Airworthiness Directives; Airbus Model A330 Airplanes; and Model A340-200 and -300 Airplanes, 34228-34233 [E8-13568]
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(j) The Manager, International Branch,
ANM–116, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Vladimir Ulyanov,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1138; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
Related Information
(k) European Aviation Safety Agency
(EASA) airworthiness directive 2007–0243,
dated September 4, 2007, also addresses the
subject of this AD.
Issued in Renton, Washington, on June 10,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–13566 Filed 6–16–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 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: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
jlentini on PROD1PC65 with PROPOSALS
SUMMARY: We are revising an original
NPRM for the products listed above.
This action revises the original NPRM
by expanding the scope. 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,
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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 July 14, 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: 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:
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–2007–27739; 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://
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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
We proposed to amend 14 CFR part
39 with an earlier NPRM for the
specified products, which was
published in the Federal Register on
March 30, 2007 (72 FR 15063). That
earlier NPRM proposed to require
actions intended to address the unsafe
condition for the products listed above.
Since that NPRM was issued, we have
determined that additional bonding
points must be modified and that the
compliance time for performing the
action specified in paragraph (f)(4)(ii) of
this supplemental NPRM (increasing the
distance between metallic parts on the
trimmable horizontal stabilizer (THS)
trim tank) may be extended for airplanes
that are already compliant with certain
requirements of Airbus All Operators
Telex (AOT) 55–03, dated August 22,
1996. In addition, we have referred to
the latest revisions of the service
bulletins as the appropriate sources of
service information for accomplishing
certain actions in this supplemental
NPRM. European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Community, has issued
Airworthiness Directive 2007–0278,
dated November 5, 2007 [Corrected:
November 8, 2007] (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
You may obtain further information by
examining the MCAI in the AD docket.
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 3,402 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 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
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
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 Trim
Tank,
• Installation of a bonding lead between
the bonding tags on the Jettison valve
actuator and drive assembly.
This new AD supersedes EASA AD 2006–
0322 taking over its requirements and:
• Mandates SB A330–28–3082 Revision 04
which introduces an additional work for
some bonding points which were omitted
from the center tank at original issue (action
n°2 [paragraph (f)(2) of this AD]);
• Mandates SB A340–28–4097 Revision 03
which introduces an additional work by
addition of electrical bondings omitted from
previous revisions (action n°2);
• Introduces an extension of the required
compliance time to perform action n°4 for
those aircraft already compliant with
AIRBUS AOT 55–03 dated 22 August 1996
(‘‘solution A’’), mandated by DGAC
´ ´
[Direction Generale de l’Aviation Civile] AD
F–1996–178–049(B) R1 and DGAC AD F–
1996–177–038(B) with a compliance time of
November 15th, 1996;
• Refers to the latest revision of certain
AIRBUS SBs.
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.
Relevant Service Information
Airbus has issued the service
bulletins described in the following
table.
AIRBUS SERVICE BULLETINS
Airbus service bulletin
Revision level
A330–28–3082, including Appendix 01 .......................................................................................................
A330–55–3016 .............................................................................................................................................
A340–28–4073 .............................................................................................................................................
A340–28–4078 .............................................................................................................................................
A340–28–4097, including Appendix 01 .......................................................................................................
A340–28–4118 .............................................................................................................................................
A340–55–4017 .............................................................................................................................................
The actions described in the service
information are intended to correct the
unsafe condition identified in the
MCAI.
Comments
We have considered the following
comments received on the earlier
NPRM.
Request to Use Latest Versions of
Service Information
Air Transport Association, on behalf
of its member U.S. Airways, requests
that we allow for the most recent
revisions to the applicable service
bulletins to be used for compliance with
the AD.
04
02
02
01
03
02
02
Date
August 3, 2007.
March 16, 2007.
March 8, 2007.
January 25, 2007.
July 3, 2007.
July 10, 2007.
March 16, 2007.
We agree. Airbus has revised the
service bulletins described in the
following table.
SERVICE BULLETINS THAT HAVE BEEN REVISED SINCE WE ISSUED THE NPRM
Airbus service
bulletin
New revision
A330–28–3082 ..
Revision 04, including Appendix 01, dated August 3,
2007.
Revision 02, including Appendix 01, dated August
11, 2006.
A330–55–3016 ..
Revision 02, dated March 16,
2007.
Revision 02, dated March 8,
2007.
Revision 1, dated February
12, 1997.
Revision 01, dated October
9, 1998.
A340–28–4097 ..
Revision 01, dated January
25, 2007.
Revision 03, including Appendix 01, dated July 3,
2007.
Original Issue, dated March
17, 2000.
Revision 02, including Appendix 01, dated August
16, 2006.
A340–28–4118 ..
Revision 02, dated July 10,
2007.
Revision 01, dated October
11, 2006.
No ..........................................
A340–55–4017 ..
Revision 02, dated March 16,
2007.
Revision 1, dated February
12, 1997.
No ..........................................
A340–28–4073 ..
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A340–28–4078 ..
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Revision level in original
NPRM
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Additional work necessary?
Reason for revision
Yes, for those modified in ac- Adds bonding points that
cordance with original reviwere omitted from the Acsion (dated June 14, 2004).
complishment Instructions
of the original revision of
the service bulletin.
No .......................................... Changes compliance classification.
No .......................................... Updates effectivity, revise jettison-valve procedure, and
format changes.
No .......................................... Changes a kit quantity.
Yes, for those modified in accordance with any previous
revision.
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Includes instructions for electrical bonding of fuel pump
canisters for certain airplanes and for the water
drain valve between rib 1
and rib 2 for all airplanes;
adds new airplane configurations.
Updates the effectivity, includes changes that followed validation of the
service bulletin.
Changes compliance classification.
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
performing the action specified in
paragraph (f)(4) of this supplemental
NPRM for airplanes that are already
compliant with certain requirements of
Airbus AOT 55–03 (mentioned in Table
1 of this Supplemental NPRM).
We have also revised the
supplemental NPRM to give credit for
accomplishment of earlier revisions of
service information that specify that no
additional work is necessary for
airplanes on which the earlier revision
was accomplished; we have removed
credit for accomplishment of the
original issue of Airbus Service Bulletin
A330–28–3082; and we have removed
credit for accomplishment of any
revision of Airbus Service Bulletin
A340–28–4097 that is earlier than
Revision 03.
Explanation of Change to Certain
Compliance Times
We have revised our month-based
compliance times to correspond to the
amount of elapsed time between the
effective date of the MCAI and the
compliance dates specified in the MCAI.
jlentini on PROD1PC65 with PROPOSALS
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.
Certain changes described above
expand the scope of the earlier NPRM.
As a result, we have determined that it
is necessary to reopen the comment
period to provide additional
opportunity for the public to comment
on this proposed AD.
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
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16:08 Jun 16, 2008
Jkt 214001
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 28 products of U.S. registry. We
also estimate that it would take 670
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
$1,576,904, or $56,318 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
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3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2007–27739;
Directorate Identifier 2006–NM–250–AD.
Comments Due Date
(a) We must receive comments by July 14,
2008.
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) Air Transport Association (ATA) of
America Codes 28: Fuel, and 55: Stabilizers.
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 3,402 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 remove
the risks of fuel quantity indicator (FQI) and
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Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
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.
This new AD supersedes EASA AD 2006–
0322 taking over its requirements and:
• Mandates SB A330–28–3082 Revision 04
which introduces an additional work for
some bonding points which were omitted
from the center tank at original issue (action
n°2 [paragraph (f)(2) of this AD]);
• Mandates SB A340–28–4097 Revision 03
which introduces an additional work by
addition of electrical bondings omitted from
previous revisions (action n°2);
• Introduces an extension of the required
compliance time to perform action n°4 for
those aircraft already compliant with
AIRBUS AOT 55–03 dated 22 August 1996
34231
(‘‘solution A’’), mandated by DGAC
´ ´
[Direction Generale de l’Aviation Civile] AD
F–1996–178–049(B) R1 and DGAC AD F–
1996–177–038(B) with a compliance time of
November 15th, 1996;
• Refers to the latest revision of certain
AIRBUS SBs.
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.
Actions and Compliance
(f) Unless already done, do the actions in
paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(5)
of this AD for the applicable airplanes
identified in Table 1 of this AD.
TABLE 1.—APPLICABLE PARAGRAPHS BY AIRPLANE MODEL
These airplane models—
Except airplanes—
Are affected by these paragraphs of this AD—
Model A330, A340–200, and A340–330 airplanes.
On which Airbus Modification 47634 has been
embodied in production.
• On which both Airbus Modifications 49135
and 49630 have been embodied in production.
• Both Airbus Modifications 51825 and 55118
have been embodied in production.
• That have been modified in-service in accordance with both Airbus Service Bulletin
A330–28–3082, Revision 04, including Appendix 01, dated August 3, 2007; and Airbus Service Bulletin A330–28–3101, Revision 01, dated October 11, 2006.
• That have been modified in-service in accordance with both Airbus Service Bulletin
A340–28–4097, Revision 03, including Appendix 01, dated July 3, 2007; and Airbus
Service Bulletin A340–28–4118, Revision
02, dated July 10, 2007.
• On which both Airbus Modifications 49135
and 49630 have been embodied in production.
• Both Airbus Modifications 51825 and 55118
have been embodied in production.
• That have been modified in-service in accordance with both Airbus Service Bulletin
A330–28–3082, Revision 04, including Appendix 01, dated August 3, 2007, and Airbus Service Bulletin A330–28–3101, Revision 01, dated October 11, 2006.
• That have been modified in-service in accordance with both Airbus Service Bulletin
A340–28–4097, Revision 03, including Appendix 01, dated July 3, 2007, and Airbus
Service Bulletin A340–28–4118, Revision
02, dated July 10, 2007.
That have been modified in service by Airbus
Service Bulletin A340–28–4078, Revision
01, dated January 25, 2007.
(f)(1).
• On which Airbus Modification 44252 has
been embodied in production.
• That have been modified in-service in accordance with Airbus Service Bulletin
A340–55–4017.
• On which Airbus Modification 44252 has
been embodied in production.
• That have been modified in-service in accordance with Airbus Service Bulletin
A330–55–3016.
(f)(4)(i), except as provided by paragraph
(f)(4)(ii) of this AD.
Model A330 airplanes on which the actions
specified in Airbus Service Bulletin A330–28–
3082, dated June 14, 2004, have been accomplished before the effective date of this
AD; and Model A340–200 and A340–300 airplanes on which the actions specified in Airbus Service Bulletin A340–28–4097, dated
June 14, 2004, Revision 01, dated March 3,
2005, or Revision 02, dated August 16, 2006,
have been accomplished before the effective
date of this AD.
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Model A340–200 and A340–300 airplanes that
have the ACT embodied in production or in
service (Airbus Modification 42612, 44002, or
44005).
Model A340–200 and A340–300 airplanes ........
Model A330–300, –301, –321, –322, –341,
–342 airplanes.
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(f)(2)(i), except as provided by paragraphs
(f)(2)(ii) and (f)(2)(iii) of this AD.
(f)(2)(ii) and (f)(2)(iii).
(f)(3).
(f)(4)(i), except as provided by paragraph
(f)(4)(ii) of this AD.
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TABLE 1.—APPLICABLE PARAGRAPHS BY AIRPLANE MODEL—Continued
These airplane models—
Except airplanes—
Are affected by these paragraphs of this AD—
Model A330–300, –301, –321, –322, –341,
–342 airplanes; and Model A340–200 and
A340–300 airplanes.
On which the improvement of the THS lightning strike protection has already been performed before the effective date of this AD
in accordance with Airbus All Operators
Telex (AOT) 55–03, dated August 22, 1996
(‘‘solution A’’), mandated by Direction
´ ´
Generale de l’Aviation Civile (DGAC) Airworthiness Directive F–1996–178–049(B)
R1, and DGAC Airworthiness Directive F–
1996–177–038(B), with a compliance time
of November 15, 1996.
• On which Airbus Modification 46142 has
been embodied in production.
• That have been modified in-service in accordance with Airbus Service Bulletin
A340–28–4073, Revision 02, dated March
8, 2007.
(f)(4)(ii).
Model A340–200 and A340–300 airplanes ........
(1) Within 24 months after the effective
date of this AD, do 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
applicable 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) Do the requirements of paragraphs
(f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of this AD, as
applicable, at the times specified in those
paragraphs.
(i) For airplanes affected by this paragraph,
as specified in Table 1 of this AD: Within 24
months after the effective date of this AD,
modify the electrical bonding of the
equipment installed in fuel tanks, in
accordance with both Airbus Service Bulletin
A330–28–3082, Revision 04, including
Appendix 01, dated August 3, 2007, and
Airbus Service Bulletin A330–28–3101,
Revision 01, dated October 11, 2006; or both
Airbus Service Bulletin A340–28–4097,
Revision 03, including Appendix 01, dated
July 3, 2007, and Airbus Service Bulletin
A340–28–4118, Revision 02, dated July 10,
2007; as applicable.
(ii) For airplanes affected by this
paragraph, as specified in Table 1 of this AD:
Within 24 months after the effective date of
this AD, modify the electrical bonding of the
equipment installed in fuel tanks, in
accordance with Airbus Service Bulletin
A330–28–3101, Revision 01, dated October
11, 2006; or Airbus Service Bulletin A340–
28–4118, Revision 02, dated July 10, 2007; as
applicable.
(iii) For airplanes affected by this
paragraph, as specified in Table 1 of this AD:
Within 48 months after the effective date of
this AD, do the additional work specified in
Airbus Service Bulletin A330–28–3082,
Revision 04, including Appendix 01, dated
August 3, 2007; or Airbus Service Bulletin
A340–28–4097, Revision 03, including
Appendix 01, dated July 3, 2007; in
accordance with the accomplishment
instructions of those service bulletins, as
applicable.
(3) Within 24 months after the effective
date of this AD, modify the electrical bonding
in the ACT in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A340–28–4078, Revision 01,
dated January 25, 2007.
(4) Within 24, months after the effective
date of this AD, do the requirements of
paragraphs (f)(4)(i) and (f)(4)(ii), as
applicable.
(i) For airplanes affected by this paragraph,
as specified in Table 1 of this AD: Within 24
months after the effective date of this AD,
increase the distance between metallic parts
on the THS trim tank in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–55–3016, Revision 02,
(f)(5).
March 16, 2007; or Airbus Service Bulletin
A340–55–4017, Revision 02, dated March 16,
2007; as applicable.
(ii) For airplanes affected by this
paragraph, as specified in Table 1 of this AD:
At the first THS removal from the aircraft
done for any reason after the effective date
of this AD (e.g., fuselage stress jacking, and
repair) when the airplane is on a support tool
(lifting and resting point fittings must be
installed), or at the time of the first
maintenance task that requires the use of
THS lifting and resting point fittings,
whichever occurs earlier, increase the
distance between metallic parts on the THS
trim tank in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–55–3016, Revision 02,
March 16, 2007; or Airbus Service Bulletin
A340–55–4017, Revision 02, dated March 16,
2007; as applicable.
(5) Within 24 months after the effective
date of this AD, 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 02,
dated March 8, 2007.
(6) Actions done before the effective date
of this AD in accordance with the service
bulletins listed in Table 2 of this AD are
acceptable for compliance with the
corresponding requirements of this AD.
TABLE 2.—CREDIT SERVICE BULLETINS
jlentini on PROD1PC65 with PROPOSALS
Airbus service bulletin
A330–28–3082
A330–28–3082
A330–28–3082
A330–28–3101
A330–55–3016
A330–55–3016
A340–28–4073
A340–28–4073
A340–28–4078
A340–28–4118
A340–28–4118
A340–55–4017
VerDate Aug<31>2005
..........
..........
..........
..........
..........
..........
..........
..........
..........
..........
..........
..........
Revision level
Date
01 .........................................................
02 .........................................................
03 .........................................................
Original ................................................
Original ................................................
1 ...........................................................
Original ................................................
01 .........................................................
Original ................................................
Original ................................................
01 .........................................................
Original ................................................
March 2, 2005 .....................................
August 11, 2006 ..................................
November 15, 2006 .............................
June 5, 2006 .......................................
August 20, 1996 ..................................
February 12, 1997 ...............................
May 14, 1998 ......................................
October 9, 1998 ..................................
March 17, 2000 ...................................
June 5, 2006 .......................................
October 11, 2006 ................................
August 20, 1996 ..................................
16:08 Jun 16, 2008
Jkt 214001
PO 00000
Frm 00031
Fmt 4702
Sfmt 4702
E:\FR\FM\17JNP1.SGM
Corresponding paragraphs
(f)(2)(i) of this AD.
(f)(2)(i) of this AD.
(f)(2)(i) and (f)(2)(ii)
(f)(2)(i) of this AD.
(f)(4)(i) and (f)(4)(ii)
(f)(4)(i) and (f)(4)(ii)
(f)(5) of this AD.
(f)(5) of this AD.
(f)(3) of this AD.
(f)(2)(i) and (f)(2)(ii)
(f)(2)(i) and (f)(2)(ii)
(f)(4)(i) and (f)(4)(ii)
17JNP1
of this AD.
of this AD.
of this AD.
of this AD.
of this AD.
of this AD.
34233
Federal Register / Vol. 73, No. 117 / Tuesday, June 17, 2008 / Proposed Rules
TABLE 2.—CREDIT SERVICE BULLETINS—Continued
Airbus service bulletin
Revision level
Date
A340–55–4017 ..........
1 ...........................................................
February 12, 1997 ...............................
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, ANM–116, International
Branch, Transport Airplane Directorate, FAA,
1601 Lind Ave., SW, Renton, Washington,
98057–3356, telephone (425) 227–2797; 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
Corresponding paragraphs
(f)(4)(i) and (f)(4)(ii) of this AD.
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 2007–0278, dated November 5,
2007 [Corrected: November 8, 2007], and the
service bulletins in Table 3 of this AD, for
related information.
TABLE 3.—RELATED SERVICE BULLETINS
Airbus service bulletin
Revision level
A330–28–3082, including Appendix 01 .......................................................................................................
A330–28–3092, excluding Appendix 01 ......................................................................................................
A330–28–3101 .............................................................................................................................................
A330–55–3016 .............................................................................................................................................
A340–28–4073 .............................................................................................................................................
A340–28–4078 .............................................................................................................................................
A340–28–4097, including Appendix 01 .......................................................................................................
A340–28–4107, excluding Appendix 01 ......................................................................................................
A340–28–4118 .............................................................................................................................................
A340–55–4017 .............................................................................................................................................
Issued in Renton, Washington, on June 10,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–13568 Filed 6–16–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001–NM–237–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–200 and –300 Series
Airplanes
Federal Aviation
Administration, DOT.
ACTION: Supplemental notice of
proposed rulemaking; reopening of
comment period.
jlentini on PROD1PC65 with PROPOSALS
AGENCY:
SUMMARY: This document revises an
earlier proposed airworthiness directive
(AD), applicable to certain Boeing
VerDate Aug<31>2005
16:08 Jun 16, 2008
Jkt 214001
Model 767–200 and –300 series
airplanes. That proposed rule would
have required replacing certain doormounted escape slides and slide-raft
assemblies with new slide-raft
assemblies; replacing certain escape
system latches with new latches; and
modifying or replacing certain
counterbalance assemblies with new
counterbalance assemblies; as
applicable. This new action revises the
proposed rule by extending the
compliance time, adding requirements
to install a longer firing cable and test
the valve of the inflation trigger system
of the slide-raft, and, for certain
airplanes, adding procedures to adjust
the door counter balance systems. The
actions specified by this new proposed
AD are intended to prevent the escape
slides and slide-rafts of the forward and
mid-cabin entry and service doors from
being too steep for evacuation in the
event that the airplane rotates onto the
aft fuselage into the extreme tip-back
condition. In the extreme tip-back
condition, the forward and mid-cabin
exits could result in steeper sliding
angles, which could cause injury to
passengers and crewmembers during an
PO 00000
Frm 00032
Fmt 4702
Sfmt 4702
04
01
01
02
02
01
03
01
02
02
Date
August 3, 2007.
December 14, 2005.
October 11, 2006.
March 16, 2007.
March 8, 2007.
January 25, 2007.
July 3, 2007.
December 14, 2005.
July 10, 2007.
March 16, 2007.
emergency evacuation. This action is
intended to address the identified
unsafe condition.
DATES: Comments must be received by
July 14, 2008.
ADDRESSES: Submit comments in
triplicate to the Federal Aviation
Administration (FAA), Transport
Airplane Directorate, ANM–114,
Attention: Rules Docket No. 2001–NM–
237–AD, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356.
Comments may be inspected at this
location between 9 a.m. and 3 p.m.,
Monday through Friday, except Federal
holidays. Comments may be submitted
via fax to (425) 227–1232. Comments
may also be sent via the Internet using
the following address: 9-anmnprmcomment@faa.gov. Comments sent
via fax or the Internet must contain
‘‘Docket No. 2001–NM–237–AD’’ in the
subject line and need not be submitted
in triplicate. Comments sent via the
Internet as attached electronic files must
be formatted in Microsoft Word 97 or
2000 or ASCII text.
The service information referenced in
the proposed rule may be obtained from
Boeing Commercial Airplanes, P.O. Box
E:\FR\FM\17JNP1.SGM
17JNP1
]]>Agencies
[Federal Register Volume 73, Number 117 (Tuesday, June 17, 2008)]
[Proposed Rules]
[Pages 34228-34233]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-13568]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 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: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an original NPRM for the products listed
above. This action revises the original NPRM by expanding the scope.
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 July 14, 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: 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:
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-
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://
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
We proposed to amend 14 CFR part 39 with an earlier NPRM for the
specified products, which was published in the Federal Register on
March 30, 2007 (72 FR 15063). That earlier NPRM proposed to require
actions intended to address the unsafe condition for the products
listed above.
Since that NPRM was issued, we have determined that additional
bonding points must be modified and that the compliance time for
performing the action specified in paragraph (f)(4)(ii) of this
supplemental NPRM (increasing the distance between metallic parts on
the trimmable horizontal stabilizer (THS) trim tank) may be extended
for airplanes that are already compliant with certain requirements of
Airbus All Operators Telex (AOT) 55-03, dated August 22, 1996. In
addition, we have referred to the latest revisions of the service
bulletins as the appropriate sources of service information for
accomplishing certain actions in this supplemental NPRM. European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Community, has issued Airworthiness
Directive 2007-0278, dated November 5, 2007 [Corrected: November 8,
2007] (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. You may obtain further
information by examining the MCAI in the AD docket. 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 3,402 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 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
[[Page 34229]]
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 Trim Tank,
Installation of a bonding lead between the bonding tags
on the Jettison valve actuator and drive assembly.
This new AD supersedes EASA AD 2006-0322 taking over its
requirements and:
Mandates SB A330-28-3082 Revision 04 which introduces
an additional work for some bonding points which were omitted from
the center tank at original issue (action n[deg]2 [paragraph (f)(2)
of this AD]);
Mandates SB A340-28-4097 Revision 03 which introduces
an additional work by addition of electrical bondings omitted from
previous revisions (action n[deg]2);
Introduces an extension of the required compliance time
to perform action n[deg]4 for those aircraft already compliant with
AIRBUS AOT 55-03 dated 22 August 1996 (``solution A''), mandated by
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] AD F-
1996-178-049(B) R1 and DGAC AD F-1996-177-038(B) with a compliance
time of November 15th, 1996;
Refers to the latest revision of certain AIRBUS SBs.
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.
Relevant Service Information
Airbus has issued the service bulletins described in the following
table.
Airbus Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A330-28-3082, including 04 August 3, 2007.
Appendix 01.
A330-55-3016................ 02 March 16, 2007.
A340-28-4073................ 02 March 8, 2007.
A340-28-4078................ 01 January 25, 2007.
A340-28-4097, including 03 July 3, 2007.
Appendix 01.
A340-28-4118................ 02 July 10, 2007.
A340-55-4017................ 02 March 16, 2007.
------------------------------------------------------------------------
The actions described in the service information are intended to
correct the unsafe condition identified in the MCAI.
Comments
We have considered the following comments received on the earlier
NPRM.
Request to Use Latest Versions of Service Information
Air Transport Association, on behalf of its member U.S. Airways,
requests that we allow for the most recent revisions to the applicable
service bulletins to be used for compliance with the AD.
We agree. Airbus has revised the service bulletins described in the
following table.
Service Bulletins That Have Been Revised Since We Issued the NPRM
----------------------------------------------------------------------------------------------------------------
Revision level in Additional work
Airbus service bulletin New revision original NPRM necessary? Reason for revision
----------------------------------------------------------------------------------------------------------------
A330-28-3082............. Revision 04, Revision 02, Yes, for those Adds bonding points
including Appendix including Appendix modified in that were omitted
01, dated August 3, 01, dated August accordance with from the
2007. 11, 2006. original revision Accomplishment
(dated June 14, Instructions of
2004). the original
revision of the
service bulletin.
A330-55-3016............. Revision 02, dated Revision 1, dated No.................. Changes compliance
March 16, 2007. February 12, 1997. classification.
A340-28-4073............. Revision 02, dated Revision 01, dated No.................. Updates
March 8, 2007. October 9, 1998. effectivity,
revise jettison-
valve procedure,
and format
changes.
A340-28-4078............. Revision 01, dated Original Issue, No.................. Changes a kit
January 25, 2007. dated March 17, quantity.
2000.
A340-28-4097............. Revision 03, Revision 02, Yes, for those Includes
including Appendix including Appendix modified in instructions for
01, dated July 3, 01, dated August accordance with any electrical bonding
2007. 16, 2006. previous revision. of fuel pump
canisters for
certain airplanes
and for the water
drain valve
between rib 1 and
rib 2 for all
airplanes; adds
new airplane
configurations.
A340-28-4118............. Revision 02, dated Revision 01, dated No.................. Updates the
July 10, 2007. October 11, 2006. effectivity,
includes changes
that followed
validation of the
service bulletin.
A340-55-4017............. Revision 02, dated Revision 1, dated No.................. Changes compliance
March 16, 2007. February 12, 1997. classification.
----------------------------------------------------------------------------------------------------------------
As mentioned previously, we have revised the supplemental NPRM to
refer to the latest revisions of several service bulletins, added a
requirement to modify additional bonding points, and revised the
compliance time for
[[Page 34230]]
performing the action specified in paragraph (f)(4) of this
supplemental NPRM for airplanes that are already compliant with certain
requirements of Airbus AOT 55-03 (mentioned in Table 1 of this
Supplemental NPRM).
We have also revised the supplemental NPRM to give credit for
accomplishment of earlier revisions of service information that specify
that no additional work is necessary for airplanes on which the earlier
revision was accomplished; we have removed credit for accomplishment of
the original issue of Airbus Service Bulletin A330-28-3082; and we have
removed credit for accomplishment of any revision of Airbus Service
Bulletin A340-28-4097 that is earlier than Revision 03.
Explanation of Change to Certain Compliance Times
We have revised our month-based compliance times to correspond to
the amount of elapsed time between the effective date of the MCAI and
the compliance dates specified 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.
Certain changes described above expand the scope of the earlier
NPRM. As a result, we have determined that it is necessary to reopen
the comment period to provide additional opportunity for the public to
comment on this proposed AD.
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 28 products of U.S. registry. We also estimate that it
would take 670 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 $1,576,904, or $56,318 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2007-27739; Directorate Identifier 2006-NM-
250-AD.
Comments Due Date
(a) We must receive comments by July 14, 2008.
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) Air Transport Association (ATA) of America Codes 28: Fuel,
and 55: Stabilizers.
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 3,402 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 remove
the risks of fuel quantity indicator (FQI) and
[[Page 34231]]
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.
This new AD supersedes EASA AD 2006-0322 taking over its
requirements and:
Mandates SB A330-28-3082 Revision 04 which introduces
an additional work for some bonding points which were omitted from
the center tank at original issue (action n[deg]2 [paragraph (f)(2)
of this AD]);
Mandates SB A340-28-4097 Revision 03 which introduces
an additional work by addition of electrical bondings omitted from
previous revisions (action n[deg]2);
Introduces an extension of the required compliance time
to perform action n[deg]4 for those aircraft already compliant with
AIRBUS AOT 55-03 dated 22 August 1996 (``solution A''), mandated by
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] AD F-
1996-178-049(B) R1 and DGAC AD F-1996-177-038(B) with a compliance
time of November 15th, 1996;
Refers to the latest revision of certain AIRBUS SBs.
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.
Actions and Compliance
(f) Unless already done, do the actions in paragraphs (f)(1),
(f)(2), (f)(3), (f)(4), and (f)(5) of this AD for the applicable
airplanes identified in Table 1 of this AD.
Table 1.--Applicable Paragraphs by Airplane Model
----------------------------------------------------------------------------------------------------------------
Are affected by these
These airplane models-- Except airplanes-- paragraphs of this AD--
----------------------------------------------------------------------------------------------------------------
Model A330, A340-200, and A340-330 On which Airbus Modification 47634 has (f)(1).
airplanes. been embodied in production.
On which both Airbus (f)(2)(i), except as provided
Modifications 49135 and 49630 have been by paragraphs (f)(2)(ii) and
embodied in production. (f)(2)(iii) of this AD.
Both Airbus Modifications 51825
and 55118 have been embodied in
production.
That have been modified in-
service in accordance with both Airbus
Service Bulletin A330-28-3082, Revision
04, including Appendix 01, dated August
3, 2007; and Airbus Service Bulletin A330-
28-3101, Revision 01, dated October 11,
2006.
That have been modified in-
service in accordance with both Airbus
Service Bulletin A340-28-4097, Revision
03, including Appendix 01, dated July 3,
2007; and Airbus Service Bulletin A340-28-
4118, Revision 02, dated July 10, 2007.
Model A330 airplanes on which the On which both Airbus (f)(2)(ii) and (f)(2)(iii).
actions specified in Airbus Service Modifications 49135 and 49630 have been
Bulletin A330-28-3082, dated June embodied in production.
14, 2004, have been accomplished Both Airbus Modifications 51825
before the effective date of this and 55118 have been embodied in
AD; and Model A340-200 and A340-300 production.
airplanes on which the actions That have been modified in-
specified in Airbus Service Bulletin service in accordance with both Airbus
A340-28-4097, dated June 14, 2004, Service Bulletin A330-28-3082, Revision
Revision 01, dated March 3, 2005, or 04, including Appendix 01, dated August
Revision 02, dated August 16, 2006, 3, 2007, and Airbus Service Bulletin A330-
have been accomplished before the 28-3101, Revision 01, dated October 11,
effective date of this AD. 2006.
That have been modified in-
service in accordance with both Airbus
Service Bulletin A340-28-4097, Revision
03, including Appendix 01, dated July 3,
2007, and Airbus Service Bulletin A340-28-
4118, Revision 02, dated July 10, 2007.
Model A340-200 and A340-300 airplanes That have been modified in service by (f)(3).
that have the ACT embodied in Airbus Service Bulletin A340-28-4078,
production or in service (Airbus Revision 01, dated January 25, 2007.
Modification 42612, 44002, or 44005).
Model A340-200 and A340-300 airplanes On which Airbus Modification (f)(4)(i), except as provided
44252 has been embodied in production. by paragraph (f)(4)(ii) of
That have been modified in- this AD.
service in accordance with Airbus Service
Bulletin A340-55-4017.
Model A330-300, -301, -321, -322, - On which Airbus Modification (f)(4)(i), except as provided
341, -342 airplanes. 44252 has been embodied in production. by paragraph (f)(4)(ii) of
That have been modified in- this AD.
service in accordance with Airbus Service
Bulletin A330-55-3016.
[[Page 34232]]
Model A330-300, -301, -321, -322, - On which the improvement of the THS (f)(4)(ii).
341, -342 airplanes; and Model A340- lightning strike protection has already
200 and A340-300 airplanes. been performed before the effective date
of this AD in accordance with Airbus All
Operators Telex (AOT) 55-03, dated August
22, 1996 (``solution A''), mandated by
Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC) Airworthiness
Directive F-1996-178-049(B) R1, and DGAC
Airworthiness Directive F-1996-177-
038(B), with a compliance time of
November 15, 1996.
Model A340-200 and A340-300 airplanes On which Airbus Modification (f)(5).
46142 has been embodied in production.
That have been modified in-
service in accordance with Airbus Service
Bulletin A340-28-4073, Revision 02, dated
March 8, 2007.
----------------------------------------------------------------------------------------------------------------
(1) Within 24 months after the effective date of this AD, do 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 applicable 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) Do the requirements of paragraphs (f)(2)(i), (f)(2)(ii), and
(f)(2)(iii) of this AD, as applicable, at the times specified in
those paragraphs.
(i) For airplanes affected by this paragraph, as specified in
Table 1 of this AD: Within 24 months after the effective date of
this AD, modify the electrical bonding of the equipment installed in
fuel tanks, in accordance with both Airbus Service Bulletin A330-28-
3082, Revision 04, including Appendix 01, dated August 3, 2007, and
Airbus Service Bulletin A330-28-3101, Revision 01, dated October 11,
2006; or both Airbus Service Bulletin A340-28-4097, Revision 03,
including Appendix 01, dated July 3, 2007, and Airbus Service
Bulletin A340-28-4118, Revision 02, dated July 10, 2007; as
applicable.
(ii) For airplanes affected by this paragraph, as specified in
Table 1 of this AD: Within 24 months after the effective date of
this AD, modify the electrical bonding of the equipment installed in
fuel tanks, in accordance with Airbus Service Bulletin A330-28-3101,
Revision 01, dated October 11, 2006; or Airbus Service Bulletin
A340-28-4118, Revision 02, dated July 10, 2007; as applicable.
(iii) For airplanes affected by this paragraph, as specified in
Table 1 of this AD: Within 48 months after the effective date of
this AD, do the additional work specified in Airbus Service Bulletin
A330-28-3082, Revision 04, including Appendix 01, dated August 3,
2007; or Airbus Service Bulletin A340-28-4097, Revision 03,
including Appendix 01, dated July 3, 2007; in accordance with the
accomplishment instructions of those service bulletins, as
applicable.
(3) Within 24 months after the effective date of this AD, modify
the electrical bonding in the ACT in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A340-28-4078,
Revision 01, dated January 25, 2007.
(4) Within 24, months after the effective date of this AD, do
the requirements of paragraphs (f)(4)(i) and (f)(4)(ii), as
applicable.
(i) For airplanes affected by this paragraph, as specified in
Table 1 of this AD: Within 24 months after the effective date of
this AD, increase the distance between metallic parts on the THS
trim tank in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-55-3016, Revision 02, March 16, 2007;
or Airbus Service Bulletin A340-55-4017, Revision 02, dated March
16, 2007; as applicable.
(ii) For airplanes affected by this paragraph, as specified in
Table 1 of this AD: At the first THS removal from the aircraft done
for any reason after the effective date of this AD (e.g., fuselage
stress jacking, and repair) when the airplane is on a support tool
(lifting and resting point fittings must be installed), or at the
time of the first maintenance task that requires the use of THS
lifting and resting point fittings, whichever occurs earlier,
increase the distance between metallic parts on the THS trim tank in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-55-3016, Revision 02, March 16, 2007; or Airbus
Service Bulletin A340-55-4017, Revision 02, dated March 16, 2007; as
applicable.
(5) Within 24 months after the effective date of this AD,
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 02,
dated March 8, 2007.
(6) Actions done before the effective date of this AD in
accordance with the service bulletins listed in Table 2 of this AD
are acceptable for compliance with the corresponding requirements of
this AD.
Table 2.--Credit Service Bulletins
----------------------------------------------------------------------------------------------------------------
Corresponding
Airbus service bulletin Revision level Date paragraphs
----------------------------------------------------------------------------------------------------------------
A330-28-3082....................... 01...................... March 2, 2005........... (f)(2)(i) of this AD.
A330-28-3082....................... 02...................... August 11, 2006......... (f)(2)(i) of this AD.
A330-28-3082....................... 03...................... November 15, 2006....... (f)(2)(i) and
(f)(2)(ii) of this AD.
A330-28-3101....................... Original................ June 5, 2006............ (f)(2)(i) of this AD.
A330-55-3016....................... Original................ August 20, 1996......... (f)(4)(i) and
(f)(4)(ii) of this AD.
A330-55-3016....................... 1....................... February 12, 1997....... (f)(4)(i) and
(f)(4)(ii) of this AD.
A340-28-4073....................... Original................ May 14, 1998............ (f)(5) of this AD.
A340-28-4073....................... 01...................... October 9, 1998......... (f)(5) of this AD.
A340-28-4078....................... Original................ March 17, 2000.......... (f)(3) of this AD.
A340-28-4118....................... Original................ June 5, 2006............ (f)(2)(i) and
(f)(2)(ii) of this AD.
A340-28-4118....................... 01...................... October 11, 2006........ (f)(2)(i) and
(f)(2)(ii) of this AD.
A340-55-4017....................... Original................ August 20, 1996......... (f)(4)(i) and
(f)(4)(ii) of this AD.
[[Page 34233]]
A340-55-4017....................... 1....................... February 12, 1997....... (f)(4)(i) and
(f)(4)(ii) of this AD.
----------------------------------------------------------------------------------------------------------------
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, ANM-116, International Branch,
Transport Airplane Directorate, FAA, 1601 Lind Ave., SW, Renton,
Washington, 98057-3356, telephone (425) 227-2797; fax (425) 227-
1149. Before using any approved AMOC on any airplane to which the
AMOC applies, notify your appropriate principal inspector (PI) in
the FAA Flight Standards District Office (FSDO), or lacking a PI,
your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI European Aviation Safety Agency (EASA)
Airworthiness Directive 2007-0278, dated November 5, 2007
[Corrected: November 8, 2007], and the service bulletins in Table 3
of this AD, for related information.
Table 3.--Related Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A330-28-3082, including 04 August 3, 2007.
Appendix 01.
A330-28-3092, excluding 01 December 14, 2005.
Appendix 01.
A330-28-3101................ 01 October 11, 2006.
A330-55-3016................ 02 March 16, 2007.
A340-28-4073................ 02 March 8, 2007.
A340-28-4078................ 01 January 25, 2007.
A340-28-4097, including 03 July 3, 2007.
Appendix 01.
A340-28-4107, excluding 01 December 14, 2005.
Appendix 01.
A340-28-4118................ 02 July 10, 2007.
A340-55-4017................ 02 March 16, 2007.
------------------------------------------------------------------------
Issued in Renton, Washington, on June 10, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-13568 Filed 6-16-08; 8:45 am]
BILLING CODE 4910-13-P
