CITATION MUSTANG OPERATING MANUAL … system (EICAS). ... The Mustang master warning system is pri-marily a function of the G1000 avionics sys-tem. ... CAS Message Type Priority

INTRODUCTIONThis chapter describes the master warning systems on the Citation Mustang aircraft. Themaster warning systems provide a warning of aircraft system malfunctions, indicationsof unsafe operating conditions requiring immediate attention, and indications that somespecific systems are in operation. Audio warnings provide further indications.

GENERALThe master warning system includes a pair ofMASTER WARNING and MASTER CAU-TION lights, and the crew alerting system(CAS) messages. CAS messages are displayedby the G1000 engine indicating and crew alert-ing system (EICAS).

These lights and messages provide a visualindication to the pilots of certain faults, func-tions, and/or conditions of selected systems.Each CAS message indicates an individualsystem situation, or simultaneous situations on

both sides (left and right) of a dual system.Additionally, an audio warning system pro-vides indication of some situations.

CAS messages appear on the EICAS, which ison the left side of the multifunction display(MFD). The pilot and copilot can revert to usingtheir primary flight display (PFD) to view CASmessages. A red DISPLAY BACKUP button oneach audio panel selects reversionary mode,which combines displays from the PFD andMFD (including CAS messages). The combined

TEST

CITATION MUSTANG OPERATING MANUAL

CHAPTER 4MASTER WARNING SYSTEM

510OM-00 4-1

displays appear on both the selected PFD andthe MFD. If the MFD fails, it automatically re-verts CAS messages to the pilot PFD. Whenthe MFD and a PFD are in reversionary mode,the EICAS displays the CAS messages on theupper-right section of both display panels.

NOTECrew alerts associated with the au-topilot, avionics, and engine fire warn-ing/suppress ion are d isp layedelsewhere in the displays or cockpit.The crew alerts are described in thecorresponding chapters in this manual.

The abnormal and emergency procedures in thissection are keyed, where applicable, to the ap-propriate CAS messages. The rotary TEST knobprovides testing for the master warning system.

DESCRIPTIONThe Mustang master warning system usescockpit indications (visual and aural) to ad-vise the crew of important warnings, cautions,and advisory information about the aircraft andits systems.

Pressure sensors , t empera tu re sensors ,switches, and other devices detect conditionsin the aircraft and its systems. This informa-tion is provided as analog signals or discretedigital signals to the G1000 system. Thesesignals are received at the left and right Garminintegrated avionics unit (GIAs), and at the leftand right Garmin engine/airframe interfaceunits (GEAs) (Figure 4-1). A detailed descrip-tion of G1000 system architecture is providedin Chapter 16—“Avionics.”

With the battery switch selected to EMER,only the left GIA and left GEA are powered;


4-2 510OM-00

MULTIFUNCTIONDISPLAY

(INCLUDES EICAS)

NO. 1INTEGRATED

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AIRFRAMEADAPTER(GEA71)

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Figure 4-1. G1000 Block Diagram


CAS messages requiring input from the rightGIA or right GEA are inhibited and do not ap-pear, regardless of aircraft or system condition.

CONTROLS AND INDICATIONSThe Mustang master warning system includes:

• CAS messages

• Master indicators:

• MASTER WARNING lights

• MASTER CAUTION lights

• Aural warnings—Various audio warn-ings are incorporated into aircraft sys-tems that warn of specific conditionsand malfunctions.

Control of the system is provided by:

• CAS scroll softkeys (up and/or down)

• Rotary TEST knob

CAS MESSAGESThe Mustang master warning system is pri-marily a function of the G1000 avionics sys-tem. The CAS displays warning, caution,and advisory messages in response to datafrom aircraft sensors and FADECs.

CAS Message WindowAll CAS messages are displayed in the CASmessage window. The window is on either theMFD, or on one or both of the PFDs:

• Normal display mode—CAS messagewindow is in the bottom left corner of theEICAS display, which appears on theleft side of the MFD (Figure 4-2).

• Reversionary display mode—CAS mes-sage window is on the right side of thedisplay (Figure 4-3, Sheet 1 of 2).

CAS Message TypesCAS messages are in one of three colors: red,amber, or white.

Red (Warning) MessagesRed indicates a warning (hazardous situationthat requires immediate pilot corrective ac-tion). When a red CAS message appears, itflashes in reverse video in conjunction with theMASTER WARNING lights. Pressing theMASTER WARNING light acknowledges themessage, turns off the MASTER WARNINGlights, and changes the CAS message to asteady ON state. Red CAS messages are dis-played until the situation is corrected. All redCAS messages are grouped together at the topof the CAS display window.

Amber (Caution) Messages Amber indicates a caution (abnormal or specialsituation that includes a possible need for fu-ture pilot corrective action). When an amberCAS message appears, it flashes in conjunctionwith the illumination of the MASTER CAU-TION lights. Pressing the MASTER CAUTIONlight acknowledges the message, turns off theMASTER CAUTION lights, and changes theCAS message to a steady ON state.

White (Advisory) MessagesWhite indicates an advisory. This may indicatethe following:

• Abnormal condition

• Change in status of an aircraft system

• Normal operation of a specific device

All white advisory messages are grouped to-gether at the bottom of the CAS message list.When an advisory message appears, the check-list may require an action. If required, find theac t i on i n t he FAA-app roved Abnorma lProcedures Checklist.

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CAS Message Type PrioritySome CAS messages may appear in differentcolors at different times, indicating differentconditions or levels of severity (warning, cau-tion, or advisory). For instance, the CABINALT message may appear in red, amber, orwhite, depending upon various causes andconditions.

However, the same CAS message does not ap-pear in two colors at the same time for thesame side. Each CAS message appears in itshighest-priority color appropriate at the time.

CAS Message DisplaySequenceCAS messages are sorted by color, and thenby the order in which they have been caused:

• Red (warning) messages appear at thetop of the CAS message window, withthe most recent messages first.

• Amber (caution) messages appear after thered messages (with the most recent ambermessage at the top of the amber group).

• White (advisory) messages appear last,with the newest message at the top andthe oldest message at the bottom of thewhite messages.

If a message changes color (due to changingseverity of the condition/indication), the ap-propriate master indicators will appear andthe message moves to the top of the list of theappropriate color group.

CAS Message ScrollingThe CAS message window can only display 14messages. To ensure all valid CAS messagescan be seen when appropriate, the CAS mes-sage window uses a “scrolling list” of all thecurrent valid CAS messages. If more than 14messages are valid, a scroll bar appears onthe right side of the CAS message window(Figure 4-4). A slider in the scroll bar indicateswhich portion of the list is currently visible.

Red warning messages always stay at the topof the CAS messages and are unaffected byscrolling.

Amber caution messages can run off of the dis-play. If an amber message scrolls off, or if thereare too many messages to display all activeamber messages, the scrollbar track changescolor to reflect the color of the message.

At the same time, CAS-scroll buttons (one withan up-arrow and one with a down-arrow) appearon the soft keys at the bottom of the display, al-lowing the pilot to scroll up or down through thecurrent list of CAS messages. When the top ofthe list is visible, only the CAS down-arrowscroll button appears among the soft keys. Whenthe bottom of the list is displayed, only the CASup-arrow scroll button appears.

CAS Message InhibitsMany CAS messages are inhibited (prevented)from displaying during certain phases of air-craft operation, regardless of whether theCAS message would otherwise be valid ornot. These inhibits reduce pilot workload orprevent invalid indications during certainphases of aircraft operation. Different CASmessages are inhibited by different phases ofaircraft operation.

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CAS

OIL PRESS LO LCABIN ALTT2 HTR FAIL RW/S O’HEAT LW/S A/I FAIL LFUEL PRES LO RENG A/I COLD LCABIN DOORAFT DOORP/S HTR LF/W SHUTOFF RFDR FAILSURFACE DE-ICESPD BRK EXTEND

CAS CAS

CAS

OIL PRESS LO LCABIN ALTAFT DOORP/S HTR LF/W SHUTOFF RFDR FAILSURFACE DE-ICESPD BRK EXTENDFUEL TRANSFERFUEL BOOST R

CAS CAS

Figure 4-4. CAS Scroll Buttons


4-8 510OM-00

There are six phases of aircraft operations thatinhibit various CAS messages:

• Engine start inhibit (ESI)

• Takeoff operational phase inhibit (TOPI)

• On ground/in flight (GROUND/AIR)

• Landing opera t ional phase inhib i t(LOPI)

• Engine shutdown inhibit (ESDI)

• Emergency power mode (EMER)

Engine Start InhibitWhen an engine is starting, the ESI for that en-gine inhibits some CAS messages for that en-gine and related systems. This inhibit istriggered by the full-authority digital enginecontrol (FADEC). Each FADEC only inhibitsmessages from its side.

Takeoff Operational Phase InhibitThe TOPI prevents messages from distractingthe flightcrew during takeoff.

TOPI becomes active when any of the follow-ing is true:

• The aircraft transitions from on groundto in air.

• Either indicated airspeed transitions fromless than 50 knots to more than 50 knots.

The TOPI becomes inactive when any of thefollowing is true:

• The aircraft has been in the air for morethan 25 seconds.

• Pressure altitude is more than 400 feetabove the field elevation. The field ele-vation is the pressure altitude capturedwhen the aircraft transitions from onground to in air.

• Either airspeed indication is less than 40knots.

• Both airspeed indications are invalid.

• The TOPI has been active for more than90 seconds.

On Ground/In FlightMessages with the GROUND inhibit do notappear when the aircraft is on the ground,and messages with the AIR inhibit do not ap-pear when the aircraft is in flight. The in-hibits are normally controlled by squat switchindications, but if that fails then GPS groundspeed and air data computer (ADC) are alter-nate sources used by the CAS for setting theseinhibits.

Landing Operational Phase InhibitLOPI activates when any of the following occurs:

• The aircraft transitions from in air to onground.

• Global positioning system (GPS) alti-tude transitions below 400 feet abovefield elevation stored in the terrain data-base.

LOPI becomes inactive when any of the fol-lowing is true:

• The aircraft has been on the ground formore than 25 seconds.

• Either indicated airspeed is less than 40knots.

• Both indicated airspeeds are invalid.

• The LOPI has been active for more than90 seconds.

• Global positioning system (GPS) alti-tude is greater than 600 feet above thefield elevation stored in the terrain data-base.

Engine Shutdown InhibitWhen either engine is shut down, or its FADECdetermines that the engine has failed, the ESDIfor that engine inhibits some CAS messagesfor that engine and related systems. This in-hibit is triggered by FADEC (shutdown indi-cation). Each FADEC only inhibits messagesfrom its side.

Emergency Power ModeTo prevent nuisance messages in emergencypower mode, selected messages are inhibitedwhen the emergency bus is powering the air-craft. Emergency bus status occurs when:

• The battery switch is in the EMER po-sition, and

• Both generator bus input discretes havebeen lost.

The left GIA and the left GEA receive powerin emergency bus mode. However, most of thesensors required to indicate CAS messagesare not powered, so most messages have theEMER inhibit.

Most CAS messages are inhibited in emer-gency mode. Some are inhibited to preventthe flightcrew from being distracted with low-priority issues. Other messages are inhibitedbecause their sources do not receive power inemergency mode. CAS messages without theinhibit are listed in Table 4-1.

MASTER INDICATOR LIGHTSThe master indicator lights (red MASTERWARNING and amber MASTER CAUTIONlights) illuminate to direct pilot attention tonew CAS messages. A MASTER WARNING

and MASTER CAUTION light is on the instru-ment panel above each PFD (directly in frontof the pilot and copilot) (Figure 4-5). Eachmaster indicator light has an integral momen-tary-contact pushbutton switch. Pressing thelight resets the light and acknowledges theCAS message.

NOTEWhen the aircraft is first poweredon, any CAS messages that immedi-ately appear do not cause the masterindicator lights to illuminate. TheCAS considers these messages to bealready acknowledged.

Red MASTER WARNING LightsWhen a new red CAS message appears on theMFD or PFD(s), both red MASTER WARNING


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MESSAGE NOTES GEN OFF L-R 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 Functions normally since the cabin altitude sensor is powered in emergency mode.

Table 4-1. EMERGENCY MODE CAS MESSAGES

Figure 4-5. Master Indicator Lights

lights illuminate flashing. Illumination of theL–R ENGINE FIRE light(s) also triggers theMASTER WARNING lights.

Pressing either red MASTER WARNING lightcloses the switch momentarily, resetting thelight. This extinguishes the MASTER WARN-ING light and stops the CAS message flash-ing (the CAS message remains on until thecondition that caused it is corrected).

If a new red CAS message appears in the win-dow, the MASTER WARNING light flashesagain, and continues flashing until reset. Iftwo or more red CAS messages are flashingat the same time, pressing the MASTERWARNING light once acknowledges themall at the same time.

If the condition that caused the CAS messageis corrected or stops before resetting the MAS-TER WARNING lights, the CAS message andthe red MASTER WARNING lights continueto flash until acknowledged by resetting theMASTER WARNING lights. This is to ensurethe important CAS message is seen by thepilot, even if it is only indicating an intermit-tent condition.

Amber MASTER CAUTIONLightsWhen a new amber CAS message appears onthe MFD or PFD(s), the amber MASTER CAU-TION lights both illuminate steady.

Each MASTER CAUTION light is an integralmomenta ry -con tac t pushbu t ton swi tch .Pressing either MASTER CAUTION lightcloses the switch momentarily, resetting thelight, which extinguishes. If a new amber CASmessage appears in the window, the MASTERCAUTION light illuminates again, and con-tinues illuminated until reset.

When a MASTER CAUTION light is reset,both MASTER CAUTION lights extinguish,and the flashing amber CAS message illumi-nates steady until its indicated condition stopsor is corrected. If multiple amber CAS mes-sages are flashing at the same time, pressing

a MASTER CAUTION light once acknowl-edges them all; all stop flashing and illuminatesteady. If all amber CAS message problems aresolved before the MASTER CAUTION lightsare reset, the MASTER CAUTION lights au-tomatically extinguish.

ROTARY TEST KNOBThe rotary TEST knob (Figure 4-6) is abovethe copilot PFD. Positioning the knob toANNU causes the MASTER CAUTIONlights, MASTER WARNING lights, and otherlights to illuminate (Table 4-2). Illuminationverifies only light emitting diodes (LEDs)lamp integrity.

During rotary test, audio warnings are alsotested and some other associated system indi-cations appear.

CAS MESSAGE DESCRIPTIONTables 4-3 through 4-5 show each CAS mes-sage, including its color and description. Notethat some messages appear in more than onecolor, indicating different conditions. Somemessages are followed by the letters L, R, orL-R, which respectively indicate left, right orboth systems affected.


4-10 510OM-00

Figure 4-6. Rotary TEST Knob


510OM-00 4-11

POSITION INDICATIONS ILLUSTRATIONS

FIRE WARN • Red L ENGINE FIRE and R ENGINE FIRE lights illuminate. • MASTER WARNING lights illuminate.

LANDING • Three green gear downlock lights illuminate. GEAR • 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 • 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.

Table 4-2. ROTARY TEST INDICATIONS

Table 4-3. RED CAS MESSAGES

ES

I

TOP

I

AIR

LO

PI

ES

DI

EM

ER

GN

D

INHIBITS

MESSAGE DESCRIPTION

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.

*Only affected side displayed (L, R, or L-R) in a CAS message; applicable CAS messages listed here display L-R for example.


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ES

I

TOP

I

AIR

LO

PI

ES

DI

EM

ER

GN

D

MESSAGE DESCRIPTION

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).


INHIBITS

Table 4-4. AMBER CAS MESSAGES


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ES

I

TOP

I

AIR

LO

PI

ES

DI

EM

ER

GN

D

MESSAGE DESCRIPTION

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.


INHIBITS

Table 4-4. AMBER CAS MESSAGES (Cont)


4-14 510OM-00

ES

I

TOP

I

AIR

LO

PI

ES

DI

EM

ER

GN

D

MESSAGE DESCRIPTION

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.


INHIBITS

Table 4-4. AMBER CAS MESSAGES (Cont)


510OM-00 4-15

Table 4-5. WHITE CAS MESSAGES

ES

I

TOP

I

AIR

LO

PI

ES

DI

EM

ER

GN

D

MESSAGE DESCRIPTION

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.

MANUAL mode—Displays if all pressure switches indicate deice boot inflation.


INHIBITS


4-16 510OM-00

Table 4-5. White CAS Messages (Cont)

ES

I

TOP

I

AIR

LO

PI

ES

DI

EM

ER

GN

D

MESSAGE DESCRIPTION

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.


INHIBITS

Documents

CITATION MUSTANG OPERATING MANUAL … system (EICAS). ... The Mustang master warning system is pri-marily a function of the G1000 avionics sys-tem. ... CAS Message Type Priority