[Federal Register Volume 81, Number 243 (Monday, December 19, 2016)]
[Rules and Regulations]
[Pages 91695-91698]
[FR Doc No: 2016-29511]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7425; Directorate Identifier 2014-NM-244-AD;
Amendment 39-18741; AD 2016-25-15]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2011-17-05,
for certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-
103, A300 B4-203, and A300 B4-2C airplanes. AD 2011-17-05 required
repetitive inspections in sections 13 through 18 of the fuselage
between rivets of the longitudinal lap joints between frames (FRs) 18
and 80 for cracking, and repair or modification if necessary. This new
AD requires a revised repetitive inspection program of all longitudinal
lap joints and repairs between FRs 18 and 80 to address widespread
fatigue damage (WFD). This AD was prompted by an evaluation done by the
design approval holder indicating that certain sections of the
longitudinal lap joints are subject to WFD; therefore, a revised
inspection program is necessary. We are issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective January 23, 2017.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 16,
2011 (76 FR 63177, October 12, 2011).

ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email<EMAIL_ADDRESS>Internet
http://www.airbus.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call<PHONE_NUMBER>. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7425.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7425; 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 800-
647-5527) is Docket 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2011-17-05, Amendment 39-16769 (76 FR 63177,
October 12, 2011) (``AD 2011-17-05''). AD 2011-17-05 applied to certain
Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300
B4-203, and A300 B4-2C airplanes. The NPRM published in the Federal
Register on July 7, 2016 (81 FR 44232). The NPRM was prompted by an
evaluation done by the design approval holder indicating that certain
sections of the longitudinal lap joints are subject to WFD. The NPRM
proposed to continue to require repetitive inspections in sections 13
through 18 of the fuselage between rivets of the longitudinal lap
joints between FRs 18 and 80 for cracking, and repair or modification
if necessary. The NPRM also proposed to require a revised repetitive
inspection program of all longitudinal lap joints and repairs between
FRs 18 and 80 to address this WFD. We are issuing this AD to detect and
correct fatigue cracking of the longitudinal lap joints of the
fuselage, which could result in reduced structural integrity of the
airplane.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2014-0265, dated December 9, 2014 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for the specified products.
    The MCAI states:

    Cracks were found on in-service aeroplanes in sections 13 to 18
of the fuselage between rivets of longitudinal lap joints between
frames (FR) 18 and FR80.
    This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
    To address this unsafe condition, Airbus developed an inspection
programme for the longitudinal lap joints and repairs between FR18
and FR80, and EASA issued AD 2007-0091 [which corresponds to FAA AD
2011-17-05] to require the implementation of that programme.
    Since EASA AD 2007-0091 was issued, [a] new Widespread Fatigue
Damage regulation has been issued. This new regulation led to the
revision of the maintenance programme for the longitudinal lap
joints and repairs between FR18 and FR80.
    For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2007-0091, which is superseded, and requires
implementation of the revised inspection programme.

    Required actions include repetitive inspections of the bonded inner
doublers of the longitudinal lap joints in sections 13 through 18 for
disbonding or corrosion, and repairing any disbonding and corrosion; a
follow-on rototest or ultrasonic inspection to verify cracking, and
repair of any cracking. The repetitive inspection interval ranges from
3,000 flight cycles up to 8,000 flight cycles, depending on airplane
configuration. You may examine the MCAI in the AD docket on the
Internet at http://www.regulations.gov by searching for and locating it
in Docket No. FAA-2016-7425.

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.

Conclusion

    We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed, except for
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.

Costs of Compliance

    We estimate that this AD affects 4 airplanes of U.S. registry.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
                    Action                                 Labor cost                 product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2011-17-05...........  3,735 work-hours x $85 per hour         $317,475      $1,269,900
                                                 = $317,475.
New inspections...............................  140 work-hours x $85 per hour =          $11,900         $47,600
                                                 $11,900.
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    We have received no definitive data that enables us to provide cost
estimates for the on-condition actions specified in this AD.

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 that 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 removing Airworthiness Directive (AD)
2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011), and
adding the following new AD:

2016-25-15 Airbus: Amendment 39-18741; Docket No. FAA-2016-7425;
Directorate Identifier 2014-NM-244-AD.

(a) Effective Date

    This AD is effective January 23, 2017.

(b) Affected ADs

    This AD replaces AD 2011-17-05, Amendment 39-16769 (76 FR 63177,
October 12, 2011) (``AD 2011-17-05'').

(c) Applicability

    This AD applies to Airbus Model A300 B2-1C, A300 B2-203, A300
B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes;
certificated in any category; all manufacturer serial numbers,
except those on which Airbus Modification 2611 has been embodied in
production.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation done by the design
approval holder indicating that certain sections of the longitudinal
lap joints are subject to widespread fatigue damage. We are issuing
this AD to detect and correct fatigue cracking of the longitudinal
lap joints of the fuselage, which could result in reduced structural
integrity of the airplane.

(f) Compliance

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

(g) Retained Fuselage Inner Doubler Inspections and Repair, With
Revised Formatting

    This paragraph restates the requirements of paragraph (l) of AD
2011-17-05, with revised formatting. For airplanes on which any
inspections of the fuselage bonded inner doublers of the
longitudinal lap joints in sections 13 through 18 (except sections
16 and 17 at stringer 31 left-hand and right-hand) for disbonding
and cracking have not been done as of November 16, 2011 (the
effective date of AD 2011-17-05), as specified by Airbus Service
Bulletin A300-53-229: Prior to the accumulation of 24,000 total
flight cycles or within 15 years since new, whichever occurs first;
or within 60 days after November 16, 2011; whichever occurs later;
do a detailed inspection of the fuselage bonded inner doublers of
the longitudinal lap joints in sections 13 through 18 (except
sections 16 and 17 at stringer 31 left-hand and right-hand) for
disbonding and cracking, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997. If no disbonding and no cracking are found,
repeat the inspection thereafter at the applicable intervals
specified in paragraph (h) of this AD.
    (1) If no cracking is found, and ``minor'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated
April 8, 1997, is found: Repeat the inspection thereafter at
intervals not to exceed 1 year for areas below stringer 22, and at
intervals not to exceed 2 years for areas above and including
stringer 22.
    (2) If no cracking is found, and ``major'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated
April 8, 1997, is found: Within 1,000 flight cycles after doing the
inspection, repair, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in
accordance with Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.

(h) Retained Repetitive Intervals for Inspections for Disbonding and
Cracking, With No Changes

    This paragraph restates the repetitive intervals specified in
table 1 of AD 2011-17-05, with no changes. At the applicable time
specified in paragraph (h)(1) or (h)(2) of this AD, repeat the
inspection required by paragraph (g) of this AD.
    (1) For sections 13 and 14 as specified in Airbus Service
Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the
inspection at intervals not to exceed 7 years or 12,000 flight
cycles, whichever occurs first.
    (2) For sections 15 through 18 as specified in Airbus Service
Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the
inspection within 8.5 years or 12,000 flight cycles, whichever
occurs first.

(i) Retained Fuselage Inner Doubler Inspections and Repair, With No
Changes

    This paragraph restates the requirements of paragraph (m) of AD
2011-17-05, with no changes. For airplanes on which any inspections
of the fuselage bonded inner doublers of the longitudinal lap joints
in sections 13 through 18 (except sections 16 and 17 at stringer 31
left-hand and right-hand) for disbonding and cracking have been done
as of November 16, 2011 (the effective date of AD 2011-17-05), as
specified in Airbus Service Bulletin A300-53-229; except for
airplanes on which a repair of that area has been done as specified
in Airbus Service Bulletin A300-53-229: Within 7 years or 12,000
flight cycles (for sections 13 and 14), or within 8.5 years or
12,000 flight cycles (for sections 15 and 18), after doing the
inspection, whichever occurs first; or within 60 days after November
16, 2011, whichever occurs later, do a detailed inspection of the
fuselage bonded inner doublers of the longitudinal lap joints in
sections 13 through 18 (except sections 16 and 17 at stringer 31
left-hand and right-hand) for disbonding and cracking, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and
no cracking are found, repeat the inspection at the applicable time
specified in paragraph (h) of this AD.
    (1) If no cracking is found, and ``minor'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated
April 8, 1997, is found: Repeat the inspection thereafter at
intervals not to exceed 1 year for areas below stringer 22, and at
intervals not to exceed 2 years for areas above and including
stringer 22.
    (2) If no cracking is found, and ``major'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated
April 8, 1997, is found: Within 1,000 flight cycles after doing the
inspection, repair, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in
accordance with Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.

(j) Retained Fuselage Inner Doubler Inspections and Repair, With No
Changes

    This paragraph restates the requirements of paragraph (n) of AD
2011-17-05, with no changes. For airplanes on which any inspections
of the fuselage bonded inner doublers of the longitudinal lap joints
in sections 16 and 17 at stringer 31 left-hand and right-hand for
disbonding and cracking have not been done as of November 16, 2011
(the effective date of AD 2011-17-05), as specified in Airbus
Service Bulletin A300-53-229: Prior to the accumulation of 24,000
total flight cycles or within 12 years since new, whichever occurs
first; or within 60 days after November 16, 2011, whichever occurs
later, do a detailed inspection of the fuselage bonded inner
doublers of the longitudinal lap joints in sections 16 and 17 at
stringer 31 left-hand and right-hand for disbonding and cracking, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no
disbonding and no cracking are found, repeat the inspection
thereafter at intervals not to exceed 7 years or 12,000 flight
cycles, whichever occurs first.
    (1) If no cracking is found, and ``minor'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated
April 8, 1997, is found: Repeat the inspection thereafter at
intervals not to exceed 1 year for areas below stringer 22, and at
intervals not to exceed 2 years for areas above and including
stringer 22. Doing a repair in accordance with Airbus Service
Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates
the repetitive inspections required by this paragraph for that area.
    (2) If no cracking is found, and ``major'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated
April 8, 1997, is found: Within 1,000 flight cycles after doing the
inspection, repair, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in
accordance with Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.

(k) Retained Fuselage Inner Doubler Inspections and Repair, With No
Changes

    This paragraph restates the requirements of paragraph (o) of AD
2011-17-05, with no changes. For airplanes on which any inspections
of the fuselage bonded inner doublers of the longitudinal lap joints
in sections 16 and 17 at stringer 31 left-hand and right-hand for
disbonding and cracking have been done as of November 16, 2011, as
specified in Airbus Service Bulletin A300-53-229; except airplanes
on which a repair of that area has been done as specified in Airbus
Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles
after doing the inspection, whichever occurs first; or within 60
days after November 16, 2011; whichever occurs later; do a detailed
inspection of the fuselage bonded inner doublers of the longitudinal
lap joints in sections 16 and 17 at stringer 31 left-hand and right-
hand for disbonding and cracking, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-229,
Revision 5, dated April 8, 1997. If no disbonding and no corrosion
are found, repeat the inspection thereafter at intervals not to
exceed 7 years or 12,000 flight cycles, whichever occurs first.
    (1) If no cracking is found, and ``minor'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated
April 8, 1997, is found: Repeat the inspection thereafter at
intervals not to exceed 1 year for areas below stringer 22, and at
intervals not to exceed 2 years for areas above and including
stringer 22. Doing a repair, in accordance with Airbus Service
Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates
the repetitive inspections required by this paragraph for that area.
    (2) If no cracking is found, and ``major'' disbonding, as
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated
April 8, 1997, is found: Within 1,000 flight cycles after doing the
inspection, repair, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in
accordance with Airbus Service Bulletin A300-53-229, Revision 5,
dated April 8, 1997.

(l) New Repetitive Inspections and Repair

    Within 180 days after the effective date of this AD, do rototest
and ultrasonic inspections, as applicable, for cracking of all
longitudinal lap joints and repairs between frames 18 and 80; and
repair any cracking before further flight; using a method approved
by the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). Repeat the
applicable inspection, including post-repair inspections, thereafter
at intervals approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
Accomplishing the initial inspection and applicable repairs required
by this paragraph terminates the actions required by paragraphs (g)
through (k) of this AD.

(m) Other FAA AD Provisions

    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, WA 98057-
3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information may be
emailed to<EMAIL_ADDRESS>Before using any
approved AMOC, notify your appropriate 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.
    (2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.

(n) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA AD 2014-0265, dated December 9, 2014, for related information.
This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2016-7425.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) 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 this AD specifies otherwise.
    (3) The following service information was approved for IBR on
November 16, 2011 (76 FR 63177, October 12, 2011).
    (i) Airbus Service Bulletin A300-53-229, Revision 5, dated April
8, 1997, including Appendix A300SB/53-229, dated April 10, 1989.
Only pages 1, 2, 5, 11, and 12 of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997, show revision level 5 and
issue date April 8, 1997; pages 3, 4-10, and 13-17 show revision
level 4 and issue date March 30, 1994; and pages 1-17 of Appendix
A300SB/53-229 show issue date April 10, 1989.
    (ii) Reserved.
    (4) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email<EMAIL_ADDRESS>
Internet http://www.airbus.com.
    (5) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
    (6) 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, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 1, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-29511 Filed 12-16-16; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register: November 28, 2008 (Volume 73, Number 230)]
[Notices]
[Page 72473-72474]
[DOCID:fr28no08-64]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket Nos. EL07-56-005; EL07-58-005]

Public Service Commission of Maryland; Notice of Filing

November 21, 2008.
    Take notice that on October 6, 2008, the Public Service Commission
of Maryland filed its Confidentiality Certification, pursuant to
section 18.17.4 of the Operating Agreement of the PJM Interconnection,
L.L.C.
    Any person desiring to intervene or to protest this filing must
file in accordance with Rules 211 and 214 of the Commission's Rules of
Practice and Procedure (18 CFR 385.211, 385.214). Protests will be
considered by the Commission in determining the appropriate action to
be taken, but will not serve to make protestants parties to the
proceeding. Any person wishing to become a party must file a notice of
intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed on or before the comment date.
Anyone filing a motion to intervene or protest must serve a copy of
that document on the Applicant and all the parties in this proceeding.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper using the ``eFiling'' link at http://
www.ferc.gov. Persons unable to file electronically should submit an
original and 14 copies of the protest or intervention to the Federal
Energy Regulatory Commission, 888 First Street, NE., Washington, DC
20426.
    This filing is accessible 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>.
    Comment Date: 5 p.m. Eastern Time on December 5, 2008.

Kimberly D. Bose,
Secretary.
[FR Doc. E8-28285 Filed 11-26-08; 8:45 am]

BILLING CODE 6717-01-P


[Federal Register Volume 82, Number 67 (Monday, April 10, 2017)]
[Proposed Rules]
[Pages 17154-17156]
[FR Doc No: 2017-06800]

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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

========================================================================

Federal Register / Vol. 82, No. 67 / Monday, April 10, 2017 /
Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0246; Directorate Identifier 2017-NM-011-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 777-200 and -300 series airplanes
equipped with Rolls-Royce Model RB211-Trent 800 engines. This proposed
AD was prompted by reports of inadequate clearance between the thermal
protection system (TPS) insulation blankets and the electronic engine
control (EEC) wiring, which resulted in damaged wires. This proposed AD
would require repetitive inspections of the EEC wire bundles and clips,
and corrective actions if necessary. We are proposing this AD to
address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by May 25, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone<PHONE_NUMBER>; Internet https://www.myboeingfleet.com. You may
view this referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>. It is also
available on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2017-0246.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0246; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone:<PHONE_NUMBER>) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Kevin Nguyen, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6501; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-0246;
Directorate Identifier 2017-NM-011-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

    We have received reports of inadequate clearance between the TPS
insulation blankets and the EEC wiring, which resulted in damaged
wires. This condition, if not corrected, could result in in-flight
shutdown of the engine, or the inability to properly control thrust,
and consequent reduced controllability of the airplane.
    We issued AD 2016-11-16, Amendment 39-18543 (81 FR 39547, June 17,
2016) (``AD 2016-11-16''), on May 20, 2016. Among other actions, AD
2016-11-16 requires repetitive inspections of the EEC wire bundles and
clips for airplanes with certain TPS insulation blankets. Since AD
2016-11-16 was issued, we have determined that these repetitive
inspections were inadvertently terminated in AD 2016-11-16 through the
installation of serviceable thrust reverser (T/R) halves. We are
proposing this AD to reinstate the repetitive inspections of the EEC
wire bundles and clips for certain airplanes.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 777-78-0082, Revision 1, dated
June 15, 2015. The service information describes, among other things,
procedures for repetitive inspections of the EEC wire bundles and
clips, and corrective actions if necessary. 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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified
in the service information described

previously. For information on the procedures and compliance times, see
this service information at http://www.regulations.gov by searching for
and locating Docket No. FAA-2017-0246.
    The phrase ``corrective actions'' is used in this proposed AD.
Corrective actions correct or address any condition found. Corrective
actions in an AD could include, for example, repairs.

Costs of Compliance

    We estimate that this proposed AD affects 55 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
        Action                  Labor cost            Parts cost      Cost per  product          operators
----------------------------------------------------------------------------------------------------------------
Inspection (required    3 work-hours x $85 per                  $0  $255 per engine per    $28,050 (2 T/R halves
 for right T/R half      hour = $255 per engine                      inspection cycle.      per airplane) per
 only).                  per inspection cycle.                                              inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the repairs specified in this proposed AD. We
estimate the following costs to do any necessary replacements that
would be required based on the results of the proposed inspection. We
have no way of determining the number of aircraft that might need these
repairs or replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                 Action                                Labor cost                  Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of EEC wire harness.........  1 work-hour x $85 per hour = $85....          $8,500           $8,585
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed
regulation:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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):

The Boeing Company: Docket No. FAA-2017-0246; Directorate Identifier
2017-NM-011-AD.

(a) Comments Due Date

    We must receive comments by May 25, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300
series airplanes, certificated in any category, equipped with Rolls-
Royce Model RB211-Trent 800 engines, on which the actions specified
in Boeing Alert Service Bulletin 777-78A0094 have been incorporated,
and the condition specified in either paragraph (c)(1) or (c)(2) of
this AD is met.
    (1) Thermal protection system (TPS) non-re-contoured insulation
blankets having part numbers (P/N) 315W5115-2, -6, or -20 are
installed on the thrust reverser (T/R) inner wall.
    (2) Rolls Royce Modification Service Bulletin RR.211-71-H824,
dated July 30, 2014, has not been incorporated on the engine.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine
exhaust.

(e) Unsafe Condition

    This AD was prompted by reports of inadequate clearance between
the TPS insulation blankets and the electronic engine

control (EEC) wiring, which resulted in damaged wires. We are
issuing this AD to detect and correct damaged wires, which could
result in in-flight shutdown of the engine, or the inability to
properly control thrust, and consequent reduced controllability of
the airplane.

(f) Compliance

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

(g) Repetitive EEC Wire Bundle Inspection

    Within 2,000 flight hours since the most recent EEC wire bundle
inspection done as specified in Boeing Special Attention Service
Bulletin 777-78-0071; or Boeing Service Bulletin 777-78-0082; or
within 500 flight hours after the effective date of this AD,
whichever occurs later: Do a detailed inspection for damage of the
EEC wire bundles and clips, and do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 777-78-0082, Revision 1, dated June 15,
2015. Do all applicable corrective actions before further flight.
Repeat the inspection thereafter at intervals not to exceed 2,000
flight hours.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
paragraph (h)(1) or (h)(2) of this AD.
    (1) Boeing Special Attention Service Bulletin 777-78-0071,
Revision 2, dated July 23, 2013.
    (2) Boeing Service Bulletin 777-78-0082, dated November 9, 2011.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO),
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 manager of the ACO, send it to the
attention of the person identified in paragraph (j)(1) of this AD.
Information may be emailed to<EMAIL_ADDRESS>    (2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.

(j) Related Information

    (1) For more information about this AD, contact Kevin Nguyen,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone<PHONE_NUMBER>; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.

    Issued in Renton, Washington, on March 27, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-06800 Filed 4-7-17; 8:45 am]
 BILLING CODE 4910-13-P