[Federal Register Volume 73, Number 117 (Tuesday, June 17, 2008)]
[Proposed Rules]
[Pages 34228-34233]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-13568]


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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.

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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 http://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 http://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 http://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]
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