81 FR 44246 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 130 (July 7, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 130 (July 7, 2016)
| Page Range | 44246-44249 | |
| FR Document | 2016-15914 |
[Federal Register Volume 81, Number 130 (Thursday, July 7, 2016)] [Proposed Rules] [Pages 44246-44249] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-15914] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7423; Directorate Identifier 2016-NM-034-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- [[Page 44247]] SUMMARY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 767-200, and -300 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the frame-to-floor-beam joints and frames common to shear ties at certain locations of fuselage structure are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive inspections for cracking of the frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections on the left and right fuselage sides, and corrective action if necessary. We are proposing this AD to detect and correct cracking of the frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections on the left and right fuselage sides, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by August 22, 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 NPRM, 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-2016-7423. 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-2016- 7423; 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: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057 3356; phone: 425-917-6447; fax: 425-917-6590; email: [email protected]. 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-2016-7423; Directorate Identifier 2016-NM-034-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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. An evaluation by the DAH indicates that the frame to floor beam joints and frames common to shear ties at certain locations of fuselage structure are subject to WFD. This condition, if not corrected, could result in cracking of the frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections on the left and right fuselage sides, which could result in reduced structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 767-53A0265, Revision 1, dated March 18, 2016. The service information describes procedures for doing a detailed inspection and a surface high frequency eddy current [[Page 44248]] (HFEC) inspection for cracking of the frame inner chord and web common to the floor beam joint in section 41 and 43 on the left and right sides, a detailed inspection and a surface HFEC inspection for cracking of the section 43 and 46 frames common to the shear ties on the left and right sides, and repair. 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. 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. 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-2016- 7423. The phrase ``corrective actions'' is used in this proposed AD. Corrective actions 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 306 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...................... Up to 350 work-hours $0 Up to $29,750 per Up to $9,103,500 x $85 per hour = inspection cycle. per inspection $29,750 per cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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-2016-7423; Directorate Identifier 2016-NM-034-AD. (a) Comments Due Date We must receive comments by August 22, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 767-200, and - 300 series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53; Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the frame-to-floor-beam joints and frames common to shear ties at certain locations of fuselage structure are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct cracking of the frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections on the left and right fuselage sides, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Corrective Actions Except as provided by paragraph (h) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 767-53A0265, Revision 1, dated March 18, 2016: Do the actions required in paragraphs (g)(1) and (g)(2) of this AD; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0265, Revision 1, dated March 18, 2016. Do all applicable corrective actions before further flight. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable intervals specified [[Page 44249]] in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 767-53A0265, Revision 1, dated March 18, 2016. (1) Do a detailed inspection and a surface high frequency eddy current (HFEC) inspection for cracking of the frame inner chord and web common to the floor beam joint in section 41 and 43 on the left and right sides. (2) Do a detailed inspection and a surface HFEC inspection for cracking of the section 43 and 46 frames common to the shear ties on the left and right sides. (h) Service Information Exception Where Boeing Alert Service Bulletin 767-53A0265, Revision 1, dated March 18, 2016, 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. (i) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 767- 53A0265, dated March 18, 2015. This service information is not incorporated by reference in this AD. (j) 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 (k)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 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. (k) Related Information (1) For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: [email protected]. (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 June 23, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-15914 Filed 7-6-16; 8:45 am] BILLING CODE 4910-13-P
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Regulatory Findings originated by an aviation authority of another person is not required to respond to, nor
country to identify and correct an unsafe shall a person be subject to a penalty for
We determined that this proposed AD condition on an aviation product. The MCAI failure to comply with a collection of
would not have federalism implications describes the unsafe condition as cracks information subject to the requirements of
under Executive Order 13132. This found in the horizontal stabilizer rear attach the Paperwork Reduction Act unless that
proposed AD would not have a structure and the vertical fin rear spar attach collection of information displays a current
substantial direct effect on the States, on structure. We are issuing this AD to prevent valid OMB Control Number. The OMB
the relationship between the national structural failure of the horizontal stabilizer Control Number for this information
Government and the States, or on the and/or the vertical fin rear spar attach collection is 2120–0056. Public reporting for
structure, which could result in damage to this collection of information is estimated to
distribution of power and be approximately 5 minutes per response,
the airplane and loss of control.
responsibilities among the various including the time for reviewing instructions,
levels of government. (f) Actions and Compliance completing and reviewing the collection of
For the reasons discussed above, I Unless already done, do the following information. All responses to this collection
certify this proposed regulation: actions: of information are mandatory. Comments
(1) Is not a ‘‘significant regulatory (1) At whichever of the compliance times concerning the accuracy of this burden and
action’’ under Executive Order 12866, specified in paragraphs (f)(1)(i) through (iii) suggestions for reducing the burden should
(2) Is not a ‘‘significant rule’’ under of this AD that occurs the latest after the be directed to the FAA at: 800 Independence
the DOT Regulatory Policies and effective date of this AD, and repetitively Ave. SW., Washington, DC 20591, Attn:
thereafter every 2,400 hours time-in-service Information Collection Clearance Officer,
Procedures (44 FR 11034, February 26, AES–200.
1979), (TIS), do a visual and non-destructive test
(3) Will not affect intrastate aviation (NDT) inspection of the horizontal stabilizer (h) Related Information
splice plate assembly, part number (P/N)
in Alaska, and Refer to MCAI European Aviation Safety
6032183–1 or P/N 406–5518–32183–100 (as
(4) Will not have a significant Agency (EASA) AD No.: 2016–0101, dated 25
applicable), and the attach structure
economic impact, positive or negative, assembly P/N 6031210–1. Do the inspections
May 25, 2016, and ASI Aviation Service Kit
on a substantial number of small entities SKRA40611–Rev. 2, dated December 3, 2015,
following the Accomplishment Instructions
under the criteria of the Regulatory ASI Service Kit SK406–137, dated December
in ASI Aviation Service Bulletin CAB01–5
3, 2015 (which superseded ASI Aviation
Flexibility Act. Rev 2, dated December 3, 2015.
Service Kit SKRA406–12–Rev. 2, dated
(i) Before accumulating 2,500 hours TIS; or December 3, 2015), and ASI Aviation Service
List of Subjects in 14 CFR Part 39 (ii) Within the next 100 hours TIS; or Kit SKRA406–13–Rev. 2, dated December 3,
Air transportation, Aircraft, Aviation (iii) At the next 600-hour inspection. 2015, for related information. You may
safety, Incorporation by reference, (2) If, during any inspection as required by examine the MCAI on the Internet at http://
Safety. paragraph (f)(1) of this AD, any oversized bolt www.regulations.gov by searching for and
hole or crack is detected on the horizontal locating Docket No. FAA–2016–8161. For
The Proposed Amendment stabilizer splice plate assembly or attach service information related to this AD,
Accordingly, under the authority structure assembly, before further flight, contact ASI Aviation, Aérodrome de Reims
repair or replace the affected part with a Prunay, 51360 Prunay, France; telephone:
delegated to me by the Administrator,
serviceable part following the +33 3 26 48 46 84; fax: +33 3 26 49 18 57;
the FAA proposes to amend 14 CFR part Accomplishment Instructions in ASI
39 as follows: email: contact@ask-aviation.fr; Internet:
Aviation Service Bulletin CAB01–5 Rev 2, http://asi-aviation.fr/page-Accueil.html. You
dated December 3, 2015. After taking the may review this referenced service
PART 39—AIRWORTHINESS necessary corrective action, continue with information at the FAA, Small Airplane
DIRECTIVES the repetitive inspection specified in Directorate, 901 Locust, Kansas City,
paragraph (f)(1) of this AD. Missouri 64106. For information on the
■ 1. The authority citation for part 39
(g) Other FAA AD Provisions availability of this material at the FAA, call
continues to read as follows: (816) 329–4148.
Authority: 49 U.S.C. 106(g), 40113, 44701. The following provisions also apply to this
AD: Issued in Kansas City, Missouri, on June
§ 39.13 [Amended] (1) Alternative Methods of Compliance 28, 2016.
■ 2. The FAA amends § 39.13 by adding (AMOCs): The Manager, Standards Office, Pat Mullen,
FAA, has the authority to approve AMOCs Acting Manager, Small Airplane Directorate,
the following new AD:
for this AD, if requested using the procedures Aircraft Certification Service.
REIMS AVIATION S.A.: Docket No. FAA– found in 14 CFR 39.19. Send information to [FR Doc. 2016–15862 Filed 7–6–16; 8:45 am]
2016–8161; Directorate Identifier 2016– ATTN: Albert Mercado, Aerospace Engineer,
CE–018–AD. FAA, Small Airplane Directorate, 901 Locust, BILLING CODE 4910–13–P
(a) Comments Due Date Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4119; fax: (816) 329–
We must receive comments by August 22, 4090; email: albert.mercado@faa.gov. Before DEPARTMENT OF TRANSPORTATION
2016. using any approved AMOC on any airplane
(b) Affected ADs to which the AMOC applies, notify your Federal Aviation Administration
appropriate principal inspector (PI) in the
None.
FAA Flight Standards District Office (FSDO), 14 CFR Part 39
(c) Applicability or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement [Docket No. FAA–2016–7423; Directorate
This AD applies to REIMS AVIATION S.A. Identifier 2016–NM–034–AD]
F406 airplanes, serial numbers F406–0001 in this AD to obtain corrective actions from
through F406–0098, certificated in any a manufacturer or other source, use these RIN 2120–AA64
actions if they are FAA-approved. Corrective
Lhorne on DSK30JT082PROD with PROPOSALS
category.
actions are considered FAA-approved if they Airworthiness Directives; The Boeing
(d) Subject are approved by the State of Design Authority Company Airplanes
Air Transport Association of America (or their delegated agent). You are required
(ATA) Code 55: Stabilizers. to assure the product is airworthy before it AGENCY: Federal Aviation
is returned to service. Administration (FAA), DOT.
(e) Reason (3) Reporting Requirements: For any ACTION: Notice of proposed rulemaking
This AD was prompted by mandatory reporting requirement in this AD, a federal (NPRM).
continuing airworthiness information (MCAI) agency may not conduct or sponsor, and a
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(HFEC) inspection for cracking of the FAA’s Determination this service information at http://
frame inner chord and web common to www.regulations.gov by searching for
the floor beam joint in section 41 and 43 We are proposing this AD because we and locating Docket No. FAA–2016–
on the left and right sides, a detailed evaluated all the relevant information 7423.
and determined the unsafe condition The phrase ‘‘corrective actions’’ is
inspection and a surface HFEC
described previously is likely to exist or used in this proposed AD. Corrective
inspection for cracking of the section 43
develop in other products of the same actions correct or address any condition
and 46 frames common to the shear ties
type design. found. Corrective actions in an AD
on the left and right sides, and repair.
This service information is reasonably Proposed AD Requirements could include, for example, repairs.
available because the interested parties Costs of Compliance
This proposed AD would require
have access to it through their normal
accomplishing the actions specified in We estimate that this proposed AD
course of business or by the means
the service information described affects 306 airplanes of U.S. registry.
identified in the ADDRESSES section. previously. For information on the We estimate the following costs to
procedures and compliance times, see comply with this proposed AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspections .............................. Up to 350 work-hours × $85 $0 Up to $29,750 per inspection Up to $9,103,500 per inspec-
per hour = $29,750 per in- cycle. tion cycle.
spection cycle.
We have received no definitive data (1) Is not a ‘‘significant regulatory (b) Affected ADs
that would enable us to provide cost action’’ under Executive Order 12866, None.
estimates for the on-condition actions (2) Is not a ‘‘significant rule’’ under (c) Applicability
specified in this proposed AD. the DOT Regulatory Policies and
This AD applies to all The Boeing
Authority for This Rulemaking Procedures (44 FR 11034, February 26,
Company Model 767–200, and –300 series
1979), airplanes, certificated in any category.
Title 49 of the United States Code (3) Will not affect intrastate aviation
specifies the FAA’s authority to issue in Alaska, and (d) Subject
rules on aviation safety. Subtitle I, (4) Will not have a significant Air Transport Association (ATA) of
section 106, describes the authority of economic impact, positive or negative, America Code 53; Fuselage.
the FAA Administrator. Subtitle VII: on a substantial number of small entities (e) Unsafe Condition
Aviation Programs, describes in more under the criteria of the Regulatory
detail the scope of the Agency’s This AD was prompted by an evaluation by
Flexibility Act. the design approval holder (DAH) indicating
authority. that the frame-to-floor-beam joints and
We are issuing this rulemaking under List of Subjects in 14 CFR Part 39 frames common to shear ties at certain
the authority described in Subtitle VII, Air transportation, Aircraft, Aviation locations of fuselage structure are subject to
Part A, Subpart III, Section 44701: safety, Incorporation by reference, widespread fatigue damage (WFD). We are
‘‘General requirements.’’ Under that Safety. issuing this AD to detect and correct cracking
section, Congress charges the FAA with of the frame inner chords and webs common
promoting safe flight of civil aircraft in The Proposed Amendment to the floor beam joint and at frames common
air commerce by prescribing regulations to the shear ties at certain sections on the left
Accordingly, under the authority and right fuselage sides, which could result
for practices, methods, and procedures delegated to me by the Administrator, in reduced structural integrity of the
the Administrator finds necessary for the FAA proposes to amend 14 CFR part airplane.
safety in air commerce. This regulation 39 as follows:
is within the scope of that authority (f) Compliance
because it addresses an unsafe condition PART 39—AIRWORTHINESS Comply with this AD within the
that is likely to exist or develop on DIRECTIVES compliance times specified, unless already
products identified in this rulemaking done.
action. ■ 1. The authority citation for part 39 (g) Inspections and Corrective Actions
Regulatory Findings continues to read as follows: Except as provided by paragraph (h) of this
Authority: 49 U.S.C. 106(g), 40113, 44701. AD, at the applicable time specified in
We determined that this proposed AD paragraph 1.E., ‘‘Compliance,’’ of Boeing
would not have federalism implications § 39.13 [Amended] Alert Service Bulletin 767–53A0265,
under Executive Order 13132. This ■ 2. The FAA amends § 39.13 by adding Revision 1, dated March 18, 2016: Do the
proposed AD would not have a the following new airworthiness
actions required in paragraphs (g)(1) and
substantial direct effect on the States, on (g)(2) of this AD; and do all applicable
Lhorne on DSK30JT082PROD with PROPOSALS
directive (AD): corrective actions; in accordance with the
the relationship between the national
Government and the States, or on the The Boeing Company: Docket No. FAA– Accomplishment Instructions of Boeing Alert
2016–7423; Directorate Identifier 2016– Service Bulletin 767–53A0265, Revision 1,
distribution of power and dated March 18, 2016. Do all applicable
NM–034–AD.
responsibilities among the various corrective actions before further flight.
levels of government. (a) Comments Due Date Repeat the inspections specified in
For the reasons discussed above, I We must receive comments by August 22, paragraphs (g)(1) and (g)(2) of this AD
certify this proposed regulation: 2016. thereafter at the applicable intervals specified
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![Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules 44249
in paragraph 1.E., ‘‘Compliance,’’ of Boeing accordance with the operator’s maintenance and accountability measures would
Alert Service Bulletin 767–53A0265, or inspection program without obtaining support the long-term sustainability of
Revision 1, dated March 18, 2016. approval of an AMOC, provided the RC steps, fishery resources of the U.S. Pacific
(1) Do a detailed inspection and a surface including substeps and identified figures, can Islands.
high frequency eddy current (HFEC) still be done as specified, and the airplane
inspection for cracking of the frame inner can be put back in an airworthy condition. DATES: NMFS must receive comments
chord and web common to the floor beam by July 22, 2016.
joint in section 41 and 43 on the left and (k) Related Information
ADDRESSES: You may submit comments
right sides. (1) For more information about this AD,
(2) Do a detailed inspection and a surface
on this document, identified by NOAA–
contact Wayne Lockett, Aerospace Engineer,
HFEC inspection for cracking of the section Airframe Branch, ANM–120S, FAA, Seattle NMFS–2015–0140, by either of the
43 and 46 frames common to the shear ties ACO, 1601 Lind Avenue SW., Renton, WA following methods:
on the left and right sides. 98057–3356; phone: 425–917–6447; fax: 425– • Electronic Submission: Submit all
917–6590; email: wayne.lockett@faa.gov. electronic public comments via the
(h) Service Information Exception Federal e-Rulemaking Portal. Go to
(2) For service information identified in
Where Boeing Alert Service Bulletin 767– this AD, contact Boeing Commercial http://www.regulations.gov/
53A0265, Revision 1, dated March 18, 2016, Airplanes, Attention: Data & Services #!docketDetail;D=NOAA-NMFS-2015-
specifies a compliance time ‘‘after the Management, P.O. Box 3707, MC 2H–65, 0140, click the ‘‘Comment Now!’’ icon,
original issue date of this service bulletin,’’ Seattle, WA 98124–2207; telephone 206–
this AD requires compliance within the
complete the required fields, and enter
544–5000, extension 1; fax 206–766–5680; or attach your comments.
specified compliance time after the effective Internet https://www.myboeingfleet.com. You
date of this AD. • Mail: Send written comments to
may view this referenced service information
at the FAA, Transport Airplane Directorate,
Michael D. Tosatto, Regional
(i) Credit for Previous Actions Administrator, NMFS Pacific Islands
1601 Lind Avenue SW., Renton, WA. For
This paragraph provides credit for the information on the availability of this Region (PIR), 1845 Wasp Blvd., Bldg.
actions specified in paragraph (g) of this AD, material at the FAA, call 425–227–1221. 176, Honolulu, HI 96818.
if those actions were performed before the Instructions: Comments sent by any
effective date of this AD using Boeing Alert Issued in Renton, Washington, on June 23,
2016.
other method, to any other address or
Service Bulletin 767–53A0265, dated March
18, 2015. This service information is not
individual, or received after the end of
Dorr M. Anderson,
incorporated by reference in this AD. the comment period, may not be
Acting Manager, Transport Airplane considered by NMFS. All comments
(j) Alternative Methods of Compliance Directorate, Aircraft Certification Service.
received are a part of the public record
(AMOCs) [FR Doc. 2016–15914 Filed 7–6–16; 8:45 am] and will generally be posted for public
(1) The Manager, Seattle Aircraft BILLING CODE 4910–13–P viewing on www.regulations.gov
Certification Office (ACO), FAA, has the without change. All personal identifying
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
information (e.g., name, address, etc.),
CFR 39.19. In accordance with 14 CFR 39.19, DEPARTMENT OF COMMERCE confidential business information, or
send your request to your principal inspector otherwise sensitive information
or local Flight Standards District Office, as National Oceanic and Atmospheric submitted voluntarily by the sender will
appropriate. If sending information directly Administration be publicly accessible. NMFS will
to the manager of the ACO, send it to the accept anonymous comments (enter
attention of the person identified in 50 CFR Part 665 ‘‘N/A’’ in the required fields if you wish
paragraph (k)(1) of this AD. Information may to remain anonymous).
be emailed to: 9-ANM-Seattle-ACO-AMOC- [Docket No. 151023986–6557–01]
NMFS prepared environmental
Requests@faa.gov.
(2) Before using any approved AMOC,
RIN 0648–XE284 analyses that describe the potential
notify your appropriate principal inspector, impacts on the human environment that
Pacific Island Pelagic Fisheries; 2016 would result from the proposed catch
or lacking a principal inspector, the manager
of the local flight standards district office/ U.S. Territorial Longline Bigeye Tuna limits and accountability measures. The
certificate holding district office. Catch Limits environmental analyses are available at
(3) An AMOC that provides an acceptable www.regulations.gov. The information
level of safety may be used for any repair,
AGENCY: National Marine Fisheries
Service (NMFS), National Oceanic and contained in the environmental analyses
modification, or alteration required by this is not repeated here.
AD if it is approved by the Boeing Atmospheric Administration (NOAA),
Commercial Airplanes Organization Commerce. FOR FURTHER INFORMATION CONTACT:
Designation Authorization (ODA) that has ACTION: Proposed specifications; request
Jarad Makaiau, NMFS PIRO Sustainable
been authorized by the Manager, Seattle for comments. Fisheries, 808–725–5176.
ACO, to make those findings. To be SUPPLEMENTARY INFORMATION: NMFS
approved, the repair method, modification SUMMARY: NMFS proposes a 2016 limit proposes to specify a catch limit of
deviation, or alteration deviation must meet of 2,000 metric tons (mt) of longline- 2,000 mt of longline-caught bigeye tuna
the certification basis of the airplane, and the
approval must specifically refer to this AD.
caught bigeye tuna for each U.S. Pacific for each U.S. participating territory in
(4) For service information that contains territory (American Samoa, Guam, and 2016. NMFS would also authorize each
steps that are labeled as Required for the Northern Mariana Islands). NMFS U.S. Pacific territory to allocate up to
Compliance (RC), the provisions of would allow each territory to allocate 1,000 mt of its 2,000-mt bigeye tuna
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD up to 1,000 mt each year to U.S. limit to U.S. longline fishing vessels that
apply. longline fishing vessels in a specified are permitted to fish under the Fishery
Lhorne on DSK30JT082PROD with PROPOSALS
(i) The steps labeled as RC, including fishing agreement that meets established Ecosystem Plan for Pelagic Fisheries of
substeps under an RC step and any figures criteria. As an accountability measure, the Western Pacific (FEP). Those vessels
identified in an RC step, must be done to
comply with the AD. An AMOC is required
NMFS would monitor, attribute, and must be identified in a specified fishing
for any deviations to RC steps, including restrict (if necessary) catches of agreement with the applicable territory.
substeps and identified figures. longline-caught bigeye tuna, including The Western Pacific Fishery
(ii) Steps not labeled as RC may be catches made under a specified fishing Management Council recommended
deviated from using accepted methods in agreement. The proposed catch limits these specifications.
VerDate Sep<11>2014 13:03 Jul 06, 2016 Jkt 238001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\07JYP1.SGM 07JYP1](https://thefederalregister.org/doc/81_FR_44376/page/4.svg)
Document Created: 2018-02-08 07:54:42
Document Modified: 2018-02-08 07:54:42
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 22, 2016. | |
| Contact | Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057 3356; phone: 425-917-6447; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 44246 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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