Airworthiness Directives; the Boeing Company Airplanes, 12303-12305 [2017-03996]
Download as PDF
Federal Register / Vol. 82, No. 40 / Thursday, March 2, 2017 / Proposed Rules
26, 2014; or Revision D, dated February 26,
2016.
Federal Aviation Administration
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170 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 ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone: 516–228–7300; fax: 516–794–
5531. 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(i) Related Information
pmangrum on DSK3GDR082PROD with PROPOSALS
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
AD CF–2016–27, dated September 14, 2016,
for related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2017–0125.
(2) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone: 416–375–4000; fax: 416–375–
4539; email: thd.qseries@
aero.bombardier.com; Internet: https://
www.bombardier.com. 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.
Issued in Renton, Washington, on February
22, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03995 Filed 3–1–17; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
13:51 Mar 01, 2017
DEPARTMENT OF TRANSPORTATION
Jkt 241001
14 CFR Part 39
[Docket No. FAA–2017–0126; Directorate
Identifier 2016–NM–211–AD]
RIN 2120–AA64
Airworthiness Directives; the Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–100,
–200, –200C, –300, –400, and –500
series airplanes. This proposed AD was
prompted by reports of frame web
cracking at certain locations. This
proposed AD would require repetitive
inspections in certain locations of the
frame web, and corrective action if
necessary. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by April 17, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0126.
DATES:
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12303
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–
0126; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Gaetano Settineri, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6577;
fax: 425–917–6590; email:
gaetano.settineri@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2017–0126; Directorate Identifier 2016–
NM–211–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received reports of frame
web cracking at the station (STA) 344
system penetration holes between
stringer S–22L and stringer S–24L.
There were 11 reports of cracking on
airplanes having accumulated between
25,713 and 68,093 total flight cycles and
between 55,058 and 76,358 total flight
hours. Crack lengths ranged from 0.78
inch to 1.57 inches. Frame cracking is
the result of fatigue caused by cyclic
pressurization of the fuselage.
Undetected cracks can grow until the
frames sever. Ultimately, multiple
adjacent frames could be severed, or a
severed frame could exist near cracks in
E:\FR\FM\02MRP1.SGM
02MRP1
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Federal Register / Vol. 82, No. 40 / Thursday, March 2, 2017 / Proposed Rules
the chem-milled fuselage skin. This
condition, if not corrected, could result
in uncontrolled decompression of the
airplane.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1354, dated December
2, 2016. The service information
describes procedures for repetitive high
frequency eddy current (HFEC),
detailed, and general visual inspections
in certain locations of the frame web.
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.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Between this Proposed AD
and the Service Information.’’ For
information on the procedures and
compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0126.
The phrase ‘‘corrective actions’’ is
used in this proposed AD. Corrective
actions correct or address any condition
found. Corrective actions in an AD
could include, for example, repairs.
Differences Between This Proposed AD
and the Service Information
Boeing Alert Service Bulletin 737–
53A1354, dated December 2, 2016,
specifies to contact the manufacturer for
certain instructions, but this proposed
AD would require using repair methods,
modification deviations, and alteration
deviations in one of the following ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Costs of Compliance
We estimate that this proposed AD
affects 82 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
HFEC, detailed, and general visual
inspections.
114 work-hours × $85 per hour =
$9,690 per inspection cycle.
pmangrum on DSK3GDR082PROD with PROPOSALS
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
VerDate Sep<11>2014
13:51 Mar 01, 2017
Jkt 241001
Cost per
product
Parts cost
$0
$9,690 per inspection
cycle.
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 this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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Fmt 4702
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Cost on U.S.
operators
$794,580 per inspection
cycle.
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):
■
The Boeing Company: Docket No. FAA–
2017–0126; Directorate Identifier 2016–
NM–211–AD.
(a) Comments Due Date
We must receive comments by April 17,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 737–100, –200, –200C, –300, –400,
and –500 series airplanes, certificated in any
category, as identified in Boeing Alert
Service Bulletin 737–53A1354, dated
December 2, 2016.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of frame
web cracking at station (STA) 344 system
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02MRP1
Federal Register / Vol. 82, No. 40 / Thursday, March 2, 2017 / Proposed Rules
penetration holes between stringer S–22L
and stringer S–24L. We are issuing this AD
to detect and correct such cracking, which
could grow in size until frames sever.
Multiple adjacent severed frames, or a
severed frame near cracks in the chem-milled
fuselage skin, could result in an uncontrolled
decompression of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Group 1 Airplanes: Inspections and
Corrective Actions
For airplanes identified as Group 1 in
Boeing Alert Service Bulletin 737–53A1354,
dated December 2, 2016: Within 120 days
after the effective date of this AD, inspect the
left- and right-side fuselage frames, as
specified in Parts 2 and 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1354, dated
December 2, 2016, and do all applicable
corrective actions, using a method approved
in accordance with the procedures specified
in paragraph (j) of this AD. Do all applicable
corrective actions before further flight.
pmangrum on DSK3GDR082PROD with PROPOSALS
(h) Group 2 Airplanes: Repetitive
Inspections and Corrective Actions
For airplanes identified as Group 2 in
Boeing Alert Service Bulletin 737–53A1354,
dated December 2, 2016: At the applicable
times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1354, dated December 2,
2016, except as required by paragraph (i)(1)
of this AD: Do the inspections specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this
AD, and do all applicable corrective actions,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–53A1354, dated December 2, 2016,
except as required by paragraph (i)(2) of this
AD. Repeat the inspections thereafter at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A1354, dated December 2,
2016. Do all applicable corrective actions
before further flight.
(1) Do high frequency eddy current (HFEC),
detailed, and general visual inspections for
cracking of the left side section 41 lower lobe
frames, between STA 268.25 and STA 360.
(2) Do detailed and general visual
inspections for cracking of the right side
section 41 lower lobe frames, between STA
268.25 and STA 360.
(3) Do an HFEC inspection for cracking of
the right side STA 312, STA 328, and STA
344, section 41 lower lobe frames.
(i) Service Information Exceptions
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1354,
dated December 2, 2016, specifies a
compliance time ‘‘after the original date of
this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin
737–53A1354, dated December 2, 2016,
specifies to contact Boeing for repair
instructions, and specifies that action as
Required for Compliance (RC), this AD
VerDate Sep<11>2014
13:51 Mar 01, 2017
Jkt 241001
requires repair before further flight using a
method approved in accordance with the
procedures specified in paragraph (j) of this
AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-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, Seattle
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 (i)(2)
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
(1) For more information about this AD,
contact Gaetano Settineri, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6577; fax: 425–917–6590; email:
gaetano.settineri@faa.gov.
(2) 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. You may view this
PO 00000
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Fmt 4702
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12305
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.
Issued in Renton, Washington, on February
21, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03996 Filed 3–1–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0156; Directorate
Identifier 2017–CE–003–AD]
RIN 2120–AA64
Airworthiness Directives; ZLIN
AIRCRAFT a.s. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for ZLIN
AIRCRAFT a.s. Model Z–242L airplanes
that would supersede AD 2003–11–12.
This proposed AD results from
mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority of another country to
identify and correct an unsafe condition
on an aviation product. The MCAI
describes the unsafe condition as a need
to incorporate new revisions into the
Limitations section, Chapter 9, of the
FAA-approved maintenance program
(e.g., maintenance manual) to impose
new or more restrictive life limits on
critical components. We are issuing this
proposed AD to require actions to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by April 17, 2017.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
DATES:
E:\FR\FM\02MRP1.SGM
02MRP1
Agencies
[Federal Register Volume 82, Number 40 (Thursday, March 2, 2017)]
[Proposed Rules]
[Pages 12303-12305]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03996]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0126; Directorate Identifier 2016-NM-211-AD]
RIN 2120-AA64
Airworthiness Directives; the Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and
-500 series airplanes. This proposed AD was prompted by reports of
frame web cracking at certain locations. This proposed AD would require
repetitive inspections in certain locations of the frame web, and
corrective action if necessary. We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 17, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may
view this referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the
availability of this material at the FAA, call 425-227-1221. It is also
available on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2017-0126.
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-
0126; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Gaetano Settineri, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6577; fax: 425-917-6590; email: gaetano.settineri@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-0126;
Directorate Identifier 2016-NM-211-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of frame web cracking at the station (STA)
344 system penetration holes between stringer S-22L and stringer S-24L.
There were 11 reports of cracking on airplanes having accumulated
between 25,713 and 68,093 total flight cycles and between 55,058 and
76,358 total flight hours. Crack lengths ranged from 0.78 inch to 1.57
inches. Frame cracking is the result of fatigue caused by cyclic
pressurization of the fuselage. Undetected cracks can grow until the
frames sever. Ultimately, multiple adjacent frames could be severed, or
a severed frame could exist near cracks in
[[Page 12304]]
the chem-milled fuselage skin. This condition, if not corrected, could
result in uncontrolled decompression of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016. The service information describes procedures for
repetitive high frequency eddy current (HFEC), detailed, and general
visual inspections in certain locations of the frame web. 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.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information.'' For information on the procedures and compliance times,
see this service information at https://www.regulations.gov by searching
for and locating Docket No. FAA-2017-0126.
The phrase ``corrective actions'' is used in this proposed AD.
Corrective actions correct or address any condition found. Corrective
actions in an AD could include, for example, repairs.
Differences Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016,
specifies to contact the manufacturer for certain instructions, but
this proposed AD would require using repair methods, modification
deviations, and alteration deviations in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD affects 82 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
HFEC, detailed, and general 114 work-hours x $0 $9,690 per $794,580 per
visual inspections. $85 per hour = inspection cycle. inspection cycle.
$9,690 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 proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
The Boeing Company: Docket No. FAA-2017-0126; Directorate Identifier
2016-NM-211-AD.
(a) Comments Due Date
We must receive comments by April 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category, as identified in Boeing Alert Service Bulletin 737-
53A1354, dated December 2, 2016.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of frame web cracking at station
(STA) 344 system
[[Page 12305]]
penetration holes between stringer S-22L and stringer S-24L. We are
issuing this AD to detect and correct such cracking, which could
grow in size until frames sever. Multiple adjacent severed frames,
or a severed frame near cracks in the chem-milled fuselage skin,
could result in an uncontrolled decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Group 1 Airplanes: Inspections and Corrective Actions
For airplanes identified as Group 1 in Boeing Alert Service
Bulletin 737-53A1354, dated December 2, 2016: Within 120 days after
the effective date of this AD, inspect the left- and right-side
fuselage frames, as specified in Parts 2 and 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016, and do all applicable corrective actions, using a
method approved in accordance with the procedures specified in
paragraph (j) of this AD. Do all applicable corrective actions
before further flight.
(h) Group 2 Airplanes: Repetitive Inspections and Corrective Actions
For airplanes identified as Group 2 in Boeing Alert Service
Bulletin 737-53A1354, dated December 2, 2016: At the applicable
times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1354, dated December 2, 2016, except as
required by paragraph (i)(1) of this AD: Do the inspections
specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, and
do all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
53A1354, dated December 2, 2016, except as required by paragraph
(i)(2) of this AD. Repeat the inspections thereafter at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 757-53A1354, dated December 2, 2016.
Do all applicable corrective actions before further flight.
(1) Do high frequency eddy current (HFEC), detailed, and general
visual inspections for cracking of the left side section 41 lower
lobe frames, between STA 268.25 and STA 360.
(2) Do detailed and general visual inspections for cracking of
the right side section 41 lower lobe frames, between STA 268.25 and
STA 360.
(3) Do an HFEC inspection for cracking of the right side STA
312, STA 328, and STA 344, section 41 lower lobe frames.
(i) Service Information Exceptions
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1354, dated December 2, 2016, specifies a
compliance time ``after the original date of this service
bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016, specifies to contact Boeing for repair
instructions, and specifies that action as Required for Compliance
(RC), this AD requires repair before further flight using a method
approved in accordance with the procedures specified in paragraph
(j) of this AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-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, Seattle 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 (i)(2) 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
(1) For more information about this AD, contact Gaetano
Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone:
425-917-6577; fax: 425-917-6590; email: gaetano.settineri@faa.gov.
(2) 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. 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.
Issued in Renton, Washington, on February 21, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03996 Filed 3-1-17; 8:45 am]
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