Airworthiness Directives; The Boeing Company Airplanes, 11132-11134 [2017-01825]
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11132
Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations
Assistant to the President and Chief of
Staff entitle ‘‘regulatory Freeze Pending
Review’’, FNS is delaying the effective
dates by 60 days and extending the
comment period by 30 days for this rule
as noted under the DATES section to
ensure that the public has sufficient
time to review and comment on the
rule.
The January 6, 2017 rule amends the
SNAP regulations to: Exclude military
combat pay from the income of SNAP
households; raise the minimum
standard deduction and the minimum
benefit for small households; eliminate
the cap on the deduction for dependent
care expenses; index resource limits to
inflation; exclude retirement and
education accounts from countable
resources; clarify reporting requirements
under simplified reporting; permit
States to provide transitional benefits to
households leaving State-funded cash
assistance programs; allow States to
establish telephonic and gestured
signature systems; permit States to use
E&T funds to provide job retention
services; and update requirements
regarding the E&T funding cycle. These
provisions are intended to more
accurately reflect needs, reduce barriers
to participation, and improve efficiency
in the administration of the program.
This rule also replaces outdated
language in SNAP certification
regulations with the new program name
and updates procedures for accessing
SNAP benefits in drug and alcohol
treatment centers and group living
arrangements with use of electronic
benefit transfer (EBT) cards. This rule
provides States with regulatory options
for conducting telephone interviews in
lieu of face-to-face interviews and for
averaging student work hours.
Finally, the Department issued a
portion of the rule as an interim final
rule (with a request for additional
comment) that will require that drug
and alcohol treatment and group living
arrangements (GLA) centers to: Submit
completed change report forms to the
State agency when a resident leaves the
center; notify the State agency within 5
days when the center is not able to
provide the resident with their EBT card
at departure; and return EBT cards to
residents with pro-rated benefits based
up on the date of their departure.
To the extent that 5 U.S.C. 553(b)(A)
applies to this action, it is exempt from
notice and comment rulemaking for
good cause and for reasons cited above,
FNS finds that notice and solicitation of
comment regarding the brief extension
of the effective dates and comment
period are impracticable, unnecessary,
or contrary to the public interest
pursuant to 5 U.S.C. 553(b)(B). FNS
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14:42 Feb 17, 2017
Jkt 241001
believes that affected parties need to be
informed as soon as possible of the
extensions and their length.
Dated: February 8, 2017.
Jessica Shahin,
Acting Administrator, Food and Nutrition
Service.
[FR Doc. 2017–03337 Filed 2–17–17; 8:45 am]
BILLING CODE 3410–30–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6426; Directorate
Identifier 2016–NM–023–AD; Amendment
39–18791; AD 2017–02–12]
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 737–300, –400,
and –500 series airplanes. This AD was
prompted by reports of intergranular
cracks on the front spar chord lugs of
the outboard horizontal stabilizer. This
AD requires repetitive inspections of the
front spar chord lugs and lug bores of
the horizontal stabilizer, and repair if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective March 28,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 28, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
P.O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone: 206–544–5000,
extension 1; fax: 206–766–5680;
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–
6426.
DATES:
PO 00000
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Sfmt 4700
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–
6426; 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:
Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5313; fax: 562–627–5210;
email: Payman.Soltani@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
737–300, –400, and –500 series
airplanes. The NPRM published in the
Federal Register on May 10, 2016 (81
FR 28774) (‘‘the NPRM’’). The NPRM
was prompted by reports of
intergranular cracks on the front spar
chord lugs of the outboard horizontal
stabilizer. The NPRM proposed to
require repetitive inspections of the
front spar chord lugs and lug bores of
the horizontal stabilizer, and repair if
necessary. We are issuing this AD to
detect and correct cracking of the front
spar chord lugs of the horizontal
stabilizer. Such cracking could cause
stabilizer instability, adversely affect
controllability of the airplane, and
adversely affect the 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
response to each comment.
Support for the NPRM
Boeing had no objection to the NPRM.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing Supplemental Type
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Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations
Certificate (STC) ST01219SE does not
affect the ability to accomplish the
actions specified in the proposed AD.
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.
Request To Revise Compliance Time
All Nippon Airways (ANA) requested
that we revise paragraph (i) of the
proposed AD to provide a grace period
of 27 months after the effective date of
the AD in which to accomplish the
initial inspection on horizontal
stabilizers, including replacement
horizontal stabilizers. ANA stated that
these revisions would reduce the
burden on operators. ANA proposed
new, complex language for paragraph (i)
of the proposed AD that would
incorporate their proposal.
We partially agree. We agree that the
27-month after the effective date of this
AD grace period applies to replacement
horizontal stabilizers. However, we do
not agree to add a grace period of 27
months to paragraph (i) of this AD or to
incorporate ANA’s proposed language.
We have revised paragraph (i) of this AD
to clarify the provisions to address
ANA’s concern and to align more
closely with the language used in
similar ADs.
The compliance time in paragraph (g)
of this AD applies to all horizontal
stabilizers, including those installed
after the effective date of this AD.
Because the unsafe condition is related
to corrosion, the compliance times in
this AD are measured in months.
Therefore, time accumulated on a
horizontal stabilizer on and off an
airplane applies to the initial
compliance time and the repetitive
inspection interval. A horizontal
stabilizer that is off the airplane when
the next inspection is due is not
required to be inspected until it is ready
to be installed on the airplane.
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:
11133
• 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 737–55A1092, dated August 7,
2015. The service information describes
procedures for inspections for corrosion
and cracking of the front spar chord lugs
of the horizontal stabilizer, and
inspections for corrosion of the lug
bores. 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 346
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspections ........
14 work-hours × $85 per hour = $1,190 per inspection cycle.
$0
Cost per product
Cost on U.S. operators
$1,190 per inspection
cycle.
$411,740 per inspection
cycle
that is likely to exist or develop on
products identified in this rulemaking
action.
Authority for This Rulemaking
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We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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
Regulatory Findings
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
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14:42 Feb 17, 2017
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
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11134
Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations
2017–02–12 The Boeing Company:
Amendment 39–18791; Docket No.
FAA–2016–6426; Directorate Identifier
2016–NM–023–AD.
Compliance): Before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (j) of
this AD.
(a) Effective Date
This AD is effective March 28, 2017.
(i) Parts Installation Limitation
As of the effective date of this AD: A
horizontal stabilizer may be installed on any
airplane, provided all applicable actions
required by the introductory text of
paragraph (g) and paragraphs (g)(1) and (g)(2)
of this AD are done within the compliance
times specified in the introductory text of
paragraph (g) of this AD, and in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–55A1092,
dated August 7, 2015, except as required by
paragraph (h) of this AD.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing
Company Model 737–300, –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/$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 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by reports of
intergranular cracks on the front spar chord
lugs of the outboard horizontal stabilizer. We
are issuing this AD to detect and correct
cracking of the front spar chord lugs of the
horizontal stabilizer. Such cracking could
cause stabilizer instability, adversely affect
controllability of the airplane, and adversely
affect the structural integrity of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Repairs
Within 27 months after the effective date
of this AD: Do the actions required by
paragraphs (g)(1) and (g)(2) of this AD, and
do all applicable repairs, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–55A1092, dated
August 7, 2015, except as required by
paragraph (h) of this AD. Do all applicable
repairs before further flight. Repeat the
inspections specified in paragraphs (g)(1) and
(g)(2) of this AD thereafter at the applicable
intervals specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–55A1092, dated August 7, 2015.
(1) Do a detailed inspection for corrosion
and an ultrasonic inspection for cracking of
the front spar chord lugs of the left and right
horizontal stabilizers.
(2) Do a detailed inspection for corrosion
of the lug bores of the front spar chord of the
left and right horizontal stabilizers.
(h) Service Information Exception
Where Boeing Alert Service Bulletin 737–
55A1092, dated August 7, 2015, specifies to
contact Boeing for appropriate action, and
specifies that action as ‘‘RC’’ (Required for
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14:42 Feb 17, 2017
Jkt 241001
(j) 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 (k) 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) Except as required by paragraph (h) 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 Payman Soltani, Aerospace Engineer,
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5313; fax: 562–627–5210; email:
Payman.Soltani@faa.gov.
(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–
55A1092, dated August 7, 2015.
(ii) Reserved.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone:
206–544–5000, extension 1; fax: 206–766–
5680; Internet: https://
www.myboeingfleet.com.
(4) You may view this service information
at 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 January
17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–01825 Filed 2–17–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9066; Directorate
Identifier 2014–NM–113–AD; Amendment
39–18800; AD 2017–04–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2011–10–
17 for all Airbus Model A300 and A310
series airplanes, and Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model C4–605R Variant F
SUMMARY:
E:\FR\FM\21FER1.SGM
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]]>Agencies
[Federal Register Volume 82, Number 33 (Tuesday, February 21, 2017)]
[Rules and Regulations]
[Pages 11132-11134]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-01825]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6426; Directorate Identifier 2016-NM-023-AD;
Amendment 39-18791; AD 2017-02-12]
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 737-300, -400, and -500 series airplanes. This AD
was prompted by reports of intergranular cracks on the front spar chord
lugs of the outboard horizontal stabilizer. This AD requires repetitive
inspections of the front spar chord lugs and lug bores of the
horizontal stabilizer, and repair if necessary. We are issuing this AD
to address the unsafe condition on these products.
DATES: This AD is effective March 28, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 28,
2017.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone:
206-544-5000, extension 1; fax: 206-766-5680; 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-
6426.
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-
6426; 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: Payman Soltani, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5313; fax: 562-627-5210; email: Payman.Soltani@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 737-300, -400, and -500 series airplanes. The NPRM published in
the Federal Register on May 10, 2016 (81 FR 28774) (``the NPRM''). The
NPRM was prompted by reports of intergranular cracks on the front spar
chord lugs of the outboard horizontal stabilizer. The NPRM proposed to
require repetitive inspections of the front spar chord lugs and lug
bores of the horizontal stabilizer, and repair if necessary. We are
issuing this AD to detect and correct cracking of the front spar chord
lugs of the horizontal stabilizer. Such cracking could cause stabilizer
instability, adversely affect controllability of the airplane, and
adversely affect the 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 response to each comment.
Support for the NPRM
Boeing had no objection to the NPRM.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing Supplemental
Type
[[Page 11133]]
Certificate (STC) ST01219SE does not affect the ability to accomplish
the actions specified in the proposed AD.
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.
Request To Revise Compliance Time
All Nippon Airways (ANA) requested that we revise paragraph (i) of
the proposed AD to provide a grace period of 27 months after the
effective date of the AD in which to accomplish the initial inspection
on horizontal stabilizers, including replacement horizontal
stabilizers. ANA stated that these revisions would reduce the burden on
operators. ANA proposed new, complex language for paragraph (i) of the
proposed AD that would incorporate their proposal.
We partially agree. We agree that the 27-month after the effective
date of this AD grace period applies to replacement horizontal
stabilizers. However, we do not agree to add a grace period of 27
months to paragraph (i) of this AD or to incorporate ANA's proposed
language. We have revised paragraph (i) of this AD to clarify the
provisions to address ANA's concern and to align more closely with the
language used in similar ADs.
The compliance time in paragraph (g) of this AD applies to all
horizontal stabilizers, including those installed after the effective
date of this AD. Because the unsafe condition is related to corrosion,
the compliance times in this AD are measured in months. Therefore, time
accumulated on a horizontal stabilizer on and off an airplane applies
to the initial compliance time and the repetitive inspection interval.
A horizontal stabilizer that is off the airplane when the next
inspection is due is not required to be inspected until it is ready to
be installed on the airplane.
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:
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 737-55A1092, dated August
7, 2015. The service information describes procedures for inspections
for corrosion and cracking of the front spar chord lugs of the
horizontal stabilizer, and inspections for corrosion of the lug bores.
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 346 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.............. 14 work-hours x $85 per $0 $1,190 per $411,740 per
hour = $1,190 per inspection cycle. inspection cycle
inspection cycle.
----------------------------------------------------------------------------------------------------------------
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
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):
[[Page 11134]]
2017-02-12 The Boeing Company: Amendment 39-18791; Docket No. FAA-
2016-6426; Directorate Identifier 2016-NM-023-AD.
(a) Effective Date
This AD is effective March 28, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-300, -
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/$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 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by reports of intergranular cracks on the
front spar chord lugs of the outboard horizontal stabilizer. We are
issuing this AD to detect and correct cracking of the front spar
chord lugs of the horizontal stabilizer. Such cracking could cause
stabilizer instability, adversely affect controllability of the
airplane, and adversely affect the structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Repairs
Within 27 months after the effective date of this AD: Do the
actions required by paragraphs (g)(1) and (g)(2) of this AD, and do
all applicable repairs, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-55A1092, dated
August 7, 2015, except as required by paragraph (h) of this AD. Do
all applicable repairs before further flight. Repeat the inspections
specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at
the applicable intervals specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1092, dated
August 7, 2015.
(1) Do a detailed inspection for corrosion and an ultrasonic
inspection for cracking of the front spar chord lugs of the left and
right horizontal stabilizers.
(2) Do a detailed inspection for corrosion of the lug bores of
the front spar chord of the left and right horizontal stabilizers.
(h) Service Information Exception
Where Boeing Alert Service Bulletin 737-55A1092, dated August 7,
2015, specifies to contact Boeing for appropriate action, and
specifies that action as ``RC'' (Required for Compliance): Before
further flight, repair using a method approved in accordance with
the procedures specified in paragraph (j) of this AD.
(i) Parts Installation Limitation
As of the effective date of this AD: A horizontal stabilizer may
be installed on any airplane, provided all applicable actions
required by the introductory text of paragraph (g) and paragraphs
(g)(1) and (g)(2) of this AD are done within the compliance times
specified in the introductory text of paragraph (g) of this AD, and
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-55A1092, dated August 7, 2015, except as
required by paragraph (h) of this AD.
(j) 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 (k) 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) Except as required by paragraph (h) 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 Payman Soltani,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5313; fax: 562-627-5210; email: Payman.Soltani@faa.gov.
(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 737-55A1092, dated August 7,
2015.
(ii) Reserved.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone: 206-544-5000, extension 1; fax: 206-766-5680; Internet:
https://www.myboeingfleet.com.
(4) You may view this service information at 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 January 17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-01825 Filed 2-17-17; 8:45 am]
BILLING CODE 4910-13-P
