Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company) 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W Turboprop and Turboshaft Engines, 28420-28423 [05-9660]
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Federal Register / Vol. 70, No. 95 / Wednesday, May 18, 2005 / Rules and Regulations
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); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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Jkt 205001
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–12316 (66 FR
36445, July 12, 2001) and by adding the
following new airworthiness directive
(AD):
I
2005–10–11 Boeing: Amendment 39–14088.
Docket No. FAA–2004–19531;
Directorate Identifier 2004–NM–45–AD.
Effective Date
(a) This AD becomes effective June 22,
2005.
Affected ADs
(b) This AD supersedes AD 2001–14–06,
amendment 39–12316.
Applicability
(c) This AD applies to all Boeing Model
737–300, –400, and –500 series airplanes,
certificated in any category.
Unsafe Condition
(d) This AD was prompted by the
development of a modification intended to
address the unsafe condition. We are issuing
this AD to detect and correct discrepancies
of certain connectors located in the main
wheel well. Those discrepancies could result
in electrical arcing of the connectors,
uncommanded closure of the engine fuel
shut-off valves, and consequent in-flight loss
of thrust or engine shutdown from lack of
fuel.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Modification
(f) At the applicable time specified in
paragraph (f)(1) or (f)(2) of this AD: Modify
the electrical connectors located in the main
wheel well by doing all the actions in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–28–1196, Revision 3,
dated April 1, 2004. Any corrective action
must be done before further flight in
accordance with the service bulletin.
(1) For airplanes on which no inspection
required by AD 2001–14–06 has been done
as of the effective date of this AD:
Accomplish the modification within 12
months after the effective date of this AD.
(2) For airplanes on which any inspection
required by AD 2001–14–06 has been done
as of the effective date of this AD:
Accomplish the modification at the later of
the times specified in paragraph (f)(2)(i) or
(f)(2)(ii) of this AD.
(i) Within 18 months after accomplishing
the last inspection.
(ii) Within 6 months after the effective date
of this AD.
Modifications Done Using Previous Issues of
the Service Bulletin
(g) Modifications done before the effective
date of this AD in accordance with Boeing
Special Attention Service Bulletin 737–28–
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1196, dated December 5, 2002; Revision 1,
dated March 13, 2003; or Revision 2, dated
August 21, 2003; are considered acceptable
for compliance with paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Alternative methods of compliance,
approved previously in accordance with AD
2001–14–06, amendment 39–12316, are
approved as AMOCs for this AD.
Material Incorporated by Reference
(i) You must use Boeing Special Attention
Service Bulletin 737–28–1196, Revision 3,
dated April 1, 2004, to perform the actions
that are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approves the incorporation
by reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the service information, contact
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207. To
view the AD docket, go to the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC. To review copies of the service
information, go to the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on May 9,
2005.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–9659 Filed 5–17–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19648; Directorate
Identifier 2004–NE–31–AD; Amendment 39–
14090; AD 2005–10–13]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation (Formerly Allison Engine
Company) 250–B17B, –B17C, –B17D,
–B17E, –C20, –C20B, –C20F, –C20J,
–C20S, and –C20W Turboprop and
Turboshaft Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Rolls-
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Federal Register / Vol. 70, No. 95 / Wednesday, May 18, 2005 / Rules and Regulations
Royce Corporation (RRC) (formerly
Allison Engine Company) 250–B17B,
–B17C, –B17D, –B17E, –C20, –C20B,
–C20F, –C20J, –C20S, and –C20W
turboprop and turboshaft engines that
do not have turbine energy absorbing
ring, RRC part number (P/N) 23035175,
or an equivalent FAA-approved
serviceable turbine energy absorbing
ring, installed. This AD requires
installation of a turbine energy
absorbing ring in the plane of the 1st
stage turbine wheel. This AD results
from an unacceptable rate of
uncontained 1st stage turbine wheel
failures. We are issuing this AD to
minimize the risk of uncontained 1st
stage turbine wheel fragments from
causing damage to the aircraft or
damage to the second engine on twinengine installations, which could lead
to loss of control and loss of the aircraft.
This AD becomes effective June
22, 2005. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of June 22, 2005.
DATES:
Contact Rolls-Royce
Corporation, P.O. Box 420, Indianapolis,
IN 46206–0420; telephone (317) 230–
2712; fax (317) 230–3381 for the service
information identified in this AD.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Melissa T. Bradley, Aerospace Engineer,
Chicago Aircraft Certification Office,
FAA, 2300 East Devon Avenue, Des
Plaines, IL 60018–4696; telephone (847)
294–8110; fax (847) 294–7834.
The FAA
proposed to amend 14 CFR part 39 with
a proposed airworthiness directive (AD).
The proposed AD applies to Rolls-Royce
Corporation (RRC) (formerly Allison
Engine Company) 250–B17B, –B17C,
–B17D, –B17E, –C20, –C20B, –C20F,
–C20J, –C20S, and –C20W turboprop
and turboshaft engines that do not have
turbine energy absorbing ring, RRC P/N
23035175, installed. We published the
proposed AD in the Federal Register on
November 22, 2004 (69 FR 67867). That
action proposed to require installation
of a turbine energy absorbing ring in the
plane of the 1st stage turbine wheel.
That action also proposed to require
installation of 1st stage turbine nozzles,
2nd stage turbine nozzles, and a gas
producer support assembly, all modified
to allow for installation of the turbine
energy absorbing ring.
SUPPLEMENTARY INFORMATION:
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Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the DMS Docket Offices
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Office (telephone (800) 647–
5227) is located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Add Helicopters to the
Applicability of the AD
One commenter requests that we add
to the applicability of the AD, the
Rogerson Hiller Corporation UH–12E
helicopter, modified by Supplemental
Type Certificate (STC) SH178WE, in
addition to including STC SH657NW
applicability. The commenter states that
the proposed AD did not reference all
known installations of the affected
engines.
We agree that all known installations
of the affected engines should have been
listed. We have corrected the
applicability, by adding helicopters that
are listed under STC SH177WE, STC
SH178WE, STC SH218NW–D, and STC
SH657NW.
Request the FAA Require RRC To
Supply All Parts Needed at No Cost
One commenter requests that we
require RRC to supply all parts needed
to comply with the AD, at no cost to the
operator. The commenter is concerned
about the financial impact the AD will
have on operators.
We understand the commenter’s
concern over parts costs, however, we
do not have the authority to control or
eliminate parts costs.
Request To Change the Compliance
One commenter requests that the
compliance be done at the next 1,750hour hot section inspection or turbine
overhaul.
We do not agree. Our existing
compliance time is based on minimizing
the risk of failure. If compliance time is
extended to the next hot section
inspection or turbine overhaul for the
entire population of engines, then the
associated fleet risk would increase to
an unacceptable level.
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28421
Request To Eliminate the Final
Compliance Date
One commenter requests we eliminate
the final compliance date of October 31,
2011. The commenter has a concern that
operators who have recently overhauled
the turbine, will not accumulate the
1,750 hours before the final compliance
date.
We do not agree. We have a final
compliance date in the AD to ensure
compliance within a reasonable period
of time (over six years) for engines that
may not accumulate 1,750 hours, or may
not be disassembled for any reason
before the final compliance date. Risk of
failure increases with each additional
year the engine does not comply.
Request To Include FAA–PMA P/Ns
One commenter requests that the AD
include the FAA–PMA P/N for the
turbine energy absorbing ring
manufactured by EXTEX, as well as all
other equivalent FAA–PMA P/Ns for
turbine energy absorbing rings. The
commenter’s concern is that the
proposed AD states that the AD applies
to engines that do not have turbine
energy absorbing ring, P/N 23035175,
installed. The commenter states that this
wording implies that the only method of
compliance is by installing the turbine
energy absorbing ring manufactured by
the Type Certificate holder, RRC.
Equivalent FAA–PMA turbine energy
absorbing rings are also available to
install.
We partially agree. We have changed
the AD to identify the part number
referenced, as an RRC part number, and,
to take into account that there are
equivalent parts available.
Request To Remove Paragraphs (f) and
(g) From the Compliance
One commenter requests that we
remove paragraphs (f) and (g) from the
compliance. The commenter states that
these paragraphs are unnecessary and
restrictive. AD compliance paragraph (f)
states to use paragraph 2. of RRC Alert
Commercial Engine Bulletin (CEB) No.
CEB–A–1254, Revision 3, dated May 21,
2004, to modify the gas producer
support. This paragraph would prevent
the use of currently available and
widely used FAA-Designated
Engineering Representative (DER)approved methods to modify the gas
producer support, for installing the
turbine energy absorbing ring. An
operator would have to request
numerous Alternative Methods of
Compliance (AMOCs) because of the
overly restrictive wording.
The commenter also states that AD
compliance paragraph (g) specifies to
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Federal Register / Vol. 70, No. 95 / Wednesday, May 18, 2005 / Rules and Regulations
use paragraph 2. of RRC Alert CEB No.
CEB–A–1253, Revision 4, dated May 21,
2004, to modify and install the 1st stage
turbine nozzle and 2nd stage turbine
nozzle. This CEB Revision 4 only lists
the latest P/N for the 1st stage turbine
nozzle. Since the issuance of the
original version of this CEB on June 1,
1988, several P/Ns of 1st stage turbine
nozzles exist which are the required
configuration to allow installation of a
turbine energy absorbing ring. These
earlier 1st stage turbine nozzles are still
in wide circulation and are perfectly
suitable for use. AD compliance
paragraph (g) would prevent the use of
these earlier P/N 1st stage turbine
nozzles without first receiving AMOC
approval.
The commenter concludes by stating
that installing the turbine energy
absorbing ring without modifying the
gas producer support and nozzles is
physically impossible. Paragraph 1.M of
RRC CEB No. CEB–A–1255, Revision 4,
dated September 29, 2004, lists CEB No.
CEB–A–1253 and No. CEB–A–1254 as
prerequisites to CEB No. CEB–A–1255,
without the overly restrictive use of
specific revision numbers and dates.
That same prerequisite paragraph also
includes the necessary words ‘‘or
equivalent’’ to these two CEBs.
We agree. We have replaced
paragraphs (f), (g), and (h) of this AD
with the following single paragraph: ‘‘(f)
Install a turbine energy absorbing ring,
RRC P/N 23035175, or an equivalent
FAA-approved serviceable turbine
energy absorbing ring, in the plane of
the 1st stage turbine wheel, using
paragraphs 1.M., 2.A., and 2.B. of RollsRoyce Corporation Alert Commercial
Engine Bulletin No. CEB–A–1255,
Revision 4, dated September 29, 2004,
to do the installation.’’
Request To Reevaluate the Basis for the
AD
One commenter requests we
reevaluate the basis for the AD. The
request is based on field experience of
an operator who has maintained the
250–C20 series engines for over 25
years, and is concerned with the
financial impact on operators. The
commenter has never seen a 1st stage
turbine wheel failure and questions the
validity of RRC’s analysis.
We do not agree. We reviewed the
analysis and associated risk and find it
necessary to issue this AD.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
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16:58 May 17, 2005
Jkt 205001
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are about 13,299 RRC 250–
B17B, –B17C, –B17D, –B17E, –C20,
–C20B, –C20F, –C20J, –C20S, and
–C20W turboprop and turboshaft
engines of the affected design in the
worldwide fleet. We estimate that 5,000
engines installed on helicopters of U.S.
registry require the installation of a
turbine energy absorbing ring. Of those
5,000 engines, we also estimate that
4,000 engines require installation of a
gas producer support assembly, 1st stage
turbine nozzle, and 2nd stage turbine
nozzle. About 16 work hours per engine
are needed to install the turbine energy
absorbing ring, 35 work hours to install
the gas producer support assembly, and
20 work hours to install the 1st stage
turbine nozzle, and 2nd stage turbine
nozzle. The average labor rate is $65 per
work hour. Required turbine energy
absorbing rings cost about $10,765 per
engine. Required gas producer support
assemblies cost about $2,500 per engine.
Required 1st stage turbine nozzles and
2nd stage turbine nozzles cost about
$1,000 per engine. Based on these
figures, we estimate the total cost of the
AD to U.S. operators to be $87,325,000.
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
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
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 Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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:
I
2005–10–13 Rolls-Royce Corporation
(formerly Allison Engine Company):
Amendment 39–14090. Docket No.
FAA–2004–19648; Directorate Identifier.
2004–NE–31–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 22, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce
Corporation (RRC) (formerly Allison Engine
Company) 250–B17B, B17C, –B17D, –B17E,
–C20, –C20B, –C20F, –C20J, –C20S, and
–C20W turboprop and turboshaft engines that
do not have turbine energy absorbing ring,
RRC part number (P/N) 23035175, or an
equivalent FAA-approved serviceable turbine
energy absorbing ring, installed. These
engines are installed on, but not limited to,
the following aircraft:
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Federal Register / Vol. 70, No. 95 / Wednesday, May 18, 2005 / Rules and Regulations
28423
Agusta A109
Agusta A109A
Agusta A109A II
B–N Group BN–2T
Bell 206A
Bell 206B
Bell 206L
Bell Helicopter Textron 47G–2A (Supplemental Type Certificate (STC) SH657NW)
Bell Helicopter Textron 47G–2A–1 (STC SH657NW)
Bell Helicopter Textron 47G–3B (STC SH657NW)
Bell Helicopter Textron 47G–3B–1 (TH–13T) (STC SH657NW)
Bell Helicopter Textron 47G–3B–2 (STC SH657NW)
Bell Helicopter Textron 47G–3B–2A (STC SH657NW)
Bell Helicopter Textron 47G–4 (STC SH657NW)
Bell Helicopter Textron 47G–4A (STC SH657NW)
Bell Helicopter Textron 47G–5 (STC SH657NW)
Bell Helicopter Textron 47G–5A (STC SH657NW)
Eurocopter Deutchland BO–105C
Eurocopter Deutchland BO–105C (STC SH218NW–D)
Eurocopter Deutchland BO–105S
Eurocopter France AS355E
Eurocopter France AS355F
Eurocopter France AS355F1
Eurocopter France AS355F2
FH–1100 Manufacturing Corp FH–1100
Hiller Aviation UH–12D (Army UH–23D) (STC SH177WE)
MDHI 369D
MDHI 369E
MDHI 369HM
MDHI 369HS
MDHI 369HE
Rogerson Hiller Corporation UH–12E (STC SH178WE)
Rogerson Hiller Corporation UH–12E–L (STC SH178WE)
SIAI Marchetti s.r.l. SF600
Unsafe Condition
Related Information
(d) This AD results from an unacceptable
rate of uncontained 1st stage turbine wheel
failures. We are issuing this AD to minimize
the risk of uncontained 1st stage turbine
wheel fragments from causing damage to the
aircraft or damage to the second engine on
twin-engine installations, which could lead
to loss of control and loss of the aircraft.
Compliance
(e) You are responsible for having the
actions required by this AD performed at the
next time the gas producer turbine rotor is
disassembled for any reason, or within 1,750
hours time-since-last-overhaul, time-sincenew, time-since-last-heavy-maintenance, or
time-since-last-hot section inspection after
the effective date of this AD, whichever
occurs first, but no later than October 31,
2011, unless already done.
Required Actions
(f) Install a turbine energy absorbing ring,
RRC P/N 23035175, or an equivalent FAAapproved turbine energy absorbing ring, in
the plane of the 1st stage turbine wheel,
using paragraphs 1.M., 2.A., and 2.B. of
Rolls-Royce Corporation Alert Commercial
Engine Bulletin No. CEB–A–1255, Revision
4, dated September 29, 2004, to do the
installation.
Alternative Methods of Compliance
(g) The Manager, Chicago Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
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16:58 May 17, 2005
Jkt 205001
DEPARTMENT OF TRANSPORTATION
(h) None.
Material Incorporated by Reference
(i) You must use Rolls-Royce Corporation
Alert Commercial Engine Bulletin No. CEB–
A–1255, Revision 4, dated September 29,
2004, to perform the actions required by this
AD. The Director of the Federal Register
approved the incorporation by reference of
this service bulletin in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. Contact
Rolls-Royce Corporation, P.O. Box 420,
Indianapolis, IN 46206–0420; telephone (317)
230–2712; fax (317) 230–3381 for the service
information identified in this AD for a copy
of this service information. You may review
copies at the Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building, Room
PL–401, Washington, DC 20590–001, on the
internet at https://dms.dot.gov, or 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Burlington, Massachusetts, on
May 10, 2005.
Robert Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–9660 Filed 5–17–05; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2004–19410; Airspace
Docket No. 04–ANM–09]
RIN 2120–AA66
Revision of Federal Airways V–2, V–
257 and V–343; MT
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action revises three Very
High Frequency Omnidirectional Range
(VOR) Federal airways southeast of
Missoula, MT (V–2, V–257, and V–343).
These VOR Federal airways are being
revised due to the decommissioning of
the Drummond VOR. These changes
will enhance air safety, simplify
routings, and reduce controller
workload in Montana.
DATES: Effective 0901 UTC, September
1, 2005.
FOR FURTHER INFORMATION CONTACT: Ken
McElroy, Airspace and Rules, Office of
System Operations and Safety, Federal
Aviation Administration, 800
Independence Avenue, SW.,
Washington, DC 20591; telephone: (202)
267–8783.
SUPPLEMENTARY INFORMATION:
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]]>Agencies
[Federal Register Volume 70, Number 95 (Wednesday, May 18, 2005)]
[Rules and Regulations]
[Pages 28420-28423]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-9660]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19648; Directorate Identifier 2004-NE-31-AD;
Amendment 39-14090; AD 2005-10-13]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation (Formerly
Allison Engine Company) 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -
C20F, -C20J, -C20S, and -C20W Turboprop and Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rolls-
[[Page 28421]]
Royce Corporation (RRC) (formerly Allison Engine Company) 250-B17B, -
B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W
turboprop and turboshaft engines that do not have turbine energy
absorbing ring, RRC part number (P/N) 23035175, or an equivalent FAA-
approved serviceable turbine energy absorbing ring, installed. This AD
requires installation of a turbine energy absorbing ring in the plane
of the 1st stage turbine wheel. This AD results from an unacceptable
rate of uncontained 1st stage turbine wheel failures. We are issuing
this AD to minimize the risk of uncontained 1st stage turbine wheel
fragments from causing damage to the aircraft or damage to the second
engine on twin-engine installations, which could lead to loss of
control and loss of the aircraft.
DATES: This AD becomes effective June 22, 2005. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of June 22, 2005.
ADDRESSES: Contact Rolls-Royce Corporation, P.O. Box 420, Indianapolis,
IN 46206-0420; telephone (317) 230-2712; fax (317) 230-3381 for the
service information identified in this AD.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Melissa T. Bradley, Aerospace
Engineer, Chicago Aircraft Certification Office, FAA, 2300 East Devon
Avenue, Des Plaines, IL 60018-4696; telephone (847) 294-8110; fax (847)
294-7834.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to Rolls-Royce Corporation (RRC) (formerly Allison Engine Company) 250-
B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W
turboprop and turboshaft engines that do not have turbine energy
absorbing ring, RRC P/N 23035175, installed. We published the proposed
AD in the Federal Register on November 22, 2004 (69 FR 67867). That
action proposed to require installation of a turbine energy absorbing
ring in the plane of the 1st stage turbine wheel. That action also
proposed to require installation of 1st stage turbine nozzles, 2nd
stage turbine nozzles, and a gas producer support assembly, all
modified to allow for installation of the turbine energy absorbing
ring.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the DMS Docket Offices
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Office (telephone (800) 647-5227) is located on
the plaza level of the Department of Transportation Nassif Building at
the street address stated in ADDRESSES. Comments will be available in
the AD docket shortly after the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Add Helicopters to the Applicability of the AD
One commenter requests that we add to the applicability of the AD,
the Rogerson Hiller Corporation UH-12E helicopter, modified by
Supplemental Type Certificate (STC) SH178WE, in addition to including
STC SH657NW applicability. The commenter states that the proposed AD
did not reference all known installations of the affected engines.
We agree that all known installations of the affected engines
should have been listed. We have corrected the applicability, by adding
helicopters that are listed under STC SH177WE, STC SH178WE, STC
SH218NW-D, and STC SH657NW.
Request the FAA Require RRC To Supply All Parts Needed at No Cost
One commenter requests that we require RRC to supply all parts
needed to comply with the AD, at no cost to the operator. The commenter
is concerned about the financial impact the AD will have on operators.
We understand the commenter's concern over parts costs, however, we
do not have the authority to control or eliminate parts costs.
Request To Change the Compliance
One commenter requests that the compliance be done at the next
1,750-hour hot section inspection or turbine overhaul.
We do not agree. Our existing compliance time is based on
minimizing the risk of failure. If compliance time is extended to the
next hot section inspection or turbine overhaul for the entire
population of engines, then the associated fleet risk would increase to
an unacceptable level.
Request To Eliminate the Final Compliance Date
One commenter requests we eliminate the final compliance date of
October 31, 2011. The commenter has a concern that operators who have
recently overhauled the turbine, will not accumulate the 1,750 hours
before the final compliance date.
We do not agree. We have a final compliance date in the AD to
ensure compliance within a reasonable period of time (over six years)
for engines that may not accumulate 1,750 hours, or may not be
disassembled for any reason before the final compliance date. Risk of
failure increases with each additional year the engine does not comply.
Request To Include FAA-PMA P/Ns
One commenter requests that the AD include the FAA-PMA P/N for the
turbine energy absorbing ring manufactured by EXTEX, as well as all
other equivalent FAA-PMA P/Ns for turbine energy absorbing rings. The
commenter's concern is that the proposed AD states that the AD applies
to engines that do not have turbine energy absorbing ring, P/N
23035175, installed. The commenter states that this wording implies
that the only method of compliance is by installing the turbine energy
absorbing ring manufactured by the Type Certificate holder, RRC.
Equivalent FAA-PMA turbine energy absorbing rings are also available to
install.
We partially agree. We have changed the AD to identify the part
number referenced, as an RRC part number, and, to take into account
that there are equivalent parts available.
Request To Remove Paragraphs (f) and (g) From the Compliance
One commenter requests that we remove paragraphs (f) and (g) from
the compliance. The commenter states that these paragraphs are
unnecessary and restrictive. AD compliance paragraph (f) states to use
paragraph 2. of RRC Alert Commercial Engine Bulletin (CEB) No. CEB-A-
1254, Revision 3, dated May 21, 2004, to modify the gas producer
support. This paragraph would prevent the use of currently available
and widely used FAA-Designated Engineering Representative (DER)-
approved methods to modify the gas producer support, for installing the
turbine energy absorbing ring. An operator would have to request
numerous Alternative Methods of Compliance (AMOCs) because of the
overly restrictive wording.
The commenter also states that AD compliance paragraph (g)
specifies to
[[Page 28422]]
use paragraph 2. of RRC Alert CEB No. CEB-A-1253, Revision 4, dated May
21, 2004, to modify and install the 1st stage turbine nozzle and 2nd
stage turbine nozzle. This CEB Revision 4 only lists the latest P/N for
the 1st stage turbine nozzle. Since the issuance of the original
version of this CEB on June 1, 1988, several P/Ns of 1st stage turbine
nozzles exist which are the required configuration to allow
installation of a turbine energy absorbing ring. These earlier 1st
stage turbine nozzles are still in wide circulation and are perfectly
suitable for use. AD compliance paragraph (g) would prevent the use of
these earlier P/N 1st stage turbine nozzles without first receiving
AMOC approval.
The commenter concludes by stating that installing the turbine
energy absorbing ring without modifying the gas producer support and
nozzles is physically impossible. Paragraph 1.M of RRC CEB No. CEB-A-
1255, Revision 4, dated September 29, 2004, lists CEB No. CEB-A-1253
and No. CEB-A-1254 as prerequisites to CEB No. CEB-A-1255, without the
overly restrictive use of specific revision numbers and dates. That
same prerequisite paragraph also includes the necessary words ``or
equivalent'' to these two CEBs.
We agree. We have replaced paragraphs (f), (g), and (h) of this AD
with the following single paragraph: ``(f) Install a turbine energy
absorbing ring, RRC P/N 23035175, or an equivalent FAA-approved
serviceable turbine energy absorbing ring, in the plane of the 1st
stage turbine wheel, using paragraphs 1.M., 2.A., and 2.B. of Rolls-
Royce Corporation Alert Commercial Engine Bulletin No. CEB-A-1255,
Revision 4, dated September 29, 2004, to do the installation.''
Request To Reevaluate the Basis for the AD
One commenter requests we reevaluate the basis for the AD. The
request is based on field experience of an operator who has maintained
the 250-C20 series engines for over 25 years, and is concerned with the
financial impact on operators. The commenter has never seen a 1st stage
turbine wheel failure and questions the validity of RRC's analysis.
We do not agree. We reviewed the analysis and associated risk and
find it necessary to issue this AD.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 13,299 RRC 250-B17B, -B17C, -B17D, -B17E, -C20, -
C20B, -C20F, -C20J, -C20S, and -C20W turboprop and turboshaft engines
of the affected design in the worldwide fleet. We estimate that 5,000
engines installed on helicopters of U.S. registry require the
installation of a turbine energy absorbing ring. Of those 5,000
engines, we also estimate that 4,000 engines require installation of a
gas producer support assembly, 1st stage turbine nozzle, and 2nd stage
turbine nozzle. About 16 work hours per engine are needed to install
the turbine energy absorbing ring, 35 work hours to install the gas
producer support assembly, and 20 work hours to install the 1st stage
turbine nozzle, and 2nd stage turbine nozzle. The average labor rate is
$65 per work hour. Required turbine energy absorbing rings cost about
$10,765 per engine. Required gas producer support assemblies cost about
$2,500 per engine. Required 1st stage turbine nozzles and 2nd stage
turbine nozzles cost about $1,000 per engine. Based on these figures,
we estimate the total cost of the AD to U.S. operators to be
$87,325,000.
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); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration 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:
2005-10-13 Rolls-Royce Corporation (formerly Allison Engine
Company): Amendment 39-14090. Docket No. FAA-2004-19648; Directorate
Identifier. 2004-NE-31-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 22,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce Corporation (RRC) (formerly
Allison Engine Company) 250-B17B, B17C, -B17D, -B17E, -C20, -C20B, -
C20F, -C20J, -C20S, and -C20W turboprop and turboshaft engines that
do not have turbine energy absorbing ring, RRC part number (P/N)
23035175, or an equivalent FAA-approved serviceable turbine energy
absorbing ring, installed. These engines are installed on, but not
limited to, the following aircraft:
[[Page 28423]]
Agusta A109
Agusta A109A
Agusta A109A II
B-N Group BN-2T
Bell 206A
Bell 206B
Bell 206L
Bell Helicopter Textron 47G-2A (Supplemental Type Certificate (STC)
SH657NW)
Bell Helicopter Textron 47G-2A-1 (STC SH657NW)
Bell Helicopter Textron 47G-3B (STC SH657NW)
Bell Helicopter Textron 47G-3B-1 (TH-13T) (STC SH657NW)
Bell Helicopter Textron 47G-3B-2 (STC SH657NW)
Bell Helicopter Textron 47G-3B-2A (STC SH657NW)
Bell Helicopter Textron 47G-4 (STC SH657NW)
Bell Helicopter Textron 47G-4A (STC SH657NW)
Bell Helicopter Textron 47G-5 (STC SH657NW)
Bell Helicopter Textron 47G-5A (STC SH657NW)
Eurocopter Deutchland BO-105C
Eurocopter Deutchland BO-105C (STC SH218NW-D)
Eurocopter Deutchland BO-105S
Eurocopter France AS355E
Eurocopter France AS355F
Eurocopter France AS355F1
Eurocopter France AS355F2
FH-1100 Manufacturing Corp FH-1100
Hiller Aviation UH-12D (Army UH-23D) (STC SH177WE)
MDHI 369D
MDHI 369E
MDHI 369HM
MDHI 369HS
MDHI 369HE
Rogerson Hiller Corporation UH-12E (STC SH178WE)
Rogerson Hiller Corporation UH-12E-L (STC SH178WE)
SIAI Marchetti s.r.l. SF600
Unsafe Condition
(d) This AD results from an unacceptable rate of uncontained 1st
stage turbine wheel failures. We are issuing this AD to minimize the
risk of uncontained 1st stage turbine wheel fragments from causing
damage to the aircraft or damage to the second engine on twin-engine
installations, which could lead to loss of control and loss of the
aircraft.
Compliance
(e) You are responsible for having the actions required by this
AD performed at the next time the gas producer turbine rotor is
disassembled for any reason, or within 1,750 hours time-since-last-
overhaul, time-since-new, time-since-last-heavy-maintenance, or
time-since-last-hot section inspection after the effective date of
this AD, whichever occurs first, but no later than October 31, 2011,
unless already done.
Required Actions
(f) Install a turbine energy absorbing ring, RRC P/N 23035175,
or an equivalent FAA-approved turbine energy absorbing ring, in the
plane of the 1st stage turbine wheel, using paragraphs 1.M., 2.A.,
and 2.B. of Rolls-Royce Corporation Alert Commercial Engine Bulletin
No. CEB-A-1255, Revision 4, dated September 29, 2004, to do the
installation.
Alternative Methods of Compliance
(g) The Manager, Chicago Aircraft Certification Office, has the
authority to approve alternative methods of compliance for this AD
if requested using the procedures found in 14 CFR 39.19.
Related Information
(h) None.
Material Incorporated by Reference
(i) You must use Rolls-Royce Corporation Alert Commercial Engine
Bulletin No. CEB-A-1255, Revision 4, dated September 29, 2004, to
perform the actions required by this AD. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN
46206-0420; telephone (317) 230-2712; fax (317) 230-3381 for the
service information identified in this AD for a copy of this service
information. You may review copies at the Docket Management
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC 20590-001, on the
internet at https://dms.dot.gov, or 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/code_of_federal_regulations/
ibr_locations.html.
Issued in Burlington, Massachusetts, on May 10, 2005.
Robert Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-9660 Filed 5-17-05; 8:45 am]
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