Airworthiness Directives; Airbus Model A300 B4-2C, B4-103, and B4-203 Airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R Airplanes, 11435-11439 [2010-5165]
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Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations
11435
Actions
Compliance
Procedures
(1) Inspect the installation of the stand-off hardware between the heater fuel line and heater
over-temperature sensor wires for minimum
clearance.
Within the next 50 hours time-in-service (TIS)
after April 15, 2010 (the effective date of
this AD) or within the next 12 months after
April 15, 2010 (the effective date of this
AD), whichever occurs first.
Before further flight after the inspection where
the missing stand-off hardware and/or inadequate clearance was found.
Follow Hawker Beechcraft Mandatory Service
Bulletin SB 32–3898, dated November
2008.
Within the next 50 hours TIS after April 15,
2010 (the effective date of this AD) or within the next 12 months after April 15, 2010
(the effective date of this AD), whichever
occurs first.
Before further flight after the inspection where
damaged tubing and/or wiring was found.
Follow Hawker Beechcraft Mandatory Service
Bulletin SB 32–3898, dated November
2008.
Within the next 50 hours TIS after April 15,
2010 (the effective date of this AD) or within the next 12 months after April 15, 2010
(the effective date of this AD), whichever
occurs first.
Before further flight after the inspection where
the missing stand-off hardware and/or inadequate clearance was found.
Follow Hawker Beechcraft Mandatory Service
Bulletin SB 32–3898, dated November
2008.
(4) You may also review copies of the
service information incorporated by reference
for this AD at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
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:
(2) If, during the inspection required in paragraph (f)(1) of this AD, the stand-off hardware is not installed or it does not maintain
the minimum clearance, install stand-off hardware as specified in the service information.
(3) Inspect the brake reservoir line and the fuel
heater power wire for damage.
(4) If, during the inspection required in paragraph (f)(3) of this AD, damage is found, repair or replace damaged tubing and/or wiring
found.
(5) Inspect the installation of the stand-off hardware between the brake reservoir line and
the fuel heater power wire for minimum clearance.
(6) If, during the inspection required in paragraph (f)(5) of this AD, the stand-off hardware is not installed or it does not maintain
the minimum clearance, install stand-off hardware as specified in the service information.
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Kevin
Schwemmer, Aerospace Engineer, FAA
Wichita Aircraft Certification Office, 1801
Airport Road, Room 100, Wichita, Kansas
67209; telephone: (316) 946–4174; fax: (316)
946–4107. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Kansas City, Missouri, on March
2, 2010.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–5024 Filed 3–10–10; 8:45 am]
BILLING CODE 4910–13–P
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Material Incorporated by Reference
(h) You must use Hawker Beechcraft
Mandatory Service Bulletin SB 32–3898,
dated November 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 Hawker Beechcraft
Corporation, P.O. Box 85, Wichita, Kansas
67201–0085; telephone: 1 (800) 429–5372 or
(316) 676–3140; fax: (316) 676–3340;
Internet: https://www.hawkerbeechcraft.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2009–0993; Directorate
Identifier 2009–NM–089–AD; Amendment
39–16229; AD 2010–06–05]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–2C, B4–103, and B4–203
Airplanes; and Model A300 B4–601,
B4–603, B4–620, B4–622, B4–605R,
and B4–622R Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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Follow Hawker Beechcraft Mandatory Service
Bulletin SB 32–3898, dated November
2008.
Follow Hawker Beechcraft Mandatory Service
Bulletin SB 32–3898, dated November
2008.
One A300–600 aeroplane operator reported
that, during a routine inspection, the Right
Hand frame 40 forward fitting between
stringer 32 and stringer 33 was found
cracked. The subject aeroplane had
previously been modified in accordance with
Airbus SB A300–57–6053 (Airbus
Modification 10453).
This condition, if not corrected, could
result in a deterioration of the structural
integrity of the frame.
*
14 CFR Part 39
PO 00000
Follow Hawker Beechcraft Mandatory Service
Bulletin SB 32–3898, dated November
2008.
Sfmt 4700
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective April
15, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 15, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
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Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations
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 October 28, 2009 (74 FR
55485). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
One A300–600 aeroplane operator reported
that, during a routine inspection, the Right
Hand frame 40 forward fitting between
stringer 32 and stringer 33 was found
cracked. The subject aeroplane had
previously been modified in accordance with
Airbus SB A300–57–6053 (Airbus
Modification 10453).
This condition, if not corrected, could
result in a deterioration of the structural
integrity of the frame.
As no fatigue maintenance tasks
(Inspection SB or Airworthiness Limitation
Item) presently exist to inspect the affected
area for aeroplanes having incorporated
Airbus Modification 10453 preventively
(without preliminary crack finding), Airbus
has developed a new inspection [for
cracking, and repair if necessary] to ensure
structural integrity of the concerned area of
frame 40.
*
*
*
*
*
You may obtain further information
by examining the MCAI in the AD
docket.
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Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Request To Increase Work Hours
FedEx Express states that it has
determined that the inspection
thresholds in the NPRM allow sufficient
time to accomplish the proposed
inspection during a scheduled
maintenance check. FedEx Express adds
that the number of work-hours and
elapsed time necessary to accomplish
the proposed inspections will not
impact the overall span-time of its
planned scheduled maintenance check,
unless cracks are found. FedEx Express
notes that if cracks are found, significant
downtime of approximately 42 hours
will be required to accomplish the
corrective action. FedEx Express adds
that it has already accomplished the
VerDate Nov<24>2008
16:21 Mar 10, 2010
Jkt 220001
inspections on five airplanes with no
crack findings.
From these statements, we infer that
FedEx Express is requesting that we
revise the AD to include the work-hours
necessary to repair any crack findings.
We do not agree. The economic analysis
of the AD is limited only to the cost of
actions actually required by the rule. It
does not consider the costs of ‘‘oncondition’’ actions (that is, actions
needed to correct an unsafe condition
such as cracking), because, regardless of
AD direction, those actions would be
required to correct an unsafe condition
identified in an airplane and ensure
operation of that airplane in an
airworthy condition, as required by the
Federal Aviation Regulations. We have
not changed the AD in this regard.
Explanation of Additional Note in the
Final Rule
We have included a new Note 2 in
this AD (and renumbered subsequent
notes accordingly) to provide
clarification that a repair is considered
any modification that restores the
original strength of the cracked part.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We also determined that this change
will not increase the economic burden
on any operator or increase the scope of
the AD.
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.
Explanation of Change to Costs of
Compliance
Since issuance of the original NPRM,
we have increased the labor rate used in
the Costs of Compliance from $80 per
work hour to $85 per work hour. The
Costs of Compliance information,
below, reflects this increase in the
specified hourly labor rate.
PO 00000
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Sfmt 4700
Costs of Compliance
We estimate that this AD will affect
153 products of U.S. registry. We also
estimate that it will take about 3 workhours 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 $39,015, or $255 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
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify 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 https://
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
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Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 15, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus airplanes,
certificated in any category, as identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A300 B4–2C, B4–103, and B4–
203 airplanes, all serial numbers, modified
preventively in service (without preliminary
crack findings) in accordance with Airbus
Service Bulletin A300–53–0297 (Airbus
Modification 10453).
(2) Model A300 B4–601, B4–603, B4–605R,
B4–620, B4–622, and B4–622R airplanes, all
serial numbers, modified preventively in
service (without preliminary crack findings)
in accordance with Airbus Service Bulletin
A300–57–6053 (Airbus Modification 10453).
Note 1: For airplanes on which Airbus
Service Bulletin A300–53–0297 or A300–57–
6053 (Airbus Modification 10453), as
applicable, has been incorporated as a
corrective action (repair following crack
finding), no action is required by this AD.
■
2. The FAA amends § 39.13 by adding
the following new AD:
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
2010–06–05 Airbus: Amendment 39–16229.
Docket No. FAA–2009–0993; Directorate
Identifier 2009–NM–089–AD.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
11437
‘‘One A300–600 aeroplane operator
reported that, during a routine inspection,
the Right Hand frame 40 forward fitting
between stringer 32 and stringer 33 was
found cracked. The subject aeroplane had
previously been modified in accordance with
Airbus SB A300–57–6053 (Airbus
Modification 10453).
‘‘This condition, if not corrected, could
result in a deterioration of the structural
integrity of the frame.
‘‘As no fatigue maintenance tasks
(Inspection SB or Airworthiness Limitation
Item) presently exist to inspect the affected
area for aeroplanes having incorporated
Airbus Modification 10453 preventively
(without preliminary crack finding), Airbus
has developed a new inspection [for
cracking, and repair if necessary] to ensure
structural integrity of the concerned area of
frame 40.’’
*
*
*
*
*
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) At the applicable time specified in
Table 1 of this AD: Do a one-time detailed
visual inspection of the forward fitting at
frame 40 on both sides of the airplane, in
accordance with Airbus Mandatory Service
Bulletin A300–57A6108 (for Model A300 B4–
601, B4–603, B4–605R, B4–620, B4–622, and
B4–622R airplanes) or A300–53A0387 (for
Model A300 B4–2C, B4–103, and B4–203
airplanes), both including Appendices 01
and 02, both dated September 12, 2008.
TABLE 1—COMPLIANCE TIMES
Airplane models/configuration
Compliance time
A300 B4–2C and B4–103 airplanes on which Airbus
Service Bulletin A300–53–0297 was done prior to the
accumulation of 9,000 total flight cycles.
A300 B4–2C and B4–103 airplanes on which Airbus
Service Bulletin A300–53–0297 was done on or after
the accumulation of 9,000 total flight cycles.
Prior to the accumulation of 18,000 total flight cycles, or within 3 months after the effective date of this AD, whichever occurs later.
A300 B4–203 airplanes on which Airbus Service Bulletin
A300–53–0297 was done prior to the accumulation of
8,300 total flight cycles.
A300 B4–203 airplanes on which Airbus Service Bulletin
A300–53–0297 was done on or after the accumulation
of 8,300 total flight cycles.
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A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and
B4–622R airplanes on which Airbus Service Bulletin
A300–57–6053 was done prior to the accumulation of
6,100 total flight cycles.
A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and
B4–622R airplanes on which Airbus Service Bulletin
A300–57–6053 was done on or after the accumulation
of 6,100 total flight cycles.
(2) Except as required by paragraph (f)(3)
of this AD: If any crack is found during the
inspection required by paragraph (f)(1) of this
AD, before further flight, do a temporary or
definitive repair, as applicable, in accordance
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Within 5,500 flight cycles after accomplishment of Airbus Service Bulletin A300–53–
0297, or within 6 months after the effective date of this AD, whichever occurs later;
except, for airplanes that, as of the effective date of this AD, have accumulated
11,000 flight cycles or more since accomplishment of Airbus Service Bulletin
A300–53–0297, within 3 months after the effective date of this AD.
Prior to the accumulation of 15,000 total flight cycles, or within 3 months after the effective date of this AD, whichever occurs later.
Within 4,100 flight cycles after accomplishment of Airbus Service Bulletin A300–53–
0297, or within 6 months after the effective date of this AD, whichever occurs later;
except, for airplanes that, as of the effective date of this AD, have accumulated
8,200 flight cycles or more since accomplishment of Airbus Service Bulletin A300–
53–0297, within 3 months after the effective date of this AD.
Prior to the accumulation of 11,500 total flight cycles, or within 3 months after the effective date of this AD, whichever occurs later.
Within 3,300 flight cycles after accomplishment of Airbus Service Bulletin A300–57–
6053, or within 6 months after the effective date of this AD, whichever occurs later;
except, for airplanes that, as of the effective date of this AD, have accumulated
6,600 flight cycles or more since accomplishment of Airbus Service Bulletin A300–
57–6053, within 3 months after the effective date of this AD.
with the Accomplishment Instructions of
Airbus Service Bulletin A300–53–0268,
Revision 06, dated January 7, 2002 (for Model
A300 B4–2C, B4–103, and B4–203 airplanes);
or A300–57–6052, Revision 03, dated May
PO 00000
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27, 2002, including Airbus Drawings
15R53810394, Issue A, dated December 21,
1998, and 21R57110247, Issue A, dated June
20, 1997 (for Model A300 B4–601, B4–603,
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B4–605R, B4–620, B4–622, and B4–622R
airplanes).
(3) If any crack found during the inspection
required by paragraph (f)(1) of this AD cannot
be repaired in accordance with Airbus
Service Bulletin A300–53–0268, Revision 06,
dated January 7, 2002; or A300–57–6052,
Revision 03, dated May 27, 2002: Contact
Airbus for repair instructions and before
further flight repair the crack using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA) (or its delegated
agent.)
Note 2: A repair is considered any
modification that restores the original
strength of the cracked part.
(4) Submit an inspection report in
accordance with Appendix 01 of Airbus
Mandatory Service Bulletin A300–53A0387,
dated September 12, 2008 (for Model A300
B4–2C, B4–103, and B4–203 airplanes); or
Airbus Mandatory Service Bulletin A300–
57A6108, dated September 12, 2008 (for
Model A300 B4–601, B4–603, B4–605R, B4–
620, B4–622, and B4–622R airplanes); to the
address identified on the reporting sheet, at
the applicable time specified in paragraph
(f)(4)(i) or (f)(4)(ii) of this AD.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(ii) 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.
FAA AD Differences
Note 3: This AD differs from the MCAI
and/or service information as follows:
Although the MCAI or Airbus Service
Bulletin A300–53–0268, Revision 06, dated
January 7, 2002; or A300–57–6052, Revision
03, dated May 27, 2002; allows further flight
after cracks are found during compliance
with the required action, paragraph (f)(3) of
this AD requires that the cracks be repaired
before further flight.
Other FAA AD Provisions
(g) 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.
Send information 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. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards 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.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2009–0094, dated April 21, 2009
(Correction: May 29, 2009), and the
applicable service information specified in
Table 2 of this AD, for related information.
TABLE 2—RELATED SERVICE INFORMATION
Document
Revision
Date
Airbus Mandatory Service Bulletin A300–53A0387, including Appendices 01 and 02 ........
Airbus Mandatory Service Bulletin A300–57A6108, including Appendices 01 and 02 ........
Airbus Service Bulletin A300–53–0268 .................................................................................
Airbus Service Bulletin A300–57–6052, including Airbus Drawings 15R53810394, Issue
A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997.
Original ..................................
Original ..................................
06 ..........................................
03 ..........................................
September 12, 2008.
September 12, 2008.
January 7, 2002.
May 27, 2002.
Material Incorporated by Reference
(i) You must use the service information
contained in Table 3 of this AD to do the
actions required by this AD, as applicable,
unless the AD specifies otherwise.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
Document
Revision
Date
Airbus Mandatory Service Bulletin A300–53A0387, including Appendices 01 and 02 ........
Airbus Mandatory Service Bulletin A300–57A6108, including Appendices 01 and 02 ........
Airbus Service Bulletin A300–53–0268 .................................................................................
Airbus Service Bulletin A300–57–6052, including Airbus Drawings 15R53810394, Issue
A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997.
Original ..................................
Original ..................................
06 ..........................................
03 ..........................................
September 12, 2008.
September 12, 2008.
January 7, 2002.
May 27, 2002.
Airbus Service Bulletin A300–53–0268,
Revision 06, dated January 7, 2002, has the
following effective pages:
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Page No.
Revision level shown on page
Date shown on page
1–6, 9, 10, 25–27 ..............................................................
7, 8, 11–24, 28–84 ............................................................
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05
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January 7, 2002.
June 9, 2000.
Federal Register / Vol. 75, No. 47 / Thursday, March 11, 2010 / Rules and Regulations
11439
Airbus Service Bulletin A300–57–6052,
Revision 03, dated May 27, 2002, has the
following effective pages:
Page No.
Revision level shown on page
1–56 ......................................................................................................................
03 ..........................................................
Date shown on page
May 27, 2002.
DRAWING 15R53810394
1–2 ........................................................................................................................
A ............................................................
December 21, 1998.
DRAWING 21R57110247
1–2 ........................................................................................................................
3–4 ........................................................................................................................
(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: account.airwortheas@airbus.com; Internet https://
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 or 425–227–1152.
(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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on March 4,
2010.
Suzanne Masterson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–5165 Filed 3–10–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0649; Directorate
Identifier 2008–NM–218–AD; Amendment
39–16225; AD 2010–06–01]
jlentini on DSKJ8SOYB1PROD with RULES
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319, A320, and A321 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
VerDate Nov<24>2008
16:21 Mar 10, 2010
Jkt 220001
A ............................................................
A ............................................................
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:
Two incidents [of near mid-air collision]
have occurred on Airbus A320 Family
aircraft during [a] Resolution Advisory with
Traffic Alert and Collision Avoidance System
(TCAS). One of the Human-Machine Interface
(HMI) factors was the lack of visibility of
relevant information on the Primary Flight
Display (PFD).
This condition, if not corrected, could
result in erroneous interpretation of TCAS
Resolution Advisories, leading to an
increased risk of mid-air collision.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective April
15, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 15, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
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: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2141; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
May 28, 1997.
June 20, 1997.
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on July 15, 2009 (74 FR 34274).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Two incidents [of near mid-air collision]
have occurred on Airbus A320 Family
aircraft during [a] Resolution Advisory with
Traffic Alert and Collision Avoidance System
(TCAS). One of the Human-Machine Interface
(HMI) factors was the lack of visibility of
relevant information on the Primary Flight
Display (PFD).
This condition, if not corrected, could
result in erroneous interpretation of TCAS
Resolution Advisories, leading to an
increased risk of mid-air collision.
EIS1 [Electronic Instrument System]
software standard V60 introduces
modifications to the vertical speed indication
to further improve the legibility in the case
of TCAS Resolution Advisory. This
modification consists of a change in the
needle colour and thickness and an increase
in width of the TCAS green band.
For the reasons described above, this AD
requires the introduction of the new software
standard V60 and prohibits reinstallation of
earlier software versions V32, V40 and V50.
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
considered the comments received.
Support for the NPRM
Air Line Pilots Association (ALPA),
International, supports the intent of the
AD.
Request To Shorten the Proposed
Compliance Time
ALPA states that the proposed 60month compliance time is excessive,
given that Airbus Mandatory Service
Bulletin A320–31–1286 was issued in
January, 2008. Based on the safety
benefits of the AD as well as the
minimal labor required to comply with
E:\FR\FM\11MRR1.SGM
11MRR1
]]>Agencies
[Federal Register Volume 75, Number 47 (Thursday, March 11, 2010)]
[Rules and Regulations]
[Pages 11435-11439]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-5165]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0993; Directorate Identifier 2009-NM-089-AD;
Amendment 39-16229; AD 2010-06-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-2C, B4-103, and
B4-203 Airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, and B4-622R 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:
One A300-600 aeroplane operator reported that, during a routine
inspection, the Right Hand frame 40 forward fitting between stringer
32 and stringer 33 was found cracked. The subject aeroplane had
previously been modified in accordance with Airbus SB A300-57-6053
(Airbus Modification 10453).
This condition, if not corrected, could result in a
deterioration of the structural integrity of the frame.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective April 15, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 15,
2010.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140,
[[Page 11436]]
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 October 28, 2009 (74
FR 55485). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
One A300-600 aeroplane operator reported that, during a routine
inspection, the Right Hand frame 40 forward fitting between stringer
32 and stringer 33 was found cracked. The subject aeroplane had
previously been modified in accordance with Airbus SB A300-57-6053
(Airbus Modification 10453).
This condition, if not corrected, could result in a
deterioration of the structural integrity of the frame.
As no fatigue maintenance tasks (Inspection SB or Airworthiness
Limitation Item) presently exist to inspect the affected area for
aeroplanes having incorporated Airbus Modification 10453
preventively (without preliminary crack finding), Airbus has
developed a new inspection [for cracking, and repair if necessary]
to ensure structural integrity of the concerned area of frame 40.
* * * * *
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 considered the comment received.
Request To Increase Work Hours
FedEx Express states that it has determined that the inspection
thresholds in the NPRM allow sufficient time to accomplish the proposed
inspection during a scheduled maintenance check. FedEx Express adds
that the number of work-hours and elapsed time necessary to accomplish
the proposed inspections will not impact the overall span-time of its
planned scheduled maintenance check, unless cracks are found. FedEx
Express notes that if cracks are found, significant downtime of
approximately 42 hours will be required to accomplish the corrective
action. FedEx Express adds that it has already accomplished the
inspections on five airplanes with no crack findings.
From these statements, we infer that FedEx Express is requesting
that we revise the AD to include the work-hours necessary to repair any
crack findings. We do not agree. The economic analysis of the AD is
limited only to the cost of actions actually required by the rule. It
does not consider the costs of ``on-condition'' actions (that is,
actions needed to correct an unsafe condition such as cracking),
because, regardless of AD direction, those actions would be required to
correct an unsafe condition identified in an airplane and ensure
operation of that airplane in an airworthy condition, as required by
the Federal Aviation Regulations. We have not changed the AD in this
regard.
Explanation of Additional Note in the Final Rule
We have included a new Note 2 in this AD (and renumbered subsequent
notes accordingly) to provide clarification that a repair is considered
any modification that restores the original strength of the cracked
part.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting the
AD with the change described previously. We also determined that this
change will not increase the economic burden on any operator or
increase the scope of the AD.
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.
Explanation of Change to Costs of Compliance
Since issuance of the original NPRM, we have increased the labor
rate used in the Costs of Compliance from $80 per work hour to $85 per
work hour. The Costs of Compliance information, below, reflects this
increase in the specified hourly labor rate.
Costs of Compliance
We estimate that this AD will affect 153 products of U.S. registry.
We also estimate that it will take about 3 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 $39,015, or $255 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
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify 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 https://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
[[Page 11437]]
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
0
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:
2010-06-05 Airbus: Amendment 39-16229. Docket No. FAA-2009-0993;
Directorate Identifier 2009-NM-089-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
15, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus airplanes, certificated in any
category, as identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A300 B4-2C, B4-103, and B4-203 airplanes, all serial
numbers, modified preventively in service (without preliminary crack
findings) in accordance with Airbus Service Bulletin A300-53-0297
(Airbus Modification 10453).
(2) Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-
622R airplanes, all serial numbers, modified preventively in service
(without preliminary crack findings) in accordance with Airbus
Service Bulletin A300-57-6053 (Airbus Modification 10453).
Note 1: For airplanes on which Airbus Service Bulletin A300-53-
0297 or A300-57-6053 (Airbus Modification 10453), as applicable, has
been incorporated as a corrective action (repair following crack
finding), no action is required by this AD.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
``One A300-600 aeroplane operator reported that, during a
routine inspection, the Right Hand frame 40 forward fitting between
stringer 32 and stringer 33 was found cracked. The subject aeroplane
had previously been modified in accordance with Airbus SB A300-57-
6053 (Airbus Modification 10453).
``This condition, if not corrected, could result in a
deterioration of the structural integrity of the frame.
``As no fatigue maintenance tasks (Inspection SB or
Airworthiness Limitation Item) presently exist to inspect the
affected area for aeroplanes having incorporated Airbus Modification
10453 preventively (without preliminary crack finding), Airbus has
developed a new inspection [for cracking, and repair if necessary]
to ensure structural integrity of the concerned area of frame 40.''
* * * * *
Actions and Compliance
(f) Unless already done, do the following actions.
(1) At the applicable time specified in Table 1 of this AD: Do a
one-time detailed visual inspection of the forward fitting at frame
40 on both sides of the airplane, in accordance with Airbus
Mandatory Service Bulletin A300-57A6108 (for Model A300 B4-601, B4-
603, B4-605R, B4-620, B4-622, and B4-622R airplanes) or A300-53A0387
(for Model A300 B4-2C, B4-103, and B4-203 airplanes), both including
Appendices 01 and 02, both dated September 12, 2008.
Table 1--Compliance Times
------------------------------------------------------------------------
Airplane models/configuration Compliance time
------------------------------------------------------------------------
A300 B4-2C and B4-103 airplanes on Prior to the accumulation of 18,000
which Airbus Service Bulletin total flight cycles, or within 3
A300-53-0297 was done prior to months after the effective date of
the accumulation of 9,000 total this AD, whichever occurs later.
flight cycles.
A300 B4-2C and B4-103 airplanes on Within 5,500 flight cycles after
which Airbus Service Bulletin accomplishment of Airbus Service
A300-53-0297 was done on or after Bulletin A300-53-0297, or within 6
the accumulation of 9,000 total months after the effective date of
flight cycles. this AD, whichever occurs later;
except, for airplanes that, as of
the effective date of this AD, have
accumulated 11,000 flight cycles or
more since accomplishment of Airbus
Service Bulletin A300-53-0297,
within 3 months after the effective
date of this AD.
A300 B4-203 airplanes on which Prior to the accumulation of 15,000
Airbus Service Bulletin A300-53- total flight cycles, or within 3
0297 was done prior to the months after the effective date of
accumulation of 8,300 total this AD, whichever occurs later.
flight cycles.
A300 B4-203 airplanes on which Within 4,100 flight cycles after
Airbus Service Bulletin A300-53- accomplishment of Airbus Service
0297 was done on or after the Bulletin A300-53-0297, or within 6
accumulation of 8,300 total months after the effective date of
flight cycles. this AD, whichever occurs later;
except, for airplanes that, as of
the effective date of this AD, have
accumulated 8,200 flight cycles or
more since accomplishment of Airbus
Service Bulletin A300-53-0297,
within 3 months after the effective
date of this AD.
A300 B4-601, B4-603, B4-605R, B4- Prior to the accumulation of 11,500
620, B4-622, and B4-622R total flight cycles, or within 3
airplanes on which Airbus Service months after the effective date of
Bulletin A300-57-6053 was done this AD, whichever occurs later.
prior to the accumulation of
6,100 total flight cycles.
A300 B4-601, B4-603, B4-605R, B4- Within 3,300 flight cycles after
620, B4-622, and B4-622R accomplishment of Airbus Service
airplanes on which Airbus Service Bulletin A300-57-6053, or within 6
Bulletin A300-57-6053 was done on months after the effective date of
or after the accumulation of this AD, whichever occurs later;
6,100 total flight cycles. except, for airplanes that, as of
the effective date of this AD, have
accumulated 6,600 flight cycles or
more since accomplishment of Airbus
Service Bulletin A300-57-6053,
within 3 months after the effective
date of this AD.
------------------------------------------------------------------------
(2) Except as required by paragraph (f)(3) of this AD: If any
crack is found during the inspection required by paragraph (f)(1) of
this AD, before further flight, do a temporary or definitive repair,
as applicable, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7,
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings
15R53810394, Issue A, dated December 21, 1998, and 21R57110247,
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603,
[[Page 11438]]
B4-605R, B4-620, B4-622, and B4-622R airplanes).
(3) If any crack found during the inspection required by
paragraph (f)(1) of this AD cannot be repaired in accordance with
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7,
2002; or A300-57-6052, Revision 03, dated May 27, 2002: Contact
Airbus for repair instructions and before further flight repair the
crack using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its delegated agent.)
Note 2: A repair is considered any modification that restores
the original strength of the cracked part.
(4) Submit an inspection report in accordance with Appendix 01
of Airbus Mandatory Service Bulletin A300-53A0387, dated September
12, 2008 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or
Airbus Mandatory Service Bulletin A300-57A6108, dated September 12,
2008 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and
B4-622R airplanes); to the address identified on the reporting
sheet, at the applicable time specified in paragraph (f)(4)(i) or
(f)(4)(ii) of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) 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.
FAA AD Differences
Note 3: This AD differs from the MCAI and/or service information
as follows: Although the MCAI or Airbus Service Bulletin A300-53-
0268, Revision 06, dated January 7, 2002; or A300-57-6052, Revision
03, dated May 27, 2002; allows further flight after cracks are found
during compliance with the required action, paragraph (f)(3) of this
AD requires that the cracks be repaired before further flight.
Other FAA AD Provisions
(g) 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. Send information 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. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards 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.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2009-0094, dated
April 21, 2009 (Correction: May 29, 2009), and the applicable
service information specified in Table 2 of this AD, for related
information.
Table 2--Related Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A300- Original.................... September 12, 2008.
53A0387, including Appendices 01 and 02.
Airbus Mandatory Service Bulletin A300- Original.................... September 12, 2008.
57A6108, including Appendices 01 and 02.
Airbus Service Bulletin A300-53-0268....... 06.......................... January 7, 2002.
Airbus Service Bulletin A300-57-6052, 03.......................... May 27, 2002.
including Airbus Drawings 15R53810394,
Issue A, dated December 21, 1998, and
21R57110247, Issue A, dated June 20, 1997.
----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(i) You must use the service information contained in Table 3 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
Table 3--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A300- Original.................... September 12, 2008.
53A0387, including Appendices 01 and 02.
Airbus Mandatory Service Bulletin A300- Original.................... September 12, 2008.
57A6108, including Appendices 01 and 02.
Airbus Service Bulletin A300-53-0268....... 06.......................... January 7, 2002.
Airbus Service Bulletin A300-57-6052, 03.......................... May 27, 2002.
including Airbus Drawings 15R53810394,
Issue A, dated December 21, 1998, and
21R57110247, Issue A, dated June 20, 1997.
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-53-0268, Revision 06, dated January
7, 2002, has the following effective pages:
--------------------------------------------------------------------------------------------------------------------------------------------------------
Page No. Revision level shown on page Date shown on page
--------------------------------------------------------------------------------------------------------------------------------------------------------
1-6, 9, 10, 25-27................................ 06 January 7, 2002.
7, 8, 11-24, 28-84............................... 05 June 9, 2000.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 11439]]
Airbus Service Bulletin A300-57-6052, Revision 03, dated May 27,
2002, has the following effective pages:
------------------------------------------------------------------------
Revision level
Page No. shown on page Date shown on page
------------------------------------------------------------------------
1-56........................ 03............ May 27, 2002.
------------------------------------------------------------------------
DRAWING 15R53810394
------------------------------------------------------------------------
1-2......................... A............. December 21, 1998.
------------------------------------------------------------------------
DRAWING 21R57110247
------------------------------------------------------------------------
1-2......................... A............. May 28, 1997.
3-4......................... A............. June 20, 1997.
------------------------------------------------------------------------
(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: account.airworth-eas@airbus.com;
Internet https://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 or 425-227-1152.
(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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on March 4, 2010.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-5165 Filed 3-10-10; 8:45 am]
BILLING CODE 4910-13-P
