Airworthiness Directives; The Boeing Company Airplanes, 30961-30964 [2017-13761]
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Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations
(p) 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 this AD specifies otherwise.
(i) Airbus Service Bulletin A320–52–1073,
Revision 04, dated August 10, 1999.
(ii) Airbus Service Bulletin A320–52–1073,
Revision 05, dated September 28, 2006.
(iii) Airbus Service Bulletin A320–
52A1086, Revision 01, dated September 10,
1999.
(iv) Airbus Service Bulletin A320–52–
1096, Revision 02, dated July 12, 2006.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 19,
2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–13763 Filed 7–3–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0126; Directorate
Identifier 2016–NM–211–AD; Amendment
39–18943; AD 2017–13–13]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
sradovich on DSK3GMQ082PROD with RULES
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–100,
–200, –200C, –300, –400, and –500
series airplanes. This AD was prompted
by reports of frame web cracking at
certain locations. This AD requires
repetitive inspections in certain
SUMMARY:
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locations of the frame web, and
corrective action if necessary. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 9,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 9, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. You
may view this service information at the
FAA, Transport 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Galib Abumeri, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5324; fax: 562–627–5210;
email: galib.abumeri@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. The
NPRM published in the Federal
Register on March 2, 2017 (82 FR
12303) (‘‘the NPRM’’). The NPRM was
prompted by reports of frame web
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30961
cracking at the station (STA) 344 system
penetration holes between stringer S–
22L and stringer S–24L. The NPRM
proposed to require repetitive
inspections in certain locations of the
frame web, and corrective action if
necessary. We are issuing this AD to
detect and correct frame web 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 uncontrolled decompression 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.
Request To Change Inspection and
Corrective Actions for Group 1
Airplanes
Boeing requested that we change the
language in paragraph (g) of the
proposed AD to remove a reference to
Parts 2 and 3 of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 737–53A1354, dated December
2, 2016. Boeing noted that Group 1
airplanes are those that have exceeded
their limit of validity, and that the
inspections are not applicable to those
airplanes. Boeing stated that it believes
the intent of paragraph (g) of the
proposed AD is for the operator to
obtain maintenance actions in
accordance with a method approved by
the FAA. Boeing further pointed out
that the language in paragraph (g) of the
proposed AD allows operators to
perform inspections in accordance with
Boeing Alert Service Bulletin 737–
53A1354, dated December 2, 2016,
rather than in accordance with
paragraph (j) of the proposed AD
(obtaining an alternative method of
compliance).
We agree with the commenter’s
request for the reasons provided. We
have revised paragraph (g) of this AD to
clarify the appropriate actions for Group
1 airplanes.
Request To Correct a Service Bulletin
Number
Boeing requested that we change two
sentences in paragraph (h) of the
proposed AD that refer to ‘‘Boeing Alert
Service Bulletin 757–53A1354.’’ Boeing
noted that the correct service bulletin
number is ‘‘737–53A1354.’’
We agree with the commenter’s
request and have revised paragraph (h)
of this AD accordingly.
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Request To Revise the Proposed AD To
Provide Credit for Removal of the 1Inch Diameter Hole at STA 336 or STA
344
Boeing requested that we add a
paragraph to the proposed AD to
provide credit for previous actions to
remove the 1-inch diameter hole at STA
336 or STA 344. Boeing noted that
Boeing Alert Service Bulletin 737–
53A1354, dated December 2, 2016,
provides an exception for the Part 2
high frequency eddy current (HFEC)
inspections of repaired locations,
provided the repair is the corrective
action for the crack condition, is
approved by the Boeing Organization
Designation Authorization (ODA), and
does not re-install any open hole.
Boeing added that the proposed AD
does not include such language.
We disagree with the request to revise
this AD because it is not necessary.
Paragraph (h) of this AD specifies to do
the applicable inspections and related
investigated and corrective actions in
accordance with Boeing Alert Service
Bulletin 737–53A1354, dated December
2, 2016. The service information already
contains the criteria and language
proposed by Boeing within the required
for compliance (RC) steps in the
Accomplishment Instructions of the
service information. Therefore, this
language does not need to be repeated
in this AD. We have not changed this
AD in this regard.
sradovich on DSK3GMQ082PROD with RULES
Request To Revise the Proposed AD To
Provide Credit for Repairs of the Open
Hole at STA 328
Boeing requested that we add a
paragraph to the proposed AD to
provide credit for previous actions to
repair any cracks at STA 328. Boeing
noted that Boeing Alert Service Bulletin
737–53A1354, dated December 2, 2016,
states that Part 3 HFEC inspections are
not required for the STA 328 frame if
STA 328 was repaired in accordance
with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737–
53A1323. Boeing added that the
proposed AD does not include such
language.
We disagree with the request to revise
this AD because it is not necessary.
Paragraph (h) of this AD specifies to do
the applicable inspections and related
investigated and corrective actions in
accordance with Boeing Alert Service
Bulletin 737–53A1354, dated December
2, 2016. The service information already
contains the criteria and language
proposed by Boeing within the RC steps
in the Accomplishment Instructions of
the service information. Therefore, this
language does not need to be repeated
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16:11 Jul 03, 2017
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in this AD. We have not changed this
AD in this regard.
Request To Revise the Proposed AD To
Provide Credit for Repairs That
Remove or Plug an Open Hole Between
Stringers S–20R and S–22R in the STA
328 Frame Web
Boeing requested that we add a
paragraph to the proposed AD to
provide credit for previous actions to
plug or remove any open hole between
stringers S–20R and S–22R in the STA
328 frame web. Boeing noted that
Boeing Alert Service Bulletin 737–
53A1354, dated December 2, 2016,
states that Part 3 HFEC inspections are
not required at an open hole in the STA
328 frame web if there is an installed
repair that plugs or removes the open
hole between stringers S–20R and S–
22R, and the repair was approved by the
Boeing ODA. Boeing added that the
proposed AD does not include such
language.
We disagree with the request to revise
this AD because it is not necessary.
Paragraph (h) of the proposed AD
specifies to do the applicable
inspections and related investigated and
corrective actions in accordance with
Boeing Alert Service Bulletin 737–
53A1354, dated December 2, 2016. The
service information already contains the
criteria and language proposed by
Boeing within the RC steps in the
Accomplishment Instructions of the
service information. Therefore, this
language does not need to be repeated
in this AD. We have not changed this
AD in this regard.
Request To Change Compliance Times
The European Aviation Safety Agency
(EASA) requested that we change the
compliance times for the initial HFEC
inspections required by paragraph (h) of
the proposed AD (i.e., before 35,000
total flight cycles or within 4,500 flight
cycles) to match the compliance times
specified in Boeing Alert Service
Bulletin 737–53A1323, dated December
6, 2013, (i.e., for Group 2–5 airplanes
with less than 28,300 total flight cycles,
before the accumulation of 20,000 total
flight cycles or within 2,200 flight
cycles). EASA claimed that it would be
desirable to match the compliance
times, as they are both addressing the
same root problem in the same area,
using the same inspection type. EASA
noted that Boeing Alert Service Bulletin
737–53A1323, dated December 6, 2013,
is referenced in an FAA NPRM, Docket
No. FAA–2014–0346 (we note that the
final rule has been published: AD 2015–
23–08, Amendment 39–18324 (80 FR
73949, November 27, 2015)).
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We disagree with the commenter’s
request. The HFEC inspections for the
right side frames included in Boeing
Alert Service Bulletin 737–53A1354,
dated December 2, 2016, were added
based on analysis, not reported
cracking. Boeing Alert Service Bulletin
737–53A1354, dated December 2, 2016
covers specific areas not included in
Boeing Alert Service Bulletin 737–
53A1323, dated December 6, 2013.
Since there have been no reports of
cracking in the applicable inspection
areas on the right side of the airplane,
there is no technical justification to
lower the initial inspection times in this
AD. We have not changed this AD in
this regard.
Effects of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing the supplemental type
certificate (STC) ST01219SE does not
affect the actions specified in the
NPRM.
We concur with the commenter. We
have redesignated paragraph (c) of the
proposed AD as paragraph (c)(1) of this
AD and added paragraph (c)(2) to this
AD to state that installation of STC
ST01219SE does not affect the ability to
accomplish the actions required by this
AD. Therefore, for airplanes on which
STC ST01219SE is installed, a ‘‘change
in product’’ alternative method of
compliance (AMOC) approval request is
not necessary to comply with the
requirements of 14 CFR 39.17.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule 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 final rule.
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
HFEC, detailed, and general visual
inspections in certain locations of the
frame web. This service information is
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Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations
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 82
airplanes of U.S. registry. We estimate
30963
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
HFEC, detailed, and general
visual inspections.
Labor cost
114 work-hours × $85 per
hour = $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 AD.
sradovich on DSK3GMQ082PROD with RULES
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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.
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Parts cost
Jkt 241001
Cost per product
$0
$9,690 per inspection cycle ...
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–13–13 The Boeing Company:
Amendment 39–18943; Docket No.
FAA–2017–0126; Directorate Identifier
2016–NM–211–AD.
(a) Effective Date
This AD is effective August 9, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 737–53A1354,
dated December 2, 2016.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/ebd1cec7b301293e
86257cb30045557a/$FILE/ST01219SE.pdf)
does not affect the ability to accomplish the
actions required by this AD. Therefore, for
airplanes on which STC ST01219SE is
installed, a ‘‘change in product’’ alternative
method of compliance (AMOC) approval
request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
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Cost on U.S.
operators
$794,580 per inspection
cycle.
(e) Unsafe Condition
This AD was prompted by reports of frame
web cracking at station (STA) 344 system
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 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, accomplish
actions to correct the unsafe condition (e.g.
inspections, repairs, and corrective actions),
using a method approved in accordance with
the procedures specified in paragraph (j) of
this AD.
(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
737–53A1354, 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 737–53A1354, 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.
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Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations
(3) Do an HFEC inspection for cracking of
the right side STA 312, STA 328, and STA
344, section 41 lower lobe frames.
sradovich on DSK3GMQ082PROD with RULES
(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, 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 (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.
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(k) Related Information
For more information about this AD,
contact Galib Abumeri, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office (ACO),
3960 Paramount Boulevard, Lakewood, CA
90712–4137; phone: 562–627–5324; fax: 562–
627–5210; email: galib.abumeri@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–
53A1354, dated December 2, 2016.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 21,
2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–13761 Filed 7–3–17; 8:45 am]
the associated Class D and E airspace
areas to match the FAA’s current
aeronautical database. This action does
not affect the charted boundaries or
operating requirements of the airspace.
Effective 0901 UTC, August 17,
2017. The Director of the Federal
Register approves this incorporation by
reference action under Title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.11 and publication of conforming
amendments.
DATES:
FAA Order 7400.11A,
Airspace Designations and Reporting
Points, and subsequent amendments can
be viewed on line at https://
www.faa.gov/air_traffic/publications/.
For further information, you can contact
the Airspace Policy Group, Federal
Aviation Administration, 800
Independence Avenue SW.,
Washington, DC 20591; telephone: 202–
267–8783. The Order is also available
for inspection 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/code_of_federalregulations/ibr_locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Robert LaPlante, Federal Aviation
Administration, Operations Support
Group, Western Service Center, 1601
Lind Avenue SW., Renton, WA 98057;
telephone (425) 203–4566.
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
Authority for This Rulemaking
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2017–0218; Airspace
Docket No. 17–AWP–4]
Amendment of Class D and E
Airspace; Tucson, AZ
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule, technical
amendment.
AGENCY:
This action amends the legal
description of the Class E airspace
designated as an extension, at Ryan
Field, Tucson, AZ, eliminating the
Notice to Airmen (NOTAM) part-time
status. This action also updates the
geographic coordinates of this airport in
SUMMARY:
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it removes
NOTAM part-time information for Class
E airspace designated as an extension,
and amends the geographic coordinates
in the associated Class D and E airspace
for Ryan Field, Tucson, AZ.
E:\FR\FM\05JYR1.SGM
05JYR1
Agencies
[Federal Register Volume 82, Number 127 (Wednesday, July 5, 2017)]
[Rules and Regulations]
[Pages 30961-30964]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-13761]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0126; Directorate Identifier 2016-NM-211-AD;
Amendment 39-18943; AD 2017-13-13]
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 737-100, -200, -200C, -300, -400, and -500
series airplanes. This AD was prompted by reports of frame web cracking
at certain locations. This AD requires repetitive inspections in
certain locations of the frame web, and corrective action if necessary.
We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective August 9, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 9,
2017.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this service information at the
FAA, Transport 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 final rule, the regulatory evaluation, any comments
received, and other information. The address for the Docket Office
(phone: 800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5324; fax: 562-627-5210; email: galib.abumeri@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on March 2, 2017 (82 FR 12303)
(``the NPRM''). The NPRM was prompted by reports of frame web cracking
at the station (STA) 344 system penetration holes between stringer S-
22L and stringer S-24L. The NPRM proposed to require repetitive
inspections in certain locations of the frame web, and corrective
action if necessary. We are issuing this AD to detect and correct frame
web 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 uncontrolled decompression 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.
Request To Change Inspection and Corrective Actions for Group 1
Airplanes
Boeing requested that we change the language in paragraph (g) of
the proposed AD to remove a reference to Parts 2 and 3 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1354, dated December 2, 2016. Boeing noted that Group 1 airplanes
are those that have exceeded their limit of validity, and that the
inspections are not applicable to those airplanes. Boeing stated that
it believes the intent of paragraph (g) of the proposed AD is for the
operator to obtain maintenance actions in accordance with a method
approved by the FAA. Boeing further pointed out that the language in
paragraph (g) of the proposed AD allows operators to perform
inspections in accordance with Boeing Alert Service Bulletin 737-
53A1354, dated December 2, 2016, rather than in accordance with
paragraph (j) of the proposed AD (obtaining an alternative method of
compliance).
We agree with the commenter's request for the reasons provided. We
have revised paragraph (g) of this AD to clarify the appropriate
actions for Group 1 airplanes.
Request To Correct a Service Bulletin Number
Boeing requested that we change two sentences in paragraph (h) of
the proposed AD that refer to ``Boeing Alert Service Bulletin 757-
53A1354.'' Boeing noted that the correct service bulletin number is
``737-53A1354.''
We agree with the commenter's request and have revised paragraph
(h) of this AD accordingly.
[[Page 30962]]
Request To Revise the Proposed AD To Provide Credit for Removal of the
1-Inch Diameter Hole at STA 336 or STA 344
Boeing requested that we add a paragraph to the proposed AD to
provide credit for previous actions to remove the 1-inch diameter hole
at STA 336 or STA 344. Boeing noted that Boeing Alert Service Bulletin
737-53A1354, dated December 2, 2016, provides an exception for the Part
2 high frequency eddy current (HFEC) inspections of repaired locations,
provided the repair is the corrective action for the crack condition,
is approved by the Boeing Organization Designation Authorization (ODA),
and does not re-install any open hole. Boeing added that the proposed
AD does not include such language.
We disagree with the request to revise this AD because it is not
necessary. Paragraph (h) of this AD specifies to do the applicable
inspections and related investigated and corrective actions in
accordance with Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016. The service information already contains the criteria
and language proposed by Boeing within the required for compliance (RC)
steps in the Accomplishment Instructions of the service information.
Therefore, this language does not need to be repeated in this AD. We
have not changed this AD in this regard.
Request To Revise the Proposed AD To Provide Credit for Repairs of the
Open Hole at STA 328
Boeing requested that we add a paragraph to the proposed AD to
provide credit for previous actions to repair any cracks at STA 328.
Boeing noted that Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016, states that Part 3 HFEC inspections are not required
for the STA 328 frame if STA 328 was repaired in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1323. Boeing added that the proposed AD does not include such
language.
We disagree with the request to revise this AD because it is not
necessary. Paragraph (h) of this AD specifies to do the applicable
inspections and related investigated and corrective actions in
accordance with Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016. The service information already contains the criteria
and language proposed by Boeing within the RC steps in the
Accomplishment Instructions of the service information. Therefore, this
language does not need to be repeated in this AD. We have not changed
this AD in this regard.
Request To Revise the Proposed AD To Provide Credit for Repairs That
Remove or Plug an Open Hole Between Stringers S-20R and S-22R in the
STA 328 Frame Web
Boeing requested that we add a paragraph to the proposed AD to
provide credit for previous actions to plug or remove any open hole
between stringers S-20R and S-22R in the STA 328 frame web. Boeing
noted that Boeing Alert Service Bulletin 737-53A1354, dated December 2,
2016, states that Part 3 HFEC inspections are not required at an open
hole in the STA 328 frame web if there is an installed repair that
plugs or removes the open hole between stringers S-20R and S-22R, and
the repair was approved by the Boeing ODA. Boeing added that the
proposed AD does not include such language.
We disagree with the request to revise this AD because it is not
necessary. Paragraph (h) of the proposed AD specifies to do the
applicable inspections and related investigated and corrective actions
in accordance with Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016. The service information already contains the criteria
and language proposed by Boeing within the RC steps in the
Accomplishment Instructions of the service information. Therefore, this
language does not need to be repeated in this AD. We have not changed
this AD in this regard.
Request To Change Compliance Times
The European Aviation Safety Agency (EASA) requested that we change
the compliance times for the initial HFEC inspections required by
paragraph (h) of the proposed AD (i.e., before 35,000 total flight
cycles or within 4,500 flight cycles) to match the compliance times
specified in Boeing Alert Service Bulletin 737-53A1323, dated December
6, 2013, (i.e., for Group 2-5 airplanes with less than 28,300 total
flight cycles, before the accumulation of 20,000 total flight cycles or
within 2,200 flight cycles). EASA claimed that it would be desirable to
match the compliance times, as they are both addressing the same root
problem in the same area, using the same inspection type. EASA noted
that Boeing Alert Service Bulletin 737-53A1323, dated December 6, 2013,
is referenced in an FAA NPRM, Docket No. FAA-2014-0346 (we note that
the final rule has been published: AD 2015-23-08, Amendment 39-18324
(80 FR 73949, November 27, 2015)).
We disagree with the commenter's request. The HFEC inspections for
the right side frames included in Boeing Alert Service Bulletin 737-
53A1354, dated December 2, 2016, were added based on analysis, not
reported cracking. Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016 covers specific areas not included in Boeing Alert
Service Bulletin 737-53A1323, dated December 6, 2013. Since there have
been no reports of cracking in the applicable inspection areas on the
right side of the airplane, there is no technical justification to
lower the initial inspection times in this AD. We have not changed this
AD in this regard.
Effects of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing the supplemental
type certificate (STC) ST01219SE does not affect the actions specified
in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1) of this AD and added paragraph
(c)(2) to this AD to state that installation of STC ST01219SE does not
affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST01219SE is installed, a
``change in product'' alternative method of compliance (AMOC) approval
request is not necessary to comply with the requirements of 14 CFR
39.17.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule 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 final
rule.
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 HFEC, detailed, and general visual inspections in certain
locations of the frame web. This service information is
[[Page 30963]]
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 82 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
----------------------------------------------------------------------------------------------------------------
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 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):
2017-13-13 The Boeing Company: Amendment 39-18943; Docket No. FAA-
2017-0126; Directorate Identifier 2016-NM-211-AD.
(a) Effective Date
This AD is effective August 9, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category, as identified in Boeing Alert Service Bulletin 737-
53A1354, dated December 2, 2016.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of frame web cracking at station
(STA) 344 system 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 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, accomplish actions to correct the
unsafe condition (e.g. inspections, repairs, and corrective
actions), using a method approved in accordance with the procedures
specified in paragraph (j) of this AD.
(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 737-
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 737-53A1354, 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.
[[Page 30964]]
(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, 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 (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
For more information about this AD, contact Galib Abumeri,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-5210;
email: galib.abumeri@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 737-53A1354, dated December 2,
2016.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on June 21, 2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-13761 Filed 7-3-17; 8:45 am]
BILLING CODE 4910-13-P