Airworthiness Directives; The Boeing Company Airplanes, 24-27 [2015-32903]

Download as PDF 24 Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules (b) Affected ADs None. Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (c) Applicability This AD applies to Airbus Model A330– 223F and –243F airplanes, certificated in any category; manufacturer serial numbers 1004, 1032, 1051, 1062, 1070, 1092, 1115, 1136, 1148, 1164, 1175, 1180, 1320, 1332, 1344, 1350, 1368, 1380, 1386, 1406, 1414, 1418, and 1428. (i) Reporting Requirement Submit a report (including both positive and negative findings), using the applicable report sheet attached to the applicable service information specified in paragraphs (g)(1) through (g)(4) of this AD; of the inspection required by paragraph (g) of this AD. Submit the report to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SDC32 Technical Data and Documentation Services; fax: (+33) 5 61 93 28 06; email: sb.reporting@airbus.com; at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. (1) For airplanes on which the inspection specified in paragraph (g) of this AD is accomplished on or after the effective date of this AD: Submit the report within 30 days after performing the inspection. (2) For airplanes on which the inspection specified in paragraph (g) of this AD is accomplished before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of missing fasteners in certain locations of the fuselage during production. We are issuing this AD to prevent cracking of the fuselage due to missing, damaged, or incorrectly installed fasteners, which could result in reduced structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. tkelley on DSK3SPTVN1PROD with PROPOSALS (g) Detailed Inspection Within 72 months since first flight of the airplane: Do a detailed inspection of all applicable fuselage zones for missing, damaged, or incorrectly installed fasteners, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1) through (g)(4) of this AD. (1) Airbus Service Bulletin A330–53–3202, dated May 6, 2014. (2) Airbus Service Bulletin A330–53–3212, dated May 6, 2014. (3) Airbus Service Bulletin A330–53–3213, dated May 6, 2014. (4) Airbus Service Bulletin A330–53–3214, dated May 6, 2014. (h) Corrective Actions If any missing, damaged, or incorrectly installed fasteners are found during the detailed inspection required by paragraph (g) of this AD, before further flight, do a detailed inspection for discrepancies (deformation or cracking) of the adjacent fastener rows of the applicable fuselage zones, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1) through (g)(4) of this AD. (1) If no discrepancy is found, before further flight, modify the affected fuselage zone, in accordance with the applicable service information specified in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. (i) Airbus Service Bulletin A330–53–3216, dated May 6, 2014. (ii) Airbus Service Bulletin A330–53–3217, dated May 6, 2014. (iii) Airbus Service Bulletin A330–53– 3218, dated May 6, 2014. (iv) Airbus Service Bulletin A330–53– 3219, dated May 6, 2014. (2) If any discrepancy is found, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation VerDate Sep<11>2014 16:40 Dec 31, 2015 Jkt 238001 (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (4) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0197, dated September 4, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–8136. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this 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 December 21, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–32906 Filed 12–31–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8135; Directorate Identifier 2015–NM–106–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\04JAP1.SGM 04JAP1 Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules Notice of proposed rulemaking (NPRM). ACTION: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 767–200, –300, and –400ER series airplanes. This proposed AD was prompted by multiple reports of un-commanded escape slide inflation. This proposed AD would require modifying the regulator valves of the forward entry door, forward service door, aft entry door, and aft service door, and as applicable, modifying the regulator valves of the mid entry door and mid service door. We are proposing this AD to prevent out-of-tolerance trigger mechanism components (sector and sear) in the regulator valves, which can produce insufficient trigger engagement and reduced pull force values, possibly leading to un-commanded deployment of the slide during normal airplane maintenance or operation, and could result in injury to passengers and crew, damage to equipment, and the slide becoming unusable in an emergency evacuation. SUMMARY: We must receive comments on this proposed AD by February 18, 2016. DATES: 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 98057–3356. 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– 8135. tkelley on DSK3SPTVN1PROD with PROPOSALS ADDRESSES: VerDate Sep<11>2014 16:40 Dec 31, 2015 Jkt 238001 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– 8135; 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: Kimberly DeVoe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6495; fax: 425–917–6590; email: Kimberly.DeVoe@ 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– 2015–8135; Directorate Identifier 2015– NM–106–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 received reports of two incidents of un-commanded escape slide inflation. In both cases, out-of-tolerance trigger mechanism components (sector and sear) were found in the regulator valves which produced insufficient trigger engagement and reduced pull force values. This condition, if not corrected, could result in possible uncommanded deployment of the slide during normal airplane maintenance or operation and could result in injury to passengers and crew, damage to equipment, and the slide becoming unusable in an emergency evacuation. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 25 Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin 767–25–0548, Revision 1, dated April 23, 2015. The service information describes procedures for modifying the regulator valves of the forward entry door, forward service door, aft entry door, aft service door, mid entry door and mid service door. The modification includes replacing the existing trigger mechanism sector and sear of the regulator valve with new trigger mechanism sector and sear. 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 require accomplishing the actions specified in the service information identified previously. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 8135. Explanation of ‘‘RC’’ Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as Required for Compliance (RC) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. For service information that contains steps that are labeled as RC, the following provisions apply: (1) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD, and an AMOC E:\FR\FM\04JAP1.SGM 04JAP1 26 Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules is required for any deviations to RC steps, including substeps and identified figures; and (2) steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Costs of Compliance We estimate that this proposed AD affects 302 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Cost on U.S. operators Labor cost Replacement of trigger mechanism components—forward and aft entry/service doors. Replacement of trigger mechanism components—mid entry/service doors. 15 work-hours × $85 per hour = $1,275 ........ $2,236 $3,511 $1,060,322 8 work-hours × $85 per hour = $680 ............. 1,118 1,798 542,996 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. tkelley on DSK3SPTVN1PROD 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, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. VerDate Sep<11>2014 16:40 Dec 31, 2015 Jkt 238001 Parts cost Cost per product Action List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2015–8135; Directorate Identifier 2015– NM–106–AD. (a) Comments Due Date We must receive comments by February 18, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 767–200, –300, and –400ER series airplanes, certificated in any category, as identified in Boeing Service Bulletin 767–25– 0548, Revision 1, dated April 23, 2015. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Unsafe Condition This AD was prompted by multiple reports of un-commanded escape slide inflation. We are issuing this AD to prevent out-oftolerance trigger mechanism components (sector and sear) in the regulator valves, which can produce insufficient trigger engagement and reduced pull force values, possibly leading to un-commanded deployment of the slide during normal airplane maintenance or operation, and could PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 result in injury to passengers and crew, damage to equipment, and the slide becoming unusable in an emergency evacuation. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement of the Trigger Mechanism Sector and Sear Within 42 months after the effective date of this AD, modify the regulator valves of the forward entry door, forward service door, aft entry door, and aft service door, and as applicable, modify the regulator valves of the mid entry door and mid service door, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767– 25–0548, Revision 1, dated April 23, 2015. (h) Credit for Previous Actions This paragraph provides credit for the modification required by paragraph (g) of this AD, if the modification was performed before the effective date of this AD using Boeing Service Bulletin 767–25–0548, dated November 5, 2014, which is not incorporated by reference in this AD. (i) 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 (j)(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 E:\FR\FM\04JAP1.SGM 04JAP1 Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information (1) For more information about this AD, contact Kimberly DeVoe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6495; fax: 425–917–6590; email: Kimberly.DeVoe@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 98057– 3356. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, WA, on December 21, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–5193; Directorate Identifier 2015–NE–35–AD] RIN 2120–AA64 Airworthiness Directives; Technify Motors GmbH Reciprocating Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). tkelley on DSK3SPTVN1PROD with PROPOSALS AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Technify Motors GmbH (type certificate previously held by Thielert Aircraft VerDate Sep<11>2014 16:40 Dec 31, 2015 Jkt 238001 We must receive comments on this proposed AD by March 4, 2016. DATES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: 202–493–2251. For service information identified in this proposed AD, contact Technify Motors GmbH, Platanenstrasse 14, D– 09356 Sankt Egidien, Germany, phone: +49–37204–696–0; fax: +49–37204– 696–2912; email: support@ continentaldiesel.de. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. ADDRESSES: Examining the AD Docket [FR Doc. 2015–32903 Filed 12–31–15; 8:45 am] SUMMARY: Engines GmbH) TAE 125–02–99 and TAE 125–02–114 reciprocating engines. This proposed AD was prompted by reports of in-flight shutdowns (IFSDs) on TAE 125–02 engines. This proposed AD would require removal of affected fuel feed pumps. We are proposing this AD to prevent failure of the fuel feed pump, which could result in damage to the engine and damage to the airplane. You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 5193; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The 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: Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7770; fax: 781–238– 7199; email: philip.haberlen@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 27 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–2015–5193; Directorate Identifier 2015–NE–35–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 based on 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 with FAA personnel concerning this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2015– 0189, dated September 21, 2015 (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: In-flight shut down occurrences have been reported on aeroplanes equipped with TAE 125–02 engines. The initial results of the investigations showed that a defective fuel feed pump was the probable cause of the engine failure. You may obtain further information by examining the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 5193. Related Service Information Technify Motors GmbH has issued Operation & Maintenance Manual, CD– 135/CD–155, OM–02–02, Issue 4, Revision No. 5, dated September 18, 2015. The service information describes procedures for removing and replacing the fuel feed pump. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of Germany, and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists E:\FR\FM\04JAP1.SGM 04JAP1

Agencies

[Federal Register Volume 81, Number 1 (Monday, January 4, 2016)]
[Proposed Rules]
[Pages 24-27]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-32903]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8135; Directorate Identifier 2015-NM-106-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 25]]


ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 767-200, -300, and -400ER series 
airplanes. This proposed AD was prompted by multiple reports of un-
commanded escape slide inflation. This proposed AD would require 
modifying the regulator valves of the forward entry door, forward 
service door, aft entry door, and aft service door, and as applicable, 
modifying the regulator valves of the mid entry door and mid service 
door. We are proposing this AD to prevent out-of-tolerance trigger 
mechanism components (sector and sear) in the regulator valves, which 
can produce insufficient trigger engagement and reduced pull force 
values, possibly leading to un-commanded deployment of the slide during 
normal airplane maintenance or operation, and could result in injury to 
passengers and crew, damage to equipment, and the slide becoming 
unusable in an emergency evacuation.

DATES: We must receive comments on this proposed AD by February 18, 
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 98057-3356. 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-2015-8135.

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-
8135; 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: Kimberly DeVoe, Aerospace Engineer, 
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; phone: 425-917-6495; fax: 425-917-
6590; email: Kimberly.DeVoe@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-2015-8135; 
Directorate Identifier 2015-NM-106-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 received reports of two incidents of un-commanded escape slide 
inflation. In both cases, out-of-tolerance trigger mechanism components 
(sector and sear) were found in the regulator valves which produced 
insufficient trigger engagement and reduced pull force values. This 
condition, if not corrected, could result in possible un-commanded 
deployment of the slide during normal airplane maintenance or operation 
and could result in injury to passengers and crew, damage to equipment, 
and the slide becoming unusable in an emergency evacuation.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 767-25-0548, Revision 1, dated 
April 23, 2015. The service information describes procedures for 
modifying the regulator valves of the forward entry door, forward 
service door, aft entry door, aft service door, mid entry door and mid 
service door. The modification includes replacing the existing trigger 
mechanism sector and sear of the regulator valve with new trigger 
mechanism sector and sear. 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 require accomplishing the actions specified 
in the service information identified previously. For information on 
the procedures and compliance times, see this service information at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2015-8135.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which steps in the service information are required for 
compliance with an AD. Differentiating these steps from other tasks in 
the service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The steps identified as Required for 
Compliance (RC) in any service information identified previously have a 
direct effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    For service information that contains steps that are labeled as RC, 
the following provisions apply: (1) The steps labeled as RC, including 
substeps under an RC step and any figures identified in an RC step, 
must be done to comply with the AD, and an AMOC

[[Page 26]]

is required for any deviations to RC steps, including substeps and 
identified figures; and (2) steps not labeled as RC may be deviated 
from using accepted methods in accordance with the operator's 
maintenance or inspection program without obtaining approval of an 
AMOC, provided the RC steps, including substeps and identified figures, 
can still be done as specified, and the airplane can be put back in an 
airworthy condition.

Costs of Compliance

    We estimate that this proposed AD affects 302 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replacement of trigger mechanism        15 work-hours x $85 per           $2,236          $3,511      $1,060,322
 components--forward and aft entry/      hour = $1,275.
 service doors.
Replacement of trigger mechanism        8 work-hours x $85 per             1,118           1,798         542,996
 components--mid entry/service doors.    hour = $680.
----------------------------------------------------------------------------------------------------------------

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-2015-8135; Directorate Identifier 
2015-NM-106-AD.

(a) Comments Due Date

    We must receive comments by February 18, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 767-200, -300, and -
400ER series airplanes, certificated in any category, as identified 
in Boeing Service Bulletin 767-25-0548, Revision 1, dated April 23, 
2015.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
furnishings.

(e) Unsafe Condition

    This AD was prompted by multiple reports of un-commanded escape 
slide inflation. We are issuing this AD to prevent out-of-tolerance 
trigger mechanism components (sector and sear) in the regulator 
valves, which can produce insufficient trigger engagement and 
reduced pull force values, possibly leading to un-commanded 
deployment of the slide during normal airplane maintenance or 
operation, and could result in injury to passengers and crew, damage 
to equipment, and the slide becoming unusable in an emergency 
evacuation.

(f) Compliance

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

(g) Replacement of the Trigger Mechanism Sector and Sear

    Within 42 months after the effective date of this AD, modify the 
regulator valves of the forward entry door, forward service door, 
aft entry door, and aft service door, and as applicable, modify the 
regulator valves of the mid entry door and mid service door, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 767-25-0548, Revision 1, dated April 23, 2015.

(h) Credit for Previous Actions

    This paragraph provides credit for the modification required by 
paragraph (g) of this AD, if the modification was performed before 
the effective date of this AD using Boeing Service Bulletin 767-25-
0548, dated November 5, 2014, which is not incorporated by reference 
in this AD.

(i) 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 (j)(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

[[Page 27]]

method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(i)(4)(i) and (i)(4)(ii) apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(j) Related Information

    (1) For more information about this AD, contact Kimberly DeVoe, 
Aerospace Engineer, Cabin Safety and Environmental Systems Branch, 
ANM-150S, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 
425-917-6495; fax: 425-917-6590; email: Kimberly.DeVoe@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 98057-3356. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, WA, on December 21, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-32903 Filed 12-31-15; 8:45 am]
 BILLING CODE 4910-13-P