Airworthiness Directives; The Boeing Company Airplanes, 27977-27979 [2017-12175]
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Rules and Regulations
(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 June 7,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–12396 Filed 6–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9188; Directorate
Identifier 2016–NM–102–AD; Amendment
39–18920; AD 2017–12–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2007–26–
04 for certain The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. AD
2007–26–04 required repetitive
inspections for cracking of certain
fasteners, and repair if necessary; and a
preventive modification, which
terminated the repetitive inspections.
This AD removes the mandatory
modification; adds repetitive
inspections of the skin for cracking, a
one-time inspection for defects of the
production countersunk rivets, and
corrective actions if necessary; and adds
an optional skin trim-out repair, which
will terminate certain inspections. This
AD was prompted by an evaluation by
the design approval holder (DAH)
indicating that certain skin panels are
subject to widespread fatigue damage
(WFD). We are issuing this AD to
address the unsafe condition on these
products.
asabaliauskas on DSKBBXCHB2PROD with RULES
SUMMARY:
This AD is effective July 25,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 25, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
DATES:
VerDate Sep<11>2014
16:57 Jun 19, 2017
Jkt 241001
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
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9188.
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–2016–
9188; 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 AD, 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:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email: jennifer.tsakoumakis@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2007–26–04,
Amendment 39–15306 (72 FR 71216,
December 17, 2007) (‘‘AD 2007–26–
04’’). AD 2007–26–04 applied to certain
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
The NPRM published in the Federal
Register on October 20, 2016 (81 FR
72554) (‘‘the NPRM’’). The NPRM was
prompted by an evaluation by the DAH
indicating that the forward skin panel at
the station (STA) 259.5 circumferential
butt splice between stringers 19L and
24L is subject to WFD. The NPRM
proposed to continue to require
repetitive inspections for cracking
around the heads of the fasteners on the
forward fastener row in certain areas of
a certain circumferential butt splice, and
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
27977
repair if necessary. The NPRM also
proposed to add repetitive inspections
of the skin for cracking at the aft
fastener column, and a one-time
inspection for defects in the production
countersunk rivets, and corrective
actions if necessary; and add an
optional skin trim-out repair, which
would terminate certain inspections. We
are issuing this AD to prevent cracking
of the STA 259.5 circumferential butt
splice, which could result in loss of
structural integrity of the fuselage skin
and possible loss of cabin pressure.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Revise Terminating Action
Southwest Airlines (SWA) requested
that we revise paragraph (i) of the
proposed AD to specify that doing the
optional repairs terminates the initial
and repetitive inspections instead of just
the repetitive inspections. SWA stated
that if a terminating repair were
installed prior to the initial inspection,
there is no justification for either the
initial or repetitive inspections.
We agree with SWA’s request. We
have revised paragraph (i) of this AD to
specify that the terminating repairs are
applicable to both the initial and
repetitive inspections.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing the supplemental type
certificate (STC) ST01219SE does not
affect the actions specified in the
NPRM.
We concur with the commenter. We
have redesignated paragraph (c) of the
proposed AD as paragraph (c)(1) of this
AD 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 method 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 AD
with the changes described previously,
and minor editorial changes. We have
determined that these minor changes:
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27978
Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Rules and Regulations
• 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 AD.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1267, Revision 1,
dated March 8, 2016 (‘‘ASB 737–
53A1267, R1’’). The service information
describes procedures for detailed
inspections and high frequency eddy
current (HFEC) surface inspections of
the skin around the fastener heads for
any crack on the forward and aft
fastener columns, left and right sides, at
STA 259.5 circumferential butt splice; a
detailed inspection for any defect of the
production countersunk rivet heads on
both forward and aft fastener columns,
left and right sides, at the STA 259.5
circumferential butt splice; and
corrective actions, including a skin trimout repair and other repairs. 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 115
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Inspections .....................
28 work-hours × $85 per hour = $2,380 per inspection cycle.
We have received no definitive data
that would enable us to provide cost
estimates for the optional skin-trim-out
repair specified in this AD.
We have received no definitive data
that would 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.
asabaliauskas on DSKBBXCHB2PROD with RULES
$0
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
$273,700 per inspection
cycle.
(a) Effective Date
This AD is effective July 25, 2017.
(b) Affected ADs
This AD replaces AD 2007–26–04,
Amendment 39–15306 (72 FR 71216,
December 17, 2007) (‘‘AD 2007–26–04’’).
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 737–53A1267,
Revision 1, dated March 8, 2016 (‘‘ASB 737–
53A1267, R1’’).
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/ebd1cec7b301293e86257
cb30045557a/$FILE/ST01219SE.pdf) 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.
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2007–26–04, Amendment 39–15806 (72
FR 71216, December 17, 2007), and
adding the following new AD:
2017–12–05 The Boeing Company:
Amendment 39–18920; Docket No.
FAA–2016–9188; Directorate Identifier
2016–NM–102–AD.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
Authority: 49 U.S.C. 106(g), 40113, 44701.
We have determined that 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.
■
Jkt 241001
Cost on U.S.
operators
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder indicating that
the forward skin panel at the station (STA)
259.5 circumferential butt splice between
stringers 19L and 24L is subject to
widespread fatigue damage. We are issuing
this AD to prevent cracking of the STA 259.5
circumferential butt splice, which could
result in loss of structural integrity of the
fuselage skin and possible loss of cabin
pressure.
1. The authority citation for part 39
continues to read as follows:
■
§ 39.13
16:57 Jun 19, 2017
$2,380 per inspection
cycle.
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.
Regulatory Findings
VerDate Sep<11>2014
Cost per
product
Parts cost
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Rules and Regulations
(g) Actions for Group 2 Airplanes
For airplanes identified as Group 2 in ASB
737–53A1267, R1: Within 120 days after the
effective date of this AD, inspect the airplane
and do all applicable corrective actions using
a method approved in accordance with the
procedures specified in paragraph (k) of this
AD.
asabaliauskas on DSKBBXCHB2PROD with RULES
(h) Inspections for Group 1 Airplanes
For airplanes identified as Group 1 in ASB
737–53A1267, R1: Except as specified in
paragraph (j)(1) of this AD, at the applicable
time specified in paragraph 1.E.
‘‘Compliance’’ of ASB 737–53A1267, R1, do
the applicable actions specified in
paragraphs (h)(1) and (h)(2) of this AD; and
do all applicable corrective actions; in
accordance with the Accomplishment
Instructions of ASB 737–53A1267, R1, except
as specified in paragraph (j)(2) of this AD and
as provided by paragraph (i) of this AD. Do
all applicable corrective actions before
further flight. Repeat the applicable
inspections specified in paragraph (h)(1) of
this AD thereafter at the applicable intervals
specified paragraph 1.E., ‘‘Compliance,’’ of
ASB 737–53A1267, R1, except as provided
by paragraph (i) of this AD.
(1) Do detailed inspections and high
frequency eddy current (HFEC) surface
inspections of the skin around the fastener
heads for any crack on the forward and aft
fastener columns, left and right sides, at STA
259.5 circumferential butt splice, in
accordance with Parts 1, 2, 6, 7, 8, and 9 of
the Accomplishment Instructions of ASB
737–53A1267, R1, as applicable.
(2) Do a one-time detailed inspection for
any defect of the production countersunk
rivet heads on both forward and aft fastener
columns, left and right sides, at STA 259.5
circumferential butt splice, in accordance
with Part 3 of the Accomplishment
Instructions of ASB 737–53A1267, R1.
(i) Repairs That Terminate Inspections in
Repair Areas
(1) For airplanes identified as Group 1,
Configuration 1, in ASB 737–53A1267, R1:
Doing the skin trim-out repair specified in
Part 5 of the Accomplishment Instructions of
ASB 737–53A1267, R1, terminates the initial
and repetitive inspections required by
paragraph (h) of this AD that are specified in
Part 1 of the Accomplishment Instructions of
ASB 737–53A1267, R1, only; all other
inspections required by paragraph (h) of this
AD must be done, except as provided by
paragraph (i)(2) of this AD.
(2) For airplanes identified as Group 1,
Configuration 1 in ASB 737–53A1267, R1:
Doing the skin repair specified in Part 4 of
the Accomplishment Instructions of ASB
737–53A1267, R1, terminates the initial and
repetitive inspections required by paragraph
(h) of this AD that are specified in Part 1 and
Part 2 of the Accomplishment Instructions of
ASB 737–53A1267, R1, for the repaired area
only; all other inspections required by
paragraph (h) of this AD must be done,
except as provided by paragraph (i)(1) of this
AD.
(j) Exceptions to Service Information
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
ASB 737–53A1267, R1, specifies a
VerDate Sep<11>2014
16:57 Jun 19, 2017
Jkt 241001
compliance time ‘‘after the Revision 1 date of
this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) Although ASB 737–53A1267, R1,
specifies to contact Boeing for appropriate
action, and specifies that action as ‘‘RC’’
(Required for Compliance), this AD requires
repair before further flight using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (l) of this AD. Information may be
emailed to: 9-ANM-LAACO-ACO-AMOCRequests@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, 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) AMOCs approved previously for AD
2007–26–04 are approved as AMOCs for the
corresponding provisions of this AD.
(5) Except as required by paragraph (j)(2)
of this AD: For service information that
contains steps that are labeled as RC, the
provisions of paragraphs (k)(5)(i) and
(k)(5)(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.
(l) Related Information
For more information about this AD,
contact Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles ACO, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
PO 00000
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27979
phone: 562–627–5264; fax: 562–627–5210;
email: jennifer.tsakoumakis@faa.gov.
(m) 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–
53A1267, Revision 1, dated March 8, 2016.
(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 Airplane Directorate,
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 June 2,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–12175 Filed 6–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9574; Directorate
Identifier 2016–NM–063–AD; Amendment
39–18921; AD 2017–12–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A300 series airplanes;
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model A300
C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes); and Model A310 series
airplanes. This AD is intended to
complete certain mandated programs
SUMMARY:
E:\FR\FM\20JNR1.SGM
20JNR1
Agencies
[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Rules and Regulations]
[Pages 27977-27979]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12175]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9188; Directorate Identifier 2016-NM-102-AD;
Amendment 39-18920; AD 2017-12-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2007-26-04 for
certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and
-500 series airplanes. AD 2007-26-04 required repetitive inspections
for cracking of certain fasteners, and repair if necessary; and a
preventive modification, which terminated the repetitive inspections.
This AD removes the mandatory modification; adds repetitive inspections
of the skin for cracking, a one-time inspection for defects of the
production countersunk rivets, and corrective actions if necessary; and
adds an optional skin trim-out repair, which will terminate certain
inspections. This AD was prompted by an evaluation by the design
approval holder (DAH) indicating that certain skin panels are subject
to widespread fatigue damage (WFD). We are issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective July 25, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 25,
2017.
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 Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9188.
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-2016-
9188; 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 AD, 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: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2007-26-04, Amendment 39-15306 (72 FR 71216,
December 17, 2007) (``AD 2007-26-04''). AD 2007-26-04 applied to
certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. The NPRM published in the Federal Register on October 20,
2016 (81 FR 72554) (``the NPRM''). The NPRM was prompted by an
evaluation by the DAH indicating that the forward skin panel at the
station (STA) 259.5 circumferential butt splice between stringers 19L
and 24L is subject to WFD. The NPRM proposed to continue to require
repetitive inspections for cracking around the heads of the fasteners
on the forward fastener row in certain areas of a certain
circumferential butt splice, and repair if necessary. The NPRM also
proposed to add repetitive inspections of the skin for cracking at the
aft fastener column, and a one-time inspection for defects in the
production countersunk rivets, and corrective actions if necessary; and
add an optional skin trim-out repair, which would terminate certain
inspections. We are issuing this AD to prevent cracking of the STA
259.5 circumferential butt splice, which could result in loss of
structural integrity of the fuselage skin and possible loss of cabin
pressure.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Revise Terminating Action
Southwest Airlines (SWA) requested that we revise paragraph (i) of
the proposed AD to specify that doing the optional repairs terminates
the initial and repetitive inspections instead of just the repetitive
inspections. SWA stated that if a terminating repair were installed
prior to the initial inspection, there is no justification for either
the initial or repetitive inspections.
We agree with SWA's request. We have revised paragraph (i) of this
AD to specify that the terminating repairs are applicable to both the
initial and repetitive inspections.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing the supplemental
type certificate (STC) ST01219SE does not affect the actions specified
in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1) of this AD 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 method 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 AD with the changes described previously, and minor editorial
changes. We have determined that these minor changes:
[[Page 27978]]
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 AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1267, Revision 1,
dated March 8, 2016 (``ASB 737-53A1267, R1''). The service information
describes procedures for detailed inspections and high frequency eddy
current (HFEC) surface inspections of the skin around the fastener
heads for any crack on the forward and aft fastener columns, left and
right sides, at STA 259.5 circumferential butt splice; a detailed
inspection for any defect of the production countersunk rivet heads on
both forward and aft fastener columns, left and right sides, at the STA
259.5 circumferential butt splice; and corrective actions, including a
skin trim-out repair and other repairs. 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 115 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...................... 28 work-hours x $85 $0 $2,380 per $273,700 per
per hour = $2,380 inspection cycle. inspection cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the optional skin-trim-out repair specified in this
AD.
We have received no definitive data that would 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.
Regulatory Findings
We have determined that 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 removing Airworthiness Directive (AD)
2007-26-04, Amendment 39-15806 (72 FR 71216, December 17, 2007), and
adding the following new AD:
2017-12-05 The Boeing Company: Amendment 39-18920; Docket No. FAA-
2016-9188; Directorate Identifier 2016-NM-102-AD.
(a) Effective Date
This AD is effective July 25, 2017.
(b) Affected ADs
This AD replaces AD 2007-26-04, Amendment 39-15306 (72 FR 71216,
December 17, 2007) (``AD 2007-26-04'').
(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, as identified in Boeing Alert Service Bulletin 737-
53A1267, Revision 1, dated March 8, 2016 (``ASB 737-53A1267, R1'').
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf)
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 an evaluation by the design approval
holder indicating that the forward skin panel at the station (STA)
259.5 circumferential butt splice between stringers 19L and 24L is
subject to widespread fatigue damage. We are issuing this AD to
prevent cracking of the STA 259.5 circumferential butt splice, which
could result in loss of structural integrity of the fuselage skin
and possible loss of cabin pressure.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 27979]]
(g) Actions for Group 2 Airplanes
For airplanes identified as Group 2 in ASB 737-53A1267, R1:
Within 120 days after the effective date of this AD, inspect the
airplane and do all applicable corrective actions using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD.
(h) Inspections for Group 1 Airplanes
For airplanes identified as Group 1 in ASB 737-53A1267, R1:
Except as specified in paragraph (j)(1) of this AD, at the
applicable time specified in paragraph 1.E. ``Compliance'' of ASB
737-53A1267, R1, do the applicable actions specified in paragraphs
(h)(1) and (h)(2) of this AD; and do all applicable corrective
actions; in accordance with the Accomplishment Instructions of ASB
737-53A1267, R1, except as specified in paragraph (j)(2) of this AD
and as provided by paragraph (i) of this AD. Do all applicable
corrective actions before further flight. Repeat the applicable
inspections specified in paragraph (h)(1) of this AD thereafter at
the applicable intervals specified paragraph 1.E., ``Compliance,''
of ASB 737-53A1267, R1, except as provided by paragraph (i) of this
AD.
(1) Do detailed inspections and high frequency eddy current
(HFEC) surface inspections of the skin around the fastener heads for
any crack on the forward and aft fastener columns, left and right
sides, at STA 259.5 circumferential butt splice, in accordance with
Parts 1, 2, 6, 7, 8, and 9 of the Accomplishment Instructions of ASB
737-53A1267, R1, as applicable.
(2) Do a one-time detailed inspection for any defect of the
production countersunk rivet heads on both forward and aft fastener
columns, left and right sides, at STA 259.5 circumferential butt
splice, in accordance with Part 3 of the Accomplishment Instructions
of ASB 737-53A1267, R1.
(i) Repairs That Terminate Inspections in Repair Areas
(1) For airplanes identified as Group 1, Configuration 1, in ASB
737-53A1267, R1: Doing the skin trim-out repair specified in Part 5
of the Accomplishment Instructions of ASB 737-53A1267, R1,
terminates the initial and repetitive inspections required by
paragraph (h) of this AD that are specified in Part 1 of the
Accomplishment Instructions of ASB 737-53A1267, R1, only; all other
inspections required by paragraph (h) of this AD must be done,
except as provided by paragraph (i)(2) of this AD.
(2) For airplanes identified as Group 1, Configuration 1 in ASB
737-53A1267, R1: Doing the skin repair specified in Part 4 of the
Accomplishment Instructions of ASB 737-53A1267, R1, terminates the
initial and repetitive inspections required by paragraph (h) of this
AD that are specified in Part 1 and Part 2 of the Accomplishment
Instructions of ASB 737-53A1267, R1, for the repaired area only; all
other inspections required by paragraph (h) of this AD must be done,
except as provided by paragraph (i)(1) of this AD.
(j) Exceptions to Service Information
(1) Where paragraph 1.E., ``Compliance,'' of ASB 737-53A1267,
R1, specifies a compliance time ``after the Revision 1 date of this
service bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) Although ASB 737-53A1267, R1, specifies to contact Boeing
for appropriate action, and specifies that action as ``RC''
(Required for Compliance), this AD requires repair before further
flight using a method approved in accordance with the procedures
specified in paragraph (k) of this AD.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (l) of this AD.
Information may be emailed to: 9-ANM-LAACO-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, Los Angeles ACO, to make those findings. To be approved,
the repair method, modification deviation, or alteration deviation
must meet the certification basis of the airplane and the approval
must specifically refer to this AD.
(4) AMOCs approved previously for AD 2007-26-04 are approved as
AMOCs for the corresponding provisions of this AD.
(5) Except as required by paragraph (j)(2) of this AD: For
service information that contains steps that are labeled as RC, the
provisions of paragraphs (k)(5)(i) and (k)(5)(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.
(l) Related Information
For more information about this AD, contact Jennifer
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@faa.gov.
(m) 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 737-53A1267, Revision 1, dated
March 8, 2016.
(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
Airplane Directorate, 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 June 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-12175 Filed 6-19-17; 8:45 am]
BILLING CODE 4910-13-P