曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
• Salt water spray
• Blowing sand
• Dirt, dust, or volcanic ash
• Birds
• Insects
• Leaves
• Other debris
CAUTION
CITATION MUSTANG OPERATING MANUAL
510OM-00 7-5
Figure 7-5. Engine Nacelle Doors and
Fasteners
VISUAL
INSPECTION
HOLE
Figure 7-6. Oil Servicing Panel
CITATION MUSTANG OPERATING MANUAL
7-6 510OM-00
To prevent contamination of the engine on the
ground when the engines are off, engine covers
are provided for the inlet and exhaust ports
of each engine.
ENGINE SYSTEMS
Ignition System
Each engine has dual igniters, which produce
sparks to ignite fuel in the engine combustion
chambers. They are powered by exciter boxes
and controlled by the FADEC. Igniters are normally
only operated during starting (Figure 7-7).
Engine start is initiated when the pilot presses
and releases the respective engine start button,
then immediately thereafter advances the same
side throttle into idle. Once the correct N2 is
reached, the FADEC commands the light-off
fuel flow and both igniters on. When an adequate
rise in ITT is detected, the igniters are
automatically powered off by the FADEC.
The FADECs also command the igniters on and
off during an autorelight situation. Pilot control
of the igniters consists of two options:
normal and on. In normal mode, the FADECs
command the igniters on and off as required.
For the autorelight feature, the FADEC monitors
fuel flow and N2 speed. If an
uncommanded drop in N2 rpm lasts for more
than 0.25 seconds, the FADEC activates the igniters.
Once a positive engine acceleration
and adequate rise in ITT are detected, the igniters
are turned off by the FADEC. Along
with fuel flow, the igniters are commanded off
by the FADEC when the throttles are put into
the CUT OFF position.
Engine Fuel System
The engine fuel system consists of the fuel
system components between the firewall shutoff
valves and the engine. An FMU, under the
direction of the FADEC, regulates the fuel
flow to the engines (Figure 7-8). The FMU
also provides HP motive fuel flow to the fuel
tank ejector pump system (refer to Chapter
5—“Fuel System”) and the fuel pressure is
also referenced to the BVA.
Fuel/Oil Heat Exchanger
A fuel/oil heat exchanger (FOHE) is also part
of the FMU assembly. The heat exchanger
transfers heat from the hot engine oil to the
cooler incoming fuel. This cools engine oil to
improve lubrication and warms the fuel to prevent
ice formation from water in the fuel system.
Fuel Filter and Bypass
The engine fuel system includes a fuel filter
and a bypass valve, which allows fuel to continue
to the engine in the event of a clogged
filter. Before the bypass valve opens, a pressure
sensor sends a signal to the cockpit,
alerting the pilot to an impending bypass situation.
This may indicate fuel contamination.
Emergency Fuel Shutoff Valve
The FMU incorporates an emergency fuel
shutoff valve that is automatically actuated
closed in the event of aft N1 shaft movement.
This feature prevents N1 overspeed in the
event of shaft separation by mechanically
closing the emergency fuel shutoff valve.
Permanent Magnet Alternator
The FMU also has a dual-coil permanent magnet
alternator (PMA) that is integral to the FMU
and is driven by the fuel pump drive shaft. It has
a single rotor, with dual coils for dual output of
electrical power. Under normal operating conditions,
power is provided either from DC power
by the aircraft electrical system or the PMA
(whichever source is providing the greatest
voltage). If normal DC power is not available,
the PMA provides AC electrical power to the
FADEC during all phases of operation.
Oil System
The oil system provides cooling and lubrication
of the engine bearings and the accessory
section (Figure 7-9).
CITATION MUSTANG OPERATING MANUAL
510OM-00 7-7
7.5 7.5
EXCITER BOX
LEGEND
NORMAL DC POWER
HIGH-ENERGY IGNITION
L IGNITION NO. 1
SSR
L IGNITION NO. 2
SSR
L ENG
FADEC
A
L ENG
FADEC
B
EXCITER BOX
R IGNITION NO. 1
SSR
R IGNITION NO. 2
SSR
R ENG
FADEC
A
R ENG
FADEC
B
7.5 7.5
LH IGN
SSR NO. 1
(AFT J-BOX)
LH IGN
SSR NO. 2
(AFT J-BOX)
RH IGN
SSR NO. 1
(AFT J-BOX)
RH IGN
SSR NO. 2
(AFT J-BOX)
Figure 7-7. Ignition System (Left Engine Battery Start)
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
Cessna塞斯纳公务机飞行手册(36)
