Airworthiness Directives; The Boeing Company Airplanes, 11797-11800 [2017-03265]
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Federal Register / Vol. 82, No. 37 / Monday, February 27, 2017 / Rules and Regulations
FAA–2016–9053; Directorate Identifier
2016–NM–075–AD.
(a) Effective Date
This AD is effective April 3, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 747–8 and 747–8F series
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/pylons.
(e) Unsafe Condition
This AD was prompted by reports of
damaged vapor seals, block seals, and heat
shield seals on the outboard pylons between
the engine strut and aft fairing. We are
issuing this AD to detect and correct heat
damage to the vapor seals between the engine
strut and aft fairing. Such damage could
allow flammable fluid leakage out of the aft
fairing, which could result in an
uncontrolled fire in the engine strut.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
At the later of the times specified in
paragraphs (g)(1) and (g)(2) of this AD: Do a
detailed inspection for heat damage of the
vapor seals on the outboard pylons between
the strut and aft fairing of the numbers 1 and
4 engines, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–54A2246, dated
February 5, 2016. Repeat the inspection
thereafter at intervals not to exceed 1,200
flight cycles.
(1) Before the accumulation of 1,800 total
flight cycles, or within 1,800 flight cycles
after the most recent vapor seal, block seal,
and heat shield seal replacement, whichever
is later.
(2) Within 6 months after the effective date
of this AD.
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(h) Replacement
If during any inspection required by
paragraph (g) of this AD any heat damage of
any vapor seal is found: Before further flight,
replace the vapor seal, heat shield seal, and
block seal with new seals, in accordance with
Part 3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–54A2246,
dated February 5, 2016. Repeat the
inspection required by paragraph (g) of this
AD within 1,800 flight cycles after doing the
replacement, and thereafter at intervals not to
exceed 1,200 flight cycles.
(i) 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
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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 (j) 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) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (i)(4)(ii) 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. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(j) Related Information
For more information about this AD,
contact Tung Tran, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6505; fax: 425–
917–6590; email: tung.tran@faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747–
54A2246, dated February 5, 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;
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
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11797
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 February
10, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03362 Filed 2–24–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3984; Directorate
Identifier 2015–NM–033–AD; Amendment
39–18803; AD 2017–04–08]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2008–13–
12 R1 for certain The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. AD
2008–13–12 R1 required various
repetitive inspections for cracking of a
certain splice of the fuselage, and other
specified and corrective actions if
necessary; and provided for an optional
preventive modification, which
terminated the repetitive inspections.
This new AD adds an inspection to
determine if the existing frame repair
meets all specified requirements; a
modification of a certain splice, which
terminates the repetitive inspections;
reduces certain inspection thresholds
and repetitive intervals; and adds postrepair/post-modification inspections.
This AD was prompted by reports of
additional fatigue cracking of a certain
splice of the fuselage and one report of
a severed frame, due to susceptibility to
widespread fatigue damage (WFD). We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective April 3,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 3, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
SUMMARY:
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Federal Register / Vol. 82, No. 37 / Monday, February 27, 2017 / Rules and Regulations
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. 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–2015–
3984.
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–2015–
3984; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
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
Comments
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
2008–13–12 R1, Amendment 39–15719
(73 FR 67383, November 14, 2008) (‘‘AD
2008–13–12 R1’’). AD 2008–13–12 R1
applied to certain The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. The
SNPRM published in the Federal
Register on November 14, 2016 (81 FR
79395). We preceded the SNPRM with
a notice of proposed rulemaking
(NPRM) that published in the Federal
Register on October 9, 2015 (80 FR
61133). The NPRM proposed to
continue to require the actions of AD
2008–13–12 R1. The NPRM also
proposed to add, for certain airplanes,
an inspection to determine if the
existing frame repair meets all specified
requirements, and for certain other
airplanes, a new modification of the
upper-frame-to-side-frame splice, which
would terminate the repetitive
inspections. The NPRM also proposed
to reduce certain inspection thresholds
and repetitive intervals. The NPRM was
prompted by reports of additional
fatigue cracking of the upper-frame-toside-frame splice of the fuselage, and
one report of a severed frame. The
SNPRM proposed to add post-repair/
post-modification inspections that were
not included in the NPRM. We are
issuing this AD to detect and correct
fatigue cracking of the upper-frame-toside-frame splice of the fuselage, which
could result in reduced structural
integrity of the frame and adjacent lap
joint, causing increased loading in the
fuselage skin, which will accelerate skin
crack growth and could result in
decompression of the airplane.
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
The commenter, Stephanie Reid, agreed
that the airplanes should be inspected.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed, except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1261, Revision 1,
dated January 30, 2015. The service
information describes procedures for
various repetitive inspections for
cracking of the upper-frame-to-sideframe splice of the fuselage, a
preventive modification to prevent
WFD, an inspection to determine if the
existing frame repair meets all specified
requirements, and corrective actions.
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 391
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Retained inspections
from AD 2008–13–12
R1.
New inspections ............
New modification ...........
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1 We
Cost on U.S.
operators
$0
Between $1,530 and
$3,230 per inspection
cycle.
Between $598,230 and
$1,262,930, per inspection cycle.
$0
Between 18 and 38 work-hours × $85 per hour,
depending on airplane configuration = between $1,530 and $3,230 per inspection
cycle.
213 work-hours × $85 per hour, $18,105 per inspection cycle.
256 work-hours × $85 per hour = $21,760 ........
Cost per product
$18,105 per inspection
cycle.
$21,760 ........................
Up to $7,079,055, per
inspection cycle.
Up to $8,508,160.
Parts cost
(1)
currently have no specific cost estimates associated with the parts necessary for the modification.
We have received no definitive data
that would enable us to provide a cost
estimate 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,
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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
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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 have determined that 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
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
removing Airworthiness Directive (AD)
2008–13–12 R1, Amendment 39–15719
(73 FR 67383, November 14, 2008), and
adding the following new AD:
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■
2017–04–08 The Boeing Company:
Amendment 39–18803; Docket No.
FAA–2015–3984; Directorate Identifier
2015–NM–033–AD.
(a) Effective Date
This AD is effective April 3, 2017.
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(b) Affected ADs
This AD replaces AD 2008–13–12 R1,
Amendment 39–15719 (73 FR 67383,
November 14, 2008) (‘‘AD 2008–13–12 R1’’).
(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 737–53A1261,
Revision 1, dated January 30, 2015.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/BE866B732F6CF31086257
B9700692796?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 reports of
additional fatigue cracking of the upperframe-to-side-frame splice of the fuselage,
and one report of a severed frame due to
susceptibility to widespread fatigue damage
(WFD). We are issuing this AD to detect and
correct fatigue cracking of the upper-frameto-side-frame splice of the fuselage, which
could result in reduced structural integrity of
the frame and adjacent lap joint, causing
increased loading in the fuselage skin, which
will accelerate skin crack growth and could
result in decompression of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Corrective
Actions for Certain Airplanes
(1) For Groups 1 through 3, Configurations
1, 3, 4, and 5 airplanes; Group 7,
Configurations 1, 3, 4, and 5 airplanes;
Groups 4 through 6, Configurations 1, 3, 4,
and 6 airplanes; and Groups 8 through 11,
Configurations 1, 3, 4, and 6 airplanes; as
identified in Boeing Alert Service Bulletin
737–53A1261, Revision 1, dated January 30,
2015: Do the actions specified in paragraphs
(g)(1)(i) and (g)(1)(ii) of this AD, and all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1261,
Revision 1, dated January 30, 2015, except as
required by paragraph (i)(3) of this AD. Do all
applicable corrective actions before further
flight.
(i) At the applicable time specified in
Tables 1, 2, 3, 5, 6, and 8 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1261, Revision 1, dated
January 30, 2015, except as required by
paragraphs (i)(1) and (i)(2) of this AD: Do
medium frequency eddy current inspections
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11799
for cracking of the upper-frame-to-side-frame
splice of the fuselage.
(ii) Repeat the inspections specified in
paragraph (g)(1)(i) of this AD at the
applicable time specified in Tables 1, 2, 3, 5,
6, and 8 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1261,
Revision 1, dated January 30, 2015, until the
preventive modification required by
paragraph (k) of this AD, or a terminating
action specified in paragraph (l) of this AD,
has been accomplished. The inspections are
terminated for the repaired or modified areas
only.
(2) For Groups 4 through 6, Configurations
2 and 5 airplanes; and Groups 8 through 11,
Configurations 2 and 5 airplanes; as
identified in Boeing Alert Service Bulletin
737–53A1261, Revision 1, dated January 30,
2015: Do the actions specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD, and all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1261,
Revision 1, dated January 30, 2015, except as
required by paragraph (i)(3) of this AD. Do all
applicable corrective actions before further
flight.
(i) At the applicable time specified in
Tables 4 and 7 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1261, Revision 1, dated
January 30, 2015, except as required by
paragraphs (i)(1) and (i)(2) of this AD: Do a
detailed inspection to determine if the
existing frame repair meets all requirements
specified in Boeing Alert Service Bulletin
737–53A1261, Revision 1, dated January 30,
2015, and for any frame repair that does meet
all requirements, do detailed and high
frequency eddy current (HFEC) inspections
for cracking of the existing frame repairs.
(ii) Repeat the inspections for cracking
specified in paragraph (g)(2)(i) of this AD at
the applicable time specified in Tables 4 and
7 of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1261,
Revision 1, dated January 30, 2015.
(h) Post-Repair and Post-Modification
Actions for Certain Airplanes
For Group 1, Configurations 2 and 6
airplanes; Group 2, Configurations 2 and 6
airplanes; Group 3, Configurations 2 and 6
airplanes; and Group 7, Configurations 2 and
6 airplanes; as identified in Boeing Alert
Service Bulletin 737–53A1261, Revision 1,
dated January 30, 2015: Within 120 days after
the effective date of this AD, do post-repair
and post-modification actions using a
method approved in accordance with the
procedures specified in paragraph (n) of this
AD.
(i) Exceptions to Service Bulletin
Specifications
(1) Where Boeing Alert Service Bulletin
737–53A1261, Revision 1, dated January 30,
2015, specifies a compliance time ‘‘after the
Revision 1 date of this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(2) Where the ‘‘Condition’’ column of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1261,
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Revision 1, dated January 30, 2015, specifies
a condition based on whether an airplane has
or has not been inspected, this AD bases the
condition on whether an airplane has or has
not been inspected as of the effective date of
this AD.
(3) Where Boeing Alert Service Bulletin
737–53A1261, Revision 1, dated January 30,
2015, specifies to contact Boeing for repair
instructions: Before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (n) of
this AD.
(j) Post-Repair and Post-Modification
Inspections
For Groups 4 through 6, Configurations 1,
3, 4, 6, 7, 8, 9, and 10 airplanes; and Groups
8 through 11, Configurations 1, 3, 4, 6, 7, 8,
9, and 10 airplanes; as identified in Boeing
Alert Service Bulletin 737–53A1261,
Revision 1, dated January 30, 2015: Except as
provided by paragraphs (i)(1) and (i)(2) of
this AD, at the applicable time specified in
Tables 12 through 17 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1261, Revision 1, dated
January 30, 2015; do the post-repair/postmodification inspections, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1261,
Revision 1, dated January 30, 2015, except as
required by paragraph (i)(3) of this AD. Do all
applicable corrective actions before further
flight.
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(k) Preventive Modification for Certain
Airplanes
For Groups 4 through 6, Configurations 1,
3, 4, and 6 airplanes; and Groups 8 through
11, Configurations 1, 3, 4, and 6 airplanes; as
identified in Boeing Alert Service Bulletin
737–53A1261, Revision 1, dated January 30,
2015: Except as provided by paragraphs (i)(1)
and (i)(2) of this AD, at the applicable time
specified in Tables 3, 5, 6, and 8 in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1261, Revision 1, dated
January 30, 2015, do the preventive
modification, including HFEC inspections for
cracking and applicable corrective actions, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1261, Revision 1,
dated January 30, 2015, except as required by
paragraph (i)(3) of this AD. Do all applicable
corrective actions before further flight.
Accomplishing the modification required by
this paragraph terminates the inspections
required by paragraph (g)(1) of this AD for
the modified area only.
(l) Terminating Action
(1) For Groups 4 through 6, Configurations
1, 3, 4, and 6 airplanes; and Groups 8 through
11, Configurations 1, 3, 4, and 6 airplanes; as
identified in Boeing Alert Service Bulletin
737–53A1261, Revision 1, dated January 30,
2015: Accomplishing the preventive
modification, including HFEC inspections for
cracking and applicable corrective actions, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1261, Revision 1,
dated January 30, 2015, except as required by
paragraph (i)(3) of this AD, terminates the
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inspections required by paragraph (g)(1) of
this AD for the modified area only.
(2) For Groups 4 through 6, Configurations
3 and 6 airplanes; and Groups 8 through 11,
Configurations 3 and 6 airplanes; as
identified in Boeing Alert Service Bulletin
737–53A1261, Revision 1, dated January 30,
2015: Accomplishing the repair, including
HFEC inspections for cracking and applicable
corrective actions, in accordance with Part 3
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1261,
Revision 1, dated January 30, 2015, except as
required by paragraph (i)(3) of this AD,
terminates the repetitive inspections required
by paragraph (g)(1) of this AD, and the
preventive modification required by
paragraph (k) of this AD, for the repaired area
only.
(3) Accomplishment of the repair or the
preventive modification specified in Boeing
Message M–7200–02–1294, dated August 20,
2002, before the effective date of this AD
terminates the repetitive inspections required
by paragraph (g)(1) of this AD and the
preventive modification required by
paragraph (k) of this AD for the repaired or
modified area only.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the
inspections required by paragraph (g) of this
AD, if those inspections were performed
before the effective date of this AD using
Boeing Alert Service Bulletin 737–53A1261,
dated January 19, 2006, which was
incorporated by reference in AD 2008–13–12,
Amendment 39–15575 (73 FR 38905, July 8,
2008) (‘‘AD 2008–13–12’’).
(2) This paragraph provides credit for the
modification specified in paragraphs (k) and
(l)(1) of this AD, if the modification was
performed before the effective date of this AD
using Boeing Alert Service Bulletin 737–
53A1261, dated January 19, 2006, which was
incorporated by reference in AD 2008–13–12.
(3) This paragraph provides credit for
repairs specified in paragraphs (l)(2) of this
AD, if those repairs were performed before
the effective date of this AD using Boeing
Alert Service Bulletin 737–53A1261, dated
January 19, 2006, which was incorporated by
reference in AD 2008–13–12.
(n) 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 (o)(1) 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
PO 00000
Frm 00012
Fmt 4700
Sfmt 9990
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. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2008–13–12
and AD 2008–13–12 R1 are approved as
AMOCs for the corresponding provisions of
paragraph (g) of this AD.
(o) Related Information
(1) 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.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(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 the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737–
53A1261, Revision 1, dated January 30, 2015.
(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;
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 February
1, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03265 Filed 2–24–17; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 82, Number 37 (Monday, February 27, 2017)]
[Rules and Regulations]
[Pages 11797-11800]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03265]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3984; Directorate Identifier 2015-NM-033-AD;
Amendment 39-18803; AD 2017-04-08]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2008-13-12 R1
for certain The Boeing Company Model 737-100, -200, -200C, -300, -400,
and -500 series airplanes. AD 2008-13-12 R1 required various repetitive
inspections for cracking of a certain splice of the fuselage, and other
specified and corrective actions if necessary; and provided for an
optional preventive modification, which terminated the repetitive
inspections. This new AD adds an inspection to determine if the
existing frame repair meets all specified requirements; a modification
of a certain splice, which terminates the repetitive inspections;
reduces certain inspection thresholds and repetitive intervals; and
adds post-repair/post-modification inspections. This AD was prompted by
reports of additional fatigue cracking of a certain splice of the
fuselage and one report of a severed frame, due to susceptibility to
widespread fatigue damage (WFD). We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective April 3, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 3,
2017.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes,
[[Page 11798]]
Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd.,
MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; Internet
https://www.myboeingfleet.com. 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-2015-3984.
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-2015-
3984; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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 supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD 2008-13-12 R1, Amendment 39-15719
(73 FR 67383, November 14, 2008) (``AD 2008-13-12 R1''). AD 2008-13-12
R1 applied to certain The Boeing Company Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes. The SNPRM published in the
Federal Register on November 14, 2016 (81 FR 79395). We preceded the
SNPRM with a notice of proposed rulemaking (NPRM) that published in the
Federal Register on October 9, 2015 (80 FR 61133). The NPRM proposed to
continue to require the actions of AD 2008-13-12 R1. The NPRM also
proposed to add, for certain airplanes, an inspection to determine if
the existing frame repair meets all specified requirements, and for
certain other airplanes, a new modification of the upper-frame-to-side-
frame splice, which would terminate the repetitive inspections. The
NPRM also proposed to reduce certain inspection thresholds and
repetitive intervals. The NPRM was prompted by reports of additional
fatigue cracking of the upper-frame-to-side-frame splice of the
fuselage, and one report of a severed frame. The SNPRM proposed to add
post-repair/post-modification inspections that were not included in the
NPRM. We are issuing this AD to detect and correct fatigue cracking of
the upper-frame-to-side-frame splice of the fuselage, which could
result in reduced structural integrity of the frame and adjacent lap
joint, causing increased loading in the fuselage skin, which will
accelerate skin crack growth and could result in decompression of the
airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. The commenter,
Stephanie Reid, agreed that the airplanes should be inspected.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed, except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1261, Revision 1,
dated January 30, 2015. The service information describes procedures
for various repetitive inspections for cracking of the upper-frame-to-
side-frame splice of the fuselage, a preventive modification to prevent
WFD, an inspection to determine if the existing frame repair meets all
specified requirements, and corrective actions. 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 391 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
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD Between 18 and 38 work- $0 Between $1,530 and Between $598,230
2008-13-12 R1. hours x $85 per hour, $3,230 per and $1,262,930,
depending on airplane inspection cycle. per inspection
configuration = cycle.
between $1,530 and
$3,230 per inspection
cycle.
New inspections................ 213 work[dash]hours x $0 $18,105 per Up to $7,079,055,
$85 per hour, $18,105 inspection cycle. per inspection
per inspection cycle. cycle.
New modification............... 256 work-hours x $85 (\1\) $21,760........... Up to $8,508,160.
per hour = $21,760.
----------------------------------------------------------------------------------------------------------------
\1\ We currently have no specific cost estimates associated with the parts necessary for the modification.
We have received no definitive data that would enable us to provide
a cost estimate 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
[[Page 11799]]
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 have determined that 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 removing Airworthiness Directive (AD)
2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008), and
adding the following new AD:
2017-04-08 The Boeing Company: Amendment 39-18803; Docket No. FAA-
2015-3984; Directorate Identifier 2015-NM-033-AD.
(a) Effective Date
This AD is effective April 3, 2017.
(b) Affected ADs
This AD replaces AD 2008-13-12 R1, Amendment 39-15719 (73 FR
67383, November 14, 2008) (``AD 2008-13-12 R1'').
(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-
53A1261, Revision 1, dated January 30, 2015.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?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 reports of additional fatigue cracking
of the upper-frame-to-side-frame splice of the fuselage, and one
report of a severed frame due to susceptibility to widespread
fatigue damage (WFD). We are issuing this AD to detect and correct
fatigue cracking of the upper-frame-to-side-frame splice of the
fuselage, which could result in reduced structural integrity of the
frame and adjacent lap joint, causing increased loading in the
fuselage skin, which will accelerate skin crack growth and could
result in decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Corrective Actions for Certain Airplanes
(1) For Groups 1 through 3, Configurations 1, 3, 4, and 5
airplanes; Group 7, Configurations 1, 3, 4, and 5 airplanes; Groups
4 through 6, Configurations 1, 3, 4, and 6 airplanes; and Groups 8
through 11, Configurations 1, 3, 4, and 6 airplanes; as identified
in Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated
January 30, 2015: Do the actions specified in paragraphs (g)(1)(i)
and (g)(1)(ii) of this AD, and all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015,
except as required by paragraph (i)(3) of this AD. Do all applicable
corrective actions before further flight.
(i) At the applicable time specified in Tables 1, 2, 3, 5, 6,
and 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as
required by paragraphs (i)(1) and (i)(2) of this AD: Do medium
frequency eddy current inspections for cracking of the upper-frame-
to-side-frame splice of the fuselage.
(ii) Repeat the inspections specified in paragraph (g)(1)(i) of
this AD at the applicable time specified in Tables 1, 2, 3, 5, 6,
and 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1261, Revision 1, dated January 30, 2015, until the
preventive modification required by paragraph (k) of this AD, or a
terminating action specified in paragraph (l) of this AD, has been
accomplished. The inspections are terminated for the repaired or
modified areas only.
(2) For Groups 4 through 6, Configurations 2 and 5 airplanes;
and Groups 8 through 11, Configurations 2 and 5 airplanes; as
identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1,
dated January 30, 2015: Do the actions specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD, and all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January
30, 2015, except as required by paragraph (i)(3) of this AD. Do all
applicable corrective actions before further flight.
(i) At the applicable time specified in Tables 4 and 7 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1261, Revision 1, dated January 30, 2015, except as required
by paragraphs (i)(1) and (i)(2) of this AD: Do a detailed inspection
to determine if the existing frame repair meets all requirements
specified in Boeing Alert Service Bulletin 737-53A1261, Revision 1,
dated January 30, 2015, and for any frame repair that does meet all
requirements, do detailed and high frequency eddy current (HFEC)
inspections for cracking of the existing frame repairs.
(ii) Repeat the inspections for cracking specified in paragraph
(g)(2)(i) of this AD at the applicable time specified in Tables 4
and 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1261, Revision 1, dated January 30, 2015.
(h) Post-Repair and Post-Modification Actions for Certain Airplanes
For Group 1, Configurations 2 and 6 airplanes; Group 2,
Configurations 2 and 6 airplanes; Group 3, Configurations 2 and 6
airplanes; and Group 7, Configurations 2 and 6 airplanes; as
identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1,
dated January 30, 2015: Within 120 days after the effective date of
this AD, do post-repair and post-modification actions using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD.
(i) Exceptions to Service Bulletin Specifications
(1) Where Boeing Alert Service Bulletin 737-53A1261, Revision 1,
dated January 30, 2015, specifies a compliance time ``after the
Revision 1 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where the ``Condition'' column of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261,
[[Page 11800]]
Revision 1, dated January 30, 2015, specifies a condition based on
whether an airplane has or has not been inspected, this AD bases the
condition on whether an airplane has or has not been inspected as of
the effective date of this AD.
(3) Where Boeing Alert Service Bulletin 737-53A1261, Revision 1,
dated January 30, 2015, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (n) of this
AD.
(j) Post-Repair and Post-Modification Inspections
For Groups 4 through 6, Configurations 1, 3, 4, 6, 7, 8, 9, and
10 airplanes; and Groups 8 through 11, Configurations 1, 3, 4, 6, 7,
8, 9, and 10 airplanes; as identified in Boeing Alert Service
Bulletin 737-53A1261, Revision 1, dated January 30, 2015: Except as
provided by paragraphs (i)(1) and (i)(2) of this AD, at the
applicable time specified in Tables 12 through 17 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261,
Revision 1, dated January 30, 2015; do the post-repair/post-
modification inspections, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1261, Revision
1, dated January 30, 2015, except as required by paragraph (i)(3) of
this AD. Do all applicable corrective actions before further flight.
(k) Preventive Modification for Certain Airplanes
For Groups 4 through 6, Configurations 1, 3, 4, and 6 airplanes;
and Groups 8 through 11, Configurations 1, 3, 4, and 6 airplanes; as
identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1,
dated January 30, 2015: Except as provided by paragraphs (i)(1) and
(i)(2) of this AD, at the applicable time specified in Tables 3, 5,
6, and 8 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1261, Revision 1, dated January 30, 2015, do the
preventive modification, including HFEC inspections for cracking and
applicable corrective actions, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1261, Revision 1, dated January 30, 2015, except as required by
paragraph (i)(3) of this AD. Do all applicable corrective actions
before further flight. Accomplishing the modification required by
this paragraph terminates the inspections required by paragraph
(g)(1) of this AD for the modified area only.
(l) Terminating Action
(1) For Groups 4 through 6, Configurations 1, 3, 4, and 6
airplanes; and Groups 8 through 11, Configurations 1, 3, 4, and 6
airplanes; as identified in Boeing Alert Service Bulletin 737-
53A1261, Revision 1, dated January 30, 2015: Accomplishing the
preventive modification, including HFEC inspections for cracking and
applicable corrective actions, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1261, Revision 1, dated January 30, 2015, except as required by
paragraph (i)(3) of this AD, terminates the inspections required by
paragraph (g)(1) of this AD for the modified area only.
(2) For Groups 4 through 6, Configurations 3 and 6 airplanes;
and Groups 8 through 11, Configurations 3 and 6 airplanes; as
identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1,
dated January 30, 2015: Accomplishing the repair, including HFEC
inspections for cracking and applicable corrective actions, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1261, Revision 1, dated January 30,
2015, except as required by paragraph (i)(3) of this AD, terminates
the repetitive inspections required by paragraph (g)(1) of this AD,
and the preventive modification required by paragraph (k) of this
AD, for the repaired area only.
(3) Accomplishment of the repair or the preventive modification
specified in Boeing Message M-7200-02-1294, dated August 20, 2002,
before the effective date of this AD terminates the repetitive
inspections required by paragraph (g)(1) of this AD and the
preventive modification required by paragraph (k) of this AD for the
repaired or modified area only.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the inspections required
by paragraph (g) of this AD, if those inspections were performed
before the effective date of this AD using Boeing Alert Service
Bulletin 737-53A1261, dated January 19, 2006, which was incorporated
by reference in AD 2008-13-12, Amendment 39-15575 (73 FR 38905, July
8, 2008) (``AD 2008-13-12'').
(2) This paragraph provides credit for the modification
specified in paragraphs (k) and (l)(1) of this AD, if the
modification was performed before the effective date of this AD
using Boeing Alert Service Bulletin 737-53A1261, dated January 19,
2006, which was incorporated by reference in AD 2008-13-12.
(3) This paragraph provides credit for repairs specified in
paragraphs (l)(2) of this AD, if those repairs were performed before
the effective date of this AD using Boeing Alert Service Bulletin
737-53A1261, dated January 19, 2006, which was incorporated by
reference in AD 2008-13-12.
(n) 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 (o)(1) 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 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. For a repair method to be approved, the repair
must meet the certification basis of the airplane, and the approval
must specifically refer to this AD.
(4) AMOCs approved for AD 2008-13-12 and AD 2008-13-12 R1 are
approved as AMOCs for the corresponding provisions of paragraph (g)
of this AD.
(o) Related Information
(1) 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.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.
(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 the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated
January 30, 2015.
(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;
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 February 1, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03265 Filed 2-24-17; 8:45 am]
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