Airworthiness Directives; Pratt & Whitney Division Turbofan Engines, 57007-57010 [2012-22534]
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Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations
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):
■
2012–18–09 Bell Helicopter Textron
Canada (BHTC): Amendment 39–17185;
Docket No. FAA–2012–0337; Directorate
Identifier 2010–SW–090–AD.
(a) Applicability
This AD applies to BHTC Model 407
helicopters, serial numbers 53000 through
53990, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as an
incorrect torque value of the tailboom
attachment bolt (bolt) specified in the BHTC
Model 407 Maintenance Manual and applied
during manufacturing, which exceeds the
torque range recommended for the bolts. This
condition could result in an over-torque of
the bolt, bolt failure, loss of the tailboom, and
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective October 22,
2012.
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(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless
accomplished previously.
(e) Required Actions
(1) For helicopters with 7000 hours or less
time-in-service (TIS), at the next 600 hours
scheduled inspection, or 90 days, whichever
comes first; and for helicopters with more
than 7000 hours TIS, within 150 hours TIS
or 90 days, whichever comes first, replace the
tailboom-attachment hardware (attachment
hardware) as follows:
(i) Remove the left upper bolt, washers,
and nut.
(ii) Install a new bolt, part number (P/N)
NAS627–30; washer, P/N 140–007–29S25E6;
washer(s), P/N NAS1149G0732P; and new
nut, P/N 42FLW–720 in accordance with
paragraphs 2.a) through paragraph 3.e) of the
‘‘Accomplishment Instructions: Replacement
of tailboom attachment bolts and nuts’’
section and Figure 2 in the BHTC Alert
Service Bulletin No. 407–10–93, Revision A,
dated August 30, 2010 (ASB).
(iii) Remove the opposite right upper bolt,
washers, and nut, and accomplish the
requirements in paragraph (e)(1)(ii) of this
AD.
(iv) Remove the left lower bolt, washers,
and nut.
(v) Install a new bolt, (P/N) NAS626–26;
washer, P/N 140–007–25S22E6; washer(s), P/
N NAS1149G0663P; and new nut, P/N
42FLW–624 in accordance with paragraphs
6.a) through 7.e) of the ‘‘Accomplishment
Instructions: Replacement of tailboom
attachment bolts and nuts’’ section and
Figure 2 in the ASB.
(vi) Remove the right lower bolt, washers,
and nut, and accomplish the requirements in
paragraph (e)(1)(v) of this AD.
(2) After installation of the new attachment
hardware, at intervals of not less than 1 hour
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57007
TIS but not exceeding 5 hours TIS, determine
the torque of each nut until the torque
stabilizes at each attachment location,
referring to Figure 2 of the ASB. Apply the
minimum specified torque of the range, plus
the minimum acceptable tare torque of 14
inch/lbs (1.58 Nm) for the upper nuts, and
9.5 inch/lbs (1.07 Nm) for the lower nuts.
(3) At intervals not to exceed 300 hours
TIS, determine the torque of each of the four
attachment nuts, referring to Figure 2 of the
ASB. Apply the minimum specified torque of
the range plus the minimum acceptable tare
torque of 14 inch/lbs (1.58 Nm) for the upper
nuts, and 9.5 inch/lbs (1.07 Nm) for the lower
nuts. If the proper torque has not been
retained since the last torque determination,
remove and inspect the tailboom assembly
for damage, corrosion, improper assembly,
and condition. If the tailboom assembly is
airworthy, replace the attachment hardware
in accordance with the requirements in
paragraphs (e)(1)(i) through (e)(1)(vi) and
determine that the torque has stabilized in
accordance with paragraph (e)(2) of this AD.
Replace any unairworthy tailboom assembly
with an airworthy tailboom assembly.
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137. For information on the
availability of this material at the FAA, call
(817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Sharon Miles,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone: (817) 222–5122; fax: 817–
222–5961; email: sharon.y.miles@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
14 CFR Part 39
(g) Additional Information
The subject of this AD is addressed in the
Transport Canada Civil Aviation (TCCA) AD
CF–2010–33, dated September 30, 2010.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: Rotorcraft tailboom.
(i) 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) Bell Helicopter Textron Canada Limited
Alert Service Bulletin No. 407–10–93,
Revision A, dated August 30, 2010.
(ii) Reserved.
(3) For service information identified in
this AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
Mirabel, Quebec J7J1R4, telephone (450)
437–2862 or (800) 363–8023, fax (450) 433–
0272, or at https://www.bellcustomer.com/
files/.
(4) You may review a copy of this service
information at the FAA, Office of the
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Issued in Fort Worth, Texas, on August 30,
2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2012–22038 Filed 9–14–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2010–0217; Directorate
Identifier 2009–NE–23–AD; Amendment 39–
17194; AD 2012–18–17]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Division Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
all Pratt & Whitney Division (Pratt &
Whitney) PW4052, PW4056, PW4060,
PW4062, PW4062A, PW4074, PW4077,
PW4077D, PW4084D, PW4090,
PW4090–3, PW4152, PW4156A,
PW4158, PW4164, PW4168, PW4168A,
PW4460, and PW4462 turbofan engines.
That AD currently requires initial and
repetitive fluorescent penetrant
inspections (FPI) for cracks in the blade
loading and locking slots of the highpressure compressor (HPC) drum rotor
disk assembly rear drum. This new AD
requires the same actions, requires
replacement of the 13th, 14th, and 15th
stage HPC seals with redesigned HPC
seals as an additional action, and adds
an optional terminating action to the
repetitive inspection requirements by
allowing replacement of the entire HPC
drum rotor disk assembly with a
redesigned HPC drum rotor disk
assembly. This AD was prompted by
Pratt & Whitney developing a
redesigned HPC drum rotor disk
assembly for certain affected engine
models. We are issuing this AD to
prevent failure of the HPC drum rotor
disk assembly, which could lead to an
SUMMARY:
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Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations
uncontained engine failure, and damage
to the airplane.
DATES: This AD is effective October 22,
2012.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 22, 2012.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of October 18, 2010 (75 FR
55459, September 13, 2010).
ADDRESSES: For service information
identified in this AD, contact Pratt &
Whitney, 400 Main St., East Hartford,
CT 06108; phone: 860–565–7700; fax:
860–565–1605. 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; 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:
James Gray, Aerospace Engineer, Engine
& Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7742; fax: 781–
238–7199; email: james.e.gray@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010–18–13,
Amendment 39–16427 (75 FR 55459,
September 13, 2010). That AD applies to
the specified products. The NPRM
published in the Federal Register on
May 24, 2012 (77 FR 30926). That
NPRM proposed to retain all of the
requirements of AD 2010–18–13. That
NPRM also proposed to require
replacement of the 13th, 14th, and 15th
stage HPC seals with redesigned seals
and add an optional terminating action
to the repetitive inspection requirement
by allowing replacement of the HPC
drum rotor disk assembly with a
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redesigned HPC drum rotor disk
assembly.
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.
In Agreement With the Proposed AD
The Boeing Company and FedEx
Express are in agreement with the
proposed AD.
Request To Allow for Previous Credit
FedEx Express requested that we
allow credit for prior compliance with
the AD actions.
We do not agree. The proposed AD
already allows credit for prior
compliance in paragraph (e), which
states to comply within the compliance
times specified unless already done. We
did not change the AD.
Request To Reference the Latest
Revisions of Two Service Bulletins
(SBs)
United Airlines, Korean Air, and
Atlas Air, requested that we reference
the latest revisions of two SBs which
were revised since the proposed AD was
issued.
We agree. We now reference Pratt &
Whitney SB No. PW4ENG 72–816,
Revision 1, dated June 12, 2012, and
Pratt & Whitney SB No. PW4G–100–72–
240, Revision 1, dated June 12, 2012, in
the AD.
Request To Revise Paragraph (g)
United Airlines requested that we
change paragraph (g) of the proposed
AD to only require use of paragraphs
1.A. through 1.C. of the
Accomplishment Instructions of SB No.
PW4ENG 72–816 since additional
paragraphs of the SB are not needed to
comply with the AD.
We agree. We changed paragraphs
(g)(1) and (g)(2) to only require use of
paragraphs 1.A through 1.C. of that SB
to comply with the AD.
Request To Add Previously Approved
Alternate Methods of Compliance
(AMOCs)
Japan Airlines and Korean Air
requested that we add the previously
approved AMOCs to the AD. The
commenters referenced two previously
approved AMOCs related to taking
credit for the inspections required by
AD 2005–25–09 (70 FR 73358,
December 12, 2005), and use of the disk
replacement repair included in the
PW4000 Engine Cleaning Inspection
and Repair (CIR) Manual to return non-
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cracked stages of the drum rotor disk
assembly to service.
We do not agree. We did not list the
previously approved AMOCs in the
proposed AD because paragraph (j) of
the proposed AD already allows use of
previously approved AMOCs to
paragraph (f) of the existing AD.
Paragraph (f) was specified because the
content of this paragraph did not change
in the proposed AD supersedure. We
did not change the AD.
Request To Revise Paragraph (f)(2)
Atlas Air requested that we revise
paragraph (f)(2) of the proposed AD to
remove only the cracked disk in the
HPC drum rotor disk assembly from
service. The commenter stated that
currently paragraph (f)(2) requires the
entire drum rotor disk assembly to be
removed from service if a crack is
found. The commenter believes it would
be acceptable to remove from service
only the cracked disk in the drum rotor
disk assembly and use the repair in the
PW4000 Engine CIR manual to replace
it with a serviceable disk.
We partially agree. We agree that an
acceptable level of safety would be
maintained by returning the other stages
of the drum rotor disk assembly to
service if they were not cracked, if the
cracked stages of the HPC drum rotor
disk assembly were replaced by new
disks per the disk replacement repairs
in the PW4000 Engine CIR manual. We
do not agree with revising the proposed
AD because this is already an approved
global AMOC covered under paragraph
(j) of the proposed AD. We did not
change the AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
Costs of Compliance
We estimate that this AD will affect
911 engines installed on airplanes of
U.S. registry. We also estimate that it
will take about 1 work-hour per engine
to perform an inspection using an
average labor rate of $85 per work-hour.
We estimate that there are 770 PW4000–
94″ and PW4000–100″ engines that will
require replacement of 13th, 14th, and
15th stage HPC seals, at a parts cost of
$3,000 per engine. No additional labor
is assumed when the replacement is
done at piece-part exposure of the HPC
drum rotor disk assembly. The
replacement parts cost of the redesigned
HPC drum rotor disk assembly is
$630,000. Based on these figures, we
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Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations
estimate that the total cost of the AD to
U.S. operators will be $2,387,435.
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
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
removing airworthiness directive (AD)
■
57009
2010–18–13, Amendment 39–16427 (75
FR 55459, September 13, 2010), and
adding the following new AD:
2012–18–17 Pratt & Whitney Division:
Amendment 39–17194; Docket No.
FAA–2010–0217; Directorate Identifier
2009–NE–23–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective October 22, 2012.
(b) Affected ADs
This AD supersedes AD 2010–18–13,
Amendment 39–16427 (75 FR 55459,
September 13, 2010).
(c) Applicability
This AD applies to the following Pratt &
Whitney Division (Pratt & Whitney) turbofan
engines:
(1) PW4000–94″ engine models PW4052,
PW4056, PW4060, PW4062, PW4062A,
PW4152, PW4156A, PW4158, PW4460, and
PW4462, including those models with any
dash number suffix, with a high-pressure
compressor (HPC) drum rotor disk assembly
listed in Table 1 to paragraph (c) of this AD
installed.
(2) PW4000–100″ engine models PW4164,
PW4168, and PW4168A, with a HPC drum
rotor disk assembly listed in Table 1 to
paragraph (c) of this AD installed.
(3) PW4000–112″ engine models PW4074,
PW4077, PW4077D, PW4084D, PW4090, and
PW4090–3, with a HPC drum rotor disk
assembly listed in Table 1 to paragraph (c) of
this AD installed.
TABLE 1 TO PARAGRAPH (c)—AFFECTED HPC DRUM ROTOR DISK ASSEMBLIES
Engine models
Affected HPC drum rotor disk assembly part numbers
PW4000–94″ ...................................
50H936; 50H936–002; 53H923–01; 53H923–001; 53H973–01; 53H973–001; 54H803–01; 54H803–001;
54H803–002; 56H013–01; 56H013–001; 58H236–01
53H973–01; 53H973–001; 54H803–01; 54H803–001; 54H803–002; 56H013–01; 56H013–001; 58H236–01
55H722–01; 55H410–01; 57H010–01; 57H210–01; 57H610–01; 57H910–01
PW4000–100″ .................................
PW4000–112″ .................................
(d) Unsafe Condition
This AD was prompted by Pratt & Whitney
developing a redesigned HPC drum rotor disk
assembly for certain affected engine models.
We are issuing this AD to prevent failure of
the HPC drum rotor disk assembly, which
could lead to an uncontained engine failure,
and damage to the airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(f) Local Fluorescent Penetrant Inspection
(1) Perform a local fluorescent penetrant
inspection for cracks in the HPC drum rotor
disk assembly rear drum blade loading and
locking slots of the specific stages of the HPC
drum rotor disk assemblies from which any
of the blades are removed as specified in
Table 2 to paragraph (f) of this AD.
TABLE 2 TO PARAGRAPH (f)—COMPLIANCE TIMES AND SERVICE BULLETINS BY ENGINE MODEL
For engine model
Inspect whenever . . .
To inspect, use . . .
PW4084D,
Any of the HPC 13th or 14th stage blades are
removed during a shop visit.
PW4164, PW4168, and PW4168A ....................
Any of the HPC 13th, 14th, or 15th stage
blades are removed during a shop visit.
PW4052,
PW4056,
PW4060,
PW4062,
PW4062A, PW4152, PW4156A, PW4158,
PW4460, and PW4462.
Any of the HPC 13th, 14th, or 15th stage
blades are removed during a shop visit.
Paragraphs 1.A. through 1.B. of the Accomplishment Instructions of PW4G–112–72–
264, Revision 2, dated February 23, 2010.
Paragraphs 1.A. through 1.C of the Accomplishment Instructions of PW4G–100–72–
186, Revision 1, dated September 2, 2004.
Paragraphs 1.A. through 1.C. of the Accomplishment Instructions of PW4ENG 72–796,
dated June 11, 2009.
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PW4074, PW4077, PW4077D,
PW4090, and PW4090–3.
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Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations
(h) Optional Terminating Action
As optional terminating action to the
repetitive inspection requirements of this
AD:
(1) Replace the HPC drum rotor disk
assembly of engines listed in paragraph (c)(1)
of this AD with a redesigned HPC drum rotor
disk assembly in accordance with the
Accomplishment Instructions of Pratt &
Whitney SB No. PW4ENG 72–817, dated
December 7, 2011.
(2) Replace the HPC drum rotor disk
assembly of engines listed in paragraph (c)(2)
of this AD with a redesigned HPC drum rotor
disk assembly in accordance with the
Accomplishment Instructions of Pratt &
Whitney SB No. PW4G–100–72–241, dated
November 15, 2011.
(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 October 22, 2012.
(i) Pratt & Whitney Service Bulletin No.
PW4G–100–72–240, Revision 1, dated June
12, 2012.
(ii) Pratt & Whitney Service Bulletin No.
PW4G–100–72–241, dated November 15,
2011.
(iii) Pratt & Whitney Service Bulletin No.
PW4ENG 72–816, Revision 1, dated June 12,
2012.
(iv) Pratt & Whitney Service Bulletin No.
PW4ENG 72–817, dated December 7, 2011.
(4) The following service information was
approved for IBR on October 18, 2010 (75 FR
55459, September 13, 2010).
(i) Pratt & Whitney Service Bulletin No.
PW4G–100–72–186, Revision 1, dated
September 2, 2004.
(ii) Pratt & Whitney Service Bulletin No.
PW4G–112–72–264, Revision 2, dated
February 23, 2010.
(iii) Pratt & Whitney Service Bulletin No.
PW4ENG 72–796, dated June 11, 2009.
(5) For Pratt & Whitney service information
identified in this AD, contact Pratt &
Whitney, 400 Main St., East Hartford, CT
06108; phone: 860–565–7700; fax: 860–565–
1605.
(6) You may view this service information
at 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.
(7) 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.
(i) Definition
For the purpose of this AD, piece-part
exposure means that the HPC drum rotor disk
assembly is removed from the engine and
completely disassembled.
Issued in Burlington, Massachusetts, on
September 4, 2012.
Colleen M. D’Alessandro,
Assistant Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
(j) 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. AMOCs approved previously in
accordance with AD 2010–18–13,
Amendment 39–16427 (75 FR 55459,
September 13, 2010) are approved as AMOCs
for the corresponding requirements in
paragraph (f) of this AD.
[FR Doc. 2012–22534 Filed 9–14–12; 8:45 am]
(2) Remove from service any HPC drum
rotor disk assembly rear drum found with a
crack in any of the blade loading and locking
slots.
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(g) Replacement of 13th, 14th, and 15th HPC
Seals
At the next piece-part exposure of the HPC
drum rotor disk assembly after the effective
date of this AD:
(1) Replace the 13th, 14th, and 15th stage
HPC seals with redesigned HPC seals of
engines listed in paragraph (c)(1) of this AD
in accordance with paragraphs 1.A through
1.C of the Accomplishment Instructions of
Pratt & Whitney Service Bulletin (SB) No.
PW4ENG 72–816, Revision 1, dated June 12,
2012.
(2) Replace the 13th, 14th, and 15th stage
HPC seals with redesigned HPC seals of
engines listed in paragraph (c)(2) of this AD
in accordance with paragraphs 1.A through
1.C of the Accomplishment Instructions of
Pratt & Whitney SB No. PW4G–100–72–240,
Revision 1, dated June 12, 2012.
(k) Related Information
For more information about this AD,
contact James Gray, Aerospace Engineer,
Engine & Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7742; fax: 781–238–
7199; email: james.e.gray@faa.gov.
(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.
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2011–1407; Airspace
Docket No. 11–AGL–25]
RIN 2120–AA66
Modification of Area Navigation
(RNAV) Route Q–62; Northeast United
States
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action modifies area
navigation (RNAV) route Q–62 by
extending it further west and
SUMMARY:
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incorporating two additional navigation
fixes. The route extension links two
RNAV Standard Terminal Arrival
Routes (STARs) serving the Chicago
O’Hare International Airport, IL,
terminal area with the high altitude
route. The FAA is taking this action to
increase National Airspace System
(NAS) efficiency and enhance flight
safety as aircraft transition from the en
route airway structure to the terminal
area airspace phase of flight.
DATES: Effective date 0901 UTC,
November 15, 2012. The Director of the
Federal Register approves this
incorporation by reference action under
1 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, Regulations and
ATC Procedures Group, Office of
Airspace Services, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
History
On Monday, February 6, 2012, the
FAA published in the Federal Register
a notice of proposed rulemaking to
modify RNAV route Q–62 in Northeast
United States by extending it further
west (77 FR 5733). Interested parties
were invited to participate in this
rulemaking proceeding by submitting
written comments on this proposal to
the FAA. No comments were received.
The Rule
The FAA is amending Title 14, Code
of Federal Regulations (14 CFR) part 71
by extending high altitude RNAV route
Q–62 to the west to include the WATSN
and DAIFE fixes. This action links the
WATSN and HALIE RNAV STARs
serving Chicago O’Hare International
Airport, IL, with the high altitude route
and establishes a seamless transition for
westbound air traffic from the New York
metropolitan area into the Chicago
O’Hare International Airport, IL,
terminal area. Additionally, this action
reduces ATC system complexity, air
traffic controller and pilot workload,
voice communication requirements, and
aircraft fuel consumption. It also
expands the use of RNAV within the
NAS.
High altitude RNAV routes are
published in paragraph 2006 of FAA
Order 7400.9W dated August 8, 2012,
and effective September 15, 2012, which
is incorporated by reference in 14 CFR
71.1. The RNAV route listed in this
document will be subsequently
published in the Order.
E:\FR\FM\17SER1.SGM
17SER1
]]>Agencies
[Federal Register Volume 77, Number 180 (Monday, September 17, 2012)]
[Rules and Regulations]
[Pages 57007-57010]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-22534]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0217; Directorate Identifier 2009-NE-23-AD;
Amendment 39-17194; AD 2012-18-17]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Division Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for all Pratt & Whitney Division (Pratt & Whitney) PW4052, PW4056,
PW4060, PW4062, PW4062A, PW4074, PW4077, PW4077D, PW4084D, PW4090,
PW4090-3, PW4152, PW4156A, PW4158, PW4164, PW4168, PW4168A, PW4460, and
PW4462 turbofan engines. That AD currently requires initial and
repetitive fluorescent penetrant inspections (FPI) for cracks in the
blade loading and locking slots of the high-pressure compressor (HPC)
drum rotor disk assembly rear drum. This new AD requires the same
actions, requires replacement of the 13th, 14th, and 15th stage HPC
seals with redesigned HPC seals as an additional action, and adds an
optional terminating action to the repetitive inspection requirements
by allowing replacement of the entire HPC drum rotor disk assembly with
a redesigned HPC drum rotor disk assembly. This AD was prompted by
Pratt & Whitney developing a redesigned HPC drum rotor disk assembly
for certain affected engine models. We are issuing this AD to prevent
failure of the HPC drum rotor disk assembly, which could lead to an
[[Page 57008]]
uncontained engine failure, and damage to the airplane.
DATES: This AD is effective October 22, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 22,
2012.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of October
18, 2010 (75 FR 55459, September 13, 2010).
ADDRESSES: For service information identified in this AD, contact Pratt
& Whitney, 400 Main St., East Hartford, CT 06108; phone: 860-565-7700;
fax: 860-565-1605. 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; 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: James Gray, Aerospace Engineer, Engine
& Propeller Directorate, FAA, 12 New England Executive Park,
Burlington, MA 01803; phone: 781-238-7742; fax: 781-238-7199; email:
james.e.gray@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010-18-13, Amendment 39-16427 (75 FR 55459,
September 13, 2010). That AD applies to the specified products. The
NPRM published in the Federal Register on May 24, 2012 (77 FR 30926).
That NPRM proposed to retain all of the requirements of AD 2010-18-13.
That NPRM also proposed to require replacement of the 13th, 14th, and
15th stage HPC seals with redesigned seals and add an optional
terminating action to the repetitive inspection requirement by allowing
replacement of the HPC drum rotor disk assembly with a redesigned HPC
drum rotor disk assembly.
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.
In Agreement With the Proposed AD
The Boeing Company and FedEx Express are in agreement with the
proposed AD.
Request To Allow for Previous Credit
FedEx Express requested that we allow credit for prior compliance
with the AD actions.
We do not agree. The proposed AD already allows credit for prior
compliance in paragraph (e), which states to comply within the
compliance times specified unless already done. We did not change the
AD.
Request To Reference the Latest Revisions of Two Service Bulletins
(SBs)
United Airlines, Korean Air, and Atlas Air, requested that we
reference the latest revisions of two SBs which were revised since the
proposed AD was issued.
We agree. We now reference Pratt & Whitney SB No. PW4ENG 72-816,
Revision 1, dated June 12, 2012, and Pratt & Whitney SB No. PW4G-100-
72-240, Revision 1, dated June 12, 2012, in the AD.
Request To Revise Paragraph (g)
United Airlines requested that we change paragraph (g) of the
proposed AD to only require use of paragraphs 1.A. through 1.C. of the
Accomplishment Instructions of SB No. PW4ENG 72-816 since additional
paragraphs of the SB are not needed to comply with the AD.
We agree. We changed paragraphs (g)(1) and (g)(2) to only require
use of paragraphs 1.A through 1.C. of that SB to comply with the AD.
Request To Add Previously Approved Alternate Methods of Compliance
(AMOCs)
Japan Airlines and Korean Air requested that we add the previously
approved AMOCs to the AD. The commenters referenced two previously
approved AMOCs related to taking credit for the inspections required by
AD 2005-25-09 (70 FR 73358, December 12, 2005), and use of the disk
replacement repair included in the PW4000 Engine Cleaning Inspection
and Repair (CIR) Manual to return non-cracked stages of the drum rotor
disk assembly to service.
We do not agree. We did not list the previously approved AMOCs in
the proposed AD because paragraph (j) of the proposed AD already allows
use of previously approved AMOCs to paragraph (f) of the existing AD.
Paragraph (f) was specified because the content of this paragraph did
not change in the proposed AD supersedure. We did not change the AD.
Request To Revise Paragraph (f)(2)
Atlas Air requested that we revise paragraph (f)(2) of the proposed
AD to remove only the cracked disk in the HPC drum rotor disk assembly
from service. The commenter stated that currently paragraph (f)(2)
requires the entire drum rotor disk assembly to be removed from service
if a crack is found. The commenter believes it would be acceptable to
remove from service only the cracked disk in the drum rotor disk
assembly and use the repair in the PW4000 Engine CIR manual to replace
it with a serviceable disk.
We partially agree. We agree that an acceptable level of safety
would be maintained by returning the other stages of the drum rotor
disk assembly to service if they were not cracked, if the cracked
stages of the HPC drum rotor disk assembly were replaced by new disks
per the disk replacement repairs in the PW4000 Engine CIR manual. We do
not agree with revising the proposed AD because this is already an
approved global AMOC covered under paragraph (j) of the proposed AD. We
did not change the AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously.
Costs of Compliance
We estimate that this AD will affect 911 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 1
work-hour per engine to perform an inspection using an average labor
rate of $85 per work-hour. We estimate that there are 770 PW4000-94''
and PW4000-100'' engines that will require replacement of 13th, 14th,
and 15th stage HPC seals, at a parts cost of $3,000 per engine. No
additional labor is assumed when the replacement is done at piece-part
exposure of the HPC drum rotor disk assembly. The replacement parts
cost of the redesigned HPC drum rotor disk assembly is $630,000. Based
on these figures, we
[[Page 57009]]
estimate that the total cost of the AD to U.S. operators will be
$2,387,435.
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)
2010-18-13, Amendment 39-16427 (75 FR 55459, September 13, 2010), and
adding the following new AD:
2012-18-17 Pratt & Whitney Division: Amendment 39-17194; Docket No.
FAA-2010-0217; Directorate Identifier 2009-NE-23-AD.
(a) Effective Date
This airworthiness directive (AD) is effective October 22, 2012.
(b) Affected ADs
This AD supersedes AD 2010-18-13, Amendment 39-16427 (75 FR
55459, September 13, 2010).
(c) Applicability
This AD applies to the following Pratt & Whitney Division (Pratt
& Whitney) turbofan engines:
(1) PW4000-94'' engine models PW4052, PW4056, PW4060, PW4062,
PW4062A, PW4152, PW4156A, PW4158, PW4460, and PW4462, including
those models with any dash number suffix, with a high-pressure
compressor (HPC) drum rotor disk assembly listed in Table 1 to
paragraph (c) of this AD installed.
(2) PW4000-100'' engine models PW4164, PW4168, and PW4168A, with
a HPC drum rotor disk assembly listed in Table 1 to paragraph (c) of
this AD installed.
(3) PW4000-112'' engine models PW4074, PW4077, PW4077D, PW4084D,
PW4090, and PW4090-3, with a HPC drum rotor disk assembly listed in
Table 1 to paragraph (c) of this AD installed.
Table 1 to Paragraph (c)--Affected HPC Drum Rotor Disk Assemblies
------------------------------------------------------------------------
Affected HPC drum rotor disk
Engine models assembly part numbers
------------------------------------------------------------------------
PW4000-94''....................... 50H936; 50H936-002; 53H923-01;
53H923-001; 53H973-01; 53H973-001;
54H803-01; 54H803-001; 54H803-002;
56H013-01; 56H013-001; 58H236-01
PW4000-100''...................... 53H973-01; 53H973-001; 54H803-01;
54H803-001; 54H803-002; 56H013-01;
56H013-001; 58H236-01
PW4000-112''...................... 55H722-01; 55H410-01; 57H010-01;
57H210-01; 57H610-01; 57H910-01
------------------------------------------------------------------------
(d) Unsafe Condition
This AD was prompted by Pratt & Whitney developing a redesigned
HPC drum rotor disk assembly for certain affected engine models. We
are issuing this AD to prevent failure of the HPC drum rotor disk
assembly, which could lead to an uncontained engine failure, and
damage to the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(f) Local Fluorescent Penetrant Inspection
(1) Perform a local fluorescent penetrant inspection for cracks
in the HPC drum rotor disk assembly rear drum blade loading and
locking slots of the specific stages of the HPC drum rotor disk
assemblies from which any of the blades are removed as specified in
Table 2 to paragraph (f) of this AD.
Table 2 to Paragraph (f)--Compliance Times and Service Bulletins by
Engine Model
------------------------------------------------------------------------
Inspect whenever . . To inspect, use . .
For engine model . .
------------------------------------------------------------------------
PW4074, PW4077, PW4077D, Any of the HPC 13th Paragraphs 1.A.
PW4084D, PW4090, and PW4090- or 14th stage through 1.B. of the
3. blades are removed Accomplishment
during a shop visit. Instructions of
PW4G-112-72-264,
Revision 2, dated
February 23, 2010.
PW4164, PW4168, and PW4168A. Any of the HPC 13th, Paragraphs 1.A.
14th, or 15th stage through 1.C of the
blades are removed Accomplishment
during a shop visit. Instructions of
PW4G-100-72-186,
Revision 1, dated
September 2, 2004.
PW4052, PW4056, PW4060, Any of the HPC 13th, Paragraphs 1.A.
PW4062, PW4062A, PW4152, 14th, or 15th stage through 1.C. of the
PW4156A, PW4158, PW4460, blades are removed Accomplishment
and PW4462. during a shop visit. Instructions of
PW4ENG 72-796,
dated June 11,
2009.
------------------------------------------------------------------------
[[Page 57010]]
(2) Remove from service any HPC drum rotor disk assembly rear
drum found with a crack in any of the blade loading and locking
slots.
(g) Replacement of 13th, 14th, and 15th HPC Seals
At the next piece-part exposure of the HPC drum rotor disk
assembly after the effective date of this AD:
(1) Replace the 13th, 14th, and 15th stage HPC seals with
redesigned HPC seals of engines listed in paragraph (c)(1) of this
AD in accordance with paragraphs 1.A through 1.C of the
Accomplishment Instructions of Pratt & Whitney Service Bulletin (SB)
No. PW4ENG 72-816, Revision 1, dated June 12, 2012.
(2) Replace the 13th, 14th, and 15th stage HPC seals with
redesigned HPC seals of engines listed in paragraph (c)(2) of this
AD in accordance with paragraphs 1.A through 1.C of the
Accomplishment Instructions of Pratt & Whitney SB No. PW4G-100-72-
240, Revision 1, dated June 12, 2012.
(h) Optional Terminating Action
As optional terminating action to the repetitive inspection
requirements of this AD:
(1) Replace the HPC drum rotor disk assembly of engines listed
in paragraph (c)(1) of this AD with a redesigned HPC drum rotor disk
assembly in accordance with the Accomplishment Instructions of Pratt
& Whitney SB No. PW4ENG 72-817, dated December 7, 2011.
(2) Replace the HPC drum rotor disk assembly of engines listed
in paragraph (c)(2) of this AD with a redesigned HPC drum rotor disk
assembly in accordance with the Accomplishment Instructions of Pratt
& Whitney SB No. PW4G-100-72-241, dated November 15, 2011.
(i) Definition
For the purpose of this AD, piece-part exposure means that the
HPC drum rotor disk assembly is removed from the engine and
completely disassembled.
(j) 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. AMOCs approved previously in accordance with AD 2010-18-13,
Amendment 39-16427 (75 FR 55459, September 13, 2010) are approved as
AMOCs for the corresponding requirements in paragraph (f) of this
AD.
(k) Related Information
For more information about this AD, contact James Gray,
Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA 01803; phone: 781-238-7742;
fax: 781-238-7199; email: james.e.gray@faa.gov.
(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.
(3) The following service information was approved for IBR on
October 22, 2012.
(i) Pratt & Whitney Service Bulletin No. PW4G-100-72-240,
Revision 1, dated June 12, 2012.
(ii) Pratt & Whitney Service Bulletin No. PW4G-100-72-241, dated
November 15, 2011.
(iii) Pratt & Whitney Service Bulletin No. PW4ENG 72-816,
Revision 1, dated June 12, 2012.
(iv) Pratt & Whitney Service Bulletin No. PW4ENG 72-817, dated
December 7, 2011.
(4) The following service information was approved for IBR on
October 18, 2010 (75 FR 55459, September 13, 2010).
(i) Pratt & Whitney Service Bulletin No. PW4G-100-72-186,
Revision 1, dated September 2, 2004.
(ii) Pratt & Whitney Service Bulletin No. PW4G-112-72-264,
Revision 2, dated February 23, 2010.
(iii) Pratt & Whitney Service Bulletin No. PW4ENG 72-796, dated
June 11, 2009.
(5) For Pratt & Whitney service information identified in this
AD, contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108;
phone: 860-565-7700; fax: 860-565-1605.
(6) You may view this service information at 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.
(7) 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 September 4, 2012.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2012-22534 Filed 9-14-12; 8:45 am]
BILLING CODE 4910-13-P
