Airworthiness Directives; The Boeing Company Airplanes, 59967-59969 [2017-26834]
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Federal Register / Vol. 82, No. 241 / Monday, December 18, 2017 / Rules and Regulations
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) ATR Service Bulletin ATR42–30–0080,
Revision 02, dated March 26, 2013.
(ii) ATR Service Bulletin ATR42–30–0081,
Revision 02, dated March 26, 2013.
(iii) ATR Service Bulletin ATR72–30–1049,
Revision 03, dated March 26, 2013.
(iv) ATR Service Bulletin ATR72–30–1050,
Revision 03, dated March 26, 2013.
(3) For service information identified in
this AD, contact ATR—GIE Avions de
´
´
Transport Regional, 1, Allee Pierre Nadot,
31712 Blagnac Cedex, France; telephone +33
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
email continued.airworthiness@atraircraft.com.
(4) You may view this 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 6, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–26949 Filed 12–15–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0807; Product
Identifier 2017–NM–080–AD; Amendment
39–19126; AD 2017–25–12]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This AD was prompted by
reports of cracking in the webs of the
stub beams at certain fuselage stations.
These cracks are the result of fatigue
caused by cyclical loading from
pressurization, wing loads, and landing
loads. This AD requires repetitive
inspections for cracking of the webs of
the stub beams at certain fuselage
Pmangrum on DSK3GDR082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
15:19 Dec 15, 2017
Jkt 244001
stations, and applicable on-condition
actions. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective January 22,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 22, 2018.
ADDRESSES: For service information
identified in this final rule, 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, 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0807.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0807; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT:
Galib Abumeri, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5324; fax: 562–627–
5210; email: galib.abumeri@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all The Boeing Company Model
737–100, –200, –200C, –300, –400, and
–500 series airplanes. The NPRM
published in the Federal Register on
August 30, 2017 (82 FR 41179). The
NPRM was prompted by reports of
cracking in the webs of the stub beams
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Frm 00021
Fmt 4700
Sfmt 4700
59967
at certain fuselage stations. These cracks
are a result of fatigue caused by cyclical
loading from pressurization, wing loads,
and landing loads. The NPRM proposed
to require repetitive inspections for
cracking of the webs of the stub beams
at certain fuselage stations, and
applicable on-condition actions.
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
Boeing concurred with the NPRM.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing Supplemental Type
Certificate (STC) ST01219SE does not
affect the ability to accomplish the
actions specified in the NPRM.
We concur with the commenter’s
request. We have redesignated
paragraph (c) of the proposed AD as
paragraph (c)(1) and added paragraph
(c)(2) to this AD to state that installation
of STC ST01219SE does not affect the
ability to accomplish the actions
required by this AD. Therefore, for
airplanes on which STC ST01219SE is
installed, a ‘‘change in product’’
alternative methods of compliance
(AMOC) approval request is not
necessary to comply with the
requirements of 14 CFR 39.17.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Additional Report of Cracking Since
NPRM Was Issued
Since we issued the NPRM, Boeing
received a report indicating that stub
beam cracking occurred at station (STA)
685 outside of the inspection areas
described in Boeing Alert Service
Bulletin 737–53A1364, dated May 24,
E:\FR\FM\18DER1.SGM
18DER1
59968
Federal Register / Vol. 82, No. 241 / Monday, December 18, 2017 / Rules and Regulations
2017. The cracking occurred at the
upper chord inboard corner radius near
the buttock line (BL) 45.5 longitudinal
floor beam, and the lower chord
outboard flange file radius. The cracks
were approximately 1.1 and 4.3 inches
long, and could be seen while
performing the inspections specified in
Boeing Alert Service Bulletin 737–
53A1364, dated May 24, 2017.
Concurrently with doing the inspections
required by paragraphs (g) and (h) of
this AD, operators are encouraged to
inspect for cracking in the upper chord
inboard radius near the BL 45.5
longitudinal floor bean, and the lower
chord outboard flange file radius of the
STA 685 stub beam. We are considering
issuing a separate rulemaking action to
address the stub beam cracking at STA
685 that occurred outside of the
inspection areas specified in this AD.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1364, dated May 24,
2017. This service information describes
procedures for high frequency eddy
current and detailed inspections for
cracking of the fuselage stub beam webs
below the passenger floor at STA 685,
STA 695, and STA 706, and applicable
on-condition actions. 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.
Costs of Compliance
We estimate that this AD affects 160
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Inspections .............
Up to 13 work-hours × $85 per hour = $1,105 per inspection
cycle.
Pmangrum on DSK3GDR082PROD with RULES
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 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.
15:19 Dec 15, 2017
Jkt 244001
$0
Cost on U.S.
operators
Up to $1,105 per inspection
cycle.
Regulatory Findings
We have received no definitive data
that will enable us to provide cost
estimates for the on-condition actions
specified in this AD.
VerDate Sep<11>2014
Cost per
product
Parts cost
§ 39.13
This AD will not have federalism
implications under Executive Order
13132. This AD will 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 that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
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.
Up to $176,800 per inspection
cycle.
■
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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Frm 00022
Fmt 4700
Sfmt 4700
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2017–25–12 The Boeing Company:
Amendment 39–19126; Docket No.
FAA–2017–0807; Product Identifier
2017–NM–080–AD.
(a) Effective Date
This AD is effective January 22, 2018.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://rgl.faa.
gov/Regulatory_and_Guidance_Library/rgstc.
nsf/0/EBD1CEC7B301293E86257CB30045557
A?OpenDocument&Highlight=st01219se)
does not affect the ability to accomplish the
actions required by this AD. Therefore, for
airplanes on which STC ST01219SE is
installed, a ‘‘change in product’’ alternative
method of compliance (AMOC) approval
request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking in the webs of the stub beams at
certain fuselage stations. These cracks are a
result of fatigue caused by cyclical loading
from pressurization, wing loads, and landing
loads. We are issuing this AD to detect and
correct cracking in the webs of the stub
beams at certain fuselage stations, which, if
not corrected, could result in the loss of
structural integrity of the airframe during
E:\FR\FM\18DER1.SGM
18DER1
Federal Register / Vol. 82, No. 241 / Monday, December 18, 2017 / Rules and Regulations
flight, collapse of the main landing gear, and
failure of the pressure deck.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in
Boeing Alert Service Bulletin 737–53A1364,
dated May 24, 2017, within 120 days after the
effective date of this AD, inspect the stub
beam webs for any cracking, and do all
applicable on-condition actions, using a
method approved in accordance with the
procedures specified in paragraph (j) of this
AD.
(h) Required Actions for Group 2, 3, 4, 5,
and 6 Airplanes
Except as required by paragraph (i) of this
AD: For Group 2, 3, 4, 5, and 6 airplanes, as
identified in Boeing Alert Service Bulletin
737–53A1364, dated May 24, 2017, at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1364, dated May 24, 2017,
do all applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1364, dated May 24, 2017.
Pmangrum on DSK3GDR082PROD with RULES
(i) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD,
the phrase ‘‘the effective date of this AD’’
may be substituted for ‘‘the original issue
date of this service bulletin,’’ as specified in
Boeing Alert Service Bulletin 737–53A1364,
dated May 24, 2017.
(2) Where Boeing Alert Service Bulletin
737–53A1364, dated May 24, 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 (j) of this AD.
(j) 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 (k) of this
AD. Information may be emailed to: 9-ANMLAACO-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
VerDate Sep<11>2014
15:19 Dec 15, 2017
Jkt 244001
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 (i)(2)
of this AD: For service information that
contains steps that are labeled as 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.
59969
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 52
[EPA–R01–OAR–2016–0626; A–1–FRL–
9972–20–Region 1]
Air Plan Approval; Vermont; Regional
Haze Five-Year Progress Report
Environmental Protection
Agency (EPA).
ACTION: Final rule.
AGENCY:
The Environmental Protection
Agency (EPA) is approving Vermont’s
Regional Haze Five-Year Progress
Report (Progress Report), submitted on
February 29, 2016 as a revision to its
State Implementation Plan (SIP).
Vermont’s SIP revision addresses
requirements of the Clean Air Act (CAA)
and EPA’s rules that require states to
submit periodic reports describing the
(k) Related Information
progress toward reasonable progress
goals (RPGs) established for regional
For more information about this AD,
contact Galib Abumeri, Aerospace Engineer,
haze and a determination of adequacy of
Airframe Section, FAA, Los Angeles ACO
the State’s existing regional haze SIP.
Branch, 3960 Paramount Boulevard,
EPA is approving Vermont’s Progress
Lakewood, CA 90712–4137; phone: 562–627– Report on the basis that it addresses the
5324; fax: 562–627–5210; email:
progress report and adequacy
galib.abumeri@faa.gov.
determination requirements for the first
(l) Material Incorporated by Reference
implementation period covering
through 2018.
(1) The Director of the Federal Register
approved the incorporation by reference
DATES: This rule is effective on January
(IBR) of the service information listed in this
17, 2018.
paragraph under 5 U.S.C. 552(a) and 1 CFR
ADDRESSES: EPA has established a
part 51.
docket for this action under Docket
(2) You must use this service information
Identification No. EPA–R01–OAR–
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
2016–0626. All documents in the docket
(i) Boeing Alert Service Bulletin 737–
are listed on the https://
53A1364, dated May 24, 2017.
www.regulations.gov website. Although
(ii) Reserved.
listed in the index, some information is
(3) For service information identified in
not publicly available, i.e., CBI or other
this AD, contact Boeing Commercial
information whose disclosure is
Airplanes, Attention: Contractual & Data
restricted by statute. Certain other
Services (C&DS), 2600 Westminster Blvd.,
material, such as copyrighted material,
MC 110–SK57, Seal Beach, CA 90740–5600;
is not placed on the internet and will be
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
publicly available only in hard copy
(4) You may view this service information
form. Publicly available docket
at the FAA, Transport Standards Branch,
materials are available at https://
1601 Lind Avenue SW, Renton, WA. For
www.regulations.gov or at the U.S.
information on the availability of this
Environmental Protection Agency, EPA
material at the FAA, call 425–227–1221.
New England Regional Office, Office of
(5) You may view this service information
Ecosystem Protection, Air Quality
that is incorporated by reference at the
Planning Unit, 5 Post Office Square—
National Archives and Records
Suite 100, Boston, MA. EPA requests
Administration (NARA). For information on
the availability of this material at NARA, call that if at all possible, you contact the
202–741–6030, or go to: https://
contact listed in the FOR FURTHER
www.archives.gov/federal-register/cfr/ibrINFORMATION CONTACT section to
locations.html.
schedule your inspection. The Regional
Issued in Renton, Washington, on
Office’s official hours of business are
December 5, 2017.
Monday through Friday, 8:30 a.m. to
Dionne Palermo,
4:30 p.m., excluding legal holidays.
Acting Director, System Oversight Division,
FOR FURTHER INFORMATION CONTACT:
Aircraft Certification Service.
Anne K. McWilliams, Air Quality
[FR Doc. 2017–26834 Filed 12–15–17; 8:45 am]
Planning Unit, U.S. Environmental
Protection Agency, New England
BILLING CODE 4910–13–P
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SUMMARY:
E:\FR\FM\18DER1.SGM
18DER1
Agencies
[Federal Register Volume 82, Number 241 (Monday, December 18, 2017)]
[Rules and Regulations]
[Pages 59967-59969]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26834]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0807; Product Identifier 2017-NM-080-AD; Amendment
39-19126; AD 2017-25-12]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. This AD was prompted by reports of cracking in the webs of
the stub beams at certain fuselage stations. These cracks are the
result of fatigue caused by cyclical loading from pressurization, wing
loads, and landing loads. This AD requires repetitive inspections for
cracking of the webs of the stub beams at certain fuselage stations,
and applicable on-condition actions. We are issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective January 22, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 22,
2018.
ADDRESSES: For service information identified in this final rule,
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, 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0807.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0807; 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 final rule, the regulatory evaluation, any comments
received, and other information. The address for the Docket Office
(phone: 800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-
5210; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on August 30, 2017 (82 FR
41179). The NPRM was prompted by reports of cracking in the webs of the
stub beams at certain fuselage stations. These cracks are a result of
fatigue caused by cyclical loading from pressurization, wing loads, and
landing loads. The NPRM proposed to require repetitive inspections for
cracking of the webs of the stub beams at certain fuselage stations,
and applicable on-condition actions.
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comments received on the
NPRM and the FAA's response to each comment.
Support for the NPRM
Boeing concurred with the NPRM.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing Supplemental
Type Certificate (STC) ST01219SE does not affect the ability to
accomplish the actions specified in the NPRM.
We concur with the commenter's request. We have redesignated
paragraph (c) of the proposed AD as paragraph (c)(1) and added
paragraph (c)(2) to this AD to state that installation of STC ST01219SE
does not affect the ability to accomplish the actions required by this
AD. Therefore, for airplanes on which STC ST01219SE is installed, a
``change in product'' alternative methods of compliance (AMOC) approval
request is not necessary to comply with the requirements of 14 CFR
39.17.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule with the changes described previously and minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Additional Report of Cracking Since NPRM Was Issued
Since we issued the NPRM, Boeing received a report indicating that
stub beam cracking occurred at station (STA) 685 outside of the
inspection areas described in Boeing Alert Service Bulletin 737-
53A1364, dated May 24,
[[Page 59968]]
2017. The cracking occurred at the upper chord inboard corner radius
near the buttock line (BL) 45.5 longitudinal floor beam, and the lower
chord outboard flange file radius. The cracks were approximately 1.1
and 4.3 inches long, and could be seen while performing the inspections
specified in Boeing Alert Service Bulletin 737-53A1364, dated May 24,
2017. Concurrently with doing the inspections required by paragraphs
(g) and (h) of this AD, operators are encouraged to inspect for
cracking in the upper chord inboard radius near the BL 45.5
longitudinal floor bean, and the lower chord outboard flange file
radius of the STA 685 stub beam. We are considering issuing a separate
rulemaking action to address the stub beam cracking at STA 685 that
occurred outside of the inspection areas specified in this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1364, dated May
24, 2017. This service information describes procedures for high
frequency eddy current and detailed inspections for cracking of the
fuselage stub beam webs below the passenger floor at STA 685, STA 695,
and STA 706, and applicable on-condition actions. 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.
Costs of Compliance
We estimate that this AD affects 160 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections.............. Up to 13 work[dash]hours $0 Up to $1,105 per Up to $176,800 per
x $85 per hour = $1,105 inspection cycle. inspection cycle.
per inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that will enable us to provide
cost estimates for the on-condition actions specified in this 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 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
This AD will not have federalism implications under Executive Order
13132. This AD will 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 that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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):
2017-25-12 The Boeing Company: Amendment 39-19126; Docket No. FAA-
2017-0807; Product Identifier 2017-NM-080-AD.
(a) Effective Date
This AD is effective January 22, 2018.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=st01219se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking in the webs of the
stub beams at certain fuselage stations. These cracks are a result
of fatigue caused by cyclical loading from pressurization, wing
loads, and landing loads. We are issuing this AD to detect and
correct cracking in the webs of the stub beams at certain fuselage
stations, which, if not corrected, could result in the loss of
structural integrity of the airframe during
[[Page 59969]]
flight, collapse of the main landing gear, and failure of the
pressure deck.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in Boeing Alert Service
Bulletin 737-53A1364, dated May 24, 2017, within 120 days after the
effective date of this AD, inspect the stub beam webs for any
cracking, and do all applicable on-condition actions, using a method
approved in accordance with the procedures specified in paragraph
(j) of this AD.
(h) Required Actions for Group 2, 3, 4, 5, and 6 Airplanes
Except as required by paragraph (i) of this AD: For Group 2, 3,
4, 5, and 6 airplanes, as identified in Boeing Alert Service
Bulletin 737-53A1364, dated May 24, 2017, at the applicable times
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1364, dated May 24, 2017, do all applicable actions
identified as ``RC'' (required for compliance) in, and in accordance
with, the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1364, dated May 24, 2017.
(i) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD, the phrase ``the effective date of this AD'' may be
substituted for ``the original issue date of this service
bulletin,'' as specified in Boeing Alert Service Bulletin 737-
53A1364, dated May 24, 2017.
(2) Where Boeing Alert Service Bulletin 737-53A1364, dated May
24, 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 (j) of this AD.
(j) 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 (k) of this AD. Information may
be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, 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 (i)(2) of this AD: For
service information that contains steps that are labeled as 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
For more information about this AD, contact Galib Abumeri,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5324; fax: 562-627-5210; email: [email protected].
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737-53A1364, dated May 24,
2017.
(ii) Reserved.
(3) 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.
(4) You may view this 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 5, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-26834 Filed 12-15-17; 8:45 am]
BILLING CODE 4910-13-P