[Federal Register Volume 79, Number 48 (Wednesday, March 12, 2014)]
[Proposed Rules]
[Pages 13944-13948]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-05436]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0138; Directorate Identifier 2013-NM-020-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede airworthiness directive (AD) 95-24-04,
that applies to all Airbus Model A300 series airplanes; Model A300 B4-
600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R
Variant F airplanes (collectively called Model A300-600 series
airplanes). AD 95-24-04 requires repetitive inspections to detect
cracks at the aft spar web of the wings, and repair if necessary. Since
we issued AD 95-24-04, we have determined that the inspection threshold
and interval must be reduced to allow timely detection of cracks and
accomplishment of applicable repairs, because of cracking in the rear
spar web of the wings between certain ribs due to fatigue-related high
shear stress. This proposed AD would reduce the inspection compliance
time and interval, and would expand the applicability to airplanes on
which a certain Airbus modification has been embodied in production and
to airplanes on which a certain Airbus service bulletin has been
embodied in service. We are proposing this AD to detect and correct
fatigue-related cracking, which could result in reduced structural
integrity of the wing.
DATES: We must receive comments on this proposed AD by April 28, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://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 [email protected]; Internet http://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 http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the MCAI, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations 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-2014-0138;
Directorate Identifier 2013-NM-020-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 http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each
[[Page 13945]]
substantive verbal contact we receive about this proposed AD.
Discussion
On November 9, 1995, we issued AD 95-24-04, Amendment 39-9436 (60
FR 58213, November 27, 1995). AD 95-24-04 required actions intended to
address an unsafe condition on all Airbus Model A300 series airplanes;
Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model
A300 C4-605R Variant F airplanes (collectively called Model A300-600
series airplanes).
Since we issued AD 95-24-04, Amendment 39-9436 (60 FR 58213,
November 27, 1995), the European Aviation Safety Agency (EASA), which
is the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2013-0013R1, dated February 20,
2013 (referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Wing fatigue tests carried out by Airbus revealed cracks on the
vertical web of the rear spar between Ribs 1 and 2. Similar cracks
in the same area were reportedly found by A300 aeroplane operators.
In all cases, the cracks ran from the tip of the build slot to the
nearest adjacent bolt hole.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this unsafe condition, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an
AD] to require an eddy current inspection of the aft face of the
wing rear spar in the area adjacent to the build slot on Left Hand
(LH) and Right Hand (RH) wings.
Since that [French] AD was issued, a fleet survey and updated
fatigue and damage tolerance analysis were performed in order to
substantiate the second A300-600 Extended Service Goal (ESG2)
exercise. The results of the survey and analysis showed that the
inspection threshold and interval must be reduced to allow timely
detection of cracks and accomplishment of an applicable corrective
action.
Prompted by these findings, Airbus issued Airbus Service
Bulletin (SB) A300-57-6059 Revision 04.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD 1997-375-239(B)R3, which is
superseded, but redefines the thresholds and intervals. This [EASA]
AD also expands the applicability to aeroplanes on which Airbus
modification (mod) 12102 has been embodied in production and to
aeroplanes on which Airbus SB A300-57-6063 (Airbus mod 11130) has
been embodied in service.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No.
FAA-2014-0138.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A300-57-6059, Revision
04, dated February 22, 2011. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
For pre-Airbus Modification 11130 (Airbus Service Bulletin A300-57-
6063) airplanes, the compliance times are dependent on airplane
configuration and utilization. The initial inspection thresholds
described in Airbus Mandatory Service Bulletin A300-57-6059, Revision
04, dated February 22, 2011, range between 18,000 and 23,300 total
flight cycles, and between 29,100 and 46,600 total flight hours. The
``grace period'' specified in Airbus Mandatory Service Bulletin A300-
57-6059, Revision 04, dated February 22, 2011, is either 1,000 flight
cycles, or 1,600 flight hours, or 2,100 flight hours. The repetitive
inspection interval ranges between 4,800 and 6,100 flight cycles, and
between 7,700 and 12,300 flight hours.
For post-Airbus Modification 11130 (Airbus Service Bulletin A300-
57-6063) airplanes or post-Airbus production Modification 12102
airplanes, the compliance times are dependent on airplane configuration
and utilization. The initial inspection thresholds described in Airbus
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February
22, 2011, range between 29,900 and 38,700 total flight cycles, and
between 48,400 and 77,500 total flight hours. The ``grace period''
specified in Airbus Mandatory Service Bulletin A300-57-6059, Revision
04, dated February 22, 2011, is either 800 or 1,000 flight cycles, or
1,200 or 1,700 flight hours. The repetitive inspection interval ranges
between 5,100 and 6,500 flight cycles, or between 8,200 and 13,100
flight hours.
FAA's Determination and Requirements of This Proposed AD
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 the same
type design.
Repair Approvals
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, certain requirements of this proposed
AD specify that the repair approval specifically refer to the FAA AD.
This change is 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 use the phrase ``its delegated agent, or the DAH with
State of Design Authority design organization approval, as applicable''
in this proposed AD to refer to a DAH authorized to approve certain
required repairs for this proposed AD.
Differences Between This AD and the MCAI or Service Information
Although the MCAI or service information allows further flight
after cracks are found during compliance with the required action,
paragraphs (k) and (n) of this proposed AD would require that you
repair any cracking before further flight.
Costs of Compliance
We estimate that this proposed AD affects 71 products of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 13946]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection [actions retained from 3 work-hour x $85 $0 $255 per inspection $18,105 per
AD 95-24-04, Amendment 39-9436 per hour = $255 per cycle. inspection cycle.
(60 FR 58213, November 27, inspection cycle.
1995)].
Inspection [new proposed action]. 3 work-hour x $85 0 $255 per inspection $18,105 per
per hour = $255 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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 removing airworthiness directive (AD)
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), and
adding the following new AD:
Airbus: Docket No. FAA-2014-0138; Directorate Identifier 2013-NM-
020-AD.
(a) Comments Due Date
We must receive comments by April 28, 2014.
(b) Affected ADs
This AD supersedes AD 95-24-04, Amendment 39-9436 (60 FR 58213,
November 27, 1995).
(c) Applicability
This AD applies to the Airbus airplanes specified in paragraphs
(c)(1) through (c)(5) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes
(3) Airbus Model A300 B4-605R and B4-622R airplanes.
(4) Airbus Model A300 F4-605R airplanes.
(5) Airbus Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a determination that the inspection
compliance time and interval must be reduced to allow timely
detection of cracks and accomplishment of applicable repairs if
necessary because of cracking in the rear spar web of the wings
between certain ribs due to fatigue-related high shear stress. We
are issuing this AD to detect and correct fatigue-related cracking,
which could result in reduced structural integrity of the wing.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Inspection of Model A300 B2 Series Airplanes
This paragraph restates the requirements of paragraph (a) of AD
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with
no changes. For Model A300 B2 series airplanes: Prior to the
accumulation of 18,000 total flight cycles, or within 1,400 flight
cycles after December 27, 1995 (the effective date of AD 95-24-04),
whichever occurs later, perform a high frequency eddy current (HFEC)
inspection to detect cracks at the aft spar web of the wings, in
accordance with Airbus Service Bulletin A300-57-0213, dated August
12, 1994. Repeat the inspection thereafter at intervals not to
exceed 5,000 flight cycles.
(h) Retained Inspection of Model A300 B4-103, and B4-2C Series
Airplanes
This paragraph restates the requirements of paragraph (b) of AD
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with
no changes. For Model A300 B4-103, and B4-2C series airplanes: Prior
to the accumulation of 19,000 total flight cycles, or within 1,400
flight cycles after December 27, 1995 (the effective date of AD 95-
24-04), whichever occurs later, perform an HFEC inspection to detect
cracks at the aft spar web of the wings, in accordance with Airbus
Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the
inspection thereafter at intervals not to exceed 6,000 flight
cycles.
(i) Retained Inspection of Model A300 B4-200 Series Airplanes
This paragraph restates the requirements of paragraph (c) of AD
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with
no changes. For Model A300 B4-200 series airplanes: Prior to the
accumulation of 17,000 total flight cycles, or within 1,400 flight
cycles after December 27, 1995 (the effective date of AD 95-24-04),
whichever occurs later, perform an HFEC inspection to detect cracks
at the aft spar web of the wings,
[[Page 13947]]
in accordance with Airbus Service Bulletin A300-57-0213, dated
August 12, 1994. Repeat the inspection thereafter at intervals not
to exceed 5,000 flight cycles.
(j) Retained Inspection of Model A300-600 B4-601, B4-603, B4-620, B4-
622, B4-605R, B4-622R, and F4-605R Series Airplanes
This paragraph restates the requirements of paragraph (d) of AD
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with
no changes. For Model A300-600 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R series airplanes: Prior to the
accumulation of 21,600 flight cycles, perform an HFEC inspection to
detect cracks at the aft spar web of the wings, in accordance with
Airbus Service Bulletin A300-57-6059, dated August 12, 1994. Repeat
the inspection thereafter at intervals not to exceed 5,700 flight
cycles. Accomplishment of the initial inspection required by
paragraph (l) of this AD terminates the requirements of this
paragraph.
(k) Retained Repairs
This paragraph restates the requirements of paragraph (e) of AD
95-24-04, Amendment 39-9436 (60 FR 58213, November 27, 1995), with
new actions.
(1) Before the effective date of this AD, if any crack is
detected during any inspection required by paragraphs (g) though (j)
of this AD: Prior to further flight, repair the crack, in accordance
with Airbus Service Bulletin A300-57-0213, dated August 12, 1994; or
Airbus Service Bulletin A300-57-6059, dated August 12, 1994; as
applicable; or in accordance with a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA.
(2) As of the effective date of this AD, if any crack is
detected during any inspection required by paragraphs (g) though (j)
of this AD: Before further flight, repair the crack, in accordance
with Airbus Service Bulletin A300-57-0213, dated August 12, 1994
(for Model A300 B2 series airplanes, and Model A300 B4-103 and B4-2C
series airplanes); or Airbus Mandatory Service Bulletin A300-57-
6059, Revision 04, dated February 22, 2011 (for Model A300-600 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R series
airplanes); except if Airbus Service Bulletin A300-57-0213, dated
August 12, 1994; or Airbus Mandatory Service Bulletin A300-57-6059,
Revision 04, dated February 22, 2011; specifies to contact Airbus
for an approved repair, before further flight, repair the crack
using a method approved by either the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its delegated agent, or the Design
Approval Holder with the EASA design organization approval, as
applicable). For a repair method to be approved, the repair approval
must specifically refer to this AD.
(l) New Repetitive Inspections
For airplanes identified in paragraphs (c)(2) through (c)(5) of
this AD: At the later of the compliance times specified in paragraph
(l)(1) and (l)(2) of this AD, perform an HFEC inspection to detect
cracks of the aft face of the wing rear spar web in the area
adjacent to the build slot, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A300-57-6059,
Revision 04, dated February 22, 2011. Repeat the inspection
thereafter at the applicable compliance time specified in Airbus
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February
22, 2011, except as specified in paragraph (m) of this AD.
Accomplishment of the initial inspection required by this paragraph
terminates the requirements of paragraph (j) of this AD.
(1) At the earlier of the applicable compliance times specified
in the ``Threshold Inspection'' column in table 1 through table 4 of
paragraph 1.E., ``Compliance,'' of Airbus Mandatory Service Bulletin
A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February
22, 2011, specifies ``(FH)'' and ``(FC)'' in the ``Threshold
Inspection'' columns, this AD specifies ``total flight hours'' and
``total flight cycles.''
(2) At the earlier of the applicable compliance times specified
in the ``Grace Period'' column in table 1 through table 4 of
paragraph 1.E., ``Compliance,'' of Airbus Mandatory Service Bulletin
A300-57-6059, Revision 04, dated February 22, 2011. Where Airbus
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February
22, 2011, specifies ``(FH)'' and ``(FC)'' in the ``Grace Period''
columns, this AD specifies ``flight hours'' and ``flight cycles.''
Where Airbus Mandatory Service Bulletin A300-57-6059, Revision 04,
dated February 22, 2011, specifies a grace period, this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(m) Compliance Time Exceptions
The repetitive inspection required by paragraph (l) of this AD
is to be accomplished at the earlier of the applicable compliance
time specified in column ``Repeat Interval'' of table 1 through
table 4 of Airbus Mandatory Service Bulletin A300-57-6059, Revision
04, dated February 22, 2011. Where Airbus Mandatory Service Bulletin
A300-57-6059, Revision 04, dated February 22, 2011, specifies
``(FC)'' and ``(FH)'' in the ``Repeat Interval'' columns, this AD
specifies ``flight hours'' and ``flight cycles.''
(n) New Repair
If any crack is detected during any inspection required by
paragraph (l) of this AD: Before further flight, repair the crack,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57-6059, Revision 04, dated February
22, 2011. Where Airbus Mandatory Service Bulletin A300-57-6059,
Revision 04, dated February 22, 2011, specifies to contact Airbus
for an approved repair: Before further flight, repair the crack
using a method approved by either the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its delegated agent, or the Design
Approval Holder with the EASA design organization approval, as
applicable). For a repair method to be approved, the repair approval
must specifically refer to this AD. Repair of any cracking as
required by this paragraph does not terminate the repetitive
inspections required by paragraph (l) of this AD.
(o) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (j) and (k) of this AD, if those actions were performed
before the effective date of this AD using Airbus Service Bulletin
A300-57-6059, dated August 12, 1994.
(2) This paragraph provides credit for the actions required by
paragraphs (j), (k), (l), and (n) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A300-57-6059, Revision 03, dated October 25, 1999, which is
not incorporated by reference in this AD.
(p) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, 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) 227-2125; fax (425) 227-1149.
Information may be emailed to: [email protected].
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) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the Design Approval Holder with a State of
Design Authority's design organization approval, as applicable). You
are required to ensure the product is airworthy before it is
returned to service.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Airworthiness Directive 2013-0013R1, dated February 20, 2013,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating it in Docket No. FAA-2014-0138.
(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 [email protected];
Internet http://www.airbus.com. You may view this referenced service
[[Page 13948]]
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 February 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-05436 Filed 3-11-14; 8:45 am]
BILLING CODE 4910-13-P