Airworthiness Directives; Airbus Model A330 Airplanes; and Model A340-200 and -300 Airplanes, 15063-15067 [E7-5908]
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Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules
§ 915.11
District.
6. Add a new § 915.43 to read as
follows:
(a) District 1 shall include MiamiDade County.
(b) District 2 shall include all of the
production area except Miami-Dade
County.
3. In § 915.22, paragraph (b)(1) is
revised to read as follows:
§ 915.22
§ 915.43
Nomination.
(a) * * *
(b) Successor members. (1) The
Committee shall hold or cause to be
held a meeting or meetings of growers
and handlers in each district to
designate nominees for successor
members and alternate members of the
Committee; or the Committee may
conduct nominations in Districts 1 and
2 by mail in a manner recommended by
the Committee and approved by the
Secretary. Such nominations shall be
submitted to the Secretary by the
Committee not later than March 1 of
each year. The Committee shall
prescribe procedural rules, not
inconsistent with the provisions of this
section, for the conduct of nomination.
*
*
*
*
*
4. In § 915.30, paragraph (c) is revised
to read as follows:
§ 915.30
Procedure.
(a) * * *
(b) * * *
(c) For any recommendation of the
Committee for an assessment rate
change, a quorum of seven Committee
members and a two-thirds majority vote
of approval of those in attendance is
required.
5. In § 915.41, paragraph (b) is revised
to read as follows:
pwalker on PROD1PC71 with PROPOSALS
§ 915.41
Assessments.
(a) * * *
(b) The Secretary shall fix the rate of
assessment per 55-pounds of fruit or
equivalent in any container or in bulk,
to be paid by each such handler. At any
time during or after a fiscal year, the
Secretary may increase the rate of
assessment, in order to secure sufficient
funds to cover any later finding by the
Secretary relative to the expense which
may be incurred. Such increase shall be
applied to all fruit handled during the
applicable fiscal year. In order to
provide funds for the administration of
the provisions of this part, the
Committee may accept the payment of
assessments in advance, or borrow
money on an emergency short-term
basis. The authority of the Committee to
borrow money is subject to approval of
the Secretary and may be used only to
meet financial obligations as the
obligations occur or to allow the
Committee to adjust its reserve funds to
meet such obligations.
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Contributions.
The Committee may accept voluntary
contributions. Such contributions shall
be free from any encumbrances by the
donor and the Committee shall retain
complete control of their use.
7. Revise § 915.45 to read as follows:
§ 915.45 Production research, marketing
research and development.
The committee may, with the
approval of the Secretary, establish or
provide for the establishment of
production research, marketing research
and development projects designed to
assist, improve or promote the
marketing, distribution, and
consumption or efficient production of
avocados. Such products may provide
for any form of marketing promotion,
including paid advertising. The
expenses of such projects shall be paid
from funds collected pursuant to the
applicable provisions of § 915.41, or
from such other funds as approved by
the USDA.
Dated: March 23, 2007.
Lloyd C. Day,
Administrator, Agricultural Marketing
Service.
[FR Doc. E7–5792 Filed 3–29–07; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket Number FAA–2007–27739;
Directorate Identifier 2006–NM–250–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330 Airplanes; and Model A340–200
and –300 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:
The aim of * * * [Special Federal Aviation
Regulation (SFAR) 88] is to require all
holders of type certificates * * * to carry out
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Fmt 4702
Sfmt 4702
15063
a definition review against explosion
hazards.
The unsafe condition is the potential of
ignition sources inside fuel tanks,
which, in combination with flammable
fuel vapors, could result in fuel tank
explosions and consequent loss 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 April 30, 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: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., 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 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–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
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
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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
Number FAA–2007–27739; Directorate
Identifier 2006–NM–250–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.
Discussion
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The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued Airworthiness
Directive 2006–0322, dated October 18,
2006 (referred to after this as ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
[T]he FAA published SFAR 88 (Special
Federal Aviation Regulation 88).
By mail referenced 04/00/02/07/01–L296
of March 4th, 2002 and 04/00/02/07/03–L024
of February 3rd, 2003 the JAA (Joint Aviation
Authorities) recommended to the National
Aviation Authorities (NAA) the application
of a similar regulation.
The aim of this regulation is to require all
holders of type certificates for passenger
transport aircraft certified after January 1st,
1958 with a capacity of 30 passengers or
more, or a payload of 3402 kg or more, to
carry out a definition review against
explosion hazards.
Consequently, the following measures are
rendered mandatory:
• [inspection and] replacement [if
necessary] of the white P-clips by blue Pclips which are more fuel resistant [to]
remove the risks of fuel quantity indicator
(FQI) and fuel level sensor system (FLSS)
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Jkt 211001
harnesses chafing against the metallic part of
the P-clip,
• Modification of electrical bonding of
equipment installed in fuel tanks in order to
re-establish the conformity with the design
definition by introducing additional bonding
leads, electrical bonding points and electrical
bonding of a support bracket for a diffuser
assembly installed between Rib 1 and Rib 2
on the stringers of the Number 1 bottom skin
panel,
• Modification of bonding points,
installation of additional bonding leads and
other modifications of the Additional Center
Tank (ACT),
• Modification to increase the distance
between metallic parts on the THS
(trimmable horizontal stabilizer) Trim Tank,
• Installation of a bonding lead between
the bonding tags on the Jettison valve
actuator and drive assembly.
You may obtain further information by
examining the MCAI in the AD docket.
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (66 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
Regulation Number 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
maintenance procedures if their designs
do not meet the new fuel tank safety
standards. As explained in the preamble
to the rule, we intended to adopt
airworthiness directives to mandate any
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
In evaluating these design reviews, we
have established four criteria intended
to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
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which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
Single failures, single failures in
combination with a latent condition(s),
and in-service failure experience. For all
four criteria, the evaluations included
consideration of previous actions taken
that may mitigate the need for further
action.
The Joint Aviation Authorities (JAA)
has issued a regulation that is similar to
SFAR 88. (The JAA is an associated
body of the European Civil Aviation
Conference (ECAC) representing the
civil aviation regulatory authorities of a
number of European States who have
agreed to co-operate in developing and
implementing common safety regulatory
standards and procedures.) Under this
regulation, the JAA stated that all
members of the ECAC that hold type
certificates for transport category
airplanes are required to conduct a
design review against explosion risks.
We have determined that the actions
identified in this AD are necessary to
reduce the potential of ignition sources
inside fuel tanks, which, in combination
with flammable fuel vapors, could result
in fuel tank explosions and consequent
loss of the airplane.
Relevant Service Information
Airbus has issued the following
service bulletins:
• A330–28–3082, including
Appendix 01, Revision 02, dated August
11, 2006.
• A330–28–3092, including
Appendix 01, Revision 01, dated
December 14, 2005.
• A330–28–3101, Revision 01, dated
October 11, 2006.
• A330–55–3016, Revision 1, dated
February 12, 1997.
• A340–28–4073, Revision 01,
October 9, 1998.
• A340–28–4078, dated March 17,
2000.
• A340–28–4097, including
Appendix 01, Revision 02, dated August
16, 2006.
• A340–28–4107, including
Appendix 01, Revision 01, dated
December 14, 2005.
• A340–28–4118, Revision 01, dated
October 11, 2006.
• A340–55–4017, Revision 1, dated
February 12, 1997.
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
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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.
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Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 28 products of U.S. registry.
We also estimate that it would take
about 600 work-hours per product to
comply with this proposed AD. The
average labor rate is $80 per work-hour.
Required parts would cost about $2,718
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
$1,420,104, or $50,718 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
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Jkt 211001
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 adding
the following new AD:
Airbus: Docket Number FAA–2007–27739;
Directorate Identifier 2006-NM–250–AD.
Comments Due Date
(a) We must receive comments by April 30,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model
A330, A340–200, and A340–300 airplanes,
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Sfmt 4702
15065
all certified models, all serial numbers,
certificated in any category.
Subject
(d) Fuel.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
[T]he FAA published SFAR 88 (Special
Federal Aviation Regulation 88).
By mail referenced 04/00/02/07/01–L296
of March 4th, 2002 and 04/00/02/07/03–L024
of February 3rd, 2003 the JAA (Joint Aviation
Authorities) recommended to the National
Aviation Authorities (NAA) the application
of a similar regulation.
The aim of this regulation is to require all
holders of type certificates for passenger
transport aircraft certified after January 1st,
1958 with a capacity of 30 passengers or
more, or a payload of 3402 kg or more, to
carry out a definition review against
explosion hazards.
Consequently, the following measures are
rendered mandatory:
• [Inspection and ] replacement [if
necessary] of the white P-clips by blue Pclips which are more fuel resistant [to]
remove the risks of fuel quantity indicator
(FQI) and fuel level sensor system (FLSS)
harnesses chafing against the metallic part of
the P-clip,
• Modification of electrical bonding of
equipment installed in fuel tanks in order to
re-establish the conformity with the design
definition by introducing additional bonding
leads, electrical bonding points and electrical
bonding of a support bracket for a diffuser
assembly installed between Rib 1 and Rib 2
on the stringers of the Number 1 bottom skin
panel,
• Modification of bonding points,
installation of additional bonding leads and
other modifications of the Additional Center
Tank (ACT),
• Modification to increase the distance
between metallic parts on the THS
(trimmable horizontal stabilizer) Trim Tank,
• Installation of a bonding lead between
the bonding tags on the Jettison valve
actuator and drive assembly.
Actions and Compliance
(f) Within 38 months after the effective
date of this AD, unless already done, do the
actions in paragraphs (f)(1), (f)(2), (f)(3), (f)(4),
and (f)(5).
(1) Action number 1, applicable to Model
A330, A340–200, and A340–330 aircraft, all
certified models, all serial numbers, except
for airplanes on which Airbus Modification
47634 has been embodied in production:
Perform a detailed visual inspection of the Pclips in the wings and center fuel tanks, and
apply the applicable corrective actions, in
accordance with the instructions of Airbus
Service Bulletin A330–28–3092, Revision 01,
dated December 14, 2005; or Airbus Service
Bulletin A340–28–4107, Revision 01, dated
December 14, 2005.
(2) Action number 2, applicable to Model
A330, A340–200, and A340–300 airplanes,
all certified models, all serial numbers,
except for airplanes on which Airbus
Modifications 49135 and 49630 and 51825
and 55118 have been embodied in
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production or modified in-service in
accordance with both Airbus Service Bulletin
A330–28–3082, including Appendix 01, and
Airbus Service Bulletin A330–28–3101, or
both Airbus Service Bulletin A340–28–4097
and Airbus Service Bulletin A340–28–4118:
Modify the electrical bonding of the
equipment installed in fuel tanks, in
accordance with both Airbus Service Bulletin
A330–28–3082, Revision 02, dated August
11, 2006, and Airbus Service Bulletin A330–
28–3101, Revision 01, dated October 11,
2006; or both Airbus Service Bulletin A340–
28–4097, including Appendix 01, Revision
02, dated August 16, 2006, and Airbus
Service Bulletin A340–28–4118, Revision 01,
dated October 11, 2006; as applicable.
(3) Action number 3, applicable to Model
A340–200 and A340–300 airplanes, all
certified models, all serial numbers, which
have Airbus modification 42612/Airbus
Service Bulletin A340–28–4047 or Airbus
modification 44002/Airbus Service Bulletin
A340–28–4066 or Airbus modification
44005/Airbus Service Bulletin A340–28–
4067 embodied in production/in-service
(installation of an ACT (Additional Center
Tank)), except airplanes modified by Airbus
Service Bulletin A340–28–4078 in-service:
Modify the electrical bonding in the ACT in
accordance with the instructions of Airbus
Service Bulletin A340–28–4078, dated March
17, 2000.
(4) Action number 4, applicable to Model
A330–300 airplanes, –301, –321, –322, –341,
–342 models, all serial numbers except for
airplanes on which Airbus Modification
44252 has been embodied in production or
modified in-service in accordance with
Airbus Service Bulletin A330–55–3016; and
Model A340–200 and Model A340–300
airplanes, all certified models, all serial
numbers, except for airplanes on which
Airbus Modification 44252 has been
embodied in production or modified inservice in accordance with Airbus Service
Bulletin A340–55–4017: Increase the
distance between metallic parts on the THS
(trimmable horizontal stabilizer) trim tank in
accordance with the instructions of Airbus
Service Bulletin A330–55–3016, Revision 1,
dated February 12, 1997; or Airbus Service
Bulletin A340–55–4017, Revision 1, dated
February 12, 1997; as applicable.
(5) Action number 5, applicable to Model
A340–200 and A340–300 airplanes, all
certified models, all serial numbers, except
for airplanes which have Airbus modification
46142 embodied in production or modified
in-service in accordance with Airbus Service
Bulletin A340–28–4073, Revision 01, dated
October 9, 1998: Install a bonding lead
between the bonding tags on the Jettison
valve actuator and drive assembly in
accordance with the instructions of Airbus
Service Bulletin A340–28–4073, Revision 01,
dated October 9, 1998.
(6) Actions done before the effective date
of this AD in accordance with the service
bulletins listed in Table 1 of this AD are
acceptable for compliance with the
corresponding requirements of paragraphs
(f)(1), (f)(2), (f)(3), (f)(4), and (f)(5) of this AD,
as applicable.
TABLE 1.—CREDIT SERVICE BULLETINS
Airbus Service Bulletin
A330–28–3082
A330–28–3082
A330–28–3101
A330–55–3016
A340–28–4073
A340–28–4097
A340–28–4097
A340–28–4118
A340–55–4017
Revision level
........................................................................
........................................................................
........................................................................
........................................................................
........................................................................
........................................................................
........................................................................
........................................................................
........................................................................
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, ANM–116,
International Branch, 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: Tim Backman,
Aerospace Engineer; 1601 Lind Ave. SW.,
Date
Original ...................................................................................
01 ...........................................................................................
Original ...................................................................................
Original ...................................................................................
Original ...................................................................................
Original ...................................................................................
01 ...........................................................................................
Original ...................................................................................
Original ...................................................................................
Renton, Washington 98057–3356, telephone
(425) 227–2797; fax (425) 227–1149. To
request a different method of compliance or
a different compliance time for this AD,
follow the procedures in 14 CFR 39.19.
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 FAAapproved if they are approved by the State
of Design Authority (or their delegated
June 14, 2004.
March 2, 2005.
June 5, 2006.
August 20, 1996.
May 14, 1998.
June 14, 2004.
March 3, 2005.
June 5, 2006.
August 20, 1996.
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 (EASA) Airworthiness
Directive 2006–0322, dated October 18, 2006,
and the service bulletins in Table 2 of this
AD, for related information.
TABLE 2.—RELATED SERVICE BULLETINS
Revision level
Date
A330–28–3082, including Appendix 01 ..................................
A330–28–3092 ........................................................................
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Airbus Service Bulletin
02 ...........................................................................................
01 ...........................................................................................
A330–28–3101 ........................................................................
A330–55–3016 ........................................................................
A340–28–4073 ........................................................................
A340–28–4078 ........................................................................
A340–28–4097, including Appendix 01 ..................................
A340–28–4107 ........................................................................
01 ...........................................................................................
1 .............................................................................................
01 ...........................................................................................
Original ...................................................................................
02 ...........................................................................................
01 ...........................................................................................
A340–28–4118 ........................................................................
A340–55–4017 ........................................................................
01 ...........................................................................................
1 .............................................................................................
August 11, 2006.
December 14,
2005.
October 11, 2006.
February 12, 1997.
October 9, 1998.
March 17, 2000.
August 16, 2006.
December 14,
2005.
October 11, 2006.
February 12, 1997.
VerDate Aug<31>2005
17:30 Mar 29, 2007
Jkt 211001
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
E:\FR\FM\30MRP1.SGM
30MRP1
Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules
Issued in Renton, Washington, on March
23, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–5908 Filed 3–29–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27741; Directorate
Identifier 2006–NM–261–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–201, –202, –203, –223, –243,
–301, –321, –322, –323, –341, –342, and
–343 Airplanes; and Model A340–200
and –300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
pwalker on PROD1PC71 with PROPOSALS
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)
issued 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 keel beam rupture, which
affects the structural integrity of the
area. 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 April 30, 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: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., 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.
VerDate Aug<31>2005
17:30 Mar 29, 2007
Jkt 211001
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
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–2007–27741; Directorate Identifier
2006–NM–261–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 because of 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
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
15067
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 2006–0315,
dated October 13, 2006 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states that during the A330
and A340 aircraft fatigue test, cracks
appeared on the right and left sides
between the crossing area of the keel
beam fitting and the front spar on the
center wing box (CWB). This situation if
not corrected can lead in the worst case
to keel beam rupture, which affects the
structural integrity of the area. In order
to maintain the structural integrity of
the aircraft, the MCAI requires a
repetitive special detailed inspection on
the horizontal flange of the keel beam in
the area of the first fastener hole aft of
FR (frame) 40, follow-up actions (further
inspections, installation of new
fasteners, and sealing the fasteners), and
repair if necessary. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin
A330–57–3081, including Appendix 01,
Revision 02, dated January 24, 2006;
and Service Bulletin A340–57–4089,
including Appendix 01, Revision 02,
dated January 24, 2006. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI. The compliance
times for doing the actions described in
the service bulletins are as follows:
• Service Bulletin A330–57–3081:
The mandatory thresholds range from
the earlier of 19,100 flight cycles or
57,300 flight hours, to the earlier of
24,200 flight cycles or 72,800 flight
hours; the repetitive intervals range
from the earlier of 9,800 flight cycles or
29,400 flight hours, to the earlier of
13,500 flight cycles or 40,500 flight
hours.
• Service Bulletin A340–57–4089:
The mandatory thresholds range from
the earlier of 19,000 flight cycles or
95,000 flight hours, to the earlier of
24,600 flight cycles or 49,200 flight
hours; the repetitive intervals range
from the earlier of 9,200 flight cycles or
46,000 flight hours, to the earlier of
12,600 flight cycles or 63,000 flight
hours.
E:\FR\FM\30MRP1.SGM
30MRP1
]]>Agencies
[Federal Register Volume 72, Number 61 (Friday, March 30, 2007)]
[Proposed Rules]
[Pages 15063-15067]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-5908]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket Number FAA-2007-27739; Directorate Identifier 2006-NM-250-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 Airplanes; and Model
A340-200 and -300 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:
The aim of * * * [Special Federal Aviation Regulation (SFAR) 88]
is to require all holders of type certificates * * * to carry out a
definition review against explosion hazards.
The unsafe condition is the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss 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 April 30, 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: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., 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 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) 647-5227) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2797; 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
[[Page 15064]]
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 Number FAA-2007-
27739; Directorate Identifier 2006-NM-250-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.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued
Airworthiness Directive 2006-0322, dated October 18, 2006 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
[T]he FAA published SFAR 88 (Special Federal Aviation Regulation
88).
By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and
04/00/02/07/03-L024 of February 3rd, 2003 the JAA (Joint Aviation
Authorities) recommended to the National Aviation Authorities (NAA)
the application of a similar regulation.
The aim of this regulation is to require all holders of type
certificates for passenger transport aircraft certified after
January 1st, 1958 with a capacity of 30 passengers or more, or a
payload of 3402 kg or more, to carry out a definition review against
explosion hazards.
Consequently, the following measures are rendered mandatory:
[inspection and] replacement [if necessary] of the
white P-clips by blue P-clips which are more fuel resistant [to]
remove the risks of fuel quantity indicator (FQI) and fuel level
sensor system (FLSS) harnesses chafing against the metallic part of
the P-clip,
Modification of electrical bonding of equipment
installed in fuel tanks in order to re-establish the conformity with
the design definition by introducing additional bonding leads,
electrical bonding points and electrical bonding of a support
bracket for a diffuser assembly installed between Rib 1 and Rib 2 on
the stringers of the Number 1 bottom skin panel,
Modification of bonding points, installation of
additional bonding leads and other modifications of the Additional
Center Tank (ACT),
Modification to increase the distance between metallic
parts on the THS (trimmable horizontal stabilizer) Trim Tank,
Installation of a bonding lead between the bonding tags
on the Jettison valve actuator and drive assembly.
You may obtain further information by examining the MCAI in the AD
docket.
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation Number 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: Single failures, single failures in
combination with a latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
The Joint Aviation Authorities (JAA) has issued a regulation that
is similar to SFAR 88. (The JAA is an associated body of the European
Civil Aviation Conference (ECAC) representing the civil aviation
regulatory authorities of a number of European States who have agreed
to co-operate in developing and implementing common safety regulatory
standards and procedures.) Under this regulation, the JAA stated that
all members of the ECAC that hold type certificates for transport
category airplanes are required to conduct a design review against
explosion risks.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
Relevant Service Information
Airbus has issued the following service bulletins:
A330-28-3082, including Appendix 01, Revision 02, dated
August 11, 2006.
A330-28-3092, including Appendix 01, Revision 01, dated
December 14, 2005.
A330-28-3101, Revision 01, dated October 11, 2006.
A330-55-3016, Revision 1, dated February 12, 1997.
A340-28-4073, Revision 01, October 9, 1998.
A340-28-4078, dated March 17, 2000.
A340-28-4097, including Appendix 01, Revision 02, dated
August 16, 2006.
A340-28-4107, including Appendix 01, Revision 01, dated
December 14, 2005.
A340-28-4118, Revision 01, dated October 11, 2006.
A340-55-4017, Revision 1, dated February 12, 1997.
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
[[Page 15065]]
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 28 products of U.S. registry. We also estimate that
it would take about 600 work-hours per product to comply with this
proposed AD. The average labor rate is $80 per work-hour. Required
parts would cost about $2,718 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
$1,420,104, or $50,718 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 Number FAA-2007-27739; Directorate Identifier 2006-
NM-250-AD.
Comments Due Date
(a) We must receive comments by April 30, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A330, A340-200, and
A340-300 airplanes, all certified models, all serial numbers,
certificated in any category.
Subject
(d) Fuel.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
[T]he FAA published SFAR 88 (Special Federal Aviation Regulation
88).
By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and
04/00/02/07/03-L024 of February 3rd, 2003 the JAA (Joint Aviation
Authorities) recommended to the National Aviation Authorities (NAA)
the application of a similar regulation.
The aim of this regulation is to require all holders of type
certificates for passenger transport aircraft certified after
January 1st, 1958 with a capacity of 30 passengers or more, or a
payload of 3402 kg or more, to carry out a definition review against
explosion hazards.
Consequently, the following measures are rendered mandatory:
[Inspection and ] replacement [if necessary] of the
white P-clips by blue P-clips which are more fuel resistant [to]
remove the risks of fuel quantity indicator (FQI) and fuel level
sensor system (FLSS) harnesses chafing against the metallic part of
the P-clip,
Modification of electrical bonding of equipment
installed in fuel tanks in order to re-establish the conformity with
the design definition by introducing additional bonding leads,
electrical bonding points and electrical bonding of a support
bracket for a diffuser assembly installed between Rib 1 and Rib 2 on
the stringers of the Number 1 bottom skin panel,
Modification of bonding points, installation of
additional bonding leads and other modifications of the Additional
Center Tank (ACT),
Modification to increase the distance between metallic
parts on the THS (trimmable horizontal stabilizer) Trim Tank,
Installation of a bonding lead between the bonding tags
on the Jettison valve actuator and drive assembly.
Actions and Compliance
(f) Within 38 months after the effective date of this AD, unless
already done, do the actions in paragraphs (f)(1), (f)(2), (f)(3),
(f)(4), and (f)(5).
(1) Action number 1, applicable to Model A330, A340-200, and
A340-330 aircraft, all certified models, all serial numbers, except
for airplanes on which Airbus Modification 47634 has been embodied
in production: Perform a detailed visual inspection of the P-clips
in the wings and center fuel tanks, and apply the applicable
corrective actions, in accordance with the instructions of Airbus
Service Bulletin A330-28-3092, Revision 01, dated December 14, 2005;
or Airbus Service Bulletin A340-28-4107, Revision 01, dated December
14, 2005.
(2) Action number 2, applicable to Model A330, A340-200, and
A340-300 airplanes, all certified models, all serial numbers, except
for airplanes on which Airbus Modifications 49135 and 49630 and
51825 and 55118 have been embodied in
[[Page 15066]]
production or modified in-service in accordance with both Airbus
Service Bulletin A330-28-3082, including Appendix 01, and Airbus
Service Bulletin A330-28-3101, or both Airbus Service Bulletin A340-
28-4097 and Airbus Service Bulletin A340-28-4118: Modify the
electrical bonding of the equipment installed in fuel tanks, in
accordance with both Airbus Service Bulletin A330-28-3082, Revision
02, dated August 11, 2006, and Airbus Service Bulletin A330-28-3101,
Revision 01, dated October 11, 2006; or both Airbus Service Bulletin
A340-28-4097, including Appendix 01, Revision 02, dated August 16,
2006, and Airbus Service Bulletin A340-28-4118, Revision 01, dated
October 11, 2006; as applicable.
(3) Action number 3, applicable to Model A340-200 and A340-300
airplanes, all certified models, all serial numbers, which have
Airbus modification 42612/Airbus Service Bulletin A340-28-4047 or
Airbus modification 44002/Airbus Service Bulletin A340-28-4066 or
Airbus modification 44005/Airbus Service Bulletin A340-28-4067
embodied in production/in-service (installation of an ACT
(Additional Center Tank)), except airplanes modified by Airbus
Service Bulletin A340-28-4078 in-service: Modify the electrical
bonding in the ACT in accordance with the instructions of Airbus
Service Bulletin A340-28-4078, dated March 17, 2000.
(4) Action number 4, applicable to Model A330-300 airplanes, -
301, -321, -322, -341, -342 models, all serial numbers except for
airplanes on which Airbus Modification 44252 has been embodied in
production or modified in-service in accordance with Airbus Service
Bulletin A330-55-3016; and Model A340-200 and Model A340-300
airplanes, all certified models, all serial numbers, except for
airplanes on which Airbus Modification 44252 has been embodied in
production or modified in-service in accordance with Airbus Service
Bulletin A340-55-4017: Increase the distance between metallic parts
on the THS (trimmable horizontal stabilizer) trim tank in accordance
with the instructions of Airbus Service Bulletin A330-55-3016,
Revision 1, dated February 12, 1997; or Airbus Service Bulletin
A340-55-4017, Revision 1, dated February 12, 1997; as applicable.
(5) Action number 5, applicable to Model A340-200 and A340-300
airplanes, all certified models, all serial numbers, except for
airplanes which have Airbus modification 46142 embodied in
production or modified in-service in accordance with Airbus Service
Bulletin A340-28-4073, Revision 01, dated October 9, 1998: Install a
bonding lead between the bonding tags on the Jettison valve actuator
and drive assembly in accordance with the instructions of Airbus
Service Bulletin A340-28-4073, Revision 01, dated October 9, 1998.
(6) Actions done before the effective date of this AD in
accordance with the service bulletins listed in Table 1 of this AD
are acceptable for compliance with the corresponding requirements of
paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(5) of this AD, as
applicable.
Table 1.--Credit Service Bulletins
------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
------------------------------------------------------------------------
A330-28-3082................. Original....... June 14, 2004.
A330-28-3082................. 01............. March 2, 2005.
A330-28-3101................. Original....... June 5, 2006.
A330-55-3016................. Original....... August 20, 1996.
A340-28-4073................. Original....... May 14, 1998.
A340-28-4097................. Original....... June 14, 2004.
A340-28-4097................. 01............. March 3, 2005.
A340-28-4118................. Original....... June 5, 2006.
A340-55-4017................. Original....... August 20, 1996.
------------------------------------------------------------------------
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, ANM-
116, International Branch, 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: Tim
Backman, Aerospace Engineer; 1601 Lind Ave. SW., Renton, Washington
98057-3356, telephone (425) 227-2797; fax (425) 227-1149. To request
a different method of compliance or a different compliance time for
this AD, follow the procedures in 14 CFR 39.19. 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 (EASA)
Airworthiness Directive 2006-0322, dated October 18, 2006, and the
service bulletins in Table 2 of this AD, for related information.
Table 2.--Related Service Bulletins
------------------------------------------------------------------------
Airbus Service Bulletin Revision level Date
------------------------------------------------------------------------
A330-28-3082, including 02............. August 11, 2006.
Appendix 01.
A330-28-3092................. 01............. December 14, 2005.
A330-28-3101................. 01............. October 11, 2006.
A330-55-3016................. 1.............. February 12, 1997.
A340-28-4073................. 01............. October 9, 1998.
A340-28-4078................. Original....... March 17, 2000.
A340-28-4097, including 02............. August 16, 2006.
Appendix 01.
A340-28-4107................. 01............. December 14, 2005.
A340-28-4118................. 01............. October 11, 2006.
A340-55-4017................. 1.............. February 12, 1997.
------------------------------------------------------------------------
[[Page 15067]]
Issued in Renton, Washington, on March 23, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-5908 Filed 3-29-07; 8:45 am]
BILLING CODE 4910-13-P
