Airworthiness Directives; The Boeing Company Airplanes, 17098-17106 [2016-04966]

Download as PDF 17098 Proposed Rules Federal Register Vol. 81, No. 59 Monday, March 28, 2016 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION We must receive comments on this SNPRM by May 12, 2016. DATES: Federal Aviation Administration [Docket No. FAA–2011–1068; Directorate Identifier 2010–NM–189–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) for all Boeing Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. The NPRM proposed to require installing an automatic shutoff system for the center and auxiliary tank fuel boost pumps, as applicable; installing a placard in the airplane flight deck if necessary; replacing the P5–2 fuel system module assembly; installing the ‘‘uncommanded ON’’ (UCO) protection system for the fuel boost pumps; revising the airplane flight manual to advise the flightcrew of certain operating restrictions for airplanes equipped with an automatic shutoff system; and revising the maintenance program by incorporating new airworthiness limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. The NPRM was prompted by fuel system reviews conducted by the manufacturer. This action revises the NPRM by proposing to require updated or additional actions that are necessary for certain airplane configurations. We are proposing this supplemental NPRM (SNPRM) 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 Lhorne on DSK5TPTVN1PROD with PROPOSALS SUMMARY: 14:51 Mar 25, 2016 You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Boeing service information identified in this SNPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766–5680; Internet https://www.myboeingfleet.com. For BAE Systems service information identified in this SNPRM, contact BAE Systems, Attention: Commercial Product Support, 600 Main Street, Room S18C, Johnson City, NY 13790–1806; phone: 607–770–3084; fax: 607–770– 3015; email: CS-Customer.Service@ baesystems.com; Internet: http:// www.baesystems-ps.com/customer support. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. The referenced Boeing service bulletins are also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2011– 1068. ADDRESSES: 14 CFR Part 39 VerDate Sep<11>2014 tanks. These conditions, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes. Jkt 238001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2011– 1068; 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: Christopher Baker, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6498; fax: 425–917–6590; email: Christopher.R.Baker@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to 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 http:// 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 We issued an NPRM to amend 14 CFR part 39 by adding an AD that would apply to all Boeing Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. The NPRM published in the Federal Register on October 12, 2011 (76 FR 63229) (‘‘the NPRM’’). The NPRM proposed to require installing an automatic shutoff system for the center and auxiliary tank fuel boost pumps, as E:\FR\FM\28MRP1.SGM 28MRP1 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules applicable; installing a placard in the airplane flight deck if necessary; replacing the P5–2 fuel system module assembly; installing the UCO protection system for the center and auxiliary tank fuel boost pumps, as applicable; revising the airplane flight manual to advise the flightcrew of certain operating restrictions for airplanes equipped with an automatic shutoff system; and revising the maintenance program by incorporating new airworthiness limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. Actions Since the NPRM Was Issued Since we issued the NPRM, we learned of certain inadequacies in the referenced service information. Boeing has since developed, and we have approved, revised service information. We have determined it is necessary to mandate the revised service information, which includes additional actions necessary for airplanes in certain configurations. Lhorne on DSK5TPTVN1PROD with PROPOSALS Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737–28A1210, dated August 2, 2010; Revision 1, dated May 13, 2011; and Revision 2, dated October 25, 2012. The service information describes procedures for replacing the P5-2 fuel system module assembly for Model 737–100, –200, –200C, –300, –400, and –500 airplanes. We reviewed Boeing Alert Service Bulletin 737–28A1216, dated July 29, 2010; Revision 1, dated March 26, 2012; Revision 2, dated November 12, 2012; and Revision 3, dated July 16, 2014. The service information describes procedures for installing an automatic shutoff system for the center and auxiliary fuel tank boost pumps for Model 737–300, –400, and –500 airplanes. We reviewed Boeing Alert Service Bulletin 737–28A1227, dated August 2, 2010; Revision 1, dated July 18, 2011; and Revision 2, dated September 23, 2014. The service information describes procedures for installing a UCO protection system for the center and auxiliary fuel boost pumps for Model 737–100, –200, –200C, –300, –400, and –500 airplanes. We reviewed Boeing Alert Service Bulletin 737–28A1228, dated August 2, 2010; and Revision 1, dated June 28, 2012. The service information describes procedures for installing an automatic shutoff system for the center and auxiliary fuel tank boost pumps for VerDate Sep<11>2014 14:51 Mar 25, 2016 Jkt 238001 Model 737–100, –200, and –200C airplanes. We 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 June 2014, contains AWLs 28–AWL–21, 28–AWL–22, 28–AWL–24, and 28– AWL–25 for Model 737–100, –200, and –200C airplanes, and AWLs 28–AWL– 20, 28–AWL–21, 28–AWL–23, and 28– AWL–24 for Model 737–300, –400, and –500 airplanes, which are airworthiness limitation instructions for an operational check of the installed automatic shutoff system. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Comments We gave the public the opportunity to comment on the NPRM. The following presents the comments received on the NPRM and the FAA’s response to each comment. The Air Line Pilots Association, International, submitted its support for the NPRM. Request To Match Compliance Times Japan Transocean Air requested that we revise paragraphs (g) and (h) of the proposed AD to extend the compliance time from 36 months to 60 months to match the compliance time specified in paragraph (m) of the proposed AD (in the NPRM). The commenter noted that the service information specified in paragraph (m) of the proposed AD (in the NPRM) recommends the concurrent accomplishment of the actions specified in paragraph (g)(3) of the proposed AD. The commenter asserted that requiring the same compliance time (60 months) for paragraphs (g), (h), and (m) of the proposed AD (in the NPRM) would prevent complications associated with different configurations. We disagree that it is necessary to revise the compliance time as requested. We infer that the commenter has assumed that all of those actions must be done at the same maintenance visit. As the commenter stated, the ‘‘concurrent’’ actions (in paragraph (g)(3) of this proposed AD) are to be done ‘‘before or at the same time as’’ the actions required by paragraph (m) of this proposed AD. We have determined that the compliance time for the actions specified in paragraphs (g) and (h) of this proposed AD is necessary to ensure an adequate level of safety. We have further determined that doing the PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 17099 actions required by paragraph (m) of this proposed AD later than the actions specified in paragraphs (g)(3) of this proposed AD would not affect safety, and would not affect the airplane configuration in a way that would complicate accomplishment of the proposed AD requirements for the fleet. In light of the identified unsafe condition, the proposed requirements, and the manufacturer’s recommendations, we have determined that no change to this proposed AD is warranted regarding this issue. Request To Require Two Placards Japan Transocean Air requested that we revise paragraph (i) of the proposed AD (in the NPRM) to require the installation of two placards, instead of one, adjacent to the primary flight displays. The commenter stated that both pilots operate the fuel pumps, and placards are therefore necessary for both pilots’ primary flight displays. We partially agree with the request. The intent of this SNPRM is to ensure that the placard is visible to both pilots. Although we have determined that two placards are not necessary to achieve that goal, operators may choose to install an additional placard or use a different location, if approved by an appropriate FAA principal operations inspector. We have revised paragraph (i) of this proposed AD to specify these options. Request To Correct Service Information Specifications Boeing requested certain corrections to the referenced service information. Since that comment was submitted, Boeing has included these corrections in the revised service information that is referenced in this SNPRM. Therefore, no additional change to this SNPRM is necessary. FAA’s Determination We are proposing this SNPRM because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Certain changes described above expand the scope of the NPRM. As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this SNPRM. Proposed Requirements of This SNPRM This SNPRM would require accomplishing the actions specified in the service information described previously, except as discussed under E:\FR\FM\28MRP1.SGM 28MRP1 17100 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Boeing Alert Service Bulletin 737– 28A1216, Revision 3, dated July 16, 2014, specifies a 24-month compliance time to accomplish the actions specified in that service information. However, ‘‘Differences Between this AD and the Service Information.’’ Differences Between This Proposed AD and the Service Information Where service information referenced in this proposed AD specifies that certain operators may contact the manufacturer for modification instructions, this proposed AD would require those operators to do the modification in one of the following ways: paragraph (g) of this proposed AD would require accomplishing the actions specified in that service information within 36 months. We have determined this compliance time will provide an acceptable level of safety. We have coordinated this difference with Boeing. Costs of Compliance We estimate that this proposed AD will affect 499 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost Install auto shutoff protection for Between 92 and 155 work-hours Model 737–100, –200, –200C × $85 per hours = Between airplanes (82 airplanes). $7,820 and $13,175 1. Install auto shutoff protection for Between 92 and 152 work-hours Model 737–300, –400, and × $85 per hours = Between –500 airplanes (417 airplanes). $7,820 and $12,920 1. Install P5–2 module ................... 1 work-hour × $85 per hour = $85. Install UCO protection (499 airBetween 38 and 67 work-hours planes). × $85 per hours = Between $3,230 and $5,6951. Revise aircraft flight manual ...... 1 work-hour × $85 per hour = $85. Revise Maintenance Program ... 1 work-hour × $85 per hour = $85. 1 Depending Lhorne on DSK5TPTVN1PROD with PROPOSALS Cost on U.S. operators Between $10,792 and $15,548 1. Between $18,612 and $28,723 1. Between $1,526,184 and $2,355,286.1 Between $9,869 and $16,236 1. Between $17,689 and $29,156 1. Between $7,376,313 and $12,158,052.1 $0 ................................ $85 .............................. $42,415. Between $3,742 and $4,861 1. Between $6,972 and $10,556 1. Between $3,479,028 and $5,267,444.1 $0 ................................ $85 .............................. $42,415. $0 ................................ $85 .............................. $42,415. 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 VerDate Sep<11>2014 Cost per product 14:51 Mar 25, 2016 Jkt 238001 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: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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. (a) Comments Due Date We must receive comments by May 12, 2016. (b) Affected ADs Certain requirements of this AD terminate certain requirements of AD 2001–08–24, Amendment 39–12201 (66 FR 20733, April 25, 2001). (c) Applicability This AD affects all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. E:\FR\FM\28MRP1.SGM 28MRP1 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Installation of Automatic Shutoff System for the Center and Auxiliary Tank Fuel Boost Pumps Within 36 months after the effective date of this AD, do the applicable actions specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. 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. (1) For Model 737–100, –200, and –200C series airplanes, in Groups 2 through 19, as identified in Boeing Alert Service Bulletin 737–28A1228, Revision 1, dated June 28, 2012: 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, Revision 1, dated June 28, 2012. For airplanes that do not have airstairs, accomplishment of the actions specified in Boeing Alert Service Bulletin 737–28A1228, dated August 2, 2010, is acceptable for compliance with the requirements of this paragraph, provided markers are installed on the J2802 Box for ‘‘POS 1’’ and ‘‘POS 2’’ within 90 days after the effective date of this AD, in accordance (j) Airplane Flight Manual (AFM) Revisions for Airplanes Without Boeing Auxiliary Fuel Tanks Lhorne on DSK5TPTVN1PROD with PROPOSALS For airplanes without Boeing auxiliary fuel tanks: Concurrently with accomplishment of the actions required by paragraph (g) of this VerDate Sep<11>2014 14:51 Mar 25, 2016 Jkt 238001 with Boeing Alert Service Bulletin 737– 28A1228, Revision 1, dated June 28, 2012. (2) For Model 737–100, –200, and –200C series airplanes in Group 1, as identified in Boeing Alert Service Bulletin 737–28A1228, Revision 1, dated June 28, 2012: Install the automatic shutoff system for the center and auxiliary fuel tank boost pumps, as applicable, using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (3) For Model 737–300, –400, and –500 series airplanes in Groups 1 through 31, as identified in Boeing Alert Service Bulletin 737–28A1216, Revision 3, dated July 16, 2014: 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, Revision 3, dated July 16, 2014. For airplanes that do not have airstairs: Accomplishment of the actions specified in Boeing Service Bulletin 737– 28A1216, dated July 29, 2010, is acceptable for compliance with the requirements of this paragraph, provided markers are installed on the J2802 Box for ‘‘POS 1’’ and ‘‘POS 2’’ within 90 days after the effective date of this AD, in accordance with Boeing Alert Service Bulletin 737–28A1216, Revision 1, dated March 26, 2012; or Boeing Alert Service Bulletin 737–28A1216, Revision 2, dated November 12, 2012. 2, dated February 10, 2010, the P/N marking is etched/scribed or labeled as P/N 69– 37335–2129, within 90 days after the effective date of this AD. (1) For airplanes in Group 2, as identified in Boeing Service Bulletin 737–28A1210, Revision 2, dated October 25, 2012: 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 2, dated October 25, 2012. Note 1 to paragraph (h)(1) of this AD: Boeing Service Bulletin 737–28A1210, Revision 2, dated October 25, 2012, refers to BAE Systems Service Bulletin 69–37335–28– 04 as an additional source of guidance for modifying and updating the existing P5–2 fuel system module assembly part numbers. (2) For airplanes in Group 1, as identified in Boeing Service Bulletin 737–28A1210, Revision 2, dated October 25, 2012, replace the P5–2 fuel system module assembly, as applicable, using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (i) Concurrent Installation of a Placard for Mixed Fleet Operation (h) Concurrent Installation of P5–2 Fuel System Module Assembly Before or concurrently with accomplishment of the actions required by paragraph (g) of this AD, do the actions specified in paragraph (h)(1) or (h)(2) of this AD, as applicable. Accomplishment of the actions specified in Boeing Alert Service Bulletin 737–28A1210, dated August 2, 2010, or Boeing Service Bulletin 737–28A1210, Revision 1, dated May 13, 2011, is acceptable for compliance with the requirements of paragraph (h)(1) of this AD, provided that for any original P5–2 Fuel System Module P/N 69–37335–129 installed that has been reworked as specified in BAE Systems Service Bulletin 69–37335–28–04, Revision Concurrently with accomplishment of the actions 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 must include the statement in figure 1 to paragraph (i) of this AD. Optionally, the placard may include alternative text or be installed in a different location, or an additional placard may be installed, if approved by an appropriate FAA principal operations inspector. 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. 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 statement in figure 2 to paragraph (j)(1) of this AD. This may be done by inserting a copy of this AD into the AFM. When a statement identical to that in figure 2 to 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\28MRP1.SGM 28MRP1 EP28MR16.016</GPH> (e) Unsafe Condition 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. 17101 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules Lhorne on DSK5TPTVN1PROD with PROPOSALS (2) Revise Section 3 of the Normal Procedures section of the applicable Boeing 737 AFM to include to include the text specified in figure 3 to paragraph (j)(2) of this VerDate Sep<11>2014 14:51 Mar 25, 2016 Jkt 238001 AD. 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 appropriate FAA principal operations inspector. BILLING CODE 4910–13–P E:\FR\FM\28MRP1.SGM 28MRP1 EP28MR16.017</GPH> 17102 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 17103 Figure 3 to paragraph G)(2) of this AD 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. (k) AFM Revisions for Airplanes With Boeing Auxiliary Fuel Tanks For airplanes with Boeing auxiliary fuel tanks: Concurrently with accomplishment of the actions required by paragraph (g) of this VerDate Sep<11>2014 14:51 Mar 25, 2016 Jkt 238001 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 text specified in figure 4 to paragraph (k)(1) of this AD. This may be done by inserting a copy of this AD into the AFM. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 When a statement identical to that in figure 4 to 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. E:\FR\FM\28MRP1.SGM 28MRP1 EP28MR16.018</GPH> Lhorne on DSK5TPTVN1PROD with PROPOSALS [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). Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules Lhorne on DSK5TPTVN1PROD with PROPOSALS (2) Revise Section 3 of the Normal Procedures section of the applicable Boeing 737 AFM to include the text specified in VerDate Sep<11>2014 14:51 Mar 25, 2016 Jkt 238001 figure 5 to paragraph (k)(2) of this AD. This may be done by inserting a copy of this AD into the AFM. Alternative statements that PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 meet the intent of the following requirements may be used if approved by an appropriate FAA principal operations inspector. E:\FR\FM\28MRP1.SGM 28MRP1 EP28MR16.019</GPH> 17104 BILLING CODE 4910–13–C Lhorne on DSK5TPTVN1PROD with PROPOSALS (l) Airworthiness Limitations (AWLs) Revision for Automatic Shutoff System Concurrently with accomplishment of 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 accomplishment of the installation VerDate Sep<11>2014 14:51 Mar 25, 2016 Jkt 238001 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: Incorporate 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 June 2014. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 17105 (2) For Model 737–100, –200, and –200C series airplanes with Boeing auxiliary fuel tanks installed: Incorporate 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 June 2014. (3) For Model 737–300, –400, and –500 series airplanes without Boeing auxiliary fuel tanks installed: Incorporate AWL No. 28– E:\FR\FM\28MRP1.SGM 28MRP1 EP28MR16.020</GPH> Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 17106 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 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 June 2014. (4) For Model 737–300, –400, and –500 series airplanes with Boeing auxiliary fuel tanks installed: Incorporate 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 June 2014. Lhorne on DSK5TPTVN1PROD with PROPOSALS (m) Installation of Un-Commanded ON (UCO) Protection System 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 in Groups 2 through 13, as identified in Boeing Alert Service Bulletin 737–28A1227, Revision 2, dated September 23, 2014: Install the UCO 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 2, dated September 23, 2014. For airplanes with enlarged J2802 box assembly relay cutouts to fit the body of relays R3334, R3336, R3338, or R3340, with BACS12HN08–10 screws for the installation of the relays as specified in Information Notice 737–28A1227 IN 05: Accomplishment of the actions specified in Boeing Alert Service Bulletin 737–28A1227, dated August 2, 2010, or Revision 1, dated July 18, 2011, is acceptable for compliance with the requirements of this paragraph, provided markers are installed that identify the function of the switches installed on the J2802 box within 90 days after the effective date of this AD, in accordance with figure 1 or figure 5, as applicable, of Boeing Alert Service Bulletin 737–28A1227, Revision 2, dated September 23, 2014. (2) For airplanes in Group 1, as identified in Boeing Alert Service Bulletin 737– 28A1227, Revision 2, dated September 23, 2014: Install the UCO protection system for the center and auxiliary tank fuel boost pumps, as applicable, using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (n) AWLs Revision for UCO Protection System Concurrently with accomplishment of 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 accomplishment of 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 VerDate Sep<11>2014 14:51 Mar 25, 2016 Jkt 238001 tanks: Incorporate 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 June 2014. (2) For Model 737–100, –200, and –200C series airplanes with Boeing auxiliary fuel tanks: Incorporate 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 June 2014. (3) For Model 737–300, –400, and –500 series airplanes without Boeing auxiliary fuel tanks: Incorporate 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 June 2014. (4) For Model 737–300, –400, and –500 series airplanes with Boeing auxiliary fuel tanks: Incorporate 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 June 2014. (o) No Alternative Inspections or Inspection Intervals After accomplishment of 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 (r) of this AD. (p) Method of Compliance for Paragraph (l) of This AD 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, Amendment 39–16148 (74 FR 69264, December 31, 2009), is acceptable for compliance with the corresponding AWL incorporation required by paragraph (l) of this AD. (q) Method of Compliance for Paragraph (a) of AD 2001–08–24, Amendment 39–12201 (66 FR 20733, April 25, 2001) 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 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). PO 00000 Frm 00009 Fmt 4702 Sfmt 9990 (r) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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 paragraph (s)(1) of this AD. Information may be emailed to 9-ANM-Seattle-ACO-AMOCRequests@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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (s) Related Information (1) For more information about this AD, contact Christopher Baker, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6498; fax: 425–917–6590; email: Christopher.R.Baker@faa.gov. (2) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766– 5680; Internet https:// www.myboeingfleet.com. For BAE Systems service information identified in this AD, contact BAE Systems, Attention: Commercial Product Support, 600 Main Street, Room S18C, Johnson City, NY 13790–1806; phone: 607–770–3084; fax: 607–770–3015; email: CS-Customer.Service@baesystems.com; Internet: http://www.baesystems-ps.com/ customersupport. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on February 25, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–04966 Filed 3–25–16; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\28MRP1.SGM 28MRP1

Agencies

[Federal Register Volume 81, Number 59 (Monday, March 28, 2016)]
[Proposed Rules]
[Pages 17098-17106]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04966]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / 
Proposed Rules

[[Page 17098]]



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 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. The NPRM proposed to require installing an automatic 
shutoff system for the center and auxiliary tank fuel boost pumps, as 
applicable; installing a placard in the airplane flight deck if 
necessary; replacing the P5-2 fuel system module assembly; installing 
the ``uncommanded ON'' (UCO) protection system for the fuel boost 
pumps; revising the airplane flight manual to advise the flightcrew of 
certain operating restrictions for airplanes equipped with an automatic 
shutoff system; and revising the maintenance program by incorporating 
new airworthiness limitations for fuel tank systems to satisfy Special 
Federal Aviation Regulation No. 88 requirements. The NPRM was prompted 
by fuel system reviews conducted by the manufacturer. This action 
revises the NPRM by proposing to require updated or additional actions 
that are necessary for certain airplane configurations. We are 
proposing this supplemental NPRM (SNPRM) 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. Since these actions impose an 
additional burden over that proposed in the NPRM, we are reopening the 
comment period to allow the public the chance to comment on these 
proposed changes.

DATES: We must receive comments on this SNPRM by May 12, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For Boeing service information identified in this SNPRM, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com.
    For BAE Systems service information identified in this SNPRM, 
contact BAE Systems, Attention: Commercial Product Support, 600 Main 
Street, Room S18C, Johnson City, NY 13790-1806; phone: 607-770-3084; 
fax: 607-770-3015; email: CS-Customer.Service@baesystems.com; Internet: 
http://www.baesystems-ps.com/customersupport.
    You may view this referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221. The referenced Boeing service bulletins are also available on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2011-1068.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2011-
1068; 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: Christopher Baker, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6498; fax: 425-917-6590; email: Christopher.R.Baker@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to 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 http://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

    We issued an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to all Boeing Model 737-100, -200, -200C, -300, -400, and -
500 series airplanes. The NPRM published in the Federal Register on 
October 12, 2011 (76 FR 63229) (``the NPRM''). The NPRM proposed to 
require installing an automatic shutoff system for the center and 
auxiliary tank fuel boost pumps, as

[[Page 17099]]

applicable; installing a placard in the airplane flight deck if 
necessary; replacing the P5-2 fuel system module assembly; installing 
the UCO protection system for the center and auxiliary tank fuel boost 
pumps, as applicable; revising the airplane flight manual to advise the 
flightcrew of certain operating restrictions for airplanes equipped 
with an automatic shutoff system; and revising the maintenance program 
by incorporating new airworthiness limitations for fuel tank systems to 
satisfy Special Federal Aviation Regulation No. 88 requirements.

Actions Since the NPRM Was Issued

    Since we issued the NPRM, we learned of certain inadequacies in the 
referenced service information. Boeing has since developed, and we have 
approved, revised service information. We have determined it is 
necessary to mandate the revised service information, which includes 
additional actions necessary for airplanes in certain configurations.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-28A1210, dated August 
2, 2010; Revision 1, dated May 13, 2011; and Revision 2, dated October 
25, 2012. The service information describes procedures for replacing 
the P5-2 fuel system module assembly for Model 737-100, -200, -200C, -
300, -400, and -500 airplanes.
    We reviewed Boeing Alert Service Bulletin 737-28A1216, dated July 
29, 2010; Revision 1, dated March 26, 2012; Revision 2, dated November 
12, 2012; and Revision 3, dated July 16, 2014. The service information 
describes procedures for installing an automatic shutoff system for the 
center and auxiliary fuel tank boost pumps for Model 737-300, -400, and 
-500 airplanes.
    We reviewed Boeing Alert Service Bulletin 737-28A1227, dated August 
2, 2010; Revision 1, dated July 18, 2011; and Revision 2, dated 
September 23, 2014. The service information describes procedures for 
installing a UCO protection system for the center and auxiliary fuel 
boost pumps for Model 737-100, -200, -200C, -300, -400, and -500 
airplanes.
    We reviewed Boeing Alert Service Bulletin 737-28A1228, dated August 
2, 2010; and Revision 1, dated June 28, 2012. The service information 
describes procedures for installing an automatic shutoff system for the 
center and auxiliary fuel tank boost pumps for Model 737-100, -200, and 
-200C airplanes.
    We 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 June 2014, 
contains AWLs 28-AWL-21, 28-AWL-22, 28-AWL-24, and 28-AWL-25 for Model 
737-100, -200, and -200C airplanes, and AWLs 28-AWL-20, 28-AWL-21, 28-
AWL-23, and 28-AWL-24 for Model 737-300, -400, and -500 airplanes, 
which are airworthiness limitation instructions for an operational 
check of the installed automatic shutoff system.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Comments

    We gave the public the opportunity to comment on the NPRM. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment. The Air Line Pilots Association, 
International, submitted its support for the NPRM.

Request To Match Compliance Times

    Japan Transocean Air requested that we revise paragraphs (g) and 
(h) of the proposed AD to extend the compliance time from 36 months to 
60 months to match the compliance time specified in paragraph (m) of 
the proposed AD (in the NPRM). The commenter noted that the service 
information specified in paragraph (m) of the proposed AD (in the NPRM) 
recommends the concurrent accomplishment of the actions specified in 
paragraph (g)(3) of the proposed AD. The commenter asserted that 
requiring the same compliance time (60 months) for paragraphs (g), (h), 
and (m) of the proposed AD (in the NPRM) would prevent complications 
associated with different configurations.
    We disagree that it is necessary to revise the compliance time as 
requested. We infer that the commenter has assumed that all of those 
actions must be done at the same maintenance visit. As the commenter 
stated, the ``concurrent'' actions (in paragraph (g)(3) of this 
proposed AD) are to be done ``before or at the same time as'' the 
actions required by paragraph (m) of this proposed AD. We have 
determined that the compliance time for the actions specified in 
paragraphs (g) and (h) of this proposed AD is necessary to ensure an 
adequate level of safety. We have further determined that doing the 
actions required by paragraph (m) of this proposed AD later than the 
actions specified in paragraphs (g)(3) of this proposed AD would not 
affect safety, and would not affect the airplane configuration in a way 
that would complicate accomplishment of the proposed AD requirements 
for the fleet. In light of the identified unsafe condition, the 
proposed requirements, and the manufacturer's recommendations, we have 
determined that no change to this proposed AD is warranted regarding 
this issue.

Request To Require Two Placards

    Japan Transocean Air requested that we revise paragraph (i) of the 
proposed AD (in the NPRM) to require the installation of two placards, 
instead of one, adjacent to the primary flight displays. The commenter 
stated that both pilots operate the fuel pumps, and placards are 
therefore necessary for both pilots' primary flight displays.
    We partially agree with the request. The intent of this SNPRM is to 
ensure that the placard is visible to both pilots. Although we have 
determined that two placards are not necessary to achieve that goal, 
operators may choose to install an additional placard or use a 
different location, if approved by an appropriate FAA principal 
operations inspector. We have revised paragraph (i) of this proposed AD 
to specify these options.

Request To Correct Service Information Specifications

    Boeing requested certain corrections to the referenced service 
information. Since that comment was submitted, Boeing has included 
these corrections in the revised service information that is referenced 
in this SNPRM. Therefore, no additional change to this SNPRM is 
necessary.

FAA's Determination

    We are proposing this SNPRM because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
Certain changes described above expand the scope of the NPRM. As a 
result, we have determined that it is necessary to reopen the comment 
period to provide additional opportunity for the public to comment on 
this SNPRM.

Proposed Requirements of This SNPRM

    This SNPRM would require accomplishing the actions specified in the 
service information described previously, except as discussed under

[[Page 17100]]

``Differences Between this AD and the Service Information.''

Differences Between This Proposed AD and the Service Information

    Where service information referenced in this proposed AD specifies 
that certain operators may contact the manufacturer for modification 
instructions, this proposed AD would require those operators to do the 
modification in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.
    Boeing Alert Service Bulletin 737-28A1216, Revision 3, dated July 
16, 2014, specifies a 24-month compliance time to accomplish the 
actions specified in that service information. However, paragraph (g) 
of this proposed AD would require accomplishing the actions specified 
in that service information within 36 months. We have determined this 
compliance time will provide an acceptable level of safety. We have 
coordinated this difference with Boeing.

Costs of Compliance

    We estimate that this proposed AD will affect 499 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
             Action                    Labor cost                 Parts cost                    Cost per product             Cost on  U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Install auto shutoff protection   Between 92 and 155   Between $10,792 and $15,548 \1\  Between $18,612 and $28,723 \1\  Between $1,526,184 and
 for Model 737-100, -200, -200C    work-hours x $85                                                                       $2,355,286.\1\
 airplanes (82 airplanes).         per hours =
                                   Between $7,820 and
                                   $13,175 \1\.
Install auto shutoff protection   Between 92 and 152   Between $9,869 and $16,236 \1\.  Between $17,689 and $29,156 \1\  Between $7,376,313 and
 for Model 737-300, -400, and -    work-hours x $85                                                                       $12,158,052.\1\
 500 airplanes (417 airplanes).    per hours =
                                   Between $7,820 and
                                   $12,920 \1\.
Install P5-2 module.............  1 work-hour x $85    $0.............................  $85............................  $42,415.
                                   per hour = $85.
Install UCO protection (499       Between 38 and 67    Between $3,742 and $4,861 \1\..  Between $6,972 and $10,556 \1\.  Between $3,479,028 and
 airplanes).                       work-hours x $85                                                                       $5,267,444.\1\
                                   per hours =
                                   Between $3,230 and
                                   $5,695\1\.
Revise aircraft flight manual...  1 work-hour x $85    $0.............................  $85............................  $42,415.
                                   per hour = $85.
Revise Maintenance Program......  1 work-hour x $85    $0.............................  $85............................  $42,415.
                                   per 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

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

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


Sec.  39.13  [Amended]

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

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

(a) Comments Due Date

    We must receive comments by May 12, 2016.

(b) Affected ADs

    Certain requirements of this AD terminate certain requirements 
of AD 2001-08-24, Amendment 39-12201 (66 FR 20733, April 25, 2001).

(c) Applicability

    This AD affects all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes; certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

[[Page 17101]]

(e) Unsafe Condition

    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.

(f) Compliance

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

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

    Within 36 months after the effective date of this AD, do the 
applicable actions specified in paragraph (g)(1), (g)(2), or (g)(3) 
of this AD. 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.
    (1) For Model 737-100, -200, and -200C series airplanes, in 
Groups 2 through 19, as identified in Boeing Alert Service Bulletin 
737-28A1228, Revision 1, dated June 28, 2012: 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, Revision 1, dated June 
28, 2012. For airplanes that do not have airstairs, accomplishment 
of the actions specified in Boeing Alert Service Bulletin 737-
28A1228, dated August 2, 2010, is acceptable for compliance with the 
requirements of this paragraph, provided markers are installed on 
the J2802 Box for ``POS 1'' and ``POS 2'' within 90 days after the 
effective date of this AD, in accordance with Boeing Alert Service 
Bulletin 737-28A1228, Revision 1, dated June 28, 2012.
    (2) For Model 737-100, -200, and -200C series airplanes in Group 
1, as identified in Boeing Alert Service Bulletin 737-28A1228, 
Revision 1, dated June 28, 2012: Install the automatic shutoff 
system for the center and auxiliary fuel tank boost pumps, as 
applicable, using a method approved in accordance with the 
procedures specified in paragraph (r) of this AD.
    (3) For Model 737-300, -400, and -500 series airplanes in Groups 
1 through 31, as identified in Boeing Alert Service Bulletin 737-
28A1216, Revision 3, dated July 16, 2014: 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, Revision 3, dated July 
16, 2014. For airplanes that do not have airstairs: Accomplishment 
of the actions specified in Boeing Service Bulletin 737-28A1216, 
dated July 29, 2010, is acceptable for compliance with the 
requirements of this paragraph, provided markers are installed on 
the J2802 Box for ``POS 1'' and ``POS 2'' within 90 days after the 
effective date of this AD, in accordance with Boeing Alert Service 
Bulletin 737-28A1216, Revision 1, dated March 26, 2012; or Boeing 
Alert Service Bulletin 737-28A1216, Revision 2, dated November 12, 
2012.

(h) Concurrent Installation of P5-2 Fuel System Module Assembly

    Before or concurrently with accomplishment of the actions 
required by paragraph (g) of this AD, do the actions specified in 
paragraph (h)(1) or (h)(2) of this AD, as applicable. Accomplishment 
of the actions specified in Boeing Alert Service Bulletin 737-
28A1210, dated August 2, 2010, or Boeing Service Bulletin 737-
28A1210, Revision 1, dated May 13, 2011, is acceptable for 
compliance with the requirements of paragraph (h)(1) of this AD, 
provided that for any original P5-2 Fuel System Module P/N 69-37335-
129 installed that has been reworked as specified in BAE Systems 
Service Bulletin 69-37335-28-04, Revision 2, dated February 10, 
2010, the P/N marking is etched/scribed or labeled as P/N 69-37335-
2129, within 90 days after the effective date of this AD.
    (1) For airplanes in Group 2, as identified in Boeing Service 
Bulletin 737-28A1210, Revision 2, dated October 25, 2012: 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 2, dated October 
25, 2012.


    Note 1 to paragraph (h)(1) of this AD: Boeing Service Bulletin 
737-28A1210, Revision 2, dated October 25, 2012, refers to BAE 
Systems Service Bulletin 69-37335-28-04 as an additional source of 
guidance for modifying and updating the existing P5-2 fuel system 
module assembly part numbers.

    (2) For airplanes in Group 1, as identified in Boeing Service 
Bulletin 737-28A1210, Revision 2, dated October 25, 2012, replace 
the P5-2 fuel system module assembly, as applicable, using a method 
approved in accordance with the procedures specified in paragraph 
(r) of this AD.

(i) Concurrent Installation of a Placard for Mixed Fleet Operation

    Concurrently with accomplishment of the actions 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 must 
include the statement in figure 1 to paragraph (i) of this AD. 
Optionally, the placard may include alternative text or be installed 
in a different location, or an additional placard may be installed, 
if approved by an appropriate FAA principal operations inspector. 
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.
[GRAPHIC] [TIFF OMITTED] TP28MR16.016

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

    For airplanes without Boeing auxiliary fuel tanks: Concurrently 
with accomplishment of 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 statement in figure 2 to 
paragraph (j)(1) of this AD. This may be done by inserting a copy of 
this AD into the AFM. When a statement identical to that in figure 2 
to 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.

[[Page 17102]]

[GRAPHIC] [TIFF OMITTED] TP28MR16.017

    (2) Revise Section 3 of the Normal Procedures section of the 
applicable Boeing 737 AFM to include to include the text specified 
in figure 3 to paragraph (j)(2) of this AD. 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.
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[[Page 17103]]

[GRAPHIC] [TIFF OMITTED] TP28MR16.018

(k) AFM Revisions for Airplanes With Boeing Auxiliary Fuel Tanks

    For airplanes with Boeing auxiliary fuel tanks: Concurrently 
with accomplishment of 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 text specified in figure 4 
to paragraph (k)(1) of this AD. This may be done by inserting a copy 
of this AD into the AFM. When a statement identical to that in 
figure 4 to 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.

[[Page 17104]]

[GRAPHIC] [TIFF OMITTED] TP28MR16.019

    (2) Revise Section 3 of the Normal Procedures section of the 
applicable Boeing 737 AFM to include the text specified in figure 5 
to paragraph (k)(2) of this AD. 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.

[[Page 17105]]

[GRAPHIC] [TIFF OMITTED] TP28MR16.020

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(l) Airworthiness Limitations (AWLs) Revision for Automatic Shutoff 
System

    Concurrently with accomplishment of 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 accomplishment of 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: Incorporate 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 June 2014.
    (2) For Model 737-100, -200, and -200C series airplanes with 
Boeing auxiliary fuel tanks installed: Incorporate 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 June 2014.
    (3) For Model 737-300, -400, and -500 series airplanes without 
Boeing auxiliary fuel tanks installed: Incorporate AWL No. 28-

[[Page 17106]]

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 June 2014.
    (4) For Model 737-300, -400, and -500 series airplanes with 
Boeing auxiliary fuel tanks installed: Incorporate 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 June 2014.

(m) Installation of Un-Commanded ON (UCO) Protection System

    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 in Groups 2 through 13, as identified in 
Boeing Alert Service Bulletin 737-28A1227, Revision 2, dated 
September 23, 2014: Install the UCO 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 2, dated September 23, 2014. For 
airplanes with enlarged J2802 box assembly relay cutouts to fit the 
body of relays R3334, R3336, R3338, or R3340, with BACS12HN08-10 
screws for the installation of the relays as specified in 
Information Notice 737-28A1227 IN 05: Accomplishment of the actions 
specified in Boeing Alert Service Bulletin 737-28A1227, dated August 
2, 2010, or Revision 1, dated July 18, 2011, is acceptable for 
compliance with the requirements of this paragraph, provided markers 
are installed that identify the function of the switches installed 
on the J2802 box within 90 days after the effective date of this AD, 
in accordance with figure 1 or figure 5, as applicable, of Boeing 
Alert Service Bulletin 737-28A1227, Revision 2, dated September 23, 
2014.
    (2) For airplanes in Group 1, as identified in Boeing Alert 
Service Bulletin 737-28A1227, Revision 2, dated September 23, 2014: 
Install the UCO protection system for the center and auxiliary tank 
fuel boost pumps, as applicable, using a method approved in 
accordance with the procedures specified in paragraph (r) of this 
AD.

(n) AWLs Revision for UCO Protection System

    Concurrently with accomplishment of 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 accomplishment of 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: Incorporate 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 June 2014.
    (2) For Model 737-100, -200, and -200C series airplanes with 
Boeing auxiliary fuel tanks: Incorporate 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 June 2014.
    (3) For Model 737-300, -400, and -500 series airplanes without 
Boeing auxiliary fuel tanks: Incorporate 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 June 2014.
    (4) For Model 737-300, -400, and -500 series airplanes with 
Boeing auxiliary fuel tanks: Incorporate 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 June 2014.

(o) No Alternative Inspections or Inspection Intervals

    After accomplishment of 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 (r) of this AD.

(p) Method of Compliance for Paragraph (l) of This AD

    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, Amendment 39-16148 (74 FR 69264, December 31, 2009), 
is acceptable for compliance with the corresponding AWL 
incorporation required by paragraph (l) of this AD.

(q) Method of Compliance for Paragraph (a) of AD 2001-08-24, Amendment 
39-12201 (66 FR 20733, April 25, 2001)

    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 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).

(r) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. 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 paragraph (s)(1) of this AD. 
Information may be emailed 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.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, to make those findings. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(s) Related Information

    (1) For more information about this AD, contact Christopher 
Baker, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6498; fax: 425-917-6590; email: Christopher.R.Baker@faa.gov.
    (2) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone: 206-544-5000, extension 1; fax: 206-766-5680; Internet 
https://www.myboeingfleet.com. For BAE Systems service information 
identified in this AD, contact BAE Systems, Attention: Commercial 
Product Support, 600 Main Street, Room S18C, Johnson City, NY 13790-
1806; phone: 607-770-3084; fax: 607-770-3015; email: CS-Customer.Service@baesystems.com; Internet: http://www.baesystems-ps.com/customersupport. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on February 25, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04966 Filed 3-25-16; 8:45 am]
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