Airworthiness Directives; Airbus Model A300-600 Airplanes, 53768-53770 [E8-21724]
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53768
Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules
FAA AD Differences
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
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: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4145; fax: (816)
329–4090. 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.
(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 European Aviation
Safety Agency (EASA) AD No. 2008–0139,
dated July 24, 2008; Diamond Aircraft
Industries GmbH Mandatory Service Bulletin
No. MSB–42–058, dated May 21, 2008; and
Diamond Aircraft Industries GmbH Work
Instruction WI–MSB–42–058, dated March
12, 2008, for related information.
Issued in Kansas City, Missouri, on
September 10, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–21701 Filed 9–16–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
pwalker on PROD1PC71 with PROPOSALS
[Docket No. FAA–2008–0979; Directorate
Identifier 2008–NM–079–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300–600 Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
VerDate Aug<31>2005
17:08 Sep 16, 2008
Notice of proposed rulemaking
(NPRM).
ACTION:
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Jkt 214001
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Further to initial qualification tests of the
spoiler actuators currently installed in
position No. 3 to 7 on A300–600 and A300–
600ST aircraft fleet, a life limit [of 55,750
flight hours] has been defined by the actuator
manufacturer. Initially, this life limit had no
repercussions, as it was situated well beyond
the initial Design Service Goal (DSG) of the
aircraft. However, due to the Extended
Service Goal (ESG) activities, the spoiler
actuator life limit can be reached in service,
and therefore the spoiler actuators must be
replaced before exceeding this limit.
In order to mitigate the risk to have aircraft
on which the three hydraulic circuits would
be impacted by affected spoiler actuators,
which could result in the loss of
controllability of the aircraft, this
Airworthiness Directive (AD) requires actions
to ensure that at least the level of safety of
one hydraulic circuit will be restored within
an acceptable timeframe.
*
*
*
*
*
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by October 17, 2008.
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
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.
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.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0979; Directorate Identifier
2008–NM–079–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2008–0058,
dated March 20, 2008 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Further to initial qualification tests of the
spoiler actuators currently installed in
position No. 3 to 7 on A300–600 and A300–
600ST aircraft fleet, a life limit [of 55,750
flight hours] has been defined by the actuator
manufacturer. Initially, this life limit had no
repercussions, as it was situated well beyond
the initial Design Service Goal (DSG) of the
aircraft. However, due to the Extended
Service Goal (ESG) activities, the spoiler
actuator life limit can be reached in service,
and therefore the spoiler actuators must be
replaced before exceeding this limit.
In order to mitigate the risk to have aircraft
on which the three hydraulic circuits would
be impacted by affected spoiler actuators,
which could result in the loss of
controllability of the aircraft, this
Airworthiness Directive (AD) requires actions
to ensure that at least the level of safety of
one hydraulic circuit will be restored within
an acceptable timeframe.
E:\FR\FM\17SEP1.SGM
17SEP1
Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules
EASA AD 2007–0245, issued on 05
September 2007 as an interim action, is
superseded by the present [EASA] AD.
Corrective actions include replacing the
spoiler actuator with a serviceable unit.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletins
A300–27–6060, including Appendix 01,
dated February 18, 2008, and A300–
27A6062, including Appendix 01, dated
July 6, 2007. 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 Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
pwalker on PROD1PC71 with PROPOSALS
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 proposed
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
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 135 products of U.S.
registry. We also estimate that it would
take about 8 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Required
parts would cost about $32,000 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
VerDate Aug<31>2005
17:08 Sep 16, 2008
Jkt 214001
these costs. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$4,406,400, or $32,640 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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); 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 proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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Fmt 4702
Sfmt 4702
53769
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2008–0979;
Directorate Identifier 2008–NM–079–AD.
Comments Due Date
(a) We must receive comments by October
17, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300–
600 airplanes, all serial numbers, certificated
in any category; on which Smith spoiler
actuators having part number (P/N)
P376A0002–05, –06, –07, or –09, or P/N
P725A0001–00 are installed.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Further to initial qualification tests of the
spoiler actuators currently installed in
position No. 3 to 7 on A300–600 and A300–
600ST aircraft fleet, a life limit [of 55,750
flight hours] has been defined by the actuator
manufacturer. Initially, this life limit had no
repercussions, as it was situated well beyond
the initial Design Service Goal (DSG) of the
aircraft. However, due to the Extended
Service Goal (ESG) activities, the spoiler
actuator life limit can be reached in service,
and therefore the spoiler actuators must be
replaced before exceeding this limit.
In order to mitigate the risk to have aircraft
on which the three hydraulic circuits would
be impacted by affected spoiler actuators,
which could result in the loss of
controllability of the aircraft, this
Airworthiness Directive (AD) requires actions
to ensure that at least the level of safety of
one hydraulic circuit will be restored within
an acceptable timeframe.
EASA AD 2007–0245, issued on 05
September 2007 as an interim action, is
superseded by the present [EASA] AD.
Corrective actions include replacing the
spoiler actuator with a serviceable unit.
Actions and Compliance
(f) Unless already done: Within 700 flight
hours after the effective date of this AD, do
the following actions.
(1) Identify the total flight hours
accumulated on each spoiler actuator at
positions 3 through 7 on the left- and righthand sides of the airplane (FIN 22CP/23CP,
24CP/25CP, 26CP/27CP, 60CP/61CP and
E:\FR\FM\17SEP1.SGM
17SEP1
53770
Federal Register / Vol. 73, No. 181 / Wednesday, September 17, 2008 / Proposed Rules
62CP/63CP), in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–27A6062, dated July
6, 2007.
(2) For airplanes on which the status of any
spoiler actuator is unknown (unknown
number of accumulated flight hours,
unknown date of manufacture and/or
unknown serial number) the actuator must be
considered as having exceeded 55,750 total
flight hours.
(3) For airplanes on which all three
hydraulic circuits have a spoiler actuator that
has accumulated or exceeds 55,000 total
flight hours: Before the accumulation of
55,750 total flight hours or within 700 flight
hours after the effective date of this AD,
whichever occurs later, on at least one
hydraulic circuit, interchange the spoiler
actuator with a serviceable unit from another
hydraulic circuit, or replace the spoiler
actuator with a serviceable unit, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
27–6060, dated February 18, 2008.
(4) For airplanes on which the actions
required by paragraph (f)(1) of this AD, and,
as applicable, paragraph (f)(3) of this AD
have been accomplished, each airplane must
continue to have at least one hydraulic
circuit fitted with spoiler actuators that do
not exceed 55,750 total flight hours.
Note 1: For the purposes of this AD, a
serviceable unit is a unit that has
accumulated less than 55,750 flight hours.
(5) The operator must not interchange or
replace spoiler actuators on more than two
hydraulic circuits at the same time. This will
mitigate the risk of having a malfunction on
the three hydraulic systems at the same time.
pwalker on PROD1PC71 with PROPOSALS
Note 2: This AD differs from the MCAI
and/or service information as follows:
(1) This AD does not include the reporting
requirement specified in paragraph (1) of the
MCAI. The MCAI carried this requirement
forward from European Aviation Safety
Agency (EASA) Airworthiness Directive
2007–0245, dated September 5, 2007. We
previously determined that no action was
required on our part regarding EASA AD
2007–0245.
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
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
17:08 Sep 16, 2008
Jkt 214001
[Docket No. FAA–2008–0980; Directorate
Identifier 2008–NM–008–AD]
inspection to determine if certain
fasteners are broken or cracked, and
corrective actions if necessary. This
proposed AD results from a report that
incorrect torque values could damage
the bracket. We are proposing this AD
to prevent a cracked bracket. Failure of
this bracket, combined with failure of
the horizontal beam, could result in
collapse of the left part of the flight deck
instrument panel, and consequent
reduced controllability of the airplane.
DATES: We must receive comments on
this proposed AD by October 17, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
RIN 2120–AA64
FAA AD Differences
VerDate Aug<31>2005
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,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Examining the AD Docket
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2008–0058, dated March 20, 2008;
and Airbus Service Bulletins A300–27–6060,
dated February 18, 2008; and A300–
27A6062, dated July 6, 2007; for related
information.
Issued in Renton, Washington, on
September 9, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–21724 Filed 9–16–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Airbus Model
A330 Airplanes, and Model A340–200
and A340–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Airbus Model A330, A340–200, and
A340–300 series airplanes. The existing
AD currently requires repetitive
inspections of a certain bracket that
attaches the flight deck instrument
panel to the airplane structure; related
investigative and corrective actions if
necessary; and replacement of the
existing bracket with a titaniumreinforced bracket, which ends the
repetitive inspections in the existing
AD. This proposed AD would add
requirements only for airplanes on
which the existing bracket was replaced
with a titanium-reinforced bracket in
accordance with the existing AD. The
additional requirement is a one-time
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0980; Directorate Identifier
E:\FR\FM\17SEP1.SGM
17SEP1
]]>Agencies
[Federal Register Volume 73, Number 181 (Wednesday, September 17, 2008)]
[Proposed Rules]
[Pages 53768-53770]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-21724]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0979; Directorate Identifier 2008-NM-079-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300-600 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
Further to initial qualification tests of the spoiler actuators
currently installed in position No. 3 to 7 on A300-600 and A300-
600ST aircraft fleet, a life limit [of 55,750 flight hours] has been
defined by the actuator manufacturer. Initially, this life limit had
no repercussions, as it was situated well beyond the initial Design
Service Goal (DSG) of the aircraft. However, due to the Extended
Service Goal (ESG) activities, the spoiler actuator life limit can
be reached in service, and therefore the spoiler actuators must be
replaced before exceeding this limit.
In order to mitigate the risk to have aircraft on which the
three hydraulic circuits would be impacted by affected spoiler
actuators, which could result in the loss of controllability of the
aircraft, this Airworthiness Directive (AD) requires actions to
ensure that at least the level of safety of one hydraulic circuit
will be restored within an acceptable timeframe.
* * * * *
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by October 17,
2008.
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 proposed 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: 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0979;
Directorate Identifier 2008-NM-079-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2008-0058, dated March 20, 2008 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Further to initial qualification tests of the spoiler actuators
currently installed in position No. 3 to 7 on A300-600 and A300-
600ST aircraft fleet, a life limit [of 55,750 flight hours] has been
defined by the actuator manufacturer. Initially, this life limit had
no repercussions, as it was situated well beyond the initial Design
Service Goal (DSG) of the aircraft. However, due to the Extended
Service Goal (ESG) activities, the spoiler actuator life limit can
be reached in service, and therefore the spoiler actuators must be
replaced before exceeding this limit.
In order to mitigate the risk to have aircraft on which the
three hydraulic circuits would be impacted by affected spoiler
actuators, which could result in the loss of controllability of the
aircraft, this Airworthiness Directive (AD) requires actions to
ensure that at least the level of safety of one hydraulic circuit
will be restored within an acceptable timeframe.
[[Page 53769]]
EASA AD 2007-0245, issued on 05 September 2007 as an interim
action, is superseded by the present [EASA] AD.
Corrective actions include replacing the spoiler actuator with a
serviceable unit. You may obtain further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletins A300-27-6060, including
Appendix 01, dated February 18, 2008, and A300-27A6062, including
Appendix 01, dated July 6, 2007. 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 Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
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 proposed 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 proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 135 products of U.S. registry. We also estimate that
it would take about 8 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Required parts would cost about $32,000 per product. Where
the service information lists required parts costs that are covered
under warranty, we have assumed that there will be no charge for these
costs. As we do not control warranty coverage for affected parties,
some parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $4,406,400, or $32,640 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); 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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2008-0979; Directorate Identifier 2008-NM-
079-AD.
Comments Due Date
(a) We must receive comments by October 17, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300-600 airplanes, all
serial numbers, certificated in any category; on which Smith spoiler
actuators having part number (P/N) P376A0002-05, -06, -07, or -09,
or P/N P725A0001-00 are installed.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Further to initial qualification tests of the spoiler actuators
currently installed in position No. 3 to 7 on A300-600 and A300-
600ST aircraft fleet, a life limit [of 55,750 flight hours] has been
defined by the actuator manufacturer. Initially, this life limit had
no repercussions, as it was situated well beyond the initial Design
Service Goal (DSG) of the aircraft. However, due to the Extended
Service Goal (ESG) activities, the spoiler actuator life limit can
be reached in service, and therefore the spoiler actuators must be
replaced before exceeding this limit.
In order to mitigate the risk to have aircraft on which the
three hydraulic circuits would be impacted by affected spoiler
actuators, which could result in the loss of controllability of the
aircraft, this Airworthiness Directive (AD) requires actions to
ensure that at least the level of safety of one hydraulic circuit
will be restored within an acceptable timeframe.
EASA AD 2007-0245, issued on 05 September 2007 as an interim
action, is superseded by the present [EASA] AD.
Corrective actions include replacing the spoiler actuator with a
serviceable unit.
Actions and Compliance
(f) Unless already done: Within 700 flight hours after the
effective date of this AD, do the following actions.
(1) Identify the total flight hours accumulated on each spoiler
actuator at positions 3 through 7 on the left- and right-hand sides
of the airplane (FIN 22CP/23CP, 24CP/25CP, 26CP/27CP, 60CP/61CP and
[[Page 53770]]
62CP/63CP), in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-27A6062, dated July 6, 2007.
(2) For airplanes on which the status of any spoiler actuator is
unknown (unknown number of accumulated flight hours, unknown date of
manufacture and/or unknown serial number) the actuator must be
considered as having exceeded 55,750 total flight hours.
(3) For airplanes on which all three hydraulic circuits have a
spoiler actuator that has accumulated or exceeds 55,000 total flight
hours: Before the accumulation of 55,750 total flight hours or
within 700 flight hours after the effective date of this AD,
whichever occurs later, on at least one hydraulic circuit,
interchange the spoiler actuator with a serviceable unit from
another hydraulic circuit, or replace the spoiler actuator with a
serviceable unit, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-27-6060, dated February 18, 2008.
(4) For airplanes on which the actions required by paragraph
(f)(1) of this AD, and, as applicable, paragraph (f)(3) of this AD
have been accomplished, each airplane must continue to have at least
one hydraulic circuit fitted with spoiler actuators that do not
exceed 55,750 total flight hours.
Note 1: For the purposes of this AD, a serviceable unit is a
unit that has accumulated less than 55,750 flight hours.
(5) The operator must not interchange or replace spoiler
actuators on more than two hydraulic circuits at the same time. This
will mitigate the risk of having a malfunction on the three
hydraulic systems at the same time.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows:
(1) This AD does not include the reporting requirement specified
in paragraph (1) of the MCAI. The MCAI carried this requirement
forward from European Aviation Safety Agency (EASA) Airworthiness
Directive 2007-0245, dated September 5, 2007. We previously
determined that no action was required on our part regarding EASA AD
2007-0245.
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 appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
(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, 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 2008-0058, dated
March 20, 2008; and Airbus Service Bulletins A300-27-6060, dated
February 18, 2008; and A300-27A6062, dated July 6, 2007; for related
information.
Issued in Renton, Washington, on September 9, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-21724 Filed 9-16-08; 8:45 am]
BILLING CODE 4910-13-P
