed 10–7–11; 8:45 am] BILLING CODE 8025–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1068; Directorate Identifier 2010–NM–189–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD would require installing an automatic shutoff system for the center and auxiliary tank fuel boost pumps, as applicable, and installing a placard in the airplane flight deck if necessary; replacing the P5–2 fuel system module assembly; and installing the uncommanded on (UCO) protection system for the center and auxiliary tank fuel boost pumps, as applicable. This proposed AD would also require revisions to the Limitations and Normal Procedures sections of the airplane flight manual to advise the flightcrew of certain operating restrictions for mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:32 Oct 11, 2011 Jkt 223001 * * airplanes equipped with an automatic shutoff system. This proposed AD would also require revising the maintenance program by incorporating new airworthiness limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This proposed AD was prompted by fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent operation of the center and auxiliary tank fuel boost pumps 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 and auxiliary fuel tanks. These conditions, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by November 28, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 Size standards in number of employees 35.5 35.5 35.5 * 30.0 * 30.0 * 30.0 * 25.5 14.0 * 25.5 * * & 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. 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 https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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; telephone: 425–917–6499; fax: 425–917–6590; email: Takahisa.Kobayashi@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to E:\FR\FM\12OCP1.SGM 12OCP1 63230 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2011–1068; Directorate Identifier 2010– NM–189–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to VerDate Mar<15>2010 17:32 Oct 11, 2011 Jkt 223001 flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. The manufacturer has found that certain failures will result in the center and auxiliary tank fuel boost pumps continuing to run after the tank has been depleted. Depending on the failure, pump low pressure may not be annunciated, or power may not be removed from the pump when the pump has been commanded ‘‘OFF.’’ Operation of the center and auxiliary tank fuel boost pumps with continuous low pressure could lead to friction sparks or overheating in the fuel pump inlet. This condition, if not corrected, could result in a fuel tank explosion and consequent loss of the airplane. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 737–28A1216, Original Issue, dated July 29, 2010, which describes procedures for installing the automatic shutoff system for the center and auxiliary fuel tank boost pumps, as applicable, on Model 737–300, –400, and –500 series airplanes; and refers to Airworthiness Limitation (AWL) No. 28–AWL–20 and No. 28–AWL–21 that are related to the modifications specified in that service bulletin. We have also reviewed Boeing Alert Service Bulletin 737–28A1228, Original Issue, dated August 2, 2010, which describes procedures for installing the automatic shutoff system for the center and auxiliary fuel tank boost pumps, as applicable, on Model 737–100, –200, and –200C series airplanes; and refers to AWL No. 28–AWL–21 and AWL No. 28–AWL–22 that are related to the modifications specified in that service bulletin. Boeing Alert Service Bulletins 737– 28A1216, Original Issue, dated July 29, 2010; and 737–28A1228, Original Issue, dated August 2, 2010; specify prior or concurrent accomplishment of Boeing Service Bulletin 737–28A1210, Original Issue, dated August 2, 2010, which describes procedures for replacing the P5–2 fuel system module assembly with a new or modified P5–2 fuel system PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 module assembly having a new part number, for Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. Boeing Service Bulletin 737– 28A1210, Original Issue, dated August 2, 2010, refers to BAE Systems Service Bulletin 69–37335–28–04, Revision 2, dated February 10, 2010, as an additional source of guidance for modifying and updating the existing P5–2 fuel system module assembly part numbers to new part numbers. We have also reviewed Boeing Alert Service Bulletin 737–28A1227, Revision 1, dated July 18, 2011. The service information describes procedures for installing the ‘‘un-commanded ON’’ protection system for the center and auxiliary fuel boost pumps, as applicable, on airplanes. The installation includes installing new relays and toggle switches in the J2802 box assembly located in the electronic equipment bay (E/E bay), and changing and adding new wire bundles that route from the J2802 box assembly to the P5 forward overhead panel and the P6 disconnect panels. This service bulletin also refers to AWL No. 28–AWL–24 and No. 28–AWL–25 that are related to the modifications specified in that service bulletin for Model 737–100, –200, and –200C series airplanes; and AWL No. 28–AWL–23 and No. 28–AWL–24 that are related to the modifications specified in that service bulletin for Model 737–300, –400, and –500 airplanes. We have also reviewed Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737–100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278–CMR, Revision July 2011, which contains the following airworthiness limitations: • For Model 737–300, –400, and –500 series airplanes that have incorporated Boeing Alert Service Bulletin 737– 28A1216, AWLs No. 28–AWL–20 and No. 28–AWL–21 are airworthiness limitation instructions (ALIs) for an operational check of the installed automatic shutoff system. • For Model 737–100, –200, and –200C series airplanes that have incorporated Boeing Alert Service Bulletin 737–28A1228, AWLs No. 28– AWL–21 and No. 28–AWL–22 are ALIs for an operational check of the installed automatic shutoff system. • For Model 737–300, –400, and –500 series airplanes that have incorporated Boeing Alert Service Bulletin 737– 28A1227, AWLs No. 28–AWL–23 and No. 28–AWL–24 are ALIs for an operational check of the installed E:\FR\FM\12OCP1.SGM 12OCP1 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS power-failed-on (un-commanded ON) protection system. • For Model 737–100, –200, and –200C series airplanes that have incorporated Boeing Alert Service Bulletin 737–28A1227, AWL No. 28– AWL–24 and No. 28–AWL–25 are ALIs for an operational check of the installed power-failed-on (un-commanded ON) protection system. Other Relevant Rulemaking On April 18, 2001, we issued AD 2001–08–24, Amendment 39–12201 (66 FR 20733, April 25, 2001), for all Model 737 series airplanes. That AD requires revising the airplane flight manual to prohibit extended dry operation of the center tank fuel pumps (with no fuel passing through the pumps). We issued that AD to prevent ignition of fuel vapors due to the generation of sparks and a potential ignition source inside the center tank caused by metal-to-metal contact during dry fuel pump operation, which could result in a fire or explosion of the fuel tank. Accomplishment of the actions required by paragraphs (g), (h), (i), and (l) of this AD, and paragraph (j) or (k) of this AD, as applicable, is acceptable for compliance with the requirements of paragraph (a) of AD 2001–08–24. On December 16, 2009, we issued AD 2008–10–09 R1, Amendment 39–16148 (74 FR 69264, December 31, 2009), for all Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. That AD requires revising the maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. We issued that AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Incorporation of AWLs No. 28–AWL–21 and No. 28–AWL–22 for Model 737–100, –200, and 200C series airplanes; and AWLs No. 28–AWL–20 and No. 28–AWL–21 for Model 737– 300, –400, and –500 series airplanes; in accordance with paragraphs (g)(1) and VerDate Mar<15>2010 17:32 Oct 11, 2011 Jkt 223001 (g)(2) of AD 2008–10–09 R1, terminates the requirements of the corresponding AWLs incorporation required by paragraph (l) of this AD. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and the Service Information.’’ This proposed AD would also require installing a placard adjacent to the pilot’s primary flight display on all airplanes not equipped with an automatic shutoff system for the center tank fuel boost pumps and auxiliary fuel boost pumps, to specify that fuel usage restrictions given in AD 2001–08–24 (66 FR 20733, April 25, 2001) are required. Installing an automatic shutoff system on an airplane would end the need for the placard installation for only that airplane. This proposed AD would also require revisions to the Limitations and Normal Procedures sections of the applicable Boeing 737 Airplane Flight Manual (AFM) to advise the flightcrew of certain operating restrictions related to the automatic shutoff system for the center and auxiliary tank fuel boost pumps. Differences Between the Proposed AD and the Service Information Although Boeing Service Bulletin 737–28A1210, Revision 1, dated May 13, 2011; and Boeing Alert Service Bulletins 737–28A1227, Revision 1, dated July 18, 2011; and 737–28A1228, Original Issue, dated August 2, 2010; specify that certain operators may contact the manufacturer for modification instructions, this proposed AD would require those operators to do the modification using a method approved by the FAA. We received a copy of Boeing Information Notice 737–28A1216 IN 01, dated March 25, 2011; and Boeing Information Notice 737–28A1228 IN 01, dated March 25, 2011, which describe PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 63231 an issue pertaining to installation of the J2802 box on airplanes with airstairs. When the J2802 box is installed in accordance with Boeing Alert Service Bulletin 737–28A1216, Original Issue, dated July 29, 2010; or 737–28A1228, Original Issue, dated August 2, 2010; the forward face of the box will interfere with the airstairs and the airstairs support structure. Boeing is currently designing a new J2802 box for airplanes with airstairs. Installation of the automatic shutoff system required by paragraph (g) of this AD only applies to the affected airplanes without airstairs. In addition, installation of the ‘uncommanded ON’ protection system required by paragraph (m) of this AD only applies to the affected airplanes without airstairs. We may consider further rulemaking for installations of the automatic shutoff system and the ‘un-commanded ON’ protection system on those affected airplanes with airstairs. Installation of a placard required by paragraph (i) of this AD applies to all affected airplanes regardless of airstairs. Once the automatic shutoff system is installed on any airplanes in an operator’s fleet, a placard must be installed on all affected airplanes not equipped with an automatic shutoff system. Although Boeing Alert Service Bulletins 737–28A1216, Original Issue, dated July 29, 2010; and 737–28A1228, Original Issue, dated August 2, 2010; refer to Boeing Alert Service Bulletin 737–28A1210, Original Issue, dated August 2, 2010, as a concurrent requirement, this AD refers to Boeing Service Bulletin 737–28A1210, Revision 1, dated May 13, 2011. Since the P5–2 fuel system module assembly part numbers and the associated airplane group numbers, as shown in the figures of Boeing Alert Service Bulletin 737– 28A1210, Original Issue, dated August 2, 2010, may be incorrect for certain airplanes due to interchangeability of certain part numbers, this AD requires Revision 1 of that service bulletin. Costs of Compliance We estimate that this proposed AD will affect 701 airplanes of U.S. registry. Of those 701 airplanes, 554 airplanes are without airstairs. We estimate the following costs to comply with this proposed AD: E:\FR\FM\12OCP1.SGM 12OCP1 63232 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Proposed Rules ESTIMATED COSTS Action Labor cost Install auto shutoff protection for Model 737–100, –200, –200C airplanes (98 airplanes). Install auto shutoff protection for Model 737–300, –400, and –500 airplanes (456 airplanes). Install P5–2 module .............................. Install ‘un-commanded ON’ protection Between 92 and 152 work-hours × $85 per hour = Between $7,820 and $12,920 1. Between 92 and 152 work-hours × $85 per hour = Between $7,820 and $12,920 1. 1 work-hour × $85 per hour = $85 ...... Between 38 and 63 work-hours × $85 per hour = Between $3,230 and $5,355 1. 1 work-hour × $85 per hour = $85 ...... 1 work-hour × $85 per hour = $85 ...... Revise aircraft flight manual ................. Revise Maintenance Program .............. 1 Depending 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 mstockstill on DSK4VPTVN1PROD with PROPOSALS Cost per product Between $10,127 and $15,123 1. Between $17,947 and $28,043 1. Between $9,869 and $14,265 1. Between $17,689 and $27,185 1. $0 .......................... Between $3,440 and $5,699 1. $85 ........................ Between $6,670 and $11,054 1. $0 .......................... $0 .......................... $85 ........................ $85 ........................ Cost on U.S. operators Between $1,758,806 and $2,748,214 1. Between $8,066,184 and $12,396,360 1. $47,090. Between $3,695,180 and $6,123,916 1. $47,090. $47,090. on group. Authority for This Rulemaking We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the 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 VerDate Mar<15>2010 Parts cost 17:32 Oct 11, 2011 Jkt 223001 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): The Boeing Company: Docket No. FAA– 2011–1068; Directorate Identifier 2010– NM–189–AD. Comments Due Date (a) We must receive comments by November 28, 2011. Affected ADs (b) This AD affects AD 2001–08–24, Amendment 39–12201 (66 FR 20733, April 25, 2001). Also, AD 2008–10–09 R1, Amendment 39–16148 (74 FR 69264, December 31, 2009), affects this AD. Applicability (c) The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes; certificated in any category. 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 PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (t) 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 operation of the center and auxiliary tank fuel boost pumps 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 and auxiliary fuel tanks. These conditions, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Compliance (f) Comply with this AD within the compliance times specified, unless already done. Installation of Automatic Shutoff System for the Center and Auxiliary Tank Fuel Boost Pumps (g) Within 36 months after the effective date of this AD, do the actions required by paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable. If a placard has been previously installed on an airplane, in accordance with the requirements of paragraph (i) of this AD, the placard may be removed from the flight deck of only that airplane after the automatic shutoff system has been installed, as specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable. Installing automatic shutoff systems on all airplanes in an operator’s fleet, in accordance with this paragraph, terminates the placard installation required by paragraph (i) of this AD, for all airplanes in an operator’s fleet. (1) For Model 737–100, –200, and –200C series airplanes without airstairs, in Groups 2 through 16, as identified in Boeing Alert Service Bulletin 737–28A1228, Original E:\FR\FM\12OCP1.SGM 12OCP1 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Proposed Rules Issue, dated August 2, 2010: Install the automatic shutoff system for the center and auxiliary fuel tank boost pumps, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–28A1228, Original Issue, dated August 2, 2010. (2) For Model 737–100, –200, and –200C series airplanes in Group 1, as identified in Boeing Alert Service Bulletin 737–28A1228, Original Issue, dated August 2, 2010: Install the automatic shutoff system for the center and auxiliary fuel tank boost pumps, as applicable, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO). For a modification method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. (3) For Model 737–300, –400, and –500 series airplanes without airstairs, as identified in Boeing Alert Service Bulletin 737–28A1216, Original Issue, dated July 29, 2010: Install the automatic shutoff system for the center and auxiliary fuel tank boost pumps, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–28A1216, Original Issue, dated July 29, 2010. mstockstill on DSK4VPTVN1PROD with PROPOSALS Concurrent Installation of the P5–2 Fuel System Module Assembly (h) Before or concurrently with accomplishing the actions required by paragraph (g) of this AD, do the actions required by paragraph (h)(1) or (h)(2) of this AD, as applicable. (1) For airplanes in Group 2, as identified in Boeing Service Bulletin 737–28A1210, Revision 1, dated May 13, 2011: Replace the P5–2 fuel system module assembly with a modified or new P5–2 fuel system module assembly having a new part number, in accordance with Boeing Service Bulletin 737–28A1210, Revision 1, dated May 13, 2011. Note 2: Boeing Service Bulletin 737– 28A1210, Revision 1, dated May 13, 2011, refers to BAE Systems Service Bulletin 69– 37335–28–04, Revision 2, dated February 10, 2010, as an additional source of guidance for modifying and updating the existing P5–2 fuel system module assembly part numbers to new part numbers. (2) For airplanes in Group 1 as identified in Boeing Service Bulletin 737–28A1210, Revision 1, dated May 13, 2011: Replace the P5–2 fuel system module assembly, in accordance with a method approved by the Manager, Seattle ACO. For a modification method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. Concurrent Installation of a Placard for Mixed Fleet Operation (i) Concurrently with installing the 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 not equipped with an automatic shutoff system for the center and auxiliary tank fuel boost pumps, VerDate Mar<15>2010 17:32 Oct 11, 2011 Jkt 223001 as applicable. The placard reads as follows (alternative placard wording may be used if approved by an appropriate FAA Principal Operations Inspector): ‘‘AD 2001–08–24 fuel usage restrictions required.’’ Installing an automatic shutoff system on an airplane, in accordance with the requirements of paragraph (g) of this AD, terminates the placard installation required by this paragraph for only that airplane. Installing automatic shutoff systems on all affected airplanes in an operator’s fleet, in accordance with the requirements of paragraph (g) of this AD, terminates the placard installation required by this paragraph for all affected airplanes in an operator’s fleet. Airplane Flight Manual (AFM) Revisions for Airplanes Without Boeing Auxiliary Fuel Tanks (j) For airplanes without Boeing auxiliary fuel tanks: Concurrently with accomplishing the actions required by paragraph (g) of this AD, do the actions specified in paragraphs (j)(1) and (j)(2) of this AD. (1) Revise Section 1 of the Limitations section of the applicable Boeing 737 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: When a statement identical to that in paragraph (j)(1) of this AD has been included in the general revisions of the applicable Boeing 737 AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. (2) Revise Section 3 of the Normal Procedures section of the applicable Boeing 737 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. ‘‘NORMAL FUEL USAGE 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 1,000 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, PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 63233 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 2,000 pounds (907 kilograms).’’ AFM Revisions for Airplanes With Boeing Auxiliary Fuel Tanks (k) For airplanes with Boeing auxiliary fuel tanks: Concurrently with accomplishing the actions required by paragraph (g) of this AD, do the actions specified in paragraphs (k)(1) and (k)(2) of this AD. (1) Revise Section 1 of the Limitations section of the applicable Boeing 737 AFM to include the following statements. This may be done by inserting a copy of this AD into the AFM. ‘‘CENTER WING (AND BOEING AUXILIARY) TANK FUEL PUMPS Intentional dry running of a center wing or auxiliary tank fuel pump (low pressure light illuminated) is prohibited.’’ Note 4: When a statement identical to that in paragraph (k)(1) of this AD has been included in the general revisions of the applicable Boeing 737 AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. (2) Revise Section 3 of the Normal Procedures section of the applicable Boeing 737 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 WING (AND BOEING AUXILIARY) TANK FUEL PUMPS Center wing or auxiliary tank fuel pumps must not be ‘‘ON’’ unless personnel are available in the flight deck to monitor low pressure lights. For ground operation, center wing (or auxiliary) tank fuel pump switches must not be positioned ‘‘ON’’ unless the center wing (or auxiliary) tank fuel quantity exceeds 1,000 pounds (453 kilograms), except when defueling or transferring fuel. Upon positioning the center wing (or auxiliary) tank fuel pump switches ‘‘ON,’’ verify momentary illumination of each center wing E:\FR\FM\12OCP1.SGM 12OCP1 63234 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS (or auxiliary) tank fuel pump low pressure light. For ground and flight operations, the corresponding center wing (or auxiliary) tank fuel pump switch must be positioned ‘‘OFF’’ when a center wing (or auxiliary) tank fuel pump low pressure light illuminates [1]. Both center wing (or auxiliary) tank fuel pump switches must be positioned ‘‘OFF’’ when the first center wing (or auxiliary) tank fuel pump low pressure light illuminates if the center wing (or auxiliary) tank is empty. [1] When established in a level flight attitude, both center wing (or auxiliary) tank pump switches should be positioned ‘‘ON’’ again if the center wing (or auxiliary) tank contains usable fuel. DEFUELING AND FUEL TRANSFER When transferring fuel or defueling center wing, auxiliary 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 wing (or auxiliary) tank with passengers on board is prohibited if the center wing (or auxiliary) 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 2,000 pounds (907 kilograms).’’ Airworthiness Limitations (AWLs) Revision for Automatic Shutoff System (l) Concurrently with accomplishing the actions required by paragraph (g) of this AD, or within 30 days after the effective date of this AD, whichever occurs later: Revise the maintenance program by incorporating the AWLs specified in paragraphs (l)(1), (l)(2), (l)(3), and (l)(4) of this AD, as applicable. The initial compliance time for the actions specified in the applicable AWLs is within 1 year after accomplishing the installation required by paragraph (g) of this AD, or within 1 year after the effective date of this AD, whichever occurs later. (1) For Model 737–100, –200, and –200C series airplanes without Boeing auxiliary fuel tanks installed: AWL No. 28–AWL–21 of Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737– 100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278–CMR, Revision July 2011. (2) For Model 737–100, –200, and –200C series airplanes with Boeing auxiliary fuel tanks installed: AWL No. 28–AWL–21 and AWL No. 28–AWL–22 of Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737–100/200/200C/ 300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278– VerDate Mar<15>2010 17:32 Oct 11, 2011 Jkt 223001 CMR, Revision July 2011. (3) For Model 737– 300, –400, and –500 series airplanes without Boeing auxiliary fuel tanks installed: AWL No. 28–AWL–20 of Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737–100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278–CMR, Revision July 2011. (4) For Model 737–300, –400, and –500 series airplanes with Boeing auxiliary fuel tanks installed: AWL No. 28–AWL–20 and AWL No. 28–AWL–21 of Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737–100/200/200C/ 300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278– CMR, Revision July 2011. Installation of ‘Un-Commanded ON’ Protection System (m) Within 60 months after the effective date of this AD, do the actions required by paragraph (m)(1) or (m)(2) of this AD, as applicable. (1) For airplanes without airstairs in Groups 2 through 8, as identified in Boeing Alert Service Bulletin 737–28A1227, Revision 1, dated July 18, 2011: Install the ‘un-commanded ON’ protection system for the center and auxiliary tank fuel boost pumps, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–28A1227, Revision 1, dated July 18, 2011. (2) For airplanes in Group 1, as identified in Boeing Alert Service Bulletin 737– 28A1227, Revision 1, dated July 18, 2011: Install the ‘un-commanded ON’ protection system for the center and auxiliary tank fuel boost pumps, as applicable, in accordance with a method approved by the Manager, Seattle ACO. For an installation method to be approved by the Manager, Seattle ACO, as required by this paragraph, the manager’s approval letter must specifically refer to this AD. AWLs Revision for ‘Un-Commanded ON’ Protection System (n) Concurrently with accomplishing the actions required by paragraph (m) of this AD, or within 30 days after the effective date of this AD, whichever occurs later: Revise the maintenance program by incorporating the AWLs specified in paragraphs (n)(1), (n)(2), (n)(3), and (n)(4) of this AD, as applicable. The initial compliance time for the actions specified in applicable AWLs is within 1 year after accomplishing the installation required by paragraph (m) of this AD, or within 1 year after the effective date of this AD, whichever occurs later. (1) For Model 737–100, –200, and –200C series airplanes without Boeing auxiliary fuel tanks: AWL No. 28–AWL–24 of Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737–100/200/ 200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278– CMR, Revision July 2011. (2) For Model 737–100, –200, and –200C series airplanes with Boeing auxiliary fuel PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 tanks: AWL No. 28–AWL–24 and AWL No. 28–AWL–25 of Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737–100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278–CMR, Revision July 2011. (3) For Model 737–300, –400, and –500 series airplanes without Boeing auxiliary fuel tanks: AWL No. 28–AWL–23 of Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737–100/200/ 200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278– CMR, Revision July 2011. (4) For Model 737–300, –400, and –500 series airplanes with Boeing auxiliary fuel tanks: AWL No. 28–AWL–23 and AWL No. 28–AWL–24 of Section C, ‘‘Fuel Systems Airworthiness Limitations,’’ of Section 9 of the Boeing 737–100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278–CMR, Revision July 2011. No Alternative Inspections or Inspection Intervals (o) After accomplishing the applicable actions specified in paragraphs (l) and (n) of this AD, no alternative inspections or inspection intervals may be used unless the inspections or inspection intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (t) of this AD. Credit for Actions Accomplished in Accordance With Previous Service Information (p) Replacement of the P5–2 fuel system module assembly done before the effective date of this AD in accordance with Boeing Alert Service Bulletin 737–28A1210, Original Issue, dated August 2, 2010, is acceptable for compliance with the requirements of paragraph (h) of this AD. (q) Actions accomplished before the effective date of this AD in accordance with the Boeing 737–100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6–38278–CMR, Revision May 2009; or Revision August 2010; are acceptable for compliance with the corresponding requirements of paragraphs (l) and (n) of this AD. Method of Compliance for Paragraph (l) of This AD (r) Incorporating AWLs No. 28–AWL–21 and No. 28–AWL–22 for Model 737–100, –200, and –200C series airplanes; and AWLs No. 28–AWL–20 and No. 28–AWL–21 for Model 737–300, –400, and –500 series airplanes; in accordance with paragraphs (g)(1) and (g)(2) of AD 2008–10–09 R1 (74 FR 69264, December 31, 2009), is acceptable for compliance with the corresponding AWL incorporation required by paragraph (l) of this AD. E:\FR\FM\12OCP1.SGM 12OCP1 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Proposed Rules Method of Compliance for Paragraph (a) of AD 2001–08–24 DEPARTMENT OF TRANSPORTATION (s) Accomplishing the actions required by paragraphs (g), (h), (i), and (l) of this AD, and paragraph (j) or (k) of this AD, as applicable, is an acceptable method of compliance with the requirements of paragraph (a) of AD 2001–08–24, Amendment 39–12201 (66 FR 20733, April 25, 2001). Federal Aviation Administration Alternative Methods of Compliance (AMOCs) Related Information (u) For more information about this AD, contact Tak Kobayashi, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone: 425–917–6499; fax: 425– 917–6590; e-mail: Takahisa.Kobayashi@faa.gov. (v) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, the FAA, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on October 3, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. mstockstill on DSK4VPTVN1PROD with PROPOSALS BILLING CODE 4910–13–P VerDate Mar<15>2010 17:32 Oct 11, 2011 Jkt 223001 [Docket No. FAA–2011–0893; Airspace Docket No. 11–ANM–18] Proposed Modification of Class E Airspace; The Dalles, OR Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: (t)(1) The Manager, Seattle ACO, 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. [FR Doc. 2011–26242 Filed 10–11–11; 8:45 am] 14 CFR Part 71 This action proposes to modify Class E airspace at The Dalles, OR. Controlled airspace is necessary to accommodate aircraft using Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Columbia Gorge Regional/The Dalles Municipal Airport, The Dalles, OR. The FAA is proposing this action to enhance the safety and management of aircraft operations at the airport. This action also changes the airport name. DATES: Comments must be received on or before November 28, 2011. ADDRESSES: Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590; telephone (202) 366–9826. You must identify FAA Docket No. FAA–2011–0893; Airspace Docket No. 11–ANM–18, at the beginning of your comments. You may also submit comments through the Internet at https://www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Eldon Taylor, Federal Aviation Administration, Operations Support Group, Western Service Center, 1601 Lind Avenue, SW., Renton, WA 98057; telephone (425) 203–4537. SUPPLEMENTARY INFORMATION: SUMMARY: Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers (FAA Docket No. FAA 2011–0893 and Airspace Docket No. 11– PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 63235 ANM–18) and be submitted in triplicate to the Docket Management System (see ADDRESSES section for address and phone number). You may also submit comments through the Internet at https://www.regulations.gov. Commenters wishing the FAA to acknowledge receipt of their comments on this action must submit with those comments a self-addressed stamped postcard on which the following statement is made: ‘‘Comments to FAA Docket No. FAA–2011–0893 and Airspace Docket No. 11–ANM–18’’. The postcard will be date/time stamped and returned to the commenter. All communications received on or before the specified closing date for comments will be considered before taking action on the proposed rule. The proposal contained in this action may be changed in light of comments received. All comments submitted will be available for examination in the public docket both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerned with this rulemaking will be filed in the docket. Availability of NPRMs An electronic copy of this document may be downloaded through the Internet at https://www.regulations.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at https:// www.faa.gov/airports_airtraffic/ air_traffic/publications/ airspace_amendments/. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office (see the ADDRESSES section for the address and phone number) between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. An informal docket may also be examined during normal business hours at the Northwest Mountain Regional Office of the Federal Aviation Administration, Air Traffic Organization, Western Service Center, Operations Support Group, 1601 Lind Avenue, SW., Renton, WA 98057. Persons interested in being placed on a mailing list for future NPRMs should contact the FAA’s Office of Rulemaking, (202) 267–9677, for a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. The Proposal The FAA is proposing an amendment to Title 14 Code of Federal Regulations (14 CFR) Part 71 by modifying Class E airspace at Columbia Gorge Regional/ E:\FR\FM\12OCP1.SGM 12OCP1

Agencies

[Federal Register Volume 76, Number 197 (Wednesday, October 12, 2011)]
[Proposed Rules]
[Pages 63229-63235]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-26242]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1068; Directorate Identifier 2010-NM-189-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Model 737-100, -200,
-200C, -300, -400, and -500 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD would require installing an
automatic shutoff system for the center and auxiliary tank fuel boost
pumps, as applicable, and installing a placard in the airplane flight
deck if necessary; replacing the P5-2 fuel system module assembly; and
installing the un-commanded on (UCO) protection system for the center
and auxiliary tank fuel boost pumps, as applicable. This proposed AD
would also require 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 automatic
shutoff system. This proposed AD would also require revising the
maintenance program by incorporating new airworthiness limitations for
fuel tank systems to satisfy Special Federal Aviation Regulation No. 88
requirements. This proposed AD was prompted by fuel system reviews
conducted by the manufacturer. We are proposing this AD to prevent
operation of the center and auxiliary tank fuel boost pumps 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 and auxiliary fuel tanks. These
conditions, in combination with flammable fuel vapors, could result in
a fuel tank explosion and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by November 28,
2011.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed 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. 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 https://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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.

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; telephone:
425-917-6499; fax: 425-917-6590; e-mail: Takahisa.Kobayashi@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to

[[Page 63230]]

an address listed under the ADDRESSES section. Include ``Docket No.
FAA-2011-1068; Directorate Identifier 2010-NM-189-AD'' at the beginning
of your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of this
proposed AD. We will consider all comments received by the closing date
and may amend this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with a latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
The manufacturer has found that certain failures will result in the
center and auxiliary tank fuel boost pumps continuing to run after the
tank has been depleted. Depending on the failure, pump low pressure may
not be annunciated, or power may not be removed from the pump when the
pump has been commanded ``OFF.'' Operation of the center and auxiliary
tank fuel boost pumps with continuous low pressure could lead to
friction sparks or overheating in the fuel pump inlet. This condition,
if not corrected, could result in a fuel tank explosion and consequent
loss of the airplane.

Relevant Service Information

We have reviewed Boeing Alert Service Bulletin 737-28A1216,
Original Issue, dated July 29, 2010, which describes procedures for
installing the automatic shutoff system for the center and auxiliary
fuel tank boost pumps, as applicable, on Model 737-300, -400, and -500
series airplanes; and refers to Airworthiness Limitation (AWL) No. 28-
AWL-20 and No. 28-AWL-21 that are related to the modifications
specified in that service bulletin.
We have also reviewed Boeing Alert Service Bulletin 737-28A1228,
Original Issue, dated August 2, 2010, which describes procedures for
installing the automatic shutoff system for the center and auxiliary
fuel tank boost pumps, as applicable, on Model 737-100, -200, and -200C
series airplanes; and refers to AWL No. 28-AWL-21 and AWL No. 28-AWL-22
that are related to the modifications specified in that service
bulletin.
Boeing Alert Service Bulletins 737-28A1216, Original Issue, dated
July 29, 2010; and 737-28A1228, Original Issue, dated August 2, 2010;
specify prior or concurrent accomplishment of Boeing Service Bulletin
737-28A1210, Original Issue, dated August 2, 2010, which describes
procedures for replacing the P5-2 fuel system module assembly with a
new or modified P5-2 fuel system module assembly having a new part
number, for Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes.
Boeing Service Bulletin 737-28A1210, Original Issue, dated August
2, 2010, refers to BAE Systems Service Bulletin 69-37335-28-04,
Revision 2, dated February 10, 2010, as an additional source of
guidance for modifying and updating the existing P5-2 fuel system
module assembly part numbers to new part numbers.
We have also reviewed Boeing Alert Service Bulletin 737-28A1227,
Revision 1, dated July 18, 2011. The service information describes
procedures for installing the ``un-commanded ON'' protection system for
the center and auxiliary fuel boost pumps, as applicable, on airplanes.
The installation includes installing new relays and toggle switches in
the J2802 box assembly located in the electronic equipment bay (E/E
bay), and changing and adding new wire bundles that route from the
J2802 box assembly to the P5 forward overhead panel and the P6
disconnect panels. This service bulletin also refers to AWL No. 28-AWL-
24 and No. 28-AWL-25 that are related to the modifications specified in
that service bulletin for Model 737-100, -200, and -200C series
airplanes; and AWL No. 28-AWL-23 and No. 28-AWL-24 that are related to
the modifications specified in that service bulletin for Model 737-300,
-400, and -500 airplanes.
We have also reviewed Section C, ``Fuel Systems Airworthiness
Limitations,'' of Section 9 of the Boeing 737-100/200/200C/300/400/500
Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), Document D6-38278-CMR, Revision July 2011, which
contains the following airworthiness limitations:
For Model 737-300, -400, and -500 series airplanes that
have incorporated Boeing Alert Service Bulletin 737-28A1216, AWLs No.
28-AWL-20 and No. 28-AWL-21 are airworthiness limitation instructions
(ALIs) for an operational check of the installed automatic shutoff
system.
For Model 737-100, -200, and -200C series airplanes that
have incorporated Boeing Alert Service Bulletin 737-28A1228, AWLs No.
28-AWL-21 and No. 28-AWL-22 are ALIs for an operational check of the
installed automatic shutoff system.
For Model 737-300, -400, and -500 series airplanes that
have incorporated Boeing Alert Service Bulletin 737-28A1227, AWLs No.
28-AWL-23 and No. 28-AWL-24 are ALIs for an operational check of the
installed

[[Page 63231]]

power-failed-on (un-commanded ON) protection system.
For Model 737-100, -200, and -200C series airplanes that
have incorporated Boeing Alert Service Bulletin 737-28A1227, AWL No.
28-AWL-24 and No. 28-AWL-25 are ALIs for an operational check of the
installed power-failed-on (un-commanded ON) protection system.

Other Relevant Rulemaking

On April 18, 2001, we issued AD 2001-08-24, Amendment 39-12201 (66
FR 20733, April 25, 2001), for all Model 737 series airplanes. That AD
requires revising the airplane flight manual to prohibit extended dry
operation of the center tank fuel pumps (with no fuel passing through
the pumps). We issued that AD to prevent ignition of fuel vapors due to
the generation of sparks and a potential ignition source inside the
center tank caused by metal-to-metal contact during dry fuel pump
operation, which could result in a fire or explosion of the fuel tank.
Accomplishment of the actions required by paragraphs (g), (h), (i), and
(l) of this AD, and paragraph (j) or (k) of this AD, as applicable, is
acceptable for compliance with the requirements of paragraph (a) of AD
2001-08-24.
On December 16, 2009, we issued AD 2008-10-09 R1, Amendment 39-
16148 (74 FR 69264, December 31, 2009), for all Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes. That AD requires revising
the maintenance program to incorporate new airworthiness limitations
(AWLs) for fuel tank systems to satisfy Special Federal Aviation
Regulation No. 88 requirements. That AD also requires an initial
inspection to phase in certain repetitive AWL inspections, and repair
if necessary. We issued that AD to prevent the potential for ignition
sources inside fuel tanks caused by latent failures, alterations,
repairs, or maintenance actions, which, in combination with flammable
fuel vapors, could result in a fuel tank explosion and consequent loss
of the airplane. Incorporation of AWLs No. 28-AWL-21 and No. 28-AWL-22
for Model 737-100, -200, and 200C series airplanes; and AWLs No. 28-
AWL-20 and No. 28-AWL-21 for Model 737-300, -400, and -500 series
airplanes; in accordance with paragraphs (g)(1) and (g)(2) of AD 2008-
10-09 R1, terminates the requirements of the corresponding AWLs
incorporation required by paragraph (l) of this AD.

FAA's Determination

We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.

Proposed AD Requirements

This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between the Proposed AD and the Service
Information.''
This proposed AD would also require installing a placard adjacent
to the pilot's primary flight display on all airplanes not equipped
with an automatic shutoff system for the center tank fuel boost pumps
and auxiliary fuel boost pumps, to specify that fuel usage restrictions
given in AD 2001-08-24 (66 FR 20733, April 25, 2001) are required.
Installing an automatic shutoff system on an airplane would end the
need for the placard installation for only that airplane.
This proposed AD would also require revisions to the Limitations
and Normal Procedures sections of the applicable Boeing 737 Airplane
Flight Manual (AFM) to advise the flightcrew of certain operating
restrictions related to the automatic shutoff system for the center and
auxiliary tank fuel boost pumps.

Differences Between the Proposed AD and the Service Information

Although Boeing Service Bulletin 737-28A1210, Revision 1, dated May
13, 2011; and Boeing Alert Service Bulletins 737-28A1227, Revision 1,
dated July 18, 2011; and 737-28A1228, Original Issue, dated August 2,
2010; specify that certain operators may contact the manufacturer for
modification instructions, this proposed AD would require those
operators to do the modification using a method approved by the FAA.
We received a copy of Boeing Information Notice 737-28A1216 IN 01,
dated March 25, 2011; and Boeing Information Notice 737-28A1228 IN 01,
dated March 25, 2011, which describe an issue pertaining to
installation of the J2802 box on airplanes with airstairs. When the
J2802 box is installed in accordance with Boeing Alert Service Bulletin
737-28A1216, Original Issue, dated July 29, 2010; or 737-28A1228,
Original Issue, dated August 2, 2010; the forward face of the box will
interfere with the airstairs and the airstairs support structure.
Boeing is currently designing a new J2802 box for airplanes with
airstairs. Installation of the automatic shutoff system required by
paragraph (g) of this AD only applies to the affected airplanes without
airstairs. In addition, installation of the `un-commanded ON'
protection system required by paragraph (m) of this AD only applies to
the affected airplanes without airstairs. We may consider further
rulemaking for installations of the automatic shutoff system and the
`un-commanded ON' protection system on those affected airplanes with
airstairs. Installation of a placard required by paragraph (i) of this
AD applies to all affected airplanes regardless of airstairs. Once the
automatic shutoff system is installed on any airplanes in an operator's
fleet, a placard must be installed on all affected airplanes not
equipped with an automatic shutoff system.
Although Boeing Alert Service Bulletins 737-28A1216, Original
Issue, dated July 29, 2010; and 737-28A1228, Original Issue, dated
August 2, 2010; refer to Boeing Alert Service Bulletin 737-28A1210,
Original Issue, dated August 2, 2010, as a concurrent requirement, this
AD refers to Boeing Service Bulletin 737-28A1210, Revision 1, dated May
13, 2011. Since the P5-2 fuel system module assembly part numbers and
the associated airplane group numbers, as shown in the figures of
Boeing Alert Service Bulletin 737-28A1210, Original Issue, dated August
2, 2010, may be incorrect for certain airplanes due to
interchangeability of certain part numbers, this AD requires Revision 1
of that service bulletin.

Costs of Compliance

We estimate that this proposed AD will affect 701 airplanes of U.S.
registry. Of those 701 airplanes, 554 airplanes are without airstairs.
We estimate the following costs to comply with this proposed AD:

[[Page 63232]]

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Install auto shutoff protection Between 92 and 152 Between $10,127 Between $17,947 Between
for Model 737-100, -200, -200C work-hours x $85 per and $15,123 \1\. and $28,043 \1\. $1,758,806 and
airplanes (98 airplanes). hour = Between $7,820 $2,748,214 \1\.
and $12,920 \1\.
Install auto shutoff protection Between 92 and 152 Between $9,869 Between $17,689 Between
for Model 737-300, -400, and - work-hours x $85 per and $14,265 \1\. and $27,185 \1\. $8,066,184 and
500 airplanes (456 airplanes). hour = Between $7,820 $12,396,360 \1\.
and $12,920 \1\.
Install P5-2 module............ 1 work-hour x $85 per $0............... $85.............. $47,090.
hour = $85.
Install `un-commanded ON' Between 38 and 63 work- Between $3,440 Between $6,670 Between
protection. hours x $85 per hour and $5,699 \1\. and $11,054 \1\. $3,695,180 and
= Between $3,230 and $6,123,916 \1\.
$5,355 \1\.
Revise aircraft flight manual.. 1 work-hour x $85 per $0............... $85.............. $47,090.
hour = $85.
Revise Maintenance Program..... 1 work-hour x $85 per $0............... $85.............. $47,090.
hour = $85.
----------------------------------------------------------------------------------------------------------------
\1\ Depending on group.

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

We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.

Sec. 39.13 [Amended]

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

The Boeing Company: Docket No. FAA-2011-1068; Directorate Identifier
2010-NM-189-AD.

Comments Due Date

(a) We must receive comments by November 28, 2011.

Affected ADs

(b) This AD affects AD 2001-08-24, Amendment 39-12201 (66 FR
20733, April 25, 2001). Also, AD 2008-10-09 R1, Amendment 39-16148
(74 FR 69264, December 31, 2009), affects this AD.

Applicability

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 according
to paragraph (t) 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 operation of the
center and auxiliary tank fuel boost pumps 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 and auxiliary fuel tanks. These conditions, in
combination with flammable fuel vapors, could result in a fuel tank
explosion and consequent loss of the airplane.

Compliance

(f) Comply with this AD within the compliance times specified,
unless already done.

Installation of Automatic Shutoff System for the Center and Auxiliary
Tank Fuel Boost Pumps

(g) Within 36 months after the effective date of this AD, do the
actions required by paragraph (g)(1), (g)(2), or (g)(3) of this AD,
as applicable. If a placard has been previously installed on an
airplane, in accordance with the requirements of paragraph (i) of
this AD, the placard may be removed from the flight deck of only
that airplane after the automatic shutoff system has been installed,
as specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as
applicable. Installing automatic shutoff systems on all airplanes in
an operator's fleet, in accordance with this paragraph, terminates
the placard installation required by paragraph (i) of this AD, for
all airplanes in an operator's fleet.
(1) For Model 737-100, -200, and -200C series airplanes without
airstairs, in Groups 2 through 16, as identified in Boeing Alert
Service Bulletin 737-28A1228, Original

[[Page 63233]]

Issue, dated August 2, 2010: Install the automatic shutoff system
for the center and auxiliary fuel tank boost pumps, as applicable,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-28A1228, Original Issue, dated August 2, 2010.
(2) For Model 737-100, -200, and -200C series airplanes in Group
1, as identified in Boeing Alert Service Bulletin 737-28A1228,
Original Issue, dated August 2, 2010: Install the automatic shutoff
system for the center and auxiliary fuel tank boost pumps, as
applicable, in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO). For a modification
method to be approved by the Manager, Seattle ACO, as required by
this paragraph, the Manager's approval letter must specifically
refer to this AD.
(3) For Model 737-300, -400, and -500 series airplanes without
airstairs, as identified in Boeing Alert Service Bulletin 737-
28A1216, Original Issue, dated July 29, 2010: Install the automatic
shutoff system for the center and auxiliary fuel tank boost pumps,
as applicable, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-28A1216, Original Issue, dated
July 29, 2010.

Concurrent Installation of the P5-2 Fuel System Module Assembly

(h) Before or concurrently with accomplishing the actions
required by paragraph (g) of this AD, do the actions required by
paragraph (h)(1) or (h)(2) of this AD, as applicable.
(1) For airplanes in Group 2, as identified in Boeing Service
Bulletin 737-28A1210, Revision 1, dated May 13, 2011: Replace the
P5-2 fuel system module assembly with a modified or new P5-2 fuel
system module assembly having a new part number, in accordance with
Boeing Service Bulletin 737-28A1210, Revision 1, dated May 13, 2011.

Note 2: Boeing Service Bulletin 737-28A1210, Revision 1, dated
May 13, 2011, refers to BAE Systems Service Bulletin 69-37335-28-04,
Revision 2, dated February 10, 2010, as an additional source of
guidance for modifying and updating the existing P5-2 fuel system
module assembly part numbers to new part numbers.

(2) For airplanes in Group 1 as identified in Boeing Service
Bulletin 737-28A1210, Revision 1, dated May 13, 2011: Replace the
P5-2 fuel system module assembly, in accordance with a method
approved by the Manager, Seattle ACO. For a modification method to
be approved by the Manager, Seattle ACO, as required by this
paragraph, the Manager's approval letter must specifically refer to
this AD.

Concurrent Installation of a Placard for Mixed Fleet Operation

(i) Concurrently with installing the 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 not equipped with
an automatic shutoff system for the center and auxiliary tank fuel
boost pumps, as applicable. The placard reads as follows
(alternative placard wording may be used if approved by an
appropriate FAA Principal Operations Inspector):

``AD 2001-08-24 fuel usage restrictions required.''

Installing an automatic shutoff system on an airplane, in
accordance with the requirements of paragraph (g) of this AD,
terminates the placard installation required by this paragraph for
only that airplane. Installing automatic shutoff systems on all
affected airplanes in an operator's fleet, in accordance with the
requirements of paragraph (g) of this AD, terminates the placard
installation required by this paragraph for all affected airplanes
in an operator's fleet.

Airplane Flight Manual (AFM) Revisions for Airplanes Without Boeing
Auxiliary Fuel Tanks

(j) For airplanes without Boeing auxiliary fuel tanks:
Concurrently with accomplishing the actions required by paragraph
(g) of this AD, do the actions specified in paragraphs (j)(1) and
(j)(2) of this AD.
(1) Revise Section 1 of the Limitations section of the
applicable Boeing 737 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: When a statement identical to that in paragraph (j)(1)
of this AD has been included in the general revisions of the
applicable Boeing 737 AFM, the general revisions may be inserted
into the AFM, and the copy of this AD may be removed from the AFM.

(2) Revise Section 3 of the Normal Procedures section of the
applicable Boeing 737 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.

``NORMAL FUEL USAGE

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 1,000
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
2,000 pounds (907 kilograms).''

AFM Revisions for Airplanes With Boeing Auxiliary Fuel Tanks

(k) For airplanes with Boeing auxiliary fuel tanks: Concurrently
with accomplishing the actions required by paragraph (g) of this AD,
do the actions specified in paragraphs (k)(1) and (k)(2) of this AD.
(1) Revise Section 1 of the Limitations section of the
applicable Boeing 737 AFM to include the following statements. This
may be done by inserting a copy of this AD into the AFM.

``CENTER WING (AND BOEING AUXILIARY) TANK FUEL PUMPS

Intentional dry running of a center wing or auxiliary tank fuel
pump (low pressure light illuminated) is prohibited.''

Note 4: When a statement identical to that in paragraph (k)(1)
of this AD has been included in the general revisions of the
applicable Boeing 737 AFM, the general revisions may be inserted
into the AFM, and the copy of this AD may be removed from the AFM.

``CENTER WING (AND BOEING AUXILIARY) TANK FUEL PUMPS

Center wing or auxiliary tank fuel pumps must not be ``ON''
unless personnel are available in the flight deck to monitor low
pressure lights.
For ground operation, center wing (or auxiliary) tank fuel pump
switches must not be positioned ``ON'' unless the center wing (or
auxiliary) tank fuel quantity exceeds 1,000 pounds (453 kilograms),
except when defueling or transferring fuel. Upon positioning the
center wing (or auxiliary) tank fuel pump switches ``ON,'' verify
momentary illumination of each center wing

[[Page 63234]]

(or auxiliary) tank fuel pump low pressure light.
For ground and flight operations, the corresponding center wing
(or auxiliary) tank fuel pump switch must be positioned ``OFF'' when
a center wing (or auxiliary) tank fuel pump low pressure light
illuminates [1]. Both center wing (or auxiliary) tank fuel pump
switches must be positioned ``OFF'' when the first center wing (or
auxiliary) tank fuel pump low pressure light illuminates if the
center wing (or auxiliary) tank is empty.
[1] When established in a level flight attitude, both center
wing (or auxiliary) tank pump switches should be positioned ``ON''
again if the center wing (or auxiliary) tank contains usable fuel.

DEFUELING AND FUEL TRANSFER

When transferring fuel or defueling center wing, auxiliary 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 wing (or auxiliary) tank with passengers on
board is prohibited if the center wing (or auxiliary) 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
2,000 pounds (907 kilograms).''

Airworthiness Limitations (AWLs) Revision for Automatic Shutoff System

(l) Concurrently with accomplishing the actions required by
paragraph (g) of this AD, or within 30 days after the effective date
of this AD, whichever occurs later: Revise the maintenance program
by incorporating the AWLs specified in paragraphs (l)(1), (l)(2),
(l)(3), and (l)(4) of this AD, as applicable. The initial compliance
time for the actions specified in the applicable AWLs is within 1
year after accomplishing the installation required by paragraph (g)
of this AD, or within 1 year after the effective date of this AD,
whichever occurs later.
(1) For Model 737-100, -200, and -200C series airplanes without
Boeing auxiliary fuel tanks installed: AWL No. 28-AWL-21 of Section
C, ``Fuel Systems Airworthiness Limitations,'' of Section 9 of the
Boeing 737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs)
and Certification Maintenance Requirements (CMRs), Document D6-
38278-CMR, Revision July 2011.
(2) For Model 737-100, -200, and -200C series airplanes with
Boeing auxiliary fuel tanks installed: AWL No. 28-AWL-21 and AWL No.
28-AWL-22 of Section C, ``Fuel Systems Airworthiness Limitations,''
of Section 9 of the Boeing 737-100/200/200C/300/400/500
Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), Document D6-38278-CMR, Revision July 2011. (3)
For Model 737-300, -400, and -500 series airplanes without Boeing
auxiliary fuel tanks installed: AWL No. 28-AWL-20 of Section C,
``Fuel Systems Airworthiness Limitations,'' of Section 9 of the
Boeing 737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs)
and Certification Maintenance Requirements (CMRs), Document D6-
38278-CMR, Revision July 2011.
(4) For Model 737-300, -400, and -500 series airplanes with
Boeing auxiliary fuel tanks installed: AWL No. 28-AWL-20 and AWL No.
28-AWL-21 of Section C, ``Fuel Systems Airworthiness Limitations,''
of Section 9 of the Boeing 737-100/200/200C/300/400/500
Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), Document D6-38278-CMR, Revision July 2011.

Installation of `Un-Commanded ON' Protection System

(m) Within 60 months after the effective date of this AD, do the
actions required by paragraph (m)(1) or (m)(2) of this AD, as
applicable.
(1) For airplanes without airstairs in Groups 2 through 8, as
identified in Boeing Alert Service Bulletin 737-28A1227, Revision 1,
dated July 18, 2011: Install the `un-commanded ON' protection system
for the center and auxiliary tank fuel boost pumps, as applicable,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-28A1227, Revision 1, dated July 18, 2011.
(2) For airplanes in Group 1, as identified in Boeing Alert
Service Bulletin 737-28A1227, Revision 1, dated July 18, 2011:
Install the `un-commanded ON' protection system for the center and
auxiliary tank fuel boost pumps, as applicable, in accordance with a
method approved by the Manager, Seattle ACO. For an installation
method to be approved by the Manager, Seattle ACO, as required by
this paragraph, the manager's approval letter must specifically
refer to this AD.

AWLs Revision for `Un-Commanded ON' Protection System

(n) Concurrently with accomplishing the actions required by
paragraph (m) of this AD, or within 30 days after the effective date
of this AD, whichever occurs later: Revise the maintenance program
by incorporating the AWLs specified in paragraphs (n)(1), (n)(2),
(n)(3), and (n)(4) of this AD, as applicable. The initial compliance
time for the actions specified in applicable AWLs is within 1 year
after accomplishing the installation required by paragraph (m) of
this AD, or within 1 year after the effective date of this AD,
whichever occurs later.
(1) For Model 737-100, -200, and -200C series airplanes without
Boeing auxiliary fuel tanks: AWL No. 28-AWL-24 of Section C, ``Fuel
Systems Airworthiness Limitations,'' of Section 9 of the Boeing 737-
100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), Document D6-38278-
CMR, Revision July 2011.
(2) For Model 737-100, -200, and -200C series airplanes with
Boeing auxiliary fuel tanks: AWL No. 28-AWL-24 and AWL No. 28-AWL-25
of Section C, ``Fuel Systems Airworthiness Limitations,'' of Section
9 of the Boeing 737-100/200/200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification Maintenance Requirements
(CMRs), Document D6-38278-CMR, Revision July 2011.
(3) For Model 737-300, -400, and -500 series airplanes without
Boeing auxiliary fuel tanks: AWL No. 28-AWL-23 of Section C, ``Fuel
Systems Airworthiness Limitations,'' of Section 9 of the Boeing 737-
100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), Document D6-38278-
CMR, Revision July 2011.
(4) For Model 737-300, -400, and -500 series airplanes with
Boeing auxiliary fuel tanks: AWL No. 28-AWL-23 and AWL No. 28-AWL-24
of Section C, ``Fuel Systems Airworthiness Limitations,'' of Section
9 of the Boeing 737-100/200/200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification Maintenance Requirements
(CMRs), Document D6-38278-CMR, Revision July 2011.

No Alternative Inspections or Inspection Intervals

(o) After accomplishing the applicable actions specified in
paragraphs (l) and (n) of this AD, no alternative inspections or
inspection intervals may be used unless the inspections or
inspection intervals are approved as an alternative method of
compliance (AMOC) in accordance with the procedures specified in
paragraph (t) of this AD.

Credit for Actions Accomplished in Accordance With Previous Service
Information

(p) Replacement of the P5-2 fuel system module assembly done
before the effective date of this AD in accordance with Boeing Alert
Service Bulletin 737-28A1210, Original Issue, dated August 2, 2010,
is acceptable for compliance with the requirements of paragraph (h)
of this AD.
(q) Actions accomplished before the effective date of this AD in
accordance with the Boeing 737-100/200/200C/300/400/500
Airworthiness Limitations (AWLs) and Certification Maintenance
Requirements (CMRs), D6-38278-CMR, Revision May 2009; or Revision
August 2010; are acceptable for compliance with the corresponding
requirements of paragraphs (l) and (n) of this AD.

Method of Compliance for Paragraph (l) of This AD

(r) Incorporating AWLs No. 28-AWL-21 and No. 28-AWL-22 for Model
737-100, -200, and -200C series airplanes; and AWLs No. 28-AWL-20
and No. 28-AWL-21 for Model 737-300, -400, and -500 series
airplanes; in accordance with paragraphs (g)(1) and (g)(2) of AD
2008-10-09 R1 (74 FR 69264, December 31, 2009), is acceptable for
compliance with the corresponding AWL incorporation required by
paragraph (l) of this AD.

[[Page 63235]]

Method of Compliance for Paragraph (a) of AD 2001-08-24

(s) Accomplishing the actions required by paragraphs (g), (h),
(i), and (l) of this AD, and paragraph (j) or (k) of this AD, as
applicable, is an acceptable method of compliance with the
requirements of paragraph (a) of AD 2001-08-24, Amendment 39-12201
(66 FR 20733, April 25, 2001).

Alternative Methods of Compliance (AMOCs)

(t)(1) The Manager, Seattle ACO, 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

(u) For more information about this AD, contact Tak Kobayashi,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone: 425-917-6499; fax: 425-917-6590;
e-mail: Takahisa.Kobayashi@faa.gov.
(v) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone:
206-544-5000, extension 1; fax: 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, the FAA, 1601 Lind Avenue, SW.,
Renton, Washington. For information on the availability of this
material at the FAA, call 425-227-1221.

Issued in Renton, Washington, on October 3, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-26242 Filed 10-11-11; 8:45 am]
BILLING CODE 4910-13-P

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