[Federal Register: March 29, 2005 (Volume 70, Number 59)]
[Proposed Rules]
[Page 15784-15786]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29mr05-27]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20742; Directorate Identifier 2005-NE-03-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation (Formerly
Allison Engine Company) 501-D22A, 501-D22C, and 501-D22G Turboprop
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for Rolls-Royce Corporation (RRC) (formerly Allison Engine Company)
501-D22A, 501-D22C, and 501-D22G turboprop engines. This proposed AD
would require a onetime inspection for proper metal hardness of certain
1st stage, 2nd stage, 3rd stage, and 4th stage turbine wheels. This
proposed AD results from a report of a turbine wheel found to be over
dimensional limits, caused by improper metal hardness. We are proposing
this AD to prevent uncontained turbine wheel failure, leading to damage
of the airplane and total loss of engine power.
DATES: We must receive any comments on this proposed AD by May 31,
2005.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You can get the service information identified in this proposed AD
from Rolls-Royce Corporation, P.O. Box 420, 2001 South Tibbs Avenue,
Indianapolis, IN 46206-0420; telephone (317) 230-2000; fax (317) 230-
4020.
You may examine the comments on this proposed AD in the AD docket
on the Internet at http://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Michael Downs, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des
Plaines, IL 60018; telephone (847) 294-7870; fax (847) 294-7834.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20742;
Directorate Identifier 2005-NE-03-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
[[Page 15785]]
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of the
DMS Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit http://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the proposal, 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.
Discussion
During the rebuild of an RRC 501 industrial engine's 1st stage
turbine wheel that had accumulated 31,000 hours time-in-service, the
assembled turbine blade lengths were found to be varying up to 0.012-
inch beyond the blade tip run-out limit. The shop inspector considered
the turbine wheel suspect and returned it to RRC for metallurgical
evaluation. That evaluation revealed that a portion of the turbine
wheel had an increased radius, over the maximum radius limit, and a
metal hardness below design requirements. RRC reviewed the forging
furnace records at the forging plant that heat-treated the turbine
wheel. The records showed that the temperature of the heat-treatment
solution was about 100 degrees Fahrenheit below the minimum required
temperature, for about two hours during the heat-treatment process. RRC
reports that the effects of the improper heat treatment are a reduction
in metal strength, lower tensile yield, and probability of metal creep,
stress rupture, and metal fatigue. The same forging plant heat-treated
RRC 501-D22A, 501-D22C, and 501-D22G turboprop engine 1st stage, 2nd
stage, 3rd stage, and 4th stage turbine wheels. Those turbine wheels
are suspect for improper metal hardness. This condition, if not
corrected, could result in uncontained turbine wheel failure, leading
to airplane damage and total loss of engine power.
Relevant Service Information
We have reviewed and approved the technical contents of Rolls-Royce
Commercial Engine Bulletins (CEBs) No. CEB-72-1138, No. CEB-72-4051,
and No. CEB-72-1584, (combined in one document) dated January 23, 2004.
These bulletins describe procedures for performing a onetime inspection
for proper metal hardness of certain 1st stage, 2nd stage, 3rd stage,
and 4th stage turbine wheels.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
a onetime inspection for proper metal hardness of certain 1st stage,
2nd stage, 3rd stage, and 4th stage turbine wheels. These inspections
would be done at the next shop visit of the engine or turbine module,
but not to exceed 7,400 cycles-since-new of any 1st stage, 2nd stage,
3rd stage, or 4th stage turbine wheel. The proposed AD would require
you to use the service information described previously to perform
these actions.
Costs of Compliance
There are about 150 RRC 501-D22A, 501-D22C, and 501-D22G turboprop
engines of the affected design in the worldwide fleet. We estimate that
150 engines installed on airplanes of U.S. registry would be affected
by this proposed AD. We also estimate that it would take about 0.5 work
hour per engine to perform the proposed actions, and that the average
labor rate is $65 per work hour. Required parts would cost about $1,495
per turbine wheel. The manufacturer has stated that it may provide
replacement parts for turbine wheels that do not meet inspection
criteria, at no cost to operators. Based on these figures, we estimate
the total cost of the proposed AD to U.S. operators to be $229,125.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Would 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 proposal 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, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 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.
[[Page 15786]]
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
Rolls-Royce Corporation (formerly Allison Engine Company): Docket
No. FAA-2005-20742; Directorate Identifier 2005-NE-03-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by May 31,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce Corporation (RRC) (formerly
Allison Engine Company) 501-D22A, 501-D22C, and 501-D22G turboprop
engines with the turbine wheels listed in the following Table 1,
installed.
Table 1.--Affected Turbine Wheels
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Turbine wheel part No. Turbine wheel Serial Nos.
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6875431.................................... 1st Stage.................................. KK50152 through
KK50199.
6845592.................................... 2nd Stage.................................. KK40998 through
KK41057.
6845593.................................... 3rd Stage.................................. KK36452 through
KK36461, and KK36492
through KK36532.
6870434.................................... 4th Stage.................................. KK40320 through
KK40393, and KK40485
through KK40535.
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These engines are installed on, but not limited to, Commercial
Hercules L-100-20, L-100-30, L-382B, L-382E, and L-382G, Airbus
Super Guppy-201, and Super Convair CV-580A, and CV5800 airplanes.
Unsafe Condition
(d) This AD results from a report of a turbine wheel found to be
over dimensional limits, caused by improper metal hardness. We are
issuing this AD to prevent uncontained turbine wheel failure,
leading to damage of the airplane and total loss of engine power.
Compliance
(e) You are responsible for having the actions required by this
AD performed at the next shop visit of the engine or turbine module,
but not to exceed 7,400 cycles-since-new of any 1st stage, 2nd
stage, 3rd stage, or 4th stage turbine wheel, unless the actions
have already been done.
Onetime Inspection for Proper Metal Hardness
(f) Perform a onetime inspection for proper metal hardness of
1st stage, 2nd stage, 3rd stage, and 4th stage turbine wheels. Use
paragraphs 2.B. and 2.F. of RRC Commercial Engine Bulletins (CEBs)
No. CEB-72-1138, No. CEB-72-4051, and No. CEB-72-1584, (combined in
one document) dated January 23, 2004.
(g) Remove from service any turbine wheel that does not pass
inspection, using paragraph 2.C. of RRC CEBs No. CEB-72-1138, No.
CEB-72-4051, and No. CEB-72-1584, (combined in one document) dated
January 23, 2004.
(h) Mark the letters, HC, after the serial number on any turbine
wheel that passes inspection, using the method described in
paragraph 2.D. of RRC CEBs No. CEB-72-1138, No. CEB-72-4051, and No.
CEB-72-1584, (combined in one document) dated January 23, 2004.
Reporting Requirements
(i) Report findings of inspections using the procedures
specified in paragraph 2.E. of RRC CEBs No. CEB-72-1138, No. CEB-72-
4051, and No. CEB-72-1584, (combined in one document) dated January
23, 2004. The Office of Management and Budget (OMB) has approved the
reporting requirements specified in paragraph 2.E. of RRC CEBs No.
CEB-72-1138, No. CEB-72-4051, and No. CEB-72-1584, (combined in one
document) dated January 23, 2004, and assigned OMB control number
2120-0056.
Definition
(j) For the purpose of this AD, a serviceable turbine wheel is:
(1) A turbine wheel that has a serial number not listed in this
AD; and
(2) A turbine wheel that has a serial number listed in this AD
that passed the inspection specified in paragraph (f) of this AD.
Alternative Methods of Compliance
(k) 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
(1) None.
Issued in Burlington, Massachusetts, on March 22, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-6108 Filed 3-28-05; 8:45 am]
BILLING CODE 4910-13-P