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sumps. The concentration of additive can be checked using an anti-icing additive concentration test
kit available from Cessna Aircraft Company, Citation Marketing Division, Wichita, KS 67277. It is
imperative that the instructions for the test kit be followed explicitly when checking the additive
concentration. The additive concentrations by volume for EGME/DIEGME shall be 0.10 percent
minimum and 0.15 percent maximum, either individually or mixed in a common tank. Fuel, when
added to the tank, should have a minimum concentration of 0.10 percent by volume.
3-166 AA 510FM-07
MODEL 510 SECTION III - OPERATING PROCEDURES
NORMAL PROCEDURES
FAA APPROVED
Configuration U.S.
ENGINE
The Model 510 is powered by two Pratt & Whitney Canada PW615F-A engines each producing 1460
pounds of static takeoff thrust at sea level, standard day conditions. The PW615F-A is a two spool,
counter-rotating, medium bypass turbofan engine with a Full Authority Digital Electronic Control
(FADEC) system. The FADEC controls the engine in accordance with pilot commands, ambient
conditions, and engine operating limits. Detents are provided in the throttle quadrant to provide
automatic setting of Takeoff (T/O), Climb (CLB), and Max Cruise (CRU) power settings.
Major components of the control system for each engine includes a dual channel FADEC unit
mounted on the aft side of the aft pressure bulkhead, an Accessory Gearbox driven Fuel Metering
Unit (FMU), Bleed Valve Actuator, Ignition System, and various engine sensors.
Each FADEC contains two independent electronic control systems either of which is capable of
operating the engine. In the event of a problem with one channel the system will automatically switch
to the other channel. A failure which results in a loss of redundancy such that engine operation may
be seriously degraded will result in an ENG CTRL SYS L-R message. A FADEC RESET switch is
provided to allow the pilot to clear intermittent faults. Dispatch is prohibited with the ENG CTRL SYS
message posted. There is no mechanical backup for the electronic control system. Power for the
FADECs can be supplied by normal aircraft DC power or by the Permanent Magnet Alternator (PMA)
built into each FMU, whichever provides the highest voltage.
Ejector pumps in each wing tank supply fuel to the engine driven fuel pump in the FMU. The FMU
then meters fuel to the combustor through a ring of 14 nozzles. During engine start, fuel is metered
through only 7 nozzles to improve lightoff. Prior to reaching idle the FMU equalizes flow to all 14
nozzles. Should pressure to the engine driven pump fall below approximately 4.65 PSI, a pressure
switch will cause an amber FUEL PRESS LO L-R message to display and the MASTER CAUTION
will illuminate steady. If the FUEL BOOST switch is in the NORM position, the electric fuel boost
pump will be automatically turned on accompanied by an amber FUEL BOOST L or R message and
the FUEL PRESS LO message should clear. The fuel boost pump and CAS message can be reset
by selecting the affected FUEL BOOST switch to ON and back to NORM if the low pressure
condition has been corrected. In addition to fuel pump and fuel metering functions, the FMU also
supplies motive flow to power the wing ejector pumps as well as ecology and shaft shear protection
functions.
The ignition system consists of an engine mounted dual channel exciter box with each channel
powering one ignitor plug. The FADEC normally controls the ignitors and turns them on only during
engine start or if a flameout is detected. Cockpit mounted IGNITION switches are provided to allow
the ignitors to be turned on manually; however, manual operation of the ignitors is not required
during any normal operation of the airplane.
Engine synchronization can be selected using the ENGINE SYNC NORM/OFF switch. With the
switch in the NORM position, the FADEC’s will automatically synchronize the N1 rotation speeds
unless the landing gear is extended, the throttle levers are at either TO or IDLE, or there is a greater
than 5% difference in N1 between the two engines. When engine sync is active, SYNC will be
displayed in green between the digital N1 values on the EICAS display. With the ENGINE SYNC
switch in the OFF position, engine sync is disabled.
510FM-07 AA 3-167
SECTION III - OPERATING PROCEDURES MODEL 510
NORMAL PROCEDURES
FAA APPROVED
U.S. Configuration
ENGINE INDICATING AND CREW ALERTING SYSTEM (EICAS)
The EICAS displays N1, ITT, N2, oil pressure, oil temperature, fuel temperature, fuel flow, and fuel
quantity individually for each engine. A compressed format of the EICAS is automatically selected
during display reversion. The DISPLAY BACKUP button, located on each Audio Control Panel,
　
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