Can the engines be manually started?
No, only automatically.
What parameters are monitored by the EEC during Autostart?
EGT, N2 RPM, Oil pressure and other parameters.
How many attempts does the Autostart system make for the GE engines?
o 3 attempts on the ground
o No start attempts limit in flight.
What are the conditions that AUTO START will correct for during ground start?
o Compressor stall
o High residual EGT
o Hot start
o Hung start
o Loss of one starter
o No EGT rise
o Start time exceed the starter duty cycle
For what conditions will Autostart NOT attempt a second start?
o Loss of both starters
o No N1
o No Oil pressure rise
What happens when the fuel control switch is moved to RUN?
o opens the spar fuel valve
o arms the engine fuel valve (the EEC opens the valve when required)
o arms the selected igniters (the EEC turns the igniters on when required)
What happens when the fuel control switch is moved to CUTOFF?
o Closes fuel valve
o Removes igniter power
o Unlocks the Engine Fire switch.
What two modes does the EEC provide?
2 modes, Normal and Alternate.
How many Alternate modes are there?
2 Alternate modes, Soft and Hard.
What is the difference between Soft and Hard EEC alternates?
o Soft-When the EEC atomically switches an engine to the alternate mode and the EEC
mode switch remains in NORM. Thrust does not change.
o Hard - When the ALTN mode is manually selected on an EEC mode switch, that engine
is switched to the hard alternate mode. Thrust may change.
What types of protection do the EECs provide?
o Overspeed Protection
o Thrust Ramping
o Thrust Control Malfunction Accommodation
o Thrust Asymmetry Protection (TAP)
o Transient Bleed System
o Ice crystal anti-ice (ICA)
What is Overspeed Protection?
o The EEC monitors N2 rotor speed and commands reduced fuel flow if the rotor speed
approaches it redline limit.
o The EICAS advisory message ENG RPM LIMITED (L or R) is displayed when RPM limiting
is in effect.
o If the redline limit is exceeded the EICAS caution message ENG LIMIT EXCEED (L or R)
is displayed.
o Overspeed protection is provided on the N2 shaft (N1 is indirectly protected by the N2
protection)
o If RPM limiting fails and an overspeed condition persists, the EEC commands fuel shut
off to shut down the engine. The EICAS caution message ENG FAIL (Lor R) is displayed
with an aural beeper once the engine falls below idle speed.
o If the EECs are in alternate mode, advancing the thrust levers full forward provides some
over-boost protection and should be considered only during emergencies situations
when all other available actions have been taken, and terrain contact is imminent.
What is Thrust Ramping?
o During takeoff, the EEC compensates for high stress loads on engine fan blades due to
crosswinds and low groundspeed by slowly increasing thrust until takeoff thrust is
achieved, a process known as thrust ramping.
o Delayed engine response due to thrust ramping may be noticed by flight crews during
conditions of high altitude and high ambient temperature that necessitate maximum
takeoff thrust settings.
o Thrust ramping is only active on the ground with the EECs in normal mode.
o Due to thrust ramping, maximum takeoff thrust may not be available until reaching 65
KIAS.
What is Thrust Control Malfunction Accommodation?
o An EEC function that provides protection against idle thrust asymmetry conditions
while on the ground
o The EEC commands shutdown of the affected engine when the airplane is on the
ground and thrust lever is at idle, and engine is above idle speed and not decelerating
normally
o The EICAS caution message ENG FAIL (Lor R) is displayed with an aural beeper once
the engine falls below idle speed
What is Thrust Asymmetry Protection (TAP)?
o TAP is an automatic feature that provides protection against asymmetric thrust during
takeoff or go-around by limiting thrust on the higher thrust engine
o TAP enhances safety by allowing a decrease in approach speed at light gross weights
AND Providing engine-out control capability for speeds above stick shaker and
allowing full rated thrust to be available for all- engine operation at all weights and
airspeeds
o For an engine-out condition, TAP reduces thrust on the operating engine to ensure
there is sufficient rudder for directional control
o TAP reduces thrust when the airspeed decreases below approximately V2 on a takeoff
or below approximately VREF on a go-around
o Once speed is increased above V2/VREF, TAP increases thrust
o The TAP function does not affect thrust for engine out operations flown at or above
V2/VREF, with the exception of a light weight go-around at weights less than 152,273
kilograms where TAP reduces thrust slightly at VREF on the go-around
o TAP does not affect certified takeoff performance o For airspeeds where TAP does limit thrust, climb gradient is higher with TAP limiting
thrust than it would be if TAP did not limit thrust
o This occurs because additional thrust asymmetry creates more airplane drag than the
thrust that was added. Therefore, if TAP becomes active due to a speed reduction below
V2, any reduction in climb gradient from that scheduled for the takeoff is due to
mismanaged speed and not due to TAP
o TAP is only available when the flight controls are operating in normal mode, and the
EEC is in normal or alternate modes.
What is Transient Bleed System?
o The purpose of the transient bleed system is to unload the compressor during engine
acceleration for increased engine stall margin
o The system is composed of one fuel operated transient bleed valve (TBV) per engine
controlled by the EEC and based on N2 rotor speed
o The EEC commands the TBV to open during an above idle acceleration
o If the valve fails to open, the ENG TBV CLOSED (L or R) status message is set
o If the TBV remains open when commanded to close by the EEC, the EICAS advisory
Message ENG TBV OPEN (L or R) is displayed when the airplane is on the ground and
below 80 KCAS Additionally, the ENG TBV OPEN (L or R) status message is set
o To protect the structural integrity of the reversers from hot gases, the associated Thrust
reverser is inhibited if the TBV fails open prior to thrust reverser deployment or is limited
to idle if the failure occurs while the thrust reverser is deployed. In either case, the EICAS
advisory message ENG REV LIMITED (Lor R) is displayed.
o Failure of the TBV in the open position may lead to an EGT redline exceedance and
associated flight deck alerts.
When the thrust protection is lost?
In EEC ALTN mode.
When do the EECs set Approach Idle in flight?
o When Flaps are commanded to 25 or greater , or
o Landing Gear is selected down.
What happens to the engine idle setting when engine anti-ice is turned on?
It switches to Icing idle.
What is ICA and when does is occur and where is it displayed?
o Ice Crystal Anti-Ice (ICA) is an automatic feature that provides engine protection
against ice crystal icing (ICI).
o The ICA activates only above 30,000 feet and terminates below 28,500 feet.
o The ICA activates for 30 minutes and may continue in additional
15-minute increments, for as long as ICI conditions are encountered.
o engine parameters N1, N2, and EGT may fluctuate independently
without any flight crew inputs.
o When ICA is active, “ICA” shows on either one or both N1 engine display.
o Each engine’s ICA indication may appear, independently or not at all.
o An ICA indication does not mean that the engine is currently encountering ICI
conditions.
o After engine maintenance activities, the ICA indication can show in cruise flight, in any
weather conditions, for 75 minutes or more.
How long is the ‘RUNNING’ indication displayed?
30 sec. after the engine reaches idle.
What condition creates the AUTORELIGHT starting mode, and how does it operate?
o Any time the engine is at idle or below idle with fuel control switch in run it is activated.
o It provides protection against an engine flame out at Idle power by turning on both
ignitors.
During an in-flight engine start, with speed below that for a windmilling start, describe
the indication that is displayed if starter assist is required.
A magenta X-START is displayed under the N2
What alert is displayed if actual thrust is less than commanded thrust during takeoff and
what is the airspeed range that this alert is active?
ENG FAIL is displayed RED on the PFD and GREEN on the HUD. It is available between
65 kts and 6 kts prior to V1.
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1. Limitations16
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2. Exterior Inspection20
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3. Memory Items11
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4 NON - NORMAL MANEUVERS21
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5. SYSTEMS22
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5.2 AIR SYSTEMS36
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5.3 ANTI-LCE, RAIN14
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5.4 AUTOMATIC FLIGHT31
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5.5 COMMUNICATION6
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5.6 ELECTRICAL37
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5.7 ENGINE, APU63
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5.8 FIRE PROTECTION27
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5.9 FLIGHT CONTROL58
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5.10 FLIGHT INSTRUMENTS, DISPLAYS0
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5.11 FLIGHT MANAGEMENT, NAVIGATION14
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5.12 FUEL22
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5.13 HYDRAULICS10
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5.14 LANDING GEAR10
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5.15 WARNING SYSTEMS24
