Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes; and Model A340-200 and -300 Series Airplanes, 62208-62211 [E9-28069]
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62208
Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations
3. On page 55739, in the third column
under § 274a.2 (b)(1)(v)(D)(1)(i), revise
the phrase ‘‘Department of Labor’’ to
read ‘‘Office of the Attorney General,
Division of Immigration’’.
■
PART 1212—DOCUMENTARY
REQUIREMENTS; NONIMMIGRANTS;
WAIVERS; ADMISSION OF CERTAIN
INADMISSIBLE ALIENS; PAROLE
4. On page 55742, in the third column,
in paragraph 1212.1(q)(1) introductory
text, the citation ‘‘8 CFR 212(1)’’ is
revised to read ‘‘8 CFR 212(q)’’.
■
Rosemary Hart,
Federal Register Liaison Officer, Department
of Justice.
Christina E. McDonald,
Deputy Associate General Counsel for
Regulatory Affairs, Department of Homeland
Security.
[FR Doc. E9–28417 Filed 11–25–09; 8:45 am]
BILLING CODE 9111–97–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1092; Directorate
Identifier 2009–NM–219–AD; Amendment
39–16068; AD 2009–24–09]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200 and -300 Series Airplanes;
and Model A340–200 and -300 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
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:
srobinson on DSKHWCL6B1PROD with RULES
SUMMARY:
An A330 operator experienced a low level
of the Yellow hydraulic circuit due to a
loose[ning] of check valve part number (P/N)
CAR401. During the inspection on the other
two hydraulic systems, the other three
CAR401 check valves were also found to be
loose with their lock wire broken in two
instances.
A340 aeroplanes are also equipped with
the same high pressure manifold check
valves.
Investigations are on-going to determine
the root cause of this event.
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16:26 Nov 25, 2009
Jkt 220001
Additional cases of CAR401 check valve
loosening have been experienced in service
on aeroplanes having accumulated more than
1000 flight cycles (FC). The check valve fitted
on the Yellow hydraulic system is more
affected, probably due to additional system
cycles induced by cargo door operation.
The loss of torque due to pressure cycles
could contribute to check valve loosening,
resulting in a leak and finally the loss of the
associated hydraulic system and, in the worst
case, of the three hydraulic systems of the
aeroplane.
*
*
*
*
*
The unsafe condition is the possible
loss of all three hydraulic systems,
which could result in loss of control of
the airplane. This AD requires actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
December 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 14, 2009.
We must receive comments on this
AD by January 11, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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
contains this AD, 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Emergency Airworthiness Directive
2009–0223–E, dated October 13, 2009
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
An A330 operator experienced a low level
of the Yellow hydraulic circuit due to a
loose[ning] of check valve part number (P/N)
CAR401. During the inspection on the other
two hydraulic systems, the other three
CAR401 check valves were also found to be
loose with their lock wire broken in two
instances.
A340 aeroplanes are also equipped with
the same high pressure manifold check
valves.
Investigations are on-going to determine
the root cause of this event.
Additional cases of CAR401 check valve
loosening have been experienced in service
on aeroplanes having accumulated more than
1000 flight cycles (FC). The check valve fitted
on the Yellow hydraulic system is more
affected, probably due to additional system
cycles induced by cargo door operation.
The loss of torque due to pressure cycles
could contribute to check valve loosening,
resulting in a leak and finally the loss of the
associated hydraulic system and, in the worst
case, of the three hydraulic systems of the
aeroplane.
This AD requires to perform the following
inspection programme to detect any check
valve loosening and, if necessary, apply the
associated corrective actions:
1st Step: On yellow and blue hydraulic
circuits: lock wire inspection, inspection for
traces of seepage or black deposit, check
valve torque and red marking application.
2nd Step: On green hydraulic circuit: same
inspections as required in 1st Step and on
yellow and blue hydraulic circuits:
inspection of check valves for condition.
Finally: On green, yellow and blue
hydraulic circuits: repetitive inspection of
check valves for condition.
The unsafe condition is the possible
loss of all three hydraulic systems,
which could result in loss of control of
the airplane. The inspection program
involves a detailed inspection of the
lock wire for presence and integrity, a
detailed inspection for traces of seepage
or black deposits, an inspection for
proper torque, and a detailed inspection
to determine alignment of the check
valve and manifold. The corrective
actions include replacing seal
assemblies, replacing the check valve,
removing the lock wire, and re-torquing
the check valve. The required actions
also include installing a new lock wire.
You may obtain further information by
examining the MCAI in the AD docket.
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Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations
Relevant Service Information
Airbus has issued All Operators
Telexes A330–29A3111 and A340–
29A4086, both Revision 1, both dated
October 8, 2009. The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This 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 issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
srobinson on DSKHWCL6B1PROD with RULES
Differences Between the 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 FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because the compliance time
defined in the MCAI is 28 days for
initial inspection. Loss of torque could
lead to loosening of the check valve.
Loosening of the check valve can lead
to a hydraulic leak with possible loss of
the associated hydraulic system, and in
the case of the loss of all three hydraulic
systems of the airplane. Loss of a
hydraulic system could result in
reduced controllability and increased
workload for the flightcrew. Loss of all
three hydraulic systems could result in
loss of control of the airplane.
Therefore, we determined that notice
and opportunity for public comment
before issuing this AD are impracticable
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16:26 Nov 25, 2009
Jkt 220001
and that good cause exists for making
this amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2009–1092;
Directorate Identifier 2009–NM–219–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
62209
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.
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.
Authority for This Rulemaking
§ 39.13
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
Reason
(e) The mandatory continued airworthiness
information (MCAI) states:
An A330 operator experienced a low level
of the Yellow hydraulic circuit due to a
loose[ning] of check valve part number (P/N)
CAR401. During the inspection on the other
two hydraulic systems, the other three
CAR401 check valves were also found to be
loose with their lock wire broken in two
instances.
A340 aeroplanes are also equipped with
the same high pressure manifold check
valves.
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:
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[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
2009–24–09 AIRBUS: Amendment 39–
16068. Docket No. FAA–2009–1092;
Directorate Identifier 2009–NM–219–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 14, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model
A330–201, ¥202, ¥203, ¥223, ¥243,
¥301, ¥302, ¥303, ¥321, ¥322, ¥323,
¥341, ¥342, and ¥343 series airplanes, all
manufacturer serial numbers; and Model
A340–211, ¥212, ¥213, ¥311, ¥312, and
¥313 series airplanes, all manufacturer serial
numbers; certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 29: Hydraulic Power.
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62210
Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations
Investigations are on-going to determine
the root cause of this event.
Additional cases of CAR401 check valve
loosening have been experienced in service
on aeroplanes having accumulated more than
1000 flight cycles (FC). The check valve fitted
on the Yellow hydraulic system is more
affected, probably due to additional system
cycles induced by cargo door operation.
The loss of torque due to pressure cycles
could contribute to check valve loosening,
resulting in a leak and finally the loss of the
associated hydraulic system and, in the worst
case, of the three hydraulic systems of the
aeroplane.
This AD requires to perform the following
inspection programme to detect any check
valve loosening and, if necessary, apply the
associated corrective actions:
1st Step: On yellow and blue hydraulic
circuits: lock wire inspection, inspection for
traces of seepage or black deposit, check
valve torque and red marking application.
2nd Step: On green hydraulic circuit: same
inspections as required in 1st Step and on
yellow and blue hydraulic circuits:
inspection of check valves for condition.
Finally: On green, yellow and blue
hydraulic circuits: repetitive inspection of
check valves for condition.
The unsafe condition is the possible loss of
all three hydraulic systems, which could
result in loss of control of the airplane. The
inspection program involves a detailed
inspection of the lock wire for presence and
integrity, a detailed inspection for traces of
seepage or black deposits, an inspection for
proper torque, and a detailed inspection to
determine alignment of the check valve and
manifold. The corrective actions include
replacing seal assemblies, replacing the
check valve, removing the lock wire, and retorquing the check valve. The required
actions also include installing a new lock
wire.
srobinson on DSKHWCL6B1PROD with RULES
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.
Actions
(g) Do the actions required by paragraphs
(g)(1) through (g)(3) of this AD.
(1) For airplanes that do not have Airbus
Modification 54491 embodied in production,
or Airbus Service Bulletin A330–29–3101 or
Airbus Service Bulletin A340–29–4078
embodied in service: Within 100 flight cycles
or 28 days after the effective date of this AD,
whichever occurs first, inspect the check
valves on the blue, green, and yellow
hydraulic systems to identify their P/Ns, in
accordance with the instructions of Airbus
All Operators Telex (AOT) A330–29A3111,
Revision 1, dated October 8, 2009 (for Model
A330–200 and –300 series airplanes); or AOT
A340–29A4086, Revision 1, dated October 8,
2009 (for Model A340–200 and ¥300 series
airplanes).
(i) If check valves having P/N CAR401 are
installed on all three hydraulic systems,
before further flight, do the actions specified
in paragraph (g)(2)(i) of this AD. After
accomplishing the actions required by
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16:26 Nov 25, 2009
Jkt 220001
paragraph (g)(2)(i) of this AD, do the actions
specified in paragraphs (g)(2)(ii) and
(g)(2)(iii) of this AD at the applicable
compliance times specified in those
paragraphs.
(ii) If check valves having P/N CAR401 are
not installed on all three hydraulic systems,
no further action is required until any check
valve having P/N CAR400 is replaced with a
check valve having P/N CAR401. If any check
valve having P/N CAR400 is replaced by a
check valve having P/N CAR401, before
further flight, do the inspection specified in
paragraph (g)(1) of this AD to determine if all
three hydraulic systems are equipped with
check valve having P/N CAR401.
(2) For airplanes on which Airbus
Modification 54491 was embodied in
production, or Airbus Service Bulletin A330–
29–3101 or Airbus Service Bulletin A340–
29–4078 was embodied in service, do the
actions specified in paragraphs (g)(2)(i),
(g)(2)(ii), and (g)(2)(iii) of this AD.
(i) Except as required by paragraph (g)(1)(i)
of this AD, at the applicable times specified
in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of
this AD, as applicable: Do the inspection
program (detailed inspection of the lock wire
for presence and integrity, a detailed
inspection for traces of seepage or black
deposits, and an inspection for proper
torque) on yellow and blue high pressure
manifolds, install new lock wires, and do all
applicable corrective actions, in accordance
with the instructions of paragraph 4.1.1 of
Airbus AOT A330–29A3111, Revision 1,
dated October 8, 2009 (for Model A330–200
and ¥300 series airplanes); or AOT A340–
29A4086, Revision 1, dated October 8, 2009
(for Model A340–200 and ¥300 series
airplanes). Do all applicable corrective
actions before further flight.
(A) For airplanes on which Airbus
Modification 54491 has been embodied in
production: At the later of the times specified
in paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2)
of this AD.
(1) Before the accumulation of 1,000 total
flight cycles since first flight but no earlier
than the accumulation of 700 total flight
cycles since first flight.
(2) Within 100 flight cycles or 28 days after
the effective date of this AD, whichever
occurs first.
(B) For airplanes on which Airbus Service
Bulletin A330–29–3101 or A340–29–4078
was embodied in service: At the later of the
times specified in paragraphs (g)(2)(i)(B)(1)
and (g)(2)(i)(B)(2) of this AD.
(1) Within 1,000 flight cycles since the
embodiment of Airbus Service Bulletin
A330–29–3101 or A340–29–4078 but no
earlier than 700 flight cycles after the
embodiment of Airbus Service Bulletin
A330–29–3101 or A340–29–4078.
(2) Within 100 flight cycles or 28 days after
the effective date of this AD, whichever
occurs first.
(ii) Within 900 flight hours after
accomplishment of paragraph (g)(2)(i) of this
AD, do the inspection program (detailed
inspection of the lock wire for presence and
integrity, a detailed inspection for traces of
seepage or black deposits, and an inspection
for proper torque) and install a new lock wire
on the green high pressure manifold; and do
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an inspection (detailed inspection for traces
of seepage or black deposits, and detailed
inspection to determine alignment of the
check valve and manifold) on the yellow and
blue high pressure manifolds, and do all
applicable corrective actions; in accordance
with the instructions of paragraph 4.1.2 of
Airbus AOT A330–29A3111, Revision 1,
dated October 8, 2009 (for Model A330–200
and ¥300 series airplanes); or AOT A340–
29A4086, Revision 1, dated October 8, 2009
(for Model A340–200 and ¥300 series
airplanes). Do all applicable corrective
actions before further flight.
(iii) Within 900 flight hours after
accomplishment of paragraph (g)(2)(ii) of this
AD, and thereafter at intervals not to exceed
900 flight hours, do the inspection program
(detailed inspection for traces of seepage or
black deposits, and detailed inspection to
determine alignment of the check valve and
manifold) on the green, yellow, and blue high
pressure manifolds, and do all applicable
corrective actions, in accordance with the
instructions of paragraph 4.1.3 of Airbus
AOT A330–29A3111, Revision 1, dated
October 8, 2009 (for Model A330–200 and
¥300 series airplanes); or AOT A340–
29A4086, Revision 1, dated October 8, 2009
(for Model A340–200 and ¥300 series
airplanes). Do all applicable corrective
actions before further flight.
(iv) Actions accomplished before the
effective date of this AD, according to Airbus
AOT A330–29A3111, dated September 2,
2009 (for Model A330–200 and ¥300 series
airplanes); or AOT A340–29A4086, dated
September 2, 2009 (for Model A340–200 and
¥300 series airplanes); are considered
acceptable for compliance with the
corresponding actions specified in paragraph
(g)(2)(i) of this AD.
(3) Within 10 days after accomplishment of
the inspections specified in paragraphs (g)(1)
and (g)(2) of this AD, or within 10 days after
the effective date of this AD, whichever
occurs later, report all inspection results to
Airbus in accordance with Airbus AOT
A330–29A3111, Revision 1, dated October 8,
2009 (for Model A330–200 and –300 series
airplanes); or AOT A340–29A4086, Revision
1, dated October 8, 2009 (for Model A340–
200 and –300 series airplanes).
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(h) 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: Vladimir
Ulyanov, Aerospace Engineer, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
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Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations
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
(i) Refer to MCAI European Aviation Safety
Agency Emergency Airworthiness Directive
2009–0223–E, dated October 13, 2009; and
Airbus AOTs A330–29A3111 and A340–
29A4086, both Revision 1, both dated
October 8, 2009; for related information.
srobinson on DSKHWCL6B1PROD with RULES
Material Incorporated by Reference
(j) You must use Airbus All Operators
Telex A330–29A3111, Revision 1, dated
October 8, 2009; or Airbus All Operators
Telex A340–29A4086, Revision 1, dated
October 8, 2009; as applicable; to do the
actions required by this AD, unless the AD
specifies otherwise. (Only the first page of
these documents contains the document
number, revision level, and date; no other
page of these documents contain this
information.)
(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—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80, e-mail
airworthiness.A330-A340@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.
VerDate Nov<24>2008
16:26 Nov 25, 2009
Jkt 220001
Issued in Renton, Washington, on
November 16, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–28069 Filed 11–25–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0869; Directorate
Identifier 2009–CE–043–AD; Amendment
39–16090; AD 2009–24–03]
RIN 2120–AA64
Airworthiness Directives; Vulcanair
S.p.A. Models P 68, P 68B, P 68C,
P 68C–TC, and P 68 ‘‘OBSERVER’’
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) to
supersede AD 85–08–04, which applies
to certain Vulcanair S.p.A. Models P 68,
P 68B, P 68C, P 68C–TC, and P 68
‘‘OBSERVER’’ airplanes. AD 85–08–04
currently requires you to repetitively
visually inspect the front and rear wing
spars for cracks. If cracks are found, AD
85–08–04 requires you to modify the
wing spars. The wing spar modification
terminates the repetitive inspection AD
action and may be installed before
cracks develop. Since we issued AD 85–
08–04, the manufacturer revised the
modification kit and identified
additional airplane serial numbers that
require the inspection and/or
modification. Consequently, this AD
would retain the actions of AD 85–08–
04, allow you to install the revised
modification kit, and add additional
serial numbers to the Applicability
section. We are issuing this AD to detect
and correct cracks in the front and rear
wing spar, which could result in the
wing separating from the airplane. This
failure could lead to loss of control.
DATES: This AD becomes effective on
January 4, 2010.
On January 4, 2010, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: For service information
identified in this AD, contact Vulcanair
S.p.A, Via G. Pascoli, 7, Casoria (Naples)
80026 Italy; telephone:
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
62211
(+39)081.5918111; fax:
(+39)081.5918172; e-mail:
customerservice@vulcanair.com;
Internet: https://www.vulcanair.com.
To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2009–0869; Directorate
Identifier 2009–CE–043–AD.
FOR FURTHER INFORMATION CONTACT:
Sarjapur Nagarajan, Aerospace Engineer,
901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
On September 15, 2009, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Vulcanair S.p.A. Models P 68, P
68B, P 68C, P 68C–TC, and P 68
‘‘OBSERVER’’ airplanes. This proposal
was published in the Federal Register
as a notice of proposed rulemaking
(NPRM) on September 21, 2009 (74 FR
48016). The NPRM proposed to
supersede AD 85–08–04 (50 FR 14370,
April 12, 1985) with a new AD that
would retain the actions of AD 85–08–
04, allow you to install the revised
modification kit, and add additional
serial numbers to the Applicability
section.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 81
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
E:\FR\FM\27NOR1.SGM
27NOR1
]]>Agencies
[Federal Register Volume 74, Number 227 (Friday, November 27, 2009)]
[Rules and Regulations]
[Pages 62208-62211]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28069]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1092; Directorate Identifier 2009-NM-219-AD;
Amendment 39-16068; AD 2009-24-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200 and -300 Series
Airplanes; and Model A340-200 and -300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
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:
An A330 operator experienced a low level of the Yellow hydraulic
circuit due to a loose[ning] of check valve part number (P/N)
CAR401. During the inspection on the other two hydraulic systems,
the other three CAR401 check valves were also found to be loose with
their lock wire broken in two instances.
A340 aeroplanes are also equipped with the same high pressure
manifold check valves.
Investigations are on-going to determine the root cause of this
event.
Additional cases of CAR401 check valve loosening have been
experienced in service on aeroplanes having accumulated more than
1000 flight cycles (FC). The check valve fitted on the Yellow
hydraulic system is more affected, probably due to additional system
cycles induced by cargo door operation.
The loss of torque due to pressure cycles could contribute to
check valve loosening, resulting in a leak and finally the loss of
the associated hydraulic system and, in the worst case, of the three
hydraulic systems of the aeroplane.
* * * * *
The unsafe condition is the possible loss of all three hydraulic
systems, which could result in loss of control of the airplane. This AD
requires actions that are intended to address the unsafe condition
described in the MCAI.
DATES: This AD becomes effective December 14, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 14,
2009.
We must receive comments on this AD by January 11, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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 contains this AD, 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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Emergency Airworthiness Directive 2009-0223-E, dated October 13, 2009
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
An A330 operator experienced a low level of the Yellow hydraulic
circuit due to a loose[ning] of check valve part number (P/N)
CAR401. During the inspection on the other two hydraulic systems,
the other three CAR401 check valves were also found to be loose with
their lock wire broken in two instances.
A340 aeroplanes are also equipped with the same high pressure
manifold check valves.
Investigations are on-going to determine the root cause of this
event.
Additional cases of CAR401 check valve loosening have been
experienced in service on aeroplanes having accumulated more than
1000 flight cycles (FC). The check valve fitted on the Yellow
hydraulic system is more affected, probably due to additional system
cycles induced by cargo door operation.
The loss of torque due to pressure cycles could contribute to
check valve loosening, resulting in a leak and finally the loss of
the associated hydraulic system and, in the worst case, of the three
hydraulic systems of the aeroplane.
This AD requires to perform the following inspection programme
to detect any check valve loosening and, if necessary, apply the
associated corrective actions:
1st Step: On yellow and blue hydraulic circuits: lock wire
inspection, inspection for traces of seepage or black deposit, check
valve torque and red marking application.
2nd Step: On green hydraulic circuit: same inspections as
required in 1st Step and on yellow and blue hydraulic circuits:
inspection of check valves for condition.
Finally: On green, yellow and blue hydraulic circuits:
repetitive inspection of check valves for condition.
The unsafe condition is the possible loss of all three hydraulic
systems, which could result in loss of control of the airplane. The
inspection program involves a detailed inspection of the lock wire for
presence and integrity, a detailed inspection for traces of seepage or
black deposits, an inspection for proper torque, and a detailed
inspection to determine alignment of the check valve and manifold. The
corrective actions include replacing seal assemblies, replacing the
check valve, removing the lock wire, and re-torquing the check valve.
The required actions also include installing a new lock wire. You may
obtain further information by examining the MCAI in the AD docket.
[[Page 62209]]
Relevant Service Information
Airbus has issued All Operators Telexes A330-29A3111 and A340-
29A4086, both Revision 1, both dated October 8, 2009. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This 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 issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between the 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 FAA policies. Any such differences are
highlighted in a NOTE within the AD.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because the
compliance time defined in the MCAI is 28 days for initial inspection.
Loss of torque could lead to loosening of the check valve. Loosening of
the check valve can lead to a hydraulic leak with possible loss of the
associated hydraulic system, and in the case of the loss of all three
hydraulic systems of the airplane. Loss of a hydraulic system could
result in reduced controllability and increased workload for the
flightcrew. Loss of all three hydraulic systems could result in loss of
control of the airplane. Therefore, we determined that notice and
opportunity for public comment before issuing this AD are impracticable
and that good cause exists for making this amendment effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2009-1092; Directorate
Identifier 2009-NM-219-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this 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 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.
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:
2009-24-09 AIRBUS: Amendment 39-16068. Docket No. FAA-2009-1092;
Directorate Identifier 2009-NM-219-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
14, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A330-201, -202, -203, -
223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
series airplanes, all manufacturer serial numbers; and Model A340-
211, -212, -213, -311, -312, and -313 series airplanes, all
manufacturer serial numbers; certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 29:
Hydraulic Power.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
An A330 operator experienced a low level of the Yellow hydraulic
circuit due to a loose[ning] of check valve part number (P/N)
CAR401. During the inspection on the other two hydraulic systems,
the other three CAR401 check valves were also found to be loose with
their lock wire broken in two instances.
A340 aeroplanes are also equipped with the same high pressure
manifold check valves.
[[Page 62210]]
Investigations are on-going to determine the root cause of this
event.
Additional cases of CAR401 check valve loosening have been
experienced in service on aeroplanes having accumulated more than
1000 flight cycles (FC). The check valve fitted on the Yellow
hydraulic system is more affected, probably due to additional system
cycles induced by cargo door operation.
The loss of torque due to pressure cycles could contribute to
check valve loosening, resulting in a leak and finally the loss of
the associated hydraulic system and, in the worst case, of the three
hydraulic systems of the aeroplane.
This AD requires to perform the following inspection programme
to detect any check valve loosening and, if necessary, apply the
associated corrective actions:
1st Step: On yellow and blue hydraulic circuits: lock wire
inspection, inspection for traces of seepage or black deposit, check
valve torque and red marking application.
2nd Step: On green hydraulic circuit: same inspections as
required in 1st Step and on yellow and blue hydraulic circuits:
inspection of check valves for condition.
Finally: On green, yellow and blue hydraulic circuits:
repetitive inspection of check valves for condition.
The unsafe condition is the possible loss of all three hydraulic
systems, which could result in loss of control of the airplane. The
inspection program involves a detailed inspection of the lock wire
for presence and integrity, a detailed inspection for traces of
seepage or black deposits, an inspection for proper torque, and a
detailed inspection to determine alignment of the check valve and
manifold. The corrective actions include replacing seal assemblies,
replacing the check valve, removing the lock wire, and re-torquing
the check valve. The required actions also include installing a new
lock wire.
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.
Actions
(g) Do the actions required by paragraphs (g)(1) through (g)(3)
of this AD.
(1) For airplanes that do not have Airbus Modification 54491
embodied in production, or Airbus Service Bulletin A330-29-3101 or
Airbus Service Bulletin A340-29-4078 embodied in service: Within 100
flight cycles or 28 days after the effective date of this AD,
whichever occurs first, inspect the check valves on the blue, green,
and yellow hydraulic systems to identify their P/Ns, in accordance
with the instructions of Airbus All Operators Telex (AOT) A330-
29A3111, Revision 1, dated October 8, 2009 (for Model A330-200 and -
300 series airplanes); or AOT A340-29A4086, Revision 1, dated
October 8, 2009 (for Model A340-200 and -300 series airplanes).
(i) If check valves having P/N CAR401 are installed on all three
hydraulic systems, before further flight, do the actions specified
in paragraph (g)(2)(i) of this AD. After accomplishing the actions
required by paragraph (g)(2)(i) of this AD, do the actions specified
in paragraphs (g)(2)(ii) and (g)(2)(iii) of this AD at the
applicable compliance times specified in those paragraphs.
(ii) If check valves having P/N CAR401 are not installed on all
three hydraulic systems, no further action is required until any
check valve having P/N CAR400 is replaced with a check valve having
P/N CAR401. If any check valve having P/N CAR400 is replaced by a
check valve having P/N CAR401, before further flight, do the
inspection specified in paragraph (g)(1) of this AD to determine if
all three hydraulic systems are equipped with check valve having P/N
CAR401.
(2) For airplanes on which Airbus Modification 54491 was
embodied in production, or Airbus Service Bulletin A330-29-3101 or
Airbus Service Bulletin A340-29-4078 was embodied in service, do the
actions specified in paragraphs (g)(2)(i), (g)(2)(ii), and
(g)(2)(iii) of this AD.
(i) Except as required by paragraph (g)(1)(i) of this AD, at the
applicable times specified in paragraphs (g)(2)(i)(A) and
(g)(2)(i)(B) of this AD, as applicable: Do the inspection program
(detailed inspection of the lock wire for presence and integrity, a
detailed inspection for traces of seepage or black deposits, and an
inspection for proper torque) on yellow and blue high pressure
manifolds, install new lock wires, and do all applicable corrective
actions, in accordance with the instructions of paragraph 4.1.1 of
Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 (for
Model A330-200 and -300 series airplanes); or AOT A340-29A4086,
Revision 1, dated October 8, 2009 (for Model A340-200 and -300
series airplanes). Do all applicable corrective actions before
further flight.
(A) For airplanes on which Airbus Modification 54491 has been
embodied in production: At the later of the times specified in
paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) of this AD.
(1) Before the accumulation of 1,000 total flight cycles since
first flight but no earlier than the accumulation of 700 total
flight cycles since first flight.
(2) Within 100 flight cycles or 28 days after the effective date
of this AD, whichever occurs first.
(B) For airplanes on which Airbus Service Bulletin A330-29-3101
or A340-29-4078 was embodied in service: At the later of the times
specified in paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this
AD.
(1) Within 1,000 flight cycles since the embodiment of Airbus
Service Bulletin A330-29-3101 or A340-29-4078 but no earlier than
700 flight cycles after the embodiment of Airbus Service Bulletin
A330-29-3101 or A340-29-4078.
(2) Within 100 flight cycles or 28 days after the effective date
of this AD, whichever occurs first.
(ii) Within 900 flight hours after accomplishment of paragraph
(g)(2)(i) of this AD, do the inspection program (detailed inspection
of the lock wire for presence and integrity, a detailed inspection
for traces of seepage or black deposits, and an inspection for
proper torque) and install a new lock wire on the green high
pressure manifold; and do an inspection (detailed inspection for
traces of seepage or black deposits, and detailed inspection to
determine alignment of the check valve and manifold) on the yellow
and blue high pressure manifolds, and do all applicable corrective
actions; in accordance with the instructions of paragraph 4.1.2 of
Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009 (for
Model A330-200 and -300 series airplanes); or AOT A340-29A4086,
Revision 1, dated October 8, 2009 (for Model A340-200 and -300
series airplanes). Do all applicable corrective actions before
further flight.
(iii) Within 900 flight hours after accomplishment of paragraph
(g)(2)(ii) of this AD, and thereafter at intervals not to exceed 900
flight hours, do the inspection program (detailed inspection for
traces of seepage or black deposits, and detailed inspection to
determine alignment of the check valve and manifold) on the green,
yellow, and blue high pressure manifolds, and do all applicable
corrective actions, in accordance with the instructions of paragraph
4.1.3 of Airbus AOT A330-29A3111, Revision 1, dated October 8, 2009
(for Model A330-200 and -300 series airplanes); or AOT A340-29A4086,
Revision 1, dated October 8, 2009 (for Model A340-200 and -300
series airplanes). Do all applicable corrective actions before
further flight.
(iv) Actions accomplished before the effective date of this AD,
according to Airbus AOT A330-29A3111, dated September 2, 2009 (for
Model A330-200 and -300 series airplanes); or AOT A340-29A4086,
dated September 2, 2009 (for Model A340-200 and -300 series
airplanes); are considered acceptable for compliance with the
corresponding actions specified in paragraph (g)(2)(i) of this AD.
(3) Within 10 days after accomplishment of the inspections
specified in paragraphs (g)(1) and (g)(2) of this AD, or within 10
days after the effective date of this AD, whichever occurs later,
report all inspection results to Airbus in accordance with Airbus
AOT A330-29A3111, Revision 1, dated October 8, 2009 (for Model A330-
200 and -300 series airplanes); or AOT A340-29A4086, Revision 1,
dated October 8, 2009 (for Model A340-200 and -300 series
airplanes).
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(h) 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:
Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your
[[Page 62211]]
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
(i) Refer to MCAI European Aviation Safety Agency Emergency
Airworthiness Directive 2009-0223-E, dated October 13, 2009; and
Airbus AOTs A330-29A3111 and A340-29A4086, both Revision 1, both
dated October 8, 2009; for related information.
Material Incorporated by Reference
(j) You must use Airbus All Operators Telex A330-29A3111,
Revision 1, dated October 8, 2009; or Airbus All Operators Telex
A340-29A4086, Revision 1, dated October 8, 2009; as applicable; to
do the actions required by this AD, unless the AD specifies
otherwise. (Only the first page of these documents contains the
document number, revision level, and date; no other page of these
documents contain this information.)
(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--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80, e-mail airworthiness.A330-A340@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 November 16, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-28069 Filed 11-25-09; 8:45 am]
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