[Federal Register Volume 85, Number 66 (Monday, April 6, 2020)]
[Rules and Regulations]
[Pages 19077-19080]
[FR Doc No: 2020-07140]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0019; Product Identifier 2017-SW-074-AD; Amendment
39-19881; AD 2020-06-12]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD
requires determining the accumulated hours time-in-service (TIS) of
certain part-numbered main gearbox (MGB) suspension bar attachment
bolts and fittings, applying a life limit add-on factor, and inspecting
the torque of certain MGB suspension bar attachment nuts. This AD was
prompted by a report of torque loss on an MGB suspension bar bolt. The
actions of this AD are intended to address an unsafe condition on these
products.

DATES: This AD is effective May 11, 2020.
    The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of May 11, 2020.

ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX
75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>; or at
https://www.airbus.com/helicopters/services/technical-support.html. You
may view this referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0019.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2018-0019; or in person at Docket
Operations between 9 a.m. and 5 p.m.,

Monday through Friday, except Federal holidays. The AD docket contains
this AD, the European Union Aviation Safety Agency (previously European
Aviation Safety Agency) (EASA) AD, any service information that is
incorporated by reference, any comments received, and other
information. The street address for Docket Operations is U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC
20590.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone<PHONE_NUMBER>;
email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    On December 9, 2019, at 84 FR 67248, the Federal Register published
the FAA's notice of proposed rulemaking (NPRM), which proposed to amend
14 CFR part 39 by adding an AD that would apply to Airbus Helicopters
Model AS332L2 and EC225LP helicopters, with an MGB suspension bar front
attachment bolt (bolt) part number (P/N) 332A22-1613-21 or 332A22-1613-
20, MGB suspension bar rear bolt P/N 332A22-1614-20, MGB suspension bar
front attachment fitting (fitting) P/N 332A22-1623-01, MGB suspension
bar rear left hand fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB
suspension bar rear right hand fitting P/N 332A22-1624-03 or 332A22-
1624-05 installed.
    For Airbus Helicopters Model AS332L2 and EC225LP helicopters, the
NPRM proposed to require, within 30 hours time-in-service (TIS), re-
calculating the life limit accumulated by each front and rear bolt by
applying an add-on factor listed in the applicable service information.
For each bolt that meets or exceeds its life limit, also known as
service life limit (SLL), the NPRM proposed to require removing each
bolt from service before further flight. For each bolt that has not
exceeded its life limit, the NPRM proposed to require continuing to
calculate and record the life limit of each bolt on its component
history card or equivalent record and removing the bolt from service
before reaching its life limit.
    For Model AS332L2 helicopters, the NPRM proposed to require, within
30 hours TIS, re-calculating the life limit accumulated by the front,
rear left hand, and rear right hand fittings by applying an add-on
factor listed in the applicable service information. For each fitting
that meets or exceeds its life limit, the NPRM proposed to require
removing the fitting from service before further flight. For each
fitting that has not exceeded its life limit, the NPRM proposed to
require continuing to calculate and record the life limit of each
fitting on its component history card or equivalent record and removing
the fitting from service before reaching its life limit.
    For Model AS332L2 helicopters, the NPRM proposed to require, within
150 hours TIS (without applying an add on-factor), inspecting the
torque of each MGB suspension bar fitting front and rear nut. If the
torque on any nut is higher than the maximum allowable limit, the NPRM
proposed to require removing the nut and its bolt from service before
further flight. If the torque on any nut is lower than the minimum
allowable limit, the NPRM proposed to require tightening the nut before
further flight and removing the nut and its bolt from service within
150 hours TIS.
    The proposed requirements were intended prevent the MGB suspension
bar bolts and fittings remaining in service beyond their fatigue life,
which could result in structural failure of the MGB suspension bar and
loss of helicopter control.
    The NPRM was prompted by EASA AD No. 2017-0189, dated September 22,
2017, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition for Airbus
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)
Model AS 332 L2 and EC 225 LP helicopters. EASA advises that the
installation of the MGB upper deck fittings of the three MGB suspension
bars could lead to tightening torque loss on the fittings' attachment
pins (bolts). Due to design similarities, Model AS 332 L2 helicopters
could also be affected by the same installation condition. An
investigation determined that the life limits in the Airworthiness
Limitations Sections for the pins and fittings are valid if an ``add-on
penalty factor'' is applied.
    EASA states that this condition, if not corrected, could lead to
structural failure of the MGB suspension bar attachment pins or
fittings. Accordingly, the EASA AD requires applying the add-on penalty
factor to the flight hours to re-calculate the life limits and
replacing an affected part before exceeding its life limit. EASA
further advises that Airbus Helicopters' initial service information
contained an error that may have resulted in the installation of pins
or fittings using an incorrect torque value. As a result, the EASA AD
also requires replacing pins if an incorrect torque value was applied
and reporting the information to Airbus Helicopters.

Comments

    The FAA gave the public the opportunity to participate in
developing this AD, but the FAA did not receive any comments on the
NPRM.

FAA's Determination

    These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA is issuing this AD after
evaluating all information provided by EASA and determining the unsafe
condition exists and is likely to exist or develop on other helicopters
of these same type designs and that air safety and the public interest
require adopting the AD requirements as proposed.

Differences Between This AD and the EASA AD

    The EASA AD allows an optional 150 hours TIS extension to the life
limit of an affected fitting for Model AS 332 L2 helicopters by
performing dye-penetrant inspections. This AD does not allow this
option. For Model AS 332 L2 helicopters, the EASA AD requires replacing
pins (bolts) that are replacement pins installed before the AD's
effective date with an incorrect torque value applied. This AD requires
inspecting the torque for each nut for Model AS 332 L2 helicopters
instead and depending on the outcome, removing the nut and its bolt
from service. The EASA AD requires reporting certain information to
Airbus Helicopters, while this AD does not.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Emergency Alert Service
Bulletin (EASB) No. 01.00.86 for Model AS332 helicopters and Airbus
Helicopters EASB No. 04A013 for Model EC225LP helicopters, both
Revision 1 and dated August 25, 2017. This service information
specifies applying an add-on factor to the flying hours logged by the
pins and fittings and replacing them if the SLL is exceeded. If an
incorrect tightening torque value was applied to the pins, the service
information specifies replacing the pins and contacting Airbus
Helicopters.
    This service information is reasonably available because the
interested parties have access to it through their normal

course of business or by the means identified in the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 23 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
    Determining the adjusted life limit for the bolts and fittings
takes about 0.5 work-hour for an estimated cost of $43 per helicopter
and $989 for the U.S. fleet.
    Replacing a bolt takes about 4 work-hours and parts cost about $89
for an estimated cost of $429 per bolt.
    There are no costs of compliance for replacing a fitting and
inspecting, and if necessary tightening, the torque for Model AS332L2
helicopters by this AD because there are no Model AS332L2 helicopters
on the U.S. Registry.

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.
    The FAA is 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 helicopters identified in this rulemaking action.

Regulatory Findings

    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 that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order
12866,
    2. Will not affect intrastate aviation in Alaska, 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.

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 airworthiness
directive (AD):

2020-06-12 Airbus Helicopters: Amendment 39-19881; Docket No. FAA-
2018-0019; Product Identifier 2017-SW-074-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS332L2 and EC225LP
helicopters, certificated in any category, with a main gearbox (MGB)
suspension bar front attachment bolt (bolt) part number (P/N)
332A22-1613-21 or 332A22-1613-20, MGB suspension bar rear bolt P/N
332A22-1614-20, MGB suspension bar front attachment fitting
(fitting) P/N 332A22-1623-01, MGB suspension bar rear left hand
fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB suspension bar
rear right hand fitting P/N 332A22-1624-03 or 332A22-1624-05
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as MGB suspension bar bolts
and fittings remaining in service beyond their fatigue life and
loose MGB suspension bar bolts or fittings, which could result in
structural failure of the MGB suspension bar and loss of helicopter
control.

(c) Effective Date

    This AD becomes effective May 11, 2020.

(d) Compliance

    You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.

(e) Required Actions

    (1) Within 30 hours time-in-service (TIS), review records to
determine the total hours TIS of each MGB suspension bar bolt.
    (i) Determine the life limit of each bolt by applying the hours
TIS by the add-on factor listed in Table No. 1 of Airbus Helicopters
Emergency Alert Service Bulletin No. 01.00.86, Revision 1, dated
August 25, 2017 (EASB 01.00.86), or Airbus Helicopters Emergency
Alert Service Bulletin No. 04A013, Revision 1, dated August 25,
2017, as applicable to your model helicopter.
    Note 1 to paragraph (e)(1)(i) of this AD: Airbus Helicopters
refers to bolts as ``pins.''
    (A) Before further flight, remove from service any bolt that has
reached or exceeded its life limit.
    (B) For each bolt that has not exceeded its life limit, continue
to calculate and record the life limit on its component history card
or equivalent record by applying the add-on factor each time the
helicopter accumulates hours TIS, and remove from service any bolt
before reaching its life limit.
    (ii) Thereafter following paragraph (e)(1)(i) of this AD,
continue to calculate and record the life limit of each bolt on its
component history card or equivalent record by applying the add-on
factor each time the helicopter accumulates hours TIS and remove
from service any bolt before reaching its life limit.
    (2) For Model AS332L2 helicopters, within 30 hours TIS, review
records to determine the total hours TIS of each MGB suspension bar
fitting.
    (i) Determine the life limit of each fitting by applying the
hours TIS by the add-on factor listed in Table No. 1 of EASB
01.00.86.
    (A) Before further flight, remove from service any fitting that
has reached or exceeded its life limit.
    (B) For each fitting that has not exceeded its life limit,
continue to calculate and record the life limit on its component
history card or equivalent record by applying the add-on factor each
time the helicopter accumulates hours TIS, and remove from service
any fitting before reaching its life limit.
    (ii) Thereafter following paragraph (e)(2)(i) of this AD,
continue to calculate and record the life limit of each fitting on
its component history card or equivalent record by applying the add-
on factor each time the helicopter accumulates hours TIS and remove
from service any fitting before reaching its life limit.
    (3) For Model AS332L2 helicopters, within 150 hours TIS (without
the add-on factor), inspect the torque of each MGB suspension bar
attachment front and rear nut. The allowable torque for each front
nut is 602-663 lbf. in (6.8-7.5 daN.m) and the allowable torque for
each rear nut is 337-398 lbf. in (3.8-4.5 daN.m).
    (i) If the torque on any nut is higher than the maximum
allowable torque stated in paragraph (e)(3) of this AD, before
further flight, remove from service the bolt and nut.
    (ii) If the torque on any nut is lower than the minimum
allowable torque value stated in paragraph (e)(3) of this AD, before
further flight, tighten the nut to the allowable torque stated in
paragraph (e)(3) of this AD. Within 150 hours TIS (without the add-
on factor), remove from service any bolt and nut that were tightened
as required by this paragraph.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
Matt Fuller, Senior Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA, 10101

Hillwood Pkwy., Fort Worth, TX 76177; telephone<PHONE_NUMBER>; email
<EMAIL_ADDRESS>    (2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or certificate holding district office, before operating any
aircraft complying with this AD through an AMOC.

(g) Additional Information

    The subject of this AD is addressed in European Union Aviation
Safety Agency (previously European Aviation Safety Agency) (EASA) AD
No. 2017-0189, dated September 22, 2017. You may view the EASA AD on
the internet at https://www.regulations.gov in Docket No. FAA-2018-
0019.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor
Gearbox.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Helicopters Emergency Alert Service Bulletin (EASB)
No. 01.00.86, Revision 1, dated August 25, 2017.
    (ii) Airbus Helicopters EASB No. 04A013, Revision 1, dated
August 25, 2017.
    (3) For service information identified in this AD, contact
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052;
telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>; or at
https://www.airbus.com/helicopters/services/technical-support.html.
    (4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call<PHONE_NUMBER>.
    (5) You may view this 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, email<EMAIL_ADDRESS>or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on March 25, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-07140 Filed 4-3-20; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register: December 11, 2008 (Volume 73, Number 239)]
[Rules and Regulations]
[Page 75305-75307]
[DOCID:fr11de08-1]

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Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0590; Directorate Identifier 2008-NM-057-AD;
Amendment 39-15765; AD 2008-25-07]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, and 747SR Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes.
This AD requires repetitive inspections for cracks or fractures of the
forward end attachment and the forward lower flange of the flap tracks
of the trailing edge flaps, and corrective actions if necessary. For
certain airplanes, this AD would also require modifying the fail-safe
links of the main carriage. This AD results from a detailed structural
analysis of the flap attach structural and fail-safe components,
accomplished as a result of a dynamic stability and control analysis,
which could not demonstrate continued safe flight and landing of the
airplane after the loss of a trailing edge flap. We are issuing this AD
to detect and correct cracks or fractures of the primary structural and
fail-safe load paths of the inboard and outboard trailing edge flaps,
which could result in the loss of a flap during takeoff or landing,
reducing flightcrew ability to maintain the safe flight and landing of
the airplane.

DATES: This AD is effective January 15, 2009.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 15,
2009.

ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1, fax<PHONE_NUMBER>; e-mail<EMAIL_ADDRESS>
Internet https://www.myboeingfleet.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone<PHONE_NUMBER>) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6443; fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that would apply to
all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C,
747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series
airplanes. That NPRM was published in the Federal Register on May 23,
2008 (73 FR 30003) That NPRM proposed to require repetitive inspections
for cracks or fractures of the forward end attachment and the forward
lower flange of the flap tracks of the trailing edge flaps, and
corrective actions if necessary. For certain airplanes, that NPRM would
also require modifying the fail-safe links of the main carriage.

Comments

    We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the commenters.

Support for the NPRM

    Boeing has reviewed the NPRM and concurs with the content of the
proposed rule.

Request To Extend Certain Compliance Times

    Northwest Airlines (NWA) asks that the repetitive inspection
intervals for the Part 1 inspections, as required by paragraph (f) of
the NPRM, be changed to specify intervals not to exceed 750 flight
cycles after accomplishing the last inspection or within 750 flight
cycles after the flap track overhaul, whichever occurs later. For Part
3 inspections, NWA asks that the repetitive inspection interval be
changed to intervals not to exceed 1,500 flight cycles after
accomplishing the last inspection or within 1,500 flight cycles after
flap track overhaul, whichever occurs later. NWA adds that the reason
for the request is that, as part of its procedure for removing the
track for overhaul, the attaching fuse pin is removed and inspected and
the defined support fitting is inspected for condition; any failure of
the track would be detected during the track overhaul.
    We do not agree with NWA's request to change the repetitive
inspection interval. The structural analysis of the flap attach
structural and fail-safe components supports the compliance time
specified for the repetitive inspection interval. In developing an
appropriate compliance time for this action, we considered the urgency
associated with the subject unsafe condition and the practical aspect
of accomplishing the required inspections within a period of time that
corresponds to the normal scheduled maintenance for most affected
operators. These maintenance schedules can vary greatly from operator
to operator. In light of these items, we have determined that the
repetitive inspection intervals specified in the service bulletin are
appropriate. However, according to the provisions of paragraph (j) of
this AD, we may approve requests to adjust the compliance time if the
request includes data that prove that the new compliance time would
provide an acceptable level

of safety. We have not changed the AD in this regard.
    NWA also asks that the FAA review the 750-flight-cycle repetitive
inspection interval requirement, and if supported by new analysis,
change it to 1,000 flight cycles. NWA states that a 1,000-flight-cycle
interval would permit accomplishing the inspections in conjunction with
scheduled airplane maintenance.
    We do not agree with the request to change the interval for the
repetitive inspections to 1,000 flight cycles. Previous analysis
supports the current 750-flight-cycle interval, and no new analysis is
currently available. However, as noted in the response to the previous
comment, we will consider requests for approval of an AMOC if
sufficient data are submitted that the new compliance time would
provide an acceptable level of safety. We have not changed the AD in
this regard.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.

Costs of Compliance

    We estimate that this AD affects 190 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                Number of
                                                             Average                                                     U.S.-
              Action                      Work hours        labor rate          Parts             Cost per product     registered        Fleet cost
                                                             per hour                                                  airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Part 1 Inspections................  4....................          $80  $0...................  $320 per inspection            190  $60,800 per
                                                                                cycle.                              inspection cycle.
Part 3 Inspections................  4....................           80  $0...................  $320 per inspection            190  $60,800 per
                                                                                cycle.                              inspection cycle.
Part 2 Modification for Groups 1-3  Between 3 and 7......           80  Between $212 and       Between $452 and               182  Between $82,264 and
 Airplanes.                                                              $7,934.                $8,494.                             $1,545,908.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

    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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Is not a ``significant rule'' under 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.
    You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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:

2008-25-07 Boeing: Amendment 39-15765. Docket No. FAA-2008-0590;
Directorate Identifier 2008-NM-057-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective January 15,
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, and 747SR series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a detailed structural analysis of the
flap attach structural and fail-safe components accomplished as a
result of a dynamic stability and control analysis, which could not
demonstrate continued safe flight and landing of the airplane after
the loss of a trailing edge flap. We are issuing this AD to detect
and correct cracks or fractures of the primary structural and fail-
safe load paths of the inboard and outboard trailing edge flaps,
which could result in the loss of a flap during takeoff or landing,
reducing flightcrew ability to maintain the safe flight and landing
of the airplane.

Compliance

    (e) Comply with this AD within the compliance times specified,
unless already done.

Repetitive Inspections/Corrective Actions

    (f) For all airplanes: Except as provided by paragraph (h) of
this AD, at the applicable times specified in paragraph 1.E. of
Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008,
inspect for cracks or fractures of the forward end attachment and
the forward lower flange of the flap tracks of the trailing edge
flaps, and do all applicable corrective actions, by doing all the
actions specified in Parts 1 and 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2323, dated

February 21, 2008, except as provided by paragraph (i) of this AD.
Do all applicable corrective actions before further flight. Repeat
the applicable inspection at the applicable time specified in
paragraph 1.E. of Boeing Alert Service Bulletin 747-57A2323, dated
February 21, 2008.

Modification of Fail Safe Links of Main Carriage

    (g) For Groups 1, 2, and 3 airplanes: Within 24 months after the
effective date of this AD, replace the fail-safe links, pins, and
attachment hardware in accordance with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2323, dated
February 21, 2008.

Exception to Compliance Times

    (h) Where Boeing Alert Service Bulletin 747-57A2323, dated
February 21, 2008, specifies counting the compliance time from ``* *
* the date on this service bulletin,'' this AD requires counting the
compliance time from the effective date of this AD.

Exception to Corrective Actions

    (i) If any fractured support fitting is found during any
inspection required by this AD, and Boeing Alert Service Bulletin
747-57A2323, dated February 21, 2008, specifies to contact Boeing
for appropriate action: Before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(j) of this AD.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Gary Oltman, Aerospace Engineer, Airframe Branch, ANM-
120S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356;
telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>; has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19.
    (2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.

Material Incorporated by Reference

    (k) You must use Boeing Alert Service Bulletin 747-57A2323,
dated February 21, 2008; to do the actions required by this AD,
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1, fax<PHONE_NUMBER>; e-mail
<EMAIL_ADDRESS>Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information that is
incorporated by reference at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For
information on the availability of this material at the FAA, call
425-227-1221 or<PHONE_NUMBER>.
    (4) You may also review copies of the service information 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 November 28, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
 [FR Doc. E8-29073 Filed 12-10-08; 8:45 am]

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[Federal Register: March 15, 2006 (Volume 71, Number 50)]
[Notices]
[Page 13369-13370]
[DOCID:fr15mr06-79]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. RP06-240-000]

National Fuel Gas Supply Corporation; Notice of Tariff Filing

March 7, 2006.
    Take notice that on February 28, 2006, National Fuel Gas Supply
Corporation (National) tendered for filing as part of its FERC Gas
Tariff, Fourth Revised Volume No. 1, Eighty Seventh Revised Sheet No.
9, to become effective March 1, 2006.
    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 and 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 in accordance with the provisions of
section 154.210 of the Commission's regulations (18 CFR 154.210).
Anyone filing an intervention or protest must serve a copy of that
document on the Applicant. Anyone filing an intervention or protest on
or before the intervention or protest date need not serve motions to
intervene or protests on persons other than the Applicant.
    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 on-line 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''
link on the Web site that enables subscribers to receive e-mail
notification when a document is added to a subscribed docket(s). For
assistance with any FERC Online service, please e-mail
<EMAIL_ADDRESS>or call<PHONE_NUMBER> (toll free). For

TTY, call<PHONE_NUMBER>.

Magalie R. Salas,
Secretary.
[FR Doc. E6-3651 Filed 3-14-06; 8:45 am]

BILLING CODE 6717-01-P


[Federal Register Volume 80, Number 230 (Tuesday, December 1, 2015)]
[Notices]
[Page 75081]
[FR Doc No: 2015-30403]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 14689-000]

Energy Resources USA Inc., Notice of Preliminary Permit
Application Accepted for Filing and Soliciting Comments and Motions To
Intervene

    On June 26, 2015, Arkansas Electric Cooperative Corporation, filed
an application for a preliminary permit, pursuant to section 4(f) of
the Federal Power Act (FPA), proposing to study the feasibility of a
hydropower project to be located at the U.S. Army Corps of Engineers'
(Corps) Col. Charles D. Maynard Lock and Dam on the Arkansas River near
the town of Pine Bluff in Jefferson County, Arkansas. The sole purpose
of a preliminary permit, if issued, is to grant the permit holder
priority to file a license application during the permit term. A
preliminary permit does not authorize the permit holder to perform any
land-disturbing activities or otherwise enter upon lands or waters
owned by others without the owners' express permission.
    The proposed project would consist of the following: (1) A 100-
foot-long overflow bank extension connecting to the existing dam; (2) a
770-foot-long, 300-foot-wide intake channel with a 85-foot-long
retaining wall; (3) a 220-foot-long, 90-foot-wide powerhouse containing
four generating units with a total capacity of 18 megawatts; (4) a
1000-foot-long, 220-foot-wide tailrace with a 85-foot-long retaining
wall; (5) a 4.16/69 kilo-Volt (kV) substation; and (6) a 3-mile-long,
69 kV transmission line. The proposed project would have an estimated
average annual generation of 123,700 megawatt-hours, and operate as
directed by the Corps.
    Applicant Contact: Mr. Ander Gonzalez, Energy Resources USA Inc.,
2655 Le Jeune Road, Suite 804, Coral Gables, Florida 33134; Phone: +34
93 252 38 40; Email<EMAIL_ADDRESS>    FERC Contact: Christiane Casey<EMAIL_ADDRESS>(202)
502-8577.
    Competing Application: This application competes with Project No.
14665-000 filed March 3, 2015. Competing applications had to be filed
on or before July 20, 2015.
    Deadline for filing comments and motions to intervene: 60 days from
the issuance of this notice. Comments and motions to intervene may be
filed electronically via the Internet. See 18 CFR 385.2001(a)(1)(iii)
and the instructions on the Commission's Web site http://www.ferc.gov/docs-filing/efiling.asp. Commenters can submit brief comments up to
6,000 characters, without prior registration, using the eComment system
at http://www.ferc.gov/docs-filing/ecomment.asp. You must include your
name and contact information at the end of your comments. For
assistance, please contact FERC Online Support at
<EMAIL_ADDRESS>or toll free at 1-866-208-3676, or for TTY,
(202) 502-8659. Although the Commission strongly encourages electronic
filing, documents may also be paper-filed. To paper-file, mail an
original and five copies to: Kimberly D. Bose, Secretary, Federal
Energy Regulatory Commission, 888 First Street NE., Washington, DC
20426.
    More information about this project, including a copy of the
application, can be viewed or printed on the ``eLibrary'' link of
Commission's Web site at http://www.ferc.gov/docs-filing/elibrary.asp.
Enter the docket number (P-14689) in the docket number field to access
the document. For assistance, contact FERC Online Support.

    Dated: November 24, 2015.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2015-30403 Filed 11-30-15; 8:45 am]
BILLING CODE 6717-01-P