83 FR 5738 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 28 (February 9, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 28 (February 9, 2018)
| Page Range | 5738-5740 | |
| FR Document | 2018-02197 |
[Federal Register Volume 83, Number 28 (Friday, February 9, 2018)] [Proposed Rules] [Pages 5738-5740] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-02197] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Proposed Rules [[Page 5738]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0073; Product Identifier 2017-NM-100-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 767-300 and -300F series airplanes. This proposed AD was prompted by reports of fatigue cracking in the lower outboard wing skin at the farthest outboard fastener of the inboard segment of a certain stringer. This proposed AD would require repetitive high frequency eddy current (HFEC) inspections for cracking of the lower outboard wing skin at the inboard segment of a certain stringer, and repair if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by March 26, 2018. 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 Aviation Partners Boeing, 2811 S. 102nd Street, Suite 200, Seattle, WA 98168; telephone 206-762-1171; internet https://www.aviationpartnersboeing.com. You may view this referenced service information at the FAA, Transport Standards Branch, 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-2018-0073. 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-2018- 0073; 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 NPRM, 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: Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW, Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: allen.rauschendorfer@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-2018-0073; Product Identifier 2017-NM-100-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 NPRM. Discussion We have received reports of fatigue cracking in the lower outboard wing skin at the farthest outboard fastener of the inboard segment of stringer L-9.5 on Model 767-300 airplanes with Aviation Partners Boeing winglets installed. The cracks were found at the fastener holes common to the stringer on the left- and right-hand wings. Investigation revealed that these were fatigue cracks related to Aviation Partners Boeing supplemental type certificate (STC) ST01920SE winglet retrofit kit installations. If not corrected, these cracks could extend to adjacent structure and could lead to reduced load carrying capability in the lower skin. These conditions, if not corrected, could result in failure and subsequent separation of the wing and winglet, and consequent reduced controllability of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Aviation Partners Boeing (APB) Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017. The service information describes procedures for an HFEC inspection for cracking of the lower outboard wing skin at the inboard segment of stringer L-9.5, and on- condition actions that include repetitive HFEC inspections; a preventative modification (repair) that includes installing new stringers; repetitive post-modification (repair) HFEC inspections for cracking; 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, except as discussed under ``Difference Between this Proposed Rule and the Service Information.'' [[Page 5739]] Difference Between Proposed Rule and Service Information Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, specifies to contact the manufacturer for instructions on how to repair certain conditions, 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. Compliance Times The initial compliance time is the later of: 1,500 flight cycles or 7,500 flight cycles after winglet installation, whichever occurs first; or 18 months after the effective date of the AD. The repetitive compliance times vary depending on inspection findings. The shortest repetitive interval is 1,500 flight cycles or 7,500 flight hours, whichever occurs first. The longest repetitive interval is 6,000 flight cycles or 18,000 flight hours, whichever occurs first. Costs of Compliance We estimate that this proposed AD affects 140 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs--Required Actions ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- HFEC Inspections................ 1 work-hour x $85 $0 $85, per inspection $11,900, per per hour = $255, cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- Estimated Costs--On-Condition Actions ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Preventative Modification (Repair)............ 50 work-hours x $85 per hour = $0 $4,250 $4,250. Post-modification (repair) Inspections........ 1 work-hour x $85 per hour = 0 85 $255. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for on-condition repairs that might be necessary as a result of the post-modification (repair) inspections 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 available 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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-2018-0073; Product Identifier 2017-NM-100-AD. (a) Comments Due Date We must receive comments by March 26, 2018. (b) Affected ADs None. [[Page 5740]] (c) Applicability This AD applies to The Boeing Company Model 767-300 and -300F series airplanes, certificated in any category, with Aviation Partners Boeing winglets installed; as identified in Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking in the lower outboard wing skin at the farthest outboard fastener of the inboard segment of stringer L-9.5 on airplanes with winglets installed per Supplemental Type Certificate ST01920SE. We are issuing this AD to prevent fatigue cracking in the lower outboard wing skin, which could result in failure and subsequent separation of the wing and winglet and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections, Preventative Modification (Repair), Repetitive Post-Modification (Repair) Inspections, and Repair At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017, except as required by paragraph (h) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking of the lower outboard wing skin at the inboard segment of stringer L-9.5, in accordance with Part 1 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017. (1) For airplanes on which ``Condition 1'' is found, as defined in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, during any inspection required by paragraph (g) or (g)(1)(i) of this AD: Do the actions required by paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Repeat the inspection specified in paragraph (g) of this AD thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017. (ii) Do the actions required by paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD: (A) Before further flight, do the preventative modification in accordance with Part 2 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017. (B) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017, do an HFEC inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 013, Revision 1, dated April 11, 2017; and repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017. (2) For airplanes on which ``Condition 2'' is found as defined in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, during any inspection required by paragraph (g) or (g)(1)(i) of this AD: Do the actions required by paragraph (g)(2)(i) and (g)(2)(ii) of this AD. (i) Before further flight, repair in accordance with Part 2 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017. (ii) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017, do an HFEC inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 013, Revision 1, dated April 11, 2017; and repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(ii)(B) or (g)(2)(ii) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Although Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, specifies to contact Boeing for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair as specified in this paragraph. (h) Exception to Service Information Specifications Where paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, specifies a compliance time of ``after the initial 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 For Group 2 airplanes: This paragraph provides credit for the actions specified in Part 1 and Part 2 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 013, Revision 1, dated April 11, 2017, that are required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Aviation Partners Boeing Service Bulletin AP767-57-013, dated November 30, 2016. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO Branch, 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 certification office, send it to the attention of the person identified in paragraph (k)(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, 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 Branch, 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) Except as required by paragraph (g)(3) of this AD: 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. If a step or substep is labeled ``RC Exempt,'' then the RC requirement is removed from that step or substep. 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 Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW, Renton, WA 98057-3356; phone: 425- 917-6450; fax: 425-917-6590; email: allen.rauschendorfer@faa.gov. (2) For service information identified in this AD, contact Aviation Partners Boeing, 2811 S. 102nd Street, Suite 200, Seattle, WA 98168; telephone 206-762-1171; internet https://www.aviationpartnersboeing.com. You may view this referenced service information at the FAA, Transport Standards Branch, 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 January 25, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-02197 Filed 2-8-18; 8:45 am] BILLING CODE 4910-13-P
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Proposed Rules Federal Register
Vol. 83, No. 28
Friday, February 9, 2018
This section of the FEDERAL REGISTER Partners Boeing, 2811 S. 102nd Street, Discussion
contains notices to the public of the proposed Suite 200, Seattle, WA 98168; telephone
issuance of rules and regulations. The 206–762–1171; internet https:// We have received reports of fatigue
purpose of these notices is to give interested www.aviationpartnersboeing.com. You cracking in the lower outboard wing
persons an opportunity to participate in the skin at the farthest outboard fastener of
may view this referenced service
rule making prior to the adoption of the final the inboard segment of stringer L–9.5 on
rules.
information at the FAA, Transport
Standards Branch, 1601 Lind Avenue Model 767–300 airplanes with Aviation
SW, Renton, WA. For information on Partners Boeing winglets installed. The
DEPARTMENT OF TRANSPORTATION the availability of this material at the cracks were found at the fastener holes
FAA, call 425–227–1221. It is also common to the stringer on the left- and
Federal Aviation Administration available on the internet at http:// right-hand wings. Investigation revealed
www.regulations.gov by searching for that these were fatigue cracks related to
14 CFR Part 39 and locating Docket No. FAA–2018– Aviation Partners Boeing supplemental
0073. type certificate (STC) ST01920SE
[Docket No. FAA–2018–0073; Product winglet retrofit kit installations. If not
Identifier 2017–NM–100–AD] Examining the AD Docket corrected, these cracks could extend to
RIN 2120–AA64 You may examine the AD docket on adjacent structure and could lead to
the internet at http:// reduced load carrying capability in the
Airworthiness Directives; The Boeing www.regulations.gov by searching for lower skin. These conditions, if not
Company Airplanes and locating Docket No. FAA–2018– corrected, could result in failure and
AGENCY: Federal Aviation 0073; or in person at the Docket subsequent separation of the wing and
Administration (FAA), DOT. Management Facility between 9 a.m. winglet, and consequent reduced
ACTION: Notice of proposed rulemaking
and 5 p.m., Monday through Friday, controllability of the airplane.
(NPRM). except Federal holidays. The AD docket
contains this NPRM, the regulatory Related Service Information Under 1
SUMMARY: We propose to adopt a new evaluation, any comments received, and CFR Part 51
airworthiness directive (AD) for certain other information. The street address for We reviewed Aviation Partners
The Boeing Company Model 767–300 the Docket Office (phone: 800–647– Boeing (APB) Service Bulletin AP767–
and –300F series airplanes. This 5527) is in the ADDRESSES section. 57–013, Revision 1, dated April 11,
proposed AD was prompted by reports Comments will be available in the AD 2017. The service information describes
of fatigue cracking in the lower outboard docket shortly after receipt. procedures for an HFEC inspection for
wing skin at the farthest outboard FOR FURTHER INFORMATION CONTACT: cracking of the lower outboard wing
fastener of the inboard segment of a Allen Rauschendorfer, Aerospace skin at the inboard segment of stringer
certain stringer. This proposed AD Engineer, Airframe Section, FAA, L–9.5, and on-condition actions that
would require repetitive high frequency Seattle ACO Branch, 1601 Lind Avenue include repetitive HFEC inspections; a
eddy current (HFEC) inspections for SW, Renton, WA 98057–3356; phone: preventative modification (repair) that
cracking of the lower outboard wing 425–917–6450; fax: 425–917–6590; includes installing new stringers;
skin at the inboard segment of a certain email: allen.rauschendorfer@faa.gov. repetitive post-modification (repair)
stringer, and repair if necessary. We are SUPPLEMENTARY INFORMATION: HFEC inspections for cracking; and
proposing this AD to address the unsafe repair. This service information is
condition on these products. Comments Invited
reasonably available because the
DATES: We must receive comments on We invite you to send any written interested parties have access to it
this proposed AD by March 26, 2018. relevant data, views, or arguments about through their normal course of business
ADDRESSES: You may send comments, this proposal. Send your comments to or by the means identified in the
using the procedures found in 14 CFR an address listed under the ADDRESSES ADDRESSES section.
11.43 and 11.45, by any of the following section. Include ‘‘Docket No. FAA–
methods: 2018–0073; Product Identifier 2017– FAA’s Determination
• Federal eRulemaking Portal: Go to NM–100–AD’’ at the beginning of your
comments. We specifically invite We are proposing this AD because we
http://www.regulations.gov. Follow the
comments on the overall regulatory, evaluated all the relevant information
instructions for submitting comments.
and determined the unsafe condition
• Fax: 202–493–2251. economic, environmental, and energy
• Mail: U.S. Department of aspects of this NPRM. We will consider described previously is likely to exist or
Transportation, Docket Operations, M– all comments received by the closing develop in other products of the same
30, West Building Ground Floor, Room date and may amend this NPRM type design.
sradovich on DSK3GMQ082PROD with PROPOSALS
W12–140, 1200 New Jersey Avenue SE, because of those comments. Proposed AD Requirements
Washington, DC 20590. We will post all comments we
• Hand Delivery: Deliver to Mail receive, without change, to http:// This proposed AD would require
address above between 9 a.m. and 5 www.regulations.gov, including any accomplishing the actions specified in
p.m., Monday through Friday, except personal information you provide. We the service information described
Federal holidays. will also post a report summarizing each previously, except as discussed under
For service information identified in substantive verbal contact we receive ‘‘Difference Between this Proposed Rule
this proposed AD, contact Aviation about this NPRM. and the Service Information.’’
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![Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Proposed Rules 5739
Difference Between Proposed Rule and • Using data that meet the The repetitive compliance times vary
Service Information certification basis of the airplane, and depending on inspection findings. The
that have been approved by the Boeing shortest repetitive interval is 1,500 flight
Aviation Partners Boeing Service Commercial Airplanes Organization cycles or 7,500 flight hours, whichever
Bulletin AP767–57–013, Revision 1, Designation Authorization (ODA) whom occurs first. The longest repetitive
dated April 11, 2017, specifies to we have authorized to make those interval is 6,000 flight cycles or 18,000
contact the manufacturer for findings. flight hours, whichever occurs first.
instructions on how to repair certain
Compliance Times Costs of Compliance
conditions, but this proposed AD would
require repairing those conditions in The initial compliance time is the
later of: 1,500 flight cycles or 7,500 We estimate that this proposed AD
one of the following ways:
flight cycles after winglet installation, affects 140 airplanes of U.S. registry. We
• In accordance with a method that whichever occurs first; or 18 months estimate the following costs to comply
we approve; or after the effective date of the AD. with this proposed AD:
ESTIMATED COSTS—REQUIRED ACTIONS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
HFEC Inspections .................. 1 work-hour × $85 per hour = $0 $85, per inspection cycle ....... $11,900, per inspection cycle.
$255, per inspection cycle.
ESTIMATED COSTS—ON-CONDITION ACTIONS
Cost per
Action Labor cost Parts cost product
Preventative Modification (Repair) ............................... 50 work-hours × $85 per hour = $4,250 ...................... $0 $4,250
Post-modification (repair) Inspections .......................... 1 work-hour × $85 per hour = $255 ............................. 0 85
We have received no definitive data products identified in this rulemaking (4) Will not have a significant
that would enable us to provide cost action. economic impact, positive or negative,
estimates for on-condition repairs that This proposed AD is issued in on a substantial number of small entities
might be necessary as a result of the accordance with authority delegated by under the criteria of the Regulatory
post-modification (repair) inspections the Executive Director, Aircraft Flexibility Act.
specified in this proposed AD. Certification Service, as authorized by List of Subjects in 14 CFR Part 39
According to the manufacturer, some FAA Order 8000.51C. In accordance
of the costs of this proposed AD may be with that order, issuance of ADs is Air transportation, Aircraft, Aviation
covered under warranty, thereby normally a function of the Compliance safety, Incorporation by reference,
reducing the cost impact on affected and Airworthiness Division, but during Safety.
individuals. We do not control warranty this transition period, the Executive
The Proposed Amendment
coverage for affected individuals. As a Director has delegated the authority to
result, we have included all available issue ADs applicable to transport Accordingly, under the authority
costs in our cost estimate. category airplanes to the Director of the delegated to me by the Administrator,
System Oversight Division. the FAA proposes to amend 14 CFR part
Authority for This Rulemaking
Regulatory Findings 39 as follows:
Title 49 of the United States Code
specifies the FAA’s authority to issue We determined that this proposed AD PART 39—AIRWORTHINESS
rules on aviation safety. Subtitle I, would not have federalism implications DIRECTIVES
section 106, describes the authority of under Executive Order 13132. This
the FAA Administrator. Subtitle VII: proposed AD would not have a ■ 1. The authority citation for part 39
Aviation Programs, describes in more substantial direct effect on the States, on continues to read as follows:
detail the scope of the Agency’s the relationship between the national Authority: 49 U.S.C. 106(g), 40113, 44701.
authority. Government and the States, or on the
distribution of power and § 39.13 [Amended]
We are issuing this rulemaking under responsibilities among the various
the authority described in Subtitle VII, ■ 2. The FAA amends § 39.13 by adding
levels of government.
Part A, Subpart III, Section 44701: the following new airworthiness
For the reasons discussed above, I directive (AD):
‘‘General requirements.’’ Under that
certify this proposed regulation:
section, Congress charges the FAA with
sradovich on DSK3GMQ082PROD with PROPOSALS
The Boeing Company: Docket No. FAA–
promoting safe flight of civil aircraft in (1) Is not a ‘‘significant regulatory 2018–0073; Product Identifier 2017–
air commerce by prescribing regulations action’’ under Executive Order 12866, NM–100–AD.
for practices, methods, and procedures (2) Is not a ‘‘significant rule’’ under
(a) Comments Due Date
the Administrator finds necessary for the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, We must receive comments by March 26,
safety in air commerce. This regulation 2018.
is within the scope of that authority 1979),
because it addresses an unsafe condition (3) Will not affect intrastate aviation (b) Affected ADs
that is likely to exist or develop on in Alaska, and None.
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(c) Applicability Instructions of Aviation Partners Boeing found in 14 CFR 39.19. In accordance with
This AD applies to The Boeing Company Service Bulletin AP767–57–013, Revision 1, 14 CFR 39.19, send your request to your
Model 767–300 and –300F series airplanes, dated April 11, 2017; and repeat the principal inspector or local Flight Standards
certificated in any category, with Aviation inspection thereafter at the applicable times District Office, as appropriate. If sending
Partners Boeing winglets installed; as specified in paragraph 1.E., ‘‘Compliance,’’ of information directly to the manager of the
identified in Aviation Partners Boeing Aviation Partners Boeing Service Bulletin certification office, send it to the attention of
Service Bulletin AP767–57–013, Revision 1, AP767–57–013, Revision 1, dated April 11, the person identified in paragraph (k)(1) of
dated April 11, 2017. 2017. this AD. Information may be emailed to: 9-
(2) For airplanes on which ‘‘Condition 2’’ ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(d) Subject is found as defined in the Accomplishment (2) Before using any approved AMOC,
Air Transport Association (ATA) of Instructions of Aviation Partners Boeing notify your appropriate principal inspector,
America Code 57, Wings. Service Bulletin AP767–57–013, Revision 1, or lacking a principal inspector, the manager
dated April 11, 2017, during any inspection of the local flight standards district office/
(e) Unsafe Condition required by paragraph (g) or (g)(1)(i) of this certificate holding district office.
This AD was prompted by reports of AD: Do the actions required by paragraph (3) An AMOC that provides an acceptable
fatigue cracking in the lower outboard wing (g)(2)(i) and (g)(2)(ii) of this AD. level of safety may be used for any repair,
skin at the farthest outboard fastener of the (i) Before further flight, repair in modification, or alteration required by this
inboard segment of stringer L–9.5 on accordance with Part 2 of the AD if it is approved by the Boeing
airplanes with winglets installed per Accomplishment Instructions of Aviation Commercial Airplanes Organization
Supplemental Type Certificate ST01920SE. Partners Boeing Service Bulletin AP767–57– Designation Authorization (ODA) that has
We are issuing this AD to prevent fatigue 013, Revision 1, dated April 11, 2017. been authorized by the Manager, Seattle ACO
cracking in the lower outboard wing skin, (ii) At the applicable time specified in Branch, to make those findings. To be
which could result in failure and subsequent paragraph 1.E., ‘‘Compliance,’’ of Aviation approved, the repair method, modification
separation of the wing and winglet and Partners Boeing Service Bulletin AP767–57– deviation, or alteration deviation must meet
consequent reduced controllability of the 013, Revision 1, dated April 11, 2017, do an the certification basis of the airplane, and the
airplane. HFEC inspection for cracking, in accordance approval must specifically refer to this AD.
with Part 3 of the Accomplishment (4) Except as required by paragraph (g)(3)
(f) Compliance Instructions of Aviation Partners Boeing of this AD: For service information that
Comply with this AD within the Service Bulletin AP767–57–013, Revision 1, contains steps that are labeled as Required
compliance times specified, unless already dated April 11, 2017; and repeat the for Compliance (RC), the provisions of
done. inspection thereafter at the applicable times paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
specified in paragraph 1.E., ‘‘Compliance,’’ of apply.
(g) Repetitive Inspections, Preventative Aviation Partners Boeing Service Bulletin (i) The steps labeled as RC, including
Modification (Repair), Repetitive Post- AP767–57–013, Revision 1, dated April 11, substeps under an RC step and any figures
Modification (Repair) Inspections, and 2017. identified in an RC step, must be done to
Repair (3) If any crack is found during any comply with the AD. If a step or substep is
At the applicable time specified in inspection required by paragraph (g)(1)(ii)(B) labeled ‘‘RC Exempt,’’ then the RC
paragraph 1.E., ‘‘Compliance,’’ of Aviation or (g)(2)(ii) of this AD, repair before further requirement is removed from that step or
Partners Boeing Service Bulletin AP767–57– flight using a method approved in substep. An AMOC is required for any
013, Revision 1, dated April 11, 2017, except accordance with the procedures specified in deviations to RC steps, including substeps
as required by paragraph (h) of this AD: Do paragraph (j) of this AD. Although Aviation and identified figures.
a high frequency eddy current (HFEC) Partners Boeing Service Bulletin AP767–57– (ii) Steps not labeled as RC may be
inspection for cracking of the lower outboard 013, Revision 1, dated April 11, 2017, deviated from using accepted methods in
wing skin at the inboard segment of stringer specifies to contact Boeing for repair accordance with the operator’s maintenance
L–9.5, in accordance with Part 1 of the instructions, and specifies that action as or inspection program without obtaining
Accomplishment Instructions of Aviation ‘‘RC’’ (Required for Compliance), this AD approval of an AMOC, provided the RC steps,
Partners Boeing Service Bulletin AP767–57– requires repair as specified in this paragraph. including substeps and identified figures, can
013, Revision 1, dated April 11, 2017. (h) Exception to Service Information still be done as specified, and the airplane
(1) For airplanes on which ‘‘Condition 1’’ Specifications can be put back in an airworthy condition.
is found, as defined in the Accomplishment (k) Related Information
Where paragraph 1.E., ‘‘Compliance,’’ of
Instructions of Aviation Partners Boeing
Aviation Partners Boeing Service Bulletin (1) For more information about this AD,
Service Bulletin AP767–57–013, Revision 1, AP767–57–013, Revision 1, dated April 11,
dated April 11, 2017, during any inspection contact Allen Rauschendorfer, Aerospace
2017, specifies a compliance time of ‘‘after Engineer, Airframe Section, FAA, Seattle
required by paragraph (g) or (g)(1)(i) of this the initial issue date of this service bulletin,’’
AD: Do the actions required by paragraph ACO Branch, 1601 Lind Avenue SW, Renton,
this AD requires compliance within the WA 98057–3356; phone: 425–917–6450; fax:
(g)(1)(i) or (g)(1)(ii) of this AD. specified compliance time after the effective
(i) Repeat the inspection specified in 425–917–6590; email: allen.rauschendorfer@
date of this AD. faa.gov.
paragraph (g) of this AD thereafter at the
applicable times specified in paragraph 1.E., (i) Credit for Previous Actions (2) For service information identified in
‘‘Compliance,’’ of Aviation Partners Boeing this AD, contact Aviation Partners Boeing,
For Group 2 airplanes: This paragraph 2811 S. 102nd Street, Suite 200, Seattle, WA
Service Bulletin AP767–57–013, Revision 1, provides credit for the actions specified in
dated April 11, 2017. 98168; telephone 206–762–1171; internet
Part 1 and Part 2 of the Accomplishment https://www.aviationpartnersboeing.com.
(ii) Do the actions required by paragraphs Instructions of Aviation Partners Boeing
(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD: You may view this referenced service
Service Bulletin AP767–57–013, Revision 1, information at the FAA, Transport Standards
(A) Before further flight, do the dated April 11, 2017, that are required by
preventative modification in accordance with Branch, 1601 Lind Avenue SW, Renton, WA.
paragraph (g) of this AD, if those actions were
Part 2 of the Accomplishment Instructions of For information on the availability of this
performed before the effective date of this AD
sradovich on DSK3GMQ082PROD with PROPOSALS
Aviation Partners Boeing Service Bulletin material at the FAA, call 425–227–1221.
using Aviation Partners Boeing Service
AP767–57–013, Revision 1, dated April 11, Bulletin AP767–57–013, dated November 30, Issued in Renton, Washington, on January
2017. 2016. 25, 2018.
(B) At the applicable time specified in Michael Kaszycki,
paragraph 1.E., ‘‘Compliance,’’ of Aviation (j) Alternative Methods of Compliance
(AMOCs) Acting Director, System Oversight Division,
Partners Boeing Service Bulletin AP767–57–
Aircraft Certification Service.
013, Revision 1, dated April 11, 2017, do an (1) The Manager, Seattle ACO Branch,
HFEC inspection for cracking, in accordance FAA, has the authority to approve AMOCs [FR Doc. 2018–02197 Filed 2–8–18; 8:45 am]
with Part 3 of the Accomplishment for this AD, if requested using the procedures BILLING CODE 4910–13–P
VerDate Sep<11>2014 16:06 Feb 08, 2018 Jkt 244001 PO 00000 Frm 00003 Fmt 4702 Sfmt 9990 E:\FR\FM\09FEP1.SGM 09FEP1](https://thefederalregister.org/doc/83_FR_5766/page/3.svg)
Document Created: 2018-02-09 00:11:48
Document Modified: 2018-02-09 00:11:48
| 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 March 26, 2018. | |
| Contact | Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW, Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 83 FR 5738 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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