The General Electric CF34 is a civilian high-bypass turbofan developed by GE Aviation from its TF34 military engine. The CF34 is used on a number of business and regional jets , including the Bombardier CRJ series, the Embraer E-Jets , and Comac ARJ21 .

The CF34-8C5 is an advanced 14,500 pound thrust class turbofan propulsion system that powers the 90-passenger Bombardier CRJ900 Series airliner, 100-passenger Bombardier CRJ1000 Series airliner and Bombardier Challenger 890 business aircraft. The engine features 50% more thrust, higher thrust to weight ratio,

The CF34-8C powers the CRJ series of regional jets. The CF34-8 engine provides the level of reliability and performance that has earned the CF34 family of engines a global reputation for exceptional service.

The wildly successful General Electric CF34 turbine is a mid-range, high-bypass-ratio fan targeting the large business jet and regional jet markets. The CF34 has been scaled from 8,500- to 18,500-lbst, compet-ing with the Rolls-Royce AE3007 and RB282, and P&WC PW300 at its lower end and the Rolls-Royce BR700 and PowerJet SaM146 at the upper end.

CF34-8C ENGINE MANUAL Dated: 03/04/2021 ESM 05-11-05 STATIC STRUCTURES - LIFE LIMITS * * * FOR ALL -8C MODELS TASK 05-11-05-200-801 1. General. A. This section contains the FAA-approved life limits for static structure parts. B. The life limit is determined by the total number of flight cycles. Refer to TASK

It replaces the CF34-8C1 initially delivered on features 50% more thrust, higher thrust to weight ratio, over 200 CRJ700 aircraft.

CF34-8C (CF34-8C5, CF34-8C5A1 & CF34-8C5B1) engines are manufactured by General Electric for Bombardier CRJ-500, CRJ-700, CRJ-900 & CRJ-1000 aircraft which were produced from 1999 to 2021. Thrust rating ranges from 13,800 lbs. to 14,500 lbs.

CF34-8C S/B 72-0137 have been required to undergo ECI of pin holes every 1,500 to 3,000 cycles. (4)Improvement: The fan blade bushing repair extends the allowable fan blade operating limits by an additional 28,000 engine cycles from the time of the bushing repair. ECI of the fan blade pinholes per CF34-8C S/B 72-0137 is no longer

CF34-8C/E FADEC Recommended First Overhaul Actions Reasons to overhaul FADEC •CF34-8C in service since 2001 and CF34-8E since 2004 •Continued on wing reliability is at risk after 13,000 flight cycles •Stabilizes and increases reliability Benefits of base overhaul

The CF34-8C1/-8C5 Turbofan Technical Manual Index has been reformatted as follows: Engine Manuals and Supporting Manuals - Section 1 – EM (Engine Manuals) Section 2 – Supplementary Support Manuals