Airworthiness Directives; The Boeing Company Airplanes, 39511-39513 [2017-17202]
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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
sradovich on DSK3GMQ082PROD with RULES
(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
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (g) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(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;
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/ibrlocations.html.
Issued in Renton, Washington, on August
8, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–17204 Filed 8–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0131; Product
Identifier 2016–NM–186–AD; Amendment
39–18996; AD 2017–17–06]
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 certain
The Boeing Company Model 737–300,
–400, and –500 series airplanes. This
AD was prompted by a report of fatigue
cracking found in a certain fuselage
(k) Related Information
frame common to the water tank
For more information about this AD,
contact Payman Soltani, Aerospace Engineer, support intercostal clip located between
certain stringers. This AD requires
Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
inspections for any cracking of a certain
Lakewood, CA 90712–4137; phone: 562–627– fuselage frame, and repair if necessary.
5313; fax: 562–627–5210; email:
We are issuing this AD to address the
payman.soltani@faa.gov.
unsafe condition on these products.
(l) Material Incorporated by Reference
DATES: This AD is effective September
25, 2017.
(1) The Director of the Federal Register
The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
approved the incorporation by reference
paragraph under 5 U.S.C. 552(a) and 1 CFR
of a certain publication listed in this AD
part 51.
as of September 25, 2017.
(2) You must use this service information
ADDRESSES: For service information
as applicable to do the actions required by
identified in this final rule, contact
this AD, unless the AD specifies otherwise.
Boeing Commercial Airplanes,
(i) Boeing Alert Service Bulletin 737–
Attention: Contractual & Data Services
57A1332, dated January 3, 2017.
(ii) Reserved.
(C&DS), 2600 Westminster Blvd., MC
VerDate Sep<11>2014
16:12 Aug 18, 2017
Jkt 241001
SUMMARY:
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
39511
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. 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.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0131.
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–
0131; 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 certain The Boeing Company
Model 737–300, –400, and –500 series
airplanes. The NPRM published in the
Federal Register on March 23, 2017 (82
FR 14835). The NPRM was prompted by
a report of fatigue cracking found in a
certain fuselage frame common to the
water tank support intercostal clip
located between certain stringers. The
NPRM proposed to require inspections
for any cracking of a certain fuselage
frame, and repair if necessary. We are
issuing this AD to detect and correct
fatigue cracking that could grow in size
and result in a severed frame. Multiple
adjacent severed frames would result in
reduced structural integrity of the
airplane.
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
E:\FR\FM\21AUR1.SGM
21AUR1
39512
Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
response to each comment. Boeing
supported the NPRM.
not necessary to comply with the
requirements of 14 CFR 39.17.
Related Service Information Under 1
CFR Part 51
Effect of Winglets on Accomplishment
of the Proposed Actions
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 change 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.
We reviewed Boeing Alert Service
Bulletin 737–53A1357, dated August 9,
2016. The service information describes
procedures for inspections for any
cracking of a certain fuselage frame, and
repair if necessary. 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.
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) 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
Costs of Compliance
We estimate that this AD affects 140
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Inspection .................
2 work-hours × $85 per hour = $170 per
inspection cycle ........................................
We estimate the following costs to do
any necessary repairs that would be
Parts cost
Cost per product
$0
$170 per inspection
cycle.
required based on the results of the
inspection. We have no way of
Cost on U.S. operators
$23,800 per inspection cycle.
determining the number of aircraft that
might need this repair:
ON-CONDITION COSTS
Action
Labor cost
Repair ..............................................
18 work-hours × $85 per hour = $1,530 ...................................................
sradovich on DSK3GMQ082PROD 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,
VerDate Sep<11>2014
16:12 Aug 18, 2017
Jkt 241001
Parts cost
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),
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Frm 00022
Fmt 4700
Sfmt 4700
Cost per
product
$100
$1,630
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
E:\FR\FM\21AUR1.SGM
21AUR1
Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–17–06 The Boeing Company:
Amendment 39–18996; Docket No.
FAA–2017–0131; Product Identifier
2016–NM–186–AD.
(a) Effective Date
This AD is effective September 25, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–300, –400, and –500
series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin
737–53A1357, dated August 9, 2016.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/ebd1cec7b301293e86257
cb30045557a/$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.
(e) Unsafe Condition
This AD was prompted by a report of
fatigue cracking found in a certain fuselage
frame common to the water tank support
intercostal clip located between certain
stringers. We are issuing this AD to detect
and correct cracking, which could grow in
size and result in a severed frame. Multiple
adjacent severed frames would result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
sradovich on DSK3GMQ082PROD with RULES
(g) Inspection
Before the accumulation of 34,000 total
flight cycles or within 6,000 flight cycles
after the effective date of this AD, whichever
occurs later, do a high frequency eddy
current (HFEC) inspection for any cracking in
the fuselage frame at station (STA) 947.5
common to the water tank support intercostal
clip located between stringers S–24R and S–
25R, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1357, dated August 9, 2016.
(1) If no cracking is found, repeat the
inspection thereafter at intervals not to
exceed 12,000 flight cycles.
(2) If any cracking is found: Before further
flight, repair in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1357, dated August
9, 2016.
VerDate Sep<11>2014
16:12 Aug 18, 2017
Jkt 241001
(h) Terminating Action
Accomplishing the repair in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1357,
dated August 9, 2016, terminates the
inspection requirements of paragraph (g) 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) 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
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) For service information that contains
steps that are labeled as Required for
Compliance (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
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:
galib.abumeri@faa.gov.
(k) 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.
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
39513
(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–
53A1357, dated August 9, 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 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 August
8, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–17202 Filed 8–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9520; Product
Identifier 2016–NM–163–AD; Amendment
39–18987; AD 2017–16–10]
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 777 airplanes.
This AD was prompted by reports of
cracks on the underwing longerons.
This AD requires repetitive inspections
of the left and right side underwing
longerons for any crack, and related
investigative and corrective actions if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective September
25, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 25, 2017.
DATES:
E:\FR\FM\21AUR1.SGM
21AUR1
Agencies
[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)]
[Rules and Regulations]
[Pages 39511-39513]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17202]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0131; Product Identifier 2016-NM-186-AD; Amendment
39-18996; AD 2017-17-06]
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 certain
The Boeing Company Model 737-300, -400, and -500 series airplanes. This
AD was prompted by a report of fatigue cracking found in a certain
fuselage frame common to the water tank support intercostal clip
located between certain stringers. This AD requires inspections for any
cracking of a certain fuselage frame, and repair if necessary. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective September 25, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
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 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-
0131.
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-
0131; 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 certain The Boeing Company
Model 737-300, -400, and -500 series airplanes. The NPRM published in
the Federal Register on March 23, 2017 (82 FR 14835). The NPRM was
prompted by a report of fatigue cracking found in a certain fuselage
frame common to the water tank support intercostal clip located between
certain stringers. The NPRM proposed to require inspections for any
cracking of a certain fuselage frame, and repair if necessary. We are
issuing this AD to detect and correct fatigue cracking that could grow
in size and result in a severed frame. Multiple adjacent severed frames
would result in reduced structural integrity of the airplane.
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
[[Page 39512]]
response to each comment. Boeing supported the NPRM.
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) 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 final rule with the change 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.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1357, dated August
9, 2016. The service information describes procedures for inspections
for any cracking of a certain fuselage frame, and repair if necessary.
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 140 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection........................ 2 work-hours x $85 per $0 $170 per inspection $23,800 per inspection cycle.
hour = $170 per. cycle.
inspection cycle..........
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspection. We have no
way of determining the number of aircraft that might need this repair:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair..................................... 18 work-hours x $85 per hour = $100 $1,630
$1,530.
----------------------------------------------------------------------------------------------------------------
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.
[[Page 39513]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-17-06 The Boeing Company: Amendment 39-18996; Docket No. FAA-
2017-0131; Product Identifier 2016-NM-186-AD.
(a) Effective Date
This AD is effective September 25, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-300, -400,
and -500 series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 737-53A1357, dated
August 9, 2016.
(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 a report of fatigue cracking found in a
certain fuselage frame common to the water tank support intercostal
clip located between certain stringers. We are issuing this AD to
detect and correct cracking, which could grow in size and result in
a severed frame. Multiple adjacent severed frames would result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
Before the accumulation of 34,000 total flight cycles or within
6,000 flight cycles after the effective date of this AD, whichever
occurs later, do a high frequency eddy current (HFEC) inspection for
any cracking in the fuselage frame at station (STA) 947.5 common to
the water tank support intercostal clip located between stringers S-
24R and S-25R, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1357, dated August 9, 2016.
(1) If no cracking is found, repeat the inspection thereafter at
intervals not to exceed 12,000 flight cycles.
(2) If any cracking is found: Before further flight, repair in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1357, dated August 9, 2016.
(h) Terminating Action
Accomplishing the repair in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1357, dated
August 9, 2016, terminates the inspection requirements of paragraph
(g) 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) 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) For service information that contains steps that are labeled
as Required for Compliance (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
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: galib.abumeri@faa.gov.
(k) 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 737-53A1357, dated August 9,
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
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 August 8, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-17202 Filed 8-18-17; 8:45 am]
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