CITATION MUSTANG OPERATING MANUAL
CHAPTER 4
MASTER WARNING SYSTEM
TEST
INTRODUCTION
This chapter describes the master warning systems on the Citation Mustang aircraft. The
master warning systems provide a warning of aircraft system malfunctions, indications
of unsafe operating conditions requiring immediate attention, and indications that some
specific systems are in operation. Audio warnings provide further indications.
GENERAL
The master warning system includes a pair of
MASTER WARNING and MASTER CAUTION lights, and the crew alerting system
(CAS) messages. CAS messages are displayed
by the G1000 engine indicating and crew alerting system (EICAS).
These lights and messages provide a visual
indication to the pilots of certain faults, functions, and/or conditions of selected systems.
Each CAS message indicates an individual
system situation, or simultaneous situations on
510OM-00
both sides (left and right) of a dual system.
Additionally, an audio warning system provides indication of some situations.
CAS messages appear on the EICAS, which is
on the left side of the multifunction display
(MFD). The pilot and copilot can revert to using
their primary flight display (PFD) to view CAS
messages. A red DISPLAY BACKUP button on
each audio panel selects reversionary mode,
which combines displays from the PFD and
MFD (including CAS messages). The combined
4-1
CITATION MUSTANG OPERATING MANUAL
displays appear on both the selected PFD and
the MFD. If the MFD fails, it automatically reverts CAS messages to the pilot PFD. When
the MFD and a PFD are in reversionary mode,
the EICAS displays the CAS messages on the
upper-right section of both display panels.
DESCRIPTION
The Mustang master warning system uses
cockpit indications (visual and aural) to advise the crew of important warnings, cautions,
and advisory information about the aircraft and
its systems.
NOTE
Crew alerts associated with the autopilot, avionics, and engine fire warning/suppression are displayed
elsewhere in the displays or cockpit.
The crew alerts are described in the
corresponding chapters in this manual.
The abnormal and emergency procedures in this
section are keyed, where applicable, to the appropriate CAS messages. The rotary TEST knob
provides testing for the master warning system.
Pressure sensors, temperature sensors,
switches, and other devices detect conditions
in the aircraft and its systems. This information is provided as analog signals or discrete
digital signals to the G1000 system. These
signals are received at the left and right Garmin
integrated avionics unit (GIAs), and at the left
and right Garmin engine/airframe interface
units (GEAs) (Figure 4-1). A detailed description of G1000 system architecture is provided
in Chapter 16—“Avionics.”
With the battery switch selected to EMER,
only the left GIA and left GEA are powered;
MULTIFUNCTION
DISPLAY
PFD
PFD
(INCLUDES EICAS)
DISCRETE
DIGITAL
INPUTS
NO. 1
INTEGRATED
AVIONICS
UNIT
(GIA63W)
NO. 1
ENGINE/
AIRFRAME
ADAPTER
(GEA71)
ANALOG
INPUTS
DISCRETE
DIGITAL
INPUTS
NO. 2
ENGINE/
AIRFRAME
ADAPTER
(GEA71)
ANALOG
INPUTS
NO. 2
INTEGRATED
AVIONICS
UNIT
(GIA63W)
Figure 4-1. G1000 Block Diagram
4-2
510OM-00
CITATION MUSTANG OPERATING MANUAL
CAS messages requiring input from the right
GIA or right GEA are inhibited and do not appear, regardless of aircraft or system condition.
CAS Message Types
CONTROLS AND
INDICATIONS
Red (Warning) Messages
The Mustang master warning system includes:
• CAS messages
• Master indicators:
• MASTER WARNING lights
• MASTER CAUTION lights
• Aural warnings—Various audio warnings are incorporated into aircraft systems that warn of specific conditions
and malfunctions.
Control of the system is provided by:
• CAS scroll softkeys (up and/or down)
• Rotary TEST knob
CAS MESSAGES
The Mustang master warning system is primarily a function of the G1000 avionics system. The CAS displays warning, caution,
and advisory messages in response to data
from aircraft sensors and FADECs.
CAS messages are in one of three colors: red,
amber, or white.
Red indicates a warning (hazardous situation
that requires immediate pilot corrective action). When a red CAS message appears, it
flashes in reverse video in conjunction with the
MASTER WARNING lights. Pressing the
MASTER WARNING light acknowledges the
message, turns off the MASTER WARNING
lights, and changes the CAS message to a
steady ON state. Red CAS messages are displayed until the situation is corrected. All red
CAS messages are grouped together at the top
of the CAS display window.
Amber (Caution) Messages
Amber indicates a caution (abnormal or special
situation that includes a possible need for future pilot corrective action). When an amber
CAS message appears, it flashes in conjunction
with the illumination of the MASTER CAUTION lights. Pressing the MASTER CAUTION
light acknowledges the message, turns off the
MASTER CAUTION lights, and changes the
CAS message to a steady ON state.
White (Advisory) Messages
White indicates an advisory. This may indicate
the following:
CAS Message Window
• Abnormal condition
All CAS messages are displayed in the CAS
message window. The window is on either the
MFD, or on one or both of the PFDs:
• Change in status of an aircraft system
• Normal display mode—CAS message
window is in the bottom left corner of the
EICAS display, which appears on the
left side of the MFD (Figure 4-2).
• Reversionary display mode—CAS message window is on the right side of the
display (Figure 4-3, Sheet 1 of 2).
510OM-00
• Normal operation of a specific device
All white advisory messages are grouped together at the bottom of the CAS message list.
When an advisory message appears, the checklist may require an action. If required, find the
a c t i o n i n t h e FA A - a p p r o v e d A b n o r m a l
Procedures Checklist.
4-3
Figure 4-2. Multifunction Display
CITATION MUSTANG OPERATING MANUAL
4-4
510OM-00
CRU
400
950
134
66
70.1
46.2
N2%
OIL
PSI
°C
FUEL
LBS
PPH
13 °C
200
500
600
700
800
900
ITT°C
20
50
80
90
100
FLAPS
DFLTS
UP
CDI
ADF/DME
E
TERM
6
CRS
V
16.5NM
ICT
NAV2
BRG2
BARO MIN
2900FT
013°
REVERSIONARY MODE
BRG1
GPS
3
054°
10
10
20
DTK
1200 ALT
R LCL
IDENT STD BARO BACK
XPDR1
ILS 01L
CHITO faf
013°
RW01L map
013°
3000FT
013°
ICT mahp
Approach –
MSG
18:11:37
6.6NM
4.8NM
3.3NM
DIS
OIL PRESS LO L
CABIN ALT
T2 HTR FAIL R
W/S O’HEAT L
W/S A/I FAIL L
FUEL PRES LO R
ENG A/I COLD L
CABIN DOOR
AFT DOOR
P/S HTR L
F/W SHUTOFF R
SURFACE DE-ICE
SPD BRK EXTEND
FUEL TRANSFER
CAS
BOTH ON GPS2
HDG MISCOMP
IAS NO COMP
ALT NO COMP
118.200 COM1
125.150 COM2
FLIGHT PLAN
4
2
-900
2
4
CHITO / KICT
29.92IN
2900
3000
1 20
33
100
00
3200
3300
3400
Figure 4-3. Primary Flight Display (Sheet 1 of 2)
DME
NAV1
109.10
–.–– NM
6.8NM
CHITO
GPS
WIND
DME
043°
10
10
20
2900
-900
126.700
121.900
3000
7.1NM BRG 034°
900FPM ASEL
DIS
S
METRIC
R
RF
1 HDG
AP
2
E
M .399
5
+6°C
3
+15°C
RAT
ISA
90
100
110
11 7
1208
130
140
CHITO faf
AP YD VS
15
CABIN PRESS
ALT FT 1400
0.8
DIFF PSI
25 DC VOLTS 20
105 DC AMPS 205
BATT VOLTS 27
300
1040
40
102
835
68.3
100.1
N1%
89.5
N
33
30
CRU
W
109.10 ITWI vtf 013°
113.80 ICT LOC HDG
24
510OM-00
12
21
NAV1 113.80
NAV2 116.80
CITATION MUSTANG OPERATING MANUAL
4-5
ICT
ARK
ANS
AS
RIV
ER
PPRE
RW01L
135
KIAB
TFR: N/A
3
5
R
RF
1 HDG
AP
2
35
043°
3
CRS
ADF/DME
NORMAL MODE
CDI
E
10
10
20
S
OBS
6
054°
LOC1
10
10
20
16.5NM
ICT
NAV2
XPDR
BARO MIN
2900FT
013°
G
20
IDENT
LANDING
TMR/REF
ID
NRST
R LCL
91KT
103KT
2000FT
1330FT FLT
1200 ALT
DEST ELV
XPDR1
REFERENCES
4
2
-900
2
4
MSG
18:11:37
ON
ON
ON
N510FS
START?
ON
ON
118.200 COM1
125.150 COM2
00:00:00 UP
99KT
140KT
BARO MIN
Vref
Vapr
V2
Venr
TIMER
29.92IN
2900
3000
1
33
100
00
3200
3300
3400
-900
126.700
121.900
3000
7.1NM BRG 034°
900FPM ASEL
DIS
15
Figure 4-3. Primary Flight Display (Sheet 2 of 2)
DME
NAV1
109.10
–.–– NM
TA OFF SCALE
50NM 7.11NM
CHITO
GPS
RAT +6°c ISA +15°c
??????
INSET SENSOR
PFD
CHITO
ENEY RESERVOIR
NORTH UP
90
100
110
120
11 8
7
130
E
N
33
CHITO faf
AP YD VS
12
30
140
W
109.10 ITWI vtf 013°
113.80 ICT LOC HDG
24
4-6
21
NAV1 113.80
NAV2 116.80
CITATION MUSTANG OPERATING MANUAL
510OM-00
CITATION MUSTANG OPERATING MANUAL
CAS Message Type Priority
Some CAS messages may appear in different
colors at different times, indicating different
conditions or levels of severity (warning, caution, or advisory). For instance, the CABIN
ALT message may appear in red, amber, or
white, depending upon various causes and
conditions.
However, the same CAS message does not appear in two colors at the same time for the
same side. Each CAS message appears in its
highest-priority color appropriate at the time.
CAS Message Display
Sequence
CAS messages are sorted by color, and then
by the order in which they have been caused:
• Red (warning) messages appear at the
top of the CAS message window, with
the most recent messages first.
• Amber (caution) messages appear after the
red messages (with the most recent amber
message at the top of the amber group).
• White (advisory) messages appear last,
with the newest message at the top and
the oldest message at the bottom of the
white messages.
If a message changes color (due to changing
severity of the condition/indication), the appropriate master indicators will appear and
the message moves to the top of the list of the
appropriate color group.
CAS
CAS
OIL PRESS LO L
CABIN ALT
T2 HTR FAIL R
W/S O’HEAT L
W/S A/I FAIL L
FUEL PRES LO R
ENG A/I COLD L
CABIN DOOR
AFT DOOR
P/S HTR L
F/W SHUTOFF R
FDR FAIL
SURFACE DE-ICE
SPD BRK EXTEND
CAS
CAS
OIL PRESS LO L
CABIN ALT
AFT DOOR
P/S HTR L
F/W SHUTOFF R
FDR FAIL
SURFACE DE-ICE
SPD BRK EXTEND
FUEL TRANSFER
FUEL BOOST R
CAS
CAS
Figure 4-4. CAS Scroll Buttons
Red warning messages always stay at the top
of the CAS messages and are unaffected by
scrolling.
Amber caution messages can run off of the display. If an amber message scrolls off, or if there
are too many messages to display all active
amber messages, the scrollbar track changes
color to reflect the color of the message.
At the same time, CAS-scroll buttons (one with
an up-arrow and one with a down-arrow) appear
on the soft keys at the bottom of the display, allowing the pilot to scroll up or down through the
current list of CAS messages. When the top of
the list is visible, only the CAS down-arrow
scroll button appears among the soft keys. When
the bottom of the list is displayed, only the CAS
up-arrow scroll button appears.
CAS Message Scrolling
The CAS message window can only display 14
messages. To ensure all valid CAS messages
can be seen when appropriate, the CAS message window uses a “scrolling list” of all the
current valid CAS messages. If more than 14
messages are valid, a scroll bar appears on
the right side of the CAS message window
(Figure 4-4). A slider in the scroll bar indicates
which portion of the list is currently visible.
510OM-00
CAS Message Inhibits
Many CAS messages are inhibited (prevented)
from displaying during certain phases of aircraft operation, regardless of whether the
CAS message would otherwise be valid or
not. These inhibits reduce pilot workload or
prevent invalid indications during certain
phases of aircraft operation. Different CAS
messages are inhibited by different phases of
aircraft operation.
4-7
CITATION MUSTANG OPERATING MANUAL
There are six phases of aircraft operations that
inhibit various CAS messages:
• Engine start inhibit (ESI)
• Takeoff operational phase inhibit (TOPI)
• On ground/in flight (GROUND/AIR)
• Landing operational phase inhibit
(LOPI)
• Engine shutdown inhibit (ESDI)
• Emergency power mode (EMER)
Engine Start Inhibit
When an engine is starting, the ESI for that engine inhibits some CAS messages for that engine and related systems. This inhibit is
triggered by the full-authority digital engine
control (FADEC). Each FADEC only inhibits
messages from its side.
On Ground/In Flight
Messages with the GROUND inhibit do not
appear when the aircraft is on the ground,
and messages with the AIR inhibit do not appear when the aircraft is in flight. The inhibits are normally controlled by squat switch
indications, but if that fails then GPS ground
speed and air data computer (ADC) are alternate sources used by the CAS for setting these
inhibits.
Landing Operational Phase Inhibit
LOPI activates when any of the following
occurs:
• The aircraft transitions from in air to on
ground.
• Global positioning system (GPS) altitude transitions below 400 feet above
field elevation stored in the terrain database.
Takeoff Operational Phase Inhibit
The TOPI prevents messages from distracting
the flightcrew during takeoff.
TOPI becomes active when any of the following is true:
• The aircraft transitions from on ground
to in air.
LOPI becomes inactive when any of the following is true:
• The aircraft has been on the ground for
more than 25 seconds.
• Either indicated airspeed is less than 40
knots.
• Both indicated airspeeds are invalid.
• Either indicated airspeed transitions from
less than 50 knots to more than 50 knots.
• The LOPI has been active for more than
90 seconds.
The TOPI becomes inactive when any of the
following is true:
• Global positioning system (GPS) altitude is greater than 600 feet above the
field elevation stored in the terrain database.
• The aircraft has been in the air for more
than 25 seconds.
• Pressure altitude is more than 400 feet
above the field elevation. The field elevation is the pressure altitude captured
when the aircraft transitions from on
ground to in air.
• Either airspeed indication is less than 40
knots.
• Both airspeed indications are invalid.
Engine Shutdown Inhibit
When either engine is shut down, or its FADEC
determines that the engine has failed, the ESDI
for that engine inhibits some CAS messages
for that engine and related systems. This inhibit is triggered by FADEC (shutdown indication). Each FADEC only inhibits messages
from its side.
• The TOPI has been active for more than
90 seconds.
4-8
510OM-00
CITATION MUSTANG OPERATING MANUAL
Emergency Power Mode
To prevent nuisance messages in emergency
power mode, selected messages are inhibited
when the emergency bus is powering the aircraft. Emergency bus status occurs when:
• The battery switch is in the EMER position, and
and MASTER CAUTION light is on the instrument panel above each PFD (directly in front
of the pilot and copilot) (Figure 4-5). Each
master indicator light has an integral momentary-contact pushbutton switch. Pressing the
light resets the light and acknowledges the
CAS message.
• Both generator bus input discretes have
been lost.
The left GIA and the left GEA receive power
in emergency bus mode. However, most of the
sensors required to indicate CAS messages
are not powered, so most messages have the
EMER inhibit.
Figure 4-5. Master Indicator Lights
Most CAS messages are inhibited in emergency mode. Some are inhibited to prevent
the flightcrew from being distracted with lowpriority issues. Other messages are inhibited
because their sources do not receive power in
emergency mode. CAS messages without the
inhibit are listed in Table 4-1.
NOTE
When the aircraft is first powered
on, any CAS messages that immediately appear do not cause the master
indicator lights to illuminate. The
CAS considers these messages to be
already acknowledged.
MASTER INDICATOR LIGHTS
The master indicator lights (red MASTER
WARNING and amber MASTER CAUTION
lights) illuminate to direct pilot attention to
new CAS messages. A MASTER WARNING
Red MASTER WARNING Lights
When a new red CAS message appears on the
MFD or PFD(s), both red MASTER WARNING
Table 4-1. EMERGENCY MODE CAS MESSAGES
MESSAGE
GEN OFF L-R
NOTES
Always displays in emergency mode.
ENG CTRL SYS L-R
Functions normally since the FADEC receives power from the engine permanent
magnetic alternator (PMA).
FUEL LO INOP L-R
Always displayed in emergency mode.
BATTERY O’TEMP
Functions normally since the battery temperature monitor does not require
outside power.
BATT TEMP FAIL
Functions normally since the battery temperature monitor does not require
outside power.
CABIN ALT
510OM-00
Functions normally since the cabin altitude sensor is powered in emergency mode.
4-9
CITATION MUSTANG OPERATING MANUAL
lights illuminate flashing. Illumination of the
L–R ENGINE FIRE light(s) also triggers the
MASTER WARNING lights.
Pressing either red MASTER WARNING light
closes the switch momentarily, resetting the
light. This extinguishes the MASTER WARNING light and stops the CAS message flashing (the CAS message remains on until the
condition that caused it is corrected).
If a new red CAS message appears in the window, the MASTER WARNING light flashes
again, and continues flashing until reset. If
two or more red CAS messages are flashing
at the same time, pressing the MASTER
WARNING light once acknowledges them
all at the same time.
a MASTER CAUTION light once acknowledges them all; all stop flashing and illuminate
steady. If all amber CAS message problems are
solved before the MASTER CAUTION lights
are reset, the MASTER CAUTION lights automatically extinguish.
ROTARY TEST KNOB
The rotary TEST knob (Figure 4-6) is above
the copilot PFD. Positioning the knob to
A N N U c a u s e s t h e M A S T E R C AU T I O N
lights, MASTER WARNING lights, and other
lights to illuminate (Table 4-2). Illumination
verifies only light emitting diodes (LEDs)
lamp integrity.
If the condition that caused the CAS message
is corrected or stops before resetting the MASTER WARNING lights, the CAS message and
the red MASTER WARNING lights continue
to flash until acknowledged by resetting the
MASTER WARNING lights. This is to ensure
the important CAS message is seen by the
pilot, even if it is only indicating an intermittent condition.
Amber MASTER CAUTION
Lights
When a new amber CAS message appears on
the MFD or PFD(s), the amber MASTER CAUTION lights both illuminate steady.
Each MASTER CAUTION light is an integral
m o m e n t a r y - c o n t a c t p u s h bu t t o n s w i t c h .
Pressing either MASTER CAUTION light
closes the switch momentarily, resetting the
light, which extinguishes. If a new amber CAS
message appears in the window, the MASTER
CAUTION light illuminates again, and continues illuminated until reset.
When a MASTER CAUTION light is reset,
both MASTER CAUTION lights extinguish,
and the flashing amber CAS message illuminates steady until its indicated condition stops
or is corrected. If multiple amber CAS messages are flashing at the same time, pressing
4-10
Figure 4-6. Rotary TEST Knob
During rotary test, audio warnings are also
tested and some other associated system indications appear.
CAS MESSAGE DESCRIPTION
Tables 4-3 through 4-5 show each CAS message, including its color and description. Note
that some messages appear in more than one
color, indicating different conditions. Some
messages are followed by the letters L, R, or
L-R, which respectively indicate left, right or
both systems affected.
510OM-00
CITATION MUSTANG OPERATING MANUAL
Table 4-2. ROTARY TEST INDICATIONS
POSITION
INDICATIONS
FIRE WARN
• Red L ENGINE FIRE and R ENGINE FIRE
lights illuminate.
• MASTER WARNING lights illuminate.
LANDING
GEAR
• Three green gear downlock lights illuminate.
• Red gear UNLOCK light illuminates.
• Gear warning horn sounds. Alternates
between pilot and copilot speakers.
CABIN ALT
• Red CABIN ALT message appears.
• Amber CABIN ALT message appears.
• MASTER WARNING/CAUTION lights illuminate.
STALL
• Amber STALL WARN FAIL message appears.
• Stall warning tone sounds and alternates
between pilot and copilot speakers.
• Amber STALL WARN HTR message appears.
• White STALL WARN HI message appears.
• MASTER CAUTION lights illuminate.
FLAPS
• The flap indicator on the MFD is replaced
with a red X for 3 seconds.
• Amber FLAPS FAIL message appears.
• Amber STALL WARN FAIL message appears
for 3 seconds.
• MASTER CAUTION lights illuminate.
OVERSPEED
• The overspeed warning tone sounds and
alternates between pilot and copilot speakers.
ANTI SKID
• Amber ANTISKID FAIL message appears for
6 seconds.
• White NO TIRE SPINDOWN message appears
for 6 seconds.
• MASTER CAUTION lights illuminate.
ANNU
510OM-00
ILLUSTRATIONS
• MASTER CAUTION illuminates and cannot
be cancelled.
• MASTER WARNING illuminates and cannot
be cancelled.
• Autopilot mode control panel indicators illuminate.
• Audio panel indicators illuminate.
• Red DUMP illuminates on Cabin Dump switch.
• Test audio tone sounds.
4-11
CITATION MUSTANG OPERATING MANUAL
Table 4-3. RED CAS MESSAGES
BATTERY O’TEMP
If the temperature reaches 71°C (160°F), a red
BATTERY O’TEMP message displays (NiCad only).
CABIN ALT
Normal mode—Red above 10,000 feet cabin altitude.
High altitude mode—Red above 15,000 feet cabin altitude.
GEN OFF L-R
Dual generator failure.
OIL PRESS LO L-R*
Indicates oil pressure is below the minimum acceptable
pressure (lower red line limit on the oil pressure display).
Indicates engine failure has occurred or may soon occur.
TAIL CONE BLD LK
Indicates tail cone temperature is higher than normal and
may indicate a possible leak of bleed air into the tail cone.
¸
¸
¸
GND
EMER
ESDI
LOPI
AIR
DESCRIPTION
TOPI
MESSAGE
ESI
INHIBITS
¸
¸ ¸
¸
¸
¸
*Only affected side displayed (L, R, or L-R) in a CAS message; applicable CAS messages listed here display L-R for example.
Table 4-4. AMBER CAS MESSAGES
AFT DOOR
Tail cone baggage door is not fully secured.
AFT JBOX CB L-R*
Indicates the left or right start circuit breaker on the aft J-box
has popped. Cannot be reset from the cockpit, maintenance
is required.
AFT JBOX LMT L-R*
Indicates failure of a 200-amp current limiter.
ANTISKID FAIL
Indicates a fault in the antiskid system. Deactivate the system.
Leaving the antiskid system on can result in unpredictable
braking system performance.
BATTERY O’TEMP
Warns the pilot of abnormally high battery temperatures of
63–70°C (145–156°F) (NiCad only).
BATT TEMP FAIL
Indicates the battery temperature sensor has failed
(NiCad only).
GND
EMER
ESDI
LOPI
AIR
DESCRIPTION
TOPI
MESSAGE
ESI
INHIBITS
¸
¸
¸
¸
¸
¸
*Only affected side displayed (L, R, or L-R) in a CAS message; applicable CAS messages listed here display L-R for example.
4-12
510OM-00
CITATION MUSTANG OPERATING MANUAL
Table 4-4. AMBER CAS MESSAGES (Cont)
CABIN ALT
High-altitude mode only—In flight, the amber CABIN ALT
Messages appears when the cabin altitude has been between
approximately 10,000 and 15,000 feet for 30 minutes.
CABIN DOOR
Indicates the cabin door is not fully secured.
CHECK DOORS
Indicates a door monitor has not been properly tested or
or has failed.
DUCT O’HEAT L-R*
Appears if either the cabin or cockpit air supply duct
temperature exceeds approximately 300°F (149°C). Crew
action is required. Message disappears if the temperature
falls below approximately 285°F (141°C).
ENG A/I COLD L-R*
Indicates that engine inlet temperature is below safe level for
satisfactory ice protection.
ENG CTRL SYS L-R*
Indicates that an input to the FADEC has failed, exceeded
tolerances, or a FADEC channel is inoperative. Maintenance
will be required prior to next flight ulnless the fault can be
cleared using the FADEC RESET switch. If you can
clear/reset it, no maintenance is required.
F/W SHUTOFF L-R*
Indicates that the firewall shutoff valve is fully closed.
FLAPS FAIL
Indicates flap system failure has occurred. Message may or
may not coincide with loss of all flap indication, which results
in removal of the analog flap signal and a red X on the
EICAS flap display.
FUEL BOOST L-R*
Indicates left and/or right low fuel pressure is detected and
the boost pumps automatically turn on.
FUEL FLTR BP L-R*
Indicates fuel filter bypass is impending, or is occurring.
Contamination of the engine (and possible engine damage
or engine failure) is imminent or is occurring.
FUEL LVL LO L-R*
Indicates that fuel level in either tank is low—less than
approximately 170 pounds/25 gal (77 kg/96 liters) in the
indicated wing tank.
FUEL PRES LO L-R*
Indicates fuel pressure is abnormally low. This may indicate
impending engine failure or flameout.
GEN OFF L-R*
Indicates a single generator is off line.
¸
¸
GND
EMER
ESDI
LOPI
AIR
DESCRIPTION
TOPI
MESSAGE
ESI
INHIBITS
¸
¸
¸ ¸ ¸
¸
¸
¸
¸ ¸
¸
¸
¸
¸
¸
¸ ¸
*Only affected side displayed (L, R, or L-R) in a CAS message; applicable CAS messages listed here display L-R for example.
510OM-00
4-13
CITATION MUSTANG OPERATING MANUAL
Table 4-4. AMBER CAS MESSAGES (Cont)
¸
GND
EMER
ESDI
LOPI
AIR
DESCRIPTION
TOPI
MESSAGE
ESI
INHIBITS
¸
HYD PRESS LO
Indicates low hydraulic system pressure (below 750 psi). This
message also indicates the need to prepare for emergency
braking and possible auxiliary extension of landing gear.
This message has a 15-second delay before turning on.
On the ground, MASTER CAUTION lights are not cancelable.
HYD PUMP ON
Indicates the hydraulic pump has been energized too long
(continuously for over 60 seconds).
NOSE DOOR L-R*
One or both of the nose baggage doors are not fully secured.
OXYGEN OFF
Appears when the oxygen system pressure-sensor switch
detects low pressure.
P/S HTR L-R*
Indicates no current is detected to the pitot-static heater.
PRESS CTRL
Indicates failure of the pressurization controller or that the pilot
has selected the PRES CONT switch to STANDBY, disabling
the pressurization controller.
STALL WARN FAIL
Indicates a failure is detected in the stall warning system.
STALL WARN HTR
Indicates no power is being delivered to the stall warning
vane heater.
T2 HTR FAIL L-R*
Indicates failure of the anti-ice heating system for the T2 probe
in the engine inlet. If the aircraft is in icing conditions, this failure
may cause improper FADEC operation and/or engine failure.
Also indicates an increased risk of ice ingestion into the engine
because ice may form on the T2 probe, then break off and
enter the engine.
TAIL DE-ICE FAIL
Indicates the tail deice system is not operating normally.
¸
W/S A/I FAIL L-R*
Indicates the windshield heater has failed.
¸
W/S O’HEAT L-R*
Indicates the windshield temperature is too high.
¸
WING DE-ICE FAIL
Indicates the wing deice system is not operating normally.
¸
WOW MISCOMPARE
Indicates the left and right squat switches have different
WOW signal indications for longer than 2 seconds. Any
aircraft systems relying on WOW signals may be inoperative
or operate incorrectly.
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸ ¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
*Only affected side displayed (L, R, or L-R) in a CAS message; applicable CAS messages listed here display L-R for example.
4-14
510OM-00
CITATION MUSTANG OPERATING MANUAL
Table 4-5. WHITE CAS MESSAGES
CABIN ALT
High-altitude mode only—In flight, the white CABIN ALT
message appears any time the cabin altitude is between
10,000 and 15,000 feet for less than 30 minutes.
ENG A/I COLD L-R*
Indicates that the engine inlet temperature is below safe level
for satisfactory ice protection. This message will post in white for
up to two minutes after engine anti-ice is turned on while the inlet
warms up to the normal operating temperature.
FUEL BOOST L-R*
Appears when the pilot commands the fuel boost pump on
(by selecting the FUEL TRANSFER knob to L TANK or R
TANK, or by selecting a FUEL BOOST L-R switch to ON, or
during an engine start.
FUEL LO INOP L-R*
Indicates the amber FUEL LVL LO L-R message is not
operational and cannot provide reliable indication of fuel level.
FUEL TRANSFER
Indicates the fuel transfer valve is open.
NO TIRE SPINDOWN
Indicates the antiskid control spindown function is not working.
PRESS CTRL
Indicates failure of the ARINC 429 data link from the G1000
system, indicating that the controller may no longer have
valid data on outside air pressure, actual aircraft altitude,
or destination elevation.
PRESS OFF
Appears when the crew selects the AIR SOURCE SELECT
knob to either OFF or FRESH AIR. This alerts the crew there
is no bleed-air inflow to pressurize the cockpit or cabin. All
pressurization leaks out of the pressure vessel, which causes
it to depressurize.
SPD BRK EXTEND
Indicates the speedbrakes are extended on either side.
STALL WARN HI
Indicates the stall warning system is operating on the
ice-contaminated schedule.
SURFACE DE-ICE
AUTO mode—Indicates when all pressure switches for the
inflation sequence (lower wing/left tail or upper wing/right
and vertical tail) are indicating deice boot inflation. The pilot
must verify the appearance of the white SURFACE DE-ICE
message following activation of the surface deice system
to protect against failures of the WING/STAB switch.
¸
¸
GND
EMER
ESDI
LOPI
AIR
DESCRIPTION
TOPI
MESSAGE
ESI
INHIBITS
¸
¸ ¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
¸
MANUAL mode—Displays if all pressure switches indicate
deice boot inflation.
*Only affected side displayed (L, R, or L-R) in a CAS message; applicable CAS messages listed here display L-R for example.
510OM-00
4-15
CITATION MUSTANG OPERATING MANUAL
Table 4-5. White CAS Messages (Cont)
W/S A/I FAIL L-R*
Normal indication after windshield heat is turned on.
Turns amber if condition exists for more than 5 seconds.
W/S O’HEAT L-R*
Normal indication after windshield heat is turned on.
Turns amber if condition exists for more than 5 seconds.
GND
EMER
ESDI
LOPI
AIR
DESCRIPTION
TOPI
MESSAGE
ESI
INHIBITS
¸
¸
*Only affected side displayed (L, R, or L-R) in a CAS message; applicable CAS messages listed here display L-R for example.
4-16
510OM-00