[Federal Register Volume 70, Number 95 (Wednesday, May 18, 2005)]
[Rules and Regulations]
[Pages 28420-28423]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-9660]


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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 http://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 http://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: http://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