66-04-01 GENERAL ELECTRIC: Amdt. 39-548 Part 39 Federal Register February 5, 1966. Applies to Models CJ805-3, -3A, -3B, -23, -23B, and -23C Turbojet Engines.
Compliance required as indicated.
To prevent the failure of thrust reverser, accomplish the following:
(a) Remove from service second stage turbine discs with less than 7,000 cycles on the effective date of this AD before the accumulation of 7,200 cycles.
(b) Remove from service second stage turbine discs with 7,000 or more cycles on the effective date of this AD within the next 200 cycles.
(c) For the purpose of this AD, the number of cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, takeoff operation, landing, and engine shutdown. The number of cycles may be determined by actual count or, subject to acceptance by the assigned FAA maintenance inspector, may be calculated by dividing each second stage turbine disc's hours time in service by theoperator's fleet average time per flight (involving an engine operating sequency consisting of engine starting, takeoff operation, landing, and engine shutdown) for airplanes equipped with General Electric CJ805 engines.
(d) The disc life specified in this AD may be extended to 10,000 cycles provided the discs meet the criteria outlined in paragraphs 1.k and 2 of General Electric Service Bulletin (880) 72-263 or (990) 72-272.
This amendment is effective February 7, 1968.
(General Electric telegram to CJ805 operators dated December 1, 1965, pertains to this subject.)
This directive effective February 3, 1966.