THRUST REVERSER UNLOCK LIGHT ON IN FLIGHT

1. Emergency Stow Switch................... ACTUATE ON AFFECTED ENGINE

2. Thrust Reverser Levers................CHECK THRUST REVERSER LEVERS AT STOWED (FULL FORWARD) POSITION IF LIGHTS WILL NOT EXTINGUISH

3. Thrust Reverser Circuit Breaker.......................................... CHECK IN

4. Maintain 200 KIAS or below.

5. Land as soon as practical. Index

THRUST REVERSER ARM LIGHT ON IN FLIGHT

1. Thrust Reverser Levers............................................ CHECK STOWED

• Full forward

2. Emergency Stow Switch...................................................VERIFY OFF

IF LIGHT IS STILL ILLUMINATED

3. Airspeed............................................... Maintain 200 KIAS or BELOW

4. HYD PRESS ON Light............................................................. CHECK

• If HYD PRESS ON Light Is Illuminated (thrust reverser isolation valve is

open):

5. Affected Thrust Reverser Circuit Breaker..............................PULL

6. Land as soon as possible.

• Affected thrust reverser should be inoperative.

• If HYD PRESS ON Light Is not Illuminated (probable pressure switch problems):

5. Land as soon as practical.

With a thrust reverser circuit breaker pulled, the emergency

stow system of the opposite reverser is deactivated. Index

THRUST REVERSERS — INADVERTENT INFLIGHT DEPLOYMENT

1. Reverser Indicator Lights.....................CHECK ILLUMINATION of ARM, UNLOCK, and DEPLOY LIGHTS

2. Affected Engine............................................................. CHECK IDLE

3. Emergency Stow Switch................... ACTUATE ON AFFECTED ENGINE

4. Airspeed.........................................REDUCE TO 125 KIAS OR BELOW

• 115 KIAS with Flaps Extended

• After thrust reverser stows, do not exceed 200 KIAS

5. Reverser Indicator Lights.......................UNLOCK AND DEPLOY LIGHT EXTINGUISHED; ARM AND HYD PRESS ON LIGHT ILLUMINATED

If thrust reverser is stowed, engine may be operated normally. Thrust reverser can not be used during landing if emergency stowed.

6. Land as soon as practical.

IF THRUST REVERSER WILL NOT STOW

7. Thrust Reverser Circuit Breaker.......................................... CHECK IN

8. Throttle (Affected Engine)......................................................CUTOFF

9. Airspeed............................................MAINTAIN 150 KIAS OR BELOW

ENGINE FIRE (ENGINE FIRE SWITCH ILLUMINATED)

1. Throttle (Affected Engine)...........................................................IDLE

IF LIGHT REMAINS ON

2. Engine Fire Switch...........................................LIFT COVER and PUSH

3. Either Illuminated Bottle Armed Light......................................... PUSH

4. Ignition...................................................................................NORM

5. Throttle (Affected Engine)............................................................OFF

6. Electrical Load............................................... REDUCE AS REQUIRED

• 400 amperes maximum to 35,000 feet; 325 amperes maximum

above 35,000 feet

ENGINES/FUEL

7. Boost Pump...............................................................................OFF

8. Land as soon as practical.

IF FIRE WARNING LIGHT ON AFTER 30 SECONDS

9. Remaining Illuminated Bottle Armed Light.................................. PUSH

10. Land as soon as possible.

IF LIGHT GOES OUT AND SECONDARY INDICATIONS ARE NOT PRESENT

2. Land as soon as practical.

SINGLE INVERTER FAILURE (INVERTER FAIL 1 OR 2 LIGHTS AND AC FAIL LIGHT ON)

Indicates loss of power from affected inverter.

1. AC Inverter No. 1 and No. 2 Circuit Breakers....................... CHECK IN

2. Master Warning.......................................... RESET and continue flight

Operation of all alternating current powered avionics

equipment will be sustained by the opposite inverter. The

flight director may disengage. It may be re-engaged to

operate on the remaining inverter. Index

10. Land as soon as practical. • Within 30 minutes Index

1. Check the right sub-circuit breaker panel for disengaged AC BUS circuit breaker(s).

IF CIRCUIT BREAKER(S) IS/ARE DISENGAGED, OPERATE WITH LOSS OF BUS AS RE-ENGAGEMENT MAY RESULT IN FURTHER DAMAGE TO THE ELECTRICAL SYSTEM.

Depending on which bus(ses) has/have been lost, the following equipment will be lost:

a. 26 VAC Bus 1 — Pilot’s ADI, pilot’s RMI; pilot’s HSI (HDG and NAV flags in view); pilot’s rate-of-turn indicator; copilot’s RMI compass card and NAV 1 bearing pointer; and ADF 1.

b. 115 VAC Bus 1 — Pilot’s flight director; autopilot; yaw damper; radar and pilot’s attitude gyro; and VNAV computer/controller.

c. 26 VAC Bus 2 — NAV 2, copilot’s ADI (optional dual flight director installation); and copilot’s HSI; copilot’s RMI; pilot’s RMI compass card and NAV 2 bearing pointer and ADF 2 (optional). Operation of the following equipment can be reinstated by placing the BATT switch to EMER: NAV 2; copilot’s RMI bearing pointer and DG of copilot’s HSI.

MASTER WARNING LIGHT ON STEADY Index

1. Warning Light Circuit Breaker................................................. CHECK

BATTERY OVERHEAT (BATT O’TEMP LIGHT ON) Index

1. Battery Switch......................................................................... EMER

2. Amperage..............................................................NOTE DECREASE

3. If battery voltage is 1 volt less than generator voltage in 30 seconds

to 2 minutes, monitor battery overheat annunciator for possible change.

IF BATTERY O’TEMP LIGHT GOES OUT

4. Battery Switch..........................................................................BATT

IF NO AMP DECREASE OR BATTERY O’TEMP LIGHT FLASHES

4. Flood Lights................................................................. FULL BRIGHT

• The BATT O’TEMP light will extinguish immediately when the generators are turned off if the battery relay is not stuck. With the battery switch in emergency position and the generators off, power is supplied for approximately 30 minutes to the following equipment: COMM 1, NAV 2, Overhead Floodlights, Voltmeter, Copilot’s HSI.

The standby attitude indicator will continue to operate powered by its own emergency battery pack. This battery pack also provides 5 volt emergency instrument lighting. Make sure that the cabin services (refreshment center, cabin lights) are OFF.

IF NORMAL DC POWER IS LOST (BATTERY RELAY NOT STUCK)

6. Generators................................................................................GEN

• BATT O’TEMP light will come back on until battery cools

7. Battery Switch...........................................................................OFF

8. Land as soon as practical.

IF NO DC POWER LOST (BATTERY RELAY STUCK)

6. Microphone Selector......................................................EMER COMM

• Headphones required to receive audio

7. Receiver Select......................................................COMM 1 to HDPH

• Required only if AUTO SELECT is OFF

8. Windshield Bleed Air Manual Valves..............................................OFF

9. DC Power LH and RH BUS NO. 1, 2 and 3 Circuit Breakers..........PULL

10. Land as soon as practical.

WHEN LANDING ASSURED

11. DC Power LH and RH Bus Circuit Breakers...............................RESET

12. Landing Gear..........................................................................DOWN

13. Flaps.......................................................................................LAND

WHEN LANDING WITH EMERGENCY POWER (BATTERY SWITCH-EMER AND BOTH GENERATORS OFF), THE FOLLOWING ARE NOT AVAILABLE:

• THE LANDING GEAR NORMAL OPERATION IS NOT AVAILABLE: THE LANDING GEAR MUST BE LOWERED USING THE BLOWDOWN SYSTEM AND THE LANDING

GEAR WARNING LIGHTS WILL NOT ILLUMINATE.

• THE FLAPS WILL NOT OPERATE. IF NOT PREVIOUSLY IN THE LANDING POSITION, A FLAP INOPERATIVE LANDING MUST BE MADE.

• THE ANTISKID/POWER BRAKE SYSTEM IS INOPERATIVE; ONLY THE EMERGENCY BRAKE SYSTEM IS AVAILABLE.

• THE ENGINE ANTI-ICE VALVES WILL BE OPEN. REFER TO ANTI-ICE ON THRUST CHARTS.

• THE OUTSIDE AIR TEMPERATURE GAGE IS NOT RELIABLE, SO USE CAUTION WHEN APPLYING POWER (EXCEPT FOR GO-AROUND WHERE GROUND TEMPERATURES CAN BE USED).

CABIN DECOMPRESSION (CAB ALT 10,000 FT WARNING LIGHT ON)

1. Oxygen Masks..............................................DON and 100% OXYGEN

2. Oxygen Microphone Switches..................................... MIC OXY MASK

3. Emergency Descent.................................................... AS REQUIRED

4. Pressurization Source Selector.............................................NORMAL

5. Passenger Oxygen........................................ENSURE passengers are receiving oxygen

• MANUAL DROP as required.

6. Transponder.................................................................EMERGENCY

• Headsets or hats worn by the crew should be removed prior to donning the oxygen masks.

• The passenger oxygen masks will deploy automatically when cabin altitude exceeds 13,500 feet ±600 feet.

• If a high altitude airport (field elevation greater than 8000 feet MSL) is selected on the cabin pressurization controller, the CAB ALT 10,000 FT warning light will illuminate at a cabin altitude of 10,000 feet ±350 feet.

IF NOT ARRESTED BY 14,000 FEET CABIN ALTITUDE

7. PRESS SOURCE Select Knob.................................................... EMER

8. Control cabin temperature with LH throttle.

9. Emergency Descent.............................................................INITIATE

11. Below 10,000 feet MSL,

consider PRESS SOURCE Select Knob..................................... NORM

12. Land as soon as practical.

IF ARRESTED BELOW 14,000 FEET CABIN ALTITUDE

1. Land as soon as practical.

BETWEEN 35 AND 70 PSI

1. Throttle (Affected Engine)......................................... REDUCE POWER

2. Land as soon as practical.

BELOW 35 PSI

1. Throttle (Affected Engine)............................................................OFF

2. Accomplish ENGINE FAILURE/PRECAUTIONARY SHUTDOWN

procedure
 

The illumination of this light serves notice to the pilot that

a minimum of 169 pounds of fuel remains in either tank.

1. Fuel Boost...................................................................................ON

• Check boost pump circuit breakers in

• Check boost pump circuit breakers in

2. Fuel Quantity......................................................................... CHECK

CONTINUOUS ILLUMINATION

1. Throttle.................................................................INCREASE POWER

2. Engine Anti-Ice Controls.... CHECK SWITCHES AND CIRCUIT BREAKERS

3. Leave icing environment.

MOMENTARY ILLUMINATION (CYCLES ON AND OFF)

LOSS OF BOTH GENERATORS

1. Generators.......................................RESET THEN GEN

IF ONLY ONE GENERATOR COMES ON

2. Electrical Load....................................................REDUCE as required

• 400 amperes maximum to 35,000 feet; 325 amperes maximum

above 35,000 feet

IF NEITHER GENERATOR COMES ON

2. Floodlights....................................................................FULL BRIGHT

3. Battery Switch......................................................................... EMER

• With the battery switch in the emergency position and the generators off, power is supplied for approximately 30 minutes to the following equipment:
COMM 1, NAV 2,
Overhead Floodlights,
Voltmeter, Copilot’s HSI

The standby attitude indicator will continue to operate powered by its own emergency battery pack. This battery pack also provides 5 volt emergency instrument lighting. Make sure that the cabin services (refreshment center, cabin lights) are OFF.

Microphone Selector......................................................EMER COMM

• Headphones required to receive audio

5. Receiver Select......................................................COMM 1 to HDPH

• Required only if AUTO SELECT is OFF

6. Windshield Bleed Air Manual Valves...................... OFF or MINIMUM for clear vision through windshield

7. Land as soon as practical

WHEN LANDING ASSURED

8. Battery Switch..........................................................................BATT

9. Landing Gear..........................................................................DOWN

10. Flaps.......................................................................................LAND

WHEN LANDING WITH EMERGENCY POWER (BATTERY SWITCH-EMER AND BOTH GENERATORS OFF), THE FOLLOWING ARE NOT AVAILABLE:

• THE LANDING GEAR NORMAL OPERATION IS NOT AVAILABLE: THE LANDING GEAR MUST BE LOWERED USING THE BLOWDOWN SYSTEM AND THE LANDING GEAR WARNING LIGHTS WILL NOT ILLUMINATE.

• THE FLAPS WILL NOT OPERATE. IF NOT PREVIOUSLY IN THE LANDING POSITION, A FLAP INOPERATIVE LANDING MUST BE MADE.

• THE ANTISKID/POWER BRAKE SYSTEM IS INOPERATIVE; ONLY THE EMERGENCY BRAKE SYSTEM IS AVAILABLE.

• THE ENGINE ANTI-ICE VALVES WILL BE OPEN. REFER TO ANTI-ICE ON THRUST CHARTS.

• THE OUTSIDE AIR TEMPERATURE GAGE IS NOT RELIABLE, SO USE CAUTION WHEN APPLYING POWER (EXCEPT FOR GO-AROUND WHERE GROUND TEMPERATURES CAN BE USED).

SINGLE GENERATOR FAILURE (GEN OFF LIGHT ON)

1. Electrical Load.................................................DECREASE if required

• 400 amperes maximum up to 35,000 feet; 325 amperes maximum over 35,000 feet

2. Failed Generator...............CHECK SWITCHES and CIRCUIT BREAKERS;

RESET AS REQUIRED

IF UNABLE TO RESET

Indicates air cycle machine shutdown or failure.

1. NORM Pressurization Circuit Breaker.................................. CHECK IN

2. Temperature Control............................ADJUST TO WARMER SETTING

• May require manual mode

A time delay relay will lock the system into emergency pressurization if air cycle machine temperature remains too high for 12 seconds or more. If machine cools sufficiently in less than 12 seconds, the system will automatically return to the previously selected mode.

3. Pressurization Source Selector................................................. EMER

Wait as least one minute after pressurization source selector has been positioned to EMER before making next selection.

4. Pressurization Source Selector................................ RH, LH, or NORM

IF EMERGENCY PRESSURIZATION REMAINS ON

5. Pressurization Source Selector................................................. EMER

Light must be out before takeoff.

IN FLIGHT

POWER BRAKE SYSTEM FAILURE (POWER BRAKE LOW PRESS AND ANTISKID INOP LIGHTS ON)

1. Skid Control Circuit Breaker....................................................RESET

IF LIGHTS REMAIN ON

2. Plan to use the emergency brake system for landing.

3. Brake Pedals............................. REMOVE FEET FROM BRAKE PEDALS

4. Emergency Brake Handle.....................................PULL AS REQUIRED

ANTISKID SYSTEM DOES NOT FUNCTION DURING EMERGENCY BRAKING. EXCESSIVE PRESSURE ON EMERGENCY BRAKE HANDLE CAN CAUSE BOTH WHEEL BRAKES TO LOCK, RESULTING IN BLOWOUT OF BOTH TIRES.

Consider possibility of partial or total loss of both engines.

Indicates that the respective fuel boost pump was either automatically or manually turned on.

1. Fuel Boost Switch (Affected Pump)................................................ON

• Then.................................................................................NORM

IF FUEL BOOST PUMP ON LIGHT REMAINS ILLUMINATED

1. Land as soon as practical.

1. Speedbrake Control Circuit Breaker...........................................PULL

2. Landing Gear Control Circuit Breaker.........................................PULL

3. Thrust Reverser Circuit Breakers...............................................PULL

• One at a time

IF SYSTEM DEPRESSURIZED

4. Circuit Breakers.....................................................................RESET

• One at a time

• Leave pulled circuit breaker which caused system to

depressurize.

5. Land as soon as practical.

• Reset Landing Gear or Speedbrake Control (not thrust reverser)

Circuit Breaker, if pulled, prior to landing

IF SYSTEM REMAINS PRESSURIZED (INDICATES BYPASS VALVE FAILED)

4. Control Circuit Breakers..........................................................RESET

• One at a time

5. Land as soon as possible.

1. Anti-Ice Switches and Circuit Breakers..................................... CHECK

2. Determine Inoperative System.

1. TEMP Circuit Breaker..............................................................RESET

2. Temperature Select.............................................................MANUAL

3. Manual Hot/Manual Cold Switch....................... MANUAL COLD; hold in this position until overheat light goes out

AFTER LIGHT GOES OUT

4. Auto Temperature Select......................................................... AUTO

If the AIR DUCT O’HEAT light illuminates again, select MANUAL on Auto Temperature Selector and Control Temperature with the MANUAL HOT/MANUAL COLD Switch.

IF LIGHT DOES NOT GO OUT

ON THE GROUND

1. Do not fly the airplane until the malfunction has been repaired.

IN FLIGHT

1. Pressurization Source Selector................... RH, reduce power on right engine to 80% turbine speed

2. EMER PRESS Circuit Breaker.....................................................PULL

3. NORM PRESS Circuit Breaker...................................PULL and RESET

4. EMER PRESS Circuit Breaker...................................................RESET

1. Autopilot/Trim Disengage Switch.............................................PRESS

The autopilot must remain off during all flights conducted

ANTISKID SYSTEM FAILURE (ANTISKID INOP LIGHT ON, POWER BRAKE LOW PRESS LIGHT OUT)
 

1. Antiskid Switch............................................................................ON

2. Skid Control Circuit Breaker....................................................RESET

IF LIGHT REMAINS ON

3. Antiskid Switch...........................................................................OFF

4. Multiply the landing distance of AFM by 1.6.

DIFFERENTIAL POWER BRAKING IS AVAILABLE. HOWEVER, SINCE THE ANTISKID IS INOPERATIVE, EXCESSIVE PRESSURE ON THE BRAKE PEDALS MAY CAUSE WHEEL BRAKES TO LOCK, RESULTING IN TIRE BLOWOUT.

5. Be prepared to use the emergency brake system.

Indicates unlatched nose or tailcone doors, failure or improper position of one or more door switches, and/or possible disengagement of the lower forward cabin door pin.

ON THE GROUND

1. Correct condition prior to flight.

IN FLIGHT

1. Cabin Altitude.................................................. SELECT to 9,500 feet

2. Airspeed..............................................................................REDUCE

3. Passenger Advisory Light............................................. PASS SAFETY

4. Cabin Door....................................................................KEEP CLEAR

5. Descend to a lower altitude.

WINDSHIELD BLEED SWITCH LOW OR HI

• Momentary Illumination (Airflow Stops)

1. If Windshield Bleed Air Switch is HI........................... SELECT LOW

2. Windshield Bleed Air Valves............................................. REDUCE

• Continuous Illumination (Airflow Stops, Probable Controller Failure)

1. Windshield Bleed Air Switch and Valves...................................OFF

2. Windshield Alcohol Anti-Ice...................................... AS REQUIRED

Ten minutes alcohol available to the pilot’s windshield only.

WINDSHIELD BLEED SWITCH OFF

• W/S Air O’Heat Light On Momentary Or Continuous

Indicates probable solenoid valve failure or leak. Winshield air temperature is not regulated. Windshield heat damage is possible. Maintenance is required.