免费精品综合导航👅_GAY取精潮喷10次龟责到哭_.手.动.输.入.网.址.联.系.客.服.人.员.lanan_shell
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 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：庞巴迪挑战者605机组操作手册 CL605-POWER_PLANT
