[Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)]
[Rules and Regulations]
[Pages 27220-27227]
[FR Doc No: 2011-10684]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1275; Directorate Identifier 2010-NM-091-AD;
Amendment 39-16688; AD 2011-10-07]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCA I) 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 Airworthiness Directive (AD) 1992-106-132(B) * * * was issued
to require a set of inspection- and modification tasks which
addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation
Regulation] 25-571 requirements related to damage-tolerance and
fatigue evaluation of structure.
* * * * *
The unsafe condition is reduced structural integrity of the wings. We
are issuing this AD to require actions to correct the unsafe condition
on these products.

DATES: This AD becomes effective June 15, 2011.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 15,
2011.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT:  Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on January 3, 2011 (76
FR 34). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France Airworthiness Directive (AD) 1992-106-132(B) original issue
up to revision 7 was issued to require a set of inspection- and
modification tasks which addressed JAR/FAR [Joint Aviation
Regulation/Federal Aviation Regulation] 25-571 requirements related
to damage-tolerance and fatigue evaluation of structure [FAA AD 98-
26-01 corresponds to DGAC AD 1992-106-132(B)R4, dated June 5, 1996].
    Following the Extended Design Service Goal activities as part of
the Structure Task Group for the Airbus A310 program, EASA issued AD
2007-0053 which replaced DGAC France AD F-1992-106-132R7. Since the
issuance of that AD, the thresholds and the intervals of some Airbus
Service Bulletins (SBs which address structure fatigue related areas
on the wing parts), until now part of the requirements of AD 2007-
0053, have been updated.
    For the reasons stated above, this new [EASA] AD requires the
accomplishment of the structural fatigue-related corrective actions
in accordance with the latest revision of these SBs which have been
reviewed in the context of the A310 Extended Service Goal
activities. Consequently, this new AD supersedes the requirements of
paragraphs 1.8, 1.9, 1.10, 1.13, 1.18 of EASA AD 2007-0053, which
has been revised accordingly.

The unsafe condition is reduced structural integrity of the wings. The
required corrective actions are as follows, depending on airplane
configuration:
     For certain Model A310-203 and A310-222 airplanes:
Repetitive detailed inspections for cracking of the leading edge access
panels around the bolt holes, and repair if necessary.
     For certain Model A310-203, A310-204, A310-222, A310-304,
A310-322, A310-324, and A310-325 airplanes: Repetitive eddy current
inspections to detect cracks in the holes around the overwing refueling
aperture at ribs 13-14, and repair if necessary.
     For certain Model A310-203, A310-204, A310-222, A310-304,
A310-322, A310-324, and A310-325 airplanes: Repetitive external
detailed inspections for cracking of the top skin at ribs 13-14,
repetitive internal detailed inspections for cracking of stringer 7 and
stringer 8 of the overwing refuel aperture, and repair if necessary.
     For certain Model A310-203 and A310-222 airplanes:
Repetitive detailed inspections for cracking around the bolts in the
wing top skin upper surface of the front spar between rib 7 and rib 28,
and repair if necessary.
     For certain Model A310-203 and A310-222 airplanes:
Repetitive high frequency eddy current (HFEC) or X-ray inspections to
detect cracking of the stringer runouts inboard and outboard of rib 14
at stringers 6, 7, 8, and 9, and repair if necessary.
     For certain Model A310-203, A310-204, A310-222, A310-304,
A310-322, and A310-324 airplanes: Repetitive ultrasonic inspections for
cracking in certain bolt holes where the main landing gear forward
pick-up fitting is attached to the rear spar, and repair if necessary.
    You may obtain further information by examining the MCAI in the AD
docket.

Comments

    We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.

Explanation of Changes to This AD

    We have moved the parenthetical information from paragraphs (g),
(i), (j), (o), and (q)(1), (q)(2), and (q)(3) of this AD. Instead, we
have provided that information in Note 1, Note 3, Note 4, Note 6, and
Note 8 of this AD.
    We have also revised tables 3 and 4 of this AD to refer to Model
``A310-322'' instead of ``A310A-322.'' We inadvertently referred to
``A310A-322'' in the NPRM.

Conclusion

    We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We determined that these change will not increase the
economic burden on any operator or increase the scope of the 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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 44 products of U.S. registry.
We also estimate that it will take about 97 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $362,780, or $8,245 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 AD will not have federalism implications
under Executive Order 13132. This AD will 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 AD:
    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 AD and placed it in the AD docket.

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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2011-10-07 Airbus: Amendment 39-16688. Docket No. FAA-2010-1275;
Directorate Identifier 2010-NM-091-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 15,
2011.

Affected ADs

    (b) This AD affects AD 90-19-07, Amendment 39-6731 (55 FR 37455,
September 12, 1990); and AD 91-06-18, Amendment 39-6940 (56 FR
10796, March 14, 1991).

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, -221, -222,
-304, -322, -324, and -325 airplanes, certificated in any category,
all certified models, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:
    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France Airworthiness Directive (AD) 1992-106-132(B) * * * was issued
to require a set of inspection- and modification tasks which
addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation
Regulation] 25-571 requirements related to damage-tolerance and
fatigue evaluation of structure.
* * * * *
    The unsafe condition is reduced structural integrity of the
wings.

Compliance

    (f) 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 Certain Requirements of AD 98-26-01, Amendment 39-10942
(63 FR 69179, December 16, 1998), With Reduced Compliance Times

Leading Edge Access Panels Landing--Lower Skin--Inspection for Cracks
at Bolt Holes

    (g) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996,
except airplanes on which Airbus modification No. 05101 has been
embodied in production, or on which Airbus Service Bulletin A310-57-
2003 has been embodied in service before the accumulation of 9,400
total flight cycles and 18,800 total flight hours: At the times
specified in paragraph (h) of this AD, perform a detailed visual
inspection to detect cracks in the external surface of the wing
lower skin around the landing access panel holes of the leading
edge, in accordance with the Airbus Service Bulletin A310-57-2002,
Revision 1, dated July 2, 1992; Airbus Service Bulletin A310-57-
2002, Revision 2, dated January 4, 1996; or Airbus Mandatory Service
Bulletin A310-57-2002, Revision 03, dated November 28, 2006. If any
discrepancy is found, prior to further flight, repair in accordance
with a method approved by either the Manager, International Branch,
ANM-116, FAA, Transport Airplane Directorate, or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent) or EASA (or its delegated agent). Except as required by
paragraph (n) of this AD, repeat the detailed inspection specified
in this paragraph at the earlier of the times specified in
paragraphs (g)(1) and (g)(2) of this AD; and thereafter at intervals
not to exceed 2,300 flight cycles or 4,700 flight hours, whichever
occurs first. As of the effective date of this AD, use only Airbus
Mandatory Service Bulletin A310-57-2002, Revision 03, dated November
28, 2006. Accomplishment of Airbus Modification 05101 before the
effective date of this AD terminates the repetitive inspection
requirements of this paragraph; however, airplanes identified in
paragraph (n) of this AD are applicable to the new inspections
required by paragraph (n) of this AD. As of the effective date of
this AD: Accomplishment of Airbus Modification 05101 before the
accumulation of 9,400 total flight cycles and 18,800 total flight
hours terminates the repetitive inspection requirements of this
paragraph.

    Note 1: Airbus Service Bulletin A310-57-2003, Revision 03, dated
October 16, 2006, is

an additional source of guidance for accomplishing Airbus
Modification 05101.

    Note 2: As of the effective date of this AD, if Airbus Service
Bulletin A310-57-2003 is done on or after the accumulation of 9,400
total flight cycles or on or after the accumulation of 18,800 total
flight hours, the actions specified in paragraph (g) of this AD are
still required.

    (1) Within 3,000 flight cycles after doing the detailed
inspection specified in paragraph (g) of this AD.
    (2) At the later of the times specified in paragraphs (g)(2)(i)
and (g)(2)(ii) of this AD.
    (i) Within 2,300 flight cycles or 4,700 flight hours, whichever
occurs first, after doing the detailed inspection required by
paragraph (g) of this AD.
    (ii) Within 1,500 flight cycles or 3,000 flight hours, whichever
occurs first, after the effective date of this AD.
    (h) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996,
except airplanes on which Airbus modification No. 05101 has been
embodied in production, or on which Airbus Service Bulletin A310-57-
2003 has been embodied in service before the accumulation of 9,400
total flight cycles and 18,800 total flight hours: At the earlier of
the times specified in paragraphs (h)(1) and (h)(2) of this AD, do
the detailed inspection required by paragraph (g) of this AD.
    (1) Prior to the accumulation of 12,000 total flight cycles, or
within 1,000 flight cycles after January 20, 1999 (the effective
date of AD 98-26-01, amendment 39-10942), whichever occurs later.
    (2) At the later of the times specified in paragraph (h)(2)(i)
and (h)(2)(ii) of this AD.
    (i) Prior to the accumulation of 9,400 total flight cycles or
18,800 total flight hours, whichever occurs first.
    (ii) Within 1,500 flight cycles or 3,000 flight hours, whichever
occurs first, after the effective date of this AD.

Inspect Area around Overwing Refueling Aperture at Ribs 13-14

    (i) For Model A310-203, A310-204, A310-222, A310-304, A310-322,
A310-324, and A310-325 airplanes that are listed in Airbus Service
Bulletin A310-57-2006, Revision 3, dated May 2, 1996, and are
identified as Configuration 1 in Airbus Mandatory Service Bulletin
A310-57-2006, Revision 04, dated May 21, 2007: Prior to the
accumulation of 6,000 total flight cycles, or within 1,000 flight
cycles after January 20, 1999, whichever occurs later, perform an
eddy current inspection to detect cracks in the holes around the
overwing refueling aperture at ribs 13-14, in accordance with Airbus
Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996; or
Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated
May 21, 2007. If any discrepancy is found, prior to further flight,
perform follow-on corrective actions, as applicable, in accordance
with Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2,
1996; or Airbus Mandatory Service Bulletin A310-57-2006, Revision
04, dated May 21, 2007; except where the service bulletin specifies
to contact Airbus for repair, before further flight, repair in
accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
or the DGAC (or its delegated agent) or EASA (or its delegated
agent). Repeat the inspection specified in this paragraph at the
earlier of the times specified in paragraphs (i)(1) and (i)(2) of
this AD, and thereafter at intervals not to exceed 2,300 flight
cycles or 4,600 flight hours, whichever occurs first. As of the
effective date of this AD, use only Airbus Mandatory Service
Bulletin A310-57-2006, Revision 04, dated May 21, 2007.
Accomplishment of Airbus Modification 05891H5128 terminates the
repetitive inspections required by this paragraph.
    (1) Within 3,000 flight cycles after doing the last inspection
required by paragraph (i) of this AD.
    (2) At the later of the times specified in paragraphs (i)(2)(i)
and (i)(2)(ii) of this AD.
    (i) Within 2,300 flight cycles or 4,600 flight hours, whichever
occurs first, after doing the most recent inspection required by
paragraph (i) of this AD.
    (ii) Within 380 flight cycles or 770 flight hours, whichever
occurs first, after the effective date of this AD.

    Note 3:  Airbus Service Bulletin A310-57-2020, Revision 07,
dated June 5, 2006, is an additional source of guidance for
accomplishing Airbus Modification 05891H5128.

Upper Skin Forward of Front Spar--Inspection for Cracks

    (j) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996,
except airplanes on which Airbus modification 05026 has been
embodied in production, or on which Airbus Service Bulletin A310-57-
2005 has been done in service before the accumulation of 10,500
total flight cycles and 21,000 total flight hours: At the times
specified in paragraph (k) of this AD, perform a detailed visual
inspection to detect cracks around the bolts in the wing top skin
upper surface of the front spar between rib 7 and rib 28, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-57-2032, Revision 3, dated January 4, 1996; or Airbus
Mandatory Service Bulletin A310-57-2032, Revision 04, dated December
1, 2006. If any discrepancy is found, prior to further flight,
repair in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
or DGAC (or its delegated agent) or EASA (or its delegated agent).
Except as required by paragraph (p) of this AD, repeat the detailed
inspection specified in this paragraph at the earlier of the times
specified in paragraphs (j)(1) and (j)(2) of this AD, and thereafter
at intervals not to exceed 3,900 flight cycles or 7,900 flight
hours, whichever occurs first. As of the effective date of this AD,
use only Airbus Mandatory Service Bulletin A310-57-2032, Revision
04, dated December 1, 2006. Accomplishment of Airbus Modification
05026H0878 before the effective date of this AD terminates the
repetitive inspection requirements of this paragraph; however,
airplanes identified in paragraph (p) of this AD are applicable to
the new inspections required by paragraph (p) of this AD. As of the
effective date of this AD: Accomplishment of Airbus Modification
05026H0878 before the accumulation of 10,500 total flight cycles and
21,000 total flight hours terminates the repetitive inspection
requirements of this paragraph.
    (1) Within 4,500 flight cycles after doing the last inspection
required by paragraph (j) of this AD.
    (2) At the later of the times specified in paragraphs (j)(2)(i)
and (j)(2)(ii) of this AD.
    (i) Within 3,900 flight cycles or 7,900 flight hours, whichever
occurs first, after doing the most recent inspection required by
paragraph (j) of this AD.
    (ii) Within 850 flight cycles or 1,700 flight hours, whichever
occurs first, after the effective date of this AD.

    Note 4: Airbus Service Bulletin A310-57-2005, Revision 03, dated
October 2, 2006, is an additional source of guidance for
accomplishing Airbus Modification 05026H0878.

    Note 5:  As of the effective date of this AD, if Airbus Service
Bulletin A310-57-2005 is done on or after the accumulation of 10,500
total flight cycles or on or after the accumulation of 21,000 total
flight hours, the actions specified in paragraph (j) of this AD are
still required.

    (k) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996,
except airplanes on which Airbus modification 05026 has been
embodied in production, or on which Airbus Service Bulletin A310-57-
2005 has been done in service before the accumulation of 10,500
total flight cycles and 21,000 total flight hours: At the earlier of
the times specified in paragraphs (k)(1) and (k)(2) of this AD, do
the detailed inspection required by paragraph (j) of this AD.
    (1) Prior to the accumulation of 12,000 total flight cycles, or
within 1,000 flight cycles after January 20, 1999, whichever occurs
later.
    (2) At the later of the times specified in paragraphs (k)(2)(i)
and (k)(2)(ii) of this AD.
    (i) Prior to the accumulation of 10,500 total flight cycles or
21,000 total flight hours, whichever occurs first.
    (ii) Within 850 flight cycles or 1,700 flight hours, whichever
occurs first, after the effective date of this AD.

Stringer Flanges at Rib 14 Wing Bottom Skin--Inspect for Cracks

    (l) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996,
except airplanes on which Airbus modification 04987 has been done in
production: At the compliance time specified in paragraph (m) of
this AD, perform a high frequency eddy current (HFEC) or X-ray
inspection to detect cracking of the stringer runouts inboard and
outboard of rib 14 at stringers 6, 7, 8, and 9, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A310-57-
2038, Revision 2, dated January 4, 1996; or Airbus Mandatory

Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006.
Do the next inspection at the earlier of the times specified in
paragraph (l)(1) and (l)(2) of this AD, and repeat the inspection
thereafter at intervals not to exceed the applicable times specified
in table 1 of this AD. If any crack is detected, prior to further
flight, repair in accordance with a method approved by either the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate, or DGAC (or its delegated agent) or EASA (or its
delegated agent). As of the effective date of this AD, use only
Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated
October 19, 2006.
    (1) Within the applicable interval specified in paragraph
1.B.(5) of Airbus Service Bulletin A310-57-2038, Revision 2, dated
January 4, 1996.
    (2) At the later of the times specified in paragraph (l)(2)(i)
and (l)(2)(ii) of this AD.
    (i) Within the applicable interval specified in table 1 of this
AD after doing the most recent inspection specified in paragraph (l)
of this AD.
    (ii) Within 1,100 flight cycles or 2,300 flight hours, whichever
occurs first, after the effective date of this AD.

       Table 1--Repetitive Intervals, Depending on Inspection Type
------------------------------------------------------------------------
                                           Repetitive interval (not to
          Type of  inspection                        exceed)
------------------------------------------------------------------------
X-Ray..................................  7,200 flight cycles or 14,500
                                          flight hours, whichever occurs
                                          first.
HFEC...................................  9,400 flight cycles or 18,800
                                          flight hours, whichever occurs
                                          first.
------------------------------------------------------------------------

    (m) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996,
except airplanes on which Airbus modification 04987 has been done in
production: At the earlier of the times specified in paragraphs
(m)(1) and (m)(2) of this AD, perform an inspection required by
paragraph (l) of this AD.
    (1) Prior to the accumulation of 12,000 total flight cycles, or
within 1,500 flight cycles after January 20, 1999, whichever occurs
later.
    (2) At the later of the times specified in paragraphs (m)(2)(i)
and (m)(2)(ii) of this AD.
    (i) Prior to the accumulation of 12,000 total flight cycles or
24,000 total flight hours, whichever occurs first.
    (ii) Within 1,100 flight cycles or 2,300 flight hours after the
effective date of this AD, whichever occurs first.

New Requirements of This AD

Leading Edge Access Panels Landing--Lower Skin--Inspection for Cracks
at Bolt Holes--Additional Inspections for Certain Airplanes

    (n) For Model A310-203 and A310-222 airplanes, on which Airbus
Service Bulletin A310-57-2003 has been done in service on or after
the accumulation of 9,400 total flight cycles or on or after the
accumulation of 18,800 total flight hours: Do the inspection
required by paragraph (g) of this AD at the later of the times
specified in paragraphs (n)(1) and (n)(2) of this AD. Repeat the
inspection required by paragraph (g) of this AD thereafter at
intervals not to exceed 2,300 flight cycles or 4,700 flight hours,
whichever occurs first.
    (1) Within 2,300 flight cycles or 4,700 flight hours, whichever
occurs first, after doing the most recent detailed inspection
required by paragraph (g) of this AD.
    (2) Within 1,500 flight cycles or 3,000 flight hours, after the
effective date of this AD, whichever occurs first.

Inspect Area Around Overwing Refueling Aperture at Ribs 13-14 for
Additional Airplanes

    (o) For Model A310-203, A310-204, A310-222, A310-304, A310-322,
A310-324, and A310-325 airplanes, except for airplanes identified in
paragraph (i) of this AD on which Airbus Modification 05891H5128 has
not been done: At the applicable compliance time specified in table
2 of this AD, do the applicable actions specified in paragraph
(o)(1) or (o)(2) of this AD, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-57-2006,
Revision 04, dated May 21, 2007. If any cracking is found, before
further flight, repair in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-57-2006,
Revision 04, dated May 21, 2007; except where this service bulletin
specifies to contact Airbus for repair, before further flight,
repair in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
or EASA (or its delegated agent). Repeat the inspections thereafter
at the applicable interval specified in table 2 of this AD. Certain
compliance times specified in table 2 of this AD are applicable to
short range use, average flight time (AFT) equal to or less than 4.0
hours, or long range use, AFT exceeding 4.0 hours. For airplanes
identified as Configuration 01 in Airbus Mandatory Service Bulletin
A310-57-2006, Revision 04, dated May 21, 2007, accomplishment of
Airbus Modification 05891H5128 terminates the repetitive inspections
required by this paragraph for Configuration 01 airplanes;
thereafter do the applicable actions specified in paragraph (o)(2)
of this AD at the times specified in table 2 of this AD.

    Note 6: Airbus Service Bulletin A310-57-2020, Revision 07, dated
June 5, 2006, is an additional source of guidance for accomplishing
Airbus Modification 05891H5128.

    (1) For Configuration 01 airplanes, as identified in Airbus
Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21,
2007: Do a rotating probe eddy current inspection for cracking in
the holes around the overwing refueling aperture at ribs 13-14.
    (2) For Configuration 02 through 06 airplanes, as identified in
Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated
May 21, 2007: Do an external detailed inspection for cracking of the
top skin at ribs 13-14, and an internal detailed inspection for
cracking of string 7 and string 8 of the overwing refuel aperture.

                       Table 2--Compliance Times for Configuration 01 Through 06 Airplanes
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
  Airplanes as Identified in Airbus        Compliance time (whichever occurs later)        Repetitive interval
 Mandatory Service Bulletin A310-57-                                                          (not to exceed)
2006, revision 04, dated May 21, 2007
----------------------------------------------------------------------------------------------------------------
Configuration 01 airplanes...........  Prior to the             Within 380 flight        2,300 flight cycles or
                                        accumulation of 6,000    cycles or 770 flight     4,600 flight hours,
                                        total flight cycles.     hours, whichever         whichever occurs
                                                                 occurs first, after      first.
                                                                 the effective date of
                                                                 this AD.
Configuration 02 airplanes...........  Within 30,900 flight     Within 1,500 flight      11,300 flight cycles or
                                        cycles or 61,900         cycles or 18 months,     22,600 flight hours,
                                        flight hours,            whichever occurs         whichever occurs
                                        whichever occurs         first, after the         first.
                                        first, after             effective date of this
                                        accomplishing Airbus     AD.
                                        Service Bulletin A310-
                                        57-2020.
Configuration 03 airplanes...........  Within 30,900 flight     Within 1,500 flight      12,000 flight cycles or
                                        cycles or 61,900         cycles or 18 months,     24,000 flight hours,
                                        flight hours,            whichever occurs         whichever occurs
                                        whichever occurs         first, after the         first.
                                        first, after Airbus      effective date of this
                                        Modification             AD.
                                        05891H5128 is done or
                                        Airbus Service
                                        Bulletin A310-57-2020
                                        is accomplished.

Configuration 04 and 05 short range    Before the accumulation  Within 1,500 flight      12,000 flight cycles or
 airplanes.                             of 25,900 total flight   cycles or 18 months,     33,600 flight hours,
                                        cycles or 72,500 total   whichever occurs         whichever occurs
                                        flight hours,            first, after the         first.
                                        whichever occurs first.  effective date of this
                                                                 AD.
Configuration 04 and 05 long range     Before the accumulation  Within 1,500 flight      9,400 flight cycles or
 airplanes.                             of 18,800 total flight   cycles or 18 months,     47,200 flight hours,
                                        cycles or 94,200 total   whichever occurs         whichever occurs
                                        flight hours,            first, after the         first.
                                        whichever occurs first.  effective date of this
                                                                 AD.
Configuration 06.....................  Before the accumulation  Within 1,500 flight      12,000 flight cycles or
                                        of 30,900 total flight   cycles or 18 months,     24,000 flight hours,
                                        cycles or 61,900 total   whichever occurs         whichever occurs
                                        flight hours,            first, after the         first.
                                        whichever occurs first.  effective date of this
                                                                 AD.
----------------------------------------------------------------------------------------------------------------

Upper Skin Forward of Front Spar--Inspection for Cracks--Additional
Inspections for Certain Airplanes

    (p) For Model A310-203 and A310-222 airplanes on which Airbus
Service Bulletin A310-57-2005 has been done in service on or after
the accumulation of 10,500 total flight cycles or on or after 21,000
total flight hours: Do the inspection required by paragraph (j) of
this AD at the later of the times specified in paragraphs (p)(1) and
(p)(2) of this AD. Repeat the inspection specified in paragraph (j)
of this AD thereafter at intervals not to exceed 3,900 flight cycles
or 7,900 flight hours, whichever occurs first.
    (1) Within 3,900 flight cycles or 7,900 flight hours, whichever
occurs first, after doing the most recent inspection required by
paragraph (j) of this AD.
    (2) Within 850 flight cycles or 1,700 flight hours, whichever
occurs first, after the effective date of this AD.

Inspection of Rear Spar at Selected Bolt Locations for Attachment of
Main landing Gear Forward Pick-Up Fitting

    (q) For Model A310-203, A310-204, A310-222, A310-304, A310-322,
and A310-324 airplanes, except airplanes on which Airbus
modification 07601 has been done in production: Do the applicable
actions specified in paragraphs (q)(1), (q)(2), and (q)(3) of this
AD. If any cracking is found during any inspection, before further
flight, repair in accordance with a method approved by either the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate, or EASA (or its delegated agent).

    Note 7:  For Model A310-304, A310-322, and A310-324 airplanes on
which Airbus modification 07601 has been done, guidance for post-
modification inspections can be found in Structure Significant Item
(SSI) 57.21.16 of the Maintenance Review Board Document (MRBD).

    (1) For airplanes on which Airbus Modification 07925H1113 and
Modification 11578H5436 have not been done: At the applicable time
specified in table 3 of this AD, perform an ultrasonic inspection
for cracking in certain bolt holes where the main landing gear
forward pick-up fitting is attached to the rear spar, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat
the inspection thereafter at the applicable interval specified in
table 3 of this AD until Airbus Modification 07925H1113 or
11578H5436 has been done. After doing Airbus Modification 07925H1113
or 11578H5436 do the applicable actions specified in paragraph
(q)(2) or (q)(3) of this AD at the times specified in paragraph
(q)(2) or (q)(3) of this AD, as applicable. Certain compliance times
specified in table 3 of this AD are applicable to short range use,
average flight time (AFT) equal to or less than 4.0 hours, or long
range use, AFT exceeding 4.0 hours.

    Note 8: Airbus Service Bulletin A310-57-2049, Revision 6, dated
November 26, 1997, is an additional source of guidance for
accomplishing Airbus Modification 07925H1113. Airbus Service
Bulletin A310-57-2074, Revision 03, dated July 3, 2006, is an
additional source of guidance for accomplishing Airbus Modification
11578H5436.

                     Table 3--Compliance Times for Airplanes Pre-Mod 07925 and Pre-Mod 11578
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
              Airplanes                    Compliance time (whichever occurs later)        Repetitive interval
                                                                                (not to exceed)
----------------------------------------------------------------------------------------------------------------
Model A310-203, A310-204, and A310-    Prior to the             Within 750 flight        2,800 flight cycles or
 222 airplanes.                         accumulation of 9,800    cycles or 1,500 flight   5,700 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        19,600 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
Model A310-304, A310-322, and A310-    Prior to the             Within 750 flight        2,400 flight cycles or
 324 short range airplanes.             accumulation of 7,100    cycles or 1,500 flight   6,900 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        20,100 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
Model A310-304, A310-322, and A310-    Prior to the             Within 750 flight        1,900 flight cycles or
 324 long range airplanes.              accumulation of 5,700    cycles or 1,500 flight   9,800 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        28,600 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
----------------------------------------------------------------------------------------------------------------

    (2) For airplanes on which Airbus Modification 07925H1113 has
been done: At the applicable time specified in table 4 of this AD,
perform an ultrasonic inspection for cracking in certain bolt holes
where the main landing gear forward pick-up fitting is attached to
the rear spar, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated
December 1, 2006. Repeat the inspection thereafter at the applicable
interval specified in table 4 of this AD. Certain compliance times
specified in table 4 of this AD are applicable to short range use,
AFT equal to or less than 4.0 hours, or long range use, AFT
exceeding 4.0 hours.

                             Table 4--Compliance Times for Airplanes Post-Mod 07925
----------------------------------------------------------------------------------------------------------------
                  --                              --                       --                       --
----------------------------------------------------------------------------------------------------------------
              Airplanes                    Compliance time (whichever occurs later)        Repetitive interval
                                                                                (not to exceed)
----------------------------------------------------------------------------------------------------------------
Model A310-203, A310-204, and A310-    Prior to the             Within 750 flight        9,400 flight cycles or
 222 airplanes.                         accumulation of 14,700   cycles or 1,500 flight   18,900 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        29,400 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
Model A310-304, A310-322, and A310-    Prior to the             Within 750 flight        5,000 flight cycles or
 324 short range airplanes.             accumulation of 11,900   cycles or 1,500 flight   14,000 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        33,500 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
Model A310-304, A310-322, and A310-    Prior to the             Within 750 flight        4,000 flight cycles or
 324 long range airplanes.              accumulation of 9,500    cycles or 1,500 flight   20,000 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        47,700 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
----------------------------------------------------------------------------------------------------------------

     (3) For airplanes on which Airbus Modification 11578H5436 has
been done: At the applicable time specified in table 5 of this AD,
perform an ultrasonic inspection for cracking in certain bolt holes
where the main landing gear forward pick-up fitting is attached to
the rear spar, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated
December 1, 2006. Repeat the inspection thereafter at the applicable
interval specified in table 5 of this AD. Certain compliance times
specified in table 5 of this AD are applicable to short range use,
average flight time (AFT) equal to or less than 4.0 hours, or long
range use, AFT exceeding 4.0 hours.

                             Table 5--Compliance Times for Airplanes Post-Mod 11578
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
              Airplanes                    Compliance time (whichever occurs later)        Repetitive interval
                                                                                (not to exceed)
----------------------------------------------------------------------------------------------------------------
Model A310-203, A310-204, and A310-    Within 29,600 flight     Within 750 flight        9,400 flight cycles or
 222 airplanes.                         cycles or 59,200         cycles or 1,500 flight   18,900 flight hours,
                                        flight hours,            hours, whichever         whichever occurs
                                        whichever occurs         occurs first, after      first.
                                        first, after Airbus      the effective date of
                                        Modification             this AD.
                                        11578H5436 has been
                                        done.
Model A310-304, A310-322, and A310-    Within 24,200 flight     Within 750 flight        5,000 flight cycles or
 324 short range airplanes.             cycles or 67,900         cycles or 1,500 flight   14,000 flight hours,
                                        flight hours,            hours, whichever         whichever occurs
                                        whichever occurs         occurs first, after      first.
                                        first, after Airbus      the effective date of
                                        Modification             this AD.
                                        11578H5436 has been
                                        done.
Model A310-304, A310-322, and A310-    Within 19,300 flight     Within 750 flight        4,000 flight cycles or
 324 long range airplanes.              cycles or 96,800         cycles or 1,500 flight   20,000 flight hours,
                                        flight hours,            hours, whichever         whichever occurs
                                        whichever occurs         occurs first, after      first.
                                        first, after Airbus      the effective date of
                                        Modification             this AD.
                                        11578H5436 has been
                                        done.
----------------------------------------------------------------------------------------------------------------

Credit for Actions Accomplished in Accordance With Previous Service
Information

    (r) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2038, Revision 03,
dated September 4, 1998, are acceptable for compliance with the
corresponding actions specified in paragraph (l) of this AD.
    (s) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A310-57-2046, Revision 07,
dated April 2, 1999, are acceptable for compliance with the
corresponding actions specified in paragraph (q) of this AD.

Terminating Action for Paragraph (a) of AD 90-19-07

    (t) Accomplishing an inspection in accordance with Airbus
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, or
Revision 03, dated September 4, 1998; or Airbus Mandatory Service
Bulletin A310-57-2038, Revision 04, dated October 19, 2006;
terminates the requirements of paragraph (a) of AD 90-19-07.

    Note 9: Airbus Service Bulletin A310-57-2038, Revision 2, dated
January 4, 1996; and Airbus Mandatory Service Bulletin A310-57-2038,
Revision 04, dated October 19, 2006; are referred to in paragraph
(l) of this AD. Airbus Service Bulletin A310-57-2038, Revision 03,
dated September 4, 1998, is referred to in paragraph (r) of this AD.

Terminating Action for AD 91-06-18

    (u) Accomplishing an inspection in accordance with Airbus
Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996,
as revised by Airbus Service Bulletin Change Notice 4A, dated
October 16, 1996; Airbus Service Bulletin A310-57-2046, Revision 07,
dated April 2, 1999; or Airbus Mandatory Service Bulletin A310-57-
2046, Revision 08, dated December 1, 2006; terminates the
requirements of AD 91-06-18.

    Note 10: Airbus Mandatory Service Bulletin A310-57-2046,
Revision 08, dated December 1, 2006, is referred to in paragraph (q)
of this AD. Airbus Service Bulletin A310-57-2046, Revision 07, dated
April 2, 1999, is referred to in paragraph (s) of this AD. Airbus
Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996,
as revised by Airbus Service Bulletin Change Notice 4A, dated
October 16, 1996, is referred to in paragraph (n) of AD 98-26-01.

FAA AD Differences

    Note 11: This AD differs from the MCAI and/or service
information as follows:
    Although the MCAI or service information allows further flight
after cracks are found during compliance with the required action,
paragraph (j) of this AD requires that you repair the crack(s)
before further flight.

Other FAA AD Provisions

    (v) 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. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport

Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
Information may be e-mailed to<EMAIL_ADDRESS>
Before using any approved AMOC, notify your principal inspector or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD. AMOCs
approved previously in accordance with AD 98-26-01, are approved as
AMOCs for the corresponding provisions of this AD.
    (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.

Related Information

    (w) Refer to MCAI EASA Airworthiness Directive 2007-0242, dated
September 4, 2007, and the Airbus service bulletins listed in table
6 of this AD for related information.

                                      Table 6--Related Service Information
----------------------------------------------------------------------------------------------------------------
            Service Bulletin                        Revision                              Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310-   03..........................  November 28, 2006.
 57-2002.
Airbus Mandatory Service Bulletin A310-   04..........................  May 21, 2007.
 57-2006.
Airbus Mandatory Service Bulletin A310-   04..........................  December 1, 2006.
 57-2032.
Airbus Mandatory Service Bulletin A310-   04..........................  October 19, 2006.
 57-2038.
Airbus Mandatory Service Bulletin A310-   08..........................  December 1, 2006.
 57-2046.
Airbus Service Bulletin A310-57-2038....  2...........................  January 4, 1996.
Airbus Service Bulletin A310-57-2038....  03..........................  September 4, 1998
Airbus Service Bulletin A310-57-2046....  4...........................  October 16, 1996.
Airbus Service Bulletin A310-57-2046....  07..........................  April 2, 1999.
Airbus Service Bulletin A310-57-2046,     Original....................  October 16, 1996.
 Change Notice 4A.
----------------------------------------------------------------------------------------------------------------

Material Incorporated by Reference

    (x) You must use the service bulletins contained in table 7 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise. If you accomplish the optional terminating
actions specified by this AD, you must use the service information
contained in table 7 of this AD to perform those actions unless the
AD specifies otherwise.

                                 Table 7--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                                                                                Required/optional
          Service Bulletin                    Revision                    Date                    action
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin     03......................  November 28, 2006......  Required.
 A310-57-2002.
Airbus Mandatory Service Bulletin     04......................  May 21, 2007...........  Required.
 A310-57-2006.
Airbus Mandatory Service Bulletin     04......................  December 1, 2006.......  Required.
 A310-57-2032.
Airbus Mandatory Service Bulletin     04......................  October 19, 2006.......  Required and optional.
 A310-57-2038.
Airbus Mandatory Service Bulletin     08......................  December 1, 2006.......  Required and optional.
 A310-57-2046.
Airbus Service Bulletin A310-57-2038  2.......................  January 4, 1996........  Optional.
Airbus Service Bulletin A310-57-2038  03......................  September 4, 1998......  Optional.
Airbus Service Bulletin A310-57-2046  4.......................  October 16, 1996.......  Optional.
Airbus Service Bulletin A310-57-2046  07......................  April 2, 1999..........  Optional.
Airbus Service Bulletin A310-57-      Original................  October 16, 1996.......  Optional.
 2046, Change Notice 4A.
----------------------------------------------------------------------------------------------------------------

     (1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
table 8 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

                                 Table 8--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                Service Bulletin                    Revision                           Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310-57-2002.              03  November 28, 2006.
Airbus Mandatory Service Bulletin A310-57-2006.              04  May 21, 2007.
Airbus Mandatory Service Bulletin A310-57-2032.              04  December 1, 2006.
Airbus Mandatory Service Bulletin A310-57-2038.              04  October 19, 2006.
Airbus Mandatory Service Bulletin A310-57-2046.              08  December 1, 2006.
Airbus Service Bulletin A310-57-2038...........              03  September 4, 1998.
Airbus Service Bulletin A310-57-2046...........              07  April 2, 1999.
----------------------------------------------------------------------------------------------------------------

     (2) The Director of the Federal Register previously approved
the incorporation by reference of the service information contained
in table 9 of this AD on January 20, 1999 (63 FR 69179, December 16,
1998).

                             Table 9--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
            Service Bulletin                        Revision                              Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A310-57-2038....  2...........................  January 4, 1996.
Airbus Service Bulletin A310-57-2046....  4...........................  October 16, 1996.
Airbus Service Bulletin A310-57-2046,     Original....................  October 16, 1996.
 Change Notice 4A.
----------------------------------------------------------------------------------------------------------------

     (3) For service information identified in this 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.
    (4) You may review copies of the 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>.
    (5) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on April 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-10684 Filed 5-10-11; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 88, Number 212 (Friday, November 3, 2023)]
[Notices]
[Pages 75571-75572]
[FR Doc No: 2023-24323]

-----------------------------------------------------------------------

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. ER24-228-000]

South Cheyenne Solar, LLC; Supplemental Notice That Initial
Market-Based Rate Filing Includes Request for Blanket Section 204
Authorization

    This is a supplemental notice in the above-referenced proceeding of
South Cheyenne Solar, LLC's application for market-based rate
authority, with an accompanying rate tariff, noting that such
application includes a request for blanket authorization, under 18 CFR
part 34, of future issuances of securities and assumptions of
liability.
    Any person desiring to intervene or to protest should file with the
Federal Energy Regulatory Commission, 888 First Street NE, Washington,
DC 20426, in accordance with Rules 211 and 214 of the Commission's
Rules of Practice and Procedure (18 CFR 385.211 and 385.214). Anyone
filing a motion to intervene or protest must serve a copy of that
document on the Applicant.
    Notice is hereby given that the deadline for filing protests with
regard to the applicant's request for blanket authorization, under 18
CFR part 34, of future issuances of securities and

assumptions of liability, is November 20, 2023.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper, using the FERC Online links at http://www.ferc.gov. To facilitate electronic service, persons with internet
access who will eFile a document and/or be listed as a contact for an
intervenor must create and validate an eRegistration account using the
eRegistration link. Select the eFiling link to log on and submit the
intervention or protests.
    Persons unable to file electronically may mail similar pleadings to
the Federal Energy Regulatory Commission, 888 First Street NE,
Washington, DC 20426. Hand delivered submissions in docketed
proceedings should be delivered to Health and Human Services, 12225
Wilkins Avenue, Rockville, Maryland 20852.
    In addition to publishing the full text of this document in the
Federal Register, the Commission provides all interested persons an
opportunity to view and/or print the contents of this document via the
internet through the Commission's Home Page (http://www.ferc.gov) using
the ``eLibrary'' link. Enter the docket number excluding the last three
digits in the docket number field to access the document. At this time,
the Commission has suspended access to the Commission's Public
Reference Room, due to the proclamation declaring a National Emergency
concerning the Novel Coronavirus Disease (COVID-19), issued by the
President on March 13, 2020. For assistance, contact the Federal Energy
Regulatory Commission at [email protected] or call toll-free,
(886) 208-3676 or TYY,<PHONE_NUMBER>.
    The Commission's Office of Public Participation (OPP) supports
meaningful public engagement and participation in Commission
proceedings. OPP can help members of the public, including landowners,
environmental justice communities, Tribal members and others, access
publicly available information and navigate Commission processes. For
public inquiries and assistance with making filings such as
interventions, comments, or requests for rehearing, the public is
encouraged to contact OPP at<PHONE_NUMBER> or [email protected].

    Dated: October 30, 2023.
Debbie-Anne A. Reese,
Deputy Secretary.
[FR Doc. 2023-24323 Filed 11-2-23; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register: June 25, 2009 (Volume 74, Number 121)]
[Notices]
[Page 30285-30288]
[DOCID:fr25jn09-35]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. PF09-3-000; BLM Reference No. UTU-87295]

Magnum Gas Storage, LLC; Notice of Intent To Prepare an
Environmental Assessment for the Proposed Magnum Gas Storage Project
and Draft Pony Express Resource Management Plan Amendment for the
Bureau of Land Management, Request for Comments on Environmental
Issues, and Notice of Public Scoping Meetings

June 18, 2009.
    The staff of the Federal Energy Regulatory Commission (FERC or
Commission) will prepare an environmental assessment (EA) and the staff
of the Bureau of Land Management (BLM) will prepare a Draft Pony
Express Resource Management Plan Amendment (Draft RMP Amendment). The
EA and the Draft RMP Amendment will discuss the environmental impacts
of the construction and operation of a new interstate natural gas
storage facility and pipeline lateral, located in central Utah,
proposed by Magnum Gas Storage, LLC (MGS) as part of its Magnum Gas
Storage Project (Project).
    This notice announces the opening of the scoping process that will
be used to gather input from the public and

interested agencies on the Project. Your input will help the Commission
staff and cooperating agencies determine which issues need to be
evaluated in the EA/Draft RMP Amendment. The staff will also use the
scoping process to determine whether preparation of an environmental
impact statement is required for this Project based on the anticipated
level of impacts. Please note that the scoping period for this Project
will close on July 27, 2009.
    Comments may be submitted in written form or verbally. Further
details on how to submit written comments are provided in the Public
Participation section of this notice. In lieu of or in addition to
sending written comments, you are invited to attend public scoping
meetings scheduled in the Project area where you can verbally comment
on the proposed Project. These meetings are scheduled as follows:

------------------------------------------------------------------------
                  Date                               Location
------------------------------------------------------------------------
Tuesday, July 7, 2009 at 6 p.m. (MST)..  Juab County School District,
                                          346 E. 600 N. Street, Nephi,
                                          UT 84648.
Wednesday, July 8, 2009 at 6 p.m. (MST)  Millard County School District,
                                          285 E. 400 N., Delta, UT
                                          84624.
------------------------------------------------------------------------

    Interested groups and individuals are encouraged to attend the
meetings and to present comments on the environmental issues they
believe should be addressed in the EA/Draft RMP Amendment. A transcript
of the meeting will be generated so that your comments will be
accurately recorded.
    The FERC will be the lead federal agency for the preparation of the
EA and the BLM will be the lead federal agency for the preparation of
the Draft RMP Amendment. The EA will satisfy the requirements of the
National Environmental Policy Act (NEPA) and will be used by the FERC
to consider the environmental impacts that could result if it issues
MGS a Certificate of Public Convenience and Necessity under section 7
of the Natural Gas Act.
    The BLM is participating as a cooperating agency in the preparation
of the EA to satisfy its respective NEPA and planning responsibilities
since the Project would cross federal land under the jurisdiction of
the Fillmore and Salt Lake Field Offices in Utah. Under section 185(f)
of the Mineral Leasing Act of 1920, the BLM has the authority to issue
right-of-way grants for all affected federal lands. This would be in
accordance with Title 43 Code of Federal Regulations (CFR) Parts 2800
and 2880, subsequent 2800 and 2880 Manuals, and Handbook 2801-1. As a
cooperating agency, the BLM would adopt the EA per Title 40 CFR 1506.3
to meet its responsibilities under NEPA in considering MGS's
application for a Right-of-Way Grant and Temporary Use Permit for the
portion of the Project on federal land. In addition, the U.S. Forest
Service (FS) will participate as a cooperating agency because FS land
may be impacted. The concurrence or non-concurrence of the FS would be
considered in the BLM's decision as well as impacts on resources and
programs and the proposed Project's conformance with land use plans as
well as the proposed land use plan amendment for the Pony Express RMP.
    With this notice, the FERC staff is asking other federal, state,
local, and tribal agencies with jurisdiction and/or special expertise
with respect to environmental issues to cooperate with us in the
preparation of the EA. In addition, the BLM is asking other federal,
state, local, and tribal agencies to cooperate in the review of the
plan amendment process. These agencies may choose to participate once
they have evaluated MGS's proposal relative to their responsibilities.
Agencies that would like to request cooperating agency status should
follow the instructions for filing comments described later in this
NOI.
    This notice is being sent to affected landowners; federal, state,
and local government representatives and agencies; environmental and
public interest groups; Native American tribes; other interested
parties in this proceeding; and local libraries and newspapers. We \1\
encourage government representatives to notify their constituents of
this planned Project and encourage them to comment on their areas of
concern.
---------------------------------------------------------------------------

    \1\ ``We,'' ``us,'' and ``our'' refer to the environmental staff
of the Office of Energy Projects (OEP).
---------------------------------------------------------------------------

    If you are a landowner receiving this notice, you may be contacted
by a pipeline company representative about the acquisition of an
easement to construct, operate, and maintain the proposed facilities.
The pipeline company would seek to negotiate a mutually acceptable
agreement. However, if the Project is approved by the Commission, that
approval conveys with it the right of eminent domain. Therefore, if
easement negotiations fail to produce an agreement, the pipeline
company could initiate condemnation proceedings in accordance with
state law.
    A fact sheet prepared by the FERC entitled ``An Interstate Natural
Gas Facility on My Land? What Do I Need To Know?'' is available for
viewing on the FERC Internet Web site (http://www.ferc.gov). This fact
sheet addresses a number of typically asked questions, including the
use of eminent domain and how to participate in the Commission's
proceedings.

Summary of the Proposed Project

    The proposed development of the Project would include construction
and operation of an underground natural gas storage field with a
capacity of 64 billion cubic feet (Bcf) on state and private land near
the town of Delta in Millard County; Utah, and a 60-mile, 36-inch-
diameter natural gas pipeline lateral linking the gas storage facility
with existing interstate gas transmission pipelines at an interconnect
site north of Goshen, Utah. The pipeline lateral could potentially
cross private, state, FS and BLM public lands in Millard, Juab, and
Utah Counties.
    The Project would consist of the following facilities:
     Eight gas storage salt caverns each having a working gas
capacity of 8 Bcf, 5.6 Bcf working capacity, and supported by 2.4 Bcf
base gas;
     Approximately 60 miles of 36-inch-diameter natural gas
pipeline;
     Water supply wells and associated water supply pipelines;
     Injection/withdrawal wells;
     Leaching facilities for solution mining and creation of
caverns;
     Brine evaporation ponds required for brine management;
     Surface facilities for gas storage that would include
central compression and gas handling facilities, valving and
dehydration facilities, pig launchers/receivers and an operations
center;
     Electric transmission lines;
     Meter and regulator stations, and
     A 4-inch-diameter natural gas supply pipeline extending
approximately 9.3 miles to the storage site for temporary power
generation.
    The locations of the Project facilities are shown in Appendix 1.\2\
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    \2\ The appendices referenced in this notice are not being
printed in the Federal Register. Copies of all appendices are
available on the Commission's Web site at the ``eLibrary'' link or
from the Commission's Public Reference Room, 888 First Street, NE.,
Washington, DC 20426, or call<PHONE_NUMBER>. For instructions on
connecting to eLibrary refer to the last page of this notice. Copies
of the appendices were sent to all those receiving this notice in
the mail.

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Land Requirements for Construction

    The proposed storage field site would be comprised of both state
and private land totaling approximately 2,050 acres. Approximately 710
acres would be required for permanent facilities and 40 acres for
temporary construction. Construction of the proposed pipeline would
result in a temporary disturbance of approximately 708 acres.
    The proposed 36-inch-diameter pipeline would generally be installed
on BLM, state, and private land within a 100-foot-wide construction
right-of-way. At certain locations (e.g., road, railroad, and waterbody
crossings), extra workspaces would be required. MGS would retain a 50-
foot-wide permanent right-of-way for the pipeline.

The EA/NEPA Process

    NEPA requires the Commission to take into account the environmental
impacts that could result from an action whenever it considers the
issuance of a Certificate of Public Convenience and Necessity. The EA
is being prepared to serve that purpose. NEPA also requires Commission
staff and its cooperators to discover and address concerns the public
may have about the proposal. This process is referred to as
``scoping.'' The main goal of the scoping process is to focus the
analysis in the EA on the important environmental issues. By this NOI,
the Commission and BLM staff request public comments on any issues that
may arise during the scoping period and need to be addressed in the EA/
Draft RMP Amendment. All scoping comments received will be considered
during the preparation of the EA/Draft RMP Amendment.
    In the EA, we will discuss impacts that could occur as a result of
the construction and operation of the proposed Project under these
general headings:
     Geology and soils;
     Mineral resources;
     Land use (recreation, aesthetics/visual resource
management, special designations, and livestock grazing);
     Water resources, riparian zones, and wetlands;
     Cultural resources;
     Vegetation;
     Fisheries and wildlife;
     Endangered and threatened species;
     Air quality and noise; and
     Public safety.
    We will also evaluate possible alternatives to the proposed
Project, and make recommendations on how to lessen or avoid impacts on
the various resource areas.
    Although no formal application has been filed, we have already
initiated our NEPA review under the Commission's Pre-filing Process.
The purpose of the Pre-filing Process is to seek public and agency
input early in the Project planning phase and encourage early
involvement of interested stakeholders in a manner that allows for the
early identification and resolution of environmental issues before an
application is filed with the FERC. The BLM has agreed to conduct its
work with all interested stakeholders to identify and attempt to
address issues before and throughout the application process.
    As part of our Pre-filing Process review, FERC has begun to contact
some federal and state agencies to discuss their involvement in the
scoping process and the preparation of the EA. In addition,
representatives from the FERC participated in a public open house
sponsored by MGS in Delta, Utah on March 3, 2009, to explain the
environmental review process to interested stakeholders. On April 8,
2009, the FERC conducted an interagency meeting with agencies and MGS
in Salt Lake City, Utah. The purpose of the meeting was to explain the
FERC's process and solicit comments and concerns about the MGS's
Project from other jurisdictional agencies.
    Our independent analysis of the issues will be discussed in the EA.
The EA/Draft RMP Amendment will be published and mailed to federal,
state, and local agencies, public interest groups, interested
individuals, affected landowners, newspapers, libraries, and the
Commission's official service list for this proceeding.
    A 30-day review and comment period will be provided when the EA/
Draft RMP Amendment are published. The Proposed Plan Amendment for the
Pony Express RMP will be provided a 30-day protest period at that time,
commensurate with a 60-day Governor's Consistency Review in accordance
with Title 43 CFR Part 1600. All comments on the EA will be considered
before the recommendations to the Commission are made. To ensure your
comments are considered, please carefully follow the instructions in
the Public Participation section below.

The BLM's Plan Amendment Process

    As discussed above, the EA will analyze the impacts of amending the
Pony Express RMP to accommodate the Proposal. An amendment is required
because the Pony Express RMP (1990) does not currently allow for major
rights-of-way to be placed outside of identified utility corridors.
Publication of this notice formally initiates the plan amendment
process and begins the scoping process. An interdisciplinary approach
will be used to develop the EA in order to consider a variety of
resource issues and concerns identified. An amendment to the Pony
Express RMP will be based upon the following planning criteria:
     The amendment will be completed in compliance with the
Federal Land Policy and Management Act (FLPMA), NEPA and all other
relevant Federal law, Executive Orders and management policies of the
BLM;
     Where existing planning decisions are still valid, those
decisions will remain unchanged and be incorporated into the new
amendment;
     The amendment will recognize valid existing rights; and
     Native American Tribal consultations will be conducted in
accordance with policy and tribal concerns will be given due
consideration. The planning process would include the consideration of
any impacts on Indian trust assets.
    The BLM regulations in Title 43 CFR Part 1600 and the NEPA process
detailed in the Council on Environmental Quality regulations in Title
40 CFR Parts 1500-1508 guide preparation of plan amendments. The
process is tailored to the anticipated level of public interest and
potential for significant impacts.
    Plan amendments (see Title 43 CFR Part 1610.5-5) change one or more
of the terms, conditions, or decisions of an approved land use plan.
These decisions may include those relating to desired outcomes;
measures to achieve desired outcomes, including resource restrictions;
or land tenure decisions. Plan amendments are required to consider any
proposal or action that does not conform to the plan.
    An applicant may request that the BLM amend the land use plan to
allow an otherwise non-conforming proposal. The amendment and any
implementation actions (i.e., granting the Right-of-Way and Temporary
Use Permit) may be considered together. However, at the decision stage,
the land use plan decisions must be separated from the implementation
decisions.

Currently Identified Environmental Issues

    The EA will discuss impacts that could occur as a result of the
construction and operation of the proposed Project. We have already
identified several issues that we think

deserve attention based on a preliminary review of the proposed
facilities, comments made to us at the MGS's open house, preliminary
consultations with other agencies, and the environmental information
provided by MGS. This preliminary list of issues may be changed based
on your comments and our analysis. Issues include, but are not limited
to:
     Cultural resources that may be affected by the Project;
     Potential impacts on streams, riparian zones, and
wetlands;
     Rights-of-way required for proposed pipeline crossing of
federal lands managed by the BLM and the FS;
     Cumulative impacts of the proposed facilities combined
with past, present, and reasonable foreseeable Projects; and
     Assessment of alternatives, including alternative routes,
that would avoid or reduce impacts on private and federal lands.

Public Participation

    You can make a difference by providing us with your specific
comments or concerns about MGS's proposal. Your comments should focus
on the potential environmental effects, reasonable alternatives, and
measures to avoid or lessen environmental impacts. The more specific
your comments, the more useful they will be. To ensure that your
comments are timely and properly recorded, please send in your comments
so that they will be received in Washington, DC on or before July 27,
2009.
    For your convenience, there are three methods, which you can use to
submit written comments to the Commission. In all instances please
reference the Project docket numbers PF09-3-000 with your submission.
The Commission encourages electronic filing of comments and has
dedicated eFiling expert staff available to assist you at<PHONE_NUMBER>
or<EMAIL_ADDRESS>    (1) You may file your comments electronically by using the Quick
Comment feature, which is located on the Commission's Internet Web site
at http://www.ferc.gov under the link to Documents and Filings. A Quick
Comment is an easy method for interested persons to submit text-only
comments on a Project;
    (2) You may file your comments electronically by using the eFiling
feature, which is located on the Commission's Internet Web site at
http://www.ferc.gov under the link to Documents and Filings. eFiling
involves preparing your submission in the same manner as you would if
filing on paper, and then saving the file on your computer's hard
drive. You will attach that file as your submission. New eFiling users
must first create an account by clicking on ``Sign up'' or
``eRegister.'' You will be asked to select the type of filing you are
making. A comment on a particular project is considered a ``Comment on
a Filing;'' or
    (3) You may file your comments via mail to the Commission by
sending an original and two copies of your letter to: Kimberly D. Bose,
Secretary, Federal Energy Regulatory Commission, 888 First St., NE.,
Room 1A, Washington, DC 20426.
    Label one copy of the comments for the attention of Gas Branch 2,
PJ-11.2.
    You may also submit oral comments at one of two public scoping
meetings identified earlier in this NOI.

Becoming an Intervenor

    Once MGS formally files its applications with the Commission, you
may want to become an ``intervenor,'' which is an official party to the
proceeding. Intervenors play a more formal role in the process and are
able to file briefs, appear at hearings, and be heard by the courts if
they choose to appeal the Commission's final ruling. An intervenor
formally participates in a Commission proceeding by filing a request to
intervene. Instructions for becoming an intervenor are included in the
User's Guide under the ``e-filing'' link on the Commission's Web site.
Please note that you may not request intervenor status at this time.
You must wait until formal applications are filed with the Commission.

Environmental Mailing List

    An effort is being made to send this notice to all individuals,
organizations, and government entities interested in and/or potentially
affected by the proposed Project. This includes all landowners who are
potential right-of-way grantors, whose property may be used temporarily
for Project purposes, or who own homes within certain distances of
aboveground facilities (as defined in the Commission's regulations).
    If you do not want to send comments at this time but still want to
remain on our mailing list, please return the Information Request
(Appendix 2). If you do not return the Information Request, you will be
taken off the mailing list.

Availability of Additional Information

    Additional information about the Project is available from the
Commission's Office of External Affairs, at 1-866-208-FERC or on the
FERC Internet Web site (http://www.ferc.gov) using the eLibrary link.
Click on the eLibrary link, click on ``General Search'' and enter the
docket number excluding the last three digits (i.e., PF09-3) in the
Docket Number field. Be sure you have selected an appropriate date
range. For assistance, please contact FERC Online Support at
<EMAIL_ADDRESS>or toll free at 1-866-208-3676, or for TTY,
contact<PHONE_NUMBER>. The eLibrary link also provides access to the
texts of formal documents issued by the Commission, such as orders,
notices, and rulemakings.
    In addition, the Commission now offers a free service called
eSubscription, which allows you to keep track of all formal issuances
and submittals in specific dockets. This can reduce the amount of time
you spend researching proceedings by automatically providing you with
notification of these filings, document summaries and direct links to
the documents. Go to http://www.ferc.gov/esubscribenow.htm.
    Finally, public meetings or site visits will be posted on the
Commission's calendar located at http://www.ferc.gov/EventCalendar/
EventsList.aspx along with other related information.

Kimberly D. Bose,
Secretary.
[FR Doc. E9-14933 Filed 6-24-09; 8:45 am]

BILLING CODE 6717-01-P