Power plant Flashcards
Main components of the engine?
What is the function of the FDGS?
Allows the Fan to rotate 3 times sloer than the LPC (n1) shaft
Where is EEC located?
On each engine
Where are REV indicated?
At N1 indicator
How many fuel nozzles are in the combustion chamber?
16
How many igniters in the fuel chamber?
2
What is provided b the Main engine gearbox?
Accessories
- hydraulic engine driven pump
- oil lubrication and scavange pump
- IFPC (integrated fuel pump and control)
- permanent magnet alternator PMA
variable frequency generator VFG
How many channels has each EEC?
2 channels - one has complete control, the other is a backup
What powers the EEC?
PMAG. If PMAG is not available, then DC ESS BUS
Meaning of EICAS
Engine indication and crew alerting system
What part of the engine is the starter turbine attached to?
Main Gear Box
What is the max speed for inflight engine e-start?
250 kt
At what point during engine start the EEC turns off the Starter air Valve (SAV) and igniters?
51% N2
How long the wait between ECU aborted start and the next try?
30 seconds and N2 below 20%
The conditions that activate the continuous ignition system automatically
are as follows:
- A second start attempt is required by the automatic start,
- During takeoff and landing phase, based on the Flight Management
System (FMS) information, - Cowl Anti-Ice System (CAIS) is turned on by automatic mode or
manual mode, - With the L ENG or R ENG switch set to ON and airspeed greater
than 60 kt, engine flameout is detected within 2 seconds by the
FADEC engine flameout protection logic, or - Surge is detected in-flight or during takeof
Normally, the EEC alternates control channels after each subsequent
start. The EEC automatically commands both igniter plugs to fire for the
conditions that follow:
Cowl anti-ice is selected,
* An engine flameout is detected,
* An in-flight start is attempted, or
- During takeoff, or if an in-flight surge is detected.
The FADEC automatic relight system energizes both igniters within 2 seconds of an engine flameout detection when the respective L ENG or
R ENG switch is in the ON position and airspeed is greater than 60 kt.
What is OCM
Oil Control Module.
The Oil Control Module (OCM) filters the oil, senses the oil pressure and temperature, monitors debris, and sends the oil to the engine bearings, Fan Drive Gear System (FDGS), Main Gearbox (MGB), Angle Gearbox (AGB), and to the heat exchangers
How many liters does the oil tank hold?
24,4 l
What is TLLS
Thrust limitation at low speed.
Thrust Limitation at Low Speed (TLLS) ensures that the nose landing gear is sufficiently loaded during the takeoff phase. The Full Authority
Digital Engine Control (FADEC) limits the thrust of the engines to approximately 60% of the takeoff power. As the aircraft accelerates in the takeoff run, thrust increases with airspeed and reaches full power at 80 kt.
The limits are indicated by a light gray sector on the N1 indications on the EICAS page. TLLS is disabled when the parking brake is set to allow
full power run-ups. Refer to Figure 18−09−5.
When is FLEX takeoff prohibited?
On contaminated runways or whe Windchear on TS in vicinity or AT inop
At waht point is Approach Idle selected by EEC?
When Flap 1 selected
When is Steep approach mode activated by EEC?
APR means?
Automatic Power Reserve
When is APR activated?
When does the EEC de-active APR mode?
When is the N1 limit reached?
