Airworthiness Directives; The Boeing Company Airplanes, 8642-8644 [2016-03456]
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8642
Federal Register / Vol. 81, No. 34 / Monday, February 22, 2016 / Rules and Regulations
violations occurring after February 22,
2016.
SUBCHAPTER C—ENTERPRISES
PART 1250—FLOOD INSURANCE
4. The authority citation for part 1250
continues to read as follows:
■
Authority: 12 U.S.C. 4521(a)(4) and 4526;
28 U.S.C. 2461 note; 42 U.S.C. 4001 note; 42
U.S.C. 4012a(f)(3), (4), (5), (8), (9), and (10).
5. Revise § 1250.3(c) to read as
follows:
■
§ 1250.3
Civil money penalties.
*
*
*
*
*
(c) Amount. The maximum civil
money penalty amount is $485 for each
violation that occurs before February 22,
2016, with total penalties not to exceed
$140,000. For violations that occur on or
after February 22, 2016, the civil money
penalty under this section may not
exceed $585 for each violation, with
total penalties assessed under this
section against an Enterprise during any
calendar year not to exceed $150,000.
*
*
*
*
*
Dated: February 15, 2016.
Melvin L. Watt,
Director, Federal Housing Finance Agency.
[FR Doc. 2016–03631 Filed 2–19–16; 8:45 am]
BILLING CODE 8070–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2456; Directorate
Identifier 2015–NM–032–AD; Amendment
39–18401; AD 2016–04–07]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 767 airplanes.
This AD was prompted by reports of
cracking at a central part of the
structure. This AD requires repetitive
inspections of the skin hidden by the
upper and lower splice fittings on both
sides of the fuselage, and corrective
action if necessary. We are issuing this
AD to detect and correct fatigue
cracking of the hidden fuselage skin and
cracking, corrosion, and other damage to
the splice fittings and adjacent visible
fuselage skin and structure that could
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:09 Feb 19, 2016
Jkt 238001
lead to loss of a primary load path
between the fuselage and the wing box,
and consequent reduced structural
integrity of the airplane.
DATES: This AD is effective March 28,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 28, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
P.O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; Internet
https://www.myboeingfleet.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2456.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2456; 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 airplanes. The NPRM published in
the Federal Register on July 6, 2015 (80
FR 38408) (‘‘the NPRM’’). The NPRM
was prompted by reports of cracking at
a central part of the structure. The
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
NPRM proposed to require repetitive
inspections of the skin hidden by the
upper and lower splice fittings on both
sides of the fuselage, and corrective
action if necessary. We are issuing this
AD to detect and correct fatigue
cracking of the hidden fuselage skin and
cracking, corrosion, and other damage to
the splice fittings and adjacent visible
fuselage skin and structure that could
lead to loss of a primary load path
between the fuselage and the wing box,
and consequent 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. Boeing
stated that it concurs with the NPRM.
United Parcel Service (UPS) and United
Airlines stated that they have no
comments on the NPRM. FedEx Express
provided information on how the NPRM
affects its fleet but made no requests.
Request Clarification on the Effect of
Winglets on Accomplishment of the
Proposed Actions
Aviation Partners Boeing stated that
accomplishing Supplemental Type
Certificate (STC) ST01920SE (https://rgl.
faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/59027f43b9a7486e
86257b1d006591ee/$FILE/
ST01920SE.pdf) does not affect the
actions specified in the NPRM.
We concur with the commenter. We
have redesignated paragraph (c) of the
proposed AD as paragraph (c)(1) of this
AD and added new paragraph (c)(2) to
this AD to state that installation of STC
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.
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 change 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
E:\FR\FM\22FER1.SGM
22FER1
Federal Register / Vol. 81, No. 34 / Monday, February 22, 2016 / Rules and Regulations
burden on any operator or increase the
scope of this AD.
describes procedures for repetitive
inspections of the skin and splice
fittings at stringer 29, body station 786
ring chord. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 767–53A0263, dated January
12, 2015. The service information
8643
or by the means identified in the
section.
ADDRESSES
Costs of Compliance
We estimate that this AD affects 430
airplanes of U.S. registry. We estimate
the following costs to comply with this
proposed AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspection ......................
9 work-hours × $85 per hour = $765 per inspection cycle.
$0
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
List of Subjects in 14 CFR Part 39
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
mstockstill on DSK4VPTVN1PROD with RULES
$765 per inspection
cycle.
under the criteria of the Regulatory
Flexibility Act.
Authority for This Rulemaking
Cost per product
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
VerDate Sep<11>2014
16:09 Feb 19, 2016
Jkt 238001
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):
■
2016–04–07 The Boeing Company:
Amendment 39–18401; Docket No.
FAA–2015–2456; Directorate Identifier
2015–NM–032–AD.
(a) Effective Date
This AD is effective March 28, 2016.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing
Company Model 767–200, –300, –300F, and
–400ER series airplanes, certificated in any
category.
(2) Installation of Supplemental Type
Certificate (STC) ST01920SE (https://rgl.faa.
gov/Regulatory_and_Guidance_Library/rgstc.
nsf/0/59027f43b9a7486e86257b1d006591ee/
$FILE/ST01920SE.pdf) 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.
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
Cost on U.S. operators
$328,950 per inspection
cycle.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking at a central part of the structure that
includes the station 786 ring chord at the
tension bolt hole common to the wing front
spar lower chord and the internal bathtub
fittings. We are issuing this AD to detect and
correct fatigue cracking of the hidden
fuselage skin and cracking, corrosion, and
other damage to the splice fittings and
adjacent visible fuselage skin and structure
that could lead to loss of a primary load path
between the fuselage and the wing box, and
consequent reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 767–53A0263, dated
January 12, 2015, except as required by
paragraph (h) of this AD, do external
ultrasonic and detailed inspections to detect
cracking, corrosion, or other damage at the
splice fitting location, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–53A0263, dated January
12, 2015.
(1) If any cracking, corrosion, or other
damage is not found, repeat the inspections
at intervals not to exceed 6,000 flight cycles
or 18,000 flight hours, whichever occurs first.
Accomplishing a repair as specified in
paragraph (g)(2) of this AD terminates the
repetitive inspections in the repaired area
only.
(2) If any cracking, corrosion, or other
damage is found, before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (i) of
this AD. The repetitive inspections of
paragraph (g)(1) are terminated in the
repaired area only.
(h) Exception to Service Information
Specifications
Where Boeing Alert Service Bulletin 767–
53A0263, dated January 12, 2015, specifies a
compliance time ‘‘after the original issue date
E:\FR\FM\22FER1.SGM
22FER1
8644
Federal Register / Vol. 81, No. 34 / Monday, February 22, 2016 / Rules and Regulations
of this Service Bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (j) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (i)(4)(ii) 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.
mstockstill on DSK4VPTVN1PROD with RULES
(j) Related Information
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.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 767–
53A0263, dated January 12, 2015.
(ii) Reserved.
VerDate Sep<11>2014
16:09 Feb 19, 2016
Jkt 238001
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(4) You may view this service information
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington on February
10, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–03456 Filed 2–19–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 157
[Docket No. RM81–19–000]
Natural Gas Pipelines; Project Cost
and Annual Limits
Federal Energy Regulatory
Commission, Energy.
ACTION: Final rule.
AGENCY:
Pursuant to the authority
delegated by 18 CFR 375.308(x)(1), the
Director of the Office of Energy Projects
(OEP) computes and publishes the
project cost and annual limits for
natural gas pipelines blanket
construction certificates for each
calendar year.
DATES: This final rule is effective
February 22, 2016 and establishes cost
limits applicable from January 1, 2016
through December 31, 2016.
FOR FURTHER INFORMATION CONTACT:
Marsha K. Palazzi, Chief, Certificates
Branch 2, Division of Pipeline
Certificates, (202) 502–6785.
Section 157.208(d) of the
Commission’s Regulations provides for
project cost limits applicable to
construction, acquisition, operation and
miscellaneous rearrangement of
facilities (Table I) authorized under the
blanket certificate procedure (Order No.
234, 19 FERC ¶ 61,216). Section
157.215(a) specifies the calendar year
dollar limit which may be expended on
underground storage testing and
SUMMARY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
development (Table II) authorized under
the blanket certificate. Section
157.208(d) requires that the ‘‘limits
specified in Tables I and II shall be
adjusted each calendar year to reflect
the ‘GDP implicit price deflator’
published by the Department of
Commerce for the previous calendar
year.’’
Pursuant to 375.308(x)(1) of the
Commission’s Regulations, the authority
for the publication of such cost limits,
as adjusted for inflation, is delegated to
the Director of the Office of Energy
Projects. The cost limits for calendar
year 2014, as published in Table I of
157.208(d) and Table II of § 157.215(a),
are hereby issued.
Effective Date
This final rule is effective February
22, 2016. The provisions of 5 U.S.C. 804
regarding Congressional review of Final
Rules does not apply to the Final Rule
because the rule concerns agency
procedure and practice and will not
substantially affect the rights or
obligations of non-agency parties. The
Final Rule merely updates amounts
published in the Code of Federal
Regulations to reflect the Department of
Commerce’s latest annual determination
of the Gross Domestic Product (GDP)
implicit price deflator, a mathematical
updating required by the Commission’s
existing regulations.
List of Subjects in 18 CFR Part 157
Administrative practice and
procedure, Natural gas, Reporting and
recordkeeping requirements.
Issued: February 11, 2016.
Ann Miles,
Director, Office of Energy Projects.
Accordingly, 18 CFR part 157 is
amended as follows:
PART 157—[AMENDED]
1. The authority citation for Part 157
continues to read as follows:
■
Authority: 15 U.S.C. 717–717w, 3301–
3432; 42 U.S.C. 7101–7352.
2. Table I in § 157.208(d) is revised to
read as follows:
■
§ 157.208 Construction, acquisition,
operation, replacement, and miscellaneous
rearrangement of facilities.
*
*
*
(d) * * *
*
*
TABLE I
Limit
Year
Auto. proj. cost
limit (Col.1)
1982
E:\FR\FM\22FER1.SGM
$4,200,000
22FER1
Prior notice proj.
cost limit (Col.2)
$12,000,000
]]>Agencies
[Federal Register Volume 81, Number 34 (Monday, February 22, 2016)]
[Rules and Regulations]
[Pages 8642-8644]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03456]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2456; Directorate Identifier 2015-NM-032-AD;
Amendment 39-18401; AD 2016-04-07]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 767 airplanes. This AD was prompted by reports of
cracking at a central part of the structure. This AD requires
repetitive inspections of the skin hidden by the upper and lower splice
fittings on both sides of the fuselage, and corrective action if
necessary. We are issuing this AD to detect and correct fatigue
cracking of the hidden fuselage skin and cracking, corrosion, and other
damage to the splice fittings and adjacent visible fuselage skin and
structure that could lead to loss of a primary load path between the
fuselage and the wing box, and consequent reduced structural integrity
of the airplane.
DATES: This AD is effective March 28, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 28,
2016.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2456.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2456; 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 airplanes. The NPRM published in the Federal Register on July
6, 2015 (80 FR 38408) (``the NPRM''). The NPRM was prompted by reports
of cracking at a central part of the structure. The NPRM proposed to
require repetitive inspections of the skin hidden by the upper and
lower splice fittings on both sides of the fuselage, and corrective
action if necessary. We are issuing this AD to detect and correct
fatigue cracking of the hidden fuselage skin and cracking, corrosion,
and other damage to the splice fittings and adjacent visible fuselage
skin and structure that could lead to loss of a primary load path
between the fuselage and the wing box, and consequent 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. Boeing stated that it concurs with
the NPRM. United Parcel Service (UPS) and United Airlines stated that
they have no comments on the NPRM. FedEx Express provided information
on how the NPRM affects its fleet but made no requests.
Request Clarification on the Effect of Winglets on Accomplishment of
the Proposed Actions
Aviation Partners Boeing stated that accomplishing Supplemental
Type Certificate (STC) ST01920SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does not affect
the actions specified in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1) of this AD and added new paragraph
(c)(2) to this AD to state that installation of STC 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.
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 change described previously and minor editorial
changes. We have determined that these minor changes:
[Agr]re 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
[[Page 8643]]
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 767-53A0263, dated
January 12, 2015. The service information describes procedures for
repetitive inspections of the skin and splice fittings at stringer 29,
body station 786 ring chord. 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 430 airplanes of U.S. registry. We
estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection..................... 9 work-hours x $85 per $0 $765 per $328,950 per
hour = $765 per inspection cycle. inspection
inspection cycle. cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2016-04-07 The Boeing Company: Amendment 39-18401; Docket No. FAA-
2015-2456; Directorate Identifier 2015-NM-032-AD.
(a) Effective Date
This AD is effective March 28, 2016.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing Company Model 767-200, -
300, -300F, and -400ER series airplanes, certificated in any
category.
(2) Installation of Supplemental Type Certificate (STC)
ST01920SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf)
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 reports of cracking at a central part of
the structure that includes the station 786 ring chord at the
tension bolt hole common to the wing front spar lower chord and the
internal bathtub fittings. We are issuing this AD to detect and
correct fatigue cracking of the hidden fuselage skin and cracking,
corrosion, and other damage to the splice fittings and adjacent
visible fuselage skin and structure that could lead to loss of a
primary load path between the fuselage and the wing box, and
consequent reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 767-53A0263, dated
January 12, 2015, except as required by paragraph (h) of this AD, do
external ultrasonic and detailed inspections to detect cracking,
corrosion, or other damage at the splice fitting location, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-53A0263, dated January 12, 2015.
(1) If any cracking, corrosion, or other damage is not found,
repeat the inspections at intervals not to exceed 6,000 flight
cycles or 18,000 flight hours, whichever occurs first. Accomplishing
a repair as specified in paragraph (g)(2) of this AD terminates the
repetitive inspections in the repaired area only.
(2) If any cracking, corrosion, or other damage is found, before
further flight, repair using a method approved in accordance with
the procedures specified in paragraph (i) of this AD. The repetitive
inspections of paragraph (g)(1) are terminated in the repaired area
only.
(h) Exception to Service Information Specifications
Where Boeing Alert Service Bulletin 767-53A0263, dated January
12, 2015, specifies a compliance time ``after the original issue
date
[[Page 8644]]
of this Service Bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (j) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-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) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(i)(4)(i) and (i)(4)(ii) 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.
(j) Related Information
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.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 767-53A0263, dated January 12,
2015.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington on February 10, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-03456 Filed 2-19-16; 8:45 am]
BILLING CODE 4910-13-P
