[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)]
[Rules and Regulations]
[Pages 14693-14698]
[FR Doc No: 2016-05249]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2961; Directorate Identifier 2014-NM-145-AD;
Amendment 39-18430; AD 2016-05-12]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2012-15-13,
for certain The Boeing Company Model 747-100B SUD, 747-300, 747-400,
and 747-400D series airplanes; and Model 747-200B series airplanes
having a stretched upper deck. AD 2012-15-13 required inspections for
cracking and discrepancies of certain fasteners; modification of the
frame-to-tension-tie joints; repetitive post-modification inspections;
related investigative and corrective actions if necessary; and
repetitive inspections for cracking in the tension tie channels, and
repair if necessary. For certain airplanes, AD 2012-15-13 also required
an inspection to determine if the angle is installed correctly, and re-
installation if necessary; and an inspection at the fastener locations
where the tension tie previously attached to the frame prior to certain
modifications, and repair if necessary. This new AD adds a new
inspection for cracking in the tension tie channels and post-
modification inspections of the modified tension ties for cracking, and
repair if necessary. This AD was prompted by an evaluation indicated
that the upper deck is subject to widespread fatigue damage (WFD). We
are issuing this AD to prevent fatigue cracking of the tension ties,
shear webs, and frames of the upper deck, which could result in rapid
decompression and reduced structural integrity of the airplane.

DATES: This AD is effective April 22, 2016.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 22,
2016.
    The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
September 12, 2012 (77 FR 47267, August 8, 2012).
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 28, 2007 (72 FR 65655, November 23, 2007).

ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone
206-544-5000, extension 1; fax<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 https:/
/

www.regulations.gov by searching for and locating Docket No. FAA-2015-
2961.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2015-
2961; 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 (phone: 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: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>; fax:
425-917-6590; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-15-13, Amendment 39-17142 (77 FR 47267,
August 8, 2012) (``AD 2012-15-13''). AD 2012-15-13 applied to certain
The Boeing Company Model 747-100B SUD, 747-300, 747-400, and 747-400D
series airplanes; and Model 747-200B series airplanes having a
stretched upper deck. The NPRM published in the Federal Register on
July 24, 2015 (80 FR 43974) (``the NPRM''). The NPRM was prompted by an
evaluation that indicated that the upper deck is subject to WFD. The
NPRM proposed to continue to require inspections for cracking and
discrepancies of certain fasteners; modification of the frame-to-
tension-tie joints; repetitive post-modification inspections; related
investigative and corrective actions if necessary; and repetitive
inspections for cracking in the tension tie channels, and repair if
necessary. For certain airplanes, the NPRM also proposed to continue to
require an inspection to determine if the angle is installed correctly,
and re-installation if necessary; and an inspection at the fastener
locations where the tension tie previously attached to the frame prior
to certain modifications, and repair if necessary. The NPRM also
proposed to add a new inspection for cracking in the tension tie
channels and post-modification inspections of the modified tension ties
for cracking, and repair if necessary. We are issuing this AD to
prevent fatigue cracking of the tension ties, shear webs, and frames of
the upper deck, which could result in rapid decompression and reduced
structural integrity of the airplane.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.

Support for the NPRM

    United Airlines concurred with the contents of the NPRM.

Requests To Include Options To Perform Inspections in Revised Service
Information

    Boeing and United Parcel Service (UPS) asked that we add a new
paragraph to the proposed AD that includes an option to perform the
inspections specified in Boeing Alert Service Bulletin 747-53A2507,
Revision 2, dated May 9, 2014. Boeing stated that these inspections are
equivalent to the inspections done in accordance with Boeing Alert
Service Bulletin 747-53A2507, Revision 1, dated January 14, 2010. UPS
recommended that Boeing Alert Service Bulletin 747-53A2507, Revision 2,
dated May 9, 2014, be added to paragraphs (g) through (o) of the
proposed AD. UPS noted that, for clarity, the proposed AD should refer
to the revised service information rather than relying on paragraph
(t)(4) of the proposed AD, which allows alternative methods of
compliance (AMOCs) previously approved for AD 2012-15-13 to be approved
as AMOCs for the proposed AD.
    We acknowledge the commenters' requests and note that we normally
add reference to later revisions of service information in the restated
paragraphs of supersedure ADs. However, in most cases, the later
revisions do not include new compliance times and the procedures are
closely aligned with those in the previous service information. Boeing
Alert Service Bulletin 747-53A2507, Revision 2, dated May 9, 2014, adds
alternative compliance times for certain airplanes and refers to
different procedures in the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2507, Revision 2, dated May 9, 2014, for
accomplishing the actions required by AD 2012-15-13. Therefore, we
cannot simply add a reference to paragraphs (g) through (o) of this AD
as requested by the commenter. We have determined that, in this case,
adding additional paragraphs to this AD to specify the alternative
method of compliance, including new compliance times and procedures, is
not necessary since Boeing Alert Service Bulletin 747-53A2507, Revision
2, dated May 9, 2014, was already approved as an AMOC to AD 2012-15-13.
As stated by the commenter, paragraph (t)(4) of this AD already allows
the use of previous AMOCs, such as Boeing Alert Service Bulletin 747-
53A2507, Revision 2, dated May 9, 2014, as AMOCs for the corresponding
provisions of this AD. We have made no change to this AD in this
regard.

Request To Include an Alternative Compliance Time for the Modification

    Boeing and UPS asked that we add a new paragraph to allow an
alternative compliance time for airplanes on which the station (STA)
1120, 1160, 1200, and 1220 tension ties were modified during a
freighter conversion, as provided in table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2559, Revision
2, dated May 13, 2014. Boeing stated that the compliance time for
modification of those airplanes can be increased because the
modification has been done during a freighter conversion. UPS noted
that paragraph (p) of the proposed AD should be changed to require
modification and all related inspections and corrective actions be
accomplished in accordance with Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014, at the applicable time
specified in Boeing Service Bulletin 747-53A2559, Revision 1, dated
August 4, 2011; or Boeing Alert Service Bulletin 747-53A2559, Revision
2, dated May 13, 2014.
    We agree with the commenter to include the alternative compliance
times for certain airplanes to accomplish the actions required by
paragraph (p) of this AD. We have added a new paragraph (p)(3) to this
AD for Group 3 through 5, Configuration 1 airplanes identified in
Boeing Alert Service Bulletin 747-53A2559, Revision 2, dated May 13,
2014, to specify that operators may accomplish the actions required by
paragraph (p) of this AD within the applicable compliance times
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2559, Revision 2, dated May 13, 2014.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the

public interest require adopting this AD with the changes described
previously and 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.
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2559, Revision 2,
dated May 13, 2014. The service information describes procedures for
modifying the tension tie and frame at certain center sections,
including related investigative and corrective actions; post-
modification inspections for cracking of the tension tie and frame
structure and corrective actions; an additional modification; an
inspection of all areas of the modified tension ties for cracking; an
inspection of the tension tie center section for cracking in certain
tension tie channels; and repair.
    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

    We estimate that this AD affects 120 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained modification in AD 2012- Between 257 and     Between $341,334    Between $363,179    Between
 15-13 (67 airplanes).             263 work-hours x    and $345,490.       and $367,845.       $24,332,993 and
                                   $85 per hour =                                              $24,645,615.
                                   between $21,845
                                   and $22,355.
Retained post[dash]modification   6 work[dash]hours   $0................  $510 per            $34,170 per
 inspections in AD 2012-15-13      x $85 per hour =                        inspection cycle.   inspection cycle.
 (67 airplanes).                   $510 per
                                   inspection cycle.
New inspection..................  10 work[dash]hours  $0................  $850..............  $102,000.
                                   x $85 per hour =
                                   $850.
New post[dash]modification eddy   216 work-hours x    $0................  $18,360 per         $2,203,200 per
 current inspections.              $85 per hour =                          inspection cycle.   inspection cycle.
                                   $18,360 per
                                   inspection cycle.
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    We have received no definitive data that will enable us to provide
a cost estimate 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 have 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 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)
2012-15-13, Amendment 39-17142 (77 FR 47267, August 8, 2012), and
adding the following new AD:

2016-05-12 The Boeing Company: Amendment 39-18430; Docket No. FAA-
2015-2961; Directorate Identifier 2014-NM-145-AD.

(a) Effective Date

    This AD is effective April 22, 2016.

(b) Affected ADs

    This AD replaces AD 2012-15-13, Amendment 39-17142 (77 FR 47267,
August 8, 2012) (``AD 2012-15-13'').

(c) Applicability

    This AD applies to The Boeing Company Model 747-100B SUD, 747-
300, 747-400, and 747-400D series airplanes; and Model 747-200B
series airplanes having a stretched upper deck; certificated in any
category; excluding airplanes that have been converted to a large
cargo freighter configuration.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracked and severed tension
ties, broken fasteners, and cracks in the frame, shear web, and
shear ties adjacent to tension ties for the upper deck. This AD was
also prompted by an evaluation by the design approval holder,

which indicated that the upper deck is subject to widespread fatigue
damage. We are issuing this AD to prevent fatigue cracking of the
tension ties, shear webs, and frames of the upper deck, which could
result in rapid decompression and reduced structural integrity of
the airplane.

(f) Compliance

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

(g) Retained Repetitive Stage 1 Inspections, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD
2012-15-13, with no changes. For all airplanes: Do detailed
inspections for cracking or discrepancies of the fasteners in the
tension ties, shear webs, and frames at body stations (STA) 1120
through 1220, and related investigative and corrective actions as
applicable, by doing all actions specified in and in accordance with
``Stage 1 Inspection'' of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2507, dated April 21, 2005, except as
provided by paragraph (k) of this AD; or Boeing Alert Service
Bulletin 747-53A2507, Revision 1, dated January 14, 2010. As of
September 12, 2012 (the effective date of AD 2012-15-13), only
Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated January
14, 2010, may be used to do the actions required by this paragraph.
Do the Stage 1 inspections at the applicable times specified in
paragraphs (h) and (i) of this AD, except as provided by paragraphs
(g)(1) and (g)(2) of this AD. Accomplishment of the initial Stage 2
inspection required by paragraph (j) of this AD terminates the
requirements of this paragraph. Any applicable related investigative
and corrective actions must be done before further flight. Doing the
modification required by paragraph (p) of this AD terminates the
repetitive inspection requirements of this paragraph.
    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2507, dated April 21, 2005, specifies a
compliance time relative to ``the original issue date on this
service bulletin,'' this AD requires compliance before the specified
compliance time after April 26, 2006 (the effective date of AD 2006-
06-11, Amendment 39-14520 (71 FR 14367, March 22, 2006)).
    (2) For any airplane that reaches the applicable compliance time
for the initial Stage 2 inspection (as specified in Table 1,
Compliance Recommendations, under paragraph 1.E., of Boeing Alert
Service Bulletin 747-53A2507, dated April 21, 2005) before reaching
the applicable compliance time for the initial Stage 1 inspection:
Accomplishment of the initial Stage 2 inspection terminates the
Stage 1 inspections.

(h) Retained Compliance Time for Initial Stage 1 Inspection, With No
Changes

    This paragraph restates the requirements of paragraph (h) of AD
2012-15-13, with no changes. Do the initial Stage 1 inspection at
the earlier of the times specified in paragraphs (h)(1) and (h)(2)
of this AD.
    (1) Inspect at the earlier of the times specified in paragraphs
(h)(1)(i) and (h)(1)(ii) of this AD.
    (i) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2507, dated
April 21, 2005.
    (ii) Before the accumulation of 10,000 total flight cycles, or
within 250 flight cycles after November 28, 2007 (the effective date
of AD 2007-23-18, Amendment 39-15266 (72 FR 65655, November 23,
2007)), whichever occurs later.
    (2) Inspect at the later of the times specified in paragraphs
(h)(2)(i) and (h)(2)(ii) of this AD.
    (i) Before the accumulation of 12,000 total flight cycles.
    (ii) Within 50 flight cycles or 20 days, whichever occurs first,
after November 28, 2007 (the effective date of AD 2007-23-18,
Amendment 39-15266 (72 FR 65655, November 23, 2007)).

(i) Retained Compliance Times for Repetitive Stage 1 Inspections, With
No Changes

    This paragraph restates the requirements of paragraph (i) of AD
2012-15-13, with no changes. Repeat the Stage 1 inspection specified
in paragraph (g) of this AD at the time specified in paragraph
(i)(1) or (i)(2) of this AD, as applicable. Repeat the inspection
thereafter at intervals not to exceed 250 flight cycles, until the
initial Stage 2 inspection required by paragraph (j) of this AD has
been done.
    (1) For airplanes on which the initial Stage 1 inspection has
not been accomplished as of November 28, 2007 (the effective date of
AD 2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 2007)):
Do the next inspection before the accumulation of 10,000 total
flight cycles, or within 250 flight cycles after the initial Stage 1
inspection done in accordance with paragraph (g) of this AD,
whichever occurs later.
    (2) For airplanes on which the initial Stage 1 inspection has
been accomplished as of November 28, 2007 (the effective date of AD
2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 2007)): Do
the next inspection at the applicable time specified in paragraph
(i)(2)(i) or (i)(2)(ii) of this AD.
    (i) For airplanes that have accumulated fewer than 12,000 total
flight cycles as of November 28, 2007 (the effective date of AD
2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 2007)): Do
the next inspection before the accumulation of 10,000 total flight
cycles, or within 250 flight cycles after November 28, 2007,
whichever occurs later.
    (ii) For airplanes that have accumulated 12,000 total flight
cycles or more as of November 28, 2007 (the effective date of AD
2007-23-18, Amendment 39-15266 (72 FR 65655, November 23, 2007)): Do
the next inspection at the later of the times specified in
paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
    (A) Within 250 flight cycles after accomplishment of the initial
Stage 1 inspection.
    (B) Within 50 flight cycles or 20 days, whichever occurs first,
after November 28, 2007 (the effective date of AD 2007-23-18,
Amendment 39-15266 (72 FR 65655, November 23, 2007)).

(j) Retained Repetitive Stage 2 Inspections, With No Changes

    This paragraph restates the requirements of paragraph (j) of AD
2012-15-13, with no changes. For all airplanes: Do detailed and high
frequency eddy current inspections for cracking or discrepancies of
the fasteners in the tension ties, shear webs, and frames at STAs
1120 through 1220, and related investigative and corrective actions
as applicable, by doing all actions specified in and in accordance
with ``Stage 2 Inspection'' of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2507, dated April 21, 2005; or
Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated January
14, 2010; except as provided by paragraph (k) of this AD. Do the
initial inspections at the earlier of the times specified in
paragraphs (j)(1) and (j)(2) of this AD. Repeat the Stage 2
inspection thereafter at the applicable times specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2507,
dated April 21, 2005; or Boeing Alert Service Bulletin 747-53A2507,
Revision 1, dated January 14, 2010. As of September 12, 2012 (the
effective date of AD 2012-15-13), only Boeing Alert Service Bulletin
747-53A2507, Revision 1, dated January 14, 2010, may be used. Any
applicable related investigative and corrective actions must be done
before further flight. Accomplishment of the initial Stage 2
inspection ends the repetitive Stage 1 inspections. Doing the
modification required by paragraph (p) of this AD terminates the
repetitive inspection requirements of this paragraph.
    (1) Before the accumulation of 16,000 total flight cycles, or
within 1,000 flight cycles after November 28, 2007 (the effective
date of AD 2007-23-18, Amendment 39-15266 (72 FR 65655, November 23,
2007)), whichever occurs later.
    (2) Before the accumulation of 10,000 total flight cycles, or
within 1,000 flight cycles after September 12, 2012 (the effective
date of AD 2012-15-13, Amendment 39-17142 (77 FR 47267, August 8,
2012)), whichever occurs later.

(k) Retained Exception to Corrective Action Instructions, With No
Changes

    This paragraph restates the requirements of paragraph (k) of AD
2012-15-13, with no changes. If any discrepancy, including but not
limited to any crack, broken fastener, loose fastener, or missing
fastener is found during any inspection required by paragraph (g),
(h), (i), or (j) of this AD, and Boeing Alert Service Bulletin 747-
53A2507, dated April 21, 2005; or Boeing Alert Service Bulletin 747-
53A2507, Revision 1, dated January 14, 2010; specifies to contact
Boeing for appropriate action: Before further flight, repair the
discrepancy using a method approved in accordance with the
procedures specified in paragraph (t) of this AD.

(l) Retained Stage 2 Inspection: Work at STA 1140, With No Changes

    This paragraph restates the requirements of paragraph (l) of AD
2012-15-13, with no changes. For all airplanes: Except as

provided by paragraph (o) of this AD, at the time specified in
paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 747-
53A2507, Revision 1, dated January 14, 2010, do an open hole high
frequency eddy current (HFEC) inspection for cracking in the forward
and aft tension tie channels at 12 fastener locations inboard of the
aluminum straps at STA 1140, and before further flight do all
applicable repairs. Do all actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2507, Revision 1, dated January 14, 2010. Repeat the inspections
thereafter at the time specified in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated
January 14, 2010. Doing the modification required by paragraph (p)
of this AD terminates the inspection requirements in this paragraph.

(m) Retained One-Time Inspection for Incorrectly Installed Angles, With
No Changes

    This paragraph restates the requirements of paragraph (m) of AD
2012-15-13, with no changes. For Group 1, Configuration 1, airplanes
as identified in Boeing Alert Service Bulletin 747-53A2507, Revision
1, dated January 14, 2010: Except as provided by paragraph (o) of
this AD, at the time specified in paragraph 1.E, ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated January
14, 2010, do a detailed inspection to determine if the angle is
installed correctly, and before further flight re-install all angles
that were installed incorrectly. Do all actions in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-53A2507, Revision 1, dated January 14, 2010.

(n) Retained One-Time Inspection for Cracks in Frames at Previous
Tension Tie Locations, With No Changes

    This paragraph restates the requirements of paragraph (n) of AD
2012-15-13, with no changes. For Group 1, Configuration 2,
airplanes; and Groups 2 and 3 airplanes; as identified in Boeing
Alert Service Bulletin 747-53A2507, Revision 1, dated January 14,
2010: Except as provided by paragraph (o) of this AD, at the time
specified in paragraph 1.E, ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2507, Revision 1, dated January 14, 2010, do an open
hole HFEC inspection for cracks at the fastener locations (STAs
1120, 1160, 1200, and 1220) where the tension tie previously
attached to the frame prior to modification to the Boeing Special
Freighter or Boeing Converted Freighter configuration, and before
further flight do all applicable repairs. Do all actions in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2507, Revision 1, dated January 14, 2010.
Doing the modification required by paragraph (p) of this AD
terminates the one-time inspection requirements in this paragraph.

(o) Retained Exception to Boeing Alert Service Bulletin 747-53A2507,
Revision 1, Dated January 14, 2010, With No Changes

    This paragraph restates the requirements of paragraph (o) of AD
2012-15-13, with no changes. Where paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated
January 14, 2010, specifies a compliance time relative to ``the
Revision 1 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after September 12,
2012 (the effective date of AD 2012-15-13).

(p) Retained Modification and Post-Modification Repetitive Inspections,
With Revised Service Information and a New Exception

    This paragraph restates the requirements of paragraph (p) of AD
2012-15-13, with revised service information and a new exception.
Except as provided by paragraphs (p)(1), (p)(2), and (p)(3) of this
AD: At the applicable times specified in paragraph 1.E,
``Compliance,'' of Boeing Service Bulletin 747-53A2559, Revision 1,
dated August 4, 2011, modify the frame-to-tension-tie joints at STAs
1120 through 1220; do all related investigative and applicable
corrective actions; do the repetitive post-modification detailed
inspections for cracking of the tension tie and frame structure and
all applicable corrective actions; and do the additional
modification. Do all actions in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2559, Revision 1,
dated August 4, 2011; or Boeing Alert Service Bulletin 747-53A2559,
Revision 2, dated May 13, 2014. Modifying the frame-to-tension-tie
joints at STAs 1120 through 1220 terminates the repetitive
inspection requirements of paragraphs (g) and (j) of this AD, the
inspection requirements of paragraph (l) of this AD, and the one-
time inspection requirement of paragraph (n) of this AD. As of the
effective date of this AD, only Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014, may be used to accomplish
the actions specified in this paragraph.
    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 747-53A2559, Revision 1, dated August 4, 2011, specifies a
compliance time relative to ``the original issue date of this
service bulletin,'' this AD requires compliance within the specified
compliance time after September 12, 2012 (the effective date of AD
2012-15-13).
    (2) Where Boeing Service Bulletin 747-53A2559, Revision 1, dated
August 4, 2011; or Boeing Alert Service Bulletin 747-53A2559,
Revision 2, dated May 13, 2014; specifies to contact Boeing for
repair instructions or additional modification requirements: Before
further flight, repair the cracking or do the additional actions
using a method approved in accordance with the procedures specified
in paragraph (t) of this AD.
    (3) For Group 3 through 5, Configuration 1 airplanes identified
in Boeing Alert Service Bulletin 747-53A2559, Revision 2, dated May
13, 2014: Operators may accomplish the actions required by paragraph
(p) of this AD within the applicable compliance times specified in
paragraph 1.E., ``Compliance'' of Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014.

(q) Retained Credit for Previous Actions, With No Changes

    This paragraph restates the credit provided by paragraph (q) of
AD 2012-15-13, with no changes. This paragraph provides credit for
the corresponding actions required by paragraph (p) of this AD, if
those actions were done before September 12, 2012 (the effective
date of AD 2012-15-13), using Boeing Alert Service Bulletin 747-
53A2559, dated January 8, 2009, which is not incorporated by
reference in this AD.

(r) New Repetitive Post-Modification Eddy Current Inspections

    Do an eddy current inspection of all areas of the modified
tension ties for cracking, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014. Do the inspection at the
time specified in Table 2 of paragraph 1.E, ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2559, Revision 2, dated May 13,
2014, except where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2559, Revision 2, dated May 13, 2014,
specifies a compliance time relative to ``the Revision 2 date of
this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD. If
any crack is found, before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (t) of this AD. If no crack is found, repeat the
inspection thereafter at the intervals specified in paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2559,
Revision 2, dated May 13, 2014.

(s) New One-Time Surface HFEC Inspections

    Do a surface HFEC inspection of the tension tie center section,
for cracking in the forward and aft tension tie channels between
STAs 1120 through 1220, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2559, Revision 2, dated May 13, 2014. Do the inspection at the
applicable time specified in Table 1 or Table 3 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2559,
Revision 2, dated May 13, 2014, except where paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2559,
Revision 2, dated May 13, 2014, specifies a compliance time relative
to ``the Revision 2 date of this service bulletin,'' this AD
requires compliance within the specified compliance time after the
effective date of this AD. If any crack is found, before further
flight, repair the crack using a method approved in accordance with
the procedures specified in paragraph (t) of this AD.

(t) 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 (u)(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, alteration, or modification 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. For a repair method 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.
    (4) AMOCs approved previously for AD 2012-15-13, are approved as
AMOCs for the corresponding provisions of this AD.

(u) Related Information

    (1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    (2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (v)(6) and (v)(7) of this AD.

(v) 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 the AD specifies otherwise.
    (3) The following service information was approved for IBR on
April 22, 2016.
    (i) Boeing Alert Service Bulletin 747-53A2559, Revision 2, dated
May 13, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on
September 12, 2012 (77 FR 47267, August 8, 2012).
    (i) Boeing Alert Service Bulletin 747-53A2507, Revision 1, dated
January 14, 2010.
    (ii) Boeing Service Bulletin 747-53A2559, Revision 1, dated
August 4, 2011.
    (5) The following service information was approved for IBR on
November 28, 2007 (72 FR 65655, November 23, 2007).
    (i) Boeing Alert Service Bulletin 747-53A2507, dated April 21,
2005.
    (ii) Reserved.
    (6) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com.
    (7) 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.
    (8) 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 February 29, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-05249 Filed 3-17-16; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 77, Number 42 (Friday, March 2, 2012)]
[Proposed Rules]
[Pages 12759-12760]
[FR Doc No: 2012-5130]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Docket No. FAA-2011-1367; Airspace Docket No. 11-ASO-41]

Proposed Amendment of Class E Airspace; Tullahoma, TN

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This action proposes to amend Class E Airspace at Tullahoma,
TN, as the Arnold Air Force Base has been closed and therefore
controlled airspace associated with the airport is being removed. This
action also would update the geographic coordinates at Tullahoma
Regional Airport/Wm Northern Field. This action would enhance the
safety and airspace management of Instrument Flight Rules (IFR)
operations in the Tullahoma, TN area.

DATES: Comments must be received on or before April 16, 2012.

ADDRESSES: Send comments on this rule to: U.S. Department of
Transportation, Docket Operations, West Building Ground Floor, Room
W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001;
Telephone: 1-800-647-5527; Fax:<PHONE_NUMBER>. You must identify the
Docket Number FAA-2011-1367; Airspace Docket No. 11-ASO-41, at the
beginning of your comments. You may also submit and review received
comments through the Internet at http://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: John Fornito, Operations Support
Group, Eastern Service Center, Federal Aviation Administration, P.O.
Box 20636, Atlanta, Georgia 30320; telephone<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments, as they may desire.
Comments that provide the factual basis supporting the views and
suggestions presented are particularly helpful in developing reasoned
regulatory decisions on the proposal. Comments are specifically invited
on the overall regulatory, aeronautical, economic, environmental, and
energy-related aspects of the proposal.
    Communications should identify both docket numbers (FAA Docket No.
FAA-2011-1367; Airspace Docket No. 11-ASO-41) and be submitted in
triplicate to the Docket Management System (see ADDRESSES section for
address and phone number). You may also submit comments through the
Internet at http://www.regulations.gov.
    Persons wishing the FAA to acknowledge receipt of their comments on
this action must submit with those comments a self-addressed stamped
postcard on which the following statement is made: ``Comments to Docket
No. FAA-2011-1367; Airspace Docket No. 11-ASO-41.'' The postcard will
be date/time stamped and returned to the commenter.
    All communications received before the specified closing date for
comments will be considered before taking action on the proposed rule.
The proposal contained in this notice may be changed in light of the
comments received. A report summarizing each substantive public contact
with FAA personnel concerned with this rulemaking will be filed in the
docket.

Availability of NPRMs

    An electronic copy of this document may be downloaded from and
comments submitted through http://www.regulations.gov. Recently
published rulemaking documents can also be accessed through the FAA's
web page at http://www.faa.gov/airports_airtraffic/air_traffic/publications/airspace_amendments/.
    You may review the public docket containing the proposal, any
comments received, and any final disposition in person in the Dockets
Office (see the ADDRESSES section for address and phone number) between
9 a.m. and 5 p.m., Monday through Friday, except Federal Holidays. An
informal docket may also be examined during normal business hours at
the office of the Eastern Service Center, Federal Aviation
Administration, room 350, 1701 Columbia Avenue, College Park, Georgia
30337.
    Persons interested in being placed on a mailing list for future
NPRMs should contact the FAA's Office of Rulemaking,<PHONE_NUMBER>, to
request a copy of Advisory circular No. 11-2A, Notice of Proposed
Rulemaking distribution System, which describes the application
procedure.

The Proposal

    The FAA is considering an amendment to Title 14, Code of Federal
Regulations (14 CFR) part 71 to amend Class E airspace extending upward
from 700 feet above the surface to support new standard instrument
approach procedures developed at Tullahoma Regional Airport/Wm Northern
Field, Tullahoma, TN. Airspace reconfiguration is necessary due to the
closing of the Arnold Air Force Base, and for continued safety and
management of IFR operations within the Tullahoma, TN airspace area.
The geographic coordinates for Tullahoma Regional Airport/Wm Northern
Field also would be adjusted to coincide with the FAAs aeronautical
database.
    Class E airspace designations are published in Paragraph 6005 of
FAA order 7400.9V, dated August 9, 2011, and effective September 15,
2011, which is incorporated by reference in 14 CFR 71.1. The Class E
airspace designation listed in this document will be published
subsequently in the Order.
    The FAA has determined that this proposed regulation only involves
an established body of technical regulations for which frequent and
routine amendments are necessary to keep them operationally current.
It, therefore, (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) does not warrant preparation of a Regulatory Evaluation as the
anticipated impact is so minimal. Since this is a routine matter that
will only affect air traffic procedures and air navigation, it is
certified that this proposed rule, when promulgated, would not have a
significant economic impact on a substantial number of small entities
under the criteria of the Regulatory Flexibility Act.
    The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. 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. This proposed rulemaking is promulgated under the authority
described in subtitle VII, part, A, subpart I, section 40103. Under
that section, the FAA is charged with prescribing regulations to assign
the use of airspace necessary to ensure the safety of aircraft and the
efficient use of airspace. This proposed regulation is within the scope
of that authority as it

would amend Class E airspace in the Tullahoma, TN area.
    This proposal will be subject to an environmental analysis in
accordance with FAA Order 1050.1E, ``Environmental Impacts: Policies
and procedures'' prior to any FAA final regulatory action.

Lists of Subjects in 14 CFR Part 71

    Airspace, Incorporation by reference, Navigation (air).

The Proposed Amendment

    In consideration of the foregoing, the Federal Aviation
Administration proposes to amend 14 CFR part 71 as follows:

PART 71--DESIGNATION OF CLASS A, B, C, D, AND E AIRSPACE AREAS; AIR
TRAFFIC SERVICE ROUTES; AND REPORTING POINTS

    1. The authority citation for part 71 continues to read as follows:

    Authority:  49 U.S.C. 106(g); 40103, 40113, 40120; E.O. 10854,
24 FR 9565, 3 CFR, 1959-1963 Comp., p. 389.

Sec.  71.1  [Amended]

    2. The incorporation by reference in 14 CFR 71.1 of Federal
Aviation Administration Order 7400.9V, Airspace Designations and
Reporting Points, dated August 9, 2011, effective September 15, 2011,
is amended as follows:

Paragraph 6005 Class E airspace areas extending upward from 700
feet or more above the surface of the earth.

* * * * *

ASO TN E5 Tullahoma, TN [Amended]

Tullahoma Regional Airport/Wm Northern Field, TN
    (Lat. 35[deg]22'48'' N., long. 86[deg]14'48'' W.)
Winchester Municipal Airport
    (Lat. 35[deg]10'39'' N., long. 86[deg]03'58'' W.)
Manchester Medical Center, Point In Space Coordinates
    (Lat. 35[deg]29'56'' N., long. 86[deg]05'37'' W.)

    That airspace extending upward from 700 feet above the surface
within a 7-mile radius of Tullahoma Regional Airport/Wm Northern
Field and within 4 miles either side of the 360[deg] bearing from
the airport extending from the 7-mile radius to 12 miles north of
the airport, and within an 11-mile radius of Winchester Municipal
Airport, and within a 6-mile radius of the point in space (lat.
35[deg]29'56'' N., long. 86[deg]05'37'' W.) serving Manchester
Medical Center.

    Issued in College Park, Georgia, on February 24, 2012.
Barry A. Knight,
Manager, Operations Support Group, Eastern Service Center, Air Traffic
Organization.
[FR Doc. 2012-5130 Filed 3-1-12; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 78, Number 4 (Monday, January 7, 2013)]
[Notices]
[Pages 937-938]
[FR Doc No: 2013-00022]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. PR13-19-000]

Cranberry Pipeline Corporation; Notice of Petition for Rate
Approval

    Take notice that on December 18, 2012, Cranberry Pipeline
Corporation (Cranberry) filed pursuant to 284.123 of the Commissions
regulations a petition for rate approval, requesting the retention of
its existing rates applicable to firm and interruptible transportation,
and proposed new, lower storage rates for services rendered on its
system in the State of West Virginia. Cranberry is also proposing to
retain its existing fuel and lost-and-unaccounted-for percentages
applicable to transportation and storage services, as more fully
detailed in the petition.
    Any person desiring to participate in this rate 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 on or before the date as indicated below. 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 7 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 email
notification when a document is added to a subscribed docket(s). For
assistance with any FERC Online service, please email
<EMAIL_ADDRESS>or call

(866) 208-3676 (toll free). For TTY, call<PHONE_NUMBER>.
    Comment Date: 5:00 p.m. Eastern Time on Friday, January 4, 2013.

    Dated: December 26, 2012.
Kimberly D. Bose,
Secretary.
[FR Doc. 2013-00022 Filed 1-4-13; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 78, Number 18 (Monday, January 28, 2013)]
[Rules and Regulations]
[Pages 5710-5712]
[FR Doc No: 2013-01552]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1293; Directorate Identifier 2012-NE-45-AD;
Amendment 39-17327; AD 2013-02-06]
RIN 2120-AA64

Airworthiness Directives; Engine Alliance Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all
Engine Alliance GP7270 and GP7277 turbofan engines. This AD requires
initial and repetitive borescope inspections and removal from service
before further flight if one or more burn holes are detected, in
certain high-pressure turbine (HPT) stage 2 nozzles. This AD also
requires mandatory removal from service of these HPT stage 2 nozzles at
the next engine shop visit. This AD was prompted by a report received
of inadequate cooling of the HPT stage 2 nozzle, leading to damage to
the HPT stage 2 nozzle, burn-through of the turbine case, and engine
shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure,
leading to uncontrolled fire, engine shutdown, and damage to the
airplane.

DATES: This AD is effective February 12, 2013.
    We must receive comments on this AD by March 14, 2013.

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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket 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 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: Martin Adler, Aerospace Engineer,
Engine & Propeller Directorate, FAA, 12 New England Executive Park,
Burlington, MA 01803; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We received a report of an engine shutdown and turbine case burn-
through, preceded by exceedance of the engine exhaust gas temperature
(EGT) limit and loss of engine oil. Investigation revealed that the
event was caused by damage to the HPT stage 2 nozzle due to inadequate
part cooling. HPT stage 2 nozzles, part numbers (P/Ns) 2101M24G01,
2101M24G02, and 2101M24G03, are identified as having

the inadequate cooling design. This condition, if not corrected, could
result in HPT stage 2 nozzle failure, leading to uncontrolled fire,
engine shutdown, and damage to the airplane.

FAA's Determination

    We are issuing 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.

AD Requirements

    This AD requires initial and repetitive borescope inspections and
removal from service before further flight if burn holes are detected,
in HPT stage 2 nozzles, P/Ns 2101M24G01, 2101M24G02, and 2101M24G03.
This AD also requires mandatory removal from service of these HPT stage
2 nozzles at the next engine shop visit.

FAA's Justification and Determination of the Effective Date

    No domestic operators use this product. Therefore, we find that
notice and opportunity for prior public comment are unnecessary, and
that good cause exists for making this amendment effective in less than
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the Docket Number FAA-2012-1293 and
Directorate Identifier 2012-NE-45-AD at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD will affect no engines installed on
airplanes of U.S. registry. We also estimate that it would take about
two hours per engine to perform a borescope inspection of the HPT stage
2 nozzle. The average labor rate is $85 per work hour. Required parts
would cost about $487,312 per engine. Based on these figures, we
estimate the cost of this proposed AD to U.S. operators to be $0.

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),
    (3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, 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 adding the following new airworthiness
directive (AD):

2013-02-06 Engine Alliance: Amendment 39-17327; Docket No. FAA-2012-
1293; Directorate Identifier 2012-NE-45-AD.

(a) Effective Date

    This AD is effective February 12, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Engine Alliance GP7270 and GP7277
turbofan engines with a high-pressure turbine (HPT) stage 2 nozzle,
part number (P/N) 2101M24G01, 2101M24G02, or 2101M24G03, installed.

(d) Unsafe Condition

    This AD was prompted by a report received of inadequate cooling
of the HPT stage 2 nozzle, leading to damage to the HPT stage 2
nozzle, burn-through of the turbine case, and engine shutdown.
Investigation revealed that the event was caused by damage to the
HPT stage 2 nozzle due to inadequate part cooling. We are issuing
this AD to prevent HPT stage 2 nozzle failure, leading to
uncontrolled fire, engine shutdown, and damage to the airplane.

(e) Compliance

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

(f) Borescope Inspections of the HPT Stage 2 Nozzle

    (1) Initially borescope inspect (360 degrees) the HPT stage 2
nozzle at the following:
    (i) Before accumulating 1,500 cycles-since-new (CSN), if the
nozzle has fewer than 1,450 CSN on the effective date of this AD.
    (ii) Within the next 50 cycles, if the nozzle has 1,450 or more
CSN on the effective date of this AD.
    (2) Thereafter, repetitively borescope inspect (360 degrees) the
HPT stage 2 nozzle within every 100 additional cycles-in-service.
    (3) If during any inspection required by this AD, any burn holes
are detected through the surface of the nozzle, remove the nozzle
from service before further flight.

(g) Mandatory Removal From Service of the HPT Stage 2 Nozzles

    At the next engine shop visit, remove HPT stage 2 nozzles P/N
2101M24G01, 2101M24G02, and 2101M24G03 from service.

(h) Definition

    For the purpose of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine

flanges except that the separation of engine flanges solely for the
purposes of transportation without subsequent engine maintenance
does not constitute an engine shop visit.

(i) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve AMOCs for
this AD. Use the procedures found in 14 CFR 39.19 to make your
request.

(j) Related Information

    For more information about this AD, contact Martin Adler,
Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA 01803; phone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
(k) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on January 15, 2013.
Thomas A. Boudreau,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2013-01552 Filed 1-25-13; 8:45 am]
BILLING CODE 4910-13-P