Airworthiness Directives; The Boeing Company Airplanes, 20505-20508 [2012-6642]

Download as PDF Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations and leaf grade of American upland cotton, and fiber property measurements such as micronaire. High Volume Instruments will determine all fiber property measurements except extraneous matter. High Volume Instrument colormeter measurements will be used for determining the official color grade. Cotton classers authorized by the Cotton and Tobacco Programs will determine the presence of extraneous matter and authorized employees of the Cotton and Tobacco Programs will determine all fiber property measurements using High Volume Instruments. Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0908; Directorate Identifier 2009–NM–067–AD; Amendment 39–16987; AD 2012–06–06] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD requires replacing the power control relays for the fuel boost pumps and override pumps with new relays having a ground fault interrupter (GFI) feature. This AD also requires an electrical bonding resistance measurement for certain GFI relays to verify that certain bonding requirements are met. This AD also requires, for certain airplanes, an inspection to ensure that certain screws are properly installed, and installing longer screws if necessary. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: This AD is effective May 10, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 10, 2012. ADDRESSES: 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; email 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. SUMMARY: PART 28—[AMENDED] 3. The authority citation for 7 CFR part 28 continues to read as follows: ■ Authority: 7 U.S.C. 55 and 61. 4. Section 28.8 is revised to read as follows: ■ § 28.8 Classification of cotton; determination. For the purposes of The Act, the classification of any cotton shall be determined by the quality of a sample in accordance with Universal Cotton Standards (the official cotton standards of the United States) for the color grade and the leaf grade of American upland cotton, the length of staple, and fiber property measurements such as micronaire. High Volume Instruments will determine all fiber property measurements except extraneous matter, special conditions and remarks. High Volume Instrument colormeter measurements will be used for determining the official color grade. Cotton classers authorized by the Cotton and Tobacco Programs will determine the presence of extraneous matter, special conditions and remarks and authorized employees of the Cotton and Tobacco Programs will determine all fiber property measurements using High Volume Instruments. The classification record of a Classing Office or the Quality Control Division with respect to any cotton shall be deemed to be the classification record of the Department. rmajette on DSK2TPTVN1PROD with RULES DEPARTMENT OF TRANSPORTATION Dated: March 30, 2012. Robert C. Keeney, Acting Administrator, Agricultural Marketing Service. [FR Doc. 2012–8125 Filed 4–4–12; 8:45 am] BILLING CODE 3410–02–P Examining the AD Docket You may examine the AD docket on the Internet at https:// VerDate Mar<15>2010 15:36 Apr 04, 2012 Jkt 226001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 20505 www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6482; fax: (425) 917– 6590; email: Georgios.Roussos@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That SNPRM was published in the Federal Register on January 3, 2011 (76 FR 28). The original NPRM (74 FR 53436, October 19, 2009) proposed to require replacing the power control relays for the fuel boost pumps and override pumps with new relays having a GFI feature. The SNPRM proposed to add an electrical bonding resistance measurement for certain GFI relays to verify that certain bonding requirements are met. The SNPRM also proposed to add, for certain airplanes, an inspection to ensure that certain screws are properly installed, and installing longer screws if necessary. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM (76 FR 28, January 3, 2011) and the FAA’s response to each comment. Boeing concurs with the contents of the SNPRM. Request To Permit Incorporation of Universal Fault Interrupter (UFI) as a Means of Compliance American Airlines (AA) and TDG Aerospace requested that we revise the SNPRM (76 FR 28, January 3, 2011) to allow incorporation of the previouslyapproved Supplemental Type Certificate (STC) ST01950LA, issued January 17, 2007, as an approved means of compliance for providing fault protection for the center override fuel pumps. The commenters stated that the E:\FR\FM\05APR1.SGM 05APR1 20506 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations rmajette on DSK2TPTVN1PROD with RULES UFI, in accordance with STC ST01950LA, performs as a GFI for the center override pumps, providing equivalent or better protection for detection and prevention of ground fault anomalies. The commenters added that the FAA has acknowledged that the UFI provides transient fault detection and steady state fault detection; and in response to any of the above electrical faults, the UFI will de-energize the airplane electromechanical relay to shut off the fuel pump. TDG stated that Boeing Model 757 airplanes utilize the same fuel pump part number for the center tank fuel boost pump application as the Boeing Model 737NG airplane. TDG Aerospace STC ST01950LA for Model 757 airplanes utilizes the same UFI part number as STC ST02076LA for Model 737NG airplanes that have the UFI as an acceptable means of compliance through the Manager, Seattle Aircraft Certification Office (ACO) approval process under Docket No. FAA–2010–1199 (AD 2011–20–07, Amendment 39–16818 (76 FR 60710, September 30, 2011)). TDG Aerospace pointed out that a large number of Model 757 operators have already incorporated STC ST01950LA as a means of compliance with FAA AD 2008–11–07, Amendment 39–15529 (73 FR 30755, May 29, 2008). We partially agree. We have been informed that referring to an STC now violates Office of the Federal Register (OFR) regulations (1 CFR part 51) for approval of optional materials ‘‘incorporated by reference’’ in rules. However, we have added paragraph (g)(2)(ii) to this AD to specify that installation of TDG Aerospace UFIs to the center tank override pumps must be done in accordance with a method approved by the Manager, Seattle ACO, FAA. We have also added ‘‘Note 1 to paragraph (g)(2)(ii) of this AD’’ to specify that additional guidance on installing TDG Aerospace UFIs can be found in TDG Aerospace STC ST01950LA. Request To Forego Screw Length Inspections and Electrical Bonding Checks for Center Override Pumps AA requested that we exempt airplanes that have the UFI installed for the center override pumps from performing screw length inspections and electrical bonding checks that are specific to the GFI installation. The commenter stated that the UFI installation under STC ST01950LA already complies with proper grip length. The commenter also stated that the UFI STC requires the bonding check of the installed UFI bracket to each panel. VerDate Mar<15>2010 15:36 Apr 04, 2012 Jkt 226001 We disagree with the commenter’s request because the inspection requirements of paragraph (h) of the final rule clearly identify that the screw grip length inspections and GFI bonding checks are applicable only to airplanes that have Boeing Alert Service Bulletin 757–28A0078 or 757–28A0079, both dated July 16, 2008, accomplished before the effective date of the AD. Airplanes that have incorporated the UFI under STC ST01950LA on their center tank override pumps do not need to perform these additional inspections required by paragraph (h) of this AD. No changes have been made to this AD in this regard. Request To Correct Typographical Errors in Service Bulletins AA and United Airlines requested correction of a number of typographical errors in Boeing Service Bulletins 757– 28A0078 and 757–28A0079, both Revision 1, both dated August 24, 2010. AA stated that typographical errors in Boeing Service Bulletin 757–28A0078, Revision 1, dated August 24, 2010, mistakenly refer to the P37 panel as ‘‘P33.’’ In addition, AA and United Airlines stated that those service bulletins mistakenly refer to the standard wiring practices manual rather than the standard overhaul practices manual (SOPM) for the P33 and P37 panel identification. United Airlines requested that paragraph (i) of the SNPRM (76 FR 28, January 3, 2011) be corrected to identify paragraph 3.B.12.l.(5) of Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 757–28A0078, Revision 1, dated August 24, 2010, and not the currently referenced paragraph 3.B.12.i.(5). Boeing Service Bulletin Information Notice 757–28A0078 IN 02, dated October 6, 2010, identifies paragraph 3.B.12.l.(5) as the impacted paragraph of the service bulletins. We agree that the typographical errors needed to be corrected. Boeing has released Service Bulletins 757–28A0078 and 757–28A0079, both Revision 2, both dated January 11, 2012, which correct typographical errors in the calculations in paragraphs 3.B.12.m.(5) and 3.B.12.m.(6) of Boeing Service Bulletins 757–28A0078 and 757–28A0079, both Revision 1, both dated August 24, 2010. These service bulletin revisions also clarify certain actions and correct other typographical errors. Paragraphs (c), (g), and (h) of this AD have been updated to refer to Boeing Service Bulletins 757– 28A0078 and 757–28A0079, both Revision 2, both dated January 11, 2012. Paragraph (i) of the SNPRM (76 FR 28, January 3, 2011) has been removed from this final rule. We have also added a PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 new paragraph (i) to this AD to allow credit for accomplishing Boeing Service Bulletin 757–28A0078 or 757–28A0079, both Revision 1, both dated August 24, 2010, before the effective date of this AD. Request To Allow Identification of P33 and P37 Panels ‘‘Outside the Scope of the AD’’ AA recommended that we allow the identification of the P33 and P37 panels as a statement ‘‘outside the scope of the AD.’’ AA stated that the GFI physical differences would be enough to distinguish between the old and new relay types. The commenter also stated that post-modification parts are illustrated in the revisions to operators’ manuals, in the illustrated parts catalog, and airplane maintenance manual. The commenter pointed out that the lack of panel labeling would not affect the level of safety. We disagree with the commenter’s recommendation to change the final rule to address this issue. The requirement for panel identification specified in Step 3 in Figure 1 and Figure 2 of Boeing Service Bulletins 757–28A0078 and 757–28A0079, both Revision 1, both dated August 24, 2010, refers to identifying the P33 and P37 panels to show that this change was accomplished. Note (a) that accompanies the Step 3 instructions in those service bulletins calls for marking the panels with a unique marking under SOPM 20–50–10, which points to the incorporation of the changes under the accomplishment instructions of those service bulletins. It does not call for a change to the P33 and P37 panel part number. No change has been made to the AD in this regard. Explanation of Changes to Final Rule We have restructured paragraph (g) of this AD to clarify the locations for replacing the power control relays. Paragraph (g)(1) of this AD specifies the ‘‘main tank fuel boost pumps,’’ and paragraph (g)(2) of this AD specifies the ‘‘center tank override fuel boost pumps.’’ In addition, we have removed the Paperwork Reduction Act Burden Statement paragraph since no reporting is required in this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously— and minor editorial changes. We have determined that these minor changes: E:\FR\FM\05APR1.SGM 05APR1 20507 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations • Are consistent with the intent that was proposed in the SNPRM (76 FR 28, January 3, 2011) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already Costs of Compliance proposed in the SNPRM (76 FR 28, January 3, 2011). We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. We estimate that this AD affects 696 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Replacement, measurement, and operational test ......... 7 work-hours × $85 per hour = $595. 1 work-hour × $85 per hour = $85. Inspection of screw installation and bonding resistance measurement. 1 The Cost per product Parts cost $12,600 $13,195 $0 $85 Cost on U.S. operators Up to $9,183,720.1 $59,160. cost for U.S. operators depends on airplane configuration. We estimate the following costs to do any necessary installation that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need this installation: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Installation of longer screw ....................................... 1 work-hour × $85 per hour = $85 ........................... $0 $85 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. rmajette on DSK2TPTVN1PROD with RULES Regulatory Findings 15:36 Apr 04, 2012 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, VerDate Mar<15>2010 (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Jkt 226001 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): ■ 2012–06–06 The Boeing Company: Amendment 39–16987; Docket No. FAA–2009–0908; Directorate Identifier 2009–NM–067–AD. (a) Effective Date This AD is effective May 10, 2012. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757–200, –200PF, –200CB, and –300 series airplanes, certificated in any category; as identified in the applicable service bulletin specified in paragraph (c)(1) or (c)(2) of this AD. (1) For Model 757–200, –200PF, and –200CB series airplanes: Boeing Service Bulletin 757–28A0078, Revision 2, dated January 11, 2012. (2) For Model 757–300 series airplanes: Boeing Service Bulletin 757–28A0079, Revision 2, dated January 11, 2012. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 28, Fuel. (e) Unsafe Condition This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, which, 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) Replacement, Measurements, and Test For airplanes on which the actions specified in Boeing Alert Service Bulletin 757–28A0078, dated July 16, 2008, or 757– 28A0079, dated July 16, 2008, have not been accomplished before the effective date of this E:\FR\FM\05APR1.SGM 05APR1 20508 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations rmajette on DSK2TPTVN1PROD with RULES AD: Within 60 months after the effective date of this AD, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Replace the power control relays for the main tank fuel boost pumps with new relays having a ground fault interrupter (GFI) feature; do applicable electrical bonding resistance measurements between the GFI relays and their installation panel to verify that applicable bonding requirements are met; and do an operational test to ensure correct operation; as specified in Boeing Service Bulletin 757–28A0078, Revision 2, dated January 11, 2012 (for Model 757–200, –200CB, and –200PF series airplanes); or Boeing Service Bulletin 757–28A0079, Revision 2, dated January 11, 2012 (for Model 757–300 series airplanes). Do all actions in accordance with Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 757–28A0078, Revision 2, dated January 11, 2012 (for Model 757–200, –200CB, and –200PF series airplanes); or Boeing Service Bulletin 757–28A0079, Revision 2, dated January 11, 2012 (for Model 757–300 series airplanes). (2) Replace the power control relays for the center tank override fuel boost pumps with new relays having a GFI feature, in accordance with the actions required in paragraph (g)(2)(i) or (g)(2)(ii) of this AD. (i) Replace the power control relays with new relays having a GFI feature; do applicable electrical bonding resistance measurements between the GFI relays and their installation panel to verify that applicable bonding requirements are met; and do an operational test to ensure correct operation; as specified in Boeing Service Bulletin 757–28A0078, Revision 2, dated January 11, 2012 (for Model 757–200, –200CB, and –200PF series airplanes); or Boeing Service Bulletin 757–28A0079, Revision 2, dated January 11, 2012 (for Model 757–300 series airplanes). Do all actions in accordance with Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 757–28A0078, Revision 2, dated January 11, 2012 (for Model 757–200, –200CB, and –200PF series airplanes), or Boeing Service Bulletin 757–28A0079, Revision 2, dated January 11, 2012 (for Model 757–300 series airplanes). (ii) Install and maintain TDG Aerospace universal fault interrupters (UFIs), in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Note 1 to paragraph (g)(2)(ii) of this AD: Guidance on installing TDG Aerospace UFIs can be found in Supplemental Type Certificate ST01950LA (https://rgl.faa.gov/ Regulatory_and_Guidance_Library/rgSTC. nsf/0/196ec7e864607b5b862573c5007cb3b5/ $FILE/ST01950LA.pdf). (h) Inspection For airplanes on which the actions specified in Boeing Alert Service Bulletin 757–28A0078, dated July 16, 2008, or 757– 28A0079, dated July 16, 2008, have been accomplished before the effective date of this AD: Within 60 months after the effective date of this AD, do a general visual inspection to verify that each GFI installation screw has enough grip length to hold the screws in each VerDate Mar<15>2010 15:36 Apr 04, 2012 Jkt 226001 nut plate, and do applicable electrical bonding resistance measurements between the GFI relays and their installation panel to verify that applicable bonding requirements are met. If the screw does not have enough grip length, before further flight, install a longer screw. Do all actions in accordance with Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 757– 28A0078, Revision 2, dated January 11, 2012 (for Model 757–200, –200CB, and –200PF series airplanes); or Boeing Service Bulletin 757–28A0079, Revision 2, dated January 11, 2012 (for Model 757–300 series airplanes). (i) Credit for Previous Actions This paragraph provides credit for the actions required by this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 757– 28A0078 or 757–28A0079, both Revision 1, both dated August 24, 2010. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed 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. (k) Related Information For more information about this AD, contact Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, Seattle ACO, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: (425) 917–6482; fax: (425) 917– 6590; email: Georgios.Roussos@faa.gov. Or, email information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. (l) Material Incorporated by Reference (1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following service information: (i) Boeing Service Bulletin 757–28A0078, Revision 2, dated January 11, 2012. (ii) Boeing Service Bulletin 757–28A0079, Revision 2, dated January 11, 2012. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Washington. For information on the availability of this material at the FAA, call 425–227–1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 9, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–6642 Filed 4–4–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0821; Directorate Identifier 2010–NE–30–AD; Amendment 39– 17004; AD 2012–06–23] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211–Trent 875–17, RB211–Trent 877–17, RB211– Trent 884–17, RB211–Trent 884B–17, RB211–Trent 892–17, RB211–Trent 892B–17, and RB211–Trent 895–17 turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections (UIs) of certain low-pressure (LP) compressor blades identified by serial number (S/N). This AD requires the same actions but expands the population of blades. This AD was prompted by RR concluding that additional blades affected must be inspected. We are issuing this AD to prevent LP compressor blades from failing due to blade root cracks, which could lead to uncontained engine failure and damage to the airplane. DATES: This AD is effective April 20, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 20, 2012. We must receive any comments on this AD by May 21, 2012. ADDRESSES: You may send comments by any of the following methods: SUMMARY: E:\FR\FM\05APR1.SGM 05APR1

Agencies

[Federal Register Volume 77, Number 66 (Thursday, April 5, 2012)]
[Rules and Regulations]
[Pages 20505-20508]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-6642]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0908; Directorate Identifier 2009-NM-067-AD; 
Amendment 39-16987; AD 2012-06-06]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 757 airplanes. This AD requires replacing the 
power control relays for the fuel boost pumps and override pumps with 
new relays having a ground fault interrupter (GFI) feature. This AD 
also requires an electrical bonding resistance measurement for certain 
GFI relays to verify that certain bonding requirements are met. This AD 
also requires, for certain airplanes, an inspection to ensure that 
certain screws are properly installed, and installing longer screws if 
necessary. This AD was prompted by fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent damage to the fuel 
pumps caused by electrical arcing that could introduce an ignition 
source in the fuel tank, which, in combination with flammable fuel 
vapors, could result in a fuel tank explosion and consequent loss of 
the airplane.

DATES: This AD is effective May 10, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of May 10, 2012.

ADDRESSES: 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; email 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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, Seattle Aircraft Certification 
Office, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; 
phone: 425-917-6482; fax: (425) 917-6590; email: 
Georgios.Roussos@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to include an airworthiness directive (AD) that 
would apply to the specified products. That SNPRM was published in the 
Federal Register on January 3, 2011 (76 FR 28). The original NPRM (74 
FR 53436, October 19, 2009) proposed to require replacing the power 
control relays for the fuel boost pumps and override pumps with new 
relays having a GFI feature. The SNPRM proposed to add an electrical 
bonding resistance measurement for certain GFI relays to verify that 
certain bonding requirements are met. The SNPRM also proposed to add, 
for certain airplanes, an inspection to ensure that certain screws are 
properly installed, and installing longer screws if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the SNPRM (76 
FR 28, January 3, 2011) and the FAA's response to each comment. Boeing 
concurs with the contents of the SNPRM.

Request To Permit Incorporation of Universal Fault Interrupter (UFI) as 
a Means of Compliance

    American Airlines (AA) and TDG Aerospace requested that we revise 
the SNPRM (76 FR 28, January 3, 2011) to allow incorporation of the 
previously-approved Supplemental Type Certificate (STC) ST01950LA, 
issued January 17, 2007, as an approved means of compliance for 
providing fault protection for the center override fuel pumps. The 
commenters stated that the

[[Page 20506]]

UFI, in accordance with STC ST01950LA, performs as a GFI for the center 
override pumps, providing equivalent or better protection for detection 
and prevention of ground fault anomalies. The commenters added that the 
FAA has acknowledged that the UFI provides transient fault detection 
and steady state fault detection; and in response to any of the above 
electrical faults, the UFI will de-energize the airplane 
electromechanical relay to shut off the fuel pump. TDG stated that 
Boeing Model 757 airplanes utilize the same fuel pump part number for 
the center tank fuel boost pump application as the Boeing Model 737NG 
airplane. TDG Aerospace STC ST01950LA for Model 757 airplanes utilizes 
the same UFI part number as STC ST02076LA for Model 737NG airplanes 
that have the UFI as an acceptable means of compliance through the 
Manager, Seattle Aircraft Certification Office (ACO) approval process 
under Docket No. FAA-2010-1199 (AD 2011-20-07, Amendment 39-16818 (76 
FR 60710, September 30, 2011)). TDG Aerospace pointed out that a large 
number of Model 757 operators have already incorporated STC ST01950LA 
as a means of compliance with FAA AD 2008-11-07, Amendment 39-15529 (73 
FR 30755, May 29, 2008).
    We partially agree. We have been informed that referring to an STC 
now violates Office of the Federal Register (OFR) regulations (1 CFR 
part 51) for approval of optional materials ``incorporated by 
reference'' in rules. However, we have added paragraph (g)(2)(ii) to 
this AD to specify that installation of TDG Aerospace UFIs to the 
center tank override pumps must be done in accordance with a method 
approved by the Manager, Seattle ACO, FAA. We have also added ``Note 1 
to paragraph (g)(2)(ii) of this AD'' to specify that additional 
guidance on installing TDG Aerospace UFIs can be found in TDG Aerospace 
STC ST01950LA.

Request To Forego Screw Length Inspections and Electrical Bonding 
Checks for Center Override Pumps

    AA requested that we exempt airplanes that have the UFI installed 
for the center override pumps from performing screw length inspections 
and electrical bonding checks that are specific to the GFI 
installation. The commenter stated that the UFI installation under STC 
ST01950LA already complies with proper grip length. The commenter also 
stated that the UFI STC requires the bonding check of the installed UFI 
bracket to each panel.
    We disagree with the commenter's request because the inspection 
requirements of paragraph (h) of the final rule clearly identify that 
the screw grip length inspections and GFI bonding checks are applicable 
only to airplanes that have Boeing Alert Service Bulletin 757-28A0078 
or 757-28A0079, both dated July 16, 2008, accomplished before the 
effective date of the AD. Airplanes that have incorporated the UFI 
under STC ST01950LA on their center tank override pumps do not need to 
perform these additional inspections required by paragraph (h) of this 
AD. No changes have been made to this AD in this regard.

Request To Correct Typographical Errors in Service Bulletins

    AA and United Airlines requested correction of a number of 
typographical errors in Boeing Service Bulletins 757-28A0078 and 757-
28A0079, both Revision 1, both dated August 24, 2010.
    AA stated that typographical errors in Boeing Service Bulletin 757-
28A0078, Revision 1, dated August 24, 2010, mistakenly refer to the P37 
panel as ``P33.'' In addition, AA and United Airlines stated that those 
service bulletins mistakenly refer to the standard wiring practices 
manual rather than the standard overhaul practices manual (SOPM) for 
the P33 and P37 panel identification.
    United Airlines requested that paragraph (i) of the SNPRM (76 FR 
28, January 3, 2011) be corrected to identify paragraph 3.B.12.l.(5) of 
Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 
757-28A0078, Revision 1, dated August 24, 2010, and not the currently 
referenced paragraph 3.B.12.i.(5). Boeing Service Bulletin Information 
Notice 757-28A0078 IN 02, dated October 6, 2010, identifies paragraph 
3.B.12.l.(5) as the impacted paragraph of the service bulletins.
    We agree that the typographical errors needed to be corrected. 
Boeing has released Service Bulletins 757-28A0078 and 757-28A0079, both 
Revision 2, both dated January 11, 2012, which correct typographical 
errors in the calculations in paragraphs 3.B.12.m.(5) and 3.B.12.m.(6) 
of Boeing Service Bulletins 757-28A0078 and 757-28A0079, both Revision 
1, both dated August 24, 2010. These service bulletin revisions also 
clarify certain actions and correct other typographical errors. 
Paragraphs (c), (g), and (h) of this AD have been updated to refer to 
Boeing Service Bulletins 757-28A0078 and 757-28A0079, both Revision 2, 
both dated January 11, 2012. Paragraph (i) of the SNPRM (76 FR 28, 
January 3, 2011) has been removed from this final rule. We have also 
added a new paragraph (i) to this AD to allow credit for accomplishing 
Boeing Service Bulletin 757-28A0078 or 757-28A0079, both Revision 1, 
both dated August 24, 2010, before the effective date of this AD.

Request To Allow Identification of P33 and P37 Panels ``Outside the 
Scope of the AD''

    AA recommended that we allow the identification of the P33 and P37 
panels as a statement ``outside the scope of the AD.'' AA stated that 
the GFI physical differences would be enough to distinguish between the 
old and new relay types. The commenter also stated that post-
modification parts are illustrated in the revisions to operators' 
manuals, in the illustrated parts catalog, and airplane maintenance 
manual. The commenter pointed out that the lack of panel labeling would 
not affect the level of safety.
    We disagree with the commenter's recommendation to change the final 
rule to address this issue. The requirement for panel identification 
specified in Step 3 in Figure 1 and Figure 2 of Boeing Service 
Bulletins 757-28A0078 and 757-28A0079, both Revision 1, both dated 
August 24, 2010, refers to identifying the P33 and P37 panels to show 
that this change was accomplished. Note (a) that accompanies the Step 3 
instructions in those service bulletins calls for marking the panels 
with a unique marking under SOPM 20-50-10, which points to the 
incorporation of the changes under the accomplishment instructions of 
those service bulletins. It does not call for a change to the P33 and 
P37 panel part number. No change has been made to the AD in this 
regard.

Explanation of Changes to Final Rule

    We have restructured paragraph (g) of this AD to clarify the 
locations for replacing the power control relays. Paragraph (g)(1) of 
this AD specifies the ``main tank fuel boost pumps,'' and paragraph 
(g)(2) of this AD specifies the ``center tank override fuel boost 
pumps.''
    In addition, we have removed the Paperwork Reduction Act Burden 
Statement paragraph since no reporting is required in this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously--and minor editorial 
changes. We have determined that these minor changes:

[[Page 20507]]

     Are consistent with the intent that was proposed in the 
SNPRM (76 FR 28, January 3, 2011) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (76 FR 28, January 3, 2011).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 696 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                       Cost per
             Action                  Labor cost       Parts cost        product        Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Replacement, measurement, and    7 work-hours x            $12,600         $13,195  Up to $9,183,720.\1\
 operational test.                $85 per hour =
                                  $595.
Inspection of screw              1 work-hour x $85              $0             $85  $59,160.
 installation and bonding         per hour = $85.
 resistance measurement.
----------------------------------------------------------------------------------------------------------------
\1\ The cost for U.S. operators depends on airplane configuration.

    We estimate the following costs to do any necessary installation 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
this installation:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                   Action                              Labor cost               Parts cost      Cost per product
----------------------------------------------------------------------------------------------------------------
Installation of longer screw...............  1 work-hour x $85 per hour =                 $0                $85
                                              $85.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2012-06-06 The Boeing Company: Amendment 39-16987; Docket No. FAA-
2009-0908; Directorate Identifier 2009-NM-067-AD.

(a) Effective Date

    This AD is effective May 10, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 757-200, -200PF, -
200CB, and -300 series airplanes, certificated in any category; as 
identified in the applicable service bulletin specified in paragraph 
(c)(1) or (c)(2) of this AD.
    (1) For Model 757-200, -200PF, and -200CB series airplanes: 
Boeing Service Bulletin 757-28A0078, Revision 2, dated January 11, 
2012.
    (2) For Model 757-300 series airplanes: Boeing Service Bulletin 
757-28A0079, Revision 2, dated January 11, 2012.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent damage to the fuel 
pumps caused by electrical arcing that could introduce an ignition 
source in the fuel tank, which, 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) Replacement, Measurements, and Test

    For airplanes on which the actions specified in Boeing Alert 
Service Bulletin 757-28A0078, dated July 16, 2008, or 757-28A0079, 
dated July 16, 2008, have not been accomplished before the effective 
date of this

[[Page 20508]]

AD: Within 60 months after the effective date of this AD, do the 
actions specified in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Replace the power control relays for the main tank fuel 
boost pumps with new relays having a ground fault interrupter (GFI) 
feature; do applicable electrical bonding resistance measurements 
between the GFI relays and their installation panel to verify that 
applicable bonding requirements are met; and do an operational test 
to ensure correct operation; as specified in Boeing Service Bulletin 
757-28A0078, Revision 2, dated January 11, 2012 (for Model 757-200, 
-200CB, and -200PF series airplanes); or Boeing Service Bulletin 
757-28A0079, Revision 2, dated January 11, 2012 (for Model 757-300 
series airplanes). Do all actions in accordance with Part 1 of the 
Accomplishment Instructions of Boeing Service Bulletin 757-28A0078, 
Revision 2, dated January 11, 2012 (for Model 757-200, -200CB, and -
200PF series airplanes); or Boeing Service Bulletin 757-28A0079, 
Revision 2, dated January 11, 2012 (for Model 757-300 series 
airplanes).
    (2) Replace the power control relays for the center tank 
override fuel boost pumps with new relays having a GFI feature, in 
accordance with the actions required in paragraph (g)(2)(i) or 
(g)(2)(ii) of this AD.
    (i) Replace the power control relays with new relays having a 
GFI feature; do applicable electrical bonding resistance 
measurements between the GFI relays and their installation panel to 
verify that applicable bonding requirements are met; and do an 
operational test to ensure correct operation; as specified in Boeing 
Service Bulletin 757-28A0078, Revision 2, dated January 11, 2012 
(for Model 757-200, -200CB, and -200PF series airplanes); or Boeing 
Service Bulletin 757-28A0079, Revision 2, dated January 11, 2012 
(for Model 757-300 series airplanes). Do all actions in accordance 
with Part 1 of the Accomplishment Instructions of Boeing Service 
Bulletin 757-28A0078, Revision 2, dated January 11, 2012 (for Model 
757-200, -200CB, and -200PF series airplanes), or Boeing Service 
Bulletin 757-28A0079, Revision 2, dated January 11, 2012 (for Model 
757-300 series airplanes).
    (ii) Install and maintain TDG Aerospace universal fault 
interrupters (UFIs), in accordance with a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA.

    Note 1 to paragraph (g)(2)(ii) of this AD: Guidance on 
installing TDG Aerospace UFIs can be found in Supplemental Type 
Certificate ST01950LA (https://rgl.faa.gov/Regulatory--and--
Guidance--Library/rgSTC.nsf/0/196ec7e864607b5b862573c5007cb3b5/
$FILE/ST01950LA.pdf).

(h) Inspection

    For airplanes on which the actions specified in Boeing Alert 
Service Bulletin 757-28A0078, dated July 16, 2008, or 757-28A0079, 
dated July 16, 2008, have been accomplished before the effective 
date of this AD: Within 60 months after the effective date of this 
AD, do a general visual inspection to verify that each GFI 
installation screw has enough grip length to hold the screws in each 
nut plate, and do applicable electrical bonding resistance 
measurements between the GFI relays and their installation panel to 
verify that applicable bonding requirements are met. If the screw 
does not have enough grip length, before further flight, install a 
longer screw. Do all actions in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Service Bulletin 757-28A0078, 
Revision 2, dated January 11, 2012 (for Model 757-200, -200CB, and -
200PF series airplanes); or Boeing Service Bulletin 757-28A0079, 
Revision 2, dated January 11, 2012 (for Model 757-300 series 
airplanes).

(i) Credit for Previous Actions

    This paragraph provides credit for the actions required by this 
AD, if those actions were performed before the effective date of 
this AD using Boeing Service Bulletin 757-28A0078 or 757-28A0079, 
both Revision 1, both dated August 24, 2010.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
ACO, send it to the attention of the person identified in the 
Related Information section of this AD. Information may be 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.

(k) Related Information

    For more information about this AD, contact Georgios Roussos, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, Seattle 
ACO, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; 
phone: (425) 917-6482; fax: (425) 917-6590; email: 
Georgios.Roussos@faa.gov. Or, email information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.

(l) Material Incorporated by Reference

    (1) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the 
following service information:
    (i) Boeing Service Bulletin 757-28A0078, Revision 2, dated 
January 11, 2012.
    (ii) Boeing Service Bulletin 757-28A0079, Revision 2, dated 
January 11, 2012.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; email 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on March 9, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-6642 Filed 4-4-12; 8:45 am]
BILLING CODE 4910-13-P

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