Airworthiness Directives; Pratt & Whitney Turbofan Engines, 17856-17859 [2014-06953]
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Federal Register / Vol. 79, No. 61 / Monday, March 31, 2014 / Rules and Regulations
Title VI of the Appropriations Act
supports an interim final rulemaking as
the limitation arguably makes formal
proposed and final rulemaking
procedures ‘‘impracticable,
unnecessary, or contrary to the public
interest.’’ Further, we believe amending
the rule to remove the requirements for
non-binding, advisory votes will ensure
compliance with the Appropriations
Act. Consistent with the Appropriations
Act, as well as the Farm Bill, this
interim final rulemaking is limited to
the advisory vote provisions of the
October 3, 2012, (77 FR 60582)
rulemaking.
Specifically, we are removing the
following rule provisions:
D § 611.100(a), defining the term
‘‘advisory vote’’;
D § 611.360, requiring policies and
procedures for non-binding, advisory
votes on senior officer compensation;
D § 611.410, addressing non-binding,
advisory votes on senior officer
compensation;
D § 620.5(a)(11), requiring disclosure
of any advisory votes held during the
reporting year at the institution;
D § 620.6(c)(6), requiring disclosure
(adjacent to the compensation table) in
the annual report of a stockholder’s
right to petition for a non-binding,
advisory vote on senior officer
compensation; and
D § 630.20(i)(last sentence), requiring
disclosure of any advisory votes held
during the reporting year within the
System.
All other regulatory provisions and
changes resulting from the October 3,
2012 (77 FR 60582) rulemaking remain
in effect.
IV. Regulatory Flexibility Act
Pursuant to section 605(b) of the
Regulatory Flexibility Act (5 U.S.C. 601
et seq.), the FCA hereby certifies that
this interim final rule will not have a
significant economic impact on a
substantial number of small entities.
Each of the banks in the System,
considered together with its affiliated
associations, has assets and annual
income in excess of the amounts that
would qualify them as small entities.
Therefore, System institutions are not
‘‘small entities’’ as defined in the
Regulatory Flexibility Act.
emcdonald on DSK67QTVN1PROD with RULES
PART 611—ORGANIZATION
Authority: Secs. 1.2, 1.3, 1.4, 1.5, 1.12,
1.13, 2.0, 2.1, 2.2, 2.10, 2.11, 2.12, 3.0, 3.1,
3.2, 3.3, 3.7, 3.8, 3.9, 3.21, 4.3A, 4.12, 4.12A,
4.15, 4.20, 4.21, 4.25, 4.26, 4.27, 4.28A, 5.9,
5.17, 5.25, 7.0–7.13, 8.5(e) of the Farm Credit
Act (12 U.S.C. 2002, 2011, 2012, 2013, 2020,
2021, 2071, 2072, 2073, 2091, 2092, 2093,
2121, 2122, 2123, 2124, 2128, 2129, 2130,
2142, 2154a, 2183, 2184, 2203, 2208, 2209,
2211, 2212, 2213, 2214, 2243, 2252, 2261,
2279a–2279f–1, 2279aa–5(e)); secs. 411 and
412 of Pub. L. 100–233, 101 Stat. 1568, 1638;
sec. 414 of Pub. L. 100–399, 102 Stat. 989,
1004.
§ 611.100
Jkt 232001
8. The authority citation for part 630
continues to read as follows:
■
Authority: Secs. 4.2, 4.9, 5.9, 5.17, 5.19 of
the Farm Credit Act (12 U.S.C. 2153, 2160,
2243, 2252, 2254); sec. 424 of Pub. L. 100–
233, 101 Stat. 1568, 1656; sec. 514 of Pub. L.
102–552, 106 Stat. 4102.
2. Section 611.100 is amended by
removing paragraph (a) and
redesignating paragraphs (b) through (h)
as new paragraphs (a) through (g),
respectively.
§ 611.360
[Removed and reserved]
3. Section 611.360 is removed and
reserved.
■
§ 611.410
[Removed and reserved]
4. Section 611.410 is removed and
reserved.
■
PART 620—DISCLOSURE TO
SHAREHOLDERS
5. The authority citation for part 620
continues to read as follows:
■
Authority: Secs. 4.3, 4.3A, 4.19, 5.9, 5.17,
5.19 of the Farm Credit Act (12 U.S.C. 2154,
2154a, 2207, 2243, 2252, 2254); sec. 424 of
Pub. L. 100–233, 101 Stat. 1568, 1656; sec.
514 of Pub. L. 102–552, 106 Stat. 4102.
§ 620.5
[Amended]
[Amended]
7. Section 620.6 is amended by
removing paragraph (c)(6) and
redesignating paragraph (c)(7) as new
paragraph (c)(6).
■
PO 00000
[Amended]
9. Section 630.20 is amended by
removing the last sentence of paragraph
(i).
■
Dated: March 21, 2014.
Dale L. Aultman,
Secretary, Farm Credit Administration Board.
[FR Doc. 2014–06783 Filed 3–28–14; 8:45 a.m.]
BILLING CODE 6705–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Amended]
■
§ 620.6
12 CFR Part 620
Accounting, Agriculture, Banks,
banking, Reporting and recordkeeping
requirements, Rural areas.
PART 630—DISCLOSURE TO
INVESTORS IN SYSTEM-WIDE AND
CONSOLIDATED BANK DEBT
OBLIGATIONS OF THE FARM CREDIT
SYSTEM
§ 630.20
1. The authority citation for part 611
continues to read as follows:
■
6. Section 620.5 is amended by
removing paragraph (a)(11) and
redesignating paragraph (a)(12) as new
paragraph (a)(11).
12 CFR Part 611
Agriculture, Banks, banking, Rural
areas.
16:18 Mar 28, 2014
Accounting, Agriculture, Banks,
banking, Organization and functions
(Government agencies), Reporting and
recordkeeping requirements, Rural
areas.
For the reasons stated in the
preamble, parts 611, 620, and 630 of
chapter VI, title 12 of the Code of
Federal Regulations are amended as
follows:
■
List of Subjects
VerDate Mar<15>2010
12 CFR Part 630
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[Docket No. FAA–2013–0740; Directorate
Identifier 2013–NE–24–AD; Amendment 39–
17804; AD 2014–05–32]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all Pratt
& Whitney (PW) PW2037, PW2037D,
PW2037M, PW2040, PW2040D,
PW2043, PW2146, PW2240, PW2337,
PW2643, and F117–PW–100 turbofan
engines. This AD was prompted by a
rupture of the diffuser-to-high-pressure
turbine (HPT) case flange. This AD
requires a one-time eddy current
inspection (ECI) of affected engines with
certain diffuser and HPT cases installed.
This AD also requires a fluorescentpenetrant inspection (FPI) of the
diffuser case rear flange and HPT case
front flange. We are issuing this AD to
prevent failure of the diffuser-to-HPT
case flange, which could lead to
uncontained engine failure and damage
to the airplane.
DATES: This AD is effective May 5, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 5, 2014.
SUMMARY:
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Federal Register / Vol. 79, No. 61 / Monday, March 31, 2014 / Rules and Regulations
For service information
identified in this AD, contact Pratt &
Whitney, 400 Main St., East Hartford,
CT 06108; phone: 860–565–8770; fax:
860–565–4503. You may view this
service information at the FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0740; 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
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7758; fax: 781–238–
7199; email: mark.riley@faa.gov.
SUPPLEMENTARY INFORMATION:
emcdonald on DSK67QTVN1PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all PW PW2037, PW2037D,
PW2037M, PW2040, PW2040D,
PW2043, PW2146, PW2240, PW2337,
PW2643, and F117–PW–100 turbofan
engines. The NPRM published in the
Federal Register on October 29, 2013
(78 FR 64419). The NPRM was
prompted by a rupture of the diffuserto-HPT case flange. The NPRM
proposed to require a one-time ECI of
affected engines with certain diffuser
and HPT cases installed and an FPI of
the diffuser case rear flange and HPT
case front flange. We are issuing this AD
to prevent failure of the diffuser-to-HPT
case flange, which could lead to
uncontained engine failure and damage
to the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal and the FAA’s
response to each comment.
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Request Credit for FPI at Piece Part
Level
deleting diffuser and HPT cases that
have been inspected.
Delta Air Lines (DAL), PW, Federal
Express, and United Parcel Service
(UPS) requested that previous FPI of
cases at the piece part level be allowed
for AD compliance in lieu of ECI. The
justification for this request is that FPI
of diffuser/HPT cases at the piece part
level performed after January 1, 2010 are
equivalent to the ECI procedures.
We agree. We changed the AD to
allow credit for FPI of diffuser and HPT
cases performed after January 1, 2010.
Request Definition for Piece Part
Exposure
DAL, UPS, and an individual
commenter requested that a definition
be provided for ‘‘piece part exposure’’ as
it applies to repetitive inspections of
diffuser and HPT cases. The reason for
this request was to clarify when
inspections are required.
We agree. We added a definition for
‘‘piece part exposure’’ in this AD.
Request to Eliminate Initial Inspection
and Mandated Repetitive Inspections
DAL and PW requested elimination of
inspection for diffuser/HPT cases
identified in Table 1 to paragraph (e) of
this AD because the inspections have
already been completed. DAL and PW
also requested that mandated repetitive
inspections of the diffuser and HPT case
be eliminated since this requirement is
already in the engine manual and part
of DAL’s PW2000 maintenance program.
Mandated inspection results in a quality
records burden. The AD is requested to
be withdrawn based on these requested
actions.
We partially agree. We agree that
many of the diffuser/HPT case
inspections have been completed. PW
reports that all diffuser and HPT cases
have been inspected except for three.
Those three cases are installed on
engines not currently in service. We
changed the AD to eliminate Table 1 to
paragraph (e) of this AD. We added the
remaining diffuser cases and HPT cases
requiring inspection to paragraph (e) of
this AD.
We do not agree that mandated
inspections for the diffuser and HPT
cases are not required as diffuser or HPT
case failure may result in a catastrophic
aircraft event. We did not change the
AD requirement for repetitive
inspections. This AD will not be
withdrawn.
Request to Exclude F117–PW–100
Requirements
PW requested that F117–PW–100
requirements not be included in this AD
as the inspections will be completed by
December 2013.
We partially agree. We received
confirmation that the diffuser and HPT
cases that are applicable to F117–PW–
100 engines have been inspected.
However, since the F117–PW–100
engine model has been certified by the
FAA and is on the type certificate data
sheet, we will require repetitive FPI of
the diffuser and HPT cases at piece part
opportunity. We changed this AD by
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Request for New Compliance Method
DAL requested that the compliance
requirement for repetitive inspections
direct operator’s to revise their
approved maintenance programs with
an FPI of the diffuser and HPT cases and
not require documenting AD
compliance for each individual case.
This change would help to eliminate
undue burden on operator/maintenance
facility for AD tracking requirements.
We partially agree. We agree that
changing the continuous airworthiness
maintenance program (CAMP) to require
diffuser and HPT case inspections
adequately addresses our safety
concerns.
We do not agree that tracking
repetitive inspections to show AD
compliance is an undue burden. We
changed the AD by adding an Optional
Terminating Action allowing diffuser
and HPT case inspections to be added
to the CAMP to satisfy repetitive
inspection requirements of this AD.
Request FAA Standard Practices,
Processes, Consumables, and Standard
Tooling be Allowed to Perform ECI
One individual commenter requested
that only Non-destructive Inspection
Procedure sections IX through XVIII be
mandated as these sections contain the
only items that have an actual effect on
the unsafe condition of the AD.
We disagree. The specific ECI
inspection equipment and procedures
developed by PW have been verified as
being able to detect cracks in the
diffuser case and HPT case M-flange.
The specific equipment and procedures
must be used to ensure proper
inspection results. However, operators
and maintenance facilities can propose
use of other equipment and/or
procedures as an alternative method of
compliance if they can validate
equivalent results. We did not change
this AD.
Request Clarification for Applicability
The same individual commenter
requested clarification that the
Compliance paragraph apply to all HPT
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and diffuser cases regardless of whether
they are listed in Table 1 to paragraph
(e) or not. The reason for this request is
that it is unclear if the repetitive
inspections are required only for those
cases specified in Table 1.
We agree. We deleted Table 1 to
paragraph (e) of this AD and added the
remaining diffuser cases and HPT cases
requiring inspection to paragraph (e) of
this AD.
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 changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
64419, October 29, 2013) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 64419,
October 29, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
emcdonald on DSK67QTVN1PROD with RULES
Costs of Compliance
We estimate that this AD will affect
638 engines installed on airplanes of
U.S. registry. Of the 638 engines, we
estimate that about 3 engines will be
subject to ECI and all engines will be
subject to the FPI. We also estimate that
it will take about 5 hours to perform the
ECI and 3 hours to perform the FPI
required by this AD. Materials cost for
the FPI will be about $20 per engine.
The average labor rate is $85 per hour.
Based on these figures, we estimate the
total cost of this AD to U.S. operators is
$176,725.
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
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–05–32 Pratt & Whitney: Amendment
39–17804 Docket No. FAA–2013–0740;
Directorate Identifier 2013–NE–24–AD.
(a) Effective Date
This AD is effective May 5, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Pratt & Whitney
(PW) PW2037, PW2037D, PW2037M,
PW2040, PW2040D, PW2043, PW2146,
PW2240, PW2337, PW2643, and F117–PW–
100 turbofan engines.
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(d) Unsafe Condition
This AD was prompted by a rupture of the
diffuser-to-high-pressure turbine (HPT) case
flange. We are issuing this AD to prevent
failure of the diffuser-to-HPT case flange,
which could lead to uncontained engine
failure and damage to the airplane.
(e) Compliance
Unless already done, comply with this AD
within the compliance times specified.
(1) For diffuser case part number (P/N)
1B7461, serial numbers (S/Ns) DGGUAK1306
and DGGUAK1308, and HPT case P/N
1B2440, S/N DKLBCS1032:
(i) Within 100 flight cycles or 30 days after
the effective date of this AD, whichever is
later, eddy current inspect (ECI) the diffuser
case and the HPT case M-flange. Use PW
Service Bulletin (SB) No. PW2000 72–763,
Revision 1, dated August 30, 2013, to do the
inspection.
(ii) Reserved.
(2) For all diffuser and HPT cases at the
next piece part opportunity and every piece
part opportunity thereafter, perform a high
sensitivity fluorescent-penetrant inspection
(FPI) of the entire diffuser case rear flange
(M-flange) and bolt holes, and the entire HPT
case forward flange (M-flange) and bolt holes.
(f) Optional Terminating Action
As a terminating action to the repetitive
inspection requirements of this AD, you may
insert the repetitive inspection requirement
identified in paragraph (e)(2) of this AD into
the required inspection portion of your
continuous airworthiness maintenance
program.
(g) Definition
For the purpose of this AD, piece part
opportunity is defined as when the part is
completely disassembled.
(h) Prohibition Statement
After the effective date of this AD, do not
install any engine with a diffuser or HPT case
onto any airplane that was not inspected
using paragraph (e) of this AD.
(i) Credit for Previous Actions
If you performed an ECI of the diffuser case
and HPT case M-flange using the
Accomplishment Instructions of PW SB No.
PW2000 72–763, dated March 22, 2013, or
you performed a high sensitivity FPI of the
diffuser case and HPT case at the piece part
opportunity after January 1, 2010, you met
the requirements of paragraph (e)(1) of this
AD.
(j) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request.
(k) Related Information
(1) For more information about this AD,
contact Mark Riley, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7758; fax: 781–238–7199;
email: mark.riley@faa.gov.
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(2) Pratt & Whitney Engine Manual, P/N
1A6231, (PW2000) and P/N 1B2412 (F117),
Chapter 72–41–00, Inspection/Check-02,
(Task 72–41–00–230–002) and Chapter 72–
52–00, Inspection/Check-02 (Task 72–52–00–
230–000), which are not incorporated by
reference in this AD, can be obtained from
Pratt & Whitney, using the contact
information in paragraph (l)(3) of this AD.
(l) 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.
(i) Pratt & Whitney Service Bulletin No.
PW2000 72–763, Revision 1, dated August
30, 2013.
(ii) Reserved
(3) For PW service information identified
in this AD, contact Pratt & Whitney, 400
Main St., East Hartford, CT 06108; phone:
860–565–8770; fax: 860–565–4503.
(4) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
(5) You may view this service information
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
March 6, 2014.
Colleen M. D’Alessandro,
Assistant Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2014–06953 Filed 3–28–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2013–0079; Airspace
Docket No. 09–AWA–4]
RIN 2120–AA66
Amendment to Class B Airspace Area;
Detroit, MI
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
emcdonald on DSK67QTVN1PROD with RULES
AGENCY:
This action corrects a final
rule published in the Federal Register
January 21, 2014. In that rule, the shared
boundary between the Detroit Class B
airspace Area A and Area B subareas
did not match, as originally intended, in
the regulatory text descriptions. This
SUMMARY:
VerDate Mar<15>2010
16:18 Mar 28, 2014
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correction is necessary to close the
unintended gap between subareas
created by the boundary error and to
ensure the accuracy of the charted
Detroit Class B airspace area.
DATES: Effective Date: 0901 UTC, April
3, 2014. The Director of the Federal
Register approves this incorporation by
reference action under 3 CFR part 51,
subject to the annual revision of FAA
Order 7400.9 and publication of
conforming amendments.
FOR FURTHER INFORMATION CONTACT:
Colby Abbott, Airspace Policy and
Regulations Group, Office of Airspace
Services, Mission Support, Federal
Aviation Administration, 800
Independence Avenue SW.,
Washington, DC 20591; telephone: (202)
267–8783.
SUPPLEMENTARY INFORMATION:
History
Correction to Final Rule
Accordingly, pursuant to the
authority delegated to me, in the
Federal Register of January 21, 2014,
the text on page 3312, column 2, line 47,
is corrected to read:
Frm 00011
[Amended]
AGL MI B Detroit, MI [Corrected]
For Area A, between the words
‘‘Airport;’’ and ‘‘thence’’, add the
following: ‘‘thence northeast to the
intersection of the DXO VOR/DME 354°
radial and the Detroit Willow Run
Airport 047° bearing:’’.
Issued in Washington, DC, on March 24,
2014.
Ellen Crum,
Acting Manager, Airspace Policy and
Regulations Group.
[FR Doc. 2014–06959 Filed 3–28–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Part 558
On January 21, 2014, a final rule for
FAA Docket No. FAA–2012–0661,
Airspace Docket No. 09–AWA–4, was
published in the Federal Register (79
FR 3305) to amend the Detroit Class B
airspace area. The Detroit Class B
airspace area was modified to contain
aircraft conducting published
instrument procedures at Detroit
Metropolitan Wayne County Airport
(DTW) within Class B airspace, enhance
safety, improve the flow of air traffic,
and reduce the potential for midair
collisions in the DTW terminal area,
while accommodating the concerns of
all airspace users.
Subsequent to publication of the rule,
the FAA determined the boundary
segment described in Area A, from lat.
42°17′18″ N., long. 83°27′27″ W. on the
4.4-mile radius of the Detroit Willow
Run Airport to lat. 42°20′47″ N., long.
83°22′12″ W. on the 8-mile arc of the
DXO VOR/DME, and the boundary
segment described in Area B, from the
intersection of the DXO VOR/DME 354°
radial and the Detroit Willow Run
Airport 047° bearing to lat. 42°20′47″ N.,
long. 83°22′12″ W., did not align as
intended and contained a gap between
the two adjacent subareas. The FAA is
correcting this minor error by adding
the geographic point defined by the
intersection of the DXO VOR/DME 354°
radial and the Detroit Willow Run
Airport 047° bearing in the Area A
description to remove the gap.
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§ 71.1
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[Docket No. FDA–2014–N–0002]
Zoetis Inc., et al.; Withdrawal of
Approval of New Animal Drug
Applications for Combination Drug
Medicated Feeds Containing an
Arsenical Drug; Correction
AGENCY:
Food and Drug Administration,
HHS.
Final rule; correcting
amendments.
ACTION:
The Food and Drug
Administration (FDA) is correcting a
document amending the animal drug
regulations to reflect the withdrawal of
approval of new animal drug
applications (NADAs) that appeared in
the Federal Register of February 27,
2014 (79 FR 10976). That document
listed an NADA for which a withdrawal
of approval (WOA) was not intended
and failed to remove all conditions of
use associated with the withdrawn
NADAs. This correction is being made
to improve the accuracy of the animal
drug regulations.
DATES: This correction is effective
March 31, 2014.
FOR FURTHER INFORMATION CONTACT:
George K. Haibel, Center for Veterinary
Medicine (HFV–6), Food and Drug
Administration, 7519 Standish Pl.,
Rockville, MD 20855, 240–276–9019,
george.haibel@fda.hhs.gov.
SUPPLEMENTARY INFORMATION: FDA is
correcting a document amending the
animal drug regulations to reflect the
WOA of NADAs that appeared in the
Federal Register of February 27, 2014
(79 FR 10976). That document listed an
NADA for which a WOA was not
intended and failed to remove all
SUMMARY:
E:\FR\FM\31MRR1.SGM
31MRR1
]]>Agencies
[Federal Register Volume 79, Number 61 (Monday, March 31, 2014)]
[Rules and Regulations]
[Pages 17856-17859]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06953]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0740; Directorate Identifier 2013-NE-24-AD;
Amendment 39-17804; AD 2014-05-32]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for all
Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043,
PW2146, PW2240, PW2337, PW2643, and F117-PW-100 turbofan engines. This
AD was prompted by a rupture of the diffuser-to-high-pressure turbine
(HPT) case flange. This AD requires a one-time eddy current inspection
(ECI) of affected engines with certain diffuser and HPT cases
installed. This AD also requires a fluorescent-penetrant inspection
(FPI) of the diffuser case rear flange and HPT case front flange. We
are issuing this AD to prevent failure of the diffuser-to-HPT case
flange, which could lead to uncontained engine failure and damage to
the airplane.
DATES: This AD is effective May 5, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 5, 2014.
[[Page 17857]]
ADDRESSES: For service information identified in this AD, contact Pratt
& Whitney, 400 Main St., East Hartford, CT 06108; phone: 860-565-8770;
fax: 860-565-4503. You may view this service information at the FAA,
Engine & Propeller Directorate, 12 New England Executive Park,
Burlington, MA. For information on the availability of this material at
the FAA, call 781-238-7125.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0740; 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 Document Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; phone: 781-238-7758; fax:
781-238-7199; email: mark.riley@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all PW PW2037, PW2037D,
PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643, and
F117-PW-100 turbofan engines. The NPRM published in the Federal
Register on October 29, 2013 (78 FR 64419). The NPRM was prompted by a
rupture of the diffuser-to-HPT case flange. The NPRM proposed to
require a one-time ECI of affected engines with certain diffuser and
HPT cases installed and an FPI of the diffuser case rear flange and HPT
case front flange. We are issuing this AD to prevent failure of the
diffuser-to-HPT case flange, which could lead to uncontained engine
failure and damage to the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.
Request Credit for FPI at Piece Part Level
Delta Air Lines (DAL), PW, Federal Express, and United Parcel
Service (UPS) requested that previous FPI of cases at the piece part
level be allowed for AD compliance in lieu of ECI. The justification
for this request is that FPI of diffuser/HPT cases at the piece part
level performed after January 1, 2010 are equivalent to the ECI
procedures.
We agree. We changed the AD to allow credit for FPI of diffuser and
HPT cases performed after January 1, 2010.
Request to Eliminate Initial Inspection and Mandated Repetitive
Inspections
DAL and PW requested elimination of inspection for diffuser/HPT
cases identified in Table 1 to paragraph (e) of this AD because the
inspections have already been completed. DAL and PW also requested that
mandated repetitive inspections of the diffuser and HPT case be
eliminated since this requirement is already in the engine manual and
part of DAL's PW2000 maintenance program. Mandated inspection results
in a quality records burden. The AD is requested to be withdrawn based
on these requested actions.
We partially agree. We agree that many of the diffuser/HPT case
inspections have been completed. PW reports that all diffuser and HPT
cases have been inspected except for three. Those three cases are
installed on engines not currently in service. We changed the AD to
eliminate Table 1 to paragraph (e) of this AD. We added the remaining
diffuser cases and HPT cases requiring inspection to paragraph (e) of
this AD.
We do not agree that mandated inspections for the diffuser and HPT
cases are not required as diffuser or HPT case failure may result in a
catastrophic aircraft event. We did not change the AD requirement for
repetitive inspections. This AD will not be withdrawn.
Request to Exclude F117-PW-100 Requirements
PW requested that F117-PW-100 requirements not be included in this
AD as the inspections will be completed by December 2013.
We partially agree. We received confirmation that the diffuser and
HPT cases that are applicable to F117-PW-100 engines have been
inspected. However, since the F117-PW-100 engine model has been
certified by the FAA and is on the type certificate data sheet, we will
require repetitive FPI of the diffuser and HPT cases at piece part
opportunity. We changed this AD by deleting diffuser and HPT cases that
have been inspected.
Request Definition for Piece Part Exposure
DAL, UPS, and an individual commenter requested that a definition
be provided for ``piece part exposure'' as it applies to repetitive
inspections of diffuser and HPT cases. The reason for this request was
to clarify when inspections are required.
We agree. We added a definition for ``piece part exposure'' in this
AD.
Request for New Compliance Method
DAL requested that the compliance requirement for repetitive
inspections direct operator's to revise their approved maintenance
programs with an FPI of the diffuser and HPT cases and not require
documenting AD compliance for each individual case. This change would
help to eliminate undue burden on operator/maintenance facility for AD
tracking requirements.
We partially agree. We agree that changing the continuous
airworthiness maintenance program (CAMP) to require diffuser and HPT
case inspections adequately addresses our safety concerns.
We do not agree that tracking repetitive inspections to show AD
compliance is an undue burden. We changed the AD by adding an Optional
Terminating Action allowing diffuser and HPT case inspections to be
added to the CAMP to satisfy repetitive inspection requirements of this
AD.
Request FAA Standard Practices, Processes, Consumables, and Standard
Tooling be Allowed to Perform ECI
One individual commenter requested that only Non-destructive
Inspection Procedure sections IX through XVIII be mandated as these
sections contain the only items that have an actual effect on the
unsafe condition of the AD.
We disagree. The specific ECI inspection equipment and procedures
developed by PW have been verified as being able to detect cracks in
the diffuser case and HPT case M-flange. The specific equipment and
procedures must be used to ensure proper inspection results. However,
operators and maintenance facilities can propose use of other equipment
and/or procedures as an alternative method of compliance if they can
validate equivalent results. We did not change this AD.
Request Clarification for Applicability
The same individual commenter requested clarification that the
Compliance paragraph apply to all HPT
[[Page 17858]]
and diffuser cases regardless of whether they are listed in Table 1 to
paragraph (e) or not. The reason for this request is that it is unclear
if the repetitive inspections are required only for those cases
specified in Table 1.
We agree. We deleted Table 1 to paragraph (e) of this AD and added
the remaining diffuser cases and HPT cases requiring inspection to
paragraph (e) of this AD.
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 changes:
[Agr]re consistent with the intent that was proposed in
the NPRM (78 FR 64419, October 29, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 64419, October 29, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD will affect 638 engines installed on
airplanes of U.S. registry. Of the 638 engines, we estimate that about
3 engines will be subject to ECI and all engines will be subject to the
FPI. We also estimate that it will take about 5 hours to perform the
ECI and 3 hours to perform the FPI required by this AD. Materials cost
for the FPI will be about $20 per engine. The average labor rate is $85
per hour. Based on these figures, we estimate the total cost of this AD
to U.S. operators is $176,725.
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):
2014-05-32 Pratt & Whitney: Amendment 39-17804 Docket No. FAA-2013-
0740; Directorate Identifier 2013-NE-24-AD.
(a) Effective Date
This AD is effective May 5, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D,
PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643,
and F117-PW-100 turbofan engines.
(d) Unsafe Condition
This AD was prompted by a rupture of the diffuser-to-high-
pressure turbine (HPT) case flange. We are issuing this AD to
prevent failure of the diffuser-to-HPT case flange, which could lead
to uncontained engine failure and damage to the airplane.
(e) Compliance
Unless already done, comply with this AD within the compliance
times specified.
(1) For diffuser case part number (P/N) 1B7461, serial numbers
(S/Ns) DGGUAK1306 and DGGUAK1308, and HPT case P/N 1B2440, S/N
DKLBCS1032:
(i) Within 100 flight cycles or 30 days after the effective date
of this AD, whichever is later, eddy current inspect (ECI) the
diffuser case and the HPT case M-flange. Use PW Service Bulletin
(SB) No. PW2000 72-763, Revision 1, dated August 30, 2013, to do the
inspection.
(ii) Reserved.
(2) For all diffuser and HPT cases at the next piece part
opportunity and every piece part opportunity thereafter, perform a
high sensitivity fluorescent-penetrant inspection (FPI) of the
entire diffuser case rear flange (M-flange) and bolt holes, and the
entire HPT case forward flange (M-flange) and bolt holes.
(f) Optional Terminating Action
As a terminating action to the repetitive inspection
requirements of this AD, you may insert the repetitive inspection
requirement identified in paragraph (e)(2) of this AD into the
required inspection portion of your continuous airworthiness
maintenance program.
(g) Definition
For the purpose of this AD, piece part opportunity is defined as
when the part is completely disassembled.
(h) Prohibition Statement
After the effective date of this AD, do not install any engine
with a diffuser or HPT case onto any airplane that was not inspected
using paragraph (e) of this AD.
(i) Credit for Previous Actions
If you performed an ECI of the diffuser case and HPT case M-
flange using the Accomplishment Instructions of PW SB No. PW2000 72-
763, dated March 22, 2013, or you performed a high sensitivity FPI
of the diffuser case and HPT case at the piece part opportunity
after January 1, 2010, you met the requirements of paragraph (e)(1)
of this AD.
(j) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request.
(k) Related Information
(1) For more information about this AD, contact Mark Riley,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: 781-238-7758; fax: 781-238-7199; email:
mark.riley@faa.gov.
[[Page 17859]]
(2) Pratt & Whitney Engine Manual, P/N 1A6231, (PW2000) and P/N
1B2412 (F117), Chapter 72-41-00, Inspection/Check-02, (Task 72-41-
00-230-002) and Chapter 72-52-00, Inspection/Check-02 (Task 72-52-
00-230-000), which are not incorporated by reference in this AD, can
be obtained from Pratt & Whitney, using the contact information in
paragraph (l)(3) of this AD.
(l) 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.
(i) Pratt & Whitney Service Bulletin No. PW2000 72-763, Revision
1, dated August 30, 2013.
(ii) Reserved
(3) For PW service information identified in this AD, contact
Pratt & Whitney, 400 Main St., East Hartford, CT 06108; phone: 860-
565-8770; fax: 860-565-4503.
(4) You may view this service information at the FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington,
MA. For information on the availability of this material at the FAA,
call 781-238-7125.
(5) You may view this service information at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on March 6, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2014-06953 Filed 3-28-14; 8:45 am]
BILLING CODE 4910-13-P
