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messages. The logic inhibits messages during takeoff when the left and right engine N1
are greater or equal to 79% and above 80 kts with weight-on-wheels. On landing, the
messages are inhibited when radio altitude is less than 400 feet above ground level
(AGL) with landing gear extended.
CONDITION VOICE WARNING EICAS MESSAGE MASTER WARNING
AUTOPILOT ENGAGED “CONFIG AUTOPILOT” CONFIG AP FLASHES
FLAPS NOT SET FOR TAKEOFF “CONFIG FLAPS” CONFIG FLAPS FLASHES
ALL SPOILERS NOT IN TAKEOFF
POSITION “CONFIG SPOILERS” CONFIG SPOILERS FLASHES
HORIZONTAL STAB NOT IN T/O
RANGE “CONFIG TRIM” CONFIG STAB FLASHES
PARKING BRAKE SET “CONFIG BRAKES” PARKING BRAKE FLASHES
Takeoff Configuration Warnings
Table 3-2
AURAL/VISUAL WARNING
For Training Purposes Only
Jan 04
3-17
P I LOT T R A I N I N G GU I D E
The inhibit logic is removed when:
• left and right engine N1 are less than 67.6%; or
• radio altitude is greater than 400 feet AGL with the landing gear extended; or
• 30 seconds after the inhibit starts; or
• 30 seconds after the air-to-ground transition
Caution messages and their associated aural alerts that are NOT inhibited during
takeoff and landings are shown in the following table.
AIRPLANE SYSTEM CAUTION MESSAGE NOT INHIBITED TAKEOFF LANDING
POWER PLANT
APR INOP √ √
APR CMD SET √
L (R) REV UNLOCKED √ √
L (R) REV UNSAFE √ √
AUTOMATIC FLIGHT CONTROL
SYSTEM
AP TRIM IS LWD (RWD) (ND) (NU) √
AP PITCH TRIM √
YAW DAMPER √
FIRE PROTECTION
APU BTL LO √
ENG BTL 1 (2) LO √
FLIGHT CONTROLS
ELEVATOR SPLIT √ √
FLAPS FAIL √
FLT SPLRS √
FLT SPLRS DEPLOY √
GND SPLRS √
GND SPLRS DEPLOY √ √
GND SPLRS NOT ARMED √
STAB TRIM √
FUEL
FUEL IMBALANCE √
L (R) FUEL LO PRESS √ √
HYDRAULICS HYD 3 LO PRESS √
INSTRUMENTS EFIS COMP MON √ √
LANDING GEAR
A/SKID INBD (OUTBD) √ √
INBD (OUTBD) BRAKE PRESS √ √
PROX SYS √
STEERING INOP √
WOW INPUT OR OUTPUT √
Caution Messages Not Inhibited during Takeoff and Landing
Table 3-3
AURAL/VISUAL WARNING
3-18 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Display Reversionary Control
EICAS Reversionary Mode
The EICAS reversionary mode provides an alternate method of displaying EICAS
information should ED 1 or ED 2 fail.
In the event of ED 1 failure, the primary page is automatically transferred to ED 2.
This automatic feature ensures that engine indications and warning and caution
messages are always available to the pilot. There is no automatic transfer of status
page information should ED 2 fail.
Display Reversionary Control Panel
The display reversionary control panel is located on the center pedestal. The
reversionary selector switches (L MFD, EICAS, R MFD) are used when a malfunction
exists.
The L MFD and R MFD reversionary switches are identical, and have three positions
designated as PFD, NORM and EICAS. In EICAS position, the status-page
information is displayed by default on the MFD.
The EICAS reversionary selector is also a three-position switch designated as NORM,
ED 1 and ED 2. In the NORM position, normal EICAS display is represented on ED 1
and ED 2. When the selector is moved to either ED 1 or ED 2 position, the opposite
ED is disabled and blanked while the primary and secondary information is available
on the selected display.
PFD Reversionary Mode
When a primary flight display (PFD) fails, the information can be transferred to the
associated MFD. The L (R) MFD rotary knob on the display reversionary control
panel, when selected to the PFD position, effects the transfer.
MFD Reversionary Mode
There is no reversionary mode for the data normally presented on the multifunction
displays (MFDs).
AURAL/VISUAL WARNING
For Training Purposes Only
May 03
3-19
P I LOT T R A I N I N G GU I D E
Display Reversionary Control Panel
Figure 3-9
P604_03_009
VFE (45 FLAPS)
VFE (30 FLAPS)
VFE (20 FLAPS)
VA (MANEUVERING)
(AT SEA LEVEL 48,200LB)
(AT 20,000FT 26,000LB)
VNO (BELOW 8,000FT)
VNO (8,000 TO 22,150 FT)
AIRSPEED LIMITS - (INDICATED SPEEDS)
MMO (22,150FT TO 26,570FT)
VMO (26,570FT TO 30,990FT)
MMO (30,990FT TO 41,000FT)
VLO (EXT) (L/G EXTENSION)
VLO (RET) (L/G RETRACTION)
　
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