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.

EFFECTIVE DATE: 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 Number 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 [degrees] 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 [degrees] 2);

. Introduces an extension of the required compliance time to perform action n [degrees] 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            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
Airbus service New revision   Revision level Additional     Reason for
bulletin                      in original    work           revision
                              NPRM           necessary?
A330-28-3082   Revision 04,   Revision 02,   Yes, for those Adds bonding
               including      including      modified in    points that were
               Appendix 01,   Appendix 01,   accordance     omitted from the
               dated August   dated August   with original  Accomplishment
               3, 2007        11, 2006       revision       Instructions of
                                             (dated June    the original
                                             14, 2004)      revision of the
                                                            service bulletin.
A330-55-3016   Revision 02,   Revision 1,    No             Changes
               dated March    dated February                compliance
               16, 2007       12, 1997                      classification.
A340-28-4073   Revision 02,   Revision 01,   No             Updates
               dated March 8, dated October                 effectivity,
               2007           9, 1998                       revise jettison-
                                                            valve procedure,
                                                            and format
                                                            changes.
A340-28-4078   Revision 01,   Original       No             Changes a kit
               dated January  Issue, dated                  quantity.
               25, 2007       March 17, 2000
A340-28-4097   Revision 03,   Revision 02,   Yes, for those Includes
               including      including      modified in    instructions for
               Appendix 01,   Appendix 01,   accordance     electrical
               dated July 3,  dated August   with any       bonding of fuel
               2007           16, 2006       previous       pump canisters
                                             revision       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,   Revision 01,   No             Updates the
               dated July 10, dated October                 effectivity,
               2007           11, 2006                      includes changes
                                                            that followed
                                                            validation of the
                                                            service bulletin.
A340-55-4017   Revision 02,   Revision 1,    No             Changes
               dated March    dated February                compliance
               16, 2007       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 Number 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.

[Section] 39.13 [Amended]

2. The FAA amends [Section] 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 Number 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 [degrees] 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 [degrees] 2);

. Introduces an extension of the required compliance time to perform action n [degrees] 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.

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
Model A330, A340-200, and On which Airbus           (f)(1).
A340-330 airplanes        Modification 47634 has
                          been embodied in
                          production.
                          . On which both Airbus    (f)(2)(i), except as
                          Modifications 49135 and   provided by paragraphs
                          49630 have been embodied  (f)(2)(ii) and
                          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   . On which both Airbus    (f)(2)(ii) and
which the actions         Modifications 49135 and   (f)(2)(iii).
specified in Airbus       49630 have been embodied
Service Bulletin          in production.
A330-28-3082, dated June  . Both Airbus
14, 2004, have been       Modifications 51825 and
accomplished before the   55118 have been embodied
effective date of this    in production.
AD; and Model A340-200    . That have been modified
and A340-300 airplanes on in-service in accordance
which the actions         with both Airbus Service
specified in Airbus       Bulletin A330-28-3082,
Service Bulletin          Revision 04, including
A340-28-4097, dated June  Appendix 01, dated August
14, 2004, Revision 01,    3, 2007, and Airbus
dated March 3, 2005, or   Service Bulletin
Revision 02, dated August A330-28-3101, Revision
16, 2006, have been       01, dated October 11,
accomplished before the   2006.
effective date of this AD . 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        That have been modified   (f)(3).
A340-300 airplanes that   in service by Airbus
have the ACT embodied in  Service Bulletin
production or in service  A340-28-4078, Revision
(Airbus Modification      01, dated January 25,
42612, 44002, or 44005)   2007.
Model A340-200 and        . On which Airbus         (f)(4)(i), except as
A340-300 airplanes        Modification 44252 has    provided by paragraph
                          been embodied in          (f)(4)(ii) of this AD.
                          production.
                          . That have been modified
                          in-service in accordance
                          with Airbus Service
                          Bulletin A340-55-4017.
Model A330-300, -301,     .  On which Airbus        (f)(4)(i), except as
-321, -322, -341, -342    Modification 44252 has    provided by paragraph
airplanes                 been embodied in          (f)(4)(ii) of this AD.
                          production.
                          . That have been modified
                          in-service in accordance
                          with Airbus Service
                          Bulletin A330-55-3016.
Model A330-300, -301,     On which the improvement  (f)(4)(ii).
-321, -322, -341, -342    of the THS lightning
airplanes; and Model      strike protection has
A340-200 and A340-300     already been performed
airplanes                 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.
Model A340-200 and        . On which Airbus         (f)(5).
A340-300 airplanes        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.

(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
Airbus service     Revision level     Date               Corresponding
bulletin                                                 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.
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

Vol. 73, No. 117

14 CFR Part 39; [Docket No. FAA-2007-27739; Directorate Identifier 2006-NM- 250-AD]; RIN 2120-AA64

Proposed Rules

ADDRESSES: Use one of the following addresses to submit comments on this proposed AD.

. DOT Docket Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.

. Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.

. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

. Fax: (202) 493-2251.

. Hand Delivery: Room W12-140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer International Branch, ANM-116, FAA, International Branch, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: We invite you to submit any relevant written data, views, or arguments regarding this proposal. Send your comments to an address listed in the ADDRESSES section. Include the docket number "Docket No. FAA-2007-27715; Directorate Identifier 2006-NM-140-AD" at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this supplemental NPRM. We will

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consider all comments received by the closing date and may amend this supplemental NPRM in light of those comments.

We will post all comments submitted, without change, to http://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477- 78), or you may visit http://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647-5527) is located on the ground level of the West Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them.

Discussion

We proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) with a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2006-09-07, amendment 39-14577 (71 FR 25919, May 3, 2006). The existing AD applies to all Airbus Model A330- 200, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and A340-642 airplanes. The first supplemental NPRM was published in the Federal Register on August 16, 2007 (72 FR 45965). The original NPRM proposed to revise the ALS, for all affected airplanes, by adding new Airworthiness Limitations Items (ALIs) to incorporate service life limits for certain items and inspections to detect fatigue cracking, accidental damage, or corrosion in certain structures, in accordance with the revised ALS of the Instructions for Continued Airworthiness (ICA). The first supplemental NPRM proposed to add airplanes, add new requirements, and include more restrictive compliance thresholds and intervals.

Actions Since First Supplemental NPRM Was Issued

Since we issued the first supplemental NPRM, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, issued EASA airworthiness directive 2008-0023, dated February 6, 2008.

The EASA advises that Airbus has revised Document AI/SE-M4/95A.0089/97, "A330 Airworthiness Limitation Items (ALI)," from Issue 14, dated October 10, 2005, to Issue 15, dated March 26, 2007, to add a new weight variant configuration and include more restrictive compliance thresholds and intervals.

Incorporating this revision into the ALS of the Instructions for Continued Airworthiness is intended to ensure the continued structural integrity of these airplanes.

Explanation of Additional Changes to the First Supplemental NPRM

For standardization purposes, we have revised this AD in the following ways:

We have revised paragraph (i) of this AD to specify that no alternative inspections/limitation tasks or inspection/limitation task intervals may be used unless the inspections/limitation tasks or inspection/limitation task intervals are part of a later approved revision of the documents specified in paragraphs (h)(1) and (h)(2) of this AD, as applicable, or unless they are approved as an alternative method of compliance (AMOC). Inclusion of this paragraph in the AD is intended to ensure that the AD-mandated airworthiness limitations changes are treated the same as the airworthiness limitations issued with the original type certificate.

We have simplified the language in Note 1 of this AD to clarify that an operator must request approval for an AMOC if the operator cannot accomplish the required inspections because an airplane has been previously modified, altered, or repaired in the areas addressed by the required inspections.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

The changes discussed above expand the scope of the first supplemental NPRM; therefore, we have determined that it is necessary to reopen the comment period to provide additional opportunity for public comment on this second supplemental NPRM.

Costs of Compliance

This proposed AD would affect about 41 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD.

     Estimated Costs
Action            Work hour Average   Parts     Cost per  Number of Fleet
                            labor               airplane  U.S.-re-  cost
                            rate per                      gistered
                            hour                          airplanes
Revise the ALS,   1         $80      None      $80      20        $1,600
required by AD
2006-09-07
Revise the ALS,   1         80        None      80        41        3,280
new proposed
action

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.

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Regulatory Findings

We have 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 that the 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 supplemental NPRM and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation.

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.

[Section] 39.13 [Amended]

2. The Federal Aviation Administration (FAA) amends [Section] 39.13 by removing amendment 39-14577 (71 FR 25919, May 3, 2006) and adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-27715; Directorate Identifier 2006-NM-140-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by July 28, 2008.

Affected ADs

(b) This AD supersedes AD 2006-09-07.

Applicability

(c) This AD applies to all Airbus Model A330 and A340 airplanes, certificated in any category.

Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane.

Unsafe Condition

(d) This AD results from the issuance of new and more restrictive service life limits and structural inspections based on fatigue testing and in-service findings. We are issuing this AD to detect and correct fatigue cracking, accidental damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane.

Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Restatement of Requirements of AD 2006-09-07

Airworthiness Limitations Revision

(f) Within 3 months after June 7, 2006 (the effective date of AD 2006-09- 07): Revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness by incorporating into the ALS the documents in paragraphs (f)(1) and (f)(2) of this AD, as applicable, until paragraph (h) of this AD is accomplished.

(1) Airbus Document AI/SE-M4/95A.0089/97, "A330 Airworthiness Limitations Items," Issue 12, dated November 1, 2003, as specified in Section 9-2 of the Airbus A330 Maintenance Planning Document (MPD).

(2) Section 9-1, "Life limits/Monitored parts," Revision 05, dated April 7, 2005, of the Airbus A330 and A340 MPDs.

(g) Except as provided by paragraph (h) or (j) of this AD: After the actions in paragraph (f) of this AD have been accomplished, no alternative inspections or inspection intervals may be approved for the structural elements specified in the documents listed in paragraph (f) of this AD.

New Requirements of This AD

ALS Revision

(h) Within 3 months after the effective date of this AD: Revise the ALS of the Instructions for Continued Airworthiness to incorporate the documents specified in paragraphs (h)(1) and (h)(2) of this AD, as applicable. Accomplishing the revision in this paragraph terminates the requirements in paragraph (f) of this AD.

(1) Airbus Document AI/SE-M4/95A.0089/97, "A330 Airworthiness Limitation Items (ALI)," Issue 15, dated March 26, 2007; or Airbus Document AI/SE- M4/95A.0051/97, "A340 Airworthiness Limitations Items," Issue 10, dated February 1, 2007.

(2) Sub-part 1-2 "Life Limits," and Sub-part 1-3 "Demonstrated Fatigue Lives," of Airbus A330 or A340 ALS Part 1, "Safe Life Airworthiness Limitation Items," Revision 01, dated March 30, 2007, as applicable.

(i) After accomplishing the actions specified in paragraph (h) of this AD, no alternative inspections/limitation tasks or inspection/limitation task intervals may be used unless the inspections/limitation tasks or inspection/limitation task intervals are part of a later approved revision of the documents specified in paragraphs (h)(1) and (h)(2) of this AD, as applicable, that is approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or unless the inspection/limitation task or inspection/limitation task interval is approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD.

Alternative Methods of Compliance (AMOCs)

(j)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

Related Information

(k) European Aviation Safety Agency airworthiness directives 2008-0023, dated February 6, 2008, 2007-0133, dated May 11, 2007, and 2007-0158, dated June 4, 2007; also address the subject of this AD.

Issued in Renton, Washington, on June 13, 2008.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. E8-14480 Filed 6-25-08; 8:45 am]

BILLING CODE 4910-13-P

Vol. 73, No. 124

14 CFR Part 39; [Docket No. FAA-2007-27715; Directorate Identifier 2006-NM- 140-AD]; RIN 2120-AA64

Proposed Rules

The Sultan and his entourage arrived by a special Airbus A340-200 aircraft at Halim Perdanakusuma Airport in East Jakarta at 10 on Tuesday morning.

His entourage was also made up of, among others, Foreign and Trade Affairs Minister HE Datin Pehin Dato LIm Jock Seng, Culture and Youth Affairs Minister Pehin Mej-en Dato Haji Awang Mohammad, Deputy Foreign Affairs Minister Datin Tan Bee Yong, and the country's ambassador to Indonesia Dato Hajah Husin.

After the reception ceremony, President Yudhoyono and Sultan Hassanal Bolkiah were to hold a bilateral meeting for about 45 minutes.

Afterwards, the two leaders would witness the signing of a memorandum of understanding (MoU) on cultural cooperation between the two countries by Indonesian Culture and Tourism Minister Jero Wacik and Bruneian Minister for Culture, Youth and Sports Affairs Dato Haji Awang Mohammad.

During his three-day visit to Indonesia, the sultan is scheduled to play badminton at the Indonesian Badminton Association (PBSI) sport hall in Cipayung, East Jakarta, on Tuesday and Wednesday afternoon.

And at 7 on Wednesday morning, Sultan Bolkiah and President Yudhoyono would go jogging around the National Defense Forces (TNI) Headquarters building in Cipayung before witnessing a hostage-rescuing demonstration by members of the Indonesian Air Force's elite unit, Bravo-90.