[Federal Register: March 31, 2005 (Volume 70, Number 61)]
[Rules and Regulations]
[Page 16406-16407]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31mr05-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18024; Directorate Identifier 2003-NE-39-AD;
Amendment 39-14034; AD 2005-07-10]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce (1971) Limited, Bristol
Engine Division Model Viper Mk.601-22 Turbojet Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls-Royce (1971) Limited, Bristol Engine Division (RR) model
Viper Mk.601-22 turbojet engines. That AD currently requires reducing
the life of certain 1st stage turbine rotor blades from 7,000 hours
time-in-service (TIS) to 4,600 hours TIS, and provides a drawdown
schedule for blades that have already exceeded the new reduced life
limit. This AD requires the same actions but changes certain compliance
times to be in agreement with RR Alert Service Bulletin (ASB) No. 72-
A184, dated January 2001. This AD results from comments received on AD
2004-13-03, that the AD is unnecessarily more restrictive than the
requirements in the associated RR ASB No. 72-A184. We are issuing this
AD to prevent multiple failures of 1st stage turbine rotor blades that
could result in a dual-engine shutdown.
DATES: This AD becomes effective May 5, 2005.
ADDRESSES: You can get the service information identified in this
proposed AD from Rolls-Royce Limited, Bristol Engines Division,
Technical Publications Department CLS-4, P.O. Box 3, Filton, Bristol,
BS34 7QE England; telephone 117-979-1234, fax 117-979-7575.
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: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to Rolls-Royce (1971) Limited, Bristol Engine Division (RR) model Viper
Mk.601-22 turbojet engines. We published the proposed AD in the Federal
Register on October 29, 2004 (69 FR 63104). That action proposed to
require reducing the life of certain 1st stage turbine rotor blades
from 7,000 hours TIS to 4,600 hours TIS, provide a drawdown schedule
for blades that have already exceeded the new reduced life limit, and
change certain compliance times to be in agreement with RR ASB No. 72-
A184, dated January 2001.
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 received no comments on the proposal or on
the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
We estimate that 84 RR model Viper Mk.601-22 turbojet engines
installed on airplanes of U.S. registry will be affected by this AD. We
estimate that no additional labor cost will be incurred to replace 1st
stage turbine rotor blades when done at time of engine overhaul. A
replacement set 1st stage turbine rotor blades costs about $166,987.
Based on these figures, we estimate the total cost of the AD to U.S.
operators to be $14,026,950.
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.
[[Page 16407]]
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, 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 removing Amendment 39-13684 69 FR
34563, June 22, 2004, and by adding a new airworthiness directive,
Amendment 39-14034, to read as follows:
2005-07-10 Rolls-Royce (1971) Limited, Bristol Engine Division:
Amendment 39-14034 Docket No. FAA-2004-18024; Directorate Identifier
2003-NE-39-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 5,
2005.
Affected ADs
(b) This AD supersedes AD 2004-13-03.
Applicability
(c) This AD applies to Rolls-Royce (1971) Limited, Bristol
Engine Division (RR) Model Viper Mk.601-22 turbojet engines. These
engines are installed on, but not limited to, Raytheon HS.125 Series
600 and BH.125 Series 600 airplanes.
Unsafe Condition
(d) This AD results from comments received on AD 2004-13-03,
that the AD is unnecessarily more restrictive than the requirements
in the associated RR Alert Service Bulletin (ASB) No. 72-A184. We
are issuing this AD to prevent multiple failures of 1st stage
turbine rotor blades that could result in a dual-engine shutdown.
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.
New Reduced Life Limit
(f) Change the RR Time Limits Manual life limit for the 1st
stage turbine rotor blades, part numbers (P/Ns) V926000, V926293,
and V926319, from 7,000 hours time-in-service (TIS) to 4,600 hours
TIS.
(g) Limit the number of installed engines with 1st stage turbine
rotor blades that exceed 4,600 hours TIS on the effective date of
this AD as specified in the following Table 1:
Table 1.--Installed Engines
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On the effective date of this AD, if: Then:
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(1) Both engines installed on the Replace the 1st stage turbine
airplane have 1st stage turbine rotor rotor blades in the engine
blades that exceed 5,800 hours TIS. that has the higher blade
life within 50 hours TIS or 6
weeks after the effective
date of this AD, whichever
occurs first.
(2) One engine installed on the airplane Replace the 1st stage turbine
has 1st stage turbine rotor blades that rotor blades in the engine
exceed 5,800 hours TIS, and the other that has the higher blade
engine has 1st stage turbine rotor life within 100 hours TIS or
blades that exceed 4,600 hours TIS. 4 months after the effective
date of this AD, whichever
occurs first.
(3) One engine installed on the airplane Replace the 1st stage turbine
has 1st stage turbine rotor blades that rotor blades in the engine
exceed 5,800 hours TIS, and the other that has the higher blade
engine has 1st stage turbine rotor life within 200 hours TIS or
blades with fewer than 4,600 hours TIS. 6 months after the effective
date of this AD, whichever
occurs first.
(4) One engine installed on the airplane Replace the 1st stage turbine
has 1st stage turbine rotor blades that rotor blades in the engine
exceed 4,600 hours TIS, but have fewer that has the higher blade
than 5,800 hours TIS, and the other life at 5,800 hours TIS or 6
engine has 1st stage turbine rotor months after the effective
blades with fewer than 4,600 hours TIS. date of this AD, whichever
occurs later.
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(h) No engine may operate with a blade life exceeding 5,800
hours TIS, applicable beginning 6 months from the effective date of
this AD.
(i) No engine may operate with a blade life exceeding 4,600
hours TIS, applicable beginning 3 years from the effective date of
this AD.
Installation of Engines After the Effective Date of This AD
(j) After the effective date of this AD, do not install any
engine that has 1st stage turbine rotor blades, P/Ns V926000,
V926293, or V926319, that exceed 4,600 hours TIS, except as allowed
in Table 1 of this AD.
Alternative Methods of Compliance
(k) The Manager, Engine 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.
Material Incorporated by Reference
(l) None.
Related Information
(m) Civil Aviation Authority airworthiness directive AD 004-01-
2001, dated January 2001, also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on March 25, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-6342 Filed 3-30-05; 8:45 am]
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