FR Doc E8-13568

[Federal Register: June 17, 2008 (Volume 73, Number 117)]
[Proposed Rules]
[Page 34228-34233]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17jn08-13]

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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.

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:

[[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.

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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