Airworthiness directives › 2005-07-10
AD 2005-07-10 Airworthiness Directives; Rolls-Royce (1971) Limited, Bristol Engine Division Model Viper Mk.601-22 Turbojet Engines
Models named: Viper Mk.601-22 turbojet. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
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.
Compliance
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 airplane have 1st stage turbine rotor blades that exceed 5,800 hours TIS Replace the 1st stage turbine rotor blades in the engine 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 has 1st stage turbine rotor blades that exceed 5,800 hours TIS, and the other engine has 1st stage turbine rotor blades that exceed 4,600 hours TIS Replace the 1st stage turbine rotor blades in the engine that has the higher blade life within 100 hours TIS or 4 months after the effective date of this AD, whichever occurs first. (3) One engine installed on the airplane has 1st stage turbine rotor blades that exceed 5,800 hours TIS, and the other engine has 1st stage turbine rotor blades with fewer than 4,600 hours TIS Replace the 1st stage turbine rotor blades in the engine that has the higher blade life within 200 hours TIS or 6 months after the effective date of this AD, whichever occurs first. (4) One engine installed on the airplane has 1st stage turbine rotor blades that exceed 4,600 hours TIS, but have fewer than 5,800 hours TIS, and the other engine has 1st stage turbine rotor blades with fewer than 4,600 hours TIS Replace the 1st stage turbine rotor blades in the engine that has the higher blade life at 5,800 hours TIS or 6 months after the effective 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
Unsafe condition
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.
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1