Airworthiness Directives; The Boeing Company Airplanes, 44504-44509 [2017-20114]
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Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations
condition on these products as a result of
possible corrosion on the rudder upper hinge
bracket and internal wing, areas of the
passenger/crew door hinges and supporting
structure, the main spar joint, and the engine
support attachment bolts, which could lead
to reduced structural integrity with
consequent loss of control.
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(f) Actions and Compliance
Comply with paragraphs (f)(1) through (3)
of this AD within the compliance times
specified, unless already done:
(1) Before further flight after October 30,
2017 (the effective date of this AD),
incorporate BAE Systems (Operations)
Limited Jetstream Series 3100 & 3200
Corrosion Prevention and Control
Programme, Manual Ref. JS/CPCP/01,
Revision 8, dated October 15, 2016, into the
Limitations of your FAA-approved
maintenance program (instructions for
continued airworthiness) on the basis of
which the operator or the owner ensures the
continuing airworthiness of each operated
airplane, as applicable to the airplane model.
(2) Do all tasks in the BAE Systems
(Operations) Limited Jetstream Series 3100 &
3200 Corrosion Prevention and Control
Programme, Manual Ref. JS/CPCP/01,
Revision 8, dated October 15, 2016, at the
compliance times specified in the manual, or
within the next 12 months after October 30,
2017 (the effective date of this AD),
whichever occurs later; except for the
following tasks, which must be done within
12 months after October 30, 2017 (the
effective date of this AD): 52–11–002 C1,
200/EX/01 C2, 500/IN/02 C1, 600/IN/04 C1,
and 700/IN/04 C1.
(3) If any discrepancy, particularly
corrosion, is found during any inspections or
tasks required by paragraphs (f)(1) or (2) of
this AD, within the compliance time
specified, repair or replace, as applicable, all
damaged structural parts and components
and do the maintenance procedures for
corrective action following BAE Systems
(Operations) Limited Jetstream Series 3100 &
3200 Corrosion Prevention and Control
Programme, Manual Ref. JS/CPCP/01,
Revision 8, dated October 15, 2016. If no
compliance time is defined, do the applicable
corrective action before further flight.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Small Airplane
Standards Branch, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Doug Rudolph,
Aerospace Engineer, FAA, Small Airplane
Standards Branch, 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) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
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actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, Small Airplane Standards
Branch; or the European Aviation Safety
Agency (EASA), or BAE Systems
(Operations) Limited’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Reporting Requirements: For any
reporting requirement in this AD, a federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency 2017–0073, dated April 27, 2017.
The MCAI can be found in the AD docket on
the Internet at: https://www.regulations.gov/
document?D=FAA-2017-0639-0002.
(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 the AD specifies otherwise.
(i) BAE Systems (Operations) Limited
Jetstream Series 3100 & 3200 Corrosion
Prevention and Control Programme, Manual
Ref. JS/CPCP/01, Revision 8, dated October
15, 2016.
(ii) Reserved.
(3) For British Aerospace Jetstream Series
3100 and 3200 service information related to
this AD, contact BAE Systems (Operations)
Limited, Customer Information Department,
Prestwick International Airport, Ayrshire,
KA9 2RW, Scotland, United Kingdom;
telephone: +44 1292 675207; fax: +44 1292
675704; email: RApublications@
baesystems.com; Internet: https://
www.baesystems.com/Businesses/
RegionalAircraft/.
(4) You may review copies of the
referenced service information at the FAA,
Policy and Innovation Division, 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–
2017–0639.
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(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 Kansas City, Missouri, on
September 14, 2017.
Pat Mullen,
Acting Deputy Director, Policy & Innovation
Division, Aircraft Certification Service.
[FR Doc. 2017–20047 Filed 9–22–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9301; Product
Identifier 2015–NM–193–AD; Amendment
39–19056; AD 2017–19–26]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2008–12–
04, which applied to certain The Boeing
Company Model 737–600, –700, –700C,
–800, and –900 series airplanes. AD
2008–12–04 required various repetitive
inspections to detect cracks along the
chem-milled steps of the fuselage skin,
and to detect missing or loose fasteners
in the area of a certain preventive
modification or repairs; replacement of
the time-limited repair with a
permanent repair, if applicable; and
applicable corrective actions which
would end certain repetitive
inspections. This AD reduces the postmodification inspection compliance
times, limits installation of the
preventive modification to airplanes
with fewer than 30,000 total flight
cycles, and adds repetitive inspections
for modified airplanes. This AD was
prompted by an evaluation by the
design approval holder (DAH) that
indicated that the upper skin panel at
the chem-milled step above the lap joint
is subject to widespread fatigue damage
(WFD) if the modification was installed
after 30,000 total flight cycles. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective October 30,
2017.
SUMMARY:
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Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 30, 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;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 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–
9301.
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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–
9301; 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:
Alan Pohl, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO
Branch, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6450;
fax: 425–917–6590; email: alan.pohl@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008–12–04,
Amendment 39–15547 (73 FR 32991,
June 11, 2008) (‘‘AD 2008–12–04’’). AD
2008–12–04 applied to certain The
Boeing Company Model 737–600, –700,
–700C, –800, and –900 series airplanes.
The NPRM published in the Federal
Register on November 22, 2016 (81 FR
83745) (‘‘the NPRM’’). The NPRM was
prompted by an evaluation by the DAH
that indicated that the upper skin panel
at the chem-milled step above the lap
joint is subject to WFD if the
modification was installed after 30,000
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total flight cycles. The NPRM proposed
to continue to require various repetitive
inspections to detect cracks along the
chem-milled steps of the fuselage skin,
and to detect missing or loose fasteners
in the area of the preventive
modification or repairs; replacement of
the time-limited repair with a
permanent repair, if applicable; and
applicable corrective actions which
would end certain repetitive
inspections. The NPRM also proposed
to reduce the post-modification
inspection compliance times, limit
installation of the preventive
modification to airplanes with fewer
than 30,000 total flight cycles, and add
repetitive inspections for modified
airplanes. We are issuing this AD to
detect and correct cracking of the upper
skin panel at the chem-milled step
above the lap joint, which could result
in 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.
Support for the NPRM
Boeing and United Airlines supported
the NPRM.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
installation of winglets, as provided in
Supplemental Type Certificate (STC)
ST00830SE, does not affect the ability to
accomplish the actions proposed in the
NPRM.
We agree with the commenter. We
have redesignated paragraph (c) of the
proposed AD as (c)(1) and added
paragraph (c)(2) to this AD to state that
installation of STC ST00830SE does not
affect the ability to accomplish the
actions required by this AD. Therefore,
for airplanes on which STC ST00830SE
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.
Request To Revise Certain Compliance
Time Provisions
Southwest Airlines (SWA) asked that
we revise certain compliance language
in paragraph (p)(4) of the proposed AD,
which stipulated that post-repair or
post-mod inspections be done at the
time specified in the service information
or at the time specified in the previously
approved AMOC, ‘‘whichever occurs
first.’’ SWA stated that previously
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approved AMOCs for post-repair or
post-modification supplemental
inspections that comply with certain
regulations may contain unique damage
tolerance inspection programs that
demonstrate a level of safety equivalent
to that of AD 2008–12–04. SWA added
that altering those supplemental
inspections to post-repair or postmodification inspections as specified in
Boeing Alert Service Bulletin 737–
53A1232, Revision 3, dated July 27,
2015, when those are done first, could
result in incorrect inspection methods
to geometrical structure that does not
conform to the repair or modification
definitions specified in Revisions 1 and
3 of that service information.
We partially agree with the
commenter’s request. We have
determined that repairs and preventive
modifications should be handled
separately. Fleet experience and
subsequent analysis of Model 737–200,
–200C, –300, –400, and –500 airplanes,
which have similar chem-milled step
details, have shown that certain postpreventative modification inspection
programs may not adequately address
the unsafe condition. Therefore,
paragraph (p)(4) of this AD has been
changed to remove the language
‘‘preventative modifications’’ and
remove the reference to the service
information and ‘‘whichever occurs
first’’ from the compliance time
specified. In addition, we have added
paragraph (p)(5) to this AD to address
only the preventive modifications
without change to the service
information and ‘‘whichever occurs
first’’ language.
Request To Retain Certain Exceptions
Additionally, SWA asked that
paragraphs (j) and (k) of AD 2008–12–
04 be included in the proposed AD.
Paragraph (j) of AD 2008–12–04
provides an allowance for repairs that
are FAA-approved and that have a
minimum of three rows of fasteners
above and below the chem-milled step.
SWA stated that paragraph (k) of AD
2008–12–04 provides a means of
inspections without an AMOC when an
external repair is covering the chemmilled step, but that the doubler does
not span the step by a minimum of three
rows of fasteners above and below the
chem-milled step. SWA added that both
paragraphs (j) and (k) of AD 2008–12–
04 are missing from the proposed AD
and should be added, with certain
clarifications, to paragraph (j) of the
proposed AD. First, the repair is an
external doubler repair. Second, in lieu
of the doing the post-repair
supplemental inspections in accordance
with table 2 of paragraph 1.E.,
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‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1232, Revision 3,
dated July 27, 2015, the inspections
should be done in accordance with 14
CFR 121.1109(c)(2) or 14 CFR
129.109(b)(2) supplemental inspection
requirements, or in accordance with
FAA-approved damage tolerance
inspection requirements.
SWA also stated that if paragraphs (j)
and (k) of AD 2008–12–04 are not
restated for compliance with existing
FAA-approved repairs, operators will be
required to seek AMOC approvals for
such existing repairs prior to the
inspection threshold or repeat interval
of table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1232, Revision 3,
dated July 27, 2015. SWA stated that not
including the exceptions in paragraphs
(j) and (k) of AD 2008–12–04 could
potentially lead to disruption of
operations if it is necessary to request
AMOC approvals during repair
discovery, or could burden operators
with records research to identify these
repairs for AMOC approvals prior to the
required compliance times.
We agree that an allowance can be
made for repairs that meet the criteria
specified in paragraph (j) of AD 2008–
12–04. These repairs address the unsafe
condition identified in this AD.
Therefore, we have added paragraph
(l)(3) to this AD to include the provision
of paragraph (j) of AD 2008–12–04 for
repairs that were accomplished before
the effective date of this AD.
We disagree that post-repair
inspections for these repairs should be
done in accordance with 14 CFR
121.1109(c)(2) or 14 CFR 129.109(b)(2)
supplemental inspection requirements.
Post-repair inspections for repairs that
meet the criteria of paragraph (j) of this
AD are to be accomplished in
accordance with table 2 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert
Service Bulletin 737–53A1232, Revision
3, dated July 27, 2015. This is consistent
with the DAH’s current
recommendation as well as the
requirements of paragraph (j) of AD
2008–12–04. Paragraph (l)(3) of this AD
reflects these provisions.
We also disagree with the
commenter’s request to change the word
‘‘repair’’ to ‘‘external doubler repair’’ in
paragraph (l)(3) of this AD because we
are retaining the provisions of paragraph
(j) of AD 2008–12–04.
We also agree to add certain
provisions of paragraph (k) of AD 2008–
12–04 to this AD. We have added
paragraph (l)(4) to this AD to address
certain repairs as defined in paragraph
(k) of AD 2008–12–04. However,
paragraph (l)(4) of this AD does not
include a reference to Boeing Model 737
Non-destructive Test (NDT) Manual,
Part 6, Subject 53–30–20, and instead
requires that the inspection be done
using FAA-approved procedures. We
have also added Note 1 to paragraph
(l)(4) of this AD to specify that guidance
on the inspection specified in paragraph
(l)(4) of this AD can be found in Boeing
Model 737 NDT Manual, Part 6, Subject
53–30–20.
Clarification of Paragraph (i)(1) of This
AD
We have revised the language in
paragraph (i)(1) of this AD to clarify
which modifications are exempt from
the actions required by paragraph (i)(1)
of this AD.
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 Boeing Alert Service
Bulletin 737–53A1232, Revision 3,
dated July 27, 2015. This service
information describes procedures for an
external detailed inspection and an
external nondestructive inspection
(NDI) for cracks in the fuselage skin at
chem-milled steps. Corrective actions
include a permanent or time-limited
repair, a preventive modification, and
replacement of loose and missing
fasteners. Related investigative actions
include internal and external detailed
inspections of the repair area. 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 376
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspections ............
Up to 25 work-hours × $85 per
hour = $2,125 per inspection
cycle.
We estimate the following costs to do
any necessary repairs and replacements
that would be required based on the
Parts cost
Cost per product
$0
Cost on U.S. operators
Up to $2,125 per inspection cycle
Up to $799,000 per inspection
cycle.
results of the inspections. We have no
way of determining the number of
aircraft that might need these
replacements:
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ON-CONDITION COSTS
Action
Labor cost
Parts cost
Fastener replacement ......................
Up to 1 work-hour × $85 per hour = $85 ...................................................
Minimal .........
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Cost per
product
$85
Federal Register / Vol. 82, No. 184 / Monday, September 25, 2017 / Rules and Regulations
We have received no definitive data
that would enable us to provide cost
estimates for the related investigative
actions, certain repairs, and other
applicable actions specified in this AD.
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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
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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.
16:53 Sep 22, 2017
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Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Authority for This Rulemaking
VerDate Sep<11>2014
List of Subjects in 14 CFR Part 39
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)
2008–12–04, Amendment 39–15547 (73
FR 32991, June 11, 2008), and adding
the following new AD:
■
2017–19–26 The Boeing Company:
Amendment 39–19056; Docket No.
FAA–2016–9301; Product Identifier
2015–NM–193–AD.
(a) Effective Date
This AD is effective October 30, 2017.
(b) Affected ADs
This AD replaces AD 2008–12–04,
Amendment 39–15547 (73 FR 32991, June
11, 2008) (‘‘AD 2008–12–04’’).
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–600, –700, –700C,
–800, and –900 series airplanes, certificated
in any category, as identified in Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015.
(2) Installation of Supplemental Type
Certificate (STC) ST00830SE [https://rgl.faa.
gov/Regulatory_and_Guidance_Library/rgstc.
nsf/0/184DE9A71EC3FA5586257EAE00
707DA6?OpenDocument&Highlight=
st00830se] does not affect the ability to
accomplish the actions required by this AD.
Therefore, for airplanes on which STC
ST00830SE 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 a fatigue test
that revealed numerous cracks in the upper
skin panel at the chem-milled step above the
lap joint, followed by an evaluation by the
design approval holder (DAH) that indicated
that location is subject to widespread fatigue
damage (WFD) on airplanes on which a
certain modification was installed after
30,000 total flight cycles. We are issuing this
AD to detect and correct cracking of the
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44507
upper skin panel at the chem-milled step
above the lap joint, which could result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections at Locations Without the
Preventive Modification, Time-Limited
Repair, or Permanent Repair Installed
At locations where a preventive
modification, time-limited repair, or
permanent repair has not been installed as
specified in Boeing Service Bulletin 737–
53A1232: At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015, do an
external detailed inspection and an
inspection specified in either paragraph (g)(1)
or (g)(2) of this AD, for any crack in the
fuselage skin at the chem-milled steps at
specified locations, in accordance with
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015. Do all applicable related
investigative and corrective actions before
further flight in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015, except as required by
paragraph (l)(1) of this AD, and except as
provided in paragraphs (l)(3) and (l)(4) of this
AD. Repeat the inspections thereafter at the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1232, Revision 3, dated July
27, 2015.
(1) Do an external medium frequency eddy
current (MFEC), or magneto optic imager
(MOI), or C-Scan inspection.
(2) Do an external ultrasonic phased array
(UTPA) inspection.
(h) Repetitive Post-Modification Inspections
and Repair at Any Location With the
Preventive Modification But No TimeLimited or Permanent Repair
At any location with a preventive
modification installed as specified in Boeing
Service Bulletin 737–53A1232: At the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1232, Revision 3, dated July
27, 2015, except as required by paragraph
(l)(2) of this AD, do the actions specified in
paragraphs (h)(1) and (h)(2) of this AD.
(1) Do external detailed and external high
frequency and medium frequency eddy
current inspections for any crack, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015. If no crack is found
during the inspection, repeat the inspections
thereafter at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015. If any crack
is found during any inspection required by
this paragraph, repair before further flight, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1232, Revision 3, dated July 27,
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2015, except as required by paragraph (l)(1)
of this AD.
(2) Do a detailed inspection for any crack
and any loose or missing fasteners, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015. Repeat the inspections
thereafter at applicable time specified in
paragraph 1.E, ‘‘Compliance,’’ of Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015. If any crack is found
during any inspection, or any loose or
missing fastener is found, before further
flight, do all applicable corrective actions, in
accordance with Part V of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015, except as specified in
paragraph (l)(1) of this AD.
asabaliauskas on DSKBBXCHB2PROD with RULES
(i) Additional Actions for Modified
Airplanes
(1) At any location where a preventive
modification as specified in Boeing Service
Bulletin 737–53A1232 was installed after the
accumulation of 30,000 total flight cycles, at
the applicable time specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1232, Revision 3, dated July
27, 2015, except as required by paragraph
(l)(2) of this AD, do all applicable
investigative and corrective actions using a
method approved in accordance with the
procedures specified in paragraph (p) of this
AD. For preventive modifications installed
on airplanes listed in Appendix A of Boeing
Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015, at the
specified total flight cycles: The actions
specified in this paragraph are not required.
(2) For airplanes which have installed STC
ST01697SE (https://rgl.faa.gov/Regulatory_
and_Guidance_Library/rgstc.nsf/0/0812969a
86af879b8625766400600105/$FILE/
ST01697SE.pdf) and the preventive
modification has been installed after 15,000
total flight cycles: Before the accumulation of
25,000 total flight cycles, do all applicable
investigative and corrective actions using a
method approved in accordance with the
procedures specified in paragraph (p) of this
AD.
(j) Inspections and Repair at Locations With
the Permanent Chem-Milled Step Repair
Installed
At any location where a permanent repair
has been installed as specified in Boeing
Service Bulletin 737–53A1232: At the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1232, Revision 3, dated July
27, 2015, do the inspections specified in
paragraph (j)(1) or (j)(2) of this AD, in
accordance with Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1232, Revision 3, dated July 27,
2015. Repeat the inspections thereafter at the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1232, Revision 3, dated July
27, 2015. Do all applicable related
investigative and corrective actions before
further flight in accordance with Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
VerDate Sep<11>2014
16:53 Sep 22, 2017
Jkt 241001
dated July 27, 2015, except as required by
paragraph (l)(1) of this AD.
(1) Do an external low frequency eddy
current (LFEC) inspection for any crack, and
doubler external LFEC and external detailed
inspections for any crack and loose or
missing fasteners.
(2) Do an external LFEC inspection for any
crack, a doubler external LFEC and external
detailed inspections for any crack and loose
or missing fasteners, and an internal MFEC
for any crack.
(k) Inspection and Replacement at Locations
With a Chem-Milled Time-Limited Repair
Installed
At any location where a chem-milled timelimited repair is installed, do the actions
specified in paragraphs (k)(1) and (k)(2) of
this AD, at the applicable time specified in
1.E. ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1232, Revision 3, dated July
27, 2015.
(1) Do internal and external detailed
inspections of the time-limited repair for any
crack, or loose or missing fasteners, in
accordance with Part IV of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015. Repeat the inspections
thereafter at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015. If any crack
is found during any inspection, or if any
loose or missing fastener is found, before
further flight, do all applicable corrective
actions, in accordance with Part IV of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1232, Revision 3,
dated July 27, 2015, except as specified in
paragraph (l)(1) of this AD.
(2) Replace the time-limited repair with the
permanent repair, in accordance with Part IV
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015.
(l) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
737–53A1232, Revision 3, dated July 27,
2015, specifies to contact Boeing for repair
instructions, this AD requires repair before
further flight using a method approved in
accordance with the procedures specified in
paragraph (p) of this AD.
(2) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015, specifies a
compliance time ‘‘after the date of Revision
2 of this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(3) For airplanes on which the actions
specified in paragraph (g) of this AD are
required: Inspections specified in table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015, are not
required in areas that are spanned by an
FAA-approved repair that has a minimum of
3 rows of fasteners above and below the
chem-milled step, provided that the repair
was installed before the effective date of this
AD. Operators must accomplish post-repair
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
inspections at the applicable time specified
in table 2 of paragraph 1.E, ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015.
(4) For any airplane that has an external
doubler covering the chem-milled step, but
the doubler does not span the step by a
minimum of 3 rows of fasteners above and
below the chem-milled step and the doubler
was installed before the effective date of this
AD: One method of compliance with the
inspection requirement of paragraph (g) of
this AD is to inspect all chem-milled steps
covered by the repair using non-destructive
test (NDT) methods approved in accordance
with the procedures specified in paragraph
(p) of this AD. These repairs are to be
considered time-limited and are subject to
the post-repair supplemental inspections and
replacement at the times specified in table 3
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015.
Note 1 to paragraph (l)(4) of this AD:
Guidance for the procedures for the
alternative inspection specified in paragraph
(l)(4) of this AD can be found in the Boeing
737 NDT Manual, Part 6, Subject 53–30–20.
(m) Optional Terminating Action
(1) For airplanes that have accumulated
30,000 total flight cycles or fewer, or for
airplanes on which STC ST01697SE was
installed and that have accumulated 15,000
total flight cycles or fewer, accomplishment
of the preventive modification specified in
Part V of Boeing Alert Service Bulletin 737–
53A1232, Revision 3, dated July 27, 2015,
terminates the inspections required by
paragraph (g) of this AD in the modified areas
only.
(2) Installation of a permanent repair as
specified in Part III of Boeing Alert Service
Bulletin 737–53A1232, Revision 3, dated July
27, 2015, or a time-limited repair as specified
in Part IV of Boeing Alert Service Bulletin
737–53A1232, Revision 3, dated July 27,
2015, terminates the inspections required by
paragraph (g) of this AD in the repaired areas
only.
(n) Installation Limitations of Preventive
Modification
As of the effective date of this AD,
installation of the preventive modification
specified in Boeing Service Bulletin 737–
53A1232 is prohibited on the airplanes
identified in paragraphs (n)(1) and (n)(2) of
this AD.
(1) Airplanes that have accumulated more
than 30,000 total flight cycles.
(2) Airplanes which have installed STC
ST01697SE and that have accumulated more
than 15,000 total flight cycles.
(o) Credit for Previous Actions
This paragraph provides credit for the
corresponding actions specified in
paragraphs (g), (h), (i), (j), (k), and (m) of this
AD, if those actions were performed before
the effective date of this AD using the service
information identified in paragraph (o)(1),
(o)(2), or (o)(3) of this AD.
(1) Boeing Special Attention Service
Bulletin 737–53A1232, dated April 2, 2007.
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(2) Boeing Special Attention Service
Bulletin 737–53A1232, Revision 1, dated
May 18, 2012.
(3) Boeing Special Attention Service
Bulletin 737–53A1232, Revision 2, dated July
26, 2013.
asabaliauskas on DSKBBXCHB2PROD with RULES
(p) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (q)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously for repairs
for AD 2008–12–04 are approved as AMOCs
for the installation of the repair specified in
this AD, provided all post-repair inspections
are done at the applicable times specified in
the AMOC.
(5) AMOCs approved previously for
preventive modifications for AD 2008–12–04
are approved as AMOCs for the installation
of the preventive modification specified in
this AD, provided all post-modification
inspections are done at the applicable times
specified in the AMOC, or in tables 1a and
1b of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1232,
Revision 3, dated July 27, 2015, whichever
occurs first. The AMOC must include all of
the inspections specified in Tables 1a and 1b
of Boeing Alert Service Bulletin 737–
53A1232, Revision 3, dated July 27, 2015.
(q) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6577; fax: 425–917–
6450; email: alan.pohl@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
(r) 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.
VerDate Sep<11>2014
16:53 Sep 22, 2017
Jkt 241001
(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–
53A1232, Revision 3, dated July 27, 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 Standards Branch,
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
September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–20114 Filed 9–22–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9143; Product
Identifier 2013–SW–037–AD; Amendment
39–19051; AD 2017–19–21]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model EC225LP helicopters.
This AD requires modifying the
emergency lubrication system (EMLUB).
This AD was prompted by two incidents
of emergency ditching after there was a
warning of a loss of oil pressure and a
false EMLUB failure. The actions of this
AD are intended to address an unsafe
condition on these products.
DATES: This AD is effective October 30,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of October 30, 2017.
ADDRESSES: For service information
identified in this final rule, contact
SUMMARY:
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
44509
Airbus Helicopters, 2701 N Forum
Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced
service information at the FAA, Office
of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room
6N–321, Fort Worth, TX 76177.
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–
9143; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the European Aviation
Safety Agency (EASA) AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Rao
Edupuganti, Aviation Safety Engineer,
Regulations & Policy Section, Rotorcraft
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, Texas
76177; telephone (817) 222–5110; email
rao.edupuganti@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On March 14, 2017, at 82 FR 13565,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 by adding an AD that would apply
to Airbus Helicopters (formerly
Eurocopter France) Model EC225LP
helicopters. The NPRM proposed to
require replacing the EMLUB glycol
pump, the air and glycol pressure
switches, and the MGB lubrication card,
and modifying and re-identifying the
helicopter wiring harness. The NPRM
also proposed testing the function of the
EMLUB and electrical systems and
revising the Emergency Procedures
section of the RFM. Lastly, the NPRM
proposed to prohibit installing certain
part-numbered EMLUB glycol pumps,
air-pressure switches, glycol pressure
switches and electronic boards on any
helicopter. The proposed requirements
were intended to prevent a false EMLUB
warning. This condition when
associated with a loss of the MGB oil
pressure could result in an unnecessary
emergency landing or ditching.
E:\FR\FM\25SER1.SGM
25SER1
]]>Agencies
[Federal Register Volume 82, Number 184 (Monday, September 25, 2017)]
[Rules and Regulations]
[Pages 44504-44509]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-20114]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9301; Product Identifier 2015-NM-193-AD; Amendment
39-19056; AD 2017-19-26]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2008-12-04,
which applied to certain The Boeing Company Model 737-600, -700, -700C,
-800, and -900 series airplanes. AD 2008-12-04 required various
repetitive inspections to detect cracks along the chem-milled steps of
the fuselage skin, and to detect missing or loose fasteners in the area
of a certain preventive modification or repairs; replacement of the
time-limited repair with a permanent repair, if applicable; and
applicable corrective actions which would end certain repetitive
inspections. This AD reduces the post-modification inspection
compliance times, limits installation of the preventive modification to
airplanes with fewer than 30,000 total flight cycles, and adds
repetitive inspections for modified airplanes. This AD was prompted by
an evaluation by the design approval holder (DAH) that indicated that
the upper skin panel at the chem-milled step above the lap joint is
subject to widespread fatigue damage (WFD) if the modification was
installed after 30,000 total flight cycles. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective October 30, 2017.
[[Page 44505]]
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 30,
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; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
You may view this referenced service information at the FAA, Transport
Standards Branch, 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-2016-9301.
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-
9301; 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: Alan Pohl, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email:
alan.pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008-12-04, Amendment 39-15547 (73 FR 32991,
June 11, 2008) (``AD 2008-12-04''). AD 2008-12-04 applied to certain
The Boeing Company Model 737-600, -700, -700C, -800, and -900 series
airplanes. The NPRM published in the Federal Register on November 22,
2016 (81 FR 83745) (``the NPRM''). The NPRM was prompted by an
evaluation by the DAH that indicated that the upper skin panel at the
chem-milled step above the lap joint is subject to WFD if the
modification was installed after 30,000 total flight cycles. The NPRM
proposed to continue to require various repetitive inspections to
detect cracks along the chem-milled steps of the fuselage skin, and to
detect missing or loose fasteners in the area of the preventive
modification or repairs; replacement of the time-limited repair with a
permanent repair, if applicable; and applicable corrective actions
which would end certain repetitive inspections. The NPRM also proposed
to reduce the post-modification inspection compliance times, limit
installation of the preventive modification to airplanes with fewer
than 30,000 total flight cycles, and add repetitive inspections for
modified airplanes. We are issuing this AD to detect and correct
cracking of the upper skin panel at the chem-milled step above the lap
joint, which could result in 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.
Support for the NPRM
Boeing and United Airlines supported the NPRM.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that installation of winglets, as
provided in Supplemental Type Certificate (STC) ST00830SE, does not
affect the ability to accomplish the actions proposed in the NPRM.
We agree with the commenter. We have redesignated paragraph (c) of
the proposed AD as (c)(1) and added paragraph (c)(2) to this AD to
state that installation of STC ST00830SE does not affect the ability to
accomplish the actions required by this AD. Therefore, for airplanes on
which STC ST00830SE 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.
Request To Revise Certain Compliance Time Provisions
Southwest Airlines (SWA) asked that we revise certain compliance
language in paragraph (p)(4) of the proposed AD, which stipulated that
post-repair or post-mod inspections be done at the time specified in
the service information or at the time specified in the previously
approved AMOC, ``whichever occurs first.'' SWA stated that previously
approved AMOCs for post-repair or post-modification supplemental
inspections that comply with certain regulations may contain unique
damage tolerance inspection programs that demonstrate a level of safety
equivalent to that of AD 2008-12-04. SWA added that altering those
supplemental inspections to post-repair or post-modification
inspections as specified in Boeing Alert Service Bulletin 737-53A1232,
Revision 3, dated July 27, 2015, when those are done first, could
result in incorrect inspection methods to geometrical structure that
does not conform to the repair or modification definitions specified in
Revisions 1 and 3 of that service information.
We partially agree with the commenter's request. We have determined
that repairs and preventive modifications should be handled separately.
Fleet experience and subsequent analysis of Model 737-200, -200C, -300,
-400, and -500 airplanes, which have similar chem-milled step details,
have shown that certain post-preventative modification inspection
programs may not adequately address the unsafe condition. Therefore,
paragraph (p)(4) of this AD has been changed to remove the language
``preventative modifications'' and remove the reference to the service
information and ``whichever occurs first'' from the compliance time
specified. In addition, we have added paragraph (p)(5) to this AD to
address only the preventive modifications without change to the service
information and ``whichever occurs first'' language.
Request To Retain Certain Exceptions
Additionally, SWA asked that paragraphs (j) and (k) of AD 2008-12-
04 be included in the proposed AD. Paragraph (j) of AD 2008-12-04
provides an allowance for repairs that are FAA-approved and that have a
minimum of three rows of fasteners above and below the chem-milled
step. SWA stated that paragraph (k) of AD 2008-12-04 provides a means
of inspections without an AMOC when an external repair is covering the
chem-milled step, but that the doubler does not span the step by a
minimum of three rows of fasteners above and below the chem-milled
step. SWA added that both paragraphs (j) and (k) of AD 2008-12-04 are
missing from the proposed AD and should be added, with certain
clarifications, to paragraph (j) of the proposed AD. First, the repair
is an external doubler repair. Second, in lieu of the doing the post-
repair supplemental inspections in accordance with table 2 of paragraph
1.E.,
[[Page 44506]]
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision
3, dated July 27, 2015, the inspections should be done in accordance
with 14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2) supplemental
inspection requirements, or in accordance with FAA-approved damage
tolerance inspection requirements.
SWA also stated that if paragraphs (j) and (k) of AD 2008-12-04 are
not restated for compliance with existing FAA-approved repairs,
operators will be required to seek AMOC approvals for such existing
repairs prior to the inspection threshold or repeat interval of table 1
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1232, Revision 3, dated July 27, 2015. SWA stated that not
including the exceptions in paragraphs (j) and (k) of AD 2008-12-04
could potentially lead to disruption of operations if it is necessary
to request AMOC approvals during repair discovery, or could burden
operators with records research to identify these repairs for AMOC
approvals prior to the required compliance times.
We agree that an allowance can be made for repairs that meet the
criteria specified in paragraph (j) of AD 2008-12-04. These repairs
address the unsafe condition identified in this AD. Therefore, we have
added paragraph (l)(3) to this AD to include the provision of paragraph
(j) of AD 2008-12-04 for repairs that were accomplished before the
effective date of this AD.
We disagree that post-repair inspections for these repairs should
be done in accordance with 14 CFR 121.1109(c)(2) or 14 CFR
129.109(b)(2) supplemental inspection requirements. Post-repair
inspections for repairs that meet the criteria of paragraph (j) of this
AD are to be accomplished in accordance with table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232, Revision
3, dated July 27, 2015. This is consistent with the DAH's current
recommendation as well as the requirements of paragraph (j) of AD 2008-
12-04. Paragraph (l)(3) of this AD reflects these provisions.
We also disagree with the commenter's request to change the word
``repair'' to ``external doubler repair'' in paragraph (l)(3) of this
AD because we are retaining the provisions of paragraph (j) of AD 2008-
12-04.
We also agree to add certain provisions of paragraph (k) of AD
2008-12-04 to this AD. We have added paragraph (l)(4) to this AD to
address certain repairs as defined in paragraph (k) of AD 2008-12-04.
However, paragraph (l)(4) of this AD does not include a reference to
Boeing Model 737 Non-destructive Test (NDT) Manual, Part 6, Subject 53-
30-20, and instead requires that the inspection be done using FAA-
approved procedures. We have also added Note 1 to paragraph (l)(4) of
this AD to specify that guidance on the inspection specified in
paragraph (l)(4) of this AD can be found in Boeing Model 737 NDT
Manual, Part 6, Subject 53-30-20.
Clarification of Paragraph (i)(1) of This AD
We have revised the language in paragraph (i)(1) of this AD to
clarify which modifications are exempt from the actions required by
paragraph (i)(1) of this AD.
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 Boeing Alert Service Bulletin 737-53A1232, Revision 3,
dated July 27, 2015. This service information describes procedures for
an external detailed inspection and an external nondestructive
inspection (NDI) for cracks in the fuselage skin at chem-milled steps.
Corrective actions include a permanent or time-limited repair, a
preventive modification, and replacement of loose and missing
fasteners. Related investigative actions include internal and external
detailed inspections of the repair area. 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 376 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
----------------------------------------------------------------------------------------------------------------
Inspections................. Up to 25 work-hours x $0 Up to $2,125 per Up to $799,000 per
$85 per hour = inspection cycle. inspection cycle.
$2,125 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs and
replacements 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 replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Fastener replacement.................. Up to 1 work-hour x $85 per Minimal.................. $85
hour = $85.
----------------------------------------------------------------------------------------------------------------
[[Page 44507]]
We have received no definitive data that would enable us to provide
cost estimates for the related investigative actions, certain repairs,
and other applicable actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
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)
2008-12-04, Amendment 39-15547 (73 FR 32991, June 11, 2008), and adding
the following new AD:
2017-19-26 The Boeing Company: Amendment 39-19056; Docket No. FAA-
2016-9301; Product Identifier 2015-NM-193-AD.
(a) Effective Date
This AD is effective October 30, 2017.
(b) Affected ADs
This AD replaces AD 2008-12-04, Amendment 39-15547 (73 FR 32991,
June 11, 2008) (``AD 2008-12-04'').
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, and -900 series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin 737-53A1232, Revision
3, dated July 27, 2015.
(2) Installation of Supplemental Type Certificate (STC)
ST00830SE [https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/184DE9A71EC3FA5586257EAE00707DA6?OpenDocument&Highlight=st00830se]
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST00830SE 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 a fatigue test that revealed numerous
cracks in the upper skin panel at the chem-milled step above the lap
joint, followed by an evaluation by the design approval holder (DAH)
that indicated that location is subject to widespread fatigue damage
(WFD) on airplanes on which a certain modification was installed
after 30,000 total flight cycles. We are issuing this AD to detect
and correct cracking of the upper skin panel at the chem-milled step
above the lap joint, which could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections at Locations Without the Preventive Modification, Time-
Limited Repair, or Permanent Repair Installed
At locations where a preventive modification, time-limited
repair, or permanent repair has not been installed as specified in
Boeing Service Bulletin 737-53A1232: At the applicable time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1232, Revision 3, dated July 27, 2015, do an
external detailed inspection and an inspection specified in either
paragraph (g)(1) or (g)(2) of this AD, for any crack in the fuselage
skin at the chem-milled steps at specified locations, in accordance
with Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1232, Revision 3, dated July 27, 2015. Do all applicable
related investigative and corrective actions before further flight
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015,
except as required by paragraph (l)(1) of this AD, and except as
provided in paragraphs (l)(3) and (l)(4) of this AD. Repeat the
inspections thereafter at the applicable time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232,
Revision 3, dated July 27, 2015.
(1) Do an external medium frequency eddy current (MFEC), or
magneto optic imager (MOI), or C-Scan inspection.
(2) Do an external ultrasonic phased array (UTPA) inspection.
(h) Repetitive Post-Modification Inspections and Repair at Any Location
With the Preventive Modification But No Time-Limited or Permanent
Repair
At any location with a preventive modification installed as
specified in Boeing Service Bulletin 737-53A1232: At the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015,
except as required by paragraph (l)(2) of this AD, do the actions
specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Do external detailed and external high frequency and medium
frequency eddy current inspections for any crack, in accordance with
Part 7 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1232, Revision 3, dated July 27, 2015. If no crack
is found during the inspection, repeat the inspections thereafter at
the applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July
27, 2015. If any crack is found during any inspection required by
this paragraph, repair before further flight, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1232, Revision 3, dated July 27,
[[Page 44508]]
2015, except as required by paragraph (l)(1) of this AD.
(2) Do a detailed inspection for any crack and any loose or
missing fasteners, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1232, Revision
3, dated July 27, 2015. Repeat the inspections thereafter at
applicable time specified in paragraph 1.E, ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July
27, 2015. If any crack is found during any inspection, or any loose
or missing fastener is found, before further flight, do all
applicable corrective actions, in accordance with Part V of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1232, Revision 3, dated July 27, 2015, except as specified in
paragraph (l)(1) of this AD.
(i) Additional Actions for Modified Airplanes
(1) At any location where a preventive modification as specified
in Boeing Service Bulletin 737-53A1232 was installed after the
accumulation of 30,000 total flight cycles, at the applicable time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1232, Revision 3, dated July 27, 2015, except as
required by paragraph (l)(2) of this AD, do all applicable
investigative and corrective actions using a method approved in
accordance with the procedures specified in paragraph (p) of this
AD. For preventive modifications installed on airplanes listed in
Appendix A of Boeing Alert Service Bulletin 737-53A1232, Revision 3,
dated July 27, 2015, at the specified total flight cycles: The
actions specified in this paragraph are not required.
(2) For airplanes which have installed STC ST01697SE (https://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
0812969a86af879b8625766400600105/$FILE/ST01697SE.pdf) and the
preventive modification has been installed after 15,000 total flight
cycles: Before the accumulation of 25,000 total flight cycles, do
all applicable investigative and corrective actions using a method
approved in accordance with the procedures specified in paragraph
(p) of this AD.
(j) Inspections and Repair at Locations With the Permanent Chem-Milled
Step Repair Installed
At any location where a permanent repair has been installed as
specified in Boeing Service Bulletin 737-53A1232: At the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015, do
the inspections specified in paragraph (j)(1) or (j)(2) of this AD,
in accordance with Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015.
Repeat the inspections thereafter at the applicable time specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1232, Revision 3, dated July 27, 2015. Do all applicable
related investigative and corrective actions before further flight
in accordance with Boeing Alert Service Bulletin 737-53A1232,
Revision 3, dated July 27, 2015, except as required by paragraph
(l)(1) of this AD.
(1) Do an external low frequency eddy current (LFEC) inspection
for any crack, and doubler external LFEC and external detailed
inspections for any crack and loose or missing fasteners.
(2) Do an external LFEC inspection for any crack, a doubler
external LFEC and external detailed inspections for any crack and
loose or missing fasteners, and an internal MFEC for any crack.
(k) Inspection and Replacement at Locations With a Chem-Milled Time-
Limited Repair Installed
At any location where a chem-milled time-limited repair is
installed, do the actions specified in paragraphs (k)(1) and (k)(2)
of this AD, at the applicable time specified in 1.E. ``Compliance,''
of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July
27, 2015.
(1) Do internal and external detailed inspections of the time-
limited repair for any crack, or loose or missing fasteners, in
accordance with Part IV of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015.
Repeat the inspections thereafter at the applicable time specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1232, Revision 3, dated July 27, 2015. If any crack is found
during any inspection, or if any loose or missing fastener is found,
before further flight, do all applicable corrective actions, in
accordance with Part IV of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015,
except as specified in paragraph (l)(1) of this AD.
(2) Replace the time-limited repair with the permanent repair,
in accordance with Part IV of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July
27, 2015.
(l) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 737-53A1232, Revision 3,
dated July 27, 2015, specifies to contact Boeing for repair
instructions, this AD requires repair before further flight using a
method approved in accordance with the procedures specified in
paragraph (p) of this AD.
(2) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015,
specifies a compliance time ``after the date of Revision 2 of this
service bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(3) For airplanes on which the actions specified in paragraph
(g) of this AD are required: Inspections specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1232, Revision 3, dated July 27, 2015, are not required in
areas that are spanned by an FAA-approved repair that has a minimum
of 3 rows of fasteners above and below the chem-milled step,
provided that the repair was installed before the effective date of
this AD. Operators must accomplish post-repair inspections at the
applicable time specified in table 2 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232,
Revision 3, dated July 27, 2015.
(4) For any airplane that has an external doubler covering the
chem-milled step, but the doubler does not span the step by a
minimum of 3 rows of fasteners above and below the chem-milled step
and the doubler was installed before the effective date of this AD:
One method of compliance with the inspection requirement of
paragraph (g) of this AD is to inspect all chem-milled steps covered
by the repair using non-destructive test (NDT) methods approved in
accordance with the procedures specified in paragraph (p) of this
AD. These repairs are to be considered time-limited and are subject
to the post-repair supplemental inspections and replacement at the
times specified in table 3 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July
27, 2015.
Note 1 to paragraph (l)(4) of this AD: Guidance for the
procedures for the alternative inspection specified in paragraph
(l)(4) of this AD can be found in the Boeing 737 NDT Manual, Part 6,
Subject 53-30-20.
(m) Optional Terminating Action
(1) For airplanes that have accumulated 30,000 total flight
cycles or fewer, or for airplanes on which STC ST01697SE was
installed and that have accumulated 15,000 total flight cycles or
fewer, accomplishment of the preventive modification specified in
Part V of Boeing Alert Service Bulletin 737-53A1232, Revision 3,
dated July 27, 2015, terminates the inspections required by
paragraph (g) of this AD in the modified areas only.
(2) Installation of a permanent repair as specified in Part III
of Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July
27, 2015, or a time-limited repair as specified in Part IV of Boeing
Alert Service Bulletin 737-53A1232, Revision 3, dated July 27, 2015,
terminates the inspections required by paragraph (g) of this AD in
the repaired areas only.
(n) Installation Limitations of Preventive Modification
As of the effective date of this AD, installation of the
preventive modification specified in Boeing Service Bulletin 737-
53A1232 is prohibited on the airplanes identified in paragraphs
(n)(1) and (n)(2) of this AD.
(1) Airplanes that have accumulated more than 30,000 total
flight cycles.
(2) Airplanes which have installed STC ST01697SE and that have
accumulated more than 15,000 total flight cycles.
(o) Credit for Previous Actions
This paragraph provides credit for the corresponding actions
specified in paragraphs (g), (h), (i), (j), (k), and (m) of this AD,
if those actions were performed before the effective date of this AD
using the service information identified in paragraph (o)(1),
(o)(2), or (o)(3) of this AD.
(1) Boeing Special Attention Service Bulletin 737-53A1232, dated
April 2, 2007.
[[Page 44509]]
(2) Boeing Special Attention Service Bulletin 737-53A1232,
Revision 1, dated May 18, 2012.
(3) Boeing Special Attention Service Bulletin 737-53A1232,
Revision 2, dated July 26, 2013.
(p) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, 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 certification office, send it to the attention of the
person identified in paragraph (q)(1) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for repairs for AD 2008-12-04 are
approved as AMOCs for the installation of the repair specified in
this AD, provided all post-repair inspections are done at the
applicable times specified in the AMOC.
(5) AMOCs approved previously for preventive modifications for
AD 2008-12-04 are approved as AMOCs for the installation of the
preventive modification specified in this AD, provided all post-
modification inspections are done at the applicable times specified
in the AMOC, or in tables 1a and 1b of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1232,
Revision 3, dated July 27, 2015, whichever occurs first. The AMOC
must include all of the inspections specified in Tables 1a and 1b of
Boeing Alert Service Bulletin 737-53A1232, Revision 3, dated July
27, 2015.
(q) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601
Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; fax:
425-917-6450; email: alan.pohl@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
(r) 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 737-53A1232, Revision 3, dated
July 27, 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
Standards Branch, 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 September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-20114 Filed 9-22-17; 8:45 am]
BILLING CODE 4910-13-P
