83 FR 8951 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 42 (March 2, 2018)

Page Range		8951-8953
FR Document		2018-04229
We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the longitudinal lap splices of the fuselage skin are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive inspections of the longitudinal lap splices of the fuselage skin for cracking and protruding fasteners, and applicable corrective actions. We are proposing this AD to address the unsafe condition on these products.
Federal Register, Volume 83 Issue 42 (Friday, March 2, 2018)
[Federal Register Volume 83, Number 42 (Friday, March 2, 2018)]
[Proposed Rules]
[Pages 8951-8953]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-04229]


========================================================================
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. 42 / Friday, March 2, 2018 / Proposed 
Rules

[[Page 8951]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0163; Product Identifier 2017-NM-168-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 757 airplanes. This proposed AD was 
prompted by an evaluation by the design approval holder (DAH) 
indicating that the longitudinal lap splices of the fuselage skin are 
subject to widespread fatigue damage (WFD). This proposed AD would 
require repetitive inspections of the longitudinal lap splices of the 
fuselage skin for cracking and protruding fasteners, and applicable 
corrective actions. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by April 16, 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 NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may 
view this referenced service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For information 
on the availability of this material at the FAA, call 206-231-3195. It 
is also available on the internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2018-0163.

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-
0163; 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: David Truong, Aerospace Engineer, 
Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5224; fax: 562-627-
5210; email: david.truong@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-2018-0163; 
Product Identifier 2017-NM-168-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

[[Page 8952]]

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.
    The longitudinal lap splices of the fuselage skin on Model 757 
airplanes have been determined to be susceptible to WFD. No cracking 
was found on the fatigue test article, but WFD analysis has identified 
the need for more frequent repetitive inspections. Existing maintenance 
planning data (MPD) inspections are not sufficient to detect widespread 
fatigue cracks before they become critical. Currently, there have been 
no reports of WFD cracking on airplanes in service. Any fatigue 
cracking of the longitudinal lap splices of the fuselage skin could go 
undetected and grow in length. This condition could result in reduced 
structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 757-53A0104, dated 
November 6, 2017. The service information describes procedures for 
visual and eddy current inspections of the longitudinal lap splices of 
the fuselage skin for cracking and protruding head fasteners.
    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 accomplishment of the actions 
identified as ``RC'' (required for compliance) in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0104, dated 
November 6, 2017, described previously, except for any differences 
identified as exceptions in the regulatory text of this proposed AD.
    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-2018-0163.

Costs of Compliance

    We estimate that this proposed AD affects 509 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......................  367 work-hours x                 $0  $31,195 per          $15,878,255 per
                                    $85 per hour =                       inspection cycle.    inspection cycle.
                                    $31,195.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repairs 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.
    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-2018-0163; Product Identifier 
2017-NM-168-AD.

(a) Comments Due Date

    We must receive comments by April 16, 2018.

[[Page 8953]]

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 757-200, -200PF, -
200CB, and -300 series airplanes, certificated in any category, as 
identified in Boeing Alert Service Bulletin 757-53A0104, dated 
November 6, 2017.

(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 indicating that the longitudinal lap splices of the fuselage 
skin are subject to widespread fatigue damage. We are issuing this 
AD to address fatigue cracking of the longitudinal lap splices of 
the fuselage skin, 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) Required Actions

    Except as required by paragraph (h) of this AD: At the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 757-53A0104, dated November 6, 2017, 
do all applicable actions identified as ``RC'' (required for 
compliance) in, and in accordance with, the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0104, dated 
November 6, 2017.

(h) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD, where Boeing Alert Service Bulletin 757-53A0104, dated 
November 6, 2017, uses the phrase ``the original issue date of this 
service bulletin,'' this AD requires using ``the effective date of 
this AD.''
    (2) Where Boeing Alert Service Bulletin 757-53A0104, dated 
November 6, 2017, specifies contacting Boeing, and specifies that 
action as RC: This AD requires using a method approved in accordance 
with the procedures specified in paragraph (i) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (j)(1) of this AD. Information 
may be emailed to: 9-ANM-LAACO-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, Los Angeles 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 (h)(2) of this AD: For 
service information that contains steps that are labeled as RC, the 
provisions of paragraphs (i)(4)(i) and (i)(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.

(j) Related Information

    (1) For more information about this AD, contact David Truong, 
Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5224; fax: 562-627-5210; email: david.truong@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.

    Issued in Renton, Washington, on February 22, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-04229 Filed 3-1-18; 8:45 am]
 BILLING CODE 4910-13-P
8951

Proposed Rules Federal Register
Vol. 83, No. 42

Friday, March 2, 2018

This section of the FEDERAL REGISTER For service information identified in www.regulations.gov, including any
contains notices to the public of the proposed this NPRM, contact Boeing Commercial personal information you provide. We
issuance of rules and regulations. The Airplanes, Attention: Contractual & Data will also post a report summarizing each
purpose of these notices is to give interested Services (C&DS), 2600 Westminster substantive verbal contact we receive
persons an opportunity to participate in the Blvd., MC 110–SK57, Seal Beach, CA about this proposed AD.
rule making prior to the adoption of the final
rules.
90740–5600; telephone 562–797–1717;
internet https://www.myboeingfleet. Discussion
com. You may view this referenced Fatigue damage can occur locally, in
DEPARTMENT OF TRANSPORTATION service information at the FAA, small areas or structural design details,
Transport Standards Branch, 2200 or globally, in widespread areas.
Federal Aviation Administration South 216th St., Des Moines, WA. For Multiple-site damage is widespread
information on the availability of this damage that occurs in a large structural
14 CFR Part 39 material at the FAA, call 206–231–3195. element such as a single rivet line of a
It is also available on the internet at lap splice joining two large skin panels.
[Docket No. FAA–2018–0163; Product
http://www.regulations.gov by searching Widespread damage can also occur in
Identifier 2017–NM–168–AD]
for and locating Docket No. FAA–2018– multiple elements such as adjacent
RIN 2120–AA64 0163. frames or stringers. Multiple-site
Examining the AD Docket damage and multiple-element damage
Airworthiness Directives; The Boeing
cracks are typically too small initially to
Company Airplanes You may examine the AD docket on
be reliably detected with normal
the internet at http://
AGENCY: Federal Aviation inspection methods. Without
www.regulations.gov by searching for
Administration (FAA), DOT. intervention, these cracks will grow,
and locating Docket No. FAA–2016–
ACTION: Notice of proposed rulemaking and eventually compromise the
0163; or in person at the Docket
(NPRM). structural integrity of the airplane. This
Management Facility between 9 a.m.
condition is known as widespread
and 5 p.m., Monday through Friday,
SUMMARY: We propose to adopt a new fatigue damage. It is associated with
except Federal holidays. The AD docket
airworthiness directive (AD) for certain general degradation of large areas of
contains this proposed AD, the
The Boeing Company Model 757 structure with similar structural details
regulatory evaluation, any comments
airplanes. This proposed AD was and stress levels. As an airplane ages,
received, and other information. The
prompted by an evaluation by the WFD will likely occur, and will
street address for the Docket Office
design approval holder (DAH) certainly occur if the airplane is
(phone: 800–647–5527) is in the
indicating that the longitudinal lap operated long enough without any
ADDRESSES section. Comments will be
splices of the fuselage skin are subject intervention.
available in the AD docket shortly after
to widespread fatigue damage (WFD). The FAA’s WFD final rule (75 FR
receipt.
This proposed AD would require 69746, November 15, 2010) became
FOR FURTHER INFORMATION CONTACT:
repetitive inspections of the effective on January 14, 2011. The WFD
longitudinal lap splices of the fuselage David Truong, Aerospace Engineer,
Airframe Section, Los Angeles ACO rule requires certain actions to prevent
skin for cracking and protruding structural failure due to WFD
fasteners, and applicable corrective Branch, FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137; throughout the operational life of
actions. We are proposing this AD to certain existing transport category
address the unsafe condition on these phone: 562–627–5224; fax: 562–627–
5210; email: david.truong@faa.gov. airplanes and all of these airplanes that
products. will be certificated in the future. For
SUPPLEMENTARY INFORMATION:
DATES: We must receive comments on existing and future airplanes subject to
this proposed AD by April 16, 2018. Comments Invited the WFD rule, the rule requires that
ADDRESSES: You may send comments, We invite you to send any written DAHs establish a limit of validity (LOV)
using the procedures found in 14 CFR relevant data, views, or arguments about of the engineering data that support the
11.43 and 11.45, by any of the following this proposal. Send your comments to structural maintenance program.
methods: an address listed under the ADDRESSES Operators affected by the WFD rule may
• Federal eRulemaking Portal: Go to section. Include ‘‘Docket No. FAA– not fly an airplane beyond its LOV,
http://www.regulations.gov. Follow the 2018–0163; Product Identifier 2017– unless an extended LOV is approved.
instructions for submitting comments. NM–168–AD’’ at the beginning of your The WFD rule (75 FR 69746,
• Fax: 202–493–2251. comments. We specifically invite November 15, 2010) does not require
• Mail: U.S. Department of comments on the overall regulatory, identifying and developing maintenance
daltland on DSKBBV9HB2PROD with PROPOSALS

Transportation, Docket Operations, M– economic, environmental, and energy actions if the DAHs can show that such
30, West Building Ground Floor, Room aspects of this proposed AD. We will actions are not necessary to prevent
W12–140, 1200 New Jersey Avenue SE, consider all comments received by the WFD before the airplane reaches the
Washington, DC 20590. closing date and may amend this LOV. Many LOVs, however, do depend
• Hand Delivery: Deliver to Mail proposed AD because of those on accomplishment of future
address above between 9 a.m. and 5 comments. maintenance actions. As stated in the
p.m., Monday through Friday, except We will post all comments we WFD rule, any maintenance actions
Federal holidays. receive, without change, to http:// necessary to reach the LOV will be

VerDate Sep<11>2014 17:47 Mar 01, 2018 Jkt 244001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\02MRP1.SGM 02MRP1
8952 Federal Register / Vol. 83, No. 42 / Friday, March 2, 2018 / Proposed Rules

mandated by airworthiness directives airplanes in service. Any fatigue described previously is likely to exist or
through separate rulemaking actions. cracking of the longitudinal lap splices develop in other products of the same
In the context of WFD, this action is of the fuselage skin could go undetected type design.
necessary to enable DAHs to propose and grow in length. This condition
LOVs that allow operators the longest Proposed AD Requirements
could result in reduced structural
operational lives for their airplanes, and integrity of the airplane. This proposed AD would require
still ensure that WFD will not occur. accomplishment of the actions
This approach allows for an Related Service Information Under 1
CFR Part 51 identified as ‘‘RC’’ (required for
implementation strategy that provides compliance) in the Accomplishment
flexibility to DAHs in determining the We reviewed Boeing Alert Service Instructions of Boeing Alert Service
timing of service information Bulletin 757–53A0104, dated November Bulletin 757–53A0104, dated November
development (with FAA approval), 6, 2017. The service information 6, 2017, described previously, except for
while providing operators with certainty describes procedures for visual and any differences identified as exceptions
regarding the LOV applicable to their eddy current inspections of the in the regulatory text of this proposed
airplanes. longitudinal lap splices of the fuselage AD.
The longitudinal lap splices of the skin for cracking and protruding head
fuselage skin on Model 757 airplanes fasteners. For information on the procedures
have been determined to be susceptible This service information is reasonably and compliance times, see this service
to WFD. No cracking was found on the available because the interested parties information at http://www.regulations.
fatigue test article, but WFD analysis has have access to it through their normal gov by searching for and locating Docket
identified the need for more frequent course of business or by the means No. FAA–2018–0163.
repetitive inspections. Existing identified in the ADDRESSES section. Costs of Compliance
maintenance planning data (MPD)
inspections are not sufficient to detect FAA’s Determination We estimate that this proposed AD
widespread fatigue cracks before they We are proposing this AD because we affects 509 airplanes of U.S. registry. We
become critical. Currently, there have evaluated all the relevant information estimate the following costs to comply
been no reports of WFD cracking on and determined the unsafe condition with this proposed AD:

ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspections ......... 367 work-hours × $85 per hour = $0 $31,195 per inspection cycle ........ $15,878,255 per inspection cycle.
$31,195.

We have received no definitive data FAA Order 8000.51C. In accordance on a substantial number of small entities
that would enable us to provide cost with that order, issuance of ADs is under the criteria of the Regulatory
estimates for the on-condition repairs normally a function of the Compliance Flexibility Act.
specified in this proposed AD. and Airworthiness Division, but during
List of Subjects in 14 CFR Part 39
this transition period, the Executive
Authority for This Rulemaking
Director has delegated the authority to Air transportation, Aircraft, Aviation
Title 49 of the United States Code issue ADs applicable to transport safety, Incorporation by reference,
specifies the FAA’s authority to issue category airplanes to the Director of the Safety.
rules on aviation safety. Subtitle I, System Oversight Division.
section 106, describes the authority of The Proposed Amendment
the FAA Administrator. Subtitle VII: Regulatory Findings
Accordingly, under the authority
Aviation Programs, describes in more We determined that this proposed AD delegated to me by the Administrator,
detail the scope of the Agency’s would not have federalism implications the FAA proposes to amend 14 CFR part
authority. under Executive Order 13132. This 39 as follows:
We are issuing this rulemaking under proposed AD would not have a
the authority described in Subtitle VII, substantial direct effect on the States, on PART 39—AIRWORTHINESS
Part A, Subpart III, Section 44701: the relationship between the national DIRECTIVES
‘‘General requirements.’’ Under that Government and the States, or on the
section, Congress charges the FAA with distribution of power and ■ 1. The authority citation for part 39
promoting safe flight of civil aircraft in responsibilities among the various continues to read as follows:
air commerce by prescribing regulations levels of government. Authority: 49 U.S.C. 106(g), 40113, 44701.
for practices, methods, and procedures For the reasons discussed above, I
the Administrator finds necessary for certify this proposed regulation: § 39.13 [Amended]
safety in air commerce. This regulation (1) Is not a ‘‘significant regulatory ■ 2. The FAA amends § 39.13 by adding
is within the scope of that authority action’’ under Executive Order 12866, the following new airworthiness
daltland on DSKBBV9HB2PROD with PROPOSALS

because it addresses an unsafe condition (2) Is not a ‘‘significant rule’’ under directive (AD):
that is likely to exist or develop on the DOT Regulatory Policies and
products identified in this rulemaking Procedures (44 FR 11034, February 26, The Boeing Company: Docket No. FAA–
action. 1979), 2018–0163; Product Identifier 2017–
NM–168–AD.
This proposed AD is issued in (3) Will not affect intrastate aviation
accordance with authority delegated by in Alaska, and (a) Comments Due Date
the Executive Director, Aircraft (4) Will not have a significant We must receive comments by April 16,
Certification Service, as authorized by economic impact, positive or negative, 2018.

VerDate Sep<11>2014 17:47 Mar 01, 2018 Jkt 244001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\02MRP1.SGM 02MRP1
Document Created: 2018-03-01 23:56:11
Document Modified: 2018-03-01 23:56:11
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 April 16, 2018.
Contact		David Truong, Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5224; fax: 562-627- 5210; email: [email protected]
FR Citation		83 FR 8951
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
83 FR 8951 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 83, Issue 42 (March 2, 2018)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
