Airworthiness Directives; The Boeing Company Airplanes, 35628-35630 [2017-15477]
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35628
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
the clothing should be in contrast to the
color of the restraint system. The ES–2re
jacket is sufficient for torso clothing,
although a form-fitting shirt may be
used in addition if desired.
(3) ES–2re ATD lateral
instrumentation: The rib-module linear
slides are directional, i.e., deflection
occurs in either a positive or negative
ATD y-axis direction. The modules
must be installed such that the moving
end of the rib module is toward the
front of the airplane. The three
abdominal-force sensors must be
installed such that they are on the side
of the ATD toward the front of the
airplane.
f. The combined horizontal/vertical
test, required by § 25.562(b)(1) and these
special conditions, must be conducted
with a Hybrid II ATD (49 CFR part 572,
subpart B, as specified in § 25.562), or
equivalent, occupying each seat
position.
g. Restraint systems:
(1) If inflatable restraint systems are
used, they must be active during all
dynamic tests conducted to show
compliance with § 25.562.
(2) The design and installation of
seatbelt buckles must prevent
unbuckling due to applied inertial
forces, or impact of the hands or arms
of the occupant during an emergency
landing.
2. Additional performance measures
applicable to tests and rational analysis
conducted to show compliance with
§§ 25.562 and 25.785 for side-facing
seats:
a. Body-to-body contact: Contact
between the head, pelvis, torso, or
shoulder area of one ATD with the
adjacent-seated ATD’s head, pelvis,
torso, or shoulder area is not allowed.
Contact during rebound is allowed.
b. Thoracic: The deflection of any of
the ES–2re ATD upper, middle, and
lower ribs must not exceed 1.73 in. (44
mm). Data must be processed as defined
in Federal Motor Vehicle Safety
Standards (FMVSS) 571.214.
c. Abdominal: The sum of the
measured ES–2re ATD front, middle,
and rear abdominal forces must not
exceed 562 lb (2,500 N). Data must be
processed as defined in FMVSS
571.214.
d. Pelvic: The pubic symphysis force
measured by the ES–2re ATD must not
exceed 1,350 lb (6,000 N). Data must be
processed as defined in FMVSS
571.214.
e. Leg: Axial rotation of the upper-leg
(femur) must be limited to 35 degrees in
either direction from the nominal seated
position.
f. Neck: As measured by the ES–2re
ATD and filtered at Channel Frequency
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Class 600 as defined in SAE J211,
‘‘Instrumentation for Impact Test—Part
1—Electronic Instrumentation.’’
(1) The upper-neck tension force at
the occipital condyle (O.C.) location
must be less than 405 lb (1,800 N).
(2) The upper-neck compression force
at the O.C. location must be less than
405 lb (1,800 N).
(3) The upper-neck bending torque
about the ATD x-axis at the O.C.
location must be less than 1,018 in-lb
(115 Nm).
(4) The upper-neck resultant shear
force at the O.C. location must be less
than 186 lb (825 N).
g. Occupant (ES–2re ATD) retention:
The pelvic restraint must remain on the
ES–2re ATD’s pelvis during the impact
and rebound phases of the test. The
upper-torso restraint straps (if present)
must remain on the ATD’s shoulder
during the impact.
h. Occupant (ES–2re ATD) support:
(1) Pelvis excursion: The load-bearing
portion of the bottom of the ATD pelvis
must not translate beyond the edges of
its seat’s bottom seat-cushion
supporting structure.
(2) Upper-torso support: The lateral
flexion of the ATD torso must not
exceed 40 degrees from the normal
upright position during the impact.
Issued in Renton, Washington, on July 13,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–16099 Filed 7–31–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0330; Directorate
Identifier 2017–NM–016–AD; Amendment
39–18972; AD 2017–15–12]
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 certain
The Boeing Company Model 737–300,
–400, and –500 series airplanes. This
AD was prompted by an evaluation by
the design approval holder (DAH)
indicating that the lower skin at the skin
lap splice lower fastener row is subject
to widespread fatigue damage (WFD).
SUMMARY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
This AD requires repetitive inspections
for cracking in the skin lap splice at the
lower fastener row, and repair if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective September 5,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 5, 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. Boeing Alert
Service Bulletin 737–53A1365, dated
January 23, 2017, is also available on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2017–0330.
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–
0330; 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:
James Guo, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5357; fax: 562–627–5210;
email: james.guo@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
E:\FR\FM\01AUR1.SGM
01AUR1
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
Federal Register on May 1, 2017 (82 FR
20288). The NPRM was prompted by an
evaluation by the DAH indicating that
the lower skin at the skin lap splice
lower fastener row is subject to WFD.
The NPRM proposed to require
repetitive inspections for cracking in the
skin lap splice at the lower fastener row,
and repair if necessary.
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.
Supportive Comment
Boeing stated that it concurred with
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 request. 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
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
35629
• Do not add any additional burden
upon the public than was already
proposed in 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 737–53A1365, dated January
23, 2017. The service information
describes procedures for eddy current
inspections for cracking at the skin lap
splice in the lower fastener row, 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 126
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspection .........
84 work-hours × $85 per hour =
$7,140 per 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.
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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.
VerDate Sep<11>2014
17:30 Jul 31, 2017
Jkt 241001
Cost per product
$0
Cost on U.S. operators
$7,140 per inspection cycle ..........
$899,640 per inspection cycle.
Regulatory Findings
Adoption of the Amendment
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Frm 00007
Fmt 4700
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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):
■
2017–15–12 The Boeing Company:
Amendment 39–18972; Docket No.
FAA–2017–0330; Directorate Identifier
2017–NM–016–AD.
(a) Effective Date
This AD is effective September 5, 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,
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01AUR1
35630
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
as identified in Boeing Alert Service Bulletin
737–53A1365, dated January 23, 2017.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/EBD1CEC7B301293
E86257CB30045557A?OpenDocument&
Highlight=st01219se) does not affect the
ability to accomplish the actions required by
this AD. Therefore, for airplanes on which
STC ST01219SE is installed, a ‘‘change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 53; Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder indicating that
the lower skin at the skin lap splice lower
fastener row is subject to widespread fatigue
damage. We are issuing this AD to detect and
correct cracks in the lower skin, which, if not
detected, could link up, resulting in reduced
structural integrity of the airplane and
consequent uncontrolled decompression of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Except as provided by paragraph (i) of this
AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1365, dated
January 23, 2017: Do external eddy current
inspections at stringer S–14 on the left and
right sides of the airplane (S–14L and S–14R)
for any crack in the skin lap splice at the
lower fastener row, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1365, dated January
23, 2017. Repeat the inspections thereafter at
the applicable times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1365, dated January 23,
2017.
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(h) Repair
If any crack is found during any inspection
required by paragraph (g) of this AD, repair
before further flight using a method approved
in accordance with the procedures specified
in paragraph (j) of this AD. Although Boeing
Alert Service Bulletin 737–53A1365, dated
January 23, 2017, specifies to contact Boeing
for appropriate action and specifies that
action as ‘‘RC’’ (Required for Compliance),
this AD requires repair as specified in this
paragraph.
(i) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
737–53A1365, dated January 23, 2017,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
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17:30 Jul 31, 2017
Jkt 241001
(2) The Condition column of Table 1 and
Table 2 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1365,
dated January 23, 2017, refers to total flight
cycles ‘‘at the original issue date of this
service bulletin.’’ This AD, however, applies
to the airplanes with the specified total flight
cycles as of the effective date 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-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 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.
(k) Related Information
For more information about this AD,
contact James Guo, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5357; fax: 562–627–5210; email: james.guo@
faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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Frm 00008
Fmt 4700
Sfmt 4700
(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–
53A1365, dated January 23, 2017.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport 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 July 14,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–15477 Filed 7–31–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0640; Directorate
Identifier 2017–CE–020–AD; Amendment
39–18969; AD 2017–15–09]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries GmbH Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Diamond Aircraft Industries GmbH
Model DA 42 airplanes. This AD
requires installing engine exhaust pipe
clamps with spring washers, repetitively
inspecting the engine exhaust pipe
clamps for cracks, and replacing the
clamps if found cracked. This AD was
prompted by cracks in the affected
engine exhaust pipes, which could
cause failure of the propeller regulating
valve because of hot exhaust gases
coming from the fractured pipes. We are
issuing this AD to correct the unsafe
condition on these products.
SUMMARY:
E:\FR\FM\01AUR1.SGM
01AUR1
Agencies
[Federal Register Volume 82, Number 146 (Tuesday, August 1, 2017)]
[Rules and Regulations]
[Pages 35628-35630]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15477]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0330; Directorate Identifier 2017-NM-016-AD;
Amendment 39-18972; AD 2017-15-12]
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 certain
The Boeing Company Model 737-300, -400, and -500 series airplanes. This
AD was prompted by an evaluation by the design approval holder (DAH)
indicating that the lower skin at the skin lap splice lower fastener
row is subject to widespread fatigue damage (WFD). This AD requires
repetitive inspections for cracking in the skin lap splice at the lower
fastener row, and repair if necessary. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective September 5, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September 5,
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. Boeing Alert Service Bulletin 737-53A1365,
dated January 23, 2017, is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0330.
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-
0330; 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: James Guo, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5357; fax: 562-627-5210; email: james.guo@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
[[Page 35629]]
Federal Register on May 1, 2017 (82 FR 20288). The NPRM was prompted by
an evaluation by the DAH indicating that the lower skin at the skin lap
splice lower fastener row is subject to WFD. The NPRM proposed to
require repetitive inspections for cracking in the skin lap splice at
the lower fastener row, and repair if necessary.
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.
Supportive Comment
Boeing stated that it concurred with 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 request. 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 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 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 737-53A1365, dated
January 23, 2017. The service information describes procedures for eddy
current inspections for cracking at the skin lap splice in the lower
fastener row, 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 126 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
----------------------------------------------------------------------------------------------------------------
Inspection................. 84 work-hours x $85 $0 $7,140 per inspection $899,640 per
per hour = $7,140 cycle. inspection cycle.
per 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):
2017-15-12 The Boeing Company: Amendment 39-18972; Docket No. FAA-
2017-0330; Directorate Identifier 2017-NM-016-AD.
(a) Effective Date
This AD is effective September 5, 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,
[[Page 35630]]
as identified in Boeing Alert Service Bulletin 737-53A1365, dated
January 23, 2017.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=st01219se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 53; Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder indicating that the lower skin at the skin lap splice lower
fastener row is subject to widespread fatigue damage. We are issuing
this AD to detect and correct cracks in the lower skin, which, if
not detected, could link up, resulting in reduced structural
integrity of the airplane and consequent uncontrolled decompression
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Except as provided by paragraph (i) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1365, dated January 23, 2017:
Do external eddy current inspections at stringer S-14 on the left
and right sides of the airplane (S-14L and S-14R) for any crack in
the skin lap splice at the lower fastener row, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1365, dated January 23, 2017. Repeat the inspections
thereafter at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1365, dated
January 23, 2017.
(h) Repair
If any crack is found during any inspection required by
paragraph (g) of this AD, repair before further flight using a
method approved in accordance with the procedures specified in
paragraph (j) of this AD. Although Boeing Alert Service Bulletin
737-53A1365, dated January 23, 2017, specifies to contact Boeing for
appropriate action and specifies that action as ``RC'' (Required for
Compliance), this AD requires repair as specified in this paragraph.
(i) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 737-53A1365, dated
January 23, 2017, specifies a compliance time ``after the original
issue date of this service bulletin,'' this AD requires compliance
within the specified compliance time after the effective date of
this AD.
(2) The Condition column of Table 1 and Table 2 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1365,
dated January 23, 2017, refers to total flight cycles ``at the
original issue date of this service bulletin.'' This AD, however,
applies to the airplanes with the specified total flight cycles as
of the effective date 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-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 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.
(k) Related Information
For more information about this AD, contact James Guo, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960
Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5357;
fax: 562-627-5210; email: james.guo@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 737-53A1365, dated January 23,
2017.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
(4) You may view this service information at the FAA, Transport
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 July 14, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-15477 Filed 7-31-17; 8:45 am]
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