国内精品♨️_pp网名大全_.手.动.输.入.网.址.联.系.客.服.人.员.lanan_shell
OPERATING MANUAL 2A-73-00 PRODUCTION AIRCRAFT SYSTEMS Page 4 May 31/01 Revision 4 HP Fuel Cock Positions Figure 2 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A-73-00 Page 5 May 31/01 Revision 4 OPERATING MANUAL THIS PAGE IS INTENTIONALLY LEFT BLANK. 2A-73-00 PRODUCTION AIRCRAFT SYSTEMS Page 6 May 31/01 Engine Fuel System Controls and Indications Figure 3 OPERATING MANUAL 2A-73-00 Page 7 / 8 May 31/01 ENGINE IGNITION 2A-74-10: Engine Ignition System 1. General: A. Description: The ignition system, together with the cranking system, starts the engine on the ground and independently in flight (to re-start the engine). The function of the ignition system is to supply ignition to the fuel and air mixture in the discharge of a series of sparks across the electrodes of the igniter plugs (the igniters are in combustion liners No. 4 and No. 8 in each engine). Combustion then passes between each liner through interconnectors to complete the combustion cycle. The aircraft electrical system supplies 28V DC to the high-energy ignition units, control is by the start master switch and the individual start selector switches. B. Operation: During the start sequence (MASTER START and ENG START switchlights to the ON position), the engine’s start relay energizes to supply 28V DC power from the Essential DC bus to energize the respective ignition relay. The ignition relay then closes to supply 28V DC bus to the ignition unit(s). NOTE: On aircraft SN 1000 thru 1143 with ASC 151 and 1144 thru subsequent, only one ignition unit and igniter plug operate during ground starting, for example: • Left Engine — No. 1 Ignition Unit • Right Engine — No. 2 Ignition Unit • With the ignition unit(s) energized, a green IGN annunciation appears next to the engine’s HP RPM display. As engine RPM reaches approximately 38 to 45%, the starter’s centrifugal cutout switch opens to de-energize the start and ignition relays. The ignition unit(s) de-energize and the IGN annunciation clears. Lifting the switch guard and pressing an AIR START IGN switchlight supplies 28V DC directly from the DC bus to the corresponding ignition units. With an AIR START IGN switchlight in on, the switchlight’s blue ON caption illuminates and the green IGN annunciation appears next to the engine’s HP RPM display on EICAS. When the ignition units are receiving power through the AIR START IGN switchlight they operate continuously. C. Subsystems, Units and Components: (See Figure 2.) The Engine Ignition system is composed of the following units and components: • Ignition Relay • High Energy Transistorized Ignition Units (2 Per Engine) • High Tension Leads (2 Per Engine) OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A-74-00 Page 1 May 31/01 Revision 4 • Igniter Plugs (2 Per Engine) 2. Description of Subsystems, Units and Components: A. Ignition Relay: During ground starting, the ignition relay is energized when the starter relay and pneumatic starter are energized. When energized, the relay provides power from the Essential DC bus through the #1 IGN and #2 IGN circuit breakers to the high energy ignition units. Each ignition unit is provided with DC power from a separate circuit breaker. B. High Energy Transistorized Ignition Units: The ignition units change a low voltage DC electrical supply into a High Energy (HE.) output. They can be energized independently of the engine starting system if a re-start in flight is required. The components of the unit are housed in a light alloy case. This case also carries a Light Duty (LD) receptacle to connect it to the aircraft electrical supply and a HE receptacle to connect it to the igniters. C. High Tension Leads: A high tension lead connects the ignition unit output to its igniter plug. D. High Energy Igniter Plugs: The engine has two HE igniter plugs, installed in the diffuser case at numbers 4 and 8 combustion liner positions. The HE ignition unit supplies power to the terminal connector of the plug. This electrical energy causes a high intensity spark across the electrodes of each plug and supplies ignition to the fuel and air mixture in the combustion chamber. 3. Controls and Indications: (See Figure 1.) NOTE: A description of the Engine Instruments and Crew Alerting System (EICAS) can be found in Section 5 of Honeywell’s SPZ-8000 (or SPZ-8400) Digital Automatic Flight Control System Pilot’s Manual for the www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：湾流4操作手册 Gulfstream IV Operating Manual 3
