Airworthiness Directives; Airbus Model A310 Series Airplanes, 51386-51388 [E7-17686]
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51386
Federal Register / Vol. 72, No. 173 / Friday, September 7, 2007 / Proposed Rules
Previous Credit
DEPARTMENT OF TRANSPORTATION
(i) If you performed the actions specified
in paragraphs (f) through (h) of this AD, using
the inspection procedures in GE SB No.
CF34–8C–AL S/B 73–0030, dated May 25,
2007, SB No. CF34–8E–AL S/B 73–0015,
dated June 1, 2007, or SB No. CF34–10E S/
B 72–0067, dated June 7, 2007, before the
effective date of this AD, you have satisfied
the compliance requirements of this AD.
Reporting Requirements
(j) At the applicable time specified in
paragraph (j)(4) or (j)(5) of this AD:
(1) Submit a report of all findings (both
positive and negative) of the testing required
by paragraph (f) of this AD to Customer
Support Manager, Woodward Governor
Company, e-mail:
Jim.Akers@Woodward.com; telephone (815)
639–5365.
(2) The report must include date of
inspection, serial number of FMU, and
results of the inspection.
(3) 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 contained in this AD and has
assigned OMB Control Number 2120–0056.
(4) If the inspection is done after the
effective date of this AD, submit the report
within 10 days after the inspection.
(5) If the inspection was done before the
effective date of this AD, submit the report
within 10 days after the effective date of this
AD.
Alternative Methods of Compliance
(k) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(l) None.
(m) Contact Tara Chaidez, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: tara.chaidez@faa.gov;
telephone (781) 238–7773; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
August 28, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–17680 Filed 9–6–07; 8:45 am]
pwalker on PROD1PC71 with PROPOSALS
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29117; Directorate
Identifier 2007–NM–114–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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:
As a result of a Wide Spread Fatigue
Damage (WFD) calculation on A310 aircraft
it was found that a modification of the upper
fuselage circumferential joint at FR (frame)
55/58 is necessary to enable the aircraft to
reach the Extended Service Goal (ESG).
The unsafe condition is failure of the
circumferential joint of the upper
fuselage, which could result in reduced
structural integrity of the airplane. 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 9, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• 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: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Operations office
VerDate Aug<31>2005
19:35 Sep 06, 2007
Jkt 211001
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Sfmt 4702
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.
Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1622;
fax (425) 227–1149.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
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–2007–29117; Directorate Identifier
2007–NM–114–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://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
E:\FR\FM\07SEP1.SGM
07SEP1
Federal Register / Vol. 72, No. 173 / Friday, September 7, 2007 / Proposed Rules
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 2007–0111,
dated April 25, 2007 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
As a result of a Wide Spread Fatigue
Damage (WFD) calculation on A310 aircraft
it was found that a modification of the upper
fuselage circumferential joint at FR (frame)
55/58 is necessary to enable the aircraft to
reach the Extended Service Goal (ESG).
As a consequence, this Airworthiness
Directive (AD) requires the reinforcement of
the affected fuselage frame butt joint.
The unsafe condition is failure of the
circumferential joint of the upper
fuselage, which could result in reduced
structural integrity of the airplane. You
may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin
A310–53–2125, including Appendix 01,
dated January 9, 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
VerDate Aug<31>2005
19:35 Sep 06, 2007
Jkt 211001
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 67 products of U.S. registry.
We also estimate that it would take
about 330 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 $3,016 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
$1,970,872, or $29,416 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
PO 00000
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51387
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2007–29117;
Directorate Identifier 2007–NM–114–AD.
Comments Due Date
(a) We must receive comments by October
9, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310
series airplanes, certificated in any category;
all certified models; all serial numbers;
except airplanes that have received in-service
application of Airbus Service Bulletin A310–
53–2125.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
As a result of a Wide Spread Fatigue
Damage (WFD) calculation on A310 aircraft
it was found that a modification of the upper
fuselage circumferential joint at FR (frame)
55/58 is necessary to enable the aircraft to
reach the Extended Service Goal (ESG).
As a consequence, this Airworthiness
Directive (AD) requires the reinforcement of
the affected fuselage frame butt joint.
The unsafe condition is failure of the
circumferential joint of the upper fuselage,
which could result in reduced structural
integrity of the airplane.
Actions and Compliance
(f) Unless already done, do the following
actions: Reinforce the fuselage butt joint at
FR 55/58 in accordance with the
accomplishment instructions of Airbus
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07SEP1
51388
Federal Register / Vol. 72, No. 173 / Friday, September 7, 2007 / Proposed Rules
Service Bulletin A310–53–2125, including
Appendix 01, dated January 9, 2007, at the
applicable compliance times listed in Table
1 (threshold) or Table 2 (grace period) of this
AD, whichever occurs later.
TABLE 1.—COMPLIANCE THRESHOLDS
Whichever occurs first after the effective date of this AD
Airbus model
Accumulated time since
first flight (in flight cycles)
A310–200 .........................................................................................................................
A310–300 with an average flight time (AFT) ≤ to 4 hours ..............................................
A310–300 with an AFT > 4 hours ....................................................................................
Accumulated time since
first flight (in flight hours)
41,500
33,000
20,500
83,500
93,500
102,000
TABLE 2.—GRACE PERIODS
Whichever occurs first after the
effective date of this AD
Airbus model
Flight cycles
A310–200 .........................................................................................................................................................
A310–300 with an average flight time (AFT) ≤ 4 hours ..................................................................................
A310–300 with an AFT > 4 hours ....................................................................................................................
FAA AD Differences
pwalker on PROD1PC71 with PROPOSALS
Note: This AD differs from the MCAI and/
or service information as follows:
No differences.
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: Tom Stafford,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1622; 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 European Aviation
Safety Agency Airworthiness Directive 2007–
0111, dated April 25, 2007; and Airbus
Service Bulletin A310–53–2125, dated
January 9, 2007; for related information.
VerDate Aug<31>2005
19:35 Sep 06, 2007
Jkt 211001
Issued in Renton, Washington, on August
28, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–17686 Filed 9–6–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28413; Directorate
Identifier 2007–NE–25–AD]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80C2 and
CF6–80E1 Series Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for GE
CF6–80C2 and CF6–80E1 series
turbofan engines with fuel manifold part
numbers (P/Ns) 1303M31G12 and
1303M32G12 installed. This proposed
AD would require removing and
discarding the loop clamps that
assemble the fuel manifold to the
compressor rear frame (CRF) friction
damper brackets, visually inspecting the
fuel manifold for wear at each clamp
location, and replacing the clamps with
new, zero-time parts. This proposed AD
results from fuel manifold vibration
PO 00000
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Fmt 4702
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1,500
1,200
740
Flight hours
3,000
3,400
3,600
during engine operation that causes the
loop clamps that assemble the manifold
to the CRF to deteriorate. Fourteen fuel
leak events occurred over the past
several years. We are proposing this AD
to prevent fuel leaks during engine
operation that could result in an undercowl fire.
DATES: We must receive any comments
on this proposed AD by November 6,
2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
You may examine the comments on
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov., or in
Room W12–140 on the ground floor of
the West Building, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
E:\FR\FM\07SEP1.SGM
07SEP1
]]>Agencies
[Federal Register Volume 72, Number 173 (Friday, September 7, 2007)]
[Proposed Rules]
[Pages 51386-51388]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-17686]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29117; Directorate Identifier 2007-NM-114-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series 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:
As a result of a Wide Spread Fatigue Damage (WFD) calculation on
A310 aircraft it was found that a modification of the upper fuselage
circumferential joint at FR (frame) 55/58 is necessary to enable the
aircraft to reach the Extended Service Goal (ESG).
The unsafe condition is failure of the circumferential joint of the
upper fuselage, which could result in reduced structural integrity of
the airplane. 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 9, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
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: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.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: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
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-2007-
29117; Directorate Identifier 2007-NM-114-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://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
[[Page 51387]]
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 2007-0111, dated April 25, 2007 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
As a result of a Wide Spread Fatigue Damage (WFD) calculation on
A310 aircraft it was found that a modification of the upper fuselage
circumferential joint at FR (frame) 55/58 is necessary to enable the
aircraft to reach the Extended Service Goal (ESG).
As a consequence, this Airworthiness Directive (AD) requires the
reinforcement of the affected fuselage frame butt joint.
The unsafe condition is failure of the circumferential joint of the
upper fuselage, which could result in reduced structural integrity of
the airplane. You may obtain further information by examining the MCAI
in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin A310-53-2125, including Appendix
01, dated January 9, 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 67 products of U.S. registry. We also estimate that
it would take about 330 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 $3,016 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 $1,970,872, or $29,416 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-2007-29117; Directorate Identifier 2007-NM-
114-AD.
Comments Due Date
(a) We must receive comments by October 9, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310 series airplanes,
certificated in any category; all certified models; all serial
numbers; except airplanes that have received in-service application
of Airbus Service Bulletin A310-53-2125.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
As a result of a Wide Spread Fatigue Damage (WFD) calculation on
A310 aircraft it was found that a modification of the upper fuselage
circumferential joint at FR (frame) 55/58 is necessary to enable the
aircraft to reach the Extended Service Goal (ESG).
As a consequence, this Airworthiness Directive (AD) requires the
reinforcement of the affected fuselage frame butt joint.
The unsafe condition is failure of the circumferential joint of
the upper fuselage, which could result in reduced structural
integrity of the airplane.
Actions and Compliance
(f) Unless already done, do the following actions: Reinforce the
fuselage butt joint at FR 55/58 in accordance with the
accomplishment instructions of Airbus
[[Page 51388]]
Service Bulletin A310-53-2125, including Appendix 01, dated January
9, 2007, at the applicable compliance times listed in Table 1
(threshold) or Table 2 (grace period) of this AD, whichever occurs
later.
Table 1.--Compliance Thresholds
----------------------------------------------------------------------------------------------------------------
Whichever occurs first after the effective date of
this AD
-----------------------------------------------------
Airbus model Accumulated time since Accumulated time since
first flight (in flight first flight (in flight
cycles) hours)
----------------------------------------------------------------------------------------------------------------
A310-200.................................................. 41,500 83,500
A310-300 with an average flight time (AFT) <= to 4 hours.. 33,000 93,500
A310-300 with an AFT > 4 hours............................ 20,500 102,000
----------------------------------------------------------------------------------------------------------------
Table 2.--Grace Periods
------------------------------------------------------------------------
Whichever occurs first after the
effective date of this AD
Airbus model -----------------------------------
Flight cycles Flight hours
------------------------------------------------------------------------
A310-200............................ 1,500 3,000
A310-300 with an average flight time 1,200 3,400
(AFT) <= 4 hours...................
A310-300 with an AFT > 4 hours...... 740 3,600
------------------------------------------------------------------------
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows:
No differences.
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: Tom
Stafford, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1622; 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 European Aviation Safety Agency Airworthiness
Directive 2007-0111, dated April 25, 2007; and Airbus Service
Bulletin A310-53-2125, dated January 9, 2007; for related
information.
Issued in Renton, Washington, on August 28, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-17686 Filed 9-6-07; 8:45 am]
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