Airworthiness Directives; The Boeing Company Airplanes, 12954-12957 [2015-05032]

Download as PDF 12954 Proposed Rules Federal Register Vol. 80, No. 48 Thursday, March 12, 2015 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF AGRICULTURE Animal and Plant Health Inspection Service 7 CFR Part 319 [Docket No. APHIS–2014–0041] RIN 0579–AE01 Importation of Orchids in Growing Media From Taiwan Animal and Plant Health Inspection Service, USDA. ACTION: Proposed rule; reopening of comment period. AGENCY: We are reopening the comment period for our proposed rule that would amend the regulations governing the importation of plants and plant products to add orchid plants of the genus Oncidium from Taiwan to the list of plants that may be imported into the United States in an approved growing medium, subject to specified growing, inspection, and certification requirements. This action will allow interested persons additional time to prepare and submit comments. DATES: The comment period for the proposed rule published on December 3, 2014 (79 FR 71703–71705) is reopened. We will consider all comments that we receive on or before March 18, 2015. ADDRESSES: You may submit comments by either of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov/ #!docketDetail;D=APHIS-2014-0041. • Postal Mail/Commercial Delivery: Send your comment to Docket No. APHIS–2014–0041, Regulatory Analysis and Development, PPD, APHIS, Station 3A–03.8, 4700 River Road Unit 118, Riverdale, MD 20737–1238. Supporting documents and any comments we receive on this docket may be viewed at http:// www.regulations.gov/ #!docketDetail;D=APHIS-2014-0041 or in our reading room, which is located in room 1141 of the USDA South Building, 14th Street and Independence Avenue rljohnson on DSK3VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 14:15 Mar 11, 2015 Jkt 235001 SW., Washington, DC. Normal reading room hours are 8 a.m. to 4:30 p.m., Monday through Friday, except holidays. To be sure someone is there to help you, please call (202) 799–7039 before coming. FOR FURTHER INFORMATION CONTACT: Ms. Heather Coady, Regulatory Policy Specialist, Plants for Planting Policy, PPQ, APHIS, 4700 River Road Unit 133, Riverdale, MD 20737; (301) 851–2076. SUPPLEMENTARY INFORMATION: On December 3, 2014, we published in the Federal Register (79 FR 71703–71705, Docket No. APHIS–2014–0041) a proposal to amend the regulations in 7 CFR 319.37–8(e) by adding Oncidium spp. from Taiwan to the list of plants established in an approved growing medium that may be imported into the United States. Comments on the proposed rule were required to be received on or before February 2, 2015. We are reopening the comment period on Docket No. APHIS– 2014–0041 for an additional 45 days. We will also accept all comments received between February 3, 2015 (the day after the close of the original comment period) and the date of this notice. This action will allow interested persons additional time to prepare and submit comments. Authority: 7 U.S.C. 450, 7701–7772, and 7781–7786; 21 U.S.C. 136 and 136a; 7 CFR 2.22, 2.80, and 371.3. Done in Washington, DC, this 6th day of March 2015. Kevin Shea Administrator, Animal and Plant Health Inspection Service. [FR Doc. 2015–05659 Filed 3–11–15; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0247; Directorate Identifier 2014–NM–178–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777–200 and –300 series airplanes equipped with Rolls-Royce Trent 800 series engines. This proposed AD was prompted by a report of multiple cases of heat damage to the strut aft fairing heat shield primary seal, as well as heat and wear damage to the heat shield insulation blankets. This proposed AD would require repetitive inspections for heat damage to the strut aft fairing lower spar web structure (a flammable fluid zone barrier and fire wall) and heat shield primary seal, and heat and wear damage to heat shield insulation blankets; and related investigative and corrective actions if necessary. This proposed AD would also provide optional terminating action for the repetitive inspections. We are proposing this AD to detect and correct heat damage to the strut aft fairing lower spar web structure and heat shield primary seal, as well as heat and wear damage to the heat shield insulation blankets, which could lead to through-cracks in the aft fairing web structure and heating of the aft fairing web structure, and consequent uncontrolled fire in the aft fairing, fuel tank ignition or possible departure of the engine, and subsequent loss of the airplane. DATES: We must receive comments on this proposed AD by April 27, 2015. 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 SUMMARY: E:\FR\FM\12MRP1.SGM 12MRP1 Federal Register / Vol. 80, No. 48 / Thursday, March 12, 2015 / Proposed Rules 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 https:// www.regulations.gov by searching and locating Docket No. FAA–2015–0247. 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– 0247; 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: Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6501; fax: 425–917–6590; email: kevin.nguyen@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited rljohnson on DSK3VPTVN1PROD with PROPOSALS We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2015–0247; Directorate Identifier 2014– NM–178–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received a report of multiple cases of heat damage to the strut aft fairing heat shield primary seals, as well as heat and wear damage to the heat shield insulation blankets. Improper design of the strut aft fairing #1 heat shield (a titanium pan casting) and #1 heat shield insulation blanket allows hot turbulent gas from the exhaust nozzle to wear and cause degradation of the front face of the #1 insulation blankets and flow into the heat shield cavity, the space or cavity between the heat shields and insulation blankets, and the strut aft fairing lower spar web structure. Continuous exposure to hot turbulent gas further damages the primary seal and #1 insulation blanket, increases the temperature in the heat shield cavity, and can damage all insulation blankets and lower web structure. The insulation blankets are attached underneath the lower spar web structure and are intended to protect the web from hot exhaust gas. The insulation blankets were not originally designed to withstand additional hot gas exposure, and consequently are unable to adequately protect the lower web structure. The strut aft fairing lower spar web structure is made of aluminum and designed to be a flammable fluid zone barrier and firewall, as part of the aft fairing fire protection system. Insufficient thermal protection and continuous exposure to hot gases and elevated temperatures can degrade the lower spar web structure material property. The heat-damaged web structures could become annealed and cracked from fatigue, compromising the firewall and allowing flammable fluids to leak onto the high-temperature heat shield, initiate a fire, and cause an uncontained fire in the aft fairing, potentially leading to fire in the wing tank. An uncontained fire in the aft fairing can weaken the diagonal brace and lower wing skin, which are primary structural elements that carry and support engine loads. This condition, if not corrected, could result in throughcracks in the aft fairing web structure and heating of the aft fairing web structure, and consequent uncontrolled fire in the aft fairing, fuel tank ignition or possible departure of the engine. 12955 Related Service Information Under 1 CFR Part 51 We reviewed the following service information: • Boeing Service Bulletin 777– 54A0031, Revision 1, dated May 9, 2014. • Boeing Service Bulletin 777–54– 0030, dated May 27, 2014. The service information describes procedures for repetitive inspections for heat damage to the strut aft fairing lower spar web structure (a flammable fluid zone barrier and fire wall) and heat shield primary seal, and heat and wear damage to heat shield insulation blankets; and related investigative and corrective actions. For information on the procedures and compliance times, see this service information. This service information is reasonably available; see ADDRESSES for ways to access this service information. 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 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 actions, 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. Costs of Compliance We estimate that this proposed AD affects 57 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost Inspections ..................... 40 work-hours × $85 per hour = $3,400 per inspection cycle. $0 VerDate Sep<11>2014 14:15 Mar 11, 2015 Jkt 235001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Cost per product $3,400 per inspection cycle. E:\FR\FM\12MRP1.SGM 12MRP1 Cost on U.S. operators $193,800 per inspection cycle. 12956 Federal Register / Vol. 80, No. 48 / Thursday, March 12, 2015 / Proposed Rules We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of determining the number of airplanes that might need these replacements: ON-CONDITION COSTS Action Labor cost Heat shield primary seal replacement .......................... Cracked or damaged parts replacement ...................... 10 work-hours × $85 per hour = $850 ......................... 110 work-hours × $85 per hour = $9,350 .................... According to the manufacturer, some 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. on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Authority for This Rulemaking The Proposed Amendment 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: rljohnson on DSK3VPTVN1PROD with PROPOSALS Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, VerDate Sep<11>2014 14:15 Mar 11, 2015 Jkt 235001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2015–0247; Directorate Identifier 2014– NM–178–AD. (a) Comments Due Date We must receive comments by April 27, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777–200 and –300 series airplanes equipped with Rolls-Royce Trent 800 series engines, certificated in any category, as identified in Boeing Service Bulletin 777– 54A0031, Revision 1, dated May 9, 2014. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/Pylons. (e) Unsafe Condition This AD was prompted by reports of heat damage to the strut aft fairing heat shield primary seal, as well as heat and wear damage to the heat shield insulation blankets. We are issuing this AD to detect and correct heat damage to the strut aft fairing lower spar web structure (a flammable fluid zone barrier and fire wall) and heat shield primary seal, as well as heat and wear damage to the heat shield insulation blankets, which could lead to through-cracks PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Parts cost $1,940 52,992 Cost per product $2,790 62,342 in the aft fairing web structure and heating of the aft fairing web structure, and consequent uncontrolled fire in the aft fairing, fuel tank ignition or possible departure of the engine. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 777–54A0031, Revision 1, dated May 9, 2014, except as required by paragraph (i) of this AD: Do the inspections specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777– 54A0031, Revision 1, dated May 9, 2014. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 777–54A0031, Revision 1, dated May 9, 2014. (1) Do a detailed inspection for cracks and heat damage of the aft fairing lower spar upper surface. (2) Do a conductivity inspection for heat damage of the aft fairing lower spar upper surface. (3) Do a detailed inspection for wear of the heat shield primary seal. (h) Optional Terminating Action The concurrent accomplishment of the actions specified in paragraphs (h)(1) and (h)(2) of this AD terminates the requirements of paragraph (g) of this AD. (1) Replacement of all heat shield insulation blankets (rub strips, heat shield pan casting, Velcro strips, aft fairing web drain sump, drain screen, and drain tubes, as applicable) in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–54–0030, dated May 27, 2014. (2) A one-time detailed inspection for cracks and heat damage of the aft fairing lower spar upper surface, conductivity inspection for heat damage of the aft fairing lower spar upper surface, and detailed inspection for wear of heat shield primary seal, and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–54A0031, Revision 1, dated May 9, 2014, provided all applicable E:\FR\FM\12MRP1.SGM 12MRP1 Federal Register / Vol. 80, No. 48 / Thursday, March 12, 2015 / Proposed Rules related investigative and corrective actions are done before further flight. (i) Exception to Service Information Specifications Where Boeing Service Bulletin 777– 54A0031, Revision 1, dated May 9, 2014, specifies a compliance time ‘‘After the Original Issue Date of this Service Bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (j) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (g)(1), (g)(2), (g)(3) and (h)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 777–54A0031, dated June 7, 2013. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l)(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 the airplane, and the approval must specifically refer to this AD. rljohnson on DSK3VPTVN1PROD with PROPOSALS (l) Related Information (1) For more information about this AD, contact Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6501; fax: 425–917–6590; email: kevin.nguyen@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. VerDate Sep<11>2014 14:15 Mar 11, 2015 Jkt 235001 Issued in Renton, Washington, on February 19, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–05032 Filed 3–11–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF LABOR Office of Workers’ Compensation Programs 20 CFR Parts 702 and 703 RIN 1240–AA09 Longshore and Harbor Workers’ Compensation Act: Transmission of Documents and Information Office of Workers’ Compensation Programs, Labor. ACTION: Notice of proposed rulemaking; request for comments. AGENCY: Parties to claims arising under the Longshore and Harbor Workers’ Compensation Act and its extensions (LHWCA or Act) and entities required to have insurance pursuant to the Act frequently correspond with the Office of Workers’ Compensation Programs (OWCP) and each other. The current regulations require that some of these communications be made in paper form via a specific delivery mechanism such as certified mail, U.S. mail or hand delivery. As technologies improve, other means of communication—including electronic methods—may be more efficient and cost-effective. Accordingly, this proposed rule would broaden the acceptable methods by which claimants, employers, and insurers can communicate with OWCP and each other. SUMMARY: Comments on this proposed rule must be received by midnight Eastern Standard Time on May 11, 2015. ADDRESSES: You may submit written comments, identified by RIN number 1240–AA09, by any of the following methods. • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions on the Web site for submitting comments. To facilitate receipt and processing of comments, OWCP encourages interested parties to submit their comments electronically. • Fax: (202) 693–1380 (this is not a toll-free number). Only comments of ten or fewer pages, including a Fax cover sheet and attachments, if any, will be accepted by Fax. • Regular Mail: Division of Longshore and Harbor Workers’ Compensation, DATES: PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 12957 Office of Workers’ Compensation Programs, U.S. Department of Labor, Suite C–4319, 200 Constitution Avenue NW., Washington, DC 20210. The Department’s receipt of U.S. mail may be significantly delayed due to security procedures. You must take this into consideration when preparing to meet the deadline for submitting comments. • Hand Delivery/Courier: Division of Longshore and Harbor Workers’ Compensation, Office of Workers’ Compensation Programs, U.S. Department of Labor, Suite C–4319, 200 Constitution Avenue NW., Washington, DC 20210. Instructions: All submissions received must include the agency name and the Regulatory Information Number (RIN) for this rulemaking. All comments received will be posted without change to http://www.regulations.gov, including any personal information provided. Docket: For access to the docket to read background documents or comments received, go to http:// www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Antonio Rios, Director, Division of Longshore and Harbor Workers’ Compensation, Office of Workers’ Compensation Programs, U.S. Department of Labor, Suite C–4319, 200 Constitution Avenue NW., Washington, DC 20210. Telephone: (202) 693–0038 (this is not a toll-free number). TTY/ TDD callers may dial toll-free 1–877– 889–5627 for further information. SUPPLEMENTARY INFORMATION: I. Proposed Rule Published Concurrently With Companion Direct Final Rule In the Final Rules section of this Federal Register edition, OWCP is simultaneously publishing an identical rule as a ‘‘direct final’’ rule. In direct final rulemaking, an agency publishes a direct final rule in the Federal Register with a statement that the rule will go into effect unless the agency receives significant adverse comment within a specified period. The agency concurrently publishes an identical proposed rule. If the agency receives no significant adverse comment in response to the direct final rule, the rule goes into effect. If the agency receives significant adverse comment, the agency withdraws the direct final rule and treats such comment as submissions on the proposed rule. An agency typically uses direct final rulemaking when it anticipates the rule will be noncontroversial. OWCP has determined that this rule, which modifies the existing regulations to facilitate the exchange of documents E:\FR\FM\12MRP1.SGM 12MRP1

Agencies

[Federal Register Volume 80, Number 48 (Thursday, March 12, 2015)]
[Proposed Rules]
[Pages 12954-12957]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-05032]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0247; Directorate Identifier 2014-NM-178-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 777-200 and -300 series airplanes 
equipped with Rolls-Royce Trent 800 series engines. This proposed AD 
was prompted by a report of multiple cases of heat damage to the strut 
aft fairing heat shield primary seal, as well as heat and wear damage 
to the heat shield insulation blankets. This proposed AD would require 
repetitive inspections for heat damage to the strut aft fairing lower 
spar web structure (a flammable fluid zone barrier and fire wall) and 
heat shield primary seal, and heat and wear damage to heat shield 
insulation blankets; and related investigative and corrective actions 
if necessary. This proposed AD would also provide optional terminating 
action for the repetitive inspections. We are proposing this AD to 
detect and correct heat damage to the strut aft fairing lower spar web 
structure and heat shield primary seal, as well as heat and wear damage 
to the heat shield insulation blankets, which could lead to through-
cracks in the aft fairing web structure and heating of the aft fairing 
web structure, and consequent uncontrolled fire in the aft fairing, 
fuel tank ignition or possible departure of the engine, and subsequent 
loss of the airplane.

DATES: We must receive comments on this proposed AD by April 27, 2015.

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

[[Page 12955]]

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 https://www.regulations.gov by searching and locating Docket No. FAA-2015-0247.

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-
0247; 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: Kevin Nguyen, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6501; fax: 425-917-6590; email: kevin.nguyen@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2015-0247; 
Directorate Identifier 2014-NM-178-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received a report of multiple cases of heat damage to the 
strut aft fairing heat shield primary seals, as well as heat and wear 
damage to the heat shield insulation blankets. Improper design of the 
strut aft fairing #1 heat shield (a titanium pan casting) and #1 heat 
shield insulation blanket allows hot turbulent gas from the exhaust 
nozzle to wear and cause degradation of the front face of the #1 
insulation blankets and flow into the heat shield cavity, the space or 
cavity between the heat shields and insulation blankets, and the strut 
aft fairing lower spar web structure. Continuous exposure to hot 
turbulent gas further damages the primary seal and #1 insulation 
blanket, increases the temperature in the heat shield cavity, and can 
damage all insulation blankets and lower web structure.
    The insulation blankets are attached underneath the lower spar web 
structure and are intended to protect the web from hot exhaust gas. The 
insulation blankets were not originally designed to withstand 
additional hot gas exposure, and consequently are unable to adequately 
protect the lower web structure. The strut aft fairing lower spar web 
structure is made of aluminum and designed to be a flammable fluid zone 
barrier and firewall, as part of the aft fairing fire protection 
system.
    Insufficient thermal protection and continuous exposure to hot 
gases and elevated temperatures can degrade the lower spar web 
structure material property. The heat-damaged web structures could 
become annealed and cracked from fatigue, compromising the firewall and 
allowing flammable fluids to leak onto the high-temperature heat 
shield, initiate a fire, and cause an uncontained fire in the aft 
fairing, potentially leading to fire in the wing tank. An uncontained 
fire in the aft fairing can weaken the diagonal brace and lower wing 
skin, which are primary structural elements that carry and support 
engine loads. This condition, if not corrected, could result in 
through-cracks in the aft fairing web structure and heating of the aft 
fairing web structure, and consequent uncontrolled fire in the aft 
fairing, fuel tank ignition or possible departure of the engine.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information:
     Boeing Service Bulletin 777-54A0031, Revision 1, dated May 
9, 2014.
     Boeing Service Bulletin 777-54-0030, dated May 27, 2014.
    The service information describes procedures for repetitive 
inspections for heat damage to the strut aft fairing lower spar web 
structure (a flammable fluid zone barrier and fire wall) and heat 
shield primary seal, and heat and wear damage to heat shield insulation 
blankets; and related investigative and corrective actions. For 
information on the procedures and compliance times, see this service 
information. This service information is reasonably available; see 
ADDRESSES for ways to access this service information.

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 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 actions, 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.

Costs of Compliance

    We estimate that this proposed AD affects 57 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
----------------------------------------------------------------------------------------------------------------
Inspections......................  40 work-hours x $85            $0   $3,400 per            $193,800 per
                                    per hour = $3,400                   inspection cycle.     inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 12956]]

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Heat shield primary seal replacement..........  10 work-hours x $85 per hour =            $1,940          $2,790
                                                 $850.
Cracked or damaged parts replacement..........  110 work-hours x $85 per hour =           52,992          62,342
                                                 $9,350.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some 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.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

The Boeing Company: Docket No. FAA-2015-0247; Directorate Identifier 
2014-NM-178-AD.

(a) Comments Due Date

    We must receive comments by April 27, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes equipped with Rolls-Royce Trent 800 series engines, 
certificated in any category, as identified in Boeing Service 
Bulletin 777-54A0031, Revision 1, dated May 9, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of heat damage to the strut aft 
fairing heat shield primary seal, as well as heat and wear damage to 
the heat shield insulation blankets. We are issuing this AD to 
detect and correct heat damage to the strut aft fairing lower spar 
web structure (a flammable fluid zone barrier and fire wall) and 
heat shield primary seal, as well as heat and wear damage to the 
heat shield insulation blankets, which could lead to through-cracks 
in the aft fairing web structure and heating of the aft fairing web 
structure, and consequent uncontrolled fire in the aft fairing, fuel 
tank ignition or possible departure of the engine.

(f) Compliance

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

(g) Repetitive Inspections

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 777-54A0031, Revision 1, 
dated May 9, 2014, except as required by paragraph (i) of this AD: 
Do the inspections specified in paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0031, Revision 1, 
dated May 9, 2014. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspections 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 777-54A0031, Revision 1, dated May 9, 2014.
    (1) Do a detailed inspection for cracks and heat damage of the 
aft fairing lower spar upper surface.
    (2) Do a conductivity inspection for heat damage of the aft 
fairing lower spar upper surface.
    (3) Do a detailed inspection for wear of the heat shield primary 
seal.

(h) Optional Terminating Action

    The concurrent accomplishment of the actions specified in 
paragraphs (h)(1) and (h)(2) of this AD terminates the requirements 
of paragraph (g) of this AD.
    (1) Replacement of all heat shield insulation blankets (rub 
strips, heat shield pan casting, Velcro strips, aft fairing web 
drain sump, drain screen, and drain tubes, as applicable) in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 777-54-0030, dated May 27, 2014.
    (2) A one-time detailed inspection for cracks and heat damage of 
the aft fairing lower spar upper surface, conductivity inspection 
for heat damage of the aft fairing lower spar upper surface, and 
detailed inspection for wear of heat shield primary seal, and all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 777-54A0031, Revision 1, dated May 9, 2014, provided all 
applicable

[[Page 12957]]

related investigative and corrective actions are done before further 
flight.

(i) Exception to Service Information Specifications

    Where Boeing Service Bulletin 777-54A0031, Revision 1, dated May 
9, 2014, specifies a compliance time ``After the Original Issue Date 
of this Service Bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (g)(1), (g)(2), (g)(3) and (h)(2) of this AD, if those 
actions were performed before the effective date of this AD using 
Boeing Alert Service Bulletin 777-54A0031, dated June 7, 2013.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (l)(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 the airplane, and the approval must 
specifically refer to this AD.

(l) Related Information

    (1) For more information about this AD, contact Kevin Nguyen, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, 
WA 98057-3356; phone: 425-917-6501; fax: 425-917-6590; email: 
kevin.nguyen@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 February 19, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-05032 Filed 3-11-15; 8:45 am]
 BILLING CODE 4910-13-P