80 FR 25630 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 86 (May 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 86 (May 5, 2015)
| Page Range | 25630-25633 | |
| FR Document | 2015-10316 |
[Federal Register Volume 80, Number 86 (Tuesday, May 5, 2015)] [Proposed Rules] [Pages 25630-25633] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-10316] [[Page 25630]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1266; Directorate Identifier 2014-NM-151-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-300, 747SR, and 747SP series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage skin lap joints are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive post-modification inspections for cracking of the skin or internal doubler along the edge fastener rows of the modification, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane. DATES: We must receive comments on this proposed AD by June 19, 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 the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA 2015-1266. 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- 1266; 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917- 6428; 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-2015-1266; Directorate Identifier 2014-NM-151-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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global 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, in a condition known as WFD. 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. This proposed AD was prompted by an evaluation by the DAH indicating [[Page 25631]] that certain fuselage skin lap joints are subject to WFD. We are proposing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. This service information describes procedures for inspections for cracks in the skin and doublers along the edge fastener rows of modifications in the fuselage, and repairs. Refer to this service information for information on the procedures and compliance times. This service information is reasonably available at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1266. Or see ADDRESSES for other ways to access this service information. Related Rulemaking AD 2010-10-05, Amendment 39-16284 (75 FR 27424, May 17, 2010) requires, among other things, modification of certain lap joints in fuselage sections 41 and 42. This proposed AD would require repetitive post-modification inspections for cracking of the skin or internal doubler along the edge fastener rows of the modification, and repair if necessary. 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 these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Difference Between this Proposed AD and the Service Information.'' Difference Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, specifies to contact the manufacturer for instructions on how to repair cracking, but this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 50 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Post[dash]modification inspection... 124 work-hours x $85 $0 $10,540 per inspection $527,000 per inspection cycle. per hour = $10,540 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. 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-2014-1266; Directorate Identifier 2014-NM-151-AD. (a) Comments Due Date We must receive comments by June 19, 2015. (b) Affected ADs None. [[Page 25632]] (c) Applicability This AD applies to The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (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 certain fuselage skin lap joints are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Post-Modification Inspections for Airplane Groups 1 Through 3, 7, and 8 For airplanes identified as Groups 1 through 3, 7, and 8 in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014: Except as provided by paragraph (m) of this AD, at the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do internal detailed and surface high frequency eddy current (HFEC) inspections for cracks in the skin and internal doubler along the edge fastener rows of the modification; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In unrepaired areas, repeat the internal detailed and surface HFEC inspections for cracks in the skin or internal doubler along the edge fastener rows of the modification thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (h) Initial Post-Modification Inspections for Airplane Groups 4 Through 6, and 9 Through 11 For airplanes identified as Groups 4 through 6, and 9 through 11 in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, with external doublers installed as specified in Boeing Service Bulletin 747-53-2272: Except as provided by paragraph (m) of this AD, at the applicable time specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do external detailed, low frequency eddy current (LFEC), and HFEC inspections for cracks in the skin and external doubler, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (i) Repetitive Post-Modification Inspections for Airplane Groups 4 Through 6, and 9 through 11 For airplanes with no crack findings during the inspections required by paragraph (h) of this AD: Do the applicable actions required by paragraphs (i)(1) and (i)(2) of this AD. (1) For airplanes with less than 15,000 flight cycles since stringer 6 external doublers were installed as specified in Boeing Service Bulletin 747-53-2272: At the applicable intervals specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in unrepaired areas, repeat the external detailed and LFEC inspections for cracks in the skin, and the external detailed and HFEC inspections for cracks in the external doubler, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (2) For airplanes with 15,000 or more flight cycles since the stringer 6 external doublers were installed as specified in Boeing Service Bulletin 747-53-2272: At the applicable intervals specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, in unrepaired areas, do external detailed and LFEC inspections for cracks in the skin; and do internal and external detailed and HFEC inspections for cracks in the skin and external doubler; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (j) Repetitive Post-Modification Inspections for Airplane Groups 4 Through 6, and 9 Through 11 With External Doublers For airplanes identified as Groups 4 through 6, and 9 through 11 in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, with external doublers installed as specified in Boeing Alert Service Bulletin 747-53A2367: Except as provided by paragraph (m) of this AD, at the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do internal detailed and surface HFEC inspections for cracks in the skin and internal doubler along the edge fastener rows of the modification; and do internal detailed and surface HFEC inspections for cracks in the skin or internal doubler along the edge fastener rows of the modification; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In unrepaired areas, repeat the internal detailed and surface HFEC inspections for cracks in the skin or internal doubler along the edge fastener rows of the modification thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (k) Repetitive Post-Modification Inspections for Airplane Groups 12 and 13 For airplanes identified as Groups 12 and 13 in Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014: Except as provided by paragraph (m) of this AD, at the applicable time specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, do internal detailed and surface HFEC inspections for cracks in the skin and internal doubler along the edge fastener rows of the modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. In unrepaired areas, repeat the internal detailed and surface HFEC inspections for cracks in the skin or internal doubler along the edge fastener rows of the modification thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014. (l) Corrective Actions If any cracking is found during any inspection required by this AD: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (m) Exception to Boeing Alert Service Bulletin 747-53A2367, Revision 5, Dated July 8, 2014 Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2367, Revision 5, dated July 8, 2014, specifies a compliance time ``after the Revision 5 date of this service bulletin,'' this AD requires compliance within the specified compliance time ``after the effective date of this AD.'' (n) 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 (o)(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 required by this AD if it is approved 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. (o) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected]. [[Page 25633]] (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 April 28, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-10316 Filed 5-4-15; 8:45 am] BILLING CODE 4910-13-P
![25630 Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules
DEPARTMENT OF TRANSPORTATION availability of this material at the FAA, occur locally, in small areas or
call 425–227–1221. It is also available structural design details, or globally.
Federal Aviation Administration on the Internet at http:// Global fatigue damage is general
www.regulations.gov by searching for degradation of large areas of structure
14 CFR Part 39 and locating Docket No. FAA 2015– with similar structural details and stress
[Docket No. FAA–2015–1266; Directorate 1266. levels. Multiple-site damage is global
Identifier 2014–NM–151–AD] damage that occurs in a large structural
Examining the AD Docket
element such as a single rivet line of a
RIN 2120–AA64 You may examine the AD docket on lap splice joining two large skin panels.
the Internet at http:// Global damage can also occur in
Airworthiness Directives; The Boeing www.regulations.gov by searching for multiple elements such as adjacent
Company Airplanes and locating Docket No. FAA–2015– frames or stringers. Multiple-site-
AGENCY: Federal Aviation 1266; or in person at the Docket damage and multiple-element-damage
Administration (FAA), DOT. Management Facility between 9 a.m. cracks are typically too small initially to
and 5 p.m., Monday through Friday, be reliably detected with normal
ACTION: Notice of proposed rulemaking
except Federal holidays. The AD docket inspection methods. Without
(NPRM). contains this proposed AD, the intervention, these cracks will grow,
SUMMARY: We propose to adopt a new regulatory evaluation, any comments and eventually compromise the
airworthiness directive (AD) for certain received, and other information. The structural integrity of the airplane, in a
The Boeing Company Model 747–100, street address for the Docket Office condition known as WFD. As an
747–100B, 747–100B SUD, 747–200B, (phone: 800–647–5527) is in the airplane ages, WFD will likely occur,
747–300, 747SR, and 747SP series ADDRESSES section. Comments will be and will certainly occur if the airplane
airplanes. This proposed AD was available in the AD docket shortly after is operated long enough without any
prompted by an evaluation by the receipt. intervention.
design approval holder (DAH) FOR FURTHER INFORMATION CONTACT: The FAA’s WFD final rule (75 FR
indicating that certain fuselage skin lap Nathan Weigand, Aerospace Engineer, 69746, November 15, 2010) became
joints are subject to widespread fatigue Airframe Branch, ANM–120S, FAA, effective on January 14, 2011. The WFD
damage (WFD). This proposed AD Seattle Aircraft Certification Office, rule requires certain actions to prevent
would require repetitive post- 1601 Lind Avenue SW., Renton, structural failure due to WFD
modification inspections for cracking of Washington 98057–3356; phone: 425– throughout the operational life of
the skin or internal doubler along the 917–6428; fax: 425–917–6590; email: certain existing transport category
edge fastener rows of the modification, nathan.p.weigand@faa.gov. airplanes and all of these airplanes that
and repair if necessary. We are SUPPLEMENTARY INFORMATION: will be certificated in the future. For
proposing this AD to detect and correct existing and future airplanes subject to
Comments Invited the WFD rule, the rule requires that
fatigue cracking in certain fuselage skin
lap joints, which could result in rapid We invite you to send any written DAHs establish a limit of validity (LOV)
depressurization of the airplane. relevant data, views, or arguments about of the engineering data that support the
this proposal. Send your comments to structural maintenance program.
DATES: We must receive comments on
an address listed under the ADDRESSES Operators affected by the WFD rule may
this proposed AD by June 19, 2015. section. Include ‘‘Docket No. FAA– not fly an airplane beyond its LOV,
ADDRESSES: You may send comments, 2015–1266; Directorate Identifier 2014– unless an extended LOV is approved.
using the procedures found in 14 CFR NM–151–AD’’ at the beginning of your The WFD rule (75 FR 69746,
11.43 and 11.45, by any of the following comments. We specifically invite November 15, 2010) does not require
methods: comments on the overall regulatory, identifying and developing maintenance
• Federal eRulemaking Portal: Go to economic, environmental, and energy actions if the DAHs can show that such
http://www.regulations.gov. Follow the aspects of this proposed AD. We will actions are not necessary to prevent
instructions for submitting comments. consider all comments received by the WFD before the airplane reaches the
• Fax: 202–493–2251. closing date and may amend this LOV. Many LOVs, however, do depend
• Mail: U.S. Department of proposed AD because of those on accomplishment of future
Transportation, Docket Operations, M– comments. maintenance actions. As stated in the
30, West Building Ground Floor, Room We will post all comments we WFD rule, any maintenance actions
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http:// necessary to reach the LOV will be
Washington, DC 20590. www.regulations.gov, including any mandated by airworthiness directives
• Hand Delivery: Deliver to Mail personal information you provide. We through separate rulemaking actions.
address above between 9 a.m. and 5 will also post a report summarizing each In the context of WFD, this action is
p.m., Monday through Friday, except substantive verbal contact we receive necessary to enable DAHs to propose
Federal holidays. about this proposed AD. LOVs that allow operators the longest
For service information identified in operational lives for their airplanes, and
this proposed AD, contact Boeing Discussion still ensure that WFD will not occur.
Commercial Airplanes, Attention: Data Structural fatigue damage is This approach allows for an
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
& Services Management, P. O. Box 3707, progressive. It begins as minute cracks, implementation strategy that provides
MC 2H–65, Seattle, WA 98124–2207; and those cracks grow under the action flexibility to DAHs in determining the
telephone 206–544–5000, extension 1; of repeated stresses. This can happen timing of service information
fax 206–766–5680; Internet https:// because of normal operational development (with FAA approval),
www.myboeingfleet.com. You may view conditions and design attributes, or while providing operators with certainty
this referenced service information at because of isolated situations or regarding the LOV applicable to their
the FAA, Transport Airplane incidents such as material defects, poor airplanes.
Directorate, 1601 Lind Avenue SW., fabrication quality, or corrosion pits, This proposed AD was prompted by
Renton, WA. For information on the dings, or scratches. Fatigue damage can an evaluation by the DAH indicating
VerDate Sep<11>2014 17:25 May 04, 2015 Jkt 235001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\05MYP1.SGM 05MYP1](https://thefederalregister.org/doc/80_FR_25716/page/1.svg)
![Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules 25631
that certain fuselage skin lap joints are Related Rulemaking Difference Between This Proposed AD
subject to WFD. We are proposing this AD 2010–10–05, Amendment 39– and the Service Information
AD to detect and correct fatigue 16284 (75 FR 27424, May 17, 2010)
cracking in certain fuselage skin lap Boeing Alert Service Bulletin 747–
requires, among other things,
joints, which could result in rapid 53A2367, Revision 5, dated July 8, 2014,
modification of certain lap joints in
depressurization of the airplane. fuselage sections 41 and 42. This specifies to contact the manufacturer for
proposed AD would require repetitive instructions on how to repair cracking,
Related Service Information Under 1 but this proposed AD would require
post-modification inspections for
CFR Part 51 cracking of the skin or internal doubler repairing those conditions in one of the
along the edge fastener rows of the following ways:
We reviewed Boeing Alert Service
Bulletin 747–53A2367, Revision 5, modification, and repair if necessary. • In accordance with a method that
dated July 8, 2014. This service FAA’s Determination we approve; or
information describes procedures for We are proposing this AD because we • Using data that meet the
inspections for cracks in the skin and evaluated all the relevant information certification basis of the airplane, and
doublers along the edge fastener rows of and determined the unsafe condition that have been approved by the Boeing
modifications in the fuselage, and described previously is likely to exist or Commercial Airplanes Organization
repairs. Refer to this service information develop in other products of these same Designation Authorization (ODA) whom
for information on the procedures and type designs. we have authorized to make those
compliance times. This service findings.
Proposed AD Requirements
information is reasonably available at
This proposed AD would require Costs of Compliance
http://www.regulations.gov by searching
for and locating Docket No. FAA–2015– accomplishing the actions specified in We estimate that this proposed AD
1266. Or see ADDRESSES for other ways the service information described
affects 50 airplanes of U.S. registry.
to access this service information. previously, except as discussed under
‘‘Difference Between this Proposed AD We estimate the following costs to
and the Service Information.’’ comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Post-modification inspection 124 work-hours × $85 per $0 $10,540 per inspection cycle $527,000 per inspection cycle.
hour = $10,540 per in-
spection cycle..
We have received no definitive data is within the scope of that authority List of Subjects in 14 CFR Part 39
that would enable us to provide cost because it addresses an unsafe condition
estimates for the on-condition actions that is likely to exist or develop on Air transportation, Aircraft, Aviation
specified in this proposed AD. products identified in this rulemaking safety, Incorporation by reference,
According to the manufacturer, some action. Safety.
of the costs of this proposed AD may be The Proposed Amendment
Regulatory Findings
covered under warranty, thereby
reducing the cost impact on affected We determined that this proposed AD Accordingly, under the authority
individuals. We do not control warranty would not have federalism implications delegated to me by the Administrator,
coverage for affected individuals. As a under Executive Order 13132. This the FAA proposes to amend 14 CFR part
result, we have included all costs in our proposed AD would not have a 39 as follows:
cost estimate. substantial direct effect on the States, on
PART 39—AIRWORTHINESS
the relationship between the national
Authority for This Rulemaking DIRECTIVES
Government and the States, or on the
Title 49 of the United States Code distribution of power and
■ 1. The authority citation for part 39
specifies the FAA’s authority to issue responsibilities among the various
continues to read as follows:
rules on aviation safety. Subtitle I, levels of government.
section 106, describes the authority of For the reasons discussed above, I Authority: 49 U.S.C. 106(g), 40113, 44701.
the FAA Administrator. Subtitle VII: certify this proposed regulation: § 39.13 [Amended]
Aviation Programs, describes in more (1) Is not a ‘‘significant regulatory
detail the scope of the Agency’s action’’ under Executive Order 12866, ■ 2. The FAA amends § 39.13 by adding
authority. (2) Is not a ‘‘significant rule’’ under the following new airworthiness
We are issuing this rulemaking under the DOT Regulatory Policies and directive (AD):
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
the authority described in Subtitle VII, Procedures (44 FR 11034, February 26, The Boeing Company: Docket No. FAA–
Part A, Subpart III, Section 44701: 1979), 2014–1266; Directorate Identifier 2014–
‘‘General requirements.’’ Under that (3) Will not affect intrastate aviation NM–151–AD.
section, Congress charges the FAA with in Alaska, and (a) Comments Due Date
promoting safe flight of civil aircraft in (4) Will not have a significant
We must receive comments by June 19,
air commerce by prescribing regulations economic impact, positive or negative, 2015.
for practices, methods, and procedures on a substantial number of small entities
the Administrator finds necessary for under the criteria of the Regulatory (b) Affected ADs
safety in air commerce. This regulation Flexibility Act. None.
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![Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules 25633
(2) For service information identified in information on the rulemaking process, Issued: April 23, 2015.
this AD, contact Boeing Commercial see the Comment Procedures Section of Kimberly D. Bose,
Airplanes, Attention: Data & Services this document. Secretary.
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206– FOR FURTHER INFORMATION CONTACT: [FR Doc. 2015–10310 Filed 5–4–15; 8:45 am]
544–5000, extension 1; fax 206–766–5680; Christy Walsh, Office of the General BILLING CODE 6717–01–P
Internet https://www.myboeingfleet.com. You Counsel, Federal Energy Regulatory
may view this referenced service information Commission, 888 First Street NE.,
at the Washington, DC 20426, 202–502–6523, DEPARTMENT OF LABOR
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
Christy.Walsh@ferc.gov.
Employment and Training
information on the availability of this SUPPLEMENTARY INFORMATION: Take Administration
material at the FAA, call 425–227–1221. notice that the Commission staff is
Issued in Renton, Washington, on April 28, issuing a memorandum seeking public 20 CFR Part 655
2015. comment on whether the existing
Michael Kaszycki, regulations concerning the Uniform RIN 1205–AB70
Acting Manager, Transport Airplane Systems of Accounts prescribed for oil Temporary Agricultural Employment of
Directorate, Aircraft Certification Service. pipeline companies and hydropower H–2A Foreign Workers in the Herding
[FR Doc. 2015–10316 Filed 5–4–15; 8:45 am] prefiling requirements, and a or Production of Livestock on the
BILLING CODE 4910–13–P requirement imposed in 2001 that Open Range in the United States;
Western public and non-public utilities Extension of Comment Period
offer available real-time electric energy
DEPARTMENT OF ENERGY capacity into the markets and post the AGENCY: Employment and Training
availability on their Web sites and the Administration, Labor.
Federal Energy Regulatory WSPP Web site, warrant a formal public ACTION: Proposed rule; extension of
Commission review. The memorandum is being comment period.
issued pursuant to the November 8,
18 CFR Part 352 2011 Plan for Retrospective Analysis of SUMMARY: The Department of Labor
Existing Rules prepared in response to (Department) issued a proposed rule in
[Docket No. AD12–6–001] the Federal Register of April 15, 2015
Executive Order 13579, which requested
independent regulatory agencies issue [FR Doc. 2015–08505], concerning
Retrospective Analysis of Existing
plans for periodic retrospective analysis proposed amendments to its regulations
Rules
of their existing regulations. governing certification of the
AGENCY: Federal Energy Regulatory employment of nonimmigrant workers
The Staff Memorandum is being
Commission, DOE. in temporary or seasonal agricultural
placed in the record in the above-
ACTION: Notice of staff memorandum. employment under the H–2A program
referenced administrative docket. The
to codify certain procedures for
Staff Memorandum will also be
SUMMARY: In this document, the employers seeking to hire foreign
available on the Commission’s Web site
Commission is seeking public comment temporary agricultural workers for job
at http://www.ferc.gov.
on whether the existing regulations opportunities in sheepherding, goat
concerning the Uniform Systems of Comments on the Staff Memorandum herding and production of livestock on
Accounts prescribed for oil pipeline should be filed within 30 days of the the open range. This notice extends the
companies and hydropower prefiling issuance of this document. The comment period for 15 days, from May
requirements, and a requirement Commission encourages electronic 15 to June 1, 2015. Multiple commenters
imposed in 2001 that Western public submission of comments in lieu of requested additional time to develop
and non-public utilities offer available paper using the ‘‘eFiling’’ link at http:// their comments concerning the
real-time electric energy capacity into www.ferc.gov. Persons unable to file proposed rulemaking. The Department
the markets and post the availability on electronically should submit an original is therefore extending the comment
their Web sites and the WSPP Web site, of the comment to the Federal Energy period in order to give all interested
warrant a formal public review. Regulatory Commission, 888 First Street persons the opportunity to comment
DATES: Comments are due by May 26, NE., Washington, DC 20426. fully.
2015. All filings in this docket are DATES: The comment period for the
ADDRESSES: Comments, identified by accessible on-line at http:// proposed rule published on April 15,
docket number, may be filed in the www.ferc.gov, using the ‘‘eLibrary’’ link. 2015 (80 FR 20300) is extended.
following ways: There is an ‘‘eSubscription’’ link on the Interested persons are invited to submit
• Electronic Filing through http:// Web site that enables subscribers to written comments on the proposed rule,
www.ferc.gov. Documents created receive email notification when a identified by RIN 1205–AB70, on or
electronically using word processing document is added to a subscribed before June 1, 2015
software should be filed in native docket. For assistance with any FERC ADDRESSES: You may submit comments,
applications or print-to-PDF format and Online service, please email identified by Regulatory Information
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
not in a scanned format. FERCOnlineSupport@ferc.gov, or call Number (RIN) 1205–AB70, by any one
• Mail/Hand Delivery: Those unable (866) 208–3676 (toll free). For TTY, call of the following methods:
to file electronically may mail or hand- (202) 502–8659. • Federal e-Rulemaking Portal
deliver comments to: Federal Energy Questions regarding this document www.regulations.gov. Follow the Web
Regulatory Commission, Secretary of the should be directed to: Christy Walsh, site instructions for submitting
Commission, 888 First Street NE., Office of the General Counsel, Federal comments.
Washington, DC 20426. Energy Regulatory Commission, 888 • Mail or Hand Delivery/Courier:
Instructions: For detailed instructions First Street NE., Washington, DC 20426, Please submit all written comments
on submitting comments and additional 202–502–6523, Christy.Walsh@ferc.gov. (including disk and CD–ROM
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Document Created: 2015-12-16 07:53:55
Document Modified: 2015-12-16 07:53:55
| 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 June 19, 2015. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917- 6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 25630 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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