Airworthiness Directives; The Boeing Company Airplanes, 24475-24479 [2017-10286]
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Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090; email: doug.rudolph@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2017–0005, dated
January 10, 2017, for related information. The
MCAI can be found in the AD docket on the
Internet at https://www.regulations.gov/
document?D=FAA-2017-0156-0002.
sradovich on DSK3GMQ082PROD with RULES
(i) 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.
(3) The following service information was
approved for IBR on July 5, 2017 (the
effective date of this AD).
(i) Chapter 9, Airworthiness Limitations,
Revision No. 22, dated March 15, 2016, of
ZLIN AIRCRAFT a.s. Z 242 L DOC. No.
003.22.1 Maintenance Manual—Vol. I.
(ii) Moravan-Aeroplanes a.s. Mandatory
Service Bulletin Z 142C/17a, Z 242L/37a—
Rev. 1, dated October 31, 2000.
(4) The following service information was
approved for IBR on June 5, 2003 (68 FR
32629, June 2, 2003).
(i) Moravan Mandatory Service Bulletin Z
242L/38a—Rev.1, April 15, 2003.
(ii) Reserved.
(5) For service information identified in
ˇ ˇ
this AD, contact ZLIN AIRCRAFT a.s., Letiste
1887, 765 02 Otrokovice, Czech Republic,
telephone: +420 725 266 711; fax: +420 226
013 830; email: info@zlinaircraft.eu, Internet:
https://www.zlinaircraft.eu.
(6) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call 816–329–4148. In
addition, you can access this service
information on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–0156.
(7) 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.
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Issued in Kansas City, Missouri, on May
15, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–10406 Filed 5–26–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6666; Directorate
Identifier 2015–NM–124–AD; Amendment
39–18881; AD 2017–10–07]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–400
series airplanes. This AD was prompted
by an evaluation by the design approval
holder (DAH), which indicates that the
aft fuselage skin is subject to
widespread fatigue damage (WFD), and
reports of aft fuselage skin cracking.
This AD requires repetitive inspections
to detect cracking of the aft fuselage
skin, inspections to detect missing or
loose fasteners and any disbonding or
cracking of bonded doublers, permanent
repairs of time-limited repairs, related
investigative and corrective actions if
necessary, and skin panel replacement.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective July 5, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 5, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone: 562–797–1717; Internet:
https://www.myboeingfleet.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6666.
SUMMARY:
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24475
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6666; 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:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email:
jennifer.tsakoumakis@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 Boeing Model 737–400
series airplanes. The NPRM published
in the Federal Register on May 13, 2016
(81 FR 29809) (‘‘the NPRM’’). The
NPRM was prompted by an evaluation
by the DAH, which indicates that the aft
fuselage skin is subject to WFD, and
reports of aft fuselage skin cracking. The
NPRM proposed to require repetitive
inspections to detect cracking of the aft
fuselage skin, inspections to detect
missing or loose fasteners and any
disbonding or cracking of bonded
doublers, permanent repairs of timelimited repairs, related investigative and
corrective actions if necessary, and skin
panel replacement. We are issuing this
AD to prevent cracking in the aft
fuselage skin along the longitudinal
edges of the bonded skin doubler, which
could result in possible rapid
decompression and reduced structural
integrity of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Specify Repair Procedures
Boeing requested that we revise the
proposed AD to address repairs that are
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installed on the airplane for reasons
other than chem-mill cracking. Boeing
provided suggested language for the AD.
We do not agree with Boeing’s
request. Paragraph 3.B.1 in the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–
53–1187, Revision 3, dated July 10, 2015
(‘‘SASB 737–53–1187 R3’’), which is the
referenced source of service information
in this AD, already addresses the issue
raised by Boeing. SASB 737–53–1187
R3 does not make a distinction between
repairs installed for chem-mill cracking
and repairs installed for other reasons.
Therefore, repairs that are installed for
any reason, provided they meet the
service information criteria, are already
addressed. We have not changed this
AD in this regard.
sradovich on DSK3GMQ082PROD with RULES
Request To Revise Compliance Time in
Paragraph (h)(4) of the Proposed AD
Boeing requested that we revise the
compliance time in paragraph (h)(4) of
the proposed AD from the time
specified in SASB 737–53–1187 R3, to
a time approved by the FAA through the
alternative method of compliance
(AMOC) process.
Boeing provided examples of how
replacing skin panels at certain
compliance times would require further
skin panel replacement before reaching
the airplane limit of validity. Boeing
explained that the NPRM proposed skin
panel replacement at 60,000 total flight
cycles; therefore, an FAA approval to
adjust the compliance time from total
flight cycles to cycles after skin panel
replacement would be required.
We partially agree with Boeing’s
request. Airplanes that have had a skin
replacement with a production skin
panel, as distinguished from an
improved-design kit skin panel, prior to
53,000 total flight cycles may be eligible
for an adjustment of the inspection
threshold. Currently, such an
adjustment of the AD compliance time
is not delegated to Boeing’s authorized
representatives, and the change must be
approved by the FAA. However, we
consider the number of airplanes
affected by this scenario to be quite
small. Therefore, we have decided to
approve such changes to the compliance
times on a case-by-case basis using the
procedures specified in paragraph (n)(1)
of this AD. Although we agree with the
comment, we have not changed this AD
in this regard.
Request To Reference Part 6 of the
Service Information
Boeing requested that we revise
paragraphs (i)(1)(ii), (i)(2)(ii), and (j) of
the proposed AD by specifying doing
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part 6 of the service information. Boeing
stated that specifying the service
information part reference would make
the language consistent with paragraph
(g) of the proposed AD, which specifies
the service information part reference.
We agree with Boeing’s request. These
changes will increase the paragraphs’
clarity. We have revised paragraphs
(i)(1)(ii), (i)(2)(ii), and (j) of this AD
accordingly.
Request To Revise Paragraph (l) of the
Proposed AD
Boeing requested that we revise the
provision of paragraph (l) of the
proposed AD, which would provide for
terminating action if the skin panel was
replaced with a production skin panel.
Boeing indicated that terminating action
should also apply to airplanes with the
skin panel replacement kit (S–20 to S–
25 (left and right)) specified in Boeing
Service Bulletin 737–53–1187. Boeing
stated that the skin panel replacement
using the kit specified in Boeing Service
Bulletin 737–53–1187 does not have the
lower flight cycle limit restriction of the
production panel replacement. Boeing
explained that once the kit skin panel is
replaced, the inspections specified in
SASB 737–53–1187 R3, are terminated.
We agree with Boeing’s request. The
kit skin panels are an improved design
compared with the original production
skin panels, have different inspection
requirements, and provide terminating
action. We have revised paragraph (l) of
this AD accordingly.
Request To Remove Flight Cycle
Restriction in Paragraphs (m)(2), (m)(3),
and (n)(5) of the Proposed AD
Boeing requested that we revise
paragraphs (m)(2), (m)(3), and (n)(5) of
the proposed AD by removing the flightcycle restriction for credit for the skin
panel replacement. Boeing explained
that the only skin panel replacement
specified in the service information
referenced in paragraphs (m)(2) and
(m)(3) of the proposed AD is the skin
panel replacement kit, which can be
accomplished at any time.
Boeing stated that it assumed that
only the kit skin panel replacements,
and not the original production skin
panels, are approved as AMOCs for AD
2009–21–01, Amendment 39–16038 (74
FR 52395, October 13, 2009) (‘‘AD
2009–21–01’’). Boeing asserted that,
therefore, paragraph (n)(5) of the
proposed AD should approve previous
modifications done as optional
terminating action for AD 2009–21–01
as AMOCs for the modification required
by paragraph (l) of this AD without the
flight-cycle restriction.
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We partially agree with Boeing’s
request. The kit skin panels are an
improved design compared with the
original production skin panels and
have different inspection requirements.
We have revised paragraphs (m)(2) and
(m)(3) of this AD by removing the flightcycle restriction.
However, in order to address
airplanes that have had production skin
panels replaced through AMOCs for AD
2009–21–01, paragraph (n)(5) of this AD
retains the flight-cycle restriction.
We agree to approve AMOCs for AD
2009–21–01 that require using the skin
panel kit specified in Boeing Service
Bulletin 737–53–1187 as AMOCs for the
modification required by paragraph (l)
of this AD without the flight-cycle
restriction. We have added paragraph
(n)(6) to this AD, which states that
AMOCs approved for previous
modifications done as optional
terminating action for AD 2009–21–01
are approved as AMOCs for the
modification required by paragraph (l)
of this AD provided the skin
modification replacement was done
using the skin panel kit specified in
Boeing Service Bulletin 737–53–1187.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed SASB 737–53–1187 R3.
The service information describes
procedures for doing inspections of the
fuselage skin, repairs, and skin panel
replacement. 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 84
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Inspections ....................
Up to 1,568 work-hours × $85 per hour = Up to
$133,280.
698 work-hours × $85 per hour = $59,330 ..........
Skin replacement ..........
We estimate the following costs to do
any necessary repairs that would be
Cost per
product
Parts cost
Cost on U.S.
operators
$0
Up to $133,280 .............
Up to $11,195,520.
185,147
$244,477 .......................
$20,536,068.
required based on the results of the
inspections. We have no way of
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Time-limited repair ..............................................
24 work-hours × $85 per hour = $2,040 per repair.
Up to 39 work-hours × $85 per hour = $3,315
per repair.
Permanent repair ................................................
1 We
Parts cost
Cost per product
(1)
$2,040 per repair.
(1 )
Up to $3,315 per repair.
have received no definitive data that would enable us to provide the part cost estimates for the on-condition actions specified in this AD.
We estimate the following costs to do
any necessary post-repair inspections
that would be required. We have no way
of determining the number of aircraft
that might need these inspections:
POST-REPAIR INSPECTION COSTS
Action
Labor cost
Post-repair inspection ....................................................
Up to 7 work-hours × $85 per hour = $595 ..................
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.
sradovich on DSK3GMQ082PROD with RULES
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
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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.
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Cost per
product
Parts cost
§ 39.13
$0
Up to $595.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–10–07 The Boeing Company:
Amendment 39–18881; Docket No.
FAA–2016–6666; Directorate Identifier
2015–NM–124–AD.
(a) Effective Date
This AD is effective July 5, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Boeing Model 737–400
series airplanes, certificated in any category,
as identified in Boeing Special Attention
Service Bulletin 737–53–1187, Revision 3,
dated July 10, 2015 (‘‘SASB 737–53–1187
R3’’).
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) which
indicates that the aft fuselage skin is subject
to widespread fatigue damage (WFD) and
reports of aft fuselage skin cracking. We are
issuing this AD to detect and correct cracking
in the aft fuselage skin along the longitudinal
edges of the bonded skin doubler, which
could result in possible rapid decompression
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and reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
sradovich on DSK3GMQ082PROD with RULES
(g) Inspections, Related Investigative and
Corrective Actions
At the applicable times specified in tables
1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’
of SASB 737–53–1187 R3, except as provided
by paragraph (h)(1) and (h)(2) of this AD: Do
the applicable inspections to detect cracks in
the aft fuselage skin panels; and do all
applicable related investigative and
corrective actions; in accordance with the
Accomplishment Instructions of SASB 737–
53–1187 R3, except as required by
paragraphs (h)(3) and (h)(4) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
Repeat the applicable inspections thereafter
at the applicable intervals specified in tables
1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’
of SASB 737–53–1187 R3. Accomplishment
of a repair in accordance with ‘‘Part 4:
Repair’’ of the Accomplishment Instructions
of SASB 737–53–1187 R3, except as required
by paragraph (h)(3) of this AD, is terminating
action for the repetitive inspections required
by this paragraph at the repaired locations
only.
(h) Exceptions to SASB 737–53–1187 R3
(1) Where SASB 737–53–1187 R3, specifies
compliance times ‘‘after the Revision 3 date
of this service bulletin,’’ this AD requires
compliance within the specified compliance
times after the effective date of this AD.
(2) The Condition column of Paragraph
1.E., ‘‘Compliance,’’ of SASB 737–53–1187
R3, refers to airplanes in certain
configurations as of the ‘‘issue date of
Revision 3 of this service bulletin.’’ However,
this AD applies to airplanes in the specified
configurations as of the effective date of this
AD.
(3) Where SASB 737–53–1187 R3 specifies
contacting Boeing for repair instructions or
work instructions, before further flight, repair
or perform the work instructions using a
method approved in accordance with the
procedures specified in paragraph (n) of this
AD, except as required by paragraph (h)(4) of
this AD.
(4) For airplanes on which an operator has
a record that a skin panel was replaced with
a production skin panel before 53,000 total
flight cycles: At the applicable time for the
next inspection as specified in tables 1, 2,
and 3 of paragraph 1.E., ‘‘Compliance,’’ of
SASB 737–53–1187 R3, except as provided
by paragraph (h)(1) and (h)(2) of this AD:
Perform inspections and applicable
corrective actions using a method approved
in accordance with the procedures specified
in paragraph (n) of this AD.
(i) Actions for Airplanes With a TimeLimited Repair Installed
(1) For airplanes with a time-limited repair
installed as specified in Boeing Service
Bulletin 737–53–1187, Revision 2, dated May
9, 2007: At the applicable times specified in
table 4 of paragraph 1.E., ‘‘Compliance,’’ of
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SASB 737–53–1187 R3, except as provided
by paragraphs (h)(1) and (h)(2) of this AD: Do
the actions specified in paragraphs (i)(1)(i)
and (i)(1)(ii) of this AD.
(i) Do the applicable inspections to detect
missing or loose fasteners and any
disbonding or cracking of bonded doublers;
and do all applicable related investigative
and corrective actions; in accordance with
the Accomplishment Instructions of SASB
737–53–1187 R3, except as required by
paragraph (h)(3) of this AD. Do all applicable
related investigative and corrective actions
before further flight. Repeat the applicable
inspections thereafter at the applicable
intervals specified in table 4 of paragraph
1.E., ‘‘Compliance,’’ of SASB 737–53–1187
R3.
(ii) Make the time-limited repair
permanent; and do all applicable related
investigative and corrective actions; in
accordance with Part 6 of the
Accomplishment Instructions of SASB 737–
53–1187 R3, except as required by paragraph
(h)(3) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Accomplishing the permanent
repair required by this paragraph terminates
the inspections required by paragraph (i)(1)(i)
of this AD for the permanently repaired area
only.
(2) For airplanes with a time-limited repair
installed as specified in SASB 737–53–1187
R3: At the applicable times specified in table
5 of paragraph 1.E., ‘‘Compliance,’’ of SASB
737–53–1187 R3, except as provided by
paragraph (h)(2) of this AD: Do the actions
specified in paragraphs (i)(2)(i) and (i)(2)(ii)
of this AD.
(i) Do the applicable inspections to detect
missing or loose fasteners and any
disbonding or cracking of bonded doublers;
and do all applicable corrective actions; in
accordance with the Accomplishment
Instructions of SASB 737–53–1187 R3,
except as required by paragraph (h)(3) of this
AD. Do all applicable corrective actions
before further flight. Repeat the applicable
inspections thereafter at the applicable
intervals specified in table 5 of paragraph
1.E., ‘‘Compliance,’’ of SASB 737–53–1187
R3.
(ii) Make the time-limited repair
permanent; and do all applicable related
investigative and corrective actions; in
accordance with Part 6 of the
Accomplishment Instructions of SASB 737–
53–1187 R3, except as required by paragraph
(h)(3) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Accomplishing the permanent
repair required by this paragraph terminates
the inspections required by paragraph (i)(2)(i)
of this AD for the permanently repaired area
only.
(j) Modification of Certain Permanent
Repairs
For airplanes with an existing time-limited
repair that was made permanent as specified
in Boeing Service Bulletin 737–53–1187,
Revision 2, dated May 9, 2007: At the
applicable time specified in table 6 of
paragraph 1.E., ‘‘Compliance,’’ of SASB 737–
53–1187 R3, except as provided by paragraph
(h)(1) of this AD: Modify the existing
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permanent repair; and do all applicable
related investigative and corrective actions;
in accordance with Part 6 of the
Accomplishment Instructions of SASB 737–
53–1187 R3, except as required by paragraph
(h)(3) of this AD. Do all applicable related
investigative and corrective actions before
further flight.
(k) Post-Repair Inspections
Table 7 of paragraph 1.E., ‘‘Compliance,’’
of SASB 737–53–1187 R3, specifies postrepair airworthiness limitation inspections in
compliance with 14 CFR 25.571(a)(3) at the
repaired locations, which support
compliance with 14 CFR 121.1109(c)(2) or
129.109(b)(2). As airworthiness limitations,
these inspections are required by
maintenance and operational rules. It is
therefore unnecessary to mandate them in
this AD. Deviations from these inspections
require FAA approval, but do not require an
alternative method of compliance.
(l) Skin Panel Replacement
At the later of the times specified in
paragraphs (l)(1) and (1)(2) of this AD:
Replace the applicable skin panels, and do
all applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of SASB 737–
53–1187 R3. Do all applicable related
investigative and corrective actions before
further flight. Doing the skin panel
replacement required by this paragraph
terminates the inspection requirements of
paragraphs (g), (i), and (j) of this AD for that
skin panel only, provided the skin panel
replacement was done with a production
skin panel after 53,000 total flight cycles, or
with the skin panel replacement kit (S–20 to
S–25 (left and right)) specified in Boeing
Service Bulletin 737–53–1187.
(1) Before 60,000 total flight cycles, but not
before 53,000 total flight cycles.
(2) Within 6,000 flight cycles after the
effective date of this AD, but not before
53,000 total flight cycles.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Service
Bulletin 737–53–1187, Revision 2, dated May
9, 2007, except as required by paragraph
(h)(4) of this AD. Boeing Service Bulletin
737–53–1187, Revision 2, dated May 9, 2007,
was incorporated by reference in AD 2009–
21–01, Amendment 39–16038 (74 FR 52395,
October 13, 2009) (‘‘AD 2009–21–01’’).
(2) This paragraph provides credit for the
actions required by paragraph (l) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Service
Bulletin 737–53–1187, Revision 2, dated May
9, 2007, except as required by paragraph
(h)(4) of this AD. Boeing Service Bulletin
737–53–1187, Revision 2, dated May 9, 2007,
was incorporated by reference in AD 2009–
21–01.
(3) This paragraph provides credit for the
actions required by paragraph (l) of this AD,
if those actions were performed before
November 17, 2009 (the effective date of AD
2009–21–01) using Part III of the
Accomplishment Instructions of Boeing
E:\FR\FM\30MYR1.SGM
30MYR1
Federal Register / Vol. 82, No. 102 / Tuesday, May 30, 2017 / Rules and Regulations
Service Bulletin 737–53–1187, dated
November 2, 1995; or Part III of the
Accomplishment Instructions of Boeing
Service Bulletin 737–53–1187, Revision 1,
dated January 16, 1997, except as required by
paragraph (h)(4) of this AD. Boeing Service
Bulletin 737–53–1187, dated November 2,
1995; and Boeing Service Bulletin 737–53–
1187, Revision 1, dated January 16, 1997; are
not incorporated by reference in this AD.
sradovich on DSK3GMQ082PROD with RULES
(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,
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) AMOCs approved for repairs for AD
2009–21–01 are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(5) Except as specified in paragraph (n)(6)
of this AD, AMOCs approved for previous
modifications done as optional terminating
action for AD 2009–21–01 are approved as
AMOCs for the modification required by
paragraph (l) of this AD provided the
previous modification was done after the
airplane had accumulated 53,000 total flight
cycles or more.
(6) AMOCs approved for previous
modifications done as optional terminating
action for AD 2009–21–01 are approved as
AMOCs for the modification required by
paragraph (l) of this AD provided the skin
modification replacement is done using the
skin panel kit specified Boeing Service
Bulletin 737–53–1187.
(o) Related Information
(1) For more information about this AD,
contact Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles ACO, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–5210;
email: jennifer.tsakoumakis@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.
VerDate Sep<11>2014
17:28 May 26, 2017
Jkt 241001
(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 Special Attention Service
Bulletin 737–53–1187, Revision 3, dated July
10, 2015.
(ii) Reserved.
(3) For Boeing 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 May 2,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10286 Filed 5–26–17; 8:45 am]
BILLING CODE 4910–13–P
COMMODITY FUTURES TRADING
COMMISSION
17 CFR Parts 1 and 23
RIN 3038–AE36
Recordkeeping
Commodity Futures Trading
Commission.
ACTION: Final rule.
AGENCY:
The Commodity Futures
Trading Commission (the
‘‘Commission’’) is amending the
recordkeeping obligations set forth in
Commission regulations along with
corresponding technical changes to
certain provisions regarding retention of
oral communications and record
retention requirements applicable to
swap dealers and major swap
participants, respectively. The
amendments modernize and make
technology neutral the form and manner
in which regulatory records must be
kept, as well as rationalize the rule text
for ease of understanding for those
SUMMARY:
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
24479
persons required to keep records
pursuant to the Commodity Exchange
Act (the ‘‘CEA’’ or ‘‘Act’’) and
regulations promulgated by the
Commission thereunder. The
amendments do not alter any existing
requirements regarding the types of
regulatory records to be inspected,
produced, and maintained set forth in
other Commission regulations.
The effective date for this final
rule is August 28, 2017.
DATES:
FOR FURTHER INFORMATION CONTACT:
Eileen T. Flaherty, Director, (202) 418–
5326, eflaherty@cftc.gov; Frank
Fisanich, Chief Counsel, (202) 418–
5949, ffisanich@cftc.gov; Andrew
Chapin, Associate Chief Counsel, (202)
418–5465, achapin@cftc.gov; Katherine
Driscoll, Associate Chief Counsel, (202)
418–5544, kdriscoll@cftc.gov; C. Barry
McCarty, Special Counsel, (202) 418–
6627, cmccarty@cftc.gov; or Jacob
Chachkin, Special Counsel, (202) 418–
5496, jchachkin@cftc.gov, Division of
Swap Dealer and Intermediary
Oversight, Commodity Futures Trading
Commission, 1155 21st Street NW.,
Washington, DC 20581.
SUPPLEMENTARY INFORMATION:
I. Background
In response to petitions for
rulemaking from various industry
groups requesting amendments to
§ 1.31, the Commission published in the
Federal Register on January 19, 2017 a
proposal (‘‘Proposal’’) to amend the
recordkeeping obligations applicable to
all persons required to keep records
pursuant to the Act and Commission
regulations promulgated thereunder
(referred to in the Proposal as ‘‘records
entities’’).1 Regulation 1.31 sets forth the
form and manner in which all
regulatory records must be kept by
records entities. Regulation 1.31 does
not specify the types of regulatory
records that must be kept, rather it
specifies the form and manner in which
regulatory records required by other
Commission regulations are maintained
and produced to the Commission. The
proposed amendments to § 1.31, and
related technical amendments to §§ 1.35
and 23.203, would modernize and make
technology neutral the form and manner
in which regulatory records must be
kept, as well as rationalize the current
rule text for ease of understanding.
Under the proposed amendments,
records entities would have greater
flexibility regarding the retention and
production of all regulatory records
1 Recordkeeping,
E:\FR\FM\30MYR1.SGM
30MYR1
82 FR 6356 (Jan. 19, 2017).
Agencies
[Federal Register Volume 82, Number 102 (Tuesday, May 30, 2017)]
[Rules and Regulations]
[Pages 24475-24479]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10286]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6666; Directorate Identifier 2015-NM-124-AD;
Amendment 39-18881; AD 2017-10-07]
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 737-400 series airplanes. This AD was prompted
by an evaluation by the design approval holder (DAH), which indicates
that the aft fuselage skin is subject to widespread fatigue damage
(WFD), and reports of aft fuselage skin cracking. This AD requires
repetitive inspections to detect cracking of the aft fuselage skin,
inspections to detect missing or loose fasteners and any disbonding or
cracking of bonded doublers, permanent repairs of time-limited repairs,
related investigative and corrective actions if necessary, and skin
panel replacement. We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 5, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 5,
2017.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone: 562-797-1717; Internet: https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6666.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6666; 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: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@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 Boeing Model 737-
400 series airplanes. The NPRM published in the Federal Register on May
13, 2016 (81 FR 29809) (``the NPRM''). The NPRM was prompted by an
evaluation by the DAH, which indicates that the aft fuselage skin is
subject to WFD, and reports of aft fuselage skin cracking. The NPRM
proposed to require repetitive inspections to detect cracking of the
aft fuselage skin, inspections to detect missing or loose fasteners and
any disbonding or cracking of bonded doublers, permanent repairs of
time-limited repairs, related investigative and corrective actions if
necessary, and skin panel replacement. We are issuing this AD to
prevent cracking in the aft fuselage skin along the longitudinal edges
of the bonded skin doubler, which could result in possible rapid
decompression and reduced structural integrity of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Specify Repair Procedures
Boeing requested that we revise the proposed AD to address repairs
that are
[[Page 24476]]
installed on the airplane for reasons other than chem-mill cracking.
Boeing provided suggested language for the AD.
We do not agree with Boeing's request. Paragraph 3.B.1 in the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1187, Revision 3, dated July 10, 2015 (``SASB 737-53-
1187 R3''), which is the referenced source of service information in
this AD, already addresses the issue raised by Boeing. SASB 737-53-1187
R3 does not make a distinction between repairs installed for chem-mill
cracking and repairs installed for other reasons. Therefore, repairs
that are installed for any reason, provided they meet the service
information criteria, are already addressed. We have not changed this
AD in this regard.
Request To Revise Compliance Time in Paragraph (h)(4) of the Proposed
AD
Boeing requested that we revise the compliance time in paragraph
(h)(4) of the proposed AD from the time specified in SASB 737-53-1187
R3, to a time approved by the FAA through the alternative method of
compliance (AMOC) process.
Boeing provided examples of how replacing skin panels at certain
compliance times would require further skin panel replacement before
reaching the airplane limit of validity. Boeing explained that the NPRM
proposed skin panel replacement at 60,000 total flight cycles;
therefore, an FAA approval to adjust the compliance time from total
flight cycles to cycles after skin panel replacement would be required.
We partially agree with Boeing's request. Airplanes that have had a
skin replacement with a production skin panel, as distinguished from an
improved-design kit skin panel, prior to 53,000 total flight cycles may
be eligible for an adjustment of the inspection threshold. Currently,
such an adjustment of the AD compliance time is not delegated to
Boeing's authorized representatives, and the change must be approved by
the FAA. However, we consider the number of airplanes affected by this
scenario to be quite small. Therefore, we have decided to approve such
changes to the compliance times on a case-by-case basis using the
procedures specified in paragraph (n)(1) of this AD. Although we agree
with the comment, we have not changed this AD in this regard.
Request To Reference Part 6 of the Service Information
Boeing requested that we revise paragraphs (i)(1)(ii), (i)(2)(ii),
and (j) of the proposed AD by specifying doing part 6 of the service
information. Boeing stated that specifying the service information part
reference would make the language consistent with paragraph (g) of the
proposed AD, which specifies the service information part reference.
We agree with Boeing's request. These changes will increase the
paragraphs' clarity. We have revised paragraphs (i)(1)(ii), (i)(2)(ii),
and (j) of this AD accordingly.
Request To Revise Paragraph (l) of the Proposed AD
Boeing requested that we revise the provision of paragraph (l) of
the proposed AD, which would provide for terminating action if the skin
panel was replaced with a production skin panel. Boeing indicated that
terminating action should also apply to airplanes with the skin panel
replacement kit (S-20 to S-25 (left and right)) specified in Boeing
Service Bulletin 737-53-1187. Boeing stated that the skin panel
replacement using the kit specified in Boeing Service Bulletin 737-53-
1187 does not have the lower flight cycle limit restriction of the
production panel replacement. Boeing explained that once the kit skin
panel is replaced, the inspections specified in SASB 737-53-1187 R3,
are terminated.
We agree with Boeing's request. The kit skin panels are an improved
design compared with the original production skin panels, have
different inspection requirements, and provide terminating action. We
have revised paragraph (l) of this AD accordingly.
Request To Remove Flight Cycle Restriction in Paragraphs (m)(2),
(m)(3), and (n)(5) of the Proposed AD
Boeing requested that we revise paragraphs (m)(2), (m)(3), and
(n)(5) of the proposed AD by removing the flight-cycle restriction for
credit for the skin panel replacement. Boeing explained that the only
skin panel replacement specified in the service information referenced
in paragraphs (m)(2) and (m)(3) of the proposed AD is the skin panel
replacement kit, which can be accomplished at any time.
Boeing stated that it assumed that only the kit skin panel
replacements, and not the original production skin panels, are approved
as AMOCs for AD 2009-21-01, Amendment 39-16038 (74 FR 52395, October
13, 2009) (``AD 2009-21-01''). Boeing asserted that, therefore,
paragraph (n)(5) of the proposed AD should approve previous
modifications done as optional terminating action for AD 2009-21-01 as
AMOCs for the modification required by paragraph (l) of this AD without
the flight-cycle restriction.
We partially agree with Boeing's request. The kit skin panels are
an improved design compared with the original production skin panels
and have different inspection requirements. We have revised paragraphs
(m)(2) and (m)(3) of this AD by removing the flight-cycle restriction.
However, in order to address airplanes that have had production
skin panels replaced through AMOCs for AD 2009-21-01, paragraph (n)(5)
of this AD retains the flight-cycle restriction.
We agree to approve AMOCs for AD 2009-21-01 that require using the
skin panel kit specified in Boeing Service Bulletin 737-53-1187 as
AMOCs for the modification required by paragraph (l) of this AD without
the flight-cycle restriction. We have added paragraph (n)(6) to this
AD, which states that AMOCs approved for previous modifications done as
optional terminating action for AD 2009-21-01 are approved as AMOCs for
the modification required by paragraph (l) of this AD provided the skin
modification replacement was done using the skin panel kit specified in
Boeing Service Bulletin 737-53-1187.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed SASB 737-53-1187 R3. The service information describes
procedures for doing inspections of the fuselage skin, repairs, and
skin panel replacement. 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 84 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 24477]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections.................. Up to 1,568 work- $0 Up to $133,280. Up to $11,195,520.
hours x $85 per
hour = Up to
$133,280.
Skin replacement............. 698 work-hours x $85 185,147 $244,477....... $20,536,068.
per hour = $59,330.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspections. We have no
way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Time-limited repair............. 24 work-hours x $85 per (\1\) $2,040 per repair.
hour = $2,040 per
repair.
Permanent repair................ Up to 39 work-hours x (\1\) Up to $3,315 per repair.
$85 per hour = $3,315
per repair.
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide the part cost estimates for the on-
condition actions specified in this AD.
We estimate the following costs to do any necessary post-repair
inspections that would be required. We have no way of determining the
number of aircraft that might need these inspections:
Post-Repair Inspection Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Post-repair inspection................ Up to 7 work[dash]hours x $85 $0 Up to $595.
per hour = $595.
----------------------------------------------------------------------------------------------------------------
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):
2017-10-07 The Boeing Company: Amendment 39-18881; Docket No. FAA-
2016-6666; Directorate Identifier 2015-NM-124-AD.
(a) Effective Date
This AD is effective July 5, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Boeing Model 737-400 series airplanes,
certificated in any category, as identified in Boeing Special
Attention Service Bulletin 737-53-1187, Revision 3, dated July 10,
2015 (``SASB 737-53-1187 R3'').
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) which indicates that the aft fuselage skin is subject
to widespread fatigue damage (WFD) and reports of aft fuselage skin
cracking. We are issuing this AD to detect and correct cracking in
the aft fuselage skin along the longitudinal edges of the bonded
skin doubler, which could result in possible rapid decompression
[[Page 24478]]
and reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections, Related Investigative and Corrective Actions
At the applicable times specified in tables 1, 2, and 3 of
paragraph 1.E., ``Compliance,'' of SASB 737-53-1187 R3, except as
provided by paragraph (h)(1) and (h)(2) of this AD: Do the
applicable inspections to detect cracks in the aft fuselage skin
panels; and do all applicable related investigative and corrective
actions; in accordance with the Accomplishment Instructions of SASB
737-53-1187 R3, except as required by paragraphs (h)(3) and (h)(4)
of this AD. Do all applicable related investigative and corrective
actions before further flight. Repeat the applicable inspections
thereafter at the applicable intervals specified in tables 1, 2, and
3 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1187 R3.
Accomplishment of a repair in accordance with ``Part 4: Repair'' of
the Accomplishment Instructions of SASB 737-53-1187 R3, except as
required by paragraph (h)(3) of this AD, is terminating action for
the repetitive inspections required by this paragraph at the
repaired locations only.
(h) Exceptions to SASB 737-53-1187 R3
(1) Where SASB 737-53-1187 R3, specifies compliance times
``after the Revision 3 date of this service bulletin,'' this AD
requires compliance within the specified compliance times after the
effective date of this AD.
(2) The Condition column of Paragraph 1.E., ``Compliance,'' of
SASB 737-53-1187 R3, refers to airplanes in certain configurations
as of the ``issue date of Revision 3 of this service bulletin.''
However, this AD applies to airplanes in the specified
configurations as of the effective date of this AD.
(3) Where SASB 737-53-1187 R3 specifies contacting Boeing for
repair instructions or work instructions, before further flight,
repair or perform the work instructions using a method approved in
accordance with the procedures specified in paragraph (n) of this
AD, except as required by paragraph (h)(4) of this AD.
(4) For airplanes on which an operator has a record that a skin
panel was replaced with a production skin panel before 53,000 total
flight cycles: At the applicable time for the next inspection as
specified in tables 1, 2, and 3 of paragraph 1.E., ``Compliance,''
of SASB 737-53-1187 R3, except as provided by paragraph (h)(1) and
(h)(2) of this AD: Perform inspections and applicable corrective
actions using a method approved in accordance with the procedures
specified in paragraph (n) of this AD.
(i) Actions for Airplanes With a Time-Limited Repair Installed
(1) For airplanes with a time-limited repair installed as
specified in Boeing Service Bulletin 737-53-1187, Revision 2, dated
May 9, 2007: At the applicable times specified in table 4 of
paragraph 1.E., ``Compliance,'' of SASB 737-53-1187 R3, except as
provided by paragraphs (h)(1) and (h)(2) of this AD: Do the actions
specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Do the applicable inspections to detect missing or loose
fasteners and any disbonding or cracking of bonded doublers; and do
all applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of SASB 737-53-1187
R3, except as required by paragraph (h)(3) of this AD. Do all
applicable related investigative and corrective actions before
further flight. Repeat the applicable inspections thereafter at the
applicable intervals specified in table 4 of paragraph 1.E.,
``Compliance,'' of SASB 737-53-1187 R3.
(ii) Make the time-limited repair permanent; and do all
applicable related investigative and corrective actions; in
accordance with Part 6 of the Accomplishment Instructions of SASB
737-53-1187 R3, except as required by paragraph (h)(3) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Accomplishing the permanent repair required
by this paragraph terminates the inspections required by paragraph
(i)(1)(i) of this AD for the permanently repaired area only.
(2) For airplanes with a time-limited repair installed as
specified in SASB 737-53-1187 R3: At the applicable times specified
in table 5 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1187
R3, except as provided by paragraph (h)(2) of this AD: Do the
actions specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Do the applicable inspections to detect missing or loose
fasteners and any disbonding or cracking of bonded doublers; and do
all applicable corrective actions; in accordance with the
Accomplishment Instructions of SASB 737-53-1187 R3, except as
required by paragraph (h)(3) of this AD. Do all applicable
corrective actions before further flight. Repeat the applicable
inspections thereafter at the applicable intervals specified in
table 5 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1187 R3.
(ii) Make the time-limited repair permanent; and do all
applicable related investigative and corrective actions; in
accordance with Part 6 of the Accomplishment Instructions of SASB
737-53-1187 R3, except as required by paragraph (h)(3) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Accomplishing the permanent repair required
by this paragraph terminates the inspections required by paragraph
(i)(2)(i) of this AD for the permanently repaired area only.
(j) Modification of Certain Permanent Repairs
For airplanes with an existing time-limited repair that was made
permanent as specified in Boeing Service Bulletin 737-53-1187,
Revision 2, dated May 9, 2007: At the applicable time specified in
table 6 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1187 R3,
except as provided by paragraph (h)(1) of this AD: Modify the
existing permanent repair; and do all applicable related
investigative and corrective actions; in accordance with Part 6 of
the Accomplishment Instructions of SASB 737-53-1187 R3, except as
required by paragraph (h)(3) of this AD. Do all applicable related
investigative and corrective actions before further flight.
(k) Post-Repair Inspections
Table 7 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1187
R3, specifies post-repair airworthiness limitation inspections in
compliance with 14 CFR 25.571(a)(3) at the repaired locations, which
support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As
airworthiness limitations, these inspections are required by
maintenance and operational rules. It is therefore unnecessary to
mandate them in this AD. Deviations from these inspections require
FAA approval, but do not require an alternative method of
compliance.
(l) Skin Panel Replacement
At the later of the times specified in paragraphs (l)(1) and
(1)(2) of this AD: Replace the applicable skin panels, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of SASB 737-53-1187
R3. Do all applicable related investigative and corrective actions
before further flight. Doing the skin panel replacement required by
this paragraph terminates the inspection requirements of paragraphs
(g), (i), and (j) of this AD for that skin panel only, provided the
skin panel replacement was done with a production skin panel after
53,000 total flight cycles, or with the skin panel replacement kit
(S-20 to S-25 (left and right)) specified in Boeing Service Bulletin
737-53-1187.
(1) Before 60,000 total flight cycles, but not before 53,000
total flight cycles.
(2) Within 6,000 flight cycles after the effective date of this
AD, but not before 53,000 total flight cycles.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 737-53-1187,
Revision 2, dated May 9, 2007, except as required by paragraph
(h)(4) of this AD. Boeing Service Bulletin 737-53-1187, Revision 2,
dated May 9, 2007, was incorporated by reference in AD 2009-21-01,
Amendment 39-16038 (74 FR 52395, October 13, 2009) (``AD 2009-21-
01'').
(2) This paragraph provides credit for the actions required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 737-53-1187,
Revision 2, dated May 9, 2007, except as required by paragraph
(h)(4) of this AD. Boeing Service Bulletin 737-53-1187, Revision 2,
dated May 9, 2007, was incorporated by reference in AD 2009-21-01.
(3) This paragraph provides credit for the actions required by
paragraph (l) of this AD, if those actions were performed before
November 17, 2009 (the effective date of AD 2009-21-01) using Part
III of the Accomplishment Instructions of Boeing
[[Page 24479]]
Service Bulletin 737-53-1187, dated November 2, 1995; or Part III of
the Accomplishment Instructions of Boeing Service Bulletin 737-53-
1187, Revision 1, dated January 16, 1997, except as required by
paragraph (h)(4) of this AD. Boeing Service Bulletin 737-53-1187,
dated November 2, 1995; and Boeing Service Bulletin 737-53-1187,
Revision 1, dated January 16, 1997; are not incorporated by
reference in this AD.
(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, 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) AMOCs approved for repairs for AD 2009-21-01 are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
(5) Except as specified in paragraph (n)(6) of this AD, AMOCs
approved for previous modifications done as optional terminating
action for AD 2009-21-01 are approved as AMOCs for the modification
required by paragraph (l) of this AD provided the previous
modification was done after the airplane had accumulated 53,000
total flight cycles or more.
(6) AMOCs approved for previous modifications done as optional
terminating action for AD 2009-21-01 are approved as AMOCs for the
modification required by paragraph (l) of this AD provided the skin
modification replacement is done using the skin panel kit specified
Boeing Service Bulletin 737-53-1187.
(o) Related Information
(1) For more information about this AD, contact Jennifer
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@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 Special Attention Service Bulletin 737-53-1187,
Revision 3, dated July 10, 2015.
(ii) Reserved.
(3) For Boeing 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 May 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10286 Filed 5-26-17; 8:45 am]
BILLING CODE 4910-13-P