Airworthiness Directives; Airbus Airplanes, 44241-44244 [2016-15928]
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Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0143; Directorate
Identifier 2012–NM–113–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for all Airbus Model A300 B4–603, B4–
620, B4–622, B4–605R, B4–622R, F4–
605R, F4–622R, and C4–605R variant F
airplanes. The NPRM proposed to
require repetitive detailed inspections of
the lower frame fittings, related
investigative actions, and corrective
actions if necessary. The NPRM was
prompted by reports of cracks in the
frame base fittings connecting the frame
lower positions to the center wing box.
This action revises the NPRM by
replacing the proposed requirements
with new repetitive detailed inspections
for cracking of the lower frame fittings
of the frame foot, and replacement with
a new frame foot if cracking is found.
This action also provides optional
terminating action for the repetitive
inspections. We are proposing this
supplemental NPRM (SNPRM) to detect
and correct cracking of the lower frame
fittings, which could result in reduced
structural integrity of the airplane. Since
these actions impose an additional
burden over those proposed in the
NPRM, we are reopening the comment
period to allow the public the chance to
comment on these proposed changes.
DATES: We must receive comments on
this SNPRM by August 22, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
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SUMMARY:
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Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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. 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.
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–2014–
0143; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–0143; Directorate Identifier
2012–NM–113–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
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44241
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A300 B4–603,
B4–620, B4–622, B4–605R, B4–622R,
F4–605R, F4–622R, and C4–605R
variant F airplanes. The NPRM
published in the Federal Register on
March 19, 2014 (79 FR 15266) (‘‘the
NPRM’’).
The NPRM was prompted by reports
of cracks in the frame base fittings
connecting the frame lower positions to
the center wing box. The NPRM
proposed to require repetitive detailed
inspections of the lower frame fittings,
related investigative actions, and
corrective actions if necessary.
Actions Since NPRM Was Issued
Since we issued the NPRM, we have
determined that repairs to address
cracking in the frame foot area found
during accomplishment of the detailed
inspection of the lower frame fittings
specified in Airbus Service Bulletin
A300–53–6111, Revision 05, including
Appendix 01, dated January 28, 2013,
are not adequate to prevent further
cracking. The European Aviation Safety
Agency, which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0217, dated October 30,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on all Airbus Model
A300 B4–603, B4–620, B4–622, B4–
605R, B4–622R, F4–605R, F4–622R, and
C4–605R variant F airplanes. The MCAI
states:
During accomplishment of Airbus Service
Bulletin (SB) A300–53–6111 (EASA AD
2012–0103), addressing detailed visual
inspections of the lower frame fittings
between Frame (FR) 41 and FR46, a crack
was detected on one A300–600 aeroplane in
the area 2 of the foot of FR46 at junction
radius level.
This frame, previously repaired due to a
crack finding in the frame foot area 1, was
not due to be inspected before reaching the
post-repair inspection threshold, i.e. 45,400
flight cycles since repair embodiment.
Further investigation determined that the
repairs specified in Airbus SB A300–53–6111
were of limited effect to prevent cracking in
the frame foot area 2.
This condition, if not detected and
corrected, could affect the structural integrity
of the fuselage of all aeroplanes operated up
to the extended service goal (ESG).
As a temporary action and until an
improvement of the existing repairs was
made available, EASA issued AD 2012–0229
[AD * * *] to require a one-time detailed
inspection (DET) of the frame feet that were
repaired in accordance with Airbus SB
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Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
A300–53–6111, and the reporting of findings
to Airbus.
Since that [EASA] AD was issued, a
detailed study was performed resulting in the
development of a new inspection
programme.
Consequently, Airbus cancelled SB A300–
53–6111 and replaced it with SB A300–53–
6177, introducing repetitive DET of the lower
frame fittings between FR41 and FR46 for the
entire fleet. In addition to this new
inspection programme, Airbus designed a
new frame foot which can be installed on
aeroplanes through Airbus SB A300–53–
6176.
For the reasons described above, this
[EASA] AD supersedes EASA AD 2012–0103,
not retaining its requirements, and instead
requires the new inspection programme for
the lower frame fittings. This [EASA] AD also
introduces an optional terminating action for
the repetitive inspections required by the
[EASA] AD.
Corrective actions include replacing
any cracked lower frame fittings with a
new frame foot. You may examine the
MCAI in the AD docket on the Internet
at https://www.regulations.gov by
searching for and locating FAA–2014–
0143.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A300–53–6177, dated May 20, 2015.
The service information describes
procedures for repetitive detailed
inspections for cracking of the lower
frame fittings between FR41 and FR46.
Airbus has also issued Service Bulletin
A300–53–6176, dated May 20, 2015.
The service information describes
procedures for replacing all lower frame
feet between frame FR41 and FR46 with
new, improved frame feet. 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.
for implementing the AFT method
would create uncertainty for operators
and inspectors trying to determine the
correct compliance time. UPS stated
that a defined threshold and repetitive
inspection interval would adequately
provide for timely detection of possible
damage.
We disagree with the commenter’s
request to revise the compliance times
in this proposed AD. The compliance
times in this proposed AD correspond
with those in the MCAI AD, which
refers to Airbus Service Bulletin A300–
53–6177, dated May 20, 2015. In Airbus
Service Bulletin A300–53–6177, dated
May 20, 2015, the inspection thresholds
and intervals are based on the
accumulation of both flight cycles and
flight hours, and are listed in tables
appropriately grouping airplanes with
average flight time utilization above 1.5
hours, and airplanes with average flight
time utilization at or below 1.5 hours.
We have determined these compliance
times acceptable for this proposed AD.
However, we do acknowledge that a
fixed compliance time for a fleet could
be easier for operators to schedule and
record compliance. Therefore, under the
provisions of paragraph (j)(1) of this
proposed AD, we will consider requests
for approval of an alternative method of
compliance (AMOC) if a proposal is
submitted that is supported by technical
data that includes fatigue and damage
tolerance analysis. We have not changed
this proposed AD in this regard.
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Comments
We gave the public the opportunity to
participate in developing this proposed
AD. We considered the comments
received.
Request To Remove Reporting
Requirement
FedEx objected to the reporting
requirement in the proposed AD (in the
NPRM).
We infer that FedEx wants the
reporting requirement removed. We
disagree that the reporting requirement
should be removed from this proposed
AD. We have determined that reporting
the inspection findings will enable the
manufacturer to obtain better insight
into the extent of the cracking. We have
made no change to this proposed AD in
this regard.
Request To Revise Method Used To
Determine Compliance Times
United Parcel Service (UPS) requested
that the compliance times in the
proposed AD (in the NPRM) be revised
to be less complex. UPS stated that the
proposed compliance times contain a
method known as ‘‘Average Flight
Time’’ (AFT) which results in a variable
flight hour limit and adds an
unnecessary complexity to the threshold
table and subsequent inspection actions.
UPS added that use of the AFT method,
along with a lack of standard procedures
Request To Remove Requirement To
Refer to This AD in Repair Approvals
UPS requested that we revise the
proposed AD (in the NPRM) to remove
the requirement to include the AD
reference in repair approvals. UPS noted
its concerns that the NPRM will
increase requests for approval of
alternative methods of compliance
(AMOCs) and result in delays to other
services and actions addressed by the
FAA on a daily basis.
We agree with the commenter’s
request to remove from this proposed
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AD the requirement that repair
approvals must specifically refer to this
AD. Since late 2006, we have included
a standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
authority’s AD. The MCAI or referenced
service information in an FAA AD often
directs the owner/operator to contact
the manufacturer for corrective actions,
such as a repair. Briefly, the Airworthy
Product paragraph allowed owners/
operators to use corrective actions
provided by the manufacturer if those
actions were FAA-approved. In
addition, the paragraph stated that any
actions approved by the State of Design
Authority (or its delegated agent) are
considered to be FAA-approved.
In the proposed AD (in the NPRM) we
proposed to prevent the use of repairs
that were not specifically developed to
correct the unsafe condition, by
requiring that the repair approval
provided by the State of Design
Authority or its delegated agent
specifically refer to this FAA AD. This
change was intended to clarify the
method of compliance and to provide
operators with better visibility of repairs
that are specifically developed and
approved to correct the unsafe
condition. In addition, we proposed to
change the phrase ‘‘its delegated agent’’
to include ‘‘the Design Approval Holder
(DAH) with a State of Design
Authority’s design organization
approval (DOA)’’ to refer to a DAH
authorized to approve required repairs
for the AD.
In its comments to the proposed AD
(in the NPRM), UPS stated the
following: ‘‘The proposed wording,
being specific to repairs, eliminates the
interpretation that Airbus messages or
other approved EASA documents are
acceptable for approving minor
deviations (corrective actions) needed
during accomplishment of a[n AD]
mandated Airbus service bulletin.’’
This comment has made the FAA
aware that some operators have
misunderstood or misinterpreted the
Airworthy Product paragraph to allow
the owner/operator to use messages
provided by the manufacturer as
approval of deviations during the
accomplishment of an AD-mandated
action. The Airworthy Product
paragraph does not approve messages or
other information provided by the
manufacturer for deviations to the
requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
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Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
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However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an AMOC to the AD-required actions
using the procedures found in 14 CFR
39.19.
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed
that paragraph and retitled it
‘‘Contacting the Manufacturer.’’ This
paragraph now clarifies that for any
requirement in this AD to obtain
corrective actions from a manufacturer,
the actions must be accomplished using
a method approved by the FAA, EASA,
or Airbus’s EASA DOA.
The ‘‘Contacting the Manufacturer’’
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility afforded previously by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the AD
Implementation Aviation Rulemaking
Committee to increase flexibility in
complying with ADs by identifying
those actions in manufacturers’ service
instructions that are ‘‘Required for
Compliance’’ with ADs. We continue to
work with manufacturers to implement
this recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an AMOC.
result, we have determined that it is
necessary to reopen the comment period
to provide additional opportunity for
the public to comment on this SNPRM.
FAA’s Determination and Requirements
of This SNPRM
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Certain changes described above
expand the scope of the NPRM. As a
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
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Costs of Compliance
We estimate that this SNPRM affects
123 airplanes of U.S. registry.
We estimate that it would take about
541 work-hours per product to comply
with the basic requirements of this
SNPRM, and 1 work-hour per product
for reporting. The average labor rate is
$85 per work-hour. Required parts
would cost about $0 per product. Based
on these figures, we estimate the cost of
this SNPRM on U.S. operators to be
$5,666,610, or $46,070 per product.
We estimate that the optional
terminating modification would take
about 529 work-hours and require parts
costing $131,500, for a cost of $176,465.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this proposed AD is 2120–
0056. The paperwork cost associated
with this proposed AD has been
detailed in the Costs of Compliance
section of this document and includes
time for reviewing instructions, as well
as completing and reviewing the
collection of information. Therefore, all
reporting associated with this proposed
AD is mandatory. Comments concerning
the accuracy of this burden and
suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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44243
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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2014–0143;
Directorate Identifier 2012–NM–113–AD.
(a) Comments Due Date
We must receive comments by August 22,
2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B4–
603, B4–620, B4–622, B4–605R, B4–622R,
F4–605R, F4–622R, and C4–605R variant F
airplanes; certificated in any category; all
serial numbers.
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(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks
in the frame base fittings connecting the
frame lower positions to the center wing box.
We are issuing this AD to detect and correct
cracking of the lower frame fittings, which
could result in reduced structural integrity of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Replacement
If Necessary
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Airbus
Service Bulletin A300–53–6177, dated May
20, 2015, except where Airbus Service
Bulletin A300–53–6177, dated May 20, 2015,
specifies a compliance time ‘‘from issuance
of Revision 04 of Service Bulletin A300–53–
6111,’’ this AD requires compliance within
the specified compliance time after the
effective date of this AD: Perform a detailed
inspection for cracking of the lower frame
fittings between frame (FR) 41 and FR46 of
the frame foot, and if any crack is found,
before further flight, replace with a new
frame foot, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–6177, dated May
20, 2015. Repeat the inspection thereafter at
the applicable intervals specified in
paragraph 1.E., ‘‘Compliance,’’ of Airbus
Service Bulletin A300–53–6177, dated May
20, 2015.
(h) Reporting
At the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD: Submit
a report of the findings (both positive and
negative) of each inspection required by
paragraph (g) of this AD. Send the report to
Airbus Service Bulletin Reporting Online
Application on Airbus World (https://
w3.airbus.com).
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
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(i) Optional Terminating Action
Replacement of all lower frame feet
between FR41 and FR46, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–53–6176, dated May
20, 2015, terminates the repetitive
inspections required by paragraph (g) of this
AD.
(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
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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:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–2125.
Information may be emailed to: 9-ANM-116AMOC-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. The AMOC approval letter
must specifically reference this AD.
(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 European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0217, dated
October 30, 2015, 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–2014–0143.
(2) 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.
You may view this referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
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information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on June 23,
2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–15928 Filed 7–6–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8161; Directorate
Identifier 2016–CE–018–AD]
RIN 2120–AA64
Airworthiness Directives; REIMS
AVIATION S.A. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
REIMS AVIATION S.A. Model F406
airplanes. This proposed AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as cracks found in the
horizontal stabilizer rear attach
structure and the vertical fin rear spar
attach structure. We are issuing this
proposed AD to require actions to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by August 22, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact ASI Aviation,
DATES:
E:\FR\FM\07JYP1.SGM
07JYP1
Agencies
[Federal Register Volume 81, Number 130 (Thursday, July 7, 2016)]
[Proposed Rules]
[Pages 44241-44244]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-15928]
[[Page 44241]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0143; Directorate Identifier 2012-NM-113-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for all Airbus Model A300 B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and C4-605R variant F airplanes. The NPRM
proposed to require repetitive detailed inspections of the lower frame
fittings, related investigative actions, and corrective actions if
necessary. The NPRM was prompted by reports of cracks in the frame base
fittings connecting the frame lower positions to the center wing box.
This action revises the NPRM by replacing the proposed requirements
with new repetitive detailed inspections for cracking of the lower
frame fittings of the frame foot, and replacement with a new frame foot
if cracking is found. This action also provides optional terminating
action for the repetitive inspections. We are proposing this
supplemental NPRM (SNPRM) to detect and correct cracking of the lower
frame fittings, which could result in reduced structural integrity of
the airplane. Since these actions impose an additional burden over
those proposed in the NPRM, we are reopening the comment period to
allow the public the chance to comment on these proposed changes.
DATES: We must receive comments on this SNPRM by August 22, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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. 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.
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-2014-
0143; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (telephone: 800-647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0143;
Directorate Identifier 2012-NM-113-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A300 B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R
variant F airplanes. The NPRM published in the Federal Register on
March 19, 2014 (79 FR 15266) (``the NPRM'').
The NPRM was prompted by reports of cracks in the frame base
fittings connecting the frame lower positions to the center wing box.
The NPRM proposed to require repetitive detailed inspections of the
lower frame fittings, related investigative actions, and corrective
actions if necessary.
Actions Since NPRM Was Issued
Since we issued the NPRM, we have determined that repairs to
address cracking in the frame foot area found during accomplishment of
the detailed inspection of the lower frame fittings specified in Airbus
Service Bulletin A300-53-6111, Revision 05, including Appendix 01,
dated January 28, 2013, are not adequate to prevent further cracking.
The European Aviation Safety Agency, which is the Technical Agent for
the Member States of the European Union, has issued EASA Airworthiness
Directive 2015-0217, dated October 30, 2015 (referred to after this as
the Mandatory Continuing Airworthiness Information, or ``the MCAI''),
to correct an unsafe condition on all Airbus Model A300 B4-603, B4-620,
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F
airplanes. The MCAI states:
During accomplishment of Airbus Service Bulletin (SB) A300-53-
6111 (EASA AD 2012-0103), addressing detailed visual inspections of
the lower frame fittings between Frame (FR) 41 and FR46, a crack was
detected on one A300-600 aeroplane in the area 2 of the foot of FR46
at junction radius level.
This frame, previously repaired due to a crack finding in the
frame foot area 1, was not due to be inspected before reaching the
post-repair inspection threshold, i.e. 45,400 flight cycles since
repair embodiment.
Further investigation determined that the repairs specified in
Airbus SB A300-53-6111 were of limited effect to prevent cracking in
the frame foot area 2.
This condition, if not detected and corrected, could affect the
structural integrity of the fuselage of all aeroplanes operated up
to the extended service goal (ESG).
As a temporary action and until an improvement of the existing
repairs was made available, EASA issued AD 2012-0229 [AD * * *] to
require a one-time detailed inspection (DET) of the frame feet that
were repaired in accordance with Airbus SB
[[Page 44242]]
A300-53-6111, and the reporting of findings to Airbus.
Since that [EASA] AD was issued, a detailed study was performed
resulting in the development of a new inspection programme.
Consequently, Airbus cancelled SB A300-53-6111 and replaced it
with SB A300-53-6177, introducing repetitive DET of the lower frame
fittings between FR41 and FR46 for the entire fleet. In addition to
this new inspection programme, Airbus designed a new frame foot
which can be installed on aeroplanes through Airbus SB A300-53-6176.
For the reasons described above, this [EASA] AD supersedes EASA
AD 2012-0103, not retaining its requirements, and instead requires
the new inspection programme for the lower frame fittings. This
[EASA] AD also introduces an optional terminating action for the
repetitive inspections required by the [EASA] AD.
Corrective actions include replacing any cracked lower frame
fittings with a new frame foot. You may examine the MCAI in the AD
docket on the Internet at https://www.regulations.gov by searching for
and locating FAA-2014-0143.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A300-53-6177, dated May 20,
2015. The service information describes procedures for repetitive
detailed inspections for cracking of the lower frame fittings between
FR41 and FR46. Airbus has also issued Service Bulletin A300-53-6176,
dated May 20, 2015. The service information describes procedures for
replacing all lower frame feet between frame FR41 and FR46 with new,
improved frame feet. 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.
Comments
We gave the public the opportunity to participate in developing
this proposed AD. We considered the comments received.
Request To Revise Method Used To Determine Compliance Times
United Parcel Service (UPS) requested that the compliance times in
the proposed AD (in the NPRM) be revised to be less complex. UPS stated
that the proposed compliance times contain a method known as ``Average
Flight Time'' (AFT) which results in a variable flight hour limit and
adds an unnecessary complexity to the threshold table and subsequent
inspection actions. UPS added that use of the AFT method, along with a
lack of standard procedures for implementing the AFT method would
create uncertainty for operators and inspectors trying to determine the
correct compliance time. UPS stated that a defined threshold and
repetitive inspection interval would adequately provide for timely
detection of possible damage.
We disagree with the commenter's request to revise the compliance
times in this proposed AD. The compliance times in this proposed AD
correspond with those in the MCAI AD, which refers to Airbus Service
Bulletin A300-53-6177, dated May 20, 2015. In Airbus Service Bulletin
A300-53-6177, dated May 20, 2015, the inspection thresholds and
intervals are based on the accumulation of both flight cycles and
flight hours, and are listed in tables appropriately grouping airplanes
with average flight time utilization above 1.5 hours, and airplanes
with average flight time utilization at or below 1.5 hours. We have
determined these compliance times acceptable for this proposed AD.
However, we do acknowledge that a fixed compliance time for a fleet
could be easier for operators to schedule and record compliance.
Therefore, under the provisions of paragraph (j)(1) of this proposed
AD, we will consider requests for approval of an alternative method of
compliance (AMOC) if a proposal is submitted that is supported by
technical data that includes fatigue and damage tolerance analysis. We
have not changed this proposed AD in this regard.
Request To Remove Reporting Requirement
FedEx objected to the reporting requirement in the proposed AD (in
the NPRM).
We infer that FedEx wants the reporting requirement removed. We
disagree that the reporting requirement should be removed from this
proposed AD. We have determined that reporting the inspection findings
will enable the manufacturer to obtain better insight into the extent
of the cracking. We have made no change to this proposed AD in this
regard.
Request To Remove Requirement To Refer to This AD in Repair Approvals
UPS requested that we revise the proposed AD (in the NPRM) to
remove the requirement to include the AD reference in repair approvals.
UPS noted its concerns that the NPRM will increase requests for
approval of alternative methods of compliance (AMOCs) and result in
delays to other services and actions addressed by the FAA on a daily
basis.
We agree with the commenter's request to remove from this proposed
AD the requirement that repair approvals must specifically refer to
this AD. Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD. The MCAI or referenced service
information in an FAA AD often directs the owner/operator to contact
the manufacturer for corrective actions, such as a repair. Briefly, the
Airworthy Product paragraph allowed owners/operators to use corrective
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved
by the State of Design Authority (or its delegated agent) are
considered to be FAA-approved.
In the proposed AD (in the NPRM) we proposed to prevent the use of
repairs that were not specifically developed to correct the unsafe
condition, by requiring that the repair approval provided by the State
of Design Authority or its delegated agent specifically refer to this
FAA AD. This change was intended to clarify the method of compliance
and to provide operators with better visibility of repairs that are
specifically developed and approved to correct the unsafe condition. In
addition, we proposed to change the phrase ``its delegated agent'' to
include ``the Design Approval Holder (DAH) with a State of Design
Authority's design organization approval (DOA)'' to refer to a DAH
authorized to approve required repairs for the AD.
In its comments to the proposed AD (in the NPRM), UPS stated the
following: ``The proposed wording, being specific to repairs,
eliminates the interpretation that Airbus messages or other approved
EASA documents are acceptable for approving minor deviations
(corrective actions) needed during accomplishment of a[n AD] mandated
Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements.
[[Page 44243]]
However, deviations to AD-required actions are addressed in 14 CFR
39.17, and anyone may request the approval for an AMOC to the AD-
required actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed that paragraph and
retitled it ``Contacting the Manufacturer.'' This paragraph now
clarifies that for any requirement in this AD to obtain corrective
actions from a manufacturer, the actions must be accomplished using a
method approved by the FAA, EASA, or Airbus's EASA DOA.
The ``Contacting the Manufacturer'' paragraph also clarifies that,
if approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility afforded previously
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the AD Implementation
Aviation Rulemaking Committee to increase flexibility in complying with
ADs by identifying those actions in manufacturers' service instructions
that are ``Required for Compliance'' with ADs. We continue to work with
manufacturers to implement this recommendation. But once we determine
that an action is required, any deviation from the requirement must be
approved as an AMOC.
FAA's Determination and Requirements of This SNPRM
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Certain changes described above expand the scope of the NPRM. As a
result, we have determined that it is necessary to reopen the comment
period to provide additional opportunity for the public to comment on
this SNPRM.
Costs of Compliance
We estimate that this SNPRM affects 123 airplanes of U.S. registry.
We estimate that it would take about 541 work-hours per product to
comply with the basic requirements of this SNPRM, and 1 work-hour per
product for reporting. The average labor rate is $85 per work-hour.
Required parts would cost about $0 per product. Based on these figures,
we estimate the cost of this SNPRM on U.S. operators to be $5,666,610,
or $46,070 per product.
We estimate that the optional terminating modification would take
about 529 work-hours and require parts costing $131,500, for a cost of
$176,465.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed AD is mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden should
be directed to the FAA at 800 Independence Ave. SW., Washington, DC
20591, ATTN: Information Collection Clearance Officer, AES-200.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
Airbus: Docket No. FAA-2014-0143; Directorate Identifier 2012-NM-
113-AD.
(a) Comments Due Date
We must receive comments by August 22, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F airplanes;
certificated in any category; all serial numbers.
[[Page 44244]]
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks in the frame base
fittings connecting the frame lower positions to the center wing
box. We are issuing this AD to detect and correct cracking of the
lower frame fittings, which could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Replacement If Necessary
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May
20, 2015, except where Airbus Service Bulletin A300-53-6177, dated
May 20, 2015, specifies a compliance time ``from issuance of
Revision 04 of Service Bulletin A300-53-6111,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD: Perform a detailed inspection for cracking of the
lower frame fittings between frame (FR) 41 and FR46 of the frame
foot, and if any crack is found, before further flight, replace with
a new frame foot, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-53-6177, dated May 20, 2015. Repeat
the inspection thereafter at the applicable intervals specified in
paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-53-
6177, dated May 20, 2015.
(h) Reporting
At the applicable time specified in paragraph (h)(1) or (h)(2)
of this AD: Submit a report of the findings (both positive and
negative) of each inspection required by paragraph (g) of this AD.
Send the report to Airbus Service Bulletin Reporting Online
Application on Airbus World (https://w3.airbus.com).
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(i) Optional Terminating Action
Replacement of all lower frame feet between FR41 and FR46, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-6176, dated May 20, 2015, terminates the repetitive
inspections required by paragraph (g) of this AD.
(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 ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-2125. 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. The
AMOC approval letter must specifically reference this AD.
(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
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0217, dated October 30,
2015, 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-2014-0143.
(2) 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. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. 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.
Issued in Renton, Washington, on June 23, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-15928 Filed 7-6-16; 8:45 am]
BILLING CODE 4910-13-P