Airworthiness Directives; The Boeing Company Airplanes, 72621-72624 [2015-29617]

Download as PDF Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–5809; Directorate Identifier 2015–NM–055–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2006–19– 12, which applies to certain The Boeing Model 777–200 and –300 series airplanes. AD 2006–19–12 currently requires inspecting the lower web of the aft fairing of the engine struts for any discoloration and doing any related investigative and corrective action if necessary; inspecting the heat shield castings for any damage and doing any corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. Since we issued AD 2006–19– 12, we have received a report that an aft fairing lower spar web exceeded the allowable conductivity limits. This proposed AD would also require, depending on airplane configuration, one-time or repetitive detailed inspections for cracking and deformation, as applicable, of the aft fairing lower structure, and one-time or repetitive conductivity inspections of the aft fairing lower structure and related investigative and corrective actions if necessary. This proposed AD also adds airplanes to the applicability. We are proposing this AD to detect and correct degradation of the aft fairing lower web, which could lead to cracking of the web and could allow flammable fluids to leak into the heat shield pan castings, and consequent increased risk of an uncontained fire and subsequent structural damage. DATES: We must receive comments on this proposed AD by January 4, 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. mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:58 Nov 19, 2015 Jkt 238001 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 5809. 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–2015– 5809; 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: Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; telephone: 425–917–6438; fax: 425–917–6590; email: suzanne.lucier@ 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–2015–5809; Directorate Identifier 2015–NM–055–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:// PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 72621 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 On September 13, 2006, we issued AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006), for certain Boeing Model 777–200 and –300 series airplanes. AD 2006–19–12 requires inspecting the lower web of the aft fairing of engine struts for any discoloration and doing any related investigative and corrective action if necessary; inspecting the heat shield castings for any damage and doing any corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. AD 2006–19–12 resulted from a report that several discolored fairing lower webs and some damaged/ deteriorated insulation blankets were found in the aft fairings of engine struts. We issued AD 2006–19–12 to prevent cracking of lower webs of the aft fairings, which could result in flammable hydraulic fluid leaking onto or near an ignition source, and possibly result in an uncontrollable fire in the engine strut area. Actions Since AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006) Was Issued Since we issued AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006), we have received a report that an aft fairing lower spar web exceeded the allowable conductivity limits. An investigation concluded that wear to the pan casting and gap cover strips allowed increased heat into the aft fairing heat shield cavity, which exceeded the thermal capability of the insulation blankets. Related Service Information Under 1 CFR Part 51 We have reviewed Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012. The service information describes procedures for a detailed inspection of the gap cover strips and heat shield pan castings for damage, corrective actions, and installation of new gap cover strip fillers, new velcro strips, and new aft fairing insulation blankets. We reviewed Boeing Special Attention Service Bulletin 777–54– 0038, dated March 6, 2015. The service information describes procedures for one-time and repetitive detailed inspections for any cracking and deformation, as applicable, of the aft fairing lower structure; conductivity E:\FR\FM\20NOP1.SGM 20NOP1 72622 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Proposed Rules inspections of the aft fairing lower structure; and related investigative and corrective actions. 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 of this NPRM. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain all requirements of AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006). In addition, this proposed AD would add airplanes to the applicability of this AD. This proposed AD would also require accomplishing the actions specified in the service information described previously. The phrase ‘‘related investigative actions’’ is used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ‘‘corrective actions’’ is used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Change to AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006) Since AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006) was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have been redesignated in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 2006–19–12 Corresponding requirement in this proposed AD paragraph (f) paragraph (g) paragraph (h) paragraph (g) paragraph (h) paragraph (i) Costs of Compliance We estimate that this proposed AD affects 99 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection and other actions [retained actions from AD 2006–19-12, Amendment 39–14769 (71 FR 55727, September 25, 2006)]. Inspections [new proposed action]. Parts cost Cost per product Cost on U.S. operators Up to 11 work–hours × $85 per hour = $935, depending on airplane configuration. Up to $16,179, depending Up to $17,114, depending Up to $1,694,286, dependon airplane configuration. on airplane configuration. ing on airplane configuration Up to 24 work-hours × $85 per hour = $2,040, depending on airplane configuration. $0 ...................................... We estimate the following costs to do any necessary related investigative and corrective actions that would be Up to $2,040, depending Up to $201,960, dependon airplane configuration. ing on airplane configuration required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these inspections and replacements: ON-CONDITION COSTS Action Labor cost Related Investigative Actions .................. mstockstill on DSK4VPTVN1PROD with PROPOSALS Corrective Actions ................................... Up to 36 work-hours $3,060, depending figuration. Up to 38 work-hours $3,230, depending figuration. According to the manufacturer, all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Sep<11>2014 17:58 Nov 19, 2015 Jkt 238001 Parts cost × $85 per hour = on airplane con- $0 Up to $3,060, depending on airplane configuration × $85 per hour = on airplane con- 0 Up to $3,230, depending on airplane configuration 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 PO 00000 Frm 00015 Cost per product Fmt 4702 Sfmt 4702 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. E:\FR\FM\20NOP1.SGM 20NOP1 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Proposed Rules Regulatory Findings We have 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 that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006), and adding the following new AD: ■ The Boeing Company: Docket No. FAA– 2015–5809; Directorate Identifier 2015– NM–055–AD. mstockstill on DSK4VPTVN1PROD with PROPOSALS (a) Comments Due Date The FAA must receive comments on this AD action by January 4, 2016. (b) Affected ADs This AD replaces AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006). (c) Applicability This AD applies to The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes, certified in any category, as identified in Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015. VerDate Sep<11>2014 17:58 Nov 19, 2015 Jkt 238001 (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/pylons. (e) Unsafe Condition This AD was prompted by a report that an aft fairing lower spar web exceeded the allowable conductivity limits. An investigation concluded that wear to the pan casting and gap cover strips allowed increased heat into the aft fairing heat shield cavity. We are proposing this AD to detect and correct degradation of the aft fairing lower web, which could lead to cracking of the web and could allow flammable fluids to leak into the heat shield pan castings, and consequent increased risk of an uncontained fire and subsequent structural damage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection, Installation, and Replacement Actions With No Changes This paragraph restates the actions required by paragraph (f) of AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006), with no changes. For Model 777–200 and –300 series airplanes identified in Boeing Special Attention Service Bulletin 777–54–0021, Revision 1, dated March 16, 2006: Except as provided by paragraph (h) of this AD, within 12 months after October 30, 2006 (the effective date of AD 2006–19–12), do the actions specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–54– 0021, Revision 1, dated March 16, 2006. (1) Do a general visual inspection of the lower web of the aft fairing for any discoloration and do any related investigative action. (2) Do a general visual inspection of the heat shield castings for any damage (crack(s), dent(s), gouge(s), warpage, fretting, or missing/loose nutplates). (3) Install gap cover strips on the heat shield pans. (4) Replace insulation blankets on the heat shield pans with new insulation blankets. (h) Retained Repair Instructions This paragraph restates the actions required by paragraph (g) of AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006), with no changes. If any damage, discoloration, heat damage, or crack is found during any inspection required by paragraph (g) of this AD: Before further flight, do all applicable corrective actions in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, or in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–54– 0021, Revision 1, dated March 16, 2006. (i) Retained Credit for Previous Actions With Revised Format This paragraph restates the credit provided by paragraph (h) of AD 2006–19–12, Amendment 39–14769 (71 FR 55727, PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 72623 September 25, 2006), with revised format. This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before October 30, 2006 (the effective date of AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006)) using Boeing Special Attention Service Bulletin 777–54–0021, dated June 23, 2005, except where Boeing Special Attention Service Bulletin 777–54– 0021, dated June 23, 2005, does not provide an International Annealed Copper Standard (IACS) value for determining the results of the inspection for heat damage, the maximum acceptable IACS value is 42 percent. Boeing Special Attention Service Bulletin 777–54–0021, dated June 23, 2005, is not incorporated by reference in this AD. (j) New Requirements: Detailed and Conductivity Inspections and Related Investigative and Corrective Actions (Repetitive Inspections for Certain Airplanes) Within 24 months after the effective date of this AD: Do detailed and conductivity inspections of the aft fairing lower structure for cracks and deformation, as applicable, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–54– 0038, dated March 6, 2015. Do all applicable related investigative and corrective actions before further flight. For Group 1, Configurations 1 and 3 airplanes, and Group 2, Configuration 1, airplanes, identified in Boeing Special Attention Service Bulletin 777–54–0038, dated March 6, 2015, repeat the inspections thereafter at intervals not to exceed 24 months until the terminating action specified in paragraph (k) of this AD is done. (k) Optional Terminating Action Accomplishing a detailed inspection of the gap cover strips and heat shield pan castings for damage and applicable corrective actions, and installation of new gap cover strip fillers, new velcro strips, and new aft fairing insulation blankets, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012, concurrently with accomplishing detailed and conductivity inspections and all applicable related investigative and corrective actions required by paragraph (j) of this AD, terminates the repetitive inspections specified in paragraph (j) of this AD; except where Boeing Service Bulletin 777–54–0026, Revision 2, dated January 5, 2012, specifies to contact the manufacturer, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (l) 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 E:\FR\FM\20NOP1.SGM 20NOP1 72624 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Proposed Rules attention of the person identified in paragraph (m)(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 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. For a repair method to be approved, the repair must meet the certification basis of airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2006–19–12, Amendment 39–14769 (71 FR 55727, September 25, 2006) are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), and (i) of this AD. (m) Related Information (1) For more information about this AD, contact Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–917–6438; fax: 425–917–6590; email: suzanne.lucier@ faa.gov. (2) For 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. 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 November 12, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–29617 Filed 11–19–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Highway Administration 23 CFR Parts 771 and 774 Federal Transit Administration mstockstill on DSK4VPTVN1PROD with PROPOSALS 49 CFR Part 622 [Docket No. FHWA–2015–0011] FHWA RIN 2125–AF60 FTA RIN 2132–AB26 Environmental Impact and Related Procedures Federal Highway Administration (FHWA), Federal Transit Administration (FTA), DOT. AGENCY: VerDate Sep<11>2014 17:58 Nov 19, 2015 Jkt 238001 Notice of proposed rulemaking (NPRM). ACTION: This NPRM provides interested parties with the opportunity to comment on proposed revisions to the FHWA and FTA joint regulations that implement the National Environmental Policy Act (NEPA) and Section 4(f) of the Department of Transportation Act. The revisions are prompted by the enactment of the Moving Ahead for Progress in the 21st Century Act (MAP–21), which requires rulemaking to address programmatic approaches. This NPRM proposes to revise the FHWA/FTA Environmental Impact and Related Procedures and Parks, Recreation Areas, Wildlife and Waterfowl Refuges, and Historic Sites regulations due to MAP–21 changes to the environmental review process that FHWA and FTA have not previously captured in other rulemakings, such as the use of programmatic agreements and the use of single final environmental impact statement/record of decision documents. In addition, FHWA and FTA propose changes to the regulatory text to improve readability and to reflect current practice, consistent with an Executive order to improve regulations and regulatory review. The FHWA and FTA seek comments on the proposals contained in this notice. DATES: Comments must be received on or before January 19, 2016. ADDRESSES: To ensure that you do not duplicate your docket submissions, please submit them by only one of the following means: Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the online instructions for submitting comments. Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Ave. SE., West Building Ground Floor Room W12–140, Washington, DC 20590. Hand Delivery: West Building Ground Floor, Room W12–140, 1200 New Jersey Ave. SE., between 9:00 a.m. and 5:00 p.m., Monday through Friday, except Federal holidays. The telephone number is (202) 366–9329. Instructions: You must include the agency name and docket number or the Regulatory Identifier Number (RIN) for the rulemaking at the beginning of your comments. All comments received will be posted without change to http:// www.regulations.gov, including any personal information provided. FOR FURTHER INFORMATION CONTACT: For the FHWA: Neel Vanikar, Office of Project Development and Environmental Review, (202) 366–2068, or Diane SUMMARY: PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 Mobley, Office of Chief Counsel, (202) 366–1366. For FTA: Megan Blum, Office of Planning and Environment, (202) 366–0463, or Helen Serassio, Office of Chief Counsel, (202) 366–1974. The FHWA and FTA are both located at 1200 New Jersey Ave. SE., Washington, DC 20590. Office hours are from 9:00 a.m. to 5:00 p.m., Monday through Friday, except Federal holidays. SUPPLEMENTARY INFORMATION: Background On July 6, 2012, President Obama signed into law MAP–21 (Pub. L. 112– 141, 126 Stat. 405), which contains new requirements that FHWA and FTA, hereafter referred to as the ‘‘Agencies,’’ must meet in complying with NEPA (42 U.S.C. 4321 et seq.), as well as a requirement to initiate a rulemaking to allow for the use of programmatic approaches. 23 U.S.C. 139(b)(3)(A). Through this NPRM, the Agencies propose to revise their regulations that implement NEPA at 23 CFR part 771— Environmental Impact and Related Procedures, and 23 U.S.C. 138 and 49 U.S.C. 303 (hereafter referred to as Section 4(f) 1) at 23 CFR part 774— Parks, Recreation Areas, Wildlife and Waterfowl Refuges, and Historic Sites. The proposed revisions would reflect MAP–21 requirements and better reflect current Agency practice, as well as improve readability consistent with Executive Order 13563, ‘‘Improving Regulation and Regulatory Review’’ (2011). General Discussion of the Proposals The following bullets are sections of MAP–21 that affect 23 CFR parts 771 and 774; the list does not include the sections of MAP–21 that have been the subject of other rulemakings: • Section 1119(c)(2) revised the Section 4(f) exception for park road and parkway projects to apply to Federal lands transportation facilities, which affects the Section 4(f) exception in 774.13(e); • Section 1122 replaced the former ‘‘transportation enhancement projects program’’ with a new ‘‘transportation alternatives projects program,’’ which affects the Section 4(f) exception in 774.13(g); • Section 1302 amended 23 U.S.C. 108 to address advance acquisition of real property interests, which affects the 1 Section 4(f) of the Department of Transportation Act of 1966 was repealed in 1983 when it was codified without substantive change at 49 U.S.C. 303. A provision with the same meaning is found at 23 U.S.C. 138. This regulation continues to refer to Section 4(f) as such because the policies Section 4(f) engendered are widely referred to as ‘‘Section 4(f)’’ matters. E:\FR\FM\20NOP1.SGM 20NOP1

Agencies

[Federal Register Volume 80, Number 224 (Friday, November 20, 2015)]
[Proposed Rules]
[Pages 72621-72624]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-29617]



[[Page 72621]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-5809; Directorate Identifier 2015-NM-055-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2006-19-
12, which applies to certain The Boeing Model 777-200 and -300 series 
airplanes. AD 2006-19-12 currently requires inspecting the lower web of 
the aft fairing of the engine struts for any discoloration and doing 
any related investigative and corrective action if necessary; 
inspecting the heat shield castings for any damage and doing any 
corrective action if necessary; installing gap cover strips; and 
replacing insulation blankets with new insulation blankets. Since we 
issued AD 2006-19-12, we have received a report that an aft fairing 
lower spar web exceeded the allowable conductivity limits. This 
proposed AD would also require, depending on airplane configuration, 
one-time or repetitive detailed inspections for cracking and 
deformation, as applicable, of the aft fairing lower structure, and 
one-time or repetitive conductivity inspections of the aft fairing 
lower structure and related investigative and corrective actions if 
necessary. This proposed AD also adds airplanes to the applicability. 
We are proposing this AD to detect and correct degradation of the aft 
fairing lower web, which could lead to cracking of the web and could 
allow flammable fluids to leak into the heat shield pan castings, and 
consequent increased risk of an uncontained fire and subsequent 
structural damage.

DATES: We must receive comments on this proposed AD by January 4, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 
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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-5809.

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-2015-
5809; 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: Sue Lucier, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-
6438; fax: 425-917-6590; email: suzanne.lucier@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-2015-5809; 
Directorate Identifier 2015-NM-055-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

    On September 13, 2006, we issued AD 2006-19-12, Amendment 39-14769 
(71 FR 55727, September 25, 2006), for certain Boeing Model 777-200 and 
-300 series airplanes. AD 2006-19-12 requires inspecting the lower web 
of the aft fairing of engine struts for any discoloration and doing any 
related investigative and corrective action if necessary; inspecting 
the heat shield castings for any damage and doing any corrective action 
if necessary; installing gap cover strips; and replacing insulation 
blankets with new insulation blankets. AD 2006-19-12 resulted from a 
report that several discolored fairing lower webs and some damaged/
deteriorated insulation blankets were found in the aft fairings of 
engine struts. We issued AD 2006-19-12 to prevent cracking of lower 
webs of the aft fairings, which could result in flammable hydraulic 
fluid leaking onto or near an ignition source, and possibly result in 
an uncontrollable fire in the engine strut area.

Actions Since AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 
25, 2006) Was Issued

    Since we issued AD 2006-19-12, Amendment 39-14769 (71 FR 55727, 
September 25, 2006), we have received a report that an aft fairing 
lower spar web exceeded the allowable conductivity limits. An 
investigation concluded that wear to the pan casting and gap cover 
strips allowed increased heat into the aft fairing heat shield cavity, 
which exceeded the thermal capability of the insulation blankets.

Related Service Information Under 1 CFR Part 51

    We have reviewed Boeing Service Bulletin 777-54-0026, Revision 2, 
dated January 5, 2012. The service information describes procedures for 
a detailed inspection of the gap cover strips and heat shield pan 
castings for damage, corrective actions, and installation of new gap 
cover strip fillers, new velcro strips, and new aft fairing insulation 
blankets.
    We reviewed Boeing Special Attention Service Bulletin 777-54-0038, 
dated March 6, 2015. The service information describes procedures for 
one-time and repetitive detailed inspections for any cracking and 
deformation, as applicable, of the aft fairing lower structure; 
conductivity

[[Page 72622]]

inspections of the aft fairing lower structure; and related 
investigative and corrective actions.
    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 of this 
NPRM.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2006-19-12, 
Amendment 39-14769 (71 FR 55727, September 25, 2006). In addition, this 
proposed AD would add airplanes to the applicability of this AD. This 
proposed AD would also require accomplishing the actions specified in 
the service information described previously.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary action, and (2) further investigate 
the nature of any condition found. Related investigative actions in an 
AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Change to AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 
2006)

    Since AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 
2006) was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have been redesignated in this proposed AD, as 
listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                     Corresponding  requirement in this
   Requirement in AD 2006-19-12                  proposed AD
------------------------------------------------------------------------
 paragraph (f)                       paragraph (g)
 paragraph (g)                       paragraph (h)
 paragraph (h)                       paragraph (i)
------------------------------------------------------------------------

Costs of Compliance

    We estimate that this proposed AD affects 99 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection and other actions      Up to 11 work-      Up to $16,179,      Up to $17,114,      Up to $1,694,286,
 [retained actions from AD 2006-   hours x $85 per     depending on        depending on        depending on
 19[dash]12, Amendment 39-14769    hour = $935,        airplane            airplane            airplane
 (71 FR 55727, September 25,       depending on        configuration.      configuration.      configuration
 2006)].                           airplane
                                   configuration.
Inspections [new proposed         Up to 24            $0................  Up to $2,040,       Up to $201,960,
 action].                          work[dash]hours x                       depending on        depending on
                                   $85 per hour =                          airplane            airplane
                                   $2,040, depending                       configuration.      configuration
                                   on airplane
                                   configuration.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary related 
investigative and corrective actions 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 these inspections and 
replacements:

                                               On-Condition costs
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Related Investigative Actions...........  Up to 36 work[dash]hours x              $0  Up to $3,060, depending on
                                           $85 per hour = $3,060,                      airplane configuration
                                           depending on airplane
                                           configuration.
Corrective Actions......................  Up to 38 work[dash]hours x               0  Up to $3,230, depending on
                                           $85 per hour = $3,230,                      airplane configuration
                                           depending on airplane
                                           configuration.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, all of the costs of this proposed AD 
may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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.

[[Page 72623]]

Regulatory Findings

    We have 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 that the 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 removing Airworthiness Directive (AD) 
2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2015-5809; Directorate Identifier 
2015-NM-055-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by January 4, 
2016.

(b) Affected ADs

    This AD replaces AD 2006-19-12, Amendment 39-14769 (71 FR 55727, 
September 25, 2006).

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes, certified in any category, 
as identified in Boeing Special Attention Service Bulletin 777-54-
0038, dated March 6, 2015.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Unsafe Condition

    This AD was prompted by a report that an aft fairing lower spar 
web exceeded the allowable conductivity limits. An investigation 
concluded that wear to the pan casting and gap cover strips allowed 
increased heat into the aft fairing heat shield cavity. We are 
proposing this AD to detect and correct degradation of the aft 
fairing lower web, which could lead to cracking of the web and could 
allow flammable fluids to leak into the heat shield pan castings, 
and consequent increased risk of an uncontained fire and subsequent 
structural damage.

(f) Compliance

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

(g) Retained Inspection, Installation, and Replacement Actions With No 
Changes

    This paragraph restates the actions required by paragraph (f) of 
AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), 
with no changes. For Model 777-200 and -300 series airplanes 
identified in Boeing Special Attention Service Bulletin 777-54-0021, 
Revision 1, dated March 16, 2006: Except as provided by paragraph 
(h) of this AD, within 12 months after October 30, 2006 (the 
effective date of AD 2006-19-12), do the actions specified in 
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-54-0021, Revision 1, dated March 16, 
2006.
    (1) Do a general visual inspection of the lower web of the aft 
fairing for any discoloration and do any related investigative 
action.
    (2) Do a general visual inspection of the heat shield castings 
for any damage (crack(s), dent(s), gouge(s), warpage, fretting, or 
missing/loose nutplates).
    (3) Install gap cover strips on the heat shield pans.
    (4) Replace insulation blankets on the heat shield pans with new 
insulation blankets.

(h) Retained Repair Instructions

    This paragraph restates the actions required by paragraph (g) of 
AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), 
with no changes. If any damage, discoloration, heat damage, or crack 
is found during any inspection required by paragraph (g) of this AD: 
Before further flight, do all applicable corrective actions in 
accordance with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA, or in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-54-0021, Revision 1, dated March 16, 2006.

(i) Retained Credit for Previous Actions With Revised Format

    This paragraph restates the credit provided by paragraph (h) of 
AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), 
with revised format. This paragraph provides credit for actions 
required by paragraph (g) of this AD, if those actions were 
performed before October 30, 2006 (the effective date of AD 2006-19-
12, Amendment 39-14769 (71 FR 55727, September 25, 2006)) using 
Boeing Special Attention Service Bulletin 777-54-0021, dated June 
23, 2005, except where Boeing Special Attention Service Bulletin 
777-54-0021, dated June 23, 2005, does not provide an International 
Annealed Copper Standard (IACS) value for determining the results of 
the inspection for heat damage, the maximum acceptable IACS value is 
42 percent. Boeing Special Attention Service Bulletin 777-54-0021, 
dated June 23, 2005, is not incorporated by reference in this AD.

(j) New Requirements: Detailed and Conductivity Inspections and Related 
Investigative and Corrective Actions (Repetitive Inspections for 
Certain Airplanes)

    Within 24 months after the effective date of this AD: Do 
detailed and conductivity inspections of the aft fairing lower 
structure for cracks and deformation, as applicable, and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-54-0038, dated March 6, 2015. Do all 
applicable related investigative and corrective actions before 
further flight. For Group 1, Configurations 1 and 3 airplanes, and 
Group 2, Configuration 1, airplanes, identified in Boeing Special 
Attention Service Bulletin 777-54-0038, dated March 6, 2015, repeat 
the inspections thereafter at intervals not to exceed 24 months 
until the terminating action specified in paragraph (k) of this AD 
is done.

(k) Optional Terminating Action

    Accomplishing a detailed inspection of the gap cover strips and 
heat shield pan castings for damage and applicable corrective 
actions, and installation of new gap cover strip fillers, new velcro 
strips, and new aft fairing insulation blankets, in accordance with 
the Accomplishment Instructions of Boeing Service Bulletin 777-54-
0026, Revision 2, dated January 5, 2012, concurrently with 
accomplishing detailed and conductivity inspections and all 
applicable related investigative and corrective actions required by 
paragraph (j) of this AD, terminates the repetitive inspections 
specified in paragraph (j) of this AD; except where Boeing Service 
Bulletin 777-54-0026, Revision 2, dated January 5, 2012, specifies 
to contact the manufacturer, repair using a method approved in 
accordance with the procedures specified in paragraph (l) of this 
AD.

(l) 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

[[Page 72624]]

attention of the person identified in paragraph (m)(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 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. For a repair method to be approved, the repair must 
meet the certification basis of airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved for AD 2006-19-12, Amendment 39-14769 (71 FR 
55727, September 25, 2006) are approved as AMOCs for the 
corresponding provisions of paragraphs (g), (h), and (i) of this AD.

(m) Related Information

    (1) For more information about this AD, contact Sue Lucier, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-
6438; fax: 425-917-6590; email: suzanne.lucier@faa.gov.
    (2) For 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. 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 November 12, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-29617 Filed 11-19-15; 8:45 am]
BILLING CODE 4910-13-P