[Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)]
[Rules and Regulations]
[Pages 27246-27250]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-10688]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1273; Directorate Identifier 2010-NM-089-AD;
Amendment 39-16686; AD 2011-10-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-203, -204, -222, -
304, -322, and -324 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This 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:
A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme [for cracking] * *
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail
cone. We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective June 15, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 15,
2011.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on January 3, 2011 (76
FR 46). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme specified in the
Airbus Service Bulletin (SB) A310-53-2074. EASA issued AD 2007-0053
[which superseded French AD 1992-106-132 R6; French AD 1992-106-132
corresponds to FAA AD 98-26-01] to require the accomplishment of
this SB at Revision 03.
Airbus has established that this SB needed to be revised in
order to state correct threshold and intervals due to errors
introduced at revision 03. Consequently, revision 04 of this SB has
been issued, and opportunity was taken:
--To clarify the inspection area and associated threshold and
intervals
--To take aeroplane utilisation into consideration, in accordance
with the A310 life extension programme.
For the reasons stated above, this EASA AD takes over the
requirements of paragraph 1.16 of EASA AD 2007-0053R1 [currently at
R3], which has been revised accordingly, and requires accomplishment
of the instructions contained in Airbus SB A310-53-2074 at Revision
04.
The unsafe condition is reduced structural integrity of the tail cone.
The required actions include repetitive and one-time inspections,
depending on the area, of the lower tail plane cut-out, and corrective
actions if necessary. The inspections include the following:
[[Page 27247]]
Detailed inspections in areas 1, 2, and 3 for cracking and
corrosion of the lower horizontal stabilizer cutout longeron, the
corner fitting, the skin strap, and the skin.
Detailed inspections in areas 1, 2, and 3 for damaged
sealant.
Eddy current inspections in area 1 for cracking.
Eddy current inspections in area 2 for cracking.
Rotating probe inspection for cracking of specified
fastener holes in Area 3.
The corrective actions, depending on the conditions found, include
the following:
Repairing corrosion.
Contacting Airbus for repair instructions.
Replacing damaged sealant.
Removing cracking.
Doing an eddy current inspection for cracking of the
reworked area.
Installing a new corner fitting.
Doing a rotating probe inspection for cracking of fastener
holes.
Doing an eddy current inspection of the longeron and outer
skin.
Drilling or reaming fastener holes.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 44 products of U.S. registry.
We also estimate that it will take about 36 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $134,640, or $3,060 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify this AD:
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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
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 the NPRM, 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.
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 AD:
2011-10-05 Airbus: Amendment 39-16686. Docket No. FAA-2010-1273;
Directorate Identifier 2010-NM-089-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 15,
2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model A310-203, -204, -222, -304, -322,
and -324 airplanes, certificated in any category, all serial
numbers, except airplanes on which Airbus modification 06146 has
been done in production.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme [for cracking] * *
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail
cone.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Initial Inspections of the Lower Tail Plane Cut-out Area and Corrective
Actions
(g) Within the applicable time specified in Table 1 of this AD,
do the inspections of the lower tail plane cut-out area in the tail
cone specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5),
and (g)(6) of this AD, as applicable, in accordance with the
Accomplishment Instructions of Airbus
[[Page 27248]]
Mandatory Service Bulletin A310-53-2074, Revision 04, dated October
24, 2008. Certain compliance times are applicable to short-range use
(i.e., average flight time (AFT) equal to or less than 4 flight
hours), or long-range use (i.e., AFT exceeding 4 flight hours).
Inspection areas are specified in Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
Note 1: To establish the average flight time, take the
accumulated flight time (counted from the take-off up to the
landing) and divide by the number of accumulated flight cycles. This
gives the average flight time per flight cycle.
Table 1--Initial Compliance Time
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Airplanes Inspection areas........ Compliance time (whichever occurs later)
----------------------------------------------------------------------------------------------------------------
Model A310-203, A310-204, and A310- 1 and 2................. Prior to the Within 1,500 flight
222 airplanes. accumulation of 18,000 cycles or 3,000 flight
total flight cycles or hours, whichever
36,000 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-203, A310-204, and A310- 3....................... Prior to the Within 1,500 flight
222 airplanes. accumulation of 24,000 cycles or 3,000 flight
total flight cycles or hours, whichever
48,000 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-304, A310-322, and A310- 1 and 2................. Prior to the Within 1,200 flight
324 short range airplanes. accumulation of 12,000 cycles or 3,300 flight
total flight cycles or hours, whichever
33,750 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-304, A310-322, and A310- 3....................... Prior to the Within 1,200 flight
324 short range airplanes. accumulation of 18,000 cycles or 3,300 flight
total flight cycles or hours, whichever
50,500 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-304, A310-322, and A310- 1 and 2................. Prior to the Within 750 flight
324 long range airplanes. accumulation of 7,500 cycles or 3,750 flight
total flight cycles or hours, whichever
37,500 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-304, A310-322, and A310- 3....................... Prior to the Within 750 flight
324 long range airplanes. accumulation of 11,250 cycles or 3,750 flight
total flight cycles or hours, whichever
56,000 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
----------------------------------------------------------------------------------------------------------------
(1) For areas 1, 2, and 3: Do a detailed inspection for cracking
and corrosion of the lower horizontal stabilizer cutout longeron,
the corner fitting, the skin strap, and the skin, in accordance with
the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If any corrosion is found, before further flight, repair in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(ii) If any cracking is found, before further flight, contact
Airbus for repair instructions and do the repair.
(2) For areas 1, 2, and 3 on which cracking is not found during
the inspection required by paragraph (g)(1) of this AD: Do a
detailed inspection for damaged sealant; and, if any damaged sealant
is found, before further flight, replace the sealant; in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(3) For area 1: Do an eddy current inspection for cracking in
area 1; and, if no cracking is found, before further flight, apply
sealant and corrosion compound, as applicable; in accordance with
the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If cracking is equal to or less than 2.0 mm (0.079 inch)
long and not more than 2 cracks with a minimum distance of 50.0 mm
(1.969 inch) between the cracks: Before further flight, remove any
cracking and do an eddy current inspection for cracking of the
reworked area, in accordance with the Accomplishment Instructions of
the Airbus Mandatory Service Bulletin A310-53-2074, Revision 04,
dated October 24, 2008. If no cracking is found, before further
flight, shot peen the reworked area, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(A) If cracking is found and the radius of the rework is less
than 20.0 mm (0.787 inch), before further flight, increase the
radius and do an eddy current inspection for cracking of the
reworked area, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated
October 24, 2008. If no cracking is found, before further flight,
shot peen the reworked area, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(1) If any cracking is found in the outer skin, before further
flight, contact Airbus for repair instructions and do the repair.
(2) If any cracking is found in the corner fitting and area 3
has not been cold expanded, before further flight, install new
corner fitting, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04,
dated October 24, 2008, and do the rotating probe inspection in area
3 specified in paragraph (g)(5) of this AD.
(3) If any cracking is found in the corner fitting and area 3
has been cold expanded, before further flight, do the eddy current
inspection of the longeron and outer skin specified in paragraph
(g)(6) of this AD.
(B) If cracking is found and the radius of the rework is 20.0 mm
(0.787 inch) or more, before further flight, repair in accordance
with a method approved by either the Manager, International Branch,
ANM-116, FAA, Transport Airplane Directorate, or the European
Aviation Safety Agency (EASA) (or its delegated agent)
(ii) If cracking is greater than 2.0 mm (0.079 inch) long or
there are more than 2 cracks; or if there are more than 2 cracks
with less than a minimum distance of 50.0 mm (1.969 inch) between
the cracks: Before further flight, remove the corner fitting, and do
the applicable actions specified in paragraph (g)(3)(ii)(A) or
(g)(3)(ii)(B) of this AD.
(A) If any cracking is found and area 3 has not been cold
expanded, before further flight, install a new corner fitting, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008;
and do the rotating probe inspection in area 3 specified in
paragraph (g)(5) of this AD.
(B) If any cracking is found and area 3 has been cold expanded,
before further flight, do the eddy current inspection of the
longeron and outer skin specified in paragraph (g)(6) of this AD.
(4) For area 2: Do an eddy current inspection for cracking of
area 2, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310-53-2074, Revision 04, dated October
24, 2008. If any cracking is found, before further flight, contact
Airbus for repair instructions and do the repair.
(5) For area 3: Do a rotating probe inspection for cracking of
specified fastener holes in area 3, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If no cracking is found, before further flight, drill or
ream fastener holes, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008; except where this
service bulletin specifies to contact Airbus if the fastener
diameter does not meet specifications or if the distance
[[Page 27249]]
between the hole center and material edge is less than
specifications, before further flight, contact Airbus for repair
instructions and do the repair.
(ii) If cracking is found, before further flight, drill or ream
fastener holes, and do a rotating probe inspection for cracking of
the fastener holes in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(A) If no cracking is found, cold expand the fastener holes and
countersinks, drill or ream fastener holes, and wet install with
sealant, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated
October 24, 2008; except where this service bulletin specifies to
contact Airbus if the fastener diameter does not meet specifications
or if the distance between the hole center and material edge is less
than the specifications, before further flight, contact Airbus for
repair instructions and do the repair.
(B) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.
(6) For airplanes on which cracking is found in the corner
fitting during any inspection required by paragraph (g)(3) of this
AD and area 3 is cold-expanded: Do an eddy current inspection for
cracking of the longeron and outer skin, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If no cracking is found, before further flight, install a
new corner fitting and do a rotating probe inspection for cracking
of the fastener holes, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(A) If no cracking is found, before further flight, drill or
ream fastener holes, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(B) If cracking is found and the hole diameter is less than the
maximum oversize specification, before further flight, drill or ream
holes and do a rotating probe inspection for cracking of the
fastener holes, in accordance with Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(1) If no cracking is found, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(2) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.
(C) If cracking is found and the hole diameter is equal to or
greater than the maximum oversize specification, before further
flight, contact Airbus for repair instructions and do the repair.
(ii) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.
Repetitive Inspections of the Lower Tail Plane Cut-Out Area
(h) Repeat the inspections for area 1 required by paragraphs
(g)(1) and (g)(3) of this AD thereafter at the applicable intervals
specified in Table 2 of this AD. Certain compliance times are
applicable to short-range use (AFT equal to or less than 4 flight
hours), or long-range use (AFT exceeding 4 flight hours). Inspection
areas are specified in Airbus Mandatory Service Bulletin A310-53-
2074, Revision 04, dated October 24, 2008.
Table 2--Repetitive Interval for Areas 1 and 2
------------------------------------------------------------------------
Affected airplanes Interval (not to exceed)
------------------------------------------------------------------------
(1) Model A310-203, A310-204, and A310- 6,000 flight cycles or 12,000
222 airplanes that have accumulated flight hours, whichever occurs
less than 30,000 total flight cycles first, until the airplane
and 60,000 total flight hours, as of accumulates 30,000 total
the effective date of this AD. flight cycles or 60,000 total
flight hours; then perform the
inspections within the
interval specified in
paragraph (h)(2) of this AD.
(2) Model A310-203, A310-204, and A310- 3,900 flight cycles or 7,800
222 airplanes that have accumulated flight hours, whichever occurs
30,000 total flight cycles or more or first.
60,000 total flight hours or more, as
of the effective date of this AD.
(3) Model A310-304, A310-322 and A310- 4,800 flight cycles or 13,500
324 short range airplanes that have flight hours, whichever occurs
accumulated less than 24,000 total first, until the airplane
flight cycles and 67,500 total flight accumulates 24,000 total
hours, as of the effective date of flight cycles or 67,500 total
this AD. flight hours; then perform the
inspections within the
interval specified in
paragraph (h)(4) of this AD.
(4) Model A310-304, A310-322 and A310- 3,100 flight cycles or 8,750
324 short range airplanes that have flight hours, whichever occurs
accumulated 24,000 total flight cycles first.
or more or 67,500 total flight hours
or more, as of the effective date of
this AD.
(5) Model A310-304, A310-322 and A310- 3,000 flight cycles or 15,000
324 long range airplanes that have flight hours, whichever occurs
accumulated less than 15,000 total first, until the airplane
flight cycles and 75,000 total flight accumulates 15,000 total
hours, as of the effective date of flight cycles or 75,000 total
this AD. flight hours; then perform the
inspections within the
interval specified in
paragraph (h)(6) of this AD.
(6) Model A310-304, A310-322 and A310- 1,950 flight cycles or 9,750
324 long range airplanes that have flight hours, whichever occurs
accumulated 15,000 total flight cycles first.
or more or 75,000 total flight hours
or more, as of the effective date of
this AD.
------------------------------------------------------------------------
(i) Repeat the inspections for area 2 required by paragraphs
(g)(1) and (g)(4) of this AD thereafter at the applicable intervals
specified in Table 2 of this AD. Certain compliance times are
applicable to short-range use (AFT equal to or less than 4 flight
hours), or long-range use (AFT exceeding 4 flight hours). Inspection
areas are specified in Airbus Mandatory Service Bulletin A310-53-
2074, Revision 04, dated October 24, 2008.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(j) Inspections accomplished before the effective date of this
AD in accordance with Airbus Mandatory Service Bulletin A310-53-
2074, Revision 03, dated October 13, 2006, are considered acceptable
for compliance with the corresponding action specified in this AD.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: The MCAI and service information do not specify a
corrective action if cracking is found and the radius of the rework
is 20.0 mm (0.787 inch) or more. Paragraph (g)(3)(i)(B) of this AD
requires repair in accordance with a method approved by either the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate, or EASA (or its delegated agent).
Other FAA AD Provisions
(k) 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
[[Page 27250]]
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, Washington 98057-
3356; telephone (425) 227-2125; fax (425) 227-1149. Information may
be e-mailed 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 or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
Related Information
(l) Refer to MCAI EASA Airworthiness Directive 2009-0058, dated
March 13, 2009; and Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008; for related information.
Material Incorporated by Reference
(m) You must use Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail [email protected];
Internet http://www.airbus.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-10688 Filed 5-10-11; 8:45 am]
BILLING CODE 4910-13-P