Airworthiness Directives; Airbus Model A310 and A300-600 Series Airplanes, 3656-3659 [E8-977]
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<![CDATA[
3656
Federal Register / Vol. 73, No. 14 / Tuesday, January 22, 2008 / Proposed Rules
Engine
maximum empty weight defined in
Paragraph 3.1.2 of ASTM F2245–07.
Engine
The engine may not have its own type
certificate; in such case it will be
included in the airplane type certificate
using the following as a proposed
certification basis:
1. ASTM F2339–06, ‘‘Standard
Practice for Design and Manufacture of
Reciprocating Spark Ignition Engines for
Light Sport Aircraft,’’ modified as
follows: Engine parts and assemblies
will be manufactured under the purview
of a production certificate held by the
applicant. Section 7 of ASTM F2339–06
does not apply.
2. Optionally, the applicant may elect
to use a type certificated engine up to
180 horsepower.
Propeller
A type certificated propeller will be
used.
Proposed Airworthiness Standards for
Acceptance Under the Primary
Category Rule
The FAA is requiring use of the part
23 rules in addition to the Light Sport
Airplane Consensus Standards. The
applicant has agreed to this position;
therefore, the certification basis for the
Cubcrafters, Inc., Model PC18–160 will
be the Primary Category Rule (part 21,
§ 21.24) with Amendment 23–57 for 14
CFR, part 23, §§ 23.853(a); 23.863;
23.1303(a), (b), and (c); 23.1311(a)(1)
through (a)(4), and (b); 23.1321; 23.1322;
23.1329 and 23.1359 and:
The engine may not have its own type
certificate; in such case it will be
included in the airplane type certificate
using the following as a proposed
certification basis:
1. ASTM F2339–06, ‘‘Standard
Practice for Design and Manufacture of
Reciprocating Spark Ignition Engines for
Light Sport Aircraft,’’ modified as
follows: Engine parts and assemblies
will be manufactured under the purview
of a production certificate held by the
applicant. Section 7 of ASTM F2339–06
does not apply.
2. Optionally, the applicant may elect
to use a type certificated engine up to
180 horsepower.
Propeller
A type certificated propeller will be
used.
In addition to the applicable
airworthiness regulations, the PC18–160
must comply with the fuel vent and
exhaust emission requirements of 14
CFR part 34 and the noise certification
requirements of 14 CFR part 36; and the
FAA must issue a finding of regulatory
adequacy pursuant to section 611 of
Public Law 92–574, the ‘‘Noise Control
Act of 1972.’’
Issued in Kansas City, Missouri on January
11, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–852 Filed 1–18–08; 8:45 am]
BILLING CODE 4910–13–P
yshivers on PROD1PC62 with PROPOSALS
Airframe and Systems
DEPARTMENT OF TRANSPORTATION
ASTM F2245–07, ‘‘Standard
Specification for Design and
Performance of a Light Sport Airplane,’’
modified as follows:
1. Federal Aviation Regulations 23
Loads Report and Test Proposal to be
reviewed and approved by ACO.
Specifically, Section 5 of ASTM F2245–
07 is replaced by Federal Aviation
Regulations part 23, §§ 23.301 through
23.561 (latest amendments through
Amendment 23–55) as applicable to this
airplane.
2. All major structural components
will be tested as per the approved Test
Proposal (this eliminates ‘‘analysis’’
allowed by ASTM).
3. Paragraph 4.2.1 of ASTM F2245–07
is replaced by Federal Aviation
Regulations part 23, § 23.25(b) except
that the empty weight referred to in
Federal Aviation Regulations part 23,
§ 23.25(b)(1) is replaced by the
maximum empty weight defined in
Paragraph 3.1.2 of ASTM F2245–07.
Federal Aviation Administration
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14:53 Jan 18, 2008
Jkt 214001
14 CFR Part 39
[Docket No. FAA–2008–0048; Directorate
Identifier 2007–NM–276–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 and A300–600 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. 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
SUMMARY:
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aviation product. The MCAI describes
the unsafe condition as:
Based on some recent in-service findings
for fluid ingress and/or inner skin disbond
damage on rudders, AIRBUS decided to
introduce some further structural inspections
to specific rudder areas. This type of damage
could result in reduced structural integrity of
the rudder.
*
*
*
*
*
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 February 21, 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: 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.
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–2008–0048; Directorate Identifier
2007–NM–276–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
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Federal Register / Vol. 73, No. 14 / Tuesday, January 22, 2008 / Proposed Rules
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
On March 24, 2006, we issued AD
2006–07–13, Amendment 39–14540 (71
FR 16030, March 30, 2006), to require
one-time inspections of the rudder for
discrepancies, and corrective action if
necessary. That AD required actions
intended to address an unsafe condition
on the products listed above.
Since we issued AD 2006–07–13, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2007–0266,
dated October 8, 2007 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
yshivers on PROD1PC62 with PROPOSALS
Based on some recent in-service findings
for fluid ingress and/or inner skin disbond
damage on rudders, AIRBUS decided to
introduce some further structural inspections
to specific rudder areas. This type of damage
could result in reduced structural integrity of
the rudder.
For the reasons stated above, this AD
requires the accomplishment of a thorough
inspection program [a one-time inspection
and repetitive inspections for damage of the
rudder] by ultrasonic and/or t[h]ermographic
methods, compared to the inspections
already required by Airworthiness Directive
(AD) 2006–0066, issued on 24 March 2006
[which corresponds to FAA AD 2006–07–13]
as a precautionary measure, in order to verify
the structural integrity of the rudder.
*
*
*
*
*
The corrective actions include reporting
both positive and negative findings to
Airbus, doing a temporary repair, and
contacting Airbus for repair instructions
and doing a permanent repair. The
compliance times for doing the repairs
range from before further flight to
within 4,500 flight cycles after doing the
inspection, depending on the inspection
type and the configuration of the
airplane. The repetitive inspection
intervals range from 1,200 flight cycles
to 5,000 flight cycles, depending on the
inspection type and the configuration of
the airplane. You may obtain further
information by examining the MCAI in
the AD docket.
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Jkt 214001
Relevant Service Information
Airbus has issued the following
service bulletins:
• A300–55–6043, Revision 01, dated
December 3, 2007
• A300–55–6044, Revision 01, dated
December 20, 2007
• A310–55–2044, Revision 01, dated
December 3, 2007
• A310–55–2045, Revision 01, dated
December 20, 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 123 products of U.S.
registry. We also estimate that it would
take about 22 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$216,480, or $1,760 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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3657
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14540 (71 FR
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Federal Register / Vol. 73, No. 14 / Tuesday, January 22, 2008 / Proposed Rules
16030, March 30, 2006) and adding the
following new AD:
Airbus: Docket No. FAA–2008–0048;
Directorate Identifier 2007–NM–276–AD.
Comments Due Date
(a) We must receive comments by February
21, 2008.
Affected ADs
(b) The proposed AD supersedes AD 2006–
07–13, Amendment 39–14540.
Applicability
(c) This AD applies to AIRBUS Model
A310 and A300–600 series airplanes,
certificated in any category, all certified
models, all serial numbers, on which rudder
Part Number (P/N) A55471500 series is fitted,
except for those airplanes on which AIRBUS
modification number 08827 has been
incorporated in production.
Subject
(d) Air Transport Association (ATA) of
America Code 55: Stabilizers.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Based on some recent in-service findings
for fluid ingress and/or inner skin disbond
damage on rudders, AIRBUS decided to
introduce some further structural inspections
to specific rudder areas. This type of damage
could result in reduced structural integrity of
the rudder.
For the reasons stated above, this AD
requires the accomplishment of a thorough
inspection program [a one-time inspection
and repetitive inspections for damage of the
rudder] by ultrasonic and/or t[h]ermographic
methods, compared to the inspections
already required by Airworthiness Directive
(AD) 2006–0066, issued on 24 March 2006
[which corresponds to FAA AD 2006–07–13]
as a precautionary measure, in order to verify
the structural integrity of the rudder.
*
*
*
*
*
yshivers on PROD1PC62 with PROPOSALS
The corrective actions include reporting both
positive and negative findings to Airbus,
doing a temporary repair, and contacting
Airbus for repair and doing a permanent
repair.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 500 flight cycles or 6 months
after the effective date of this AD, whichever
occurs first, perform a special detailed onetime inspection in the areas of rudder
hoisting points and trailing edge screws, in
accordance with the instructions given in
Airbus Service Bulletin A310–55–2045 or
A300–55–6044, both Revision 01, both dated
December 20, 2007, as applicable.
(i) If no damage is found, within 30 days
after the inspection or 30 days after the
effective date of this AD, whichever occurs
later, report to Airbus using Appendix 1 or
2, as applicable to the airplane configuration,
of Airbus Service Bulletin A310–55–2045 or
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14:53 Jan 18, 2008
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A300–55–6044, both Revision 01, as
applicable.
(ii) If any damage is found, within the
timescale(s) indicated in Airbus Service
Bulletin A310–55–2045 or A300–55–6044,
both Revision 01, as applicable, report to
Airbus using Appendix 1 or 2, as applicable
to the airplane configuration, of Airbus
Service Bulletin A310–55–2045 or A300–55–
6044, both Revision 01, as applicable, to get
further instructions for repair. Accomplish
the repair within the timescale(s) indicated
in, and in accordance with the instructions
given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as
applicable to the airplane configuration, of
Airbus Service Bulletin A310–55–2045 or
A300–55–6044, both Revision 01, as
applicable.
(2) Within 500 flight cycles or 6 months
after the effective date of this AD, whichever
occurs first, perform a special detailed
inspection along the rudder Z-profile, in
accordance with the instructions given in
Airbus Service Bulletin A310–55–2044 or
A300–55–6043, both Revision 01, both dated
December 3, 2007, as applicable. For
airplanes identified as configuration 01 in the
service bulletins, repeat the inspection
thereafter at intervals not to exceed 1,400
flight cycles. For airplanes identified as
Configuration 02 in the service bulletins,
repeat the inspection thereafter at intervals
not to exceed 5,000 flight cycles. For
temporary repair along the rudder Z-profile
for both airplanes identified as configuration
01 and 02, refer to paragraph 3.C.(1) of
Airbus Service Bulletin A310–55–2044 or
A300–55–6043, both Revision 01, as
applicable.
(i) If no damage is found, within 30 days
after the inspection or 30 days after the
effective date of this AD, whichever occurs
later, report to AIRBUS using Appendix 1 or
2, as applicable to the airplane configuration,
of Airbus Service Bulletin A310–55–2044 or
A300–55–6043, both Revision 01, as
applicable.
(ii) If any damage is found, verify the
findings and apply all applicable corrective
actions within the timescale(s) indicated in,
and in accordance with instructions given in
paragraph 3.B.(1)(a) or 3.B.(2)(a), as
applicable to the airplane configuration, of
Airbus Service Bulletin A310–55–2044 or
A300–55–6043, both Revision 01, as
applicable. Within 30 days after the
inspection or corrective action or 30 days
after the effective date of this AD, whichever
occurs later, submit a report to Airbus using
Appendix 1 or 2, as applicable to the airplane
configuration, of Airbus Service Bulletin
A310–55–2044 or A300–55–6043, both
Revision 01, as applicable.
Note 1: For rudder configuration
identification, refer to Appendices 3 and 4 of
Airbus Service Bulletin A310–55–2044,
A310–55–2045, A300–55–6043, and A300–
55–6044, as applicable to the airplane model
and configuration.
(3) As of 30 days after the effective date of
this AD: No person shall install a P/N
A55471500 series rudder on any airplane as
a replacement, unless it has been inspected
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and repaired, as applicable, in accordance
with the instructions of Airbus Service
Bulletins A310–55–2045, Revision 01, dated
December 20, 2007, and A310–55–2044,
Revision 01, dated December 3, 2007; or
Airbus Service Bulletins A300–55–6044,
Revision 01, dated December 20, 2007, and
A300–55–6043, Revision 01, dated December
3, 2007; as applicable.
(4) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A300–55–6044 or
A310–55–2045, both dated July 23, 2007, are
considered acceptable for compliance with
the corresponding actions specified in
paragraph (f)(1) of this AD.
(5) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A300–55–6043 or
A310–55–2044, both dated July 23, 2007, are
considered acceptable for compliance with
the corresponding actions specified in
paragraph (f)(2) of this AD.
FAA AD Differences
Note 2: 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 EASA Airworthiness
Directive 2007–0266, dated October 8, 2007,
and the service bulletins listed in Table 1 of
this AD, for related information.
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Federal Register / Vol. 73, No. 14 / Tuesday, January 22, 2008 / Proposed Rules
TABLE 1.—AIRBUS SERVICE INFORMATION
Airbus Service Bulletin
A300–55–6043
A300–55–6044
A310–55–2044
A310–55–2045
Revision
.................................................................................................................................................
.................................................................................................................................................
.................................................................................................................................................
.................................................................................................................................................
Issued in Renton, Washington, on January
15, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–977 Filed 1–18–08; 8:45 am]
yshivers on PROD1PC62 with PROPOSALS
BILLING CODE 4910–13–P
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14:53 Jan 18, 2008
Jkt 214001
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E:\FR\FM\22JAP1.SGM
22JAP1
01
01
01
01
Date
December
December
December
December
3, 2007.
20, 2007.
3, 2007.
20, 2007.
]]>Agencies
[Federal Register Volume 73, Number 14 (Tuesday, January 22, 2008)]
[Proposed Rules]
[Pages 3656-3659]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-977]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0048; Directorate Identifier 2007-NM-276-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 and A300-600 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 that would supersede an existing AD. 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:
Based on some recent in-service findings for fluid ingress and/
or inner skin disbond damage on rudders, AIRBUS decided to introduce
some further structural inspections to specific rudder areas. This
type of damage could result in reduced structural integrity of the
rudder.
* * * * *
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 February 21,
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: 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.
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-2008-0048;
Directorate Identifier 2007-NM-276-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
[[Page 3657]]
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
On March 24, 2006, we issued AD 2006-07-13, Amendment 39-14540 (71
FR 16030, March 30, 2006), to require one-time inspections of the
rudder for discrepancies, and corrective action if necessary. That AD
required actions intended to address an unsafe condition on the
products listed above.
Since we issued AD 2006-07-13, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2007-0266,
dated October 8, 2007 (referred to after this as ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
Based on some recent in-service findings for fluid ingress and/
or inner skin disbond damage on rudders, AIRBUS decided to introduce
some further structural inspections to specific rudder areas. This
type of damage could result in reduced structural integrity of the
rudder.
For the reasons stated above, this AD requires the
accomplishment of a thorough inspection program [a one-time
inspection and repetitive inspections for damage of the rudder] by
ultrasonic and/or t[h]ermographic methods, compared to the
inspections already required by Airworthiness Directive (AD) 2006-
0066, issued on 24 March 2006 [which corresponds to FAA AD 2006-07-
13] as a precautionary measure, in order to verify the structural
integrity of the rudder.
* * * * *
The corrective actions include reporting both positive and negative
findings to Airbus, doing a temporary repair, and contacting Airbus for
repair instructions and doing a permanent repair. The compliance times
for doing the repairs range from before further flight to within 4,500
flight cycles after doing the inspection, depending on the inspection
type and the configuration of the airplane. The repetitive inspection
intervals range from 1,200 flight cycles to 5,000 flight cycles,
depending on the inspection type and the configuration of the airplane.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued the following service bulletins:
A300-55-6043, Revision 01, dated December 3, 2007
A300-55-6044, Revision 01, dated December 20, 2007
A310-55-2044, Revision 01, dated December 3, 2007
A310-55-2045, Revision 01, dated December 20, 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 123 products of U.S. registry. We also estimate that
it would take about 22 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $216,480, or $1,760 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 removing Amendment 39-14540 (71 FR
[[Page 3658]]
16030, March 30, 2006) and adding the following new AD:
Airbus: Docket No. FAA-2008-0048; Directorate Identifier 2007-NM-
276-AD.
Comments Due Date
(a) We must receive comments by February 21, 2008.
Affected ADs
(b) The proposed AD supersedes AD 2006-07-13, Amendment 39-
14540.
Applicability
(c) This AD applies to AIRBUS Model A310 and A300-600 series
airplanes, certificated in any category, all certified models, all
serial numbers, on which rudder Part Number (P/N) A55471500 series
is fitted, except for those airplanes on which AIRBUS modification
number 08827 has been incorporated in production.
Subject
(d) Air Transport Association (ATA) of America Code 55:
Stabilizers.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Based on some recent in-service findings for fluid ingress and/
or inner skin disbond damage on rudders, AIRBUS decided to introduce
some further structural inspections to specific rudder areas. This
type of damage could result in reduced structural integrity of the
rudder.
For the reasons stated above, this AD requires the
accomplishment of a thorough inspection program [a one-time
inspection and repetitive inspections for damage of the rudder] by
ultrasonic and/or t[h]ermographic methods, compared to the
inspections already required by Airworthiness Directive (AD) 2006-
0066, issued on 24 March 2006 [which corresponds to FAA AD 2006-07-
13] as a precautionary measure, in order to verify the structural
integrity of the rudder.
* * * * *
The corrective actions include reporting both positive and negative
findings to Airbus, doing a temporary repair, and contacting Airbus
for repair and doing a permanent repair.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 500 flight cycles or 6 months after the effective
date of this AD, whichever occurs first, perform a special detailed
one-time inspection in the areas of rudder hoisting points and
trailing edge screws, in accordance with the instructions given in
Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision
01, both dated December 20, 2007, as applicable.
(i) If no damage is found, within 30 days after the inspection
or 30 days after the effective date of this AD, whichever occurs
later, report to Airbus using Appendix 1 or 2, as applicable to the
airplane configuration, of Airbus Service Bulletin A310-55-2045 or
A300-55-6044, both Revision 01, as applicable.
(ii) If any damage is found, within the timescale(s) indicated
in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both
Revision 01, as applicable, report to Airbus using Appendix 1 or 2,
as applicable to the airplane configuration, of Airbus Service
Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as
applicable, to get further instructions for repair. Accomplish the
repair within the timescale(s) indicated in, and in accordance with
the instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as
applicable to the airplane configuration, of Airbus Service Bulletin
A310-55-2045 or A300-55-6044, both Revision 01, as applicable.
(2) Within 500 flight cycles or 6 months after the effective
date of this AD, whichever occurs first, perform a special detailed
inspection along the rudder Z-profile, in accordance with the
instructions given in Airbus Service Bulletin A310-55-2044 or A300-
55-6043, both Revision 01, both dated December 3, 2007, as
applicable. For airplanes identified as configuration 01 in the
service bulletins, repeat the inspection thereafter at intervals not
to exceed 1,400 flight cycles. For airplanes identified as
Configuration 02 in the service bulletins, repeat the inspection
thereafter at intervals not to exceed 5,000 flight cycles. For
temporary repair along the rudder Z-profile for both airplanes
identified as configuration 01 and 02, refer to paragraph 3.C.(1) of
Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision
01, as applicable.
(i) If no damage is found, within 30 days after the inspection
or 30 days after the effective date of this AD, whichever occurs
later, report to AIRBUS using Appendix 1 or 2, as applicable to the
airplane configuration, of Airbus Service Bulletin A310-55-2044 or
A300-55-6043, both Revision 01, as applicable.
(ii) If any damage is found, verify the findings and apply all
applicable corrective actions within the timescale(s) indicated in,
and in accordance with instructions given in paragraph 3.B.(1)(a) or
3.B.(2)(a), as applicable to the airplane configuration, of Airbus
Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as
applicable. Within 30 days after the inspection or corrective action
or 30 days after the effective date of this AD, whichever occurs
later, submit a report to Airbus using Appendix 1 or 2, as
applicable to the airplane configuration, of Airbus Service Bulletin
A310-55-2044 or A300-55-6043, both Revision 01, as applicable.
Note 1: For rudder configuration identification, refer to
Appendices 3 and 4 of Airbus Service Bulletin A310-55-2044, A310-55-
2045, A300-55-6043, and A300-55-6044, as applicable to the airplane
model and configuration.
(3) As of 30 days after the effective date of this AD: No person
shall install a P/N A55471500 series rudder on any airplane as a
replacement, unless it has been inspected and repaired, as
applicable, in accordance with the instructions of Airbus Service
Bulletins A310-55-2045, Revision 01, dated December 20, 2007, and
A310-55-2044, Revision 01, dated December 3, 2007; or Airbus Service
Bulletins A300-55-6044, Revision 01, dated December 20, 2007, and
A300-55-6043, Revision 01, dated December 3, 2007; as applicable.
(4) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A300-55-6044 or A310-55-
2045, both dated July 23, 2007, are considered acceptable for
compliance with the corresponding actions specified in paragraph
(f)(1) of this AD.
(5) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A300-55-6043 or A310-55-
2044, both dated July 23, 2007, are considered acceptable for
compliance with the corresponding actions specified in paragraph
(f)(2) of this AD.
FAA AD Differences
Note 2: 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 EASA Airworthiness Directive 2007-0266, dated
October 8, 2007, and the service bulletins listed in Table 1 of this
AD, for related information.
[[Page 3659]]
Table 1.--Airbus Service Information
------------------------------------------------------------------------
Airbus Service Bulletin Revision Date
------------------------------------------------------------------------
A300-55-6043.................. 01 December 3, 2007.
A300-55-6044.................. 01 December 20, 2007.
A310-55-2044.................. 01 December 3, 2007.
A310-55-2045.................. 01 December 20, 2007.
------------------------------------------------------------------------
Issued in Renton, Washington, on January 15, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-977 Filed 1-18-08; 8:45 am]
BILLING CODE 4910-13-P
