Airworthiness Directives; Rolls-Royce (1971) Limited, Bristol Engine Division Model Viper Mk.601-22 Turbojet Engines

[Federal Register Volume 70, Number 61 (Thursday, March 31, 2005)]
[Rules and Regulations]
[Pages 16406-16407]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-6342]


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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
------------------------------------------------------------------------
  On the effective date of this AD, if:                Then:
------------------------------------------------------------------------
(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.
------------------------------------------------------------------------

    (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]
BILLING CODE 4910-13-P

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