Airworthiness Directives; Airbus Airplanes, 33787-33790 [2017-15119]
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Federal Register / Vol. 82, No. 139 / Friday, July 21, 2017 / Rules and Regulations
FAA–2016–9516; Directorate Identifier
2016–NM–053–AD.
(a) Effective Date
This AD is effective August 25, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 787–8 and 787–9 airplanes,
certificated in any category, as identified in
Boeing Service Bulletin B787–81205–
SB270030–00, Issue 001, dated October 22,
2015.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Unsafe Condition
This AD was prompted by wire harness
chafing on the electro-mechanical actuators
(EMAs) for certain spoilers due to
insufficient separation with adjacent
structure. We are issuing this AD to prevent
chafing and consequent wire damage that
could result in a potential source of ignition
in the flammable leakage zone and a
consequent fire or explosion.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) EMA Replacement
Within 40 months after the effective date
of this AD, replace the EMAs with new
EMAs, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin B787–81205–SB270030–00,
Issue 001, dated October 22, 2015.
(h) 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 (i) 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.
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(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (h)(4)(i) and (h)(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. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. 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.
(i) Related Information
For more information about this AD,
contact Sean Schauer, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6479; fax: 425–917–6590; email:
sean.schauer@faa.com.
(j) 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 Service Bulletin B787–81205–
SB270030–00, Issue 001, dated October 22,
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 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 12,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–15121 Filed 7–20–17; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9572; Directorate
Identifier 2016–NM–151–AD; Amendment
39–18963; AD 2017–15–03]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2014–08–
02 which applied to certain Airbus
Model A300 B4–600 and A300 B4–600R
series airplanes. AD 2014–08–02
required modifying the profile of
stringer run-outs of both wings,
including a high frequency eddy current
(HFEC) inspection of the fastener holes
for defects, and repairs if necessary.
This new AD retains the actions
required by AD 2014–08–02 and revises
the compliance times. This AD was
prompted by further analysis in the
context of widespread fatigue damage
(WFD), which concluded that shorter
compliance times are necessary to meet
specified requirements to address WFD.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective August 25,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 25, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of May 21, 2014 (79 FR
21392, April 16, 2014).
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@
airbus.com; Internet https://
www.airbus.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–2016–9572.
SUMMARY:
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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–
9572; 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 (telephone 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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2014–08–02,
Amendment 39–17826 (79 FR 21392,
April 16, 2014) (‘‘AD 2014–08–02’’). AD
2014–08–02 applied to certain Airbus
Model A300 B4–600 and A300 B4–600R
series airplanes. The NPRM published
in the Federal Register on March 13,
2017 (82 FR 13405). The NPRM was
prompted by further analysis in the
context of WFD, which concluded that
a shorter compliance time is necessary
to meet specified requirements to
address WFD. The NPRM proposed to
continue to require modifying the
profile of stringer run-outs of both
wings, including a high frequency eddy
current inspection of the fastener holes
for defects, and repairs if necessary. The
NPRM also proposed to require a
revised compliance time for these
actions. We are issuing this AD to
prevent cracking in the bottom wing
skin stringers, which could result in
reduced structural integrity of the
wings.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0174, dated August 30,
2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A300 B4–600 and A300 B4–600R
series airplanes. The MCAI states:
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During full-scale fatigue testing, cracks
were detected in the bottom wing skin
stringers at Rib 14. In addition, operators
have also reported finding cracks in the same
area on in-service aeroplanes.
This condition, if not detected and
corrected, could impair the structural
integrity of the wings.
Additional analysis results showed that the
improved design of the stringer run-out was
necessary for aeroplanes operating beyond
the Extended Service Goal 1.
To address this unsafe condition, Airbus
issued Service Bulletin (SB) A300–57–6046
Revision 01 to provide modification
instructions, and EASA issued AD 2013–
0008 (later revised) [which corresponds to
FAA AD 2014–08–02], to require the removal
of the stringer end run-out plate at stringer
19 on the bottom wing skin and a re-profiling
modification of the stringers 10, 11, 12, 17
and 19.
Since that [EASA] AD was issued, further
analysis in the context of Widespread Fatigue
Damage (WFD), concluded that a threshold
reduction is necessary to meet the WFD
requirements. Consequently, Airbus revised
SB A300–57–6046 accordingly (now at
Revision 03).
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2013–0008R1, which is superseded, but
reduces the modification threshold, and
introduces a pre-mod High Frequency Eddy
Current (HFEC) inspection.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9572.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
FedEx Express had no objection to the
NPRM.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Service Bulletin
A300–57–6046, Revision 03, including
Appendix 01, dated February 4, 2015.
The service information describes
procedures to modify the profile of
stringer run-outs of both wings,
including a HFEC inspection of the
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fastener holes for defects, and repairs. It
also describes new compliance times for
completing the modifications. 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 29
airplanes of U.S. registry.
The actions required by AD 2014–08–
02, and retained in this AD, take about
63 work-hours per product, at an
average labor rate of $85 per work-hour.
Required parts cost about $2,360 per
product. Based on these figures
(accounting for updated work-hour and
parts cost estimates), the estimated cost
of this AD on U.S. operators is $7,715
per product.
We have received no definitive data
that would enable us to provide cost
estimates for any on-condition actions
specified in this AD. We have no way
of determining the number of aircraft
that might need these repairs.
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
We 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;
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2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2014–08–02, Amendment 39–17826 (79
FR 21392, April 16, 2014), and adding
the following new AD:
■
2017–15–03 Airbus: Amendment 39–18963;
Docket No. FAA–2016–9572; Directorate
Identifier 2016–NM–151–AD.
(a) Effective Date
This AD is effective August 25, 2017.
(b) Affected ADs
This AD replaces AD 2014–08–02,
Amendment 39–17826 (79 FR 21392, April
16, 2014) (‘‘AD 2014–08–02’’).
(c) Applicability
This AD applies to Airbus Model A300–
B4–601, B4–603, B4–620, and B4–622
airplanes, and Model A300–B4–605R and
B4–622R airplanes, certificated in any
category, except airplanes on which Airbus
Modification 10324 or 10325 has been
embodied in production.
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(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by an evaluation by
the design approval holder indicating that
certain wing skin stringers are subject to
widespread fatigue damage. We are issuing
this AD to prevent cracking in the bottom
wing skin stringers, which could result in
reduced structural integrity of the wings.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Modification of Rib 14, With
Revised Compliance Time and Service
Information
This paragraph restates the requirements of
paragraph (g) of AD 2014–08–02, with
revised compliance times and service
information. At the time specified in
paragraph (g)(1) or (g)(2) of this AD,
whichever occurs earlier, modify the profile
of stringer run-outs at rib 14 of both wings,
including a high frequency eddy current
inspection of the fastener holes for defects
and all applicable repairs, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–57–6046, Revision 02,
dated June 21, 2013; or Revision 03,
including Appendix 01, dated February 4,
2015; except as required by paragraph (h) of
this AD. Do all applicable repairs before
further flight. As of the effective date of this
AD, only Airbus Service Bulletin A300–57–
6046, Revision 03, including Appendix 01,
dated February 4, 2015, may be used.
(1) Before the accumulation of 42,500 total
flight cycles, or within 2,000 flight cycles
after May 21, 2014 (the effective date of AD
2014–08–02), whichever occurs later.
(2) Before the accumulation of 30,000 total
flight cycles, or within 2,000 flight cycles
after the effective date of this AD, whichever
occurs later.
(h) Retained Exception to the Service
Information, With Revised Service
Information
This paragraph restates the requirements of
paragraph (h) of AD 2014–08–02, with
revised service information.
(1) Where Airbus Mandatory Service
Bulletin A300–57–6046, Revision 02, dated
June 21, 2013, specifies to contact Airbus for
repair instructions, this AD requires
contacting the Manager, ANM–116,
International Branch, Transport Airplane
Directorate, FAA, or the European Aviation
Safety Agency (EASA) (or its delegated agent)
for repair instructions and doing those
repairs before further flight.
(2) Where Airbus Service Bulletin A300–
57–6046, Revision 03, including Appendix
01, dated February 4, 2015, specifies to
contact Airbus for appropriate action: Before
further flight, accomplish corrective actions
in accordance with the procedures specified
in paragraph (j)(2) of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using the service information
specified in paragraph (i)(1), (i)(2), or (i)(3) of
this AD.
(1) Airbus Service Bulletin A300–57–6046,
dated January 18, 1994, which is not
incorporated by reference in this AD.
(2) Airbus Service Bulletin A300–57–6046,
Revision 01, dated April 18, 2011, which is
not incorporated by reference in this AD.
(3) Airbus Service Bulletin A300–57–6046,
Revision 02, dated June 21, 2013, which was
incorporated by reference in AD 2014–08–02.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
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(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to the
attention of the person identified in
paragraph (k)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (h) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
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 procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0174, dated
August 30, 2016, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–9572.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (l)(4) and (l)(5) of this AD.
(l) 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.
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(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on August 25, 2017.
(i) Airbus Service Bulletin A300–57–6046,
Revision 03, including Appendix 01, dated
February 4, 2015.
(ii) Reserved.
(4) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(5) 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.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 11,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–15119 Filed 7–20–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2016–9480; Airspace
Docket No. 16–AEA–13]
Amendment of Class D and Class E
Airspace; Morgantown, WV
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action amends Class E
airspace designated as an extension to a
Class D surface area by removing the
Notice to Airmen (NOTAM) part-time
status at Morgantown Municipal
Airport-Walter L. Bill Hart Field,
Morgantown, WV, and updating the
airport’s geographic coordinates. Also,
this action updates the geographic
coordinates of the airport listed in Class
D airspace, Class E surface area airspace,
and Class E 700 foot airspace. This
action enhances the safety and
management of instrument flight rules
(IFR) operations at the airport.
DATES: Effective 0901 UTC, October 12,
2017. The Director of the Federal
Register approves this incorporation by
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SUMMARY:
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reference action under title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.11 and publication of conforming
amendments.
ADDRESSES: FAA Order 7400.11A,
Airspace Designations and Reporting
Points, and subsequent amendments can
be viewed online at https://www.faa.gov/
air_traffic/publications/. For further
information, you can contact the
Airspace Policy Group, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.11A at NARA, call (202)
741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal-regulations/ibr_
locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
FOR FURTHER INFORMATION CONTACT: John
Fornito, Operations Support Group,
Eastern Service Center, Federal Aviation
Administration, P.O. Box 20636,
Atlanta, Georgia 30320; telephone (404)
305–6364.
SUPPLEMENTARY INFORMATION:
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it amends
Class D and Class E airspace at
Morgantown Municipal Airport-Walter
L. Bill Hart Field, Morgantown, WV, in
support of IFR operations at the airport.
History
On April 7, 2017, the FAA published
in the Federal Register (82 FR 16958)
Docket No. FAA–2016–9480, a notice of
proposed rulemaking (NPRM) to amend
Class E airspace designated as an
extension to a Class D surface area at
Morgantown Municipal Airport-Walter
L. Bill Hart Field, Morgantown, WV, by
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
removing the NOTAM part-time status
of the Class E airspace designated as an
extension to a Class D surface area.
Also, the geographic coordinates of the
airport would be adjusted in the
associated Class D and E airspace.
Interested parties were invited to
participate in this rulemaking effort by
submitting written comments on the
proposal to the FAA. No comments
were received.
This action also makes an editorial
change to the associated Class D and E
airspace legal descriptions removing the
words ‘‘(previously called Airport/
Facility Directory). Except for this
change, the rule is the same as
published in the NPRM.
Class D and E airspace designations
are published in paragraphs 5000, 6002,
6004, and 6005, respectively, of FAA
Order 7400.11A dated August 3, 2016,
and effective September 15, 2016, which
is incorporated by reference in 14 CFR
part 71.1. The Class D and E airspace
designations listed in this document
will be published subsequently in the
Order.
Availability and Summary of
Documents for Incorporation by
Reference
This document amends FAA Order
7400.11A, Airspace Designations and
Reporting Points, dated August 3, 2016,
and effective September 15, 2016. FAA
Order 7400.11A is publicly available as
listed in the ADDRESSES section of this
document. FAA Order 7400.11A lists
Class A, B, C, D, and E airspace areas,
air traffic service routes, and reporting
points.
The Rule
This amendment to Title 14, Code of
Federal Regulations (14 CFR) part 71
amends Class E Airspace designated as
an extension to a Class D surface area at
Morgantown Municipal Airport-Walter
L. Bill Hart Field, Morgantown, WV, by
eliminating the NOTAM information
from the regulatory text that reads,
‘‘This Class E airspace area is effective
during the specific dates and time
established in advance by Notice to
Airmen. The effective date and time will
thereafter be continuously published in
the Airport/Facility Directory.’’ This
action also amends Class D airspace,
Class E surface area airspace, and Class
E airspace extending upward from 700
feet or more above the surface by
updating the geographic coordinates of
the airport to be in concert with the
FAA’s aeronautical database.
Additionally, this action removes the
words ‘‘(previously called Airport/
Facility Directory)’’ from the associated
E:\FR\FM\21JYR1.SGM
21JYR1
Agencies
[Federal Register Volume 82, Number 139 (Friday, July 21, 2017)]
[Rules and Regulations]
[Pages 33787-33790]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15119]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9572; Directorate Identifier 2016-NM-151-AD;
Amendment 39-18963; AD 2017-15-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2014-08-02
which applied to certain Airbus Model A300 B4-600 and A300 B4-600R
series airplanes. AD 2014-08-02 required modifying the profile of
stringer run-outs of both wings, including a high frequency eddy
current (HFEC) inspection of the fastener holes for defects, and
repairs if necessary. This new AD retains the actions required by AD
2014-08-02 and revises the compliance times. This AD was prompted by
further analysis in the context of widespread fatigue damage (WFD),
which concluded that shorter compliance times are necessary to meet
specified requirements to address WFD. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective August 25, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 25,
2017.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of May
21, 2014 (79 FR 21392, April 16, 2014).
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet
https://www.airbus.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-
9572.
[[Page 33788]]
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-
9572; 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 (telephone 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2014-08-02, Amendment 39-17826 (79 FR 21392,
April 16, 2014) (``AD 2014-08-02''). AD 2014-08-02 applied to certain
Airbus Model A300 B4-600 and A300 B4-600R series airplanes. The NPRM
published in the Federal Register on March 13, 2017 (82 FR 13405). The
NPRM was prompted by further analysis in the context of WFD, which
concluded that a shorter compliance time is necessary to meet specified
requirements to address WFD. The NPRM proposed to continue to require
modifying the profile of stringer run-outs of both wings, including a
high frequency eddy current inspection of the fastener holes for
defects, and repairs if necessary. The NPRM also proposed to require a
revised compliance time for these actions. We are issuing this AD to
prevent cracking in the bottom wing skin stringers, which could result
in reduced structural integrity of the wings.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0174, dated August 30, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A300 B4-600 and A300 B4-600R series airplanes. The MCAI states:
During full-scale fatigue testing, cracks were detected in the
bottom wing skin stringers at Rib 14. In addition, operators have
also reported finding cracks in the same area on in-service
aeroplanes.
This condition, if not detected and corrected, could impair the
structural integrity of the wings.
Additional analysis results showed that the improved design of
the stringer run-out was necessary for aeroplanes operating beyond
the Extended Service Goal 1.
To address this unsafe condition, Airbus issued Service Bulletin
(SB) A300-57-6046 Revision 01 to provide modification instructions,
and EASA issued AD 2013-0008 (later revised) [which corresponds to
FAA AD 2014-08-02], to require the removal of the stringer end run-
out plate at stringer 19 on the bottom wing skin and a re-profiling
modification of the stringers 10, 11, 12, 17 and 19.
Since that [EASA] AD was issued, further analysis in the context
of Widespread Fatigue Damage (WFD), concluded that a threshold
reduction is necessary to meet the WFD requirements. Consequently,
Airbus revised SB A300-57-6046 accordingly (now at Revision 03).
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2013-0008R1, which is superseded, but
reduces the modification threshold, and introduces a pre-mod High
Frequency Eddy Current (HFEC) inspection.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9572.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. FedEx Express had no
objection to the NPRM.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Service Bulletin A300-57-6046, Revision 03,
including Appendix 01, dated February 4, 2015. The service information
describes procedures to modify the profile of stringer run-outs of both
wings, including a HFEC inspection of the fastener holes for defects,
and repairs. It also describes new compliance times for completing the
modifications. 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 29 airplanes of U.S. registry.
The actions required by AD 2014-08-02, and retained in this AD,
take about 63 work-hours per product, at an average labor rate of $85
per work-hour. Required parts cost about $2,360 per product. Based on
these figures (accounting for updated work-hour and parts cost
estimates), the estimated cost of this AD on U.S. operators is $7,715
per product.
We have received no definitive data that would enable us to provide
cost estimates for any on-condition actions specified in this AD. We
have no way of determining the number of aircraft that might need these
repairs.
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
We 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;
[[Page 33789]]
2. Is not a ``significant rule'' under the 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)
2014-08-02, Amendment 39-17826 (79 FR 21392, April 16, 2014), and
adding the following new AD:
2017-15-03 Airbus: Amendment 39-18963; Docket No. FAA-2016-9572;
Directorate Identifier 2016-NM-151-AD.
(a) Effective Date
This AD is effective August 25, 2017.
(b) Affected ADs
This AD replaces AD 2014-08-02, Amendment 39-17826 (79 FR 21392,
April 16, 2014) (``AD 2014-08-02'').
(c) Applicability
This AD applies to Airbus Model A300-B4-601, B4-603, B4-620, and
B4-622 airplanes, and Model A300-B4-605R and B4-622R airplanes,
certificated in any category, except airplanes on which Airbus
Modification 10324 or 10325 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder indicating that certain wing skin stringers are subject to
widespread fatigue damage. We are issuing this AD to prevent
cracking in the bottom wing skin stringers, which could result in
reduced structural integrity of the wings.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Modification of Rib 14, With Revised Compliance Time and
Service Information
This paragraph restates the requirements of paragraph (g) of AD
2014-08-02, with revised compliance times and service information.
At the time specified in paragraph (g)(1) or (g)(2) of this AD,
whichever occurs earlier, modify the profile of stringer run-outs at
rib 14 of both wings, including a high frequency eddy current
inspection of the fastener holes for defects and all applicable
repairs, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6046, Revision 02, dated June 21,
2013; or Revision 03, including Appendix 01, dated February 4, 2015;
except as required by paragraph (h) of this AD. Do all applicable
repairs before further flight. As of the effective date of this AD,
only Airbus Service Bulletin A300-57-6046, Revision 03, including
Appendix 01, dated February 4, 2015, may be used.
(1) Before the accumulation of 42,500 total flight cycles, or
within 2,000 flight cycles after May 21, 2014 (the effective date of
AD 2014-08-02), whichever occurs later.
(2) Before the accumulation of 30,000 total flight cycles, or
within 2,000 flight cycles after the effective date of this AD,
whichever occurs later.
(h) Retained Exception to the Service Information, With Revised Service
Information
This paragraph restates the requirements of paragraph (h) of AD
2014-08-02, with revised service information.
(1) Where Airbus Mandatory Service Bulletin A300-57-6046,
Revision 02, dated June 21, 2013, specifies to contact Airbus for
repair instructions, this AD requires contacting the Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, or
the European Aviation Safety Agency (EASA) (or its delegated agent)
for repair instructions and doing those repairs before further
flight.
(2) Where Airbus Service Bulletin A300-57-6046, Revision 03,
including Appendix 01, dated February 4, 2015, specifies to contact
Airbus for appropriate action: Before further flight, accomplish
corrective actions in accordance with the procedures specified in
paragraph (j)(2) of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using the service information specified in paragraph
(i)(1), (i)(2), or (i)(3) of this AD.
(1) Airbus Service Bulletin A300-57-6046, dated January 18,
1994, which is not incorporated by reference in this AD.
(2) Airbus Service Bulletin A300-57-6046, Revision 01, dated
April 18, 2011, which is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A300-57-6046, Revision 02, dated
June 21, 2013, which was incorporated by reference in AD 2014-08-02.
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to the attention of
the person identified in paragraph (k)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (h) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified 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 procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0174, dated August 30,
2016, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2016-9572.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (l)(4) and (l)(5) of this AD.
(l) 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.
[[Page 33790]]
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
August 25, 2017.
(i) Airbus Service Bulletin A300-57-6046, Revision 03, including
Appendix 01, dated February 4, 2015.
(ii) Reserved.
(4) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(5) 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.
(6) 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 July 11, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-15119 Filed 7-20-17; 8:45 am]
BILLING CODE 4910-13-P