DESCRIPTION
General 19−10−1
Flat-Rated Thrust 19−10−1
Engine Construction 19−10−1
Description 19−10−1
Engine Fuel System 19−10−3
Description 19−10−3
Components and Operation 19−10−3
Automatic Performance Reserve System 19−10−5
Description 19−10−5
Operation 19−10−6
Engine Oil System 19−10−6
Description 19−10−6
Components and Operation 19−10−6
Engine Bleed Air System 19−10−11
Description 19−10−11
Components and Operation 19−10−11
Engine Starting System 19−10−12
Description 19−10−12
Components and Operation 19−10−13
Ignition System 19−10−15
Description 19−10−15
Operation 19−10−15
Vibration Monitoring System 19−10−16
Description 19−10−16
Operation 19−10−17
Thrust Levers 19−10−17
Description 19−10−17
Operation 19−10−17
Thrust Reverser System 19−10−19
Description 19−10−19
Operation 19−10−19
Controls and Indicators 19−10−23
Engine Starting 19−10−23
Engine Speed Controls 19−10−24
POWER PLANT
Table of Contents
Vol. 2 19−00−1
Oct 05/06
CHAPTER 19 - POWER PLANT
19−00−1
CL−605 Flight Crew Operating Manual
PSP 605−6
TABLE OF CONTENTS
Page
TABLE OF CONTENTS
DESCRIPTION
Thrust Levers 19−10−25
Reverse Thrust 19−10−26
Oil System 19−10−26
EICAS Page 19−10−27
EICAS Messages 19−10−31
SUMMARY
Power Supply and Circuit Breaker Summary 19−20−1
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 19−10−1 Flow Distribution 19−10−2
Figure 19−10−2 Engine Fuel System − Schematic 19−10−4
Figure 19−10−3 ENGINE CONTROL Panel 19−10−5
Figure 19−10−4 ENGINE CONTROL Panel 19−10−6
Figure 19−10−5 Oil System Schematic 19−10−8
Figure 19−10−6 Oil Replenishment System 19−10−10
Figure 19−10−7 Engine Bleed Air System − Schematic 19−10−12
Figure 19−10−8 Starting System − Schematic 19−10−13
Figure 19−10−9 Engine Start/Ignition Panel 19−10−14
Figure 19−10−10 Ignition System 19−10−16
Figure 19−10−11 ENGINE CONTROL Panel 19−10−17
Figure 19−10−12 Thrust Levers 19−10−19
Figure 19−10−13 Thrust Reverser Operation 19−10−21
Figure 19−10−14 GND SPOILERS/THRUST REVERSER Panel 19−10−22
Figure 19−10−15 Engine Start/Ignition Panel 19−10−23
Figure 19−10−16 ENGINE CONTROL Panel 19−10−24
Figure 19−10−17 Thrust Levers 19−10−25
Figure 19−10−18 GND SPOILERS/THRUST REVERSER Panel 19−10−26
Figure 19−10−19 Impending Bypass and Chip Detector Annunciators (JB5) 19−10−26
Figure 19−10−20 N1 Indications 19−10−27
Figure 19−10−21 ITT Indications 19−10−28
Figure 19−10−22 N2 Indications 19−10−29
Figure 19−10−23 Engine Secondary Indications 19−10−30
POWER PLANT
Table of Contents
Vol. 2 19−00−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
Page
GENERAL
The Challenger 605 is equipped with two General Electric CF34-3B high-bypass ratio turbofan
engines.
The dual-assembly engine consists of a fan rotor (N1) and a compressor rotor (N2). The N1 rotor is
comprised of a single-stage fan connected through a shaft to a four-stage low-pressure turbine. The
N2 rotor is a 14-stage axial flow compressor connected through a shaft to a two-stage high-pressure
turbine. The accessory gearbox is mechanically driven by the N2 compressor.
Normal takeoff thrust rating is 8,729 pounds per engine. During engine-out operation, the automatic
performance reserve (APR) system increases thrust on the operable engine to 9,220 pounds.
FLAT-RATED THRUST
Outside air temperature and pressure altitude are determining factors in achieving takeoff and APR
power. Increases in ambient temperature or pressure altitude adversely affect the engine’s ability to
　
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