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• Left and right engine N1 are less than 67.6%; or
• Radio altimeter 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.
AURAL/VISUAL WARNING SYSTEM
Description
Vol. 2 03−10−13
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
Caution Messages NOT Inhibited During Takeoff and Landing
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 (OUTPUT) ✓
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.
AURAL/VISUAL WARNING SYSTEM
Description
Vol. 2 03−10−14
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
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 SYSTEM
Description
Vol. 2 03−10−15
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
Display Reversionary Control Panel
Figure 03−10−9
AURAL/VISUAL WARNING SYSTEM
Description
Vol. 2 03−10−16
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
MAINTENANCE DIAGNOSTIC COMPUTER
Description
The maintenance diagnostic computer (MDC) is an onboard computer that is used to record
aircraft mechanical and avionics system data. Maintenance personnel can retrieve the information
for use in engine trend analysis, significant event recording, and for avionics/aircraft system failure
detection.
Operation
The MDC continuously records data for fault analysis and engine trend monitoring. The MDC data
is downloadable to a maintenance facility computer.
MDC data is available on the flight deck by means of a red guarded switch on circuit breaker panel
number one (CBP 1). Data can be displayed on MFD 1 or MFD 2, as determined by switch
selection. Instructions on MDC data presentation are displayed on the selected MFD.
　
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