[Federal Register: May 7, 2009 (Volume 74, Number 87)]
[Proposed Rules]
[Page 21274-21278]
[DOCID:fr07my09-14]

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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-174-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A310-203 and -222
Airplanes and Model A300 B4-620 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. 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:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03,
amendment 39-5871] was issued to prevent development of damage,
which was discovered during [a] fatigue test in the attachment
angles of the rear pressure bulkhead (fuselage frame 80/82).
    Following the life extension activities linked to the A310
program, the interval of inspection for A310-200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000 FC * * *.
    Some stress analysis conducted in the frame of the life
extension activities of the A300-600 program leads the manufacturer
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.

The unsafe condition is cracking in the attachment angles of the rear
pressure bulkhead, which could result in failure of the rear pressure
bulkhead. 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 June 8, 2009.

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:<PHONE_NUMBER>.
     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.
    For service information identified in this proposed AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail<EMAIL_ADDRESS>Internet http://
www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For information on the availability of
this material at the FAA, call<PHONE_NUMBER> or<PHONE_NUMBER>.

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<PHONE_NUMBER>) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax<PHONE_NUMBER>.

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-2009-0431;
Directorate Identifier 2007-NM-174-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

    On March 3, 1988, we issued AD 88-06-03, Amendment 39-5871 (53 FR
7730, March 10, 1988). That AD required actions intended to address an
unsafe condition on the products listed above.
    Since we issued AD 88-06-03, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, advised that, due to life extension activities
linked to the A310 program and stress analysis conducted in the frame
of the life extension activities of the A300-600 program, the
repetitive inspection interval for the attachment angles of the rear
pressure bulkhead has been reduced from 12,000 flight cycles to 9,000
flight cycles for Model A310-203 and -222 airplanes and Model A300 B4-
620 airplanes.
    EASA has issued Airworthiness Directive 2007-0297R1, dated
September 17, 2008 (referred to after this as ``the MCAI''), to correct
an unsafe condition for the specified products. The MCAI states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03] was
issued to prevent development of damage, which was discovered during
[a] fatigue test in the attachment angles of the rear pressure
bulkhead (fuselage frame 80/82).
    Following the life extension activities linked to the A310
program, the interval of inspection for A310-200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the
issuance of EASA

AD 2007-0157, superseding DGAC France AD 86-102-74(B).
    Some stress analysis conducted in the frame of the life
extension activities of the A300-600 program leads the manufacturer
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.
    EASA AD 2007-02977 superseded EASA AD 2007-0157, retaining for
A310 aircraft the requirements of EASA AD 2007-0157 and requiring
the application of Airbus Service Bulletin (SB) A300-53-6005
Revision 4 on Airbus A300-600 aircraft, reducing the inspection
interval from 12000 FC to 9000 FC.
    [EASA] AD [2007-0297] has been revised to remove an
inappropriate reference regarding the normal inspection program from
the Compliance section, Note 3.

    The unsafe condition is cracking in the attachment angles of the
rear pressure bulkhead, which could result in failure of the rear
pressure bulkhead. The required actions include a modification of the
rear pressure bulkhead to improve the fatigue life of the attachment
angles at frame (FR) 80/82, and, for certain airplanes, repetitive
inspections for cracks in the rear pressure bulkhead and repair if
necessary.
    The modification includes installing additional attachment angles
on the circumference of FR 80/82; installing a filler; installing
additional supports between the aft pressure bulkhead and FR 80/82;
installing an additional frame stiffener and support between the aft
pressure bulkhead and FR 79 at stringer (STGR) 13; modifying the aft
lavatories; applying surface protection to the modified area of the aft
pressure bulkhead; modifying, reidentifying, and installing the heat
and sound insulation in the area of STGR 9 and STGR 13 and between FR
79 and FR 80/82, left and right; and for certain airplanes, doing
related investigative and corrective actions if necessary.
    The related investigative action is doing a visual inspection
around the entire circumference between FR 80/82 and the aft pressure
bulkhead for damaged filler. The corrective action is removing any
damaged filler and the adjacent area around the damage.
    We have removed Airbus Model A310-221 airplanes having serial
numbers 295 and 0306 from the applicability of this proposed AD. The
MCAI does not include Airbus Model A310-221 in its applicability as it
has been determined that those airplanes are not subject to the
identified unsafe condition addressed by the relevant service
information listed below. However, those airplanes are subject to
certain other actions required by AD 2006-22-03, amendment 39-14800 (71
FR 62890, October 27, 2006), as specified in the ``Other Relevant
Rulemaking'' paragraph below.
    You may obtain further information by examining the MCAI in the AD
docket.

Relevant Service Information

    Airbus has issued the following service bulletins:
     Airbus Service Bulletin A310-53-2024, Revision 05, dated
October 13, 2006.
     Airbus Service Bulletin A310-53-2025, Revision 06, dated
August 3, 2006.
     Airbus Service Bulletin A300-53-6005, Revision 04, dated
July 18, 2007.
     Airbus Service Bulletin A300-53-6006, Revision 3, dated
March 24, 1989.
    The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.

Other Relevant Rulemaking

    We issued AD 2006-22-03 to prevent corrosion on the inner rim angle
and cleat profile splice of the aft pressure bulkhead. That AD applies
to Airbus Model A310 and A300-600 series airplanes, except airplanes on
which Airbus Modification 6788 has been incorporated in production.
That AD requires modification of the aft pressure bulkhead for improved
corrosion protection and drainage, and a related concurrent action.
    The related concurrent action specified in paragraph (h) of AD
2006-22-03 is a modification of the aft pressure bulkhead in accordance
with Airbus Service Bulletin A310-53-2025, Revision 06, dated August 3,
2006, and Airbus Service Bulletin A300-53-6006, Revision 3, dated March
24, 1989, as applicable (which is the same modification that this NPRM
would require). The compliance time to do the modification specified in
paragraph (h) of AD 2006-22-03 is prior to or concurrent with the
actions specified in paragraph (g) of AD 2006-22-03; the compliance
time for paragraph (g) of AD 2006-22-03 is within 60 months after
December 1, 2006 (the effective date of AD 2006-22-03). This NPRM would
supersede AD 2006-22-03 to require that the modification of the aft
pressure bulkhead be done before the accumulation of 12,000 total
flight cycles since first flight, or within 1,500 flight cycles,
whichever occurs later.
    Certain airplanes affected by AD 2006-22-03 are also affected by
this NPRM, and therefore, the requirements of this NPRM would
necessitate that some operators do the modification required by
paragraph (h) of AD 2006-22-03 early. Accomplishing the modification
within the compliance time specified in paragraph (f)(2) of this NPRM
is necessary to address cracking in the attachment angles of the rear
pressure bulkhead, which could result in failure of the rear pressure
bulkhead.

Other Corrosion and Fatigue ADs

    Operators should note that we have also issued other ADs that
involve work in the area of the aft pressure bulkhead. We issued those
ADs to address unsafe conditions related to either corrosion or fatigue
in the aft pressure bulkhead. The following table, titled ``Other
relevant rulemaking,'' provides an overview of all those issued ADs.

                                        Table--Other Relevant Rulemaking
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                                       Refers to Airbus Service
                AD--                          Bulletin--                Requiring--            Addressing--
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88-06-03 (would be superseded by     A310-53-2024, Revision 1,    Repetitive inspections  Fatigue.
 this proposed AD).                   dated June 20, 1986; and
                                      Revision 3, February 17,
                                      1987.
                                     A310-53-2025, original       Modification..........  Fatigue.
                                      issue, dated April 21,
                                      1986; and Revision 3,
                                      April 7, 1987.
98-19-22, amendment 39-10763 (63 FR  A300-53-6066, dated October  Repetitive inspections  Corrosion.
 49656, September 17, 1998)           16, 1996; and Revision 01,
 (superseded by AD 2005-26-16).       dated March 11, 1998.
                                     A310-53-2092, dated October  Repetitive inspections  Corrosion.
                                      16, 1996; and Revision 01,
                                      dated March 11, 1998.
2005-26-16, amendment 39-14437 (70   A300-53-6136, Revision 01,   Repetitive inspections  Corrosion.
 FR 77307, December 30, 2005).        dated July 18, 2005.
                                     A310-53-2114, Revision 01,   Repetitive inspections  Corrosion.
                                      dated September 1, 2005.

2006-22-03, amendment 39-14800 (71   A300-53-6017, Revision 02,   Modification..........  Corrosion.
 FR 62890, October 27, 2006).         dated February 25, 2004.
                                     A310-53-2036, Revision 02,   Modification..........  Corrosion.
                                      dated February 25, 2004.
                                     A300-53-6006, Revision 3,    Modification..........  Fatigue.
                                      March 24, 1989.
                                     A310-53-2025, Revision 06,   Modification..........  Fatigue.
                                      August 3, 2006.
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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.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD
would affect about 32 products of U.S. registry. We also estimate that
it would take 668 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Required parts would cost about $15,322 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 $2,200,384, or $68,762 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, Incorporation by
reference, 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 removing Amendment 39-5871 (53 FR
7730, March 10, 1988) and adding the following new AD:

Airbus: Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-
174-AD.

Comments Due Date

    (a) We must receive comments by June 8, 2009.

Affected ADs

    (b) The proposed AD supersedes AD 88-06-03, Amendment 39-5871.

Applicability

    (c) This AD applies to Airbus Model A310-203 and -222 airplanes,
and Model A300 B4-620 airplanes; certificated in any category; all
serial numbers except airplanes on which Airbus Modification 05526
has been incorporated in production.

Subject

    (d) Air Transport Association (ATA) of America Code 53:
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:
    DGAC (Direction G[eacute]n[eacute]rale de l'Aviation Civile)
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03,
amendment 39-5871] was issued to prevent development of damage,
which was discovered during [a] fatigue test in the attachment
angles of the rear pressure bulkhead (fuselage frame 80/82).
    Following the life extension activities linked to the A310
program, the interval of inspection for A310-200 aircraft series was
reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the
issuance of EASA AD 2007-0157, superseding DGAC France AD 86-102-
74(B).
    Some stress analysis conducted in the frame of the life
extension activities of the A300-600 program leads the manufacturer
to

reduce as well the interval of inspection applicable to A300B4-620
and A300C4-620 aircraft models.
    EASA AD 2007-0297 superseded EASA AD 2007-0157, retaining for
A310 aircraft the requirements of EASA AD 2007-0157 and requiring
the application of Airbus Service Bulletin (SB) A300-53-6005
Revision 4 on Airbus A300-600 aircraft, reducing the inspection
interval from 12000 FC to 9000 FC.
    [EASA] AD [2007-0297] has been revised to remove an
inappropriate reference regarding the normal inspection program from
the Compliance section, Note 3.
    The unsafe condition is cracking in the attachment angles of the
rear pressure bulkhead, which could result in failure of the rear
pressure bulkhead. The required actions include a modification of
the rear pressure bulkhead to improve the fatigue life of the
attachment angles at frame (FR) 80/82; applicable related
investigative and corrective actions; and, for certain airplanes,
repetitive inspections for cracks in the rear pressure bulkhead and
repair if necessary.

Requirements of This AD: Actions and Compliance

    (f) Unless already done, do the following actions.

Modification

    (1) Except as required by paragraph (f)(2) of this AD: Before
the accumulation of 12,000 total flight cycles since first flight,
or within 1,500 flight cycles after the effective date of this AD,
whichever occurs later, modify the aft pressure bulkhead to improve
the fatigue life of the attachment angles at frame 80/82 and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-6006, Revision 3, dated March 24, 1989; or Airbus
Service Bulletin A310-53-2025, Revision 06, dated August 3, 2006; as
applicable. Do all applicable related investigative and corrective
actions before further flight.
    (2) For airplanes identified in paragraph (c) of AD 2006-22-03,
amendment 39-14800: At the earlier of the compliance times specified
in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions
specified in paragraph (f)(1) of this AD.
    (i) Before the accumulation of 12,000 total flight cycles since
first flight, or within 1,500 flight cycles after the effective date
of this AD, whichever occurs later.
    (ii) At the compliance time specified in paragraph (h) of AD
2006-22-03.

Inspections and Corrective Action

    (3) For airplanes on which the modification required by
paragraph (f)(1) or (f)(2) of this AD is done after the accumulation
of 6,000 total flight cycles since first flight: At the times
specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an
eddy current inspection for any cracking in the critical area of the
rear pressure bulkhead between stringers 8 and 18, and repair all
cracking before further flight, in accordance with the
Accomplishment Instructions of Airbus A300-53-6005, Revision 04,
dated July 18, 2007; or Airbus Service Bulletin A310-53-2024,
Revision 05, dated October 13, 2006; as applicable.
    (i) Before or concurrently with the modification required by
paragraph (f)(1) or (f)(2) of this AD, as applicable; and
    (ii) Before the accumulation of 18,000 total flight cycles since
first flight, or within 1,500 flight cycles after the effective date
of this AD, whichever occurs later; and thereafter at intervals not
to exceed 9,000 flight cycles.
    (4) For airplanes on which the modification required by
paragraph (f)(1) or (f)(2) of this AD is done at or before the
accumulation of 6,000 total flight cycles since first flight: Before
the accumulation of 18,000 total flight cycles since first flight,
or within 1,500 flight cycles after the effective date of this AD,
whichever occurs later, do an eddy current inspection for any
cracking in the critical area of the rear pressure bulkhead between
stringers 8 and 18, and repair all cracking before further flight,
in accordance with the Accomplishment Instructions of Airbus A300-
53-6005, Revision 04, dated July 18, 2007; or Airbus Service
Bulletin A310-53-2024, Revision 05, dated October 13, 2006; as
applicable. Repeat the inspection thereafter at intervals not to
exceed 9,000 flight cycles.
    (5) Modifications done before the effective date of this AD in
accordance with the service bulletins identified in Table 1 of this
AD are acceptable for compliance with the requirements of paragraph
(f)(1) and (f)(2) of this AD.

                          Table 1--Modifications Done Using Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                     Airbus Service
              Model                     Bulletin            Revision                       Dated
----------------------------------------------------------------------------------------------------------------
A300 B4-620 airplanes............       A300-53-6006  Original...........  May 6, 1986.
                                        A300-53-6006  1..................  September 19, 1986.
                                        A300-53-6006  2..................  August 11, 1988.
A310-203 and -222 airplanes......       A310-53-2025  Original...........  April 21, 1986.
                                        A310-53-2025  1..................  September 19, 1986.
                                        A310-53-2025  2..................  February 16, 1987.
                                        A310-53-2025  3..................  April 7, 1987.
                                        A310-53-2025  4..................  October 20, 1987.
                                        A310-53-2025  5..................  March 24, 1989.
----------------------------------------------------------------------------------------------------------------

    (6) Inspections done before the effective date of this AD in
accordance with the service bulletins identified in Table 2 of this
AD are acceptable for compliance with the requirements of paragraph
(f)(3) of this AD.

                            Table 2--Inspections Done With Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                     Airbus Service
              Model                     Bulletin            Revision                       Dated
----------------------------------------------------------------------------------------------------------------
A300 B4-620 airplanes............       A300-53-6005  Original...........  May 6, 1986.
                                        A300-53-6005  1..................  June 20, 1986.
                                        A300-53-6005  2..................  September 22, 1986.
                                        A300-53-6005  3..................  April 22, 1987.
A310-203 and -222 airplanes......       A310-53-2024  Original...........  April 21, 1986.
                                        A310-53-2024  1..................  June 20, 1986.
                                        A310-53-2024  2..................  October 2, 1986.
                                        A310-53-2024  3..................  February 17, 1987.
                                        A310-53-2024  4..................  February 2, 1988.
----------------------------------------------------------------------------------------------------------------

    (7) Modification of the aft pressure bulkhead to improve the
fatigue life of the attachment angles at frame (FR) 80/82 in
accordance with paragraph (h) of AD 2006-22-03, is acceptable for
compliance with the corresponding requirement of paragraphs (f)(1)
and (f)(2) of this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information
as follows: This AD includes a compliance time specified in
paragraph (f)(2) of this AD for airplanes that are also affected by
AD 2006-22-03. We realize that the requirements of this AD will
necessitate that some operators do the modification required by
paragraph (h) of AD 2006-22-03 early. However, accomplishing the
modification within the compliance time specified in this AD is
required to address cracking in the attachment angles of the rear
pressure bulkhead, which could result in failure of the rear
pressure bulkhead.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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: Tom
Stafford, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
    (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 EASA Airworthiness Directive 2007-0297R1,
dated September 17, 2008, and the service bulletins listed in Table
3 of this AD, for related information.

                                       Table 3--Related Service Bulletins
----------------------------------------------------------------------------------------------------------------
            Airbus Service Bulletin                   Revision                          Date
----------------------------------------------------------------------------------------------------------------
A310[dash]53[dash]2024.........................                 05  October 13, 2006.
A310[dash]53[dash]2025.........................                 06  August 3, 2006.
A300[dash]53[dash]6005.........................                 04  July 18, 2007.
A300[dash]53[dash]6006.........................                  3  March 24, 1989.
----------------------------------------------------------------------------------------------------------------

    Issued in Renton, Washington, on May 1, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-10614 Filed 5-6-09; 8:45 am]

BILLING CODE 4910-13-P


[Federal Register: January 19, 2007 (Volume 72, Number 12)]
[Notices]
[Page 2505]
[DOCID:fr19ja07-40]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. ER07-233-001]

Occidental Power Services, Inc.; Notice of Filing

January 11, 2007.
    Take notice that on January 10, 2007, Occidental Power Services,
Inc. tendered for filing an amendment to its November 17, 2006 rate
schedule amendment filing.
    Any person desiring to intervene or to protest this filing must
file in accordance with Rules 211 and 214 of the Commission's Rules of
Practice and Procedure (18 CFR 385.211, 385.214). Protests will be
considered by the Commission in determining the appropriate action to
be taken, but will not serve to make protestants parties to the
proceeding. Any person wishing to become a party must file a notice of
intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed on or before the comment date.
Anyone filing a motion to intervene or protest must serve a copy of
that document on the Applicant and all the parties in this proceeding.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper using the ``eFiling'' link at http://www.ferc.gov.
 Persons unable to file electronically should submit an

original and 14 copies of the protest or intervention to the Federal
Energy Regulatory Commission, 888 First Street, NE., Washington, DC
20426.
    This filing is accessible online at http://www.ferc.gov, using the

``eLibrary'' link and is available for review in the Commission's
Public Reference Room in Washington, DC. There is an ``eSubscription''
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    Comment Date: 5 p.m. Eastern Time on January 17, 2007.

Magalie R. Salas,
Secretary.
 [FR Doc. E7-664 Filed 1-18-07; 8:45 am]

BILLING CODE 6717-01-P