Caution and warning lights – 400

 for further details press the light –

caution lights are numbered top to bottom and  left to right warning lights are numbered left to right –

 


 


PRESS  - - for direct access to emergency section of QRH Index page

PRESS  - - for direct access to the  MEL(M and P) Ver 3 index page

PRESS  - - for direct access to AFM  Section 2, index     AFM Section 3 and Section 4 (work in progress to come)


PITCH
TRIM

LAC BUS

PITOT HEAT

STBY

ICE DETECT

FAIL

FLT COMPT

DUCT HOT

# 1 HYD

ISO VLV

# 1 PEC

 

# 1 ENG

FUEL PRESS

# 2 ENG

FUEL PRESS

# 2 PEC

 

ROLL SPLR

INBD GND

ROLL SPLR

OUTBD GND

# 1 STALL

SYST FAIL

FLT DATA

RECORDER

ELEVATOR

FEEL

RAC BUS

PITOT

HEAT 1

PITOT

HEAT 2

CABIN

DUCT HOT

# 2 HYD

ISO VLV

# 1 BLEED

HOT

# 1 ENG

HDY PUMP

# 2 ENG

HDY PUMP

# 2 BLEED

HOT

# 1 STBY HYD

PUMP HOT

SPLR

OUTBD

# 2 STALL

SYST FAIL

GPWS

ELEVATOR ASYMETRY

DC BUS

ENG ADPT

HEAT 1

ENG ADPT

HEAT 2

CABIN

PACK HOT

STBY

BATTERY

# 1 DC GEN

HOT

#1 DC GEN

#2 DC GEN

# 2 DC GEN

HOT

ROLL SPLR

INBD HYD

ROLL SPLR

OUTBD HYD

PUSHER

SYST FAIL

PARKING

BRAKE

ELEVATOR PRESS

L TRU

WSHLD

CTRL

PROP

DEICE

FLT COMPT

PACK HOT

MAIN

BATTERY

# 1 AC GEN

HOT

# 1 AC GEN

# 2 AC GEN

# 2 AC GEN

HOT

# 1 RUD

HYD

# 2 RUD

HYD

INBD

ANTI-SKID

OUTBD

ANTI-SKID

R TRU

WSHLD

HOT

DEICE

TIMER

L TRU

HOT

AUX

BATTERY

# 1 HYD

FLUID HOT

# 1 ENG

FADEC

# 2 ENG

FADEC

# 2 HYD

FLUID HOT

RUD

CTRL

FLAP

DRIVE

LDG GEAR

INOP

WT ON

WHEELS

EMER LTS DISARMED

INTERNAL

BAGG DOOR

SIDE WDO

HOT

DEICE

PRESS

R TRU

HOT

AVIONICS

# 1 FUEL

FLTR BYPAS

# 1 TANK

FUEL LOW

# 2 TANK

FUEL LOW

# 2 FUEL

FLTR BYPAS

APU

FLAP

POWER

NOSE

STEERING

FUELING

ON

CABIN

PRESS

CHECK

FIRE DET

SMOKE

TOUCHED

RUNWAY

- - - -

 

- - - -

 

# 1 ENG

OIL PRESS

# 1 ENG

FADEC FAIL

# 2 ENG

FADEC FAIL

# 2 ENG

OIL PRESS

STBY BAT

HOT

AUX BAT

HOT

MAIN BAT

HOT

FUSELAGE

DOORS


S400 Warning Light Panel Descriptions

PRESS     for direct access to the Advisory Lights  note these lights are listed from the top of the cockpit left to right and moving downwards

PRESS    for direct access to REBOOT listing note  these have been listed as they occur

PRESS     for PFD advisories – An alphabetical listing of the pilots function display

PRESS    for MFD advisories Multifunction display messages by page  ie Fuel, Hyd, etc.

PRESS     for Ed advisories  - messages on the Engine display

PRESS     for ARCDU messages

 

 

1.    

CABIN

PRESS

Cabin above 10,000 '

IF

Field elevation input is between 8000-14,500 warning  is reset to 1000' above field elevation to a Max. of 14,500' for the period of climb and or descent.

Cab Alt--check

If >8000'

Bleed Max

If Auto try alternate mode

If still   >8000'

Descend belo 14,000 asap

MELP 21

Warning light, Alt ind, dif press, rate, control and outflow vlvs  pages 7-19

FSI 21-00-00 P6 as amended in consultation with DH(carlos) system expert.

AFM 4.16.6

2.    

CHECK

FIRE DET

Engine fire detected in an engine or APU

Or

Fire loop failure or Bottle low??

shutdown

Test detection switch  Eng and APU

 

MELP 26 no known relief

FSI 26-00-00 p 19

AFM 3.1

AFM  4.10.

3.    

SMOKE

Smoke in forward or aft Baggage department

AFT

Check vents close and Aft Arm al.

Smoke/Extg switchlight – Press

Arm al out, Low al, Check Fire Det wl, Fwd low al after 30 min.

Land ASAP

FWD

Fwd Arm al.

Smoke/Extg switchlight – Press

Arm al out, Low al, Check Fire Det wl, AFT low al after 30 min.

Land ASAP

Smoke test will fail if direct?? Sunlight on detector.  Close bag door and retest, known prob.  noted in Fsi document.

MELP 26

FSI 26-00-00 p 19

AFM 3.4..2

4.      

TOUCHED

RUNWAY

Fuselage contact with the runway

Do not fly, inspection required

MELP 32-60-1

 

AFM 3.17.1

5.      

--

 

 

 

 

6.      

--

 

 

 

 

7.      

#1 ENG

OIL PRESS

Oil pressure less than 44 psi

shutdown

 

nilmel

AFM 3.2.5

8.      

#1 ENG

FADEC FAIL

Critical Fault within the Fadec Controller

Affected Power Lever  - Flt Idle and Condition lever to Fuel Off.

May cause engine to shutdown automatically or may continue to run at Flt Idle.

Note: with an engine intake fuel temp greater than 70° C gives this fault. Open cowl and cool engine??

ER 3590 Rev 2.1 PW150a Electrical Interface Doc. Pg. 167

AFM 3.2.6

9.      

#2 ENG

FADEC FAIL

Critical Fault within the Fadec Controller

Affected Power Lever  - Flt Idle and Condition lever to Fuel Off.

May cause engine to shutdown automatically or may continue to run at Flt Idle.

Note: with an engine intake fuel temp greater than 70° C gives this fault. Open cowl and cool engine??

ER 3590 Rev 2.1 PW150a Electrical Interface Doc. Pg. 167

AFM 3.2.6

10.    

#2 ENG

OIL PRESS

Oil pressure less than 44 psi

shutdown

 

nilmel

AFM 3.2.5

11.    

STBY BAT

HOT

Stby Battery temperature hot (> 65°C).

Confirm Bat overheat on MFD.

Select Stby Bat switch to Off.

If battery temperature continues to rise, land as soon as possible.

MELP 24 indication

AFM 3..7.11

12.    

AUX BAT

HOT

Aux. Battery temperature hot (> 65°C).

Confirm Bat overheat on MFD.

Select Stby Bat switch to Off.

If battery temperature continues to rise, land as soon as possible.

MELP 24

indication

AFM 3..7.11

13.    

MAIN BAT

HOT

Main Battery temperature hot (> 65°C)..

Confirm Bat overheat on MFD.

Select Stby Bat switch to Off.

If battery temperature continues to rise, land as soon as possible.

MELP 24

indication

AFM 3..7.11

14.    

FUSELAGE

DOORS

A door microswitch indicates not closed and locked.

.

On Gnd

Check MFD. Inspect and secure

In Flight

Fasten belt/no smoke--     On

Check MFD

Depressurize

Land ASAP

MELP 52

52-10-5 warning system

Warning

Do not attempt to secure door

If take-off occurs with this warning light on (flicker at the correct moment)aircraft pressurization is inhibited in auto mode

(Go manual and pressurize if needed??)

Each door  has a close handle over-center prox switch and a door ‘shift’ Prox switch.(Exception is of 2/3 exit which is a plug door with a prox switch on the top retaining pin.)

   For a door to shift door  must  move inward against pressure (design of retainers). Most (all??) door warnings are from handle over center prox switch.

FSI 01-00-00 p 14:

AFM 3 13 .1/2

LTS-S400-LSDS-001-B Issue 3 23/06/97

 


 

S400 Caution Light Panel Descriptions

 

1.      

PITCH

TRIM

FCECU detects loss of ability to command or control actuator, or airspeed 1 & 2 disagreement, or disagreement between two control column trim switches when on ground

Maintenance action before next flight

See QRH 10.7

Autopilot off

Test trim

if use autopilot

ifno maintain config as possible

see defaults to trim and flap below rt

 

 

This tested on ac 4042 4/6/01

Airspeed mismatch (26K) gives Elevator feel, Pitch trim, Rud control,and Splr outboard caution lights, will reset 5 X -after latches

Recent occurrences due poor pitch trim actuators. Can be evaluated on ground by simulating airborne(druk at 230k), autopilot on,  and moving control column back and forth.

See reboots 8a            See reboots 9  

AFM  4-18-2

lear SR406475-01 rev a pg 12/23: parker man p C43

MELP 27 and

27-30-1 and 22-10-2

2.      

ELEVATOR

FEEL

 Either FCECU detects loss of ability to command or control actuator, or airspeed 1 & 2 disagreement, or normal acceleration 1 & 2 disagree

 

Note seen with AHRS failure (ATT and HDG flag)

 

See reboots 8

Autopilot –Off

Max airspeed –200K

 

NOTE Loss of airspeed indicator and altimeter has occurred giving 4 cl +Roll splr outbd hyd cl along with autopilot and yaw damper fail. This due to ice in copilots line. Mod has rerouted line?? See reboots See reboots

IOM/IOP fail Has been accompanied with, Elevator Feel cl, Avionics cl, FD nav Data invalid, Autopilot and YD fail

Airspeed mismatch (26K) gives Elevator feel, Pitch trin, Rud control,and Splr outboard caution lights will reset 5 X after latches

Actuator remains in last position when FCECU command  fails

When Airspeed fail, and when flap 5  actuators default to 160k position, when flap 15 actuators default to 130k position.

If Airspeed and flap fail actuators default to 160K position

If acceleration failure FCECU defaults pitch feel gain schedule to 0.

AFM  4-18-7

lear SR406475-01 rev a pg 12

 

nilmel 27

3.      

ELEVATOR

ASYMMETRY

Left and Right elevator mismatch >3.4±1.6 at speeds above 185k, at ,185 tolerance is reset to 6 deg ±1.6

(Sb 84-27-14 changes this to reduce occurance)

Autopilot --Off

 Airspeed , 200 kts

 

See Reboots 25

nilmel 27

see also letters of explanation 16

This condition is a latch that will reset on ground if condition no longer exists

(This has been seen when disconnecting the autopilot when under control column pressure.and poor cable rigging load)

AFM 4.18 5

lear SR406475-01 rev a pg 13

CM # dhi/pba-424-99

4.      

ELEVATOR

PRESS

Hydraulic pressure in all three hydraulic systems.

Check Hydraulic Press #3, if O.K., then check Hyd 3 Isol Valve for normal(blank switchlight/not OPEN), if O.K., then autopilot disengage and max airspeed 200 kts

Note: isol valve fails operational (depowered on)

See reboots 15/16

nilmel 27

AFM 4.18.6

FSI 29.00.00 p 31 amended

Parker r-2920772 p 31

5.      

#3 STBY

HYD PUMP

#3 hyd system accumulator pressure low (<900 psi)

OR on ground

Pump running continuously 60 sec.

Rectify before next flight.

 

Note: system (pump) is not operational on ground without engine running. Except on aircraft power up(PSEU does bite test to airborne). Pressure will bleed down dependant on time, temp and wind conditions(elevator control lock)

Repressurize using Isolation valve and observe cl out.

Pump operates when system (accumulator)  indicated low pressure (<2600 psi) and ISOL valve open. OR

when system low pressure and airborne OR

when system low pressure and an engine is operational (oil press).

 

AFM 4.12.6

FSI 20-00-00

p 31

MELP 29 various

6.      

EMER LTS

DISARMED

Emergency lights not armed

Select Emergency Lights to Arm.

Powered from L Main

MELP 33 pages 19-21


 

7.      

L AC BUS

L AC Bus fault detected.

None.

Note:  Some operators have rebooted by selecting gen off then on if occurs on CL to max.

Indicated bus loses power.

AFM 3.7.9.

Nilmel 24

8.      

R AC BUS

R AC Bus fault detected.

None.

Note:  Some operators have rebooted by selecting gen off then on if occurs on CL to max.

Indicated bus loses power.

AFM 3.7.9.

Nilmel 24

9.      

DC BUS

DC bus fault detected

 

Usually with other cl and pfd fail on faulted side.

Wait for 10 sec.:

If no further caution lights illuminate:

1. Bus Fault switch - Reset

If batteries and a generator caution light illuminate:

1. Turn off those batteries and generator.

2. Bus Fault switch - Reset

If power is restored to the faulted main bus(dc bus cl light out) , proceed; if not, land as soon as possible.

All bus ties open

(400 amp draw on DC generator).

A RH dc bus fault causes loss of #2 ADU, thus FGC can not compare and HYD systems (IE spoilers and rud) that use airspeed input are faulted giving caution lights.  sel operating side??

A LH dc bus fault results in loss of Bleed air. (LH Min, RH Off)and Out flow auto control. Result is aircraft depressurized.  E Descent possible and Cab Press wl??

AFM 3.7.1

Nilmel 24

10.    

L TRU

L TRU Inoperative.

Depower with circuit breaker

MELP 24-30-1

AFM 3.7.2

11.    

R TRU

R TRU Inoperative.

Depower with circuit breaker

MELP 24-30-1

AFM 3.7.2

12.    

INTERNAL

BAGG DOOR


Forward baggage compt door is not latched closed (upper  latch)

Or with new cockpit door  - a door is open

Close and latch the door.

MELP 52 various

 

AFM 4.22.1

13.    

PITOT HEAT

STBY

Lack of power to the Pitot Heating circuit

Select the Stby Pitot Heat to On.

If abnormal airspeed or alt on a PFD select EFIS ADC Source  selector 1 or 2 as appropriate

Dc powered Rt Essential L7

Fsi

AFM 4.11.5

MELP 30 see 30-15, 16

14.    

PITOT

HEAT 1

Lack of power to the Pitot Heating circuit

Select the Pitot Heat 1 to On.

If abnormal airspeed or alt on a PFD select EFIS ADC Source  selector 1 or 2 as appropriate

AC powered Phase C

Fsi

AFM 4.11.5

MELP 30 see 30-15, 16

15.    

ENG ADPT

HEAT 1

No heat in intake adapter heater for the #1 side

Monitor affected engine performance and exit icing conditions as soon as possible.

Single failure is stored in a maintenance message.

On at 15°C off at 10°C.

AFM  4.17.5

MELP 30 see 30-10, to 14 and MELP 71-60-1

16.    

WSHLD

CTRL

No Heat or Failure to operate (temp. not within tolerance) after 5 min.

 

Avoid icing condition if possible.

Reboot 34 is off on

Left/Right Controller disagreement    OR

Temperature sensor failure   OR

Controller Failure    OR,   not up to temp, Or  Overheat

Normal on with props in Feather

AFM 4.17.7

MELP 30-40-2

17.    

WSHLD

HOT

Left or Right windshield has overheated (50°C) and is automatically disconnect from power source

1.      Windshield Heat selector switch - Warm Up( if warm up off)

2.      Avoid icing condition if possible

(Normally control at 34°C).

Reboot 34

AFM 4.17.7

MELP 30-40-2

18.    

SIDE WDO

HOT

Pilot's side window has overheated (50°C) and is automatically disconnect from power source.

Pilot Side Wdo/Ht switch to Off

 

AFM 4.17.7

MELP 30-40-2

19.    

ICE DETECT

FAIL

Failure of both ice detectors.(probes)

Use wiper probes to detect ice.

Single failure is stored in a maintenance message.

 

AFM 4.17.9

MELP 30-80-2

 

20.    

PITOT

HEAT 2

Lack of power to the Pitot Heating circuit

Select the Pitot Heat 2 to On.

If abnormal airspeed or alt on a PFD select EFIS ADC Source  selector 1 or 2 as appropriate

AC powered R phase C

Fsi

AFM 4.11.5

MELP 30 see 30-15, 16

21.    

ENG ADPT

HEAT 2

No heat in intake adapter heater for the #2 side

Monitor affected engine performance and exit icing conditions as soon as possible.

Single failure is stored in a maintenance message.

On at 15°C off at 10°C.

AFM  4.17.5

MELP 30 see 30-10, to 14 and MELP 71-60-1

22.    

PROP

DEICE

May not have  Prop deice

 

Note

This cl will be on with an engine shutdown and selector on  Mod coming??

 

See reboots11

Off On one time

Operate props at 1020 Np until clear of icing conditions.

Exit icing conditions as soon as possible.

Selector remains on

 

are 27 possible faults summarized as follows:

AC  current or power problems,

Communication between or  problem within or loss of controller,

Loss of ADU data Some Faults latch , some do not.

See reboots 11

Dowty POR2280 issue 4 p 10

AFM 4.17.4

MELP 30 various

23.    

DEICE

TIMER

Failure of the boot-sequencing timer.

Sequencer,logic or input disagreement.

If advisory sequencing on boot inflation is not correct, use Manual selector.

Exit icing ASAP

 

AFM 4.17.2

MELP 30 various

24.   24

DEICE

PRESS

Airframe deice system pressure low (12 down 15 up) or a boot pressure not as it should be.

ISO

Check deice press

Check panel

Select mode to manual

Rotate manual selector

Exit icing ASAP

Use appropriate additives to speed

Low pressure detection is from both sides of the isolation valve or from any distribution valve.

 

See reboots 28cd after manual ops try auto again  manual turns on heaters directly

Scmatics

Aerazur presentation, pg 4

FSI 12-20

AFM 4.17.1

MELP 30 various

25.    

FLT COMPT

DUCT HOT

Duct temp hot (exceeds 190°F)

Cabin Gauge selector --to appropriate  Duct position

 

appropriate pack --Off  

Bleed selector-- Max

If overtemp. condition is not corrected

Bleed air  is shutoff at the pack

Descend to below 14t' and ram air ventilation is required

Normal operation is interrupted, the pack valve closes and caution light will remain on until the pack switch is cycled to Off

FSI 21-00-00 p 28 verified

Ham Standard Fam training P 39

AFM 4.16.3

MELP 21 various

26.    

CABIN

DUCT HOT

Duct temp. hot (exceeds 190°F )

Cabin Gauge selector --to appropriate  Duct position

appropriate pack --Off  

Bleed selector-- Max

 

If overtemp. condition is not corrected

Bleed air  is shutoff at the pack

Descend to below 14t' and ram air ventilation is required

Normal operation is interrupted, the pack valve closes and caution light will remain on until the pack switch is cycled to Off.

FSI 21-00-00 p 28

Ham Standard Fam training P 39

AFM 4.16.3

MELP 21 various

27.    

CABIN

PACK HOT

Pack output hot (exceeds 450°F)

Pack --Off

Bleed--Max

If overtemp. condition is not corrected

Bleed air  is shutoff at the pack

Descend to below 14t' and ram air ventilation is required

Normal operation is interrupted, the pack valve closes and caution light will remain on until the pack switch is cycled to Off or Man.

FSI 21-00-00 p 28

Ham Standard Fam training P 39

AFM 4.16.2

MELP 21 various


28.  

FLT COMPT

PACK HOT

Pack output hot  (exceeds 450°F)

Pack --Off

Bleed--Max

If overtemp. condition is not corrected

Bleed air  is shutoff at the pack

Descend to below 14t' and ram air ventilation is required

Normal operation is interrupted, the pack valve closes and caution light will remain on until the pack switch is cycled to Off or Man.

FSI 21-00-00 p 28

Ham Standard Fam training P 39

AFM 4.16.2

MELP 21 various

29.    

L TRU

HOT

L TRU hot

L Tru Circuit breaker – pull ( 115 Var AC Bus)

MELP 24-30-1

Busses x tie no loss of service

monitor load on test aircraft if<1.0 load-shed FE posn .

AFM 3..7.4

Allied signal para 3.6.1

30.    

R TRU

HOT

L TRU hot

R Tru Circuit breaker – pull ( 115 Var AC Bus)

MELP 24-30-1

Busses x tie no loss of service

monitor load on test aircraft if<1.0 load-shed FE posn .

AFM 3..7.4

Allied signal para 3.6.1

31.    

# 1  HYD

ISO VLV

Partial loss of #1 Hyd system quantity.

 

Pressure downstream of #1 isolation valve low (900-1500 off on). Isolation  valve closed.

 

Inboard spoilers, flap, toe brakes systems lost.

See QRH for approach and field length increases

Close activated, in a normal system, by low quantity in reservoir . check for leaks.

Often accompanied by other  subsystem associated Caution Lights.

Nilmel 29 maybe

 

AFM 4.12.3 and 4.21.1

Parker R-2920772 p25/31

Drawing no R 2920772 p 32-33 and 83-83

32.    

# 2  HYD

ISO VLV

Partial loss of #2 Hyd system quantity.

 

Pressure downstream of #2 isolation valve low (900-1500 off on). Isolation  valve closed.

 

Outboard spoilers, normal gear operation, nosewheel steering, and replenishment of Emerg Brake functions lost

See QRH for approach and field length increases

Close activated , in a normal system, by low quantity in reservoir , check for leaks.

Often accompanied by other associated Caution Lights.

Nilmel 29 maybe

AFM 4.12.3 and 4.21.1

Parker R-2920772 p25/31

Drawing no R 2920772 p 32-33 and 83-83

33.    

STBY

BATTERY

Stby Battery is disconnected from the charging source.

Stby Battery switch - Off then On.

If Light remains illuminated then switch Off.

Normally on when DC ground power connected (customer option).

Nilmel 24

FSI 29 Aug

Pg. 70

AFM 3.7..8

34.    

MAIN

BATTERY

Main Battery is disconnected from the charging source.

Main Battery switch - Off then On.

If Light remains illuminated then switch Off.

Normally on when DC ground power connected (customer option).

Nilmel 24

FSI 29 Aug

Pg. 70

AFM 3.7.6

35.    

AUX

BATTERY

Aux Battery is disconnected from the charging source.

Aux Battery switch - Off then On.

If Light remains illuminated then switch Off.

Normally on when DC ground power connected (customer option).

Nilmel 24

FSI 29 Aug

Pg. 70

AFM 3.7.7

36.    

AVIONICS

An Avionics “No Dispatch “ condition is sensed when aircraft is on ground.

Result of DU bad config.

 

Cl acts as master for various problems

See AFM p 4-20-1 for list of possible system failures and accompanying messages on ED.

see reboots 13  and ED messages 16

AFM 4.20.2.1

MELP ?

37.    

# 1 PEC

Prop electronic controller failed 

Do not select affect Power Lever aft of Flight Idle on landing.

Loss of Beta Information  Or

Engine Speed Information  Or

Power Lever Angle  Or

Loss Cross-side Information  Or

Unstable Power Supply

AFM 3.3.1

nilmel 91

38.    

# 1 BLEED

HOT

System powered and Bleed hot, overpressure, or bleed leak detected

#1 Bleed-off

if both

then descend and ram ventilate

 

see reboots 28ab

Bleed leak could give both bleed hot lights

Is connon prob with faulty bleed valves at this time  tap valve(?) will get you goiung

AFM 4.16.1

Ham Standard p33 feb 198

nilmel?

39.    

# 1 DC GEN

HOT

Generator hot

Gen -off

Light may remain on, continued operation is permissible

AFM 3.7.12

Nilmel24


40.  

# 1 AC GEN

HOT

Generator hot

Gen -off

Light may remain on, continued operation is permissible

AFM 3.7.12

Nilmel24

41.    

# 1 HYD

FLUID HOT

#1 Hydraulic reservoir hot

Monitor pressure and quantity of affected hydraulic system

temperature switch exceed 225°F.

If temperature exceeds 275°F then hydraulic firewall shut-off valve closes.

MELP 29-30-12

AFM 4.12.4

FSI 29-00-00 p18

Parker R 2920772p 31

42.    

# 1 FUEL

FLTR BYPAS

Pressure drop across high pressure fuel filter high.

Monitor engine performance.

Indicates impending filter bypass. Full bypass indicated by erratic readings of nh itt etc.

AFM 4.9.5

Nilmel 28

43.    

# 1 ENG

FUEL PRESS

Fuel tank fuel pressure supply to engine is low

Aux. pump –On.

Check al on and  cl out.

If cl not out.

Aux. pump off and check for fuel leaks.

If leaks –shutdown engine

Ejector pump fail, or motive flow failure.

AFM 4.9.1

Nilmel 28

44.    

# 1 ENG

HYD  PUMP

Engine driven pump #1 pressure low (<1800 psi,)

 OR

Condition lever #1 position at fuel cut-off.

If no loss of fluid

Stby Hyd Press switchlight  – Press on

otherwise

Inboard spoilers, flap, toe brakes, #1 rudder, and #1 elevator systems are lost.

See QRH for increased approach speeds and landing field lengths.

Do not select PTU on.

Flap extension rate  decreased.

#3 hyd system is on automatically.

AFM 4.12..1

& 2

Parker R-2920772 p 31

MELP 29-30-9 caution lights

45.    

# 1 DC GEN

#1 Gen is off- or failed

Affected Gen switch Off, then On.

If cl. remains on, the Gen switch Off

MELP 24

AFM 3.7.3

46.    

# 1 AC GEN

#1 Gen is off- or failed

Affected Gen switch Off, then On.

If C.L. remains on, the Gen switch Off

EPCU sheds galley loads on failure of AC Gen

MELP 24

AFM 3.7.10

 

47.    

# 1 ENG

FADEC

Full authority digital electronic control has a cautionary fault

Adjust affect power lever slowly and smoothly and do not select Power Lever aft of Disc on landing.

 

AFM 3.2.7

FSI 17-58Generator

48.    

# 1 TANK

FUEL LOW

Fuel quantity in collector bay low (< 400 lbs).. and

Park brake off  and

Engine running

Check tank. If low  Xfer fuel.

If not low.

Continue and monitor eng.

When scavenge system not operating or flapper valve open, cl. will be on with 2000 lbs. remaining in tank.

Note Service letter 49-003  -min fuel qty left tank is 1000 pounds for APU running. APU uses 185 lbs per hr

Flight Test

TC.

AFM 4.9.3.

49.    

# 2 ENG

FUEL PRESS

Fuel tank fuel pressure supply to engine is low

Aux. pump –On.

Check al on and  cl out.

If cl not out.

Aux. pump off and check for fuel leaks.

If leaks –shutdown engine

Ejector pump fail, or motive flow failure.

AFM 4.9.1

Nilmel 28

50.    

# 2 ENG

HYD  PUMP

Engine driven pump #2 pressure low (<1800 psi)

 OR

Condition lever #1 position at fuel cut-off.

If no loss of fluid

PTU CNTL  switchlight  – Press on

otherwise

Outboard spoilers, normal gear retraction and extension, nosewheel steering, #2 rudder, and  #2 elevator systems are lost.

Emerg Brake will not replentish.

See QRH for increased approach speeds and landing field lengths.

#3 hyd system is on automatically.

AFM 4.12..1

& 2

 

Parker R-2920772 p 31

MELP 29-30-9 caution lights

51.    

# 2 DC GEN

#2 DC Gen is off or failed

Affected Gen switch Off, then On.

If C.L. remains on, the Gen switch Off

 

AFM 3.7.3

52.    

# 2 AC GEN

#2 AC Gen is off or failed

Affected Gen switch Off, then On.

If C.L. remains on, the Gen switch Off

EPCU sheds galley loads on failure of AC Gen

AFM 3.7.10

53.    

# 2 ENG

FADEC

Full authority digital electronic control has a cautionary fault.

Adjust affect power lever slowly and smoothly and do not select Power Lever aft of Disc on landing.

 

AFM 3.2.7

 

Fsi 17-58

54.    

# 2 TANK

FUEL LOW

Fuel quantity in collector bay low (< 400 lbs).. and

Park brake off  and

Engine running

Check tank. If low  Xfer fuel.

If not low.

Continue and monitor eng.

When scavenge system not operating or flapper valves open, cl. will be on with 2000 lbs. remaining in tank.

Flight Test

TC

AFM 4.9.3.

55.    

# 2 PEC

Prop electronic controller failed

Do not select affect Power Lever aft of Flight Idle on landing.

Loss of Beta Information  Or

Engine Speed Information  Or

Power Lever Angle  Or

Loss Cross-side Information  Or

Unstable Power Supply

AFM 3.3.1

56.    

# 2 BLEED

HOT

System powered and Bleed hot, overpressure, or bleed leak detected

#2 Bleed-off

if both

then descend and ram ventilate

see reboots 28ab

Bleed leak could give both bleed hot lights see bleed 1

AFM 4.16.1

Ham Standard p33 feb 198

nilmel?

57.    

# 2 DC GEN

HOT

Generator  hot

Gen -off

Light may remain on, continued operation is permissible

AFM 3.7.12

Nilmel24

58.    

# 2 AC GEN

HOT

Generator hot

Gen -off

Light may remain on, continued operation is permissible

AFM 3.7.12

Nilmel24

59.    

# 2 HYD

FLUID HOT

#2 hydraulic reservoir hot

Monitor pressure and quantity of affected hydraulic system

temperature switch exceed 225°F

.If temperature exceeds 275°F then hydraulic firewall shut-off valve closes.

MELP 29-30-12

AFM 4.12.4

FSI 29-00-00 p18 parker r-2920772 p31

60.    

# 2 FUEL

FLTR BYPAS

Pressure drop across high pressure fuel filter high.

Monitor engine performance.

Indicates impending filter bypass. Full bypass indicated by erratic reading

s of nh itt etc.

AFM 4.9.5

Nilmel 28

61.    

ROLL SPLR

INBD GND

Fcecu unable to control an inboard spoiler

Affected spoilers may not extend at touchdown. See QRH for airspeed and field length increases.

 

Note If both See reboots 8 or  nuisances warning SL page 6

 

Selection of taxi switch on ground initiates a BITE test of lift/dump valves

If FECU detects a spoiler panel extended cl is illuminated. No Dispatch

 

AFM  4-18-9

lear SR406475-01 rev a pg 15

AEROC 84.6.CF.1 Sect2.2 p 23

MELP 27-60-1 & sup17

62.    

#1 STBY HYD

PUMP HOT

Standby hydraulic motor is hot.

If flap >0 –no action required

If flap 0 Stby Hyd Press –Normal.

 

AFM 4.12.5

parker r-2920772 p31

63.    

ROLL SPLR

INBD HYD

#1 hyd system low at spoilers

or

if both splr hyd cl then spoiler cable break

See QRH for increased approach speeds and landing field lengths.

MELP sup17

 

AFM 4.18.10

lear reva p 16

AEROC 84.6.CF.1 sec2.2 p 23

64.    

# 1 RUD

HYD

Loss of hyd pressure to  #1 actuator (<550psi) 

If seen on startup/shutdown indicated FCECU has not seen app bal between input and output hyd press to rud system within 5 or 10 sec. See Sl 27-007.

When not associated with shutdown or Push Off switchlight:

Maintenance action before next flight

FECU shutdown PCU or

pilot pressed RUD I Push Off switchlight.

Fecu automatically adjust pressure to other actuator

 

See reboots 8b

FSI 27-00-00 p 16 &

AFM 4.18.14

65.    

RUD

CTRL

Fecu unable to control rudder pressure,

or both hyd systems failed,

or airspeed mismatch.

 

Max IAS 200k

Airspeed mismatch gives Elevator feel, Pitch trin,  Rud control, and Splr outboard caution light.

In event of airspeed mismatch rud defaults to 700 psi, when flaps seen as<15 rud press defaults to 1225 psi.

See reboots 8

FSI 27-00-00 p 16

AFM 4.18.13

66.    

APU

APU FADEC sensed a failure (fire, Gen, overheat, fail to start) and shutdown APU.

As appropriate

Restart auto limited to1/2,1/2,1/30(70)

See reboots 31 a

AFM  Sup 6

67.    

ROLL SPLR

OUTBD GND

Fcecu unable to control an outboard spoiler

Affected spoilers may not extend at touchdown. See QRH for airspeed and field length increases.

 

Note If both See reboots 8 or  nuisances warning SL page 6

Selection of taxi switch on ground initiates a BITE test of lift/dump valves

If FECU detects a spoiler panel extended cl is illuminated. No Dispatch

 

AFM  4-18-9

lear SR406475-01 rev a pg 15

AEROC 84.6.CF.1 Sect2.2 p 23

MELP 27-60-1 & sup17

68.    

SPLR

OUTBD

Outboard spoiler pressurized above 165 kts

or

Spoilers locked out below 150 K

Note if above, cl below is also on

Max airspeed 200 kts.

Airspeed lockout is 175 k rising and 165k falling

Airspeed mismatch gives Elevator feel, Pitch trin, Rud control,and Splr outboard caution lights

In this failure above 165 spoilers remain down till flap 5 selected.

AFM  4-18-8

lear SR406475-01 rev a pg 15

and flight test

AEROC 84.6.CF.1 sec2.2 p 23

69.    

ROLL SPLR

OUTBD HYD

#2 Hyd system pressure low at spoilers

or

see dual light comment above

or

if both splr hyd cl then spoiler cable break

See QRH for increased approach speeds and landing field lengths.

Mel see sup17

 

AFM 4.18.10

lear rev a p 16

AEROC 84.6.CF.1 sec2.2 p 24

70.    

# 2  RUD

HYD

Loss of hyd pressure to  #2 actuator (<550psi).

If seen on startup/shutdown indicated FCECU has not seen app bal between input and output hyd press to rud system within 5 or 10 sec. See Sl 27-007.

When not associated with shutdown or Push Off switchlight:

Maintenance action before next flight

 

FECU shutdown PCU or

pilot pressed RUD I Push Off switchlight. Fecu automatically adjust pressure to other actuator

See reboots 8b

FSI 27-00-00 p 16 &

AFM 4.18.14

lear Rev a pg 20

71.    

FLAP

DRIVE

.Flap degraded operation

Flap drive fault.

May remain in last selected position

Flap Control Unit (FCU) fault. Detection of hyd pressure without selection command, failure to operate, or some internal electrical failures ie shuttle valve fails to close after selection.

AFM 4.13 1

72.    

FLAP

POWER

Flap system failure.

 

.

Reset cb L7 one time.wait 15 sec try again

Flaps inop.  Remain in last selected position

See reboots 17

See also procedure for rebooting NVM Memory Loe #10

Also  LOE 11

Flap Control Unit (FCU) Fail.  Detection of asymmetry, uncommanded movement, position or lever transducer failure, no hyd pressure after selection, failure to arm, electrical failure or electrical component failures

AFM 4.13 2

73.    

# 1 STALL

SYST FAIL

System inoperative

May be with CUE  message

Autopilot –off

 

MELP section flight controls (ATA 27) and see sup11 20% MAC

 

See reboots 4

Failed self test, or both AOA or  both Shaker failure

 A single AOA failure, discrepancy or Shaker failure or Flap, Mach, de-icing input failure is indicated 30 sec after landing.

 

AFM  4.11.6

Aeroc 84.6.R.26 p40

74.    

# 2 STALL

SYST FAIL

System inoperative

May be with CUE  message

Autopilot –off

 

MELP section flight controls (ATA 27) and see and see sup11 20% MAC

 

See reboots 4

Failed self test, or both AOA or  both Shaker failure

 A single AOA failure, discrepancy or Shaker failure or Flap, Mach, de-icing input failure is indicated 30 sec after landing.

AFM  4.11.6

Aeroc 84.6.R.26

75.    

PUSHER

SYST FAIL

System inoperative

 

 

See  reboots # 4

Note on new l ( mod126263 or 457056) ptfg with ra disconnects will give cl after landing. If testing old system and release of test switch prior to shaker you will get cl  - retest correctly cl goes out.

Autopilot –off

Stick Pusher Shutoff Switchlight – Press

 

MELP section flight controls (ATA 27) see sup11 20% MAC

Failed self test or either Stall system failure or either glareshield Stick Pusher Shutoff switchlight is pressed, or pusher or feedback failure or AOA failure or discrepancy

Flap, Mach, de-icing input failure are indicated  30 sec after landing

See reboots 3

AFM  4.11.6/7

Aeroc 84.6.R.26

76.    

INBD

ANITSKID

Switch is selected off or computer senses a  malfunction

AntiSkid  -On

Apply brakes using Manual technique

See QRH for cautions and Landing distances

 

 

Test position will give a 6 sec light on gnd and 3 sec in air when gear in down and locked

Manual technique- intermittant application of 1 sec intervals

Msi 324000/01/6 rev A-1

AFM 4.15.2

 MELP 32-40-2  & AFM. Sup 7

77.    

LDG GEAR

INOP

Gear sequence malfunction or inhibit selected to inhibit

.

Alt Gear extension (free fall) checklist

Speed 185 .

Landing gear control output fails;

Retract and extend command not in complimentary states;

Landing gear inhibit switch selected to inhibit;

A downlock sensor fails and its redundant sensor does not report downlock

Inhibit switch disables both up and down selection and gear door activation.

BF Goodrich MSI No 326100

 system 323-60-00 REV a 11/20/97

AFM 4.21..1

78.    

NOSE

STEERING

Nosewheel steering switch on and ECU has detected a failure or

Hydraulic SOV remains open after Steering selected off

Center nosewheel

If light remains Steering -Off

Taxi using diff brakes and power ???

 

SUP requires  no contamin runway,25kX wind

System deactivated by WOW alt system 5 sec after take-off

If ECU self test failure occurs, SOV closes, system is put in free castor mode and caution light is illuminated (not airborne??)

??? sov failure will it castor???

See reboots 40

Aeroc 84.6/sect 7.3p4 issue 1  doc d-535

AFM 4.14..2

Mel 32-50-1see sup 08

79.    

FLT DATA

RECORDER

Off or Malfunction

Check and reset cb F3 L main

If not cb pull

MELP 31-30-1

Afm Sup 1

80.    

GPWS

System unservicable

 

MELP 34

Suggest  40-4  and 40-5

AFM sup 2

AFM sup 64 for  EGPWS

81.    

PARKING

BRAKE

Lever selected to Park

 

MELP 32-40-1 for pressure indicatins

 

82.    

OUTBD

ANTISKID

Switch is selected off or computer senses a  malfunction.

 

AntiSkid  -On

Apply brakes using Manual technique

See QRH for cautions and Landing distances

 

Test position will give a 6 sec light on gnd and 3 sec in air when gear in down and locked

Manual technique- intermittent application of 1 sec intervals

Msi 324000/01/6 rev A-1

MELP 32-40-2  & AFM. Sup 7

83.    

WT ON

WHEELS

Multiple non functioning sensors or disagreement between functioning sensors.

Complete flight.

 

 

NOTE Have had spoilers fail to extend on touchdown and props fail to go into reverse due same equation!!! And nose wheel fail to operate  As result of poor wow sensor. and as result of high oleo pressure.

Two circuits check WOW sensors. Landing gear may not retract. Maintenance action required.

Some of the other systems taking WOW information are: Nose wheel steering, Normal brakes, Gnd spoilers, Clocks, plus FDR, Stall warn, TO warning, Prop speed, EFIS cold start, Cabin Press, SPU turn on, Main buss batteries, APU.

AFM 4.23.1

BF Goodrich DOE D-3058 and DHC 8 prox-icd

84.    

FUELING

ON

Activated when fueling panel door is open. Which renders panel powered

Close fueling panel door.

 

MELP 28-40-3 for light

No config without door at this time 5/11/05

Arms the master refuel/defuel shut-off valve when door is open.

Transfer possible with door open or refuel selected (tested on ac 4041 4/6/0)

AFM 4.1.4

 (3)

Mike Remily

Parker Fuel Rep   x6524

 

S400 Advisory Light Panel Descriptions top to botton l to r

Fire Panel APU

1.      

APU

FUEL

OPEN

Fuel shutoff valve open

 

 

AFM Sup 6

FSI 3-9

2.      

APU

VALVE

 CLOSED

Fuel shut-off valve closed

 

Illuminates during test

 

3.      

APU

BTL

ARM

Circuits active to fire bottle

 

Illuminates during test

Arming and firing are automayic in response to a fire indication.

Fires in 7 sec.

Fsi 3-9

4.      

APU

EXTG

Fire detected circuits armed

 

Illuminates during test

PFTG P15 APU test

5.      

APU

BTL LOW

FAULT

Low pressure in APU fire bottle

 

Fault in protection circuits or  panel

 

 

 

6.      

APU

FIRE

APU Fire

Check APU automatic shutdown

Run light out, Btl Low al, and Fuel valve closed al.

If Btl Arm al or Fire al then
Entg switchlight -  lift coverguard and Press

 

Illuminates during test

Illuminates with Check Fire Det wl, Apu cl

AFM Para 6.6.3

 

Melp 26-10-3 and

26-20-1


Engine Fire Panel            MELP section index

7.      

EXTG

AFT BTL

Engine fire circuits armed  and Engine fire bottle up to pressure.

 

Armed when a “Pull fuel/hyd Handle” pulled.

AFM 3.1.2

FSI 8-7

8.      

FWD BTL

Engine fire circuits armed  and Engine fire bottle up to pressure.

 

Armed when a “Pull fuel/hyd Handle” pulled.

AFM 3.1.2

FSI 8-7

9.      

VALVES

FUEL

OPEN

Fuel shutoff valve open

 

Operated by “Pull fuel/hyd Handle”

FSI 8-7

10.    

VALVES

FUEL

CLOSED

Fuel shutoff valve closed

 

Operated by “Pull fuel/hyd Handle”

FSI 8-7

11.    

VALVES

HYD

 OPEN

Hydraulic firewall valves open

see reboots 23

valves are normally open

Parker R-2920772 p 32

12.    

VALVES

HYD

 CLOSED

Hydraulic firewall valves closed

Other Hyd caution lights lead to QRH

Electrical control to close is as follows :

Pull Fuel Off Handle pulled OR

Reservoir  temp indicates high temp(225F) and reservoir  temp switch (275F)closes OR

reservoir empty quantity switch activated .

Parker R-2920772 p 32/23

13.    

BTL

LOW

One or both engine fire bottle has low pressure

 

No dispatch

Note there is no comment on this light in any document other than FCOM

FSI 8-9

14.    

FAULT

A

Fire loop A failure

 

No dispatch

AFM 4.10 1

nilmel

15.    

FAULT

B

Fire loop B failure

 

No dispatch

Under pressure or electrical fault

AFM 4.10 1

nilmel

16.    

 

PULL FUEL/HYD OFF

 

Engine Fire

 

Fire loop shows overpressure

AFM 3.1.2

nilmel


Baggage Fire Panel/Smoke

17.    

BAGGAGE AFT

VENT

INLT

Vent valve closed

 

 

Afm 3.4.2

nilmel

18.    

BAGGAGE AFT

VENT

OTLT

Vent valve closed

 

 

Afm 3.4.2

nilmel

19.    

BAGGAGE AFT

SMOKE

EXTG

Smoke =fire/smoke detected in aft baggage compartment.

Extg = switchlight pressed to initiate fire bottle sequence

Check Vents close and  AFT bottle arms

Smoke/extg switchlight – Press

Check Bottle AFT Low al,   Arm light out, & Fwd low al maybe.

Land Imediately

No automatic firing

 

Test fail see reboot 48

Afm 3.4.2

nilmel

20.    

FIRE BOTTLE

AFT ARM\LOW

Arm = bottle firing circuits active

Low= bottle pressure low, ie fired

 

Acts as slow rate bottle for fwd compt

Afm 3.4.2

MELP 26-20-4

21.    

FIRE BOTTLE

FWD ARM\LOW

Arm = bottle firing circuits active

Low= bottle pressure low, ie fired

 

Acts as slow rate bottle for aft compt

Afm 3.4.2

MELP 26-20-4

22.    

BAGGAGE FWD

SMOKE

EXTG

Smoke =fire/smoke detected in forward baggage compartment.

Extg. = switchlight pressed to initiate fire bottle sequence

Check FWD bottle arms

Smoke/extg switchlight – Press

Check Bottle FWD Low al,   Arm light out, & Aft  low al maybe.

Land Imediately

No automatic firing.

Afm 3.4.2

MELP 26-20-4


Deice Panel - -   MELP index to section - - QRH index to section

23.    

Ice Protection

WING/TAIL

Bleed air pressure being supplied to inflate boot group equals >15 psi and is operational

If not light

Exit icing conditions

If eng intake boot

Intake –Open

Exit icing conditions

QRH 13.3 and 13. 4

Can be accompanied by Deice cl

Or Deice timer cl

MELP tail

Wing MELP

AFM 4.17.3 &2 &1

24.    

Ice Protection

PROP

System and Blade heater check

Or

Heaters (to all 6 blades)operational

If not light

See Prop Deice cl and QRH

 

Operate props at 1020 RPM

Exit icing ASAP

Selector remains on

QRH

MELP for als   ’30-60-1and 2s

Will cycle depending on temp when

Prop switch on, and TAT £5°C, and Np>400 or

Will cycle 1 time for 5 sec each side when Prop switch to test  and Np >400 or

On self test  which occurs on Dc power up (switch on) for 12 sec, if test selection has not previously been made. Note this will delay normal start by about 1 min.

D 8 400 co-ordination memo on file

AFM 4.17.4

25.    

Ice Protection

ENGINE INTAKE

OPN

Intake deflector down, arms one of two HTR circuits.

 

 

MELP  for  doors posn lights, heater lights  and actuators

 

AFM 4.17.5

FSI p 12-11

26.    

Ice Protection

ENGINE INTAKE

CLOSED

Intake deflector up

 

 

MELP  for  doors posn lights, heater lights  and actuators

 

27.    

Ice Protection

ENGINE INTAKE

HTR

Switchlight selected OPN, SAT<15°C and engine operating (as sensed by oil pressure) and AC power being supplied to intake heater

Monitor Engine performance.

Exit Icing ASAP

QRH

Failure turns on cl

MELP  for  doors posn lights, heater lights  and actuators

AFM 4.17.5


APU Panel    MELP index

28.    

Apu Control

Pwr

RUN

APU in operation and ready to load

 

On about 18 sec after start initiated.

AFM Sup 6

FSI 49-00-00 p7

29.    

Apu Control

Pwr

FAIL

APU powered and not running: or fadec system fault: or fire: or fire bottle low: or

generator overheat.

APU Starter light –out

APU PWR Press on – press off

Confirm fail light out

Wait 7 sec

Try another start, observe cranking limits

turns on Apu cl

 

restarts limited to ½,1/2,1/30 (70)

ditto

30.    

Apu Control

Start

STARTER

start in progress (initiated)

 

 

remains on for about 8 sec then out as start continues.

ditto

31.    

Apu Control

Gen

ON

Generator on line

 

MELP 24 –30-4

ditto

32.    

Apu Control

Gen

WARN

Apu powered and

Gen not selected on

Or ON and Faulted (fault or DC power supplied to main busses)

 

Cycle  Gen  Switchlight off then on

If not press off

Acts as a demand light and a fault light

 

al is on when aircraft on DC ground power and switchlight selected on.

Majnt manual

33.    

Apu Control

Bl Air

OPEN

Bleed valve open

 

Will not indicate OPEN if an aircraft bleed selected on.

Ditto

And FSI 3-7

34.    

Apu Control

 

GEN OHT

Generator overheated and taken off line.

Carry out post auto shutdown procedure

Apu Bl Air-- Press off

APU Gen – Press off

Apu Pwr – Press off

Observe correct indications

also turns on flr and apu caution light

FSI 49-00-00 p7


Start panel Pressurization

35.    

SELECT

 

 

START

Select switch moved to an engine (1or 2) position and

Start control circuitry armed

Generator in start mode and being supplied power

See reboots 64

Start light remains on see AFM 4.1.6.1

STARTER OFF, EXT PWR OFF, RESELECT dc GENS ,

 IFNO CALL MAINT.

Select light remains on see AFM  4.1.6.3 and 4.8.2

SELECT ALL ELE SOURCES OFF

 

MELP 24 re start termination 24-30 2 and  inop 24 -3--6

400 amp limiting on  dc generator output

normally remains on for about 15 sec after a start

If no ITT (20) in 8 sec second igniter cuts in auto cut off if overtemp.

Note can be result of slow contactor switchover during start,  repower ,  ifno motoring of engine (welded contactors) try another start. Repower can be by checklist or by reboot of CB H6 on L Esc.

AFM 4.1.5

FSI 17-46

FSI Main training  80—00-00 and wiring diag

Horizon expriene

36.    

FAULT

Is a self test system

Fault detected in pressure control system.

Auto/ Man/Dump -  Man

Man Diiff switch Incr/Decr as reqd

Not on in test may be off in manual

Outflow is stationary

reboot 28e  fault light -  select Man/ Auto as required to reboot

AFM 4.16.4

Mel 21-30-5


STBY Instrumentation

Stby compass -  note misalignment can occur based on position of cockpit door see Bob Mac email

37.    

Stby horizon flag

Red drop down?

Not powered or no to spin speed?

Cb’d l essential hot bat bus

No mel

 

38.    

Ihsi  (blank inop)

 

Will fail if ac moved during boot-up

Is mel’able

 See Reboots 47Cycle cb on Hl  on L esset.(hot) bat bus

Mel item 34-20-6 ONLY for T&B NOT Aspd Inication

 

39.    

Stabdby Altimeter flag

Red box center right

Indicates vibrator is inop .

Unit is cb’s on l essential hot bat bus 

experience


Glareshield Panel (L to R)

40.    

ENGINE FIRE

PRESS TO RESET

 Triggered by illumination of “pull fuel/hyd handle”

Press  1 to extinguish both.

Also initiated audio fire warning if installed.

“Pull Fuel/Hyd Handle” is master and can not be extinguished except by elimination of overheat.

AFM 4.1.10.2

41.    

ROLL OUTD

Both of tandem lift /dump solenoid (electrial) control valves have moved to the extend (up) position

 

Spoilers operating in ground mode

Control electrical, actuated Hydraulic

WOW+

Both Power lever<+12 del pla posn +

Flt taxi in Flt +

 

System Knowledge

FSI 9-43

42.    

ROLL INBG

Both of tandem lift /dump solenoid (electrial) control valves have moved to the extend (up) position

 

Spoilers operating in ground mode

Control electrical, actuated Hydraulic

WOW+

Both Power lever<+12 del pla posn +

Flt taxi in Flt +

 

System Knowledge

FSI 9-43

43.    

PULL UP

GPWS TEST

Activated during any Mode 1-4 alert or warning until warning envelope is exited OR

By pressing and holding – is a self test when aircraft is on ground.

Sink Rate, Terain, Don’t sink, Too low- Flaps, - Take appropriate action

 

To Low – Terrain, Pull Up – immediate establish  Max climb gradient

 

Failed self test

“Radio Altitude”- repair invalid signal

“Glideslope” – repair ± signal

“Baro rate” repair invalid signal

“To Low Gear” repair or adjust

if “glideslope” with GS light – Flap in landing config

Test  (flap 0)

“Pull Up” 1 time;

GPWS cl;

GPWS Flap Override al;

Below G/S al;

“Glideslope” 1 time at reduced vol.;

Pull up al

“Pull Up” 5 times

All lights off, wait at least 30 sec. To repeat test if reqd.

 

 

Allied Signal install doc P 34 and drawing no 060-3956 Rev f cage code 97856

AFM sup2

Momentary press

GPWS cl

Pull Up and Below G/S al s

“Glideslope” vw

“Pull Up” vw

 

Long press (3 sec)

All alert, warning, caution and altitude callout voices

EGPWS

AFM sup 64

cont

44.    

BELOW

G/S

Mode 5 alert

Depress switchlight cancels message

Message reset to normal after descent through 50’, climbing through 1900’, by de-selecting ILS frequency, or by pressing switchlight a second time.

Allied Signal install doc P 34 and drawing no 060-3956 Rev f cage code 97856

 

 

Message reset to normal on climb through 2000’ or descent through 30’

EGPWS

AFM sup 64

45.    

A/P

DISENG

Autopilot has disengaged itself

Flashing

 

Extinguished (out/off) by pressing

FSI 4A 29

46.    

WARNING

PRESS TO RESET

Flashing. Activated by any warning light activation which will also flash.

 

Extinguished (out/off) by pressing

Activating warning light remains on steady.

aircraft

47.    

RUD1

PUSH

OFF

Lower Actuator has jammed.

 

 

 

 

If both RUD switchlights pressed then  both “PUSH” are illuminated.

Press

observe #1 Rud Hyd caution Light

 

 

 

Push both lights

When pressed “PUSH” extinguished “OFF” remains illuminated.

Fecu shuts off hydraulics to actuator and increases pressure to other rudder channel.

 

System will not allow both to be off.

 

AFM  4.18.12

 

 

lear Rev a pg 21 update

48.    

SPLR 1

PUSH

OFF

Inboard spoiler control (PCU) has jammed

 

With both SLPR 1 & 2 lights on and roll disconnect—co-pilot roll input exceeds 50 degrees (Approx. full deflection)

Press switchlight(s).

Observe  appropriate roll splr #1 Hyd caution light, and PFCS shows spoiler retracted.

See QRH for limitations, approach speeds, and landing field increases.

 

AFM 3.8.2&3

Lear rev a pg 17

49.    

SPLR 2

PUSH

OFF

Outboard spoiler control (PCU) has jammed

 

With both SLPR 1 & 2 lights on and roll disconnect—co-pilot roll input exceeds 50 degrees (Approx. full deflection)

Press switchlight(s).

Observe  appropriate roll splr #2 Hyd caution light, and PFCS shows spoiler retracted.

See QRH for limitations, approach speeds, and landing field increases.

 

AFM 3.8.2&3

Lear rev a pg 17

50.    

RUD 2

PUSH

OFF

Lower Actuator has jammed.

 

 

 

 

If both RUD switchlights pressed then  both “PUSH” are illuminated.

Press

observe #2 Rud Hyd caution Light.

 

 

 

Push both lights

When pressed “PUSH” extinguished “OFF” remains illuminated.

Fecu shuts off hydraulics to actuator and increases pressure to other rudder channel.

 

System will not allow both to be off.

 

AFM  4.18.12

 

 

lear Rev a pg 21 update

cont


 

51.    

Propeller

Ground Range

1/2

Propeller are in ground portion of beta range

In flight

PL advance.

Avoid PL position that gives light

PL not below FI for landing

(feather after touchdown if reqd)

 

AFM 3.3.4

52.    

Stick Pusher Shut off

 

OFF

Switchlight pressed. (Actuator turned off)

Min speed 1.23 Vsr

There is a switchlight for each pilot 

cl Light on

 

AFM 4.11.7

PFTG 3 .4

53.    

Elevator Trim Shutoff

 

PUSH

OFF

Pitch trim in motion for 3 sec.(On Both)

 

Switchlight – Press

Trin indicator goes full NU

Maintain speed and config.

No autopilot

Land min X wind and Turb.

Expect high elev forces

Disables the actuator.

 “OFF” remains illuminated.

AFM 4.18.3

54.    

CAUTION

PRESS TO RESET

Activated by any caution light illuminating.

 

Extinguished (out/off) by pressing

Activating caution light remains on.

 


Landing Gear panel

55.    

Landing Gear

L DOOR
N DOOR
R DOOR

Landing gear door open

No checklist item for this

Check posn of door.

If door appears closed continue as required or try recycle if appropriate.

If door open DO NOT SELECT GEAR DOWN.

Cycle inhibit switch to shock door valve one time. Ifno Free fall the gear

See reboots section

With door open hyd pressure will continue to be supplied to the gear after an up selection (PSEU does not release to neutral)

MSI 326100/01/9 sys 32-60-00

11/20/97 rev A

56.    

Landing Gear

LEFT

NOSE

RIGHT(green)

Landing Gear down and Locked

IFNO

Landing Gear Alternate Extension door – Open

Gear Locked Down Indicator Light switch – On

Check ok

Door closed.

 

AFM 4.21.2

57.    

Landing Gear

LEFT
NOSE
RIGHT(red)

Gear unsafe.

Gear not in the position selected

 

 

MSI 326100/01/9 sys 32-60-00

11/20/97 rev A

58.    

Landing Gear

Handle

Master to the red lights above, 1 red = gear handle light

 

If gear retraction /extension is slow check alt gear hyd sys main selector valve filter for collapsed elements – ISAR 2004-03 page 19

MSI 326100/01/9 sys 32-60-00

11/20/97 rev A


GPWS/HYD Panel

59.    

gpws landing flap

10

Indicates landing flaps 10 are set in GPWS computer

 

closed loop system

AFM sup 64

60.    

gpws landing flap

15

Indicates landing flaps 15 are set in GPWS computer

 

 

AFM sup 64

61.    

gpws landing flap

35

Indicates landing flaps 35 are set in GPWS computer

 

 

AFM sup 64

62.    

Hydraulic control

stby Hyd press

 

ON green

Switch is selected on

 

Automatic on if

Flap Lever more than 0° and Park brake off and Reservoir not empty OR

Engine 1 fail (oil pressure low) and airborne

AFM 4.1.8

FSI 29-00-00 p23

Parker R-2920772 p22

63.    

Hydraulic control

ptu cntrl

 

ON green

Pressure in PTU output line.

Note not Auto on with #1 Engine fail (and shutdown) see logic

ptu on by selection OR

Flap Lever more than 0° and Park brake off and #2 Reservoir not empty and #1 EDP output.>2400 psi and PTU output pressure switchlight on within any 30 sec.period.

note the 30 sec switchlight requirement in automatic is a latching circuit and is reset by pulling the HYD PWR XFR circuit breaker, cockpit selection bypasses this latch

AFM 4.1.8

 

FSI 29-00-00 p 29 Parker R-2920772 p22

64.    

Hydraulic control

Hyd #3 isol vlv

ON amber

Switch is selected on  Valve open.

 

Automatic on if

Airborne, and Hyd 1 or Hyd 2 pressure low (900) OR

 Eng. 1 and Eng.2 failed (low oil press)

Note: this valve fails operational (depowered on)

FSI 29-00-00 p 30, Parker R-2920772 p25

And dave geib


AHRS

65.    

DG

DG switch is selected. Dg mode engaged.

 

 

Fsi 6-67

66.    

SLAVE

Flux gate failure

Select other EFIS att/hdg source.

See other messages

AFM 4.19.1

Fsi 6-67

67.    

BASIC

Loss of TAS (for acceleration compensation) information to AHRS

 

Other mismatch messages

Fsi 6-67

68.    

ATT/HDG

ALIGN

AHRS in alignment mode

 

60 sec on ground

90 sec airborne

Fsi 6-67

 

 


Fuel control ++

69.    

Fuel Control Transfer

TANK  1

AUX PUMP

ON green

Pressure in pump output line.

Failure of automatic function

Switchlight –Press

Checl al and indication on MFD

When transfer complete

Switchlight off

Pressure sensor has been known to fail.

AFM 4.9.2

Flt test

70.    

Fuel Control Transfer

TANK  2

AUX PUMP

ON green

Pressure in  pump output line.

Failure of automatic function

Switchlight –Press

Checl al and indication on MFD

When transfer complete

Switchlight off

Pressure sensor has been known to fail.

AFM 4.9.2

Flt test

71.    

Eng control

 

 

Switches only no lights

 

72.    

Prop control

FTHR

[]

Alt feather pump switchlight selected and timer running (for 33 ± 3 sec)

 

Timer and light off after 33 sec..

During autofeather test runs momentarily.

Production test and FSI 17-35

73.    

Prop control

AUTOFEATHER

 

SELECT

Autofeather circuits are activated.(electrical contact).

 

Note: uptrim (MTOP fuel schedule)will occur any time an engine fails regardless of this switch posn.?? verify

 

Initiates test when engines in feather or fuel off.

Arms; when both Torque>50% and PLA >60 deg.

Uptrim & Autofeather triggered when;

Torque <25% or Np<80% on one engine, and PLA in detent and MTOP not set.

 

 

AFM 4.1.10.1

74.    

CVR

()

STATUS

CVR malfunction

See MEL

 

 


 Crew als

75.    

GND CREW

FWD AFT

Interphone jack is active

 

Isolated airborne

Sextant verbal ??

76.    

GPWS FLAP

OVERRIDE

[yellow]

Switch label light controlled by reostat

-

 GPWS operational and Flap warnings inhibited

 

On GPWS aircraft switchlight is

illuminated when pressed and electronically latched and RA is greater than 50’ (press on press off.)

On EGPWS aircraft switchlight is mechanically latched. 

FSI 6-13

AFM 4.14.1


Allt Dn Lk als

77.    

Alternate downlock indication

O

OO

Nose gear down and Nose gear locked.

Left and right gear locked down

NOTE This system uses separate Prox. Sensors and diff card in PSEU

 BUT   Prox sensors are of same type and are mounted in close proximity to main sensors

 

System turns on nose wheel steering

and taxi light when gear down

AFM 4.21.2

MSI 326100/01/9 sys 32-60-00

11/20/97 rev A

78.    

 

 

 

 

 


Audio /Video warnings in priority status

1.      

GPWS

 

 

Voice(c nc)

sextant p86 of z1240496

 

2.      

TCAS Collision

 

 

Voice (nc)

sextant p86 of z1240496

 

time to closest point of approach 15-35  seconds

 

Solid red square and voice

See RA’s below

Bendix king manualp26/27

 

 

climb,

climb,

climb

establish a 1500fpm or greater climb

(RA)

Ivsi red  -6000’ to+1500’ and green +1500’ to +2000’

Bendix king manualp26/27

 

 

descend,

descend,

descend.

establish a 1500fpm or greater descent

(RA)

Ivsi red  +6000’ to-1500’ and green -1500’ to -2000’

Bendix king manualp26/27

 

 

monitor vertical speed,

monitor vertical speed,

Keep vertical speed out of red unsafe areas

(RA)

Ivsi red  outside present vertical speed

Bendix king manualp26/27

 

 

reduce climb

reduce climb

reduce climb to green area of indicator.

(RA)

Ivsi indicates prohibited vertical speed in red , keep vertical speed in green

Bendix king manualp26/27

 

 

reduce descent

reduce descent

reduce descent to green area of indicator

RA)

Ivsi indicates prohibited vertical speed in red , keep vertical speed in green

Bendix king manualp26/27

 

 

climb crossing climb

climb crossing climb

establish a 1500fpm or greater climb --vertical speed to green area of indicator.

(RA)

Ivsi red  -6000’ to+1500’ and green +1500’ to +2000’ and indicates flight path crossing that of intruder

Bendix king manualp26/27

 

 

descend crossing descend

descend crossing descend

establish a 1500fpm or greater descent--vertical speed to green area of indicator.

(RA)

Ivsi red  +6000’ to-1500’ and green -1500’ to -2000’ and indicates flight path crossing that of intruder

Bendix king manualp26/27

 

 

clear of conflict

return to assigned altitude

(RA)

Ivsi red and green arcs removed

Bendix king manualp26/27

 

 

increase climb

increase climb

follows a climb advisory

climb at 2500’ up or better

(RA)

I vsi red from  -6000’to+2500’, green from +2500’ to +3500’.

Bendix king manualp26/27

 

 

increase descent

increase descent

follows a descend advisory

descend at 2500’ down or better

(RA)

Ivsi red from  +6000’to-2500’, green from -2500’ to -3500’..

Bendix king manualp26/27

 

 

climb, climb now

climb, climb now

follows a descend advisory

climb at 1500’ up or better

(RA)

Ivsi red  -6000’ to+1500’ and green +1500’ to +2000’

Bendix king manualp26/27

 

 

descend, descend now

descend, descend now

follows a climb advisory

descend at 1500’ down or better

(RA)

Ivsi red  +6000’ to-1500’ and green -1500’ to -2000’

Bendix king manualp26/27

 

3.      

Fire Bell

 

 

 

 

 

4.     1

Take-off Warning Horn

Aircraft on Ground with

A power lever above 50% and

flap<3.5(and NORM selected )or >20

a condition lever not at  max or

park brake on or

a spoiler extended (not down)or

trim out of range

 

Repeating Chime (c)

 

TO Warn test switch simulates pwr.50%

See reboots if problems.

 

Can be an indication of an interrupted (control moved) fcecu self test

See reboots 10

 

 

5.     2

Autopilot Disengage

 

reconfigure aircraft

1000 hz intermittent tone(nc)

Test switch on pilot subpanel bypasses the engine torque requirement.

Flap position is read from flap indication. Horn signal given in flap <3.5 only if flap selector is in normal (TO)range.

FSI 32-00-00 p 23

sextant p86 of z1240496

 

6.     3

Pitch trim in motion

 

 

4000 hz 1-2 sec intermittent  tone (nc)

sextant p86 of z1240496

 

7.     4

Overspeed

 

 

click – continuous (nc)

sextant p86 of z1240496

 

8.     5

Landing Gear

A. Test switch selected

 

B. Gear not down and locked 

AND

1) Flap lvr >8.5, an Eng tq <50%, both PLA< detent  OR

2) both PLA <FI +12, IAS < 156 , RA  <1053’  OR

3)  one PLA < FI + 12, other PLA < detent, IAS <156, RA <1053’ and Horn Switch not mute latched]

(assumes RA Valid)

 

1000 hz tone (nc)

FSI Page 13-31

 

9.      

Altitude Alert

 

reconfigure aircraft

2000 hz tone(c-nc)

sextant p86 and 290 of z1240496

Fsi 32-00-00 p21

 

 

10.   6

beta lockout

 

 

2900hz 1 sec tone

sextant p86 of z1240496

 

11.   7

Warning

 

 

800 hz tone (nc)

3 chimes

sextant p86,292.293 of z1240496

 

12.   8

Caution

 

 

1 chime

sextant p86 of z1240496

 

13.   9

TCAS Traffic

 

 

 

sextant p86 of z1240496

 

 

Traffic within 1200’and 6 nm. range

 

Solid blue diamond

Bendix king manualp26/27

 

 

time to closest point of approach 20-48 seconds

 

Solid yellow circle and voice

see traffic traffic  (TA)  below

Bendix king manualp26/27

 

 

traffic,

traffic

(Spoken once if a second Traffic appears)

conduct visual search , identify traffic

(TA)

Solid yellow circle

Bendix king manualp26/27

 

 

TCAS system test OK

 

12 sec test conclusion

 (Show a correct test pattern for screen and VSI---our aircraft appears similar to CAS 67A illustration  in Bendix text except that 10 radar pattern shown appears in compass ring on PFD and 2) IVSI pattern is green rimmed  from 0 –2000’ up all else red and  with a red needle at 0)

Bendix king manual p 68/69

 

 

TCAS system test fail

 

 

 

 

14.   10

Selcal

 

 

Voice (nc)

1200 hz 3 sec tone

sextant p86 of z1240496

 

15.    

 

 

 

 

 

 










 

 


PFD/MFD/ED  warnings/cautions

PFD

1.      

AFCS CONTROLLER INOP

FGCP has stuck button or FGCP bus fail. (control  panel)

 

 

Para 9.9

2.      

AFCS FAIL

PFD not receiving any data from both FGM’s

 

 

Para 9.9

3.      

Aligning

Flashes yellow for 5 sec then steady

AHRS alighment

 

1 min on gnd 1.5 min in air,5 min during calibration.

 

4.      

ALRT

Not at selected altitude

 

Reverse video and Yellow

 

5.      

ALT MISSMATCH

In yellow 5 sec flashing then steady.

Altitude missmatch

See reboots 20

 

P55 Rev 4

6.      

(ALT)

NEG

Preceeds altitudes below 0

See reboots 20

 

 

7.      

ALT FAIL

Altitude failure or ICP (index control panel)is unable to set barometric pressure.

ALT flashed in yellow for 5 sec then steady =ADC providing diff. values

See reboots 20

Altitude comes from own side ADU except when select on ESCP

 

8.      

(ALT) open white rectangle/circle

Altitude invalid

See reboots 20

 

P25 REV 2c pfd customer

9.    

(ALT)

----

(in place of barometric readout)

ICP (index control panel) is unable to set barometric pressure

Try Cb reset (on pilots avionics panel, middle)

 

 

10.  

(ALT)

-----

Selected alt data not valid

Loss of FGCP/ADU source selected by HSI

 

 

 

11.    

(ALT)

Brown Band

Analog indication of Radio Altitude agl.

Appears when a/c below 550 ft.

 

 

 

12.    

ALT OFF

Altitude hold disconnected. Thunbwheel used in ALT mode

 

Yellow flash 5s then steady when FD mode lost

PARA 9.11

13.    

AP

Autopilot engaged

 

 

Para 9.12

14.    

AP/FAIL

 

 

Flash for 5s then steady

Para 9.10

15.    

AP INHIBIT

Autopilot engagement attempt not allowed

 

 

Para 9.12

16.    

AP PITCH TRIM FAIL

AFCS unable to control autopilot pitch trim. On when autopilot engaged, off when not

QRH

Often accompanied by auto trim fail message. Ac can be flown with autopilot if no power changes or config changes.

See reboots 9

Para 9.9

17.    

AP/YD DISENGAGING

 

 

Flashing,  stops when pilot actions AP Disc P/B then steady for 5 sec

Para 9.10

18.    

AP/YD FAIL

 

 

Flash for 5s then steady

Para 9.10

19.    

ATT FAIL

Red with att indication blank

Loss of Roll or Pitch information provided by AHRS as selected on ESCP

 See reboot 21

See QRH

ATT/HDG Source selector to operating side

AFM 4 19.2

Sextant PDF symbology desc p 31 rev 4

20.    

AUTO TRIM FAIL

Both FGM’s unable to perform Flap auto pitch trim function

 

See 16 above

Para 9.9

21.    

CAT2 FAIL

Cat 2 approach must be aborted due failure in IMS 100 avionics suite caused by

Dual mode drop ,fgm bus loss,missmatch on pitch,roll,ias, loc,gs ,rad alt, display monitor inop,check pfd message, pdf –

looses pitch, roll, hdg ,ias, loc, gs, rad alt ,

 

 

iop output, or opposite pfd cat II fail message from feedback bus.

Message is removed when condition corrects

Message arms when Dual FD is engaged

 And RA >50’and one Dh < 200’ or both invalid.disarmed when gs disengaged,ra <50’ or both DH >200’

Para 9.13 and

SSS/AFCS//DHC-8/400/pg 120 issue5

Page 58 pdf symboligy

22.    

CHECK PFD x

Display discrepancy in pitch,roll, IAS, ALT, HDG.

 

Yellow ,flashing for 5 sec, then steady.

Para 9.8 p 64 rev4

23.    

CHECK NAV SOURCE

Nav source change

 

Yellow flash 5s then steady when FD mode lost

White when pilot action can not be completed

PARA 9.11

24.    

CUE

On ias

In yellow

Low speed cue information invalid when IAS valid

 

 With stall and pusher cls

IOM/IOP reset/then try SPM reset Try also Aoa  reset with ac on.

 Ifno then suspect stall compuer fail

PFD Customer P21 Rev 2c

V 600 amends

25.    

DH

In yellow flashing for 3 sec then steady,  in a black box.

A/c Rad alt below DH value

Remains till a/c at dh +100’.

 

 

 

26.    

--- DH

ICP (index control panel) is unable to set barometric pressure

Digits are removed from display if set below 0 ft

 

 

 

27.    

(DME)

 H

Dme set to hold mode

 

 

 

28.    

(DME)

---

Distance not valid

 

 

 

29.    

(DME)

no display

FMS auto tune or MLS selected

 

 

Cust PFD P 38


 

30.    

DUAL FD

Both FGM avail, efis adc and att/hdg sources normal, both ADC valid, both AHRS valid, vor1 is left vor2 is right, both tuned to same loc, ils data for both valid, both courses are same, lat and vert modes active, ra valid below 1200,both FD agree, and no TCS.

 

RA above 50’, both DH above 200,

Clarify this

 

Para 9.13 and SSS/AFCS//DHC-8/400/pg 120 issue5

31.    

DUAL OFF

When duel mode canceled and DH  not selected for Cat II

 

Yellow  flashing for 5 sec.

Para 9.13 and SSS/AFCS//DHC-8/400/pg 120 issue5

32.    

EXCESS DEV

Ils LOC or GS excessive deviation

 

Yellow ,flashing for 5 sec, then steady.

DittoP 54 rev4

33.    

FD ATT DATA INVALID

AHRS failure

 

Yellow flash 5s then steady when FD mode lost

White when pilot action can not be completed

PARA 9.11

34.    

FD ADC DATA INVALID

ADC fail

 

Yellow flash 5s then steady when FD mode lost

White when pilot action can not be completed

PARA 9.11

35.    

FD HDG DATA INVALID

HDG fail

 

Yellow flash 5s then steady when FD mode lost

White when pilot action can not be completed

PARA 9.11

36.    

FD NAV DATA INVALID

Nav fail

See reboots 34

Yellow flash 5s then steady when FD mode lost

White when pilot action can not be completed

Can be as a result of adc test with command bars in place

PARA 9.11

37.    

FD MODE INHIBIT

Invalid pilot request

 

Yellow flash 5s then steady when FD mode lost

White when pilot action can not be completed

PARA 9.11

38.    

GS mismatch

Yellow flashing for 5 sec then steady

GS discrepancy detected between ILS 1 and ILS 2 during a dual mode approach .

 

 

P 55  rev 4 sextant pdf doc

39.    

(GS)

pointer and scale flashing in yellow

Deviation in excess of Cat II (Gs 75 microamps) when in dual and belo Ra of 1200’

 

 

Aeroc 84.6.R.24 pq=g 30

40.    

(GS)

o

X

o

Failure in glideslope deviation, MLS glide path or FMS vertical path depending if G,E,V is displayed above

 

 

Para7.14

41.    

 

 

 

 

 

42.    

HDG MISMATCH

Heading mismatch

Flashes yellow for 5 sec then steady

 

 

P55 Rev 4

43.    

HDG

CALIBRATION

 

 

 

 

44.    

HDG FAIL

Failure of a heading sensor.

EFIS ATT/HDG SOURCE  selector –1 or 2

Slave light on AHRS controller

Compass rose to white circle

AFM 4.19.

Para 8.4

45.    

HSI

Cross side information is selected

 

In yellow

 

46.    

IAS digits red

Vmo exceeded

Or

On SAS

IAS below low speed cue

See reboots 20

 

P 18 Rev 2C

47.    

IAS at 30 k

Ias not computed valid

 

 

P 19 Rev 2C

48.    

IAS FAIL

CAS has failed

IAS flashed in yellow for 5 sec then steady =ADC providing diff. values

See reboots 20

IAS comes from own side ADU except when select on ESCP

PFD symbology para

49.    </