Airworthiness Directives; Airbus Airplanes, 18547-18550 [2017-06712]
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18547
Rules and Regulations
Federal Register
Vol. 82, No. 75
Thursday, April 20, 2017
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9192; Directorate
Identifier 2016–NM–038–AD; Amendment
39–18845; AD 2017–07–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200, A330–300,
A340–200, and A340–300 series
airplanes. This AD was prompted by a
report of cracking at fastener holes
located at a certain frame on the lower
shell panel junction. This AD requires
repetitive inspections of certain fastener
holes, and related investigative and
corrective actions if necessary. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective May 25,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 25, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 45
80; email airworthiness.A330-A340@
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
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SUMMARY:
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at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–9192.
an unsafe condition for certain Airbus
Model A330, A340–200, and A340–300
series airplanes. The MCAI states:
Examining the AD Docket
During A330/A340 aeroplanes full scale
fatigue test specimen in the FR40-to-fuselage
skin panel junction, fatigue damage has been
found. Corrective actions consisted of the
following actions:
—In-service installation of an internal
reinforcing strap on related junction
´ ´
required by DGAC [Direction Generale de
l’Aviation Civile (DGAC)] France AD 1999–
448–126(B) and [DGAC France] AD 2001–
070(B),
—retrofit improvement of internal reinforcing
strap fatigue life through recommended
Airbus Service Bulletin (SB) A330–53–
3145, and
—new design in production through Airbus
modification 44360.
The aeroplanes listed in the Applicability
section of this [EASA] AD are all aeroplanes
post-mod 44360 and pre-mod 55792 (fuselage
reinforcement at FR40 in production).
Recently, during embodiment of a FR40
web repair on an A330 aeroplane and during
FR40 keel beam fitting replacement on an
A340 aeroplane, the internal strap was
removed and rototest inspection was
performed on several holes.
Cracks were found on both left-hand (LH)
and right-hand (RH) sides on internal strap,
or butt strap, or keel beam fitting, or forward
fitting FR40 flange.
This condition, if not detected and
corrected, could lead to crack propagation,
possibly resulting in reduced structural
integrity of the fuselage.
For the reasons described above, this
[EASA] AD requires repetitive rototest
inspections of 10 fastener holes located at
FR40 lower shell panel junction on both LH
and RH sides, and, depending on findings,
accomplishment of the applicable corrective
actions [which include oversizing, installing
fasteners and repair; and accomplishment of
applicable related investigative actions,
which include a rototest inspection for
cracking after oversizing].
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9192; 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 (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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A330–
200, A330–300, A340–200, and A340–
300 series airplanes. The NPRM
published in the Federal Register on
October 25, 2016 (81 FR 73357) (‘‘the
NPRM’’). The NPRM was prompted by
a report of cracking at fastener holes
located at a certain frame on the lower
shell panel junction. The NPRM
proposed to require repetitive
inspections of certain fastener holes,
and related investigative and corrective
actions if necessary. We are issuing this
AD to detect and correct cracking at
frame 40 on the lower shell panel
junction; such cracking could lead to
reduced structural integrity of the
fuselage.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0136, dated June 13,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
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The compliance time ranges between
20,000 flight cycles or 65,400 flight
hours and 20,800 flight cycles or 68,300
flight hours, depending on airplane
utilization and configuration. The
repetitive inspection interval ranges
between 14,000 flight cycles or 95,200
flight hours and 24,600 flight cycles or
98,700 flight hours, depending on
airplane configuration. 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–
9192.
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Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM from a single
commenter, and the FAA’s response to
that comment.
Request To Refer to Revised Service
Information
Delta Airlines (DAL) requested that
we revise paragraphs (g), (g)(1), and
(g)(2) of the proposed AD to refer to
Airbus Service Bulletin A330–53–3215,
Revision 02, dated November 23, 2016.
DAL also asked that credit be given in
paragraph (h)(1) of the proposed AD for
previously accomplished actions using
Airbus Service Bulletin A330–53–3215,
Revision 01, dated April 17, 2014. DAL
stated that if the Accomplishment
Instructions of Airbus Service Bulletin
A330–53–3215, Revision 01, dated April
17, 2014, are used, operators may
incorrectly reference kit part numbers in
their instructions and would then need
to submit a request for approval of an
alternative method of compliance for
the replaced part.
We agree with the commenter’s
request to refer to Airbus Service
Bulletin A330–53–3215, Revision 02,
dated November 23, 2016. Airbus
Service Bulletin A340–53–4215,
Revision 02, dated November 23, 2016,
has also been issued. No additional
work is required by Airbus Service
Bulletins A330–53–3215, Revision 02;
and A340–53–4215, Revision 02, both
dated November 23, 2016; the revised
service information merely corrects
typographical errors and contains minor
editorial changes.
We have revised the Related Service
Information under 1 CFR part 51 section
of this final rule and paragraphs (g),
(g)(1), and (g)(2) of this AD to refer to
Airbus Service Bulletin A330–53–3215,
Revision 02, dated November 23, 2016;
and Airbus Service Bulletin A340–53–
4215, Revision 02, dated November 23,
2016. We have also revised paragraph
(h)(1) of this AD to provide credit for
actions accomplished prior to the
effective date of this AD using Airbus
Service Bulletin A330–53–3215,
Revision 01, dated April 17, 2014; and
Airbus Service Bulletin A340–53–4215,
Revision 01, dated April 17, 2014.
Conclusion
We reviewed the relevant data,
considered the comment 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 Airbus Service Bulletin
A330–53–3215, Revision 02, dated
November 23, 2016; and Airbus Service
Bulletin A340–53–4215, Revision 02,
dated November 23, 2016. The service
information describes procedures for
repetitive rototest inspections of certain
fastener holes, and related investigative
and corrective actions if necessary.
These documents are distinct since they
apply to different airplane models. 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 41
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Inspection .....................
41 work-hours × $85 per hour = $3,485 per inspection cycle.
$0
$3,485
We estimate the following costs to do
any necessary repairs that are required
based on the results of the required
inspection. We have no way of
Cost on U.S.
operators
$142,885 per inspection cycle.
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Repair ..............................................
46 work-hours × $85 per hour = $3,910 ...................................................
$4,186
$8,096
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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.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
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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.
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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:
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1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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:
(g) Repetitive Inspections and Related
Investigative and Corrective Actions
Within the compliance times defined in
table 1 to the introductory text of paragraph
(g) of this AD, and, thereafter, at intervals not
to exceed the compliance times defined in
Airbus Service Bulletin A330–53–3215,
Revision 02, dated November 23, 2016; or
Airbus Service Bulletin A340–53–4215,
Revision 02, dated November 23, 2016; as
applicable, depending on airplane utilization
and configuration: Accomplish a special
detailed inspection of fastener holes located
at FR40 lower shell panel junction on both
left-hand (LH) and right-side (RH) sides, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
53–3215, Revision 02, dated November 23,
2016; or Airbus Service Bulletin A340–53–
4215, Revision 02, dated November 23, 2016;
as applicable.
TABLE 1 TO THE INTRODUCTORY TEXT
OF PARAGRAPH (g) OF THIS AD—
Compliance Time for Initial Inspection
PART 39—AIRWORTHINESS
DIRECTIVES
Compliance time (whichever
occurs later, A or B)
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
A ...........
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–07–07 Airbus: Amendment 39–18845;
Docket No. FAA–2016–9192; Directorate
Identifier 2016–NM–038–AD.
(a) Effective Date
This AD is effective May 25, 2017.
B ...........
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD, having
serial numbers 0176 through 0915 inclusive.
(1) Airbus Model A330–201, –202, –203,
–223, –243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes.
(2) Airbus Model A340–211, –212, –213,
–311, –312, and –313 airplanes.
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(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of
cracking at fastener holes located at frame
(FR) 40 on the lower shell panel junction. We
are issuing this AD to detect and correct
cracking at FR40 on the lower shell panel
junction; such cracking could lead to reduced
structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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Before exceeding the compliance
time ‘‘threshold’’ defined in table
1 of Airbus Service Bulletin
A330–53–3215, Revision 02,
dated November 23, 2016; or
Airbus Service Bulletin A340–
53–4215, Revision 02, dated
November 23, 2016; as applicable, depending on airplane utilization and configuration and to
be counted from airplane first
flight
For Model A330 airplanes: Within
2,400 flight cycles or 24 months,
whichever occurs first after the
effective date of this AD
For Model A340 airplanes: Within
1,300 flight cycles or 24 months,
whichever occurs first after the
effective date of this AD
(1) If, during any inspection required by
the introductory text of paragraph (g) of this
AD, any crack is detected, before further
flight, accomplish all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
53–3215, Revision 02, dated November 23,
2016; or Airbus Service Bulletin A340–53–
4215, Revision 02, dated November 23, 2016;
as applicable, except where Airbus Service
Bulletin A330–53–3215, Revision 02, dated
November 23, 2016; or Airbus Service
Bulletin A340–53–4215, Revision 02, dated
November 23, 2016, specifies to contact
Airbus for repair instructions, and specifies
that action as ‘‘RC’’ (Required for
Compliance), this AD requires repair before
further flight using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA).
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18549
(2) If, during any inspection required by
the introductory text of paragraph (g) of this
AD, the hole diameter is not within tolerance
of the transition fit as nominal, or first
oversize, or second oversize, or next nominal,
as applicable, and Airbus Service Bulletin
A330–53–3215, Revision 02, dated November
23, 2016; or Airbus Service Bulletin A340–
53–4215, Revision 02, dated November 23,
2016, specifies to contact Airbus for repair
instructions, and specifies that action as
‘‘RC’’ (Required for Compliance), before
further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
(3) Accomplishment of corrective actions,
as required by paragraph (g)(1) of this AD,
does not constitute terminating action for the
repetitive inspections required by the
introductory text of paragraph (g) of this AD.
(4) Accomplishment of a repair on an
airplane, as required by paragraph (g)(2) of
this AD, does not constitute terminating
action for the repetitive inspections required
by the introductory text of paragraph (g) of
this AD for that airplane, unless the method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA indicates otherwise.
(h) Credit for Previous Actions
(1) This paragraph provides credit for
inspections required by the introductory text
of paragraph (g) of this AD and the related
investigative and corrective actions required
by paragraph (g)(1) of this AD, if those
actions were performed before the effective
date of this AD using Airbus Service Bulletin
A330–53–3215, dated June 21, 2013; or
Revision 01, dated April 17, 2014; or Airbus
Service Bulletin A340–53–4215, dated June
21, 2013; or Revision 01, dated April 17,
2014; as applicable.
(2) This paragraph provides credit for the
inspections and corrective actions required
by paragraph (g) of this AD, if those actions
were performed before the effective date of
this AD using Airbus Technical Disposition
(TD) Reference LR57D11023360, Issue B,
dated July 12, 2011.
(i) 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 ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
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principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: 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
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (g)(1) and (g)(2) 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.
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(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0136, dated
June 13, 2014, 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–
2016–9192.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(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 this AD specifies otherwise.
(i) Airbus Service Bulletin A330–53–3215,
Revision 02, dated November 23, 2016.
(ii) Airbus Service Bulletin A340–53–4215,
Revision 02, dated November 23, 2016.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.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
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202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
28, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–06712 Filed 4–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2016–9286; Airspace
Docket No. 16–ANM–13]
Establishment of Class E Airspace,
Denver, CO
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action establishes Class
E en route airspace extending upward
from 1,200 feet above the surface to
accommodate instrument flight rules
(IFR) aircraft under control of the
Denver Air Route Traffic Control Center
(ARTCC), Denver, CO. Establishment of
this airspace area is necessary to ensure
controlled airspace exists in those areas
where the Federal airway structure is
inadequate.
SUMMARY:
Effective 0901 UTC, June 22,
2017. The Director of the Federal
Register approves this incorporation by
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 this
material at NARA, call 202–741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federalregulations/ibr_locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
DATES:
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Tom
Clark, Federal Aviation Administration,
Operations Support Group, Western
Service Center, 1601 Lind Avenue SW.,
Renton, WA 98057; telephone (425)
203–4511.
FOR FURTHER INFORMATION CONTACT:
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 establishes
Class E en route airspace at Denver Air
Route Traffic Control Center, Denver,
CO to ensure controlled airspace exists
in those areas where the Federal airway
structure is inadequate.
History
On November 16, 2016, the FAA
published in the Federal Register (81
FR 80620) Docket FAA–2016–9286 a
notice of proposed rulemaking to
establish Class E en route airspace
extending upward from 1,200 feet above
the surface at Denver, CO. Interested
parties were invited to participate in
this rulemaking effort by submitting
written comments on the proposal to the
FAA. No comments were received.
Class E airspace designations are
published in paragraph 6006 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 E airspace
designation 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.
E:\FR\FM\20APR1.SGM
20APR1
]]>Agencies
[Federal Register Volume 82, Number 75 (Thursday, April 20, 2017)]
[Rules and Regulations]
[Pages 18547-18550]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06712]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 82, No. 75 / Thursday, April 20, 2017 / Rules
and Regulations
[[Page 18547]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9192; Directorate Identifier 2016-NM-038-AD;
Amendment 39-18845; AD 2017-07-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A330-200, A330-300, A340-200, and A340-300 series
airplanes. This AD was prompted by a report of cracking at fastener
holes located at a certain frame on the lower shell panel junction.
This AD requires repetitive inspections of certain fastener holes, and
related investigative and corrective actions if necessary. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective May 25, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 25, 2017.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 45 80; email airworthiness.A330-A340@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-
9192.
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-
9192; 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 (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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A330-
200, A330-300, A340-200, and A340-300 series airplanes. The NPRM
published in the Federal Register on October 25, 2016 (81 FR 73357)
(``the NPRM''). The NPRM was prompted by a report of cracking at
fastener holes located at a certain frame on the lower shell panel
junction. The NPRM proposed to require repetitive inspections of
certain fastener holes, and related investigative and corrective
actions if necessary. We are issuing this AD to detect and correct
cracking at frame 40 on the lower shell panel junction; such cracking
could lead to reduced structural integrity of the fuselage.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0136, dated June 13, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330, A340-200, and A340-300 series airplanes. The MCAI states:
During A330/A340 aeroplanes full scale fatigue test specimen in
the FR40-to-fuselage skin panel junction, fatigue damage has been
found. Corrective actions consisted of the following actions:
--In-service installation of an internal reinforcing strap on
related junction required by DGAC [Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC)] France AD 1999-448-126(B) and [DGAC
France] AD 2001-070(B),
--retrofit improvement of internal reinforcing strap fatigue life
through recommended Airbus Service Bulletin (SB) A330-53-3145, and
--new design in production through Airbus modification 44360.
The aeroplanes listed in the Applicability section of this
[EASA] AD are all aeroplanes post-mod 44360 and pre-mod 55792
(fuselage reinforcement at FR40 in production).
Recently, during embodiment of a FR40 web repair on an A330
aeroplane and during FR40 keel beam fitting replacement on an A340
aeroplane, the internal strap was removed and rototest inspection
was performed on several holes.
Cracks were found on both left-hand (LH) and right-hand (RH)
sides on internal strap, or butt strap, or keel beam fitting, or
forward fitting FR40 flange.
This condition, if not detected and corrected, could lead to
crack propagation, possibly resulting in reduced structural
integrity of the fuselage.
For the reasons described above, this [EASA] AD requires
repetitive rototest inspections of 10 fastener holes located at FR40
lower shell panel junction on both LH and RH sides, and, depending
on findings, accomplishment of the applicable corrective actions
[which include oversizing, installing fasteners and repair; and
accomplishment of applicable related investigative actions, which
include a rototest inspection for cracking after oversizing].
The compliance time ranges between 20,000 flight cycles or 65,400
flight hours and 20,800 flight cycles or 68,300 flight hours, depending
on airplane utilization and configuration. The repetitive inspection
interval ranges between 14,000 flight cycles or 95,200 flight hours and
24,600 flight cycles or 98,700 flight hours, depending on airplane
configuration. 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-2016-9192.
[[Page 18548]]
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM from a
single commenter, and the FAA's response to that comment.
Request To Refer to Revised Service Information
Delta Airlines (DAL) requested that we revise paragraphs (g),
(g)(1), and (g)(2) of the proposed AD to refer to Airbus Service
Bulletin A330-53-3215, Revision 02, dated November 23, 2016. DAL also
asked that credit be given in paragraph (h)(1) of the proposed AD for
previously accomplished actions using Airbus Service Bulletin A330-53-
3215, Revision 01, dated April 17, 2014. DAL stated that if the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3215,
Revision 01, dated April 17, 2014, are used, operators may incorrectly
reference kit part numbers in their instructions and would then need to
submit a request for approval of an alternative method of compliance
for the replaced part.
We agree with the commenter's request to refer to Airbus Service
Bulletin A330-53-3215, Revision 02, dated November 23, 2016. Airbus
Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016,
has also been issued. No additional work is required by Airbus Service
Bulletins A330-53-3215, Revision 02; and A340-53-4215, Revision 02,
both dated November 23, 2016; the revised service information merely
corrects typographical errors and contains minor editorial changes.
We have revised the Related Service Information under 1 CFR part 51
section of this final rule and paragraphs (g), (g)(1), and (g)(2) of
this AD to refer to Airbus Service Bulletin A330-53-3215, Revision 02,
dated November 23, 2016; and Airbus Service Bulletin A340-53-4215,
Revision 02, dated November 23, 2016. We have also revised paragraph
(h)(1) of this AD to provide credit for actions accomplished prior to
the effective date of this AD using Airbus Service Bulletin A330-53-
3215, Revision 01, dated April 17, 2014; and Airbus Service Bulletin
A340-53-4215, Revision 01, dated April 17, 2014.
Conclusion
We reviewed the relevant data, considered the comment 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 Airbus Service Bulletin A330-53-3215, Revision 02,
dated November 23, 2016; and Airbus Service Bulletin A340-53-4215,
Revision 02, dated November 23, 2016. The service information describes
procedures for repetitive rototest inspections of certain fastener
holes, and related investigative and corrective actions if necessary.
These documents are distinct since they apply to different airplane
models. 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 41 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection........................... 41 work-hours x $85 per hour $0 $3,485 $142,885 per inspection cycle.
= $3,485 per inspection
cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
are required based on the results of the required inspection. We have
no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair.................................... 46 work-hours x $85 per hour = $4,186 $8,096
$3,910.
----------------------------------------------------------------------------------------------------------------
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:
[[Page 18549]]
1. Is not a ``significant regulatory action'' under Executive Order
12866;
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 adding the following new airworthiness
directive (AD):
2017-07-07 Airbus: Amendment 39-18845; Docket No. FAA-2016-9192;
Directorate Identifier 2016-NM-038-AD.
(a) Effective Date
This AD is effective May 25, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of this AD, having serial
numbers 0176 through 0915 inclusive.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of cracking at fastener holes
located at frame (FR) 40 on the lower shell panel junction. We are
issuing this AD to detect and correct cracking at FR40 on the lower
shell panel junction; such cracking could lead to reduced structural
integrity of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Related Investigative and Corrective
Actions
Within the compliance times defined in table 1 to the
introductory text of paragraph (g) of this AD, and, thereafter, at
intervals not to exceed the compliance times defined in Airbus
Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016;
or Airbus Service Bulletin A340-53-4215, Revision 02, dated November
23, 2016; as applicable, depending on airplane utilization and
configuration: Accomplish a special detailed inspection of fastener
holes located at FR40 lower shell panel junction on both left-hand
(LH) and right-side (RH) sides, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3215,
Revision 02, dated November 23, 2016; or Airbus Service Bulletin
A340-53-4215, Revision 02, dated November 23, 2016; as applicable.
Table 1 to the Introductory Text of Paragraph (g) of this AD--Compliance
Time for Initial Inspection
------------------------------------------------------------------------
Compliance time (whichever
occurs later, A or B)
------------------------------------------------------------------------
A...................................... Before exceeding the compliance
time ``threshold'' defined in
table 1 of Airbus Service
Bulletin A330-53-3215,
Revision 02, dated November
23, 2016; or Airbus Service
Bulletin A340-53-4215,
Revision 02, dated November
23, 2016; as applicable,
depending on airplane
utilization and configuration
and to be counted from
airplane first flight
B...................................... For Model A330 airplanes:
Within 2,400 flight cycles or
24 months, whichever occurs
first after the effective date
of this AD
For Model A340 airplanes:
Within 1,300 flight cycles or
24 months, whichever occurs
first after the effective date
of this AD
------------------------------------------------------------------------
(1) If, during any inspection required by the introductory text
of paragraph (g) of this AD, any crack is detected, before further
flight, accomplish all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-53-3215, Revision 02,
dated November 23, 2016; or Airbus Service Bulletin A340-53-4215,
Revision 02, dated November 23, 2016; as applicable, except where
Airbus Service Bulletin A330-53-3215, Revision 02, dated November
23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02,
dated November 23, 2016, specifies to contact Airbus for repair
instructions, and specifies that action as ``RC'' (Required for
Compliance), this AD requires repair before further flight using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(2) If, during any inspection required by the introductory text
of paragraph (g) of this AD, the hole diameter is not within
tolerance of the transition fit as nominal, or first oversize, or
second oversize, or next nominal, as applicable, and Airbus Service
Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or
Airbus Service Bulletin A340-53-4215, Revision 02, dated November
23, 2016, specifies to contact Airbus for repair instructions, and
specifies that action as ``RC'' (Required for Compliance), before
further flight, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
(3) Accomplishment of corrective actions, as required by
paragraph (g)(1) of this AD, does not constitute terminating action
for the repetitive inspections required by the introductory text of
paragraph (g) of this AD.
(4) Accomplishment of a repair on an airplane, as required by
paragraph (g)(2) of this AD, does not constitute terminating action
for the repetitive inspections required by the introductory text of
paragraph (g) of this AD for that airplane, unless the method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA indicates
otherwise.
(h) Credit for Previous Actions
(1) This paragraph provides credit for inspections required by
the introductory text of paragraph (g) of this AD and the related
investigative and corrective actions required by paragraph (g)(1) of
this AD, if those actions were performed before the effective date
of this AD using Airbus Service Bulletin A330-53-3215, dated June
21, 2013; or Revision 01, dated April 17, 2014; or Airbus Service
Bulletin A340-53-4215, dated June 21, 2013; or Revision 01, dated
April 17, 2014; as applicable.
(2) This paragraph provides credit for the inspections and
corrective actions required by paragraph (g) of this AD, if those
actions were performed before the effective date of this AD using
Airbus Technical Disposition (TD) Reference LR57D11023360, Issue B,
dated July 12, 2011.
(i) 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 ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
[[Page 18550]]
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: 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 the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (g)(1) and (g)(2) 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.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0136, dated June 13, 2014,
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-2016-9192.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(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 this AD specifies otherwise.
(i) Airbus Service Bulletin A330-53-3215, Revision 02, dated
November 23, 2016.
(ii) Airbus Service Bulletin A340-53-4215, Revision 02, dated
November 23, 2016.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 28, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-06712 Filed 4-19-17; 8:45 am]
BILLING CODE 4910-13-P
