Airworthiness Directives; The Boeing Company Airplanes, 26573-26576 [2017-11131]
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Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations
(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. 2017–0024, dated
February 13, 2017, for related information.
The MCAI can be found in the AD docket on
the Internet at https://www.regulations.gov/
document?D=FAA-2017-0194-0002.
(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) Temporary Revision No. 38 to PC–12/
47E Pilot’s Operating Handbook, Airplane
Flight Manual 02277, Section 2—Limitations,
Report No: 02277, dated February 8, 2017.
(ii) Reserved.
(3) For PILATUS AIRCRAFT LTD. service
information identified in this AD, contact
PILATUS AIRCRAFT LTD., Customer
Support PC–12, CH–6371 Stans, Switzerland;
phone: +41 41 619 33 33; fax: +41 41 619 73
11; email: SupportPC12@pilatusaircraft.com; Internet: www.pilatusaircraft.com.
(4) You may view this service information
at the 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–2017–0194.
(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 May
26, 2017.
Pat Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
asabaliauskas on DSKBBXCHB2PROD with RULES
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9115; Directorate
Identifier 2016–NM–068–AD; Amendment
39–18903; AD 2017–11–04]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
(i) Material Incorporated by Reference
[FR Doc. 2017–11411 Filed 6–7–17; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 767–200, –300,
and –400ER series airplanes. This AD
was prompted by an evaluation by the
design approval holder (DAH)
indicating that the fuselage skin lap
splices are subject to widespread fatigue
damage (WFD). This AD requires
repetitive inspections to detect any
crack in the fuselage skin at the skin lap
splices, and corrective actions if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective July 13,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 13, 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–
9115.
DATES:
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–
9115; 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
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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:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6447;
fax: 425–917–6590; email:
wayne.lockett@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 all The Boeing Company Model
767–200, –300, and –400ER series
airplanes. The NPRM published in the
Federal Register on September 28, 2016
(81 FR 66553). The NPRM was
prompted by an evaluation by the DAH
indicating that the fuselage skin lap
splices are subject to WFD. The NPRM
proposed to require repetitive
inspections to detect any crack in the
fuselage skin at the skin lap splices, and
repair of any crack found during the
inspection. We are issuing this AD to
detect and correct cracks at the fuselage
skin lap splice, which can rapidly link
up, possibly resulting in rapid
decompression and loss of 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 another commenter,
Connor Blevins, stated their support for
the content of the NPRM.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing the Supplemental Type
Certificate (STC) ST01920SE does not
affect the actions specified in the
NPRM.
We concur with the commenter. We
have redesignated paragraph (c) of the
proposed AD as (c)(1) in this AD and
added paragraph (c)(2) to state that
installation of STC ST01920SE does not
affect the ability to accomplish the
actions required by this final rule.
Therefore, for airplanes on which STC
ST01920SE is installed, a ‘‘change in
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product’’ alternative method of
compliance (AMOC) approval request is
not necessary to comply with the
requirements of 14 CFR 39.17.
FAA approval, but does not require an
alternative method of compliance
(AMOC). We have not revised this AD
in this regard.
also redesignated subsequent
paragraphs accordingly.
Request for Clarification of
Requirements
United Airlines (UAL) requested that
we clarify whether Boeing Alert Service
Bulletin 767–53A0264, Revision 1,
dated April 25, 2016 (‘‘ASB 767–
53A0264 R1’’) or the structural repair
manual (SRM) takes precedence for
inspection requirements and whether
the operator is able to choose which
inspection method to utilize. UAL
pointed out that Part 3 of ASB 767–
53A0264 R1 specifies high frequency
eddy current (HFEC) for the initial and
repeat inspections, but the
corresponding SRM repair provides the
option of HFEC or low frequency eddy
current inspections.
We agree that clarification is
necessary. Note (a) of tables 1 through
9 of paragraph 1.E., ‘‘Compliance,’’ of
ASB 767–53A0264 R1 terminates the
AD-mandated inspections for any area
under an approved repair. The repairs
are evaluated with their own damage
tolerance inspection program. The postrepair inspection program is different
than the baseline inspections specified
in Part 3 of ASB 767–53A0264 R1, and
as mentioned previously, post-repair
damage tolerance inspections are not
required by this AD, but are
airworthiness limitation items (ALIs)
and are required by maintenance and
operational rules. Any deviation from
the post-repair ALI inspections requires
Request for Clarification of Repetitive
Inspection Intervals
UAL requested that we clarify the
repetitive inspection intervals for any
Category B repair specified in the SRM
and accomplished as specified in Part 8
of ASB 767–53A0264 R1. UAL pointed
out that the Part 8 repetitive inspection
intervals conflict with the inspection
intervals of Category B repairs specified
in the SRM. UAL specified that if a
repair is accomplished at the times
proposed in the NPRM, the repair is
already past the initial inspection
thresholds specified in the SRM.
We agree that there is a conflict
between the service information and the
Category B repair specified in the SRM,
and that clarification is necessary. We
have coordinated with Boeing regarding
this issue. ASB 767–53A0264 R1 refers
to the SRM for these repair instructions.
Boeing has revised and published
temporary revisions to the SRM that
address this issue and these revisions
provide an inspection threshold based
on flight cycles after repair installation.
Additionally, we have revised
paragraph (h) of this AD to clarify that
the post-repair damage tolerance
inspections are not required by this AD,
but are ALIs and are required by
maintenance and operational rules. Any
deviation from the post-repair ALI
inspections requires FAA approval, but
does not require an AMOC. We have
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.
Conclusion
Related Service Information Under 1
CFR Part 51
We reviewed Boeing ASB 767–
53A0264 R1. The service information
describes procedures for repetitive
inspections and repair for any crack in
the fuselage skin at the skin lap splices.
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 332
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Inspections .....
168 work-hours × $85 per hour = $14,280
per inspection cycle.
The size of the area that requires
repair must be determined before
material and work-hour costs can be
estimated. Additionally, materials for
repairs must be supplied by the
operator. Therefore, we cannot provide
cost estimates for the on-condition
actions specified in this AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
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Parts cost
Cost per product
$0
$14,280 per inspection cycle.
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
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Cost on U.S. operators
$4,740,960 per inspection
cycle.
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
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Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–11–04 The Boeing Company:
Amendment 39–18903; Docket No.
FAA–2016–9115; Directorate Identifier
2016–NM–068–AD.
(a) Effective Date
This AD is effective July 13, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 767–200, –300, and –400ER
series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin
767–53A0264, Revision 1, dated April 25,
2016 (‘‘ASB 767–53A0264 R1’’).
(2) Installation of Supplemental Type
Certificate (STC) ST01920SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/59027F43B9A7486E
86257B1D006591EE?Open
Document&Highlight=st01920se) does not
affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes
on which STC ST01920SE is installed, a
‘‘change in product’’ alternative method of
compliance (AMOC) approval request is not
necessary to comply with the requirements of
14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
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(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder indicating that
the fuselage skin lap splices are subject to
widespread fatigue damage. We are issuing
this AD to detect and correct cracks at the
fuselage skin lap splice, which can rapidly
link up, possibly resulting in rapid
decompression and loss of structural
integrity of the airplane.
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16:16 Jun 07, 2017
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(g) Repetitive Inspections and Corrective
Actions
Except as specified by paragraph (i) of this
AD, at the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of ASB 767–
53A0264 R1: Do external surface high
frequency eddy current (HFEC), internal
surface HFEC, and external surface low
frequency eddy current inspections, as
applicable, to detect cracks in the fuselage
skin lap splices, in accordance with the
Accomplishment Instructions of ASB 767–
53A0264 R1. If any crack is found during any
inspection required by this AD, before further
flight, repair in accordance with Part 8 of the
Accomplishment Instructions of ASB 767–
53A0264 R1. Repeat the inspections
thereafter at the times specified in paragraph
1.E., ‘‘Compliance,’’ of ASB 767–53A0264
R1, as applicable.
(h) AD Provisions for Part 26 Supplemental
Inspections
Repairs identified in Part 8 of ASB 767–
53A0264 R1 specify post-modification
airworthiness limitation inspections in
compliance with 14 CFR 25.571(a)(3) at the
modified 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
AMOC.
(i) Service Information Exception
Where ASB 767–53A0264 R1 specifies a
compliance time ‘‘after the original issue date
of this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(j) Credit for Previous Actions
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 Alert
Service Bulletin 767–53A0264, dated May
12, 2015.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (l)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
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26575
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as specified in paragraph (h) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(l) Related Information
(1) For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6447; fax: 425–
917–6590; email: wayne.lockett@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) 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 767–
53A0264, Revision 1, dated April 25, 2016.
(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://
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www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on May 15,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–11131 Filed 6–7–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0531; Directorate
Identifier 2016–NM–178–AD; Amendment
39–18916; AD 2017–12–01]
RIN 2120–AA64
p.m., Monday through Friday, except
Federal holidays.
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–2017–
0531.
Examining the AD Docket
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767–200
series airplanes. This AD requires
repetitive inspections for damage of a
certain drive arm assembly, and related
investigative and corrective actions if
necessary. This AD was prompted by a
report indicating that during an
inspection associated with a flap, the
extend overtravel stops on an actuator
crank arm assembly were making
contact with an adjacent drive arm
assembly when the flaps were retracted.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective June 23,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 23, 2017.
We must receive comments on this
AD by July 24, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
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SUMMARY:
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You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0531; 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 street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6447;
fax: 425–917–6590; email:
wayne.lockett@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We have received a report indicating
that during an inspection of the
outboard support assembly number 3 of
the inboard flap of the left wing, an
operator observed that the extend
overtravel stops on the 4–5 actuator
crank arm assembly were making
contact with the adjacent 6–9 drive arm
assembly when the flaps were totally
retracted. The problem occurred with
the installation of 767–400ER flaps,
modified as specified in supplemental
type certificate (STC) ST01329WI–D, on
767–200 airplanes. This condition, if
not corrected, could result in
interference between the 6–9 drive arm
assembly and the 4–5 actuator crank
arm assembly, which causes a fatigue
load on the 5–7 link that could result in
failure of the 5–7 link and subsequent
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loss of the inboard flap. Continued safe
flight and landing could be adversely
affected after the departure of a flap
during takeoff or landing. We are
issuing this AD to correct the unsafe
condition on these products.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 767–57A0134, dated May 27,
2016. The service information describes
procedures for repetitive inspections for
damage caused by interference between
the 6–9 drive arm assembly and the 4–
5 actuator crank arm assembly on the
inboard flap outboard support assembly
number 3 and number 6, and related
investigative and corrective actions.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
AD Requirements
This AD requires accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between this AD and the Service
Information.’’ For information on the
procedures and compliance times, see
this service information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0531.
The phrase ‘‘related investigative
actions’’ is used in this AD. Related
investigative actions are follow-on
actions that (1) are related to the
primary action, and (2) further
investigate the nature of any condition
found. Related investigative actions in
an AD could include, for example,
inspections.
The phrase ‘‘corrective actions’’ is
used in this AD. Corrective actions
correct or address any condition found.
Corrective actions in an AD could
include, for example, repairs.
Differences Between This AD and the
Service Information
Boeing Alert Service Bulletin 767–
57A0134, dated May 27, 2016, specifies
to contact the manufacturer for certain
instructions, but this AD would require
using repair methods, modification
deviations, and alteration deviations in
one of the following ways:
E:\FR\FM\08JNR1.SGM
08JNR1
Agencies
[Federal Register Volume 82, Number 109 (Thursday, June 8, 2017)]
[Rules and Regulations]
[Pages 26573-26576]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11131]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9115; Directorate Identifier 2016-NM-068-AD;
Amendment 39-18903; AD 2017-11-04]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 767-200, -300, and -400ER series airplanes. This
AD was prompted by an evaluation by the design approval holder (DAH)
indicating that the fuselage skin lap splices are subject to widespread
fatigue damage (WFD). This AD requires repetitive inspections to detect
any crack in the fuselage skin at the skin lap splices, and corrective
actions if necessary. We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 13, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 13,
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-
9115.
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-
9115; 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; email: wayne.lockett@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 all The Boeing Company
Model 767-200, -300, and -400ER series airplanes. The NPRM published in
the Federal Register on September 28, 2016 (81 FR 66553). The NPRM was
prompted by an evaluation by the DAH indicating that the fuselage skin
lap splices are subject to WFD. The NPRM proposed to require repetitive
inspections to detect any crack in the fuselage skin at the skin lap
splices, and repair of any crack found during the inspection. We are
issuing this AD to detect and correct cracks at the fuselage skin lap
splice, which can rapidly link up, possibly resulting in rapid
decompression and loss of 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 another commenter, Connor Blevins, stated their support
for the content of the NPRM.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing the Supplemental
Type Certificate (STC) ST01920SE does not affect the actions specified
in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as (c)(1) in this AD and added paragraph (c)(2) to
state that installation of STC ST01920SE does not affect the ability to
accomplish the actions required by this final rule. Therefore, for
airplanes on which STC ST01920SE is installed, a ``change in
[[Page 26574]]
product'' alternative method of compliance (AMOC) approval request is
not necessary to comply with the requirements of 14 CFR 39.17.
Request for Clarification of Requirements
United Airlines (UAL) requested that we clarify whether Boeing
Alert Service Bulletin 767-53A0264, Revision 1, dated April 25, 2016
(``ASB 767-53A0264 R1'') or the structural repair manual (SRM) takes
precedence for inspection requirements and whether the operator is able
to choose which inspection method to utilize. UAL pointed out that Part
3 of ASB 767-53A0264 R1 specifies high frequency eddy current (HFEC)
for the initial and repeat inspections, but the corresponding SRM
repair provides the option of HFEC or low frequency eddy current
inspections.
We agree that clarification is necessary. Note (a) of tables 1
through 9 of paragraph 1.E., ``Compliance,'' of ASB 767-53A0264 R1
terminates the AD-mandated inspections for any area under an approved
repair. The repairs are evaluated with their own damage tolerance
inspection program. The post-repair inspection program is different
than the baseline inspections specified in Part 3 of ASB 767-53A0264
R1, and as mentioned previously, post-repair damage tolerance
inspections are not required by this AD, but are airworthiness
limitation items (ALIs) and are required by maintenance and operational
rules. Any deviation from the post-repair ALI inspections requires FAA
approval, but does not require an alternative method of compliance
(AMOC). We have not revised this AD in this regard.
Request for Clarification of Repetitive Inspection Intervals
UAL requested that we clarify the repetitive inspection intervals
for any Category B repair specified in the SRM and accomplished as
specified in Part 8 of ASB 767-53A0264 R1. UAL pointed out that the
Part 8 repetitive inspection intervals conflict with the inspection
intervals of Category B repairs specified in the SRM. UAL specified
that if a repair is accomplished at the times proposed in the NPRM, the
repair is already past the initial inspection thresholds specified in
the SRM.
We agree that there is a conflict between the service information
and the Category B repair specified in the SRM, and that clarification
is necessary. We have coordinated with Boeing regarding this issue. ASB
767-53A0264 R1 refers to the SRM for these repair instructions. Boeing
has revised and published temporary revisions to the SRM that address
this issue and these revisions provide an inspection threshold based on
flight cycles after repair installation. Additionally, we have revised
paragraph (h) of this AD to clarify that the post-repair damage
tolerance inspections are not required by this AD, but are ALIs and are
required by maintenance and operational rules. Any deviation from the
post-repair ALI inspections requires FAA approval, but does not require
an AMOC. We have also redesignated subsequent paragraphs accordingly.
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 ASB 767-53A0264 R1. The service information
describes procedures for repetitive inspections and repair for any
crack in the fuselage skin at the skin lap splices. 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 332 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...................... 168 work-hours x $0 $14,280 per $4,740,960 per
$85 per hour = inspection cycle.. inspection cycle.
$14,280 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
The size of the area that requires repair must be determined before
material and work-hour costs can be estimated. Additionally, materials
for repairs must be supplied by the operator. Therefore, we cannot
provide cost estimates for the on-condition actions specified in this
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities
[[Page 26575]]
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):
2017-11-04 The Boeing Company: Amendment 39-18903; Docket No. FAA-
2016-9115; Directorate Identifier 2016-NM-068-AD.
(a) Effective Date
This AD is effective July 13, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 767-200, -300,
and -400ER series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 767-53A0264, Revision 1,
dated April 25, 2016 (``ASB 767-53A0264 R1'').
(2) Installation of Supplemental Type Certificate (STC)
ST01920SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE?OpenDocument&Highlight=st01920se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01920SE 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 an evaluation by the design approval
holder indicating that the fuselage skin lap splices are subject to
widespread fatigue damage. We are issuing this AD to detect and
correct cracks at the fuselage skin lap splice, which can rapidly
link up, possibly resulting in rapid decompression and loss of
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Corrective Actions
Except as specified by paragraph (i) of this AD, at the
applicable times specified in paragraph 1.E., ``Compliance,'' of ASB
767-53A0264 R1: Do external surface high frequency eddy current
(HFEC), internal surface HFEC, and external surface low frequency
eddy current inspections, as applicable, to detect cracks in the
fuselage skin lap splices, in accordance with the Accomplishment
Instructions of ASB 767-53A0264 R1. If any crack is found during any
inspection required by this AD, before further flight, repair in
accordance with Part 8 of the Accomplishment Instructions of ASB
767-53A0264 R1. Repeat the inspections thereafter at the times
specified in paragraph 1.E., ``Compliance,'' of ASB 767-53A0264 R1,
as applicable.
(h) AD Provisions for Part 26 Supplemental Inspections
Repairs identified in Part 8 of ASB 767-53A0264 R1 specify post-
modification airworthiness limitation inspections in compliance with
14 CFR 25.571(a)(3) at the modified 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 AMOC.
(i) Service Information Exception
Where ASB 767-53A0264 R1 specifies a compliance time ``after the
original issue date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(j) Credit for Previous Actions
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 Alert Service Bulletin 767-
53A0264, dated May 12, 2015.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (l)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) Except as specified in paragraph (h) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (k)(4)(i) and
(k)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. An AMOC is required for any deviations to RC steps,
including substeps and identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(l) Related Information
(1) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447;
fax: 425-917-6590; email: wayne.lockett@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) 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 767-53A0264, Revision 1, dated
April 25, 2016.
(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://
[[Page 26576]]
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on May 15, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-11131 Filed 6-7-17; 8:45 am]
BILLING CODE 4910-13-P