CHECKRIDE Flashcards
BLEED AIR LINE FAILURE
BLEED AIR LINE FAILURE
BLD-Air Valve (affected eng)…….. INSTR / ENVIR OFF
[L BL AIR OFF] or [R BL AIR OFF] – (ILLUM)
CABIN DOOR/CARGO DOOR UNLOCKED
If the CABIN DOOR annunciator illuminates, or if an unlatched airstair/cargo door is suspected:
CABIN DOOR/CARGO DOOR UNLOCKED
All Occupants ………… SEATED /SEAT BELTS FASTENED
CABIN PRESSURIZATION LIMIT
Max Cabin Press Differential …….. ____
CABIN PRESSURIZATION LIMIT
Max Cabin Press Differential …… 6.6 psi
CFIT
CFIT
POWER ………………………………………. MAX
ATTITUDE ………………………………….. WINGS LEVEL
PITCH …………………………………………. 15°
CONFIGURATION ……………………… LEAVE AS IS
CIRCLING
CIRCLING
IAF
TORQUE …………………………… 800 LBS
FLAPS ……………………………….. APPROACH
FAF
TORQUE …………………………… 400 LBS
GEAR ………………………………… DOWN
LEAVING MDA
FLAPS ……………………………….. FULL
PROPS ………………………………. FORWARD
YAW DAMP ……………………….. OFF
ELECTRICAL
Why should the BATT switch be left on during use of external power?
To protect against voltage spikes
ELECTRICAL
If the BATTERY CHG light does not extinguish in flight when the battery control switch is placed to OFF, what action should be taken?
Land at nearest suitable airport
ELECTRICAL
If the BATTERY CHG light does not extinguish in flight when the battery control switch is placed to OFF, what action should be taken?
Land at nearest suitable airport
ELECTRICAL
Why should the BATT switch be left on during use of external power?
To protect against voltage spikes
ELECTRICAL
If the amber BATTERY CHG annunciator illuminates in flight, what initial action does the checklist say to do?
Turn the battery switch OFF
ELECTRICAL
If the BATTERY CHG light does not EXT in flight when the battery control switch is placed to OFF, what action should be taken?
Land at nearest suitable airport
ELECTRICAL
Where is the battery located?
In the right wing center section
ELECTRICAL
What is the rating for the battery?
B. 24-volt, 34/36 ampere-hour
ELECTRICAL
What is the rating for the battery?
24-volt, 34/36 ampere-hour
POH 7-34
ELECTRICAL
What are the functions of the GEN CONTROL UNIT?
- Links the isolation bus with the generator busses.
- Similar to a fuse. Once failed, must be replaced.
- Provides isolation of the generaor in the event of a genrator bus fault.
EXTERNAL POWER LIMITS
Set to _____ volts Capable of generating a minimum of ____ amps momentarily and ____ amps continuously.
EXTERNAL POWER LIMITS
Set to 28.0–28.4 volts Capable of generating a minimum of 1000 amps momentarily and 300 amps continuously
ELECTRICAL
What indication is provided to alert the operator that an external power plug is connected to the airplane?
An EXT PWR light
ELECTRICAL
To protect the battery from damage, the external power voltage must not go over what value for more than two minutes?
30 volts
ELECTRICAL
How much continuous current should the external power unit be capable of supplying?
300 amperes
ELECTRICAL SYSTEMS
Where is the external power connector located?
Under the right wing, outboard of the engine nacelle
ELECTRICAL SYSTEMS
Where is the external power connector located?
Under the right wing, outboard of the engine nacelle
ELECTRICAL
What is the minimum required battery voltage before using an external power unit?
20 volts
ELECTRICAL
What is the minimum required battery voltage before using an external power unit?
20 volts
SYSTEMS ELECTRICAL
When an engine is being started, in what position should its GEN switch be?
OFF
GENERATOR LIMITS
Maximum sustained generator load is limited as follows:
Sea Level - 31,000 Feet Altitude ……. ____
Above 31,000 Feet Altitude ……………. ____
Ground Operation …………………………… ____
GENERATOR LIMITS
Maximum sustained generator load is limited as follows:
Sea Level to 31,000 Feet Altitude ….. 100%
Above 31,000 Feet Altitude ……………. 88%
Ground Operation …………………………… 85%
ELECTRICAL
What is the individual generator rating?
28-volt, 250-ampere
ELECTRICAL
What is the individual generator rating?
28-volt, 250-ampere
ELECTRICAL
Which items are on the Hot Batt Bus?
Which items are on the Hot Batt Bus?
- Exterior entry light / Threshold lights
- Firewall Shutoff Valves
- Clocks
- EXT PWR Sensing
- BATT Relay
ELECTRICAL
What is the rating of each inverter?
115-volt and 26-volt, 400 Hz
ELECTRICAL
After starting the right engine and turning the right generator on, what should the load meter reading decrease to before starting the left engine?
50% (.50 )
ELECTRICAL
After starting the right engine and turning the right generator on, what should the load meter reading decrease to before starting the left engine?
50% (.50 )
ELECTRICAL
To protect the battery from damage, the external power voltage must not go over what value for more than two minutes?
30 volts
ELECTRICAL SMOKE OR FIRE
ELECTRICAL SMOKE OR FIRE
Oxygen System Ready …………. PULL ON (Verify)
Oxygen Masks ………………………. DON (100% position)
Mic Selector …………………………… OXYGEN MASK
Audio Speaker ………………………. ON
EMERGENCY
Simulated One-engine INOP
Propeller …………… 1600 RPM
Power Lever ……… 120 ft - lbs Torque
EMERGENCY DESCENT
EMERGENCY DESCENT
Power Levers ……………. IDLE
Propeller ……………………. FULL FORWARD
Flaps ………………………….. APPROACH
Landing Gear …………….. DWN
Airspeed …………………….. 181 KNOTS MAX
EMERGENCY DESCENT
EMERGENCY DESCENT
POWER …………………………………. IDLE
PROPS ………………………………….. FULL FORWARD
FLAPS …………………………………… APPROACH
GEAR ……………………………………. DOWN
AIRSPEED ……………………………. 181 KTS
10,000’ …………………………………. LEVEL OFF
AIRSPEED ……………………………. 163 KTS
GEAR ……………………………………. UP
FLAPS ………………………………….. UP
EMERGENCY ENGINE SHUTDOWN
EMERGENCY ENGINE SHUTDOWN
Power …………………………………….. INCREASE
Flaps ………………………………………. UP
Gear ……………………………………….. UP
Affected Engine:
Condition Lever …………………….. FUEL CUT OFF
Propeller ………………………………… FEATHER
Firewall Shutoff Valve …………… CLOSED
Fire Ext (if Installed) ………………. ACTUATE
ENGINE FAILURE - GROUND ROLL
ENGINE FAILURE - GROUND ROLL
Power Levers ................................. IDLE Brakes ............................................ AS REQUIRED Operative Engine ........................ MAXIMUM REVERSE
If Insufficient Runway Remains for Stopping:
Condition Levers ........................ CUT OFF Firewall Shutoff Valves ............. CLOSED Master Switch ............................. OFF (Gang bar down)
ENGINE FAILURE AFTER LIFT-OFF
ENGINE FAILURE AFTER LIFT-OFF
Power ……………………………… MAX ALLOWABLE
Airspeed …………………………. Takeoff speed or above
Landing Gear ………………….. UP
Propeller (inop eng) ……….. Verify
FEATHERED Airspeed…….. VYSE (after obs clearance)
ENGINE FAILURE AFTER TAKEOFF
ENGINE FAILURE AFTER TAKEOFF
RUNWAY HEADING ………………………. MAINTAIN (+/-10°)
POWER …………………………………………… MAX ALLOWABLE
POS RATE ……………………………………… GEAR UP
AIRSPEED ………………………………………. V2
PROP …………………………………………….. VERIFY FEATHERED
FLAPS ……………………………………………. UP
CLEAR OF OBSTACLES ……………….. VYSE
ENGINE FAILURE CHECKLIST …….. COMPLETE
ENGINE FIRE ON GROUND
ENGINE FIRE ON GROUND
Affected Engine:
Condition Lever …………………….. CUT OFF
Firewall Shutoff Valve …………… CLOSED
Ignition …………………………………… STARTER ONLY
ENGINE FLAMEOUT (2nd ENGINE)
ENGINE FLAMEOUT (2nd ENGINE)
Power Lever ………………. IDLE
Propeller Lever ………….. DO NOT FEATHER
Condition Lever …………. FUEL CUT OFF
Air Start Procedure ……. CONDUCT
SMOKE OR FUMES
SMOKE OR FUMES
Oxygen System Ready ………… PULL ON (Verify)
Oxygen Masks ……………………… DON (100% position)
Mic Selector ………………………….. OXYGEN MASK
Audio Speaker ……………………… ON
FIRE DETECTION
What does a “L ENG FIRE” (ILLUM) light on the Master Caution Warning Panel indicate?
Fire in Left Engine Compartment
UNSCHEDULED ELECTRIC ELEVATOR TRIM
UNSCHEDULED ELECTRIC ELEVATOR TRIM
Attitude ……………………………… MAINTAIN
Cont Wheel Disc Switch ….. DEP FULLY (2nd Level)
FLOWS - AFTER LANDING
FLOWS - AFTER LANDING
LIGHTS……………………………….OFF
FLAPS…………………………………UP
TEMP/CTRLLR……………………OFF
VENT BLOWER………………….OFF
BLEED AIR VALVES……………ENV OFF
XPNDER……………………………..SET
PRESS DIFF………………………..0
TRIMS…………………………………0/0/TAKEOFF
ENG ANTI-ICE…………………….SET
AUTO IGNITION…………………OFF
AUTO-FEATHER…………………OFF
FLOWS - AFTER START (SINGLE PILOT)
FLOWS - AFTER START (SINGLE PILOT)
INVERTERS……………………………CHECK 1 / 2 (105-120 V) LOADMETERS……………………….PARALLEL
AVIONICS MASTER………………ON
BLEED AIR VALVES………………SET
ENV SYSTEMS CONTROLS…SET
BRAKE DEICE………………………..AS REQ
FLAPS…………………………………….SET
FLIGHT CONTROLS………………CHECK
ENGINE ANTI-ICE…………………..SET
TRIMS……………………………………..0°/0°/TAKEOFF
FLOWS - AFTER TAKEOFF (SINGLE PILOT)
FLOWS - AFTER TAKEOFF (SINGLE PILOT)
YAW DAMP………………………………..ON
PROPS………………………………………..1900
WINDSHIELD / ANTI-ICE…………..AS REQ
PRESSURIZATION…………………….CHECK
FLOWS - BEFORE TAKEOFF (SINGLE PILOT)
FLOWS - BEFORE TAKEOFF (SINGLE PILOT)
PRESSURIZATION…………………………….. CHECK / SET
ELEV TRIM / AUTOPILOT / YD…………. CHECK / SET
- VAC PNEUMATIC PRESS……………….. CHECK
- ALTITUDE ALERT……………………………. CHECK
PROP SYNC……………………………………… ON
INSTRUMENTS…………………………………. CHECK
- GOVENORS / RUDDER BOOST……. CHK (1 at a time)
- AUTOFEATHER……………………………… CHK (2 at a time) / ARM
PROP LEVERS………………………………….. FORWARD
- ENGINE ANTI-ICE …………………………. CHECK / OFF
AUTO IGNITION……………………………….. CHECK / ON
ICE PROTECTION…………………………….. AS REQ
LIGHTS……………………………………………… SET
GENERATOR LOAD………………………….. PARALLEL
ANNUNCIATORS……………………………… OUT
TAKEOFF BRIEFING…………………………. COMPLETE
HOT 5s……………………………………………… ON
X-PNDER…………………………………………… SET
FLOWS - DESCENT
FLOWS - DESCENT
PRESSURIZATION ………….. SET
FUEL BALANCE ……………… CHECK
ENGINE START – [EXTERNAL POWER]
ENGINE START – [EXTERNAL POWER]
[CAUTION: Never connect EXT PWR source to airplane unless battery indicating at least 20v.
If battery voltage less than 20v, battery must be recharged or replaced before connecting EXT PWR.
NOTE: When EXT PWR source used it must be set at 28.0 – 28.4 volts and be capable of producing 1,000 amps momentarily and 300 amps continuously.
The battery should be on to absorb transients present in some EXT PWR sources, EXT PWR ANNUN is provided to alert crew when an EXT DC PWR plug is connected to airplane.]
AVIONICS MASTER ……………………… OFF
L / R GEN ………………………………………. OFF
BATT ……………………………………………… ON
EXT PWR SOURCE ………………………. OFF, THEN CONCT
EXTERNAL POWER SOURCE ……… ON
VOLTMETER …………………………………. 28.0 – 28.4 VOLTS
[NOTE: If the battery partially discharged, the BATT CHG ANNUC will ILLUM approx 6 secs after the EXT PWR is on line.
If ANNUN does not ext w/i 5 mins, refer to BATT CHRGE RATE]
PROP LEVER…………………………………. FEATHER
RH IGN ………………………………………… ON
R IGN ON (ILLUM) / R FUEL PRESS (EXT)
RH COND LVR (12% N1 OR ABV …. LOW IDLE
RH ITT / N1 ……………………………………. (1000°C MAX)
RH OIL PRESS ……………………………… CHECK
RH IGN (50% N1 OR ABOVE) ……… OFF
LH IGN / ENG START …………………… ON
[L IGN ON (ILLUM) / L FUEL PRESS (EXT)
LH COND LVR (12% N1, OR ABV) … LOW IDLE
LH ITT AND N1 ……………………………… (1000°C MAX)
LH OIL PRESS ………………………………. CHECK
LH IGN (50% N1 OR ABOVE ……….. OFF
EXT PWR SOURCE ……………………… DISC
L / R GEN ……………………………………… RESET, THEN ON
PROP LEVERS ……………………………….FULL FORWARD
FLOWS - LANDING
FLOWS - LANDING
AUTOFEATHER………………….ARM
GEAR………………………………….DWN
FLAPS…………………………………SET
PROPS………………………………..FORWARD
A/P / YAW DAMP………………..OFF
FLOWS - PARKING
FLOWS - PARKING
AVIONICS MASTER……………OFF
INVERTER ………………………….OFF
BATTERY…………………………….CHARGED
ITT……………………………………….STABILIZE
CONDITION LEVERS…………FUEL CUTOFF
PROPS………………………………..FEATHER
DC VOLT / LOADMETERS…CHECK
OVRHD PANEL………………….OFF
OXY SYSTEM READY……….OFF
FLOWS - PREFLIGHT - (SINGLE PILOT)
FLOWS - PREFLIGHT - (SINGLE PILOT)
FIRE EXTINGUISHER …………………….. COPILOT SEAT
COPILOT CIRCUIT BREAKERS ……… CHECK
ALTERNATE STATIC AIR SOURCE … NORMAL
OXYGEN SUPPLY FIRE SYSTEM ….. TEST
CABIN TEMP MODE CONTROL …… OFF
ELEC HEAT …………………………………….. OFF
AFT BLOWER …………………………………. OFF
STALL WARNING …………………………… TEST
BLEED AIR VALVES ……………………….. ENVIRON OFF
VENT BLOWER ………………………………. OFF
CONDITION LEVERS …………………….. CUTOFF
PROP LEVERS ……………………………….. FORWARD
POWER LEVERS ……………………………. IDLE
OXY MANUAL OVERRIDE ……………. IN
OXY SYSTEM HANDLE ………………… PULL
OXY ……………………………………………….. CHECK
TRIMS ……………………………………………. ZERO
CABIN PRESSURE ……………………….. PRESS
RUDDER BOOST …………………………. ON
ELEC TRIM …………………………………… ON
PRESS CONTROLLER ………………… 1000’ ABOVE CRUISE
PILOT OXY MASK ………………………. CHECK
ANNUNC PANEL ………………………… TEST
HYD FLUID SENSOR ………………….. TEST
LDG GEAR HANDLE …………………… TEST
BEACON ……………………………………… ON
ICE PROTECTION ………………………. OFF
PROP SYN ………………………………….. ON
ICE VANES …………………………………. CHECK
BATTERY ……………………………………. ON
FUEL SYSTEM …………………………… CHECK
PILOT CIRCUIT BREAKERS ………. CHECK
FLOWS - STARTING
FLOWS - STARTING
ENGINE START – [BAT] VOLT …………. (23v MIN)
RH IGN AND ENG START ………………… ON
[R FUEL PRESS] - (EXT)
RH CONDITION LEVER …………………… (12% N1)
LOW IDLE RH ITT AND N1 ………………. (1000c MAX)
RH OIL PRESSURE …………………………… Check
[NOTE: If no ITT rise observed W/I 10 secs after moving CND LVR to LOW IDLE, move to CUTOFF. Allow 60 secs.]
RH IGN AND ENG START ……………….. 50% N1 – OFF
RH COND LVR …………………………………. HIGH IDLE
RH GEN ……………………………………………. RESET / ON.
In order to turn the GEN ON, the GEN switch must be held in spring loaded RESET position for a min of 1 sec, then released to ON.
BATTERY …………………………………………. CHARGE [LOAD-50% OR LESS.
The BATTERY CHARGE ANNUN will ILLUM approx 6 seconds after the generator is on line.
If the ANNUN does not EXT w/i 5 mins, refer to OTHER NORMAL PROCEDURES.]
RH GEN………………………………………….. OFF
LH IGN / ENG START ……………………. ON
[L FUEL PRESS] - (EXT)
LH COND LVR ………………………………. (12% N1) LOW IDLE
RH GEN…………………………………………. ON
LH ITT / N1 …………………………………….. (1000c MAX)
LH OIL PRESSURE ……………………….. CHECK
LH IGN / ENG START …………………… OFF - 50% N1 – OFF
DC VOLT / LOADMETERS ……………. (27.5 – 29.0 V)
LH GEN………………………………………….. RESET / ON
RH COND LVR ……………………………… LOW IDLE
FUEL SYSTEM
Fuel is heated prior to entering the fuel control unit by:
Engine oil, through an oil-to-fuel heat exchanger
AUXILIARY FUEL
Do not put any fuel into the ____ tanks unless the ____ tanks are full.
AUXILIARY FUEL
Do not put any fuel into the auxiliary tanks unless the main tanks are full
FUEL SYSTEM
When is cross-feed use authorized?
For single-engine operation
FUEL SYSTEM
Which of the following is not affected when the cross-feed switch is moved to the right or left?
The override function for auxiliary fuel transfer
FUEL SYSTEM
Which of the fuel pumps is electrically powered?
Standby boost pump
EMERGENCY ENGINE FUELS
CommAviation Grades….. ____
Military Aviation Grades…. ____
EMERGENCY ENGINE FUELS
COMMERCIAL
- 80, 80/87 (Red)
- 91/98 • 100/130 (Green)
- 100LL Blue - In some countries colored green and designated “100L.”
MILITARY
- 115/145 Purple
FUEL GAUGES
Do not take off if:
- Fuel quantity gauges indicate _____
- Less than _____
FUEL GAUGES
In the yellow arc or Less than 265 lbs of fuel in each main tank system
FUEL SYSTEM
The fuel panel check tests electrical continuity to which items?
- Firewall Shutoff Valves
- Standby boost pumps
- Cross-feed valve
FUEL SYSTEM
Operation of the engine with the FUEL PRESS light illuminated is limited to:
10 hours - main engine fuel pump overhaul or replacement.
FUEL SYSTEM
Which limitations applies to operation with aviation gas?
- Max FL200with 1 standby pump inop
- 150 hours between overhauls
< FL200 in X-feed INOP - Flight above FL310 prohibited
FUEL
OPERATING WITH LOW FUEL PRESSSURE Operation of either engine with its corresponding fuel pressure annunciator (L / R FUEL PRESS) (ILLUM) limited to ______ before overhaul or replacement of the engine-driven fuel pump.
NOTE: Wind-milling time need not be charged against this time limit.
FUEL
Operation of either engine with its corresponding fuel pressure annunciator (L / R FUEL PRESS) illuminated limited to 10 hours before overhaul or replacement of the engine-driven fuel pump.
NOTE: Wind-milling time need not be charged against this time limit.
FUEL IMBALANCE
Max Fuel Imbalance Between Wings…… _______
FUEL IMBALANCE
Max Allowable Fuel Imbalance … 1,000 LBS
FUEL
Name the 4 fuel pumps
Name the 4 fuel pumps
- Engine driven pump - accessory case prior to FCU.
- Engine driven boost pump
- Electric standby boost pump
- Transfer jet pump.
FUEL
Fuel System Description
Fuel System Description
- Separate fuel system for each engine.
- Divided in to main and auxiliary system
- Main system - nacelle tank and five interconnected tanks
- Aux system - 1 tank located between nacelle and fuselage
- Fuel supplied to engine from nacelle tank
- Transfer pump transfers fuel from the auxiliary tank.
- Each system has 4 fuel pumps
FUEL CROSS-FEED
Cross-feeding of fuel is permitted:
one engine is inoperative
EMERGENCY ENGINE FUELS
Limitations on the Use of Aviation Gasoline:
____ hours between engine overhauls.
____ or below if either stdby pump inop.
X-feed required for climbs above ____.
Operation above ____ prohibited.
AIRSPEEDS
150 hours between engine overhauls. FL200 or below if either stdby pump inop. X-feed capability required for climbs above FL200. Above FL310 is prohibited.
FUEL LIMITS APPROVED ENGINE FUELS
Commercial Grades……… ____
Military Grades……………… ____
FUEL LIMITS APPROVED ENGINE FUELS
Commercial Grades
Jet A
Jet A-1
Jet B
Military Grades
JP-4
JP-5
JP-8
FUEL PRESSURE LOW
ENGINE FLAMEOUT (2nd ENGINE)
Standby Pump (failed side) ………… ON
FUEL SYSTEM
Which of the following is a function of the electric standby boost pump?
- Primary boost pump failure
- Aviation gas - climbs above FL200
- X-feed operation
FUEL MANAGEMENT USABLE FUEL (Gallons x 6.7 = Pounds)
Total Usable Fuel ………………….. ____
Each Main Fuel Tank …………….. ____
Each Auxiliary Tank ……………….. ____
FUEL MANAGEMENT USABLE FUEL (Gallons x 6.7 = Pounds)
Total Usable Fuel …….. 3645 lbs (544 gal)
Each Main Fuel Tank … 1,293 lbs (193 gal)
Each Auxiliary Tank …… 529 lbs (79 gal)
GENERAL
What is the width of gear?
17’ 2”
GENERAL
Total Oil capacity?
14.2 quarts
POH 1-10
GENERAL
Oil operating range?
Full - 4.0 Qts LOW
GENERAL
What is the hightto top of tail?
14’ 10”
GENERAL
What is the outside turning radius?
39’ 10”
GENERAL
What is the length from wingtip to wingtip?
54’ 6”
GLIDE
GLIDE
Landing Gear ………………….. UP
Flaps ……………………………….. UP
Propellers ……………………….. FEATHERED
Airspeed …………………………. 135 KNOTS
HIGH DIFFERENTIAL PRESSURE
Cabin Differential Pressure Exceeds 6.6 PSI
HIGH DIFFERENTIAL PRESSURE
Bleed-Air Valves …………………………….. ENVIR OFF
Oxygen (Crew and Passengers) …… AS REQUIRED
Descend …………………………………………. AS REQUIRED
ICING LIMITATIONS
Ice Vanes Extended ……………… ____
Ice Vanes Retracted ……………… ____
Manual Override System………. ____
ICING LIMITATIONS
EXT - =< +5°C
RET - All Takeoff / Flight > +15°C.
ICE VANE EMERG MANUAL EXT - Once activated do not attempt to operate electrically until override assembly inside the engine cowling has been properly reset on ground.
NOTE: Even after the manual extension handle has been pushed back in, the manual override system is still engaged.
ICING LIMITATIONS
Min Ambient Temp for Operation of Deicing Boots ____
Min Airspeed for Sustained Icing Flight ……………. ____
Flaps extended in sustained icing conditions ….. ____
ICING LIMITATIONS
Min Amb Temp for Operat of Deicing Boots …… –40°C
Min Airspeed for Sustained Icing Flight …………… 140 kts
Flaps ……. Prohibited except for approach and landings
ILS - SINGLE ENGINE
ILS - SINGLE ENGINE
2 MI. PRIOR FAF
TORQUE …………………………. 1600 LBS.
FLAPS ……………………………… APPROACH
AIRSPEED ……………………….. 135 KTS
GLIDESLOPE INT
TORQUE ………………………….. 1400 LBS
GEAR ……………………………….. DOWN
PROPS ……………………………… FORWARD
YAW DAMP ………………………. OFF
AIRSPEED …………………………. VREF +10
ILS - TWO ENGINE
ILS - TWO ENGINE
2 MI. PRIOR FAF
TORQUE ………………………….. 800 LBS.
FLAPS ………………………………. APPROACH
AIRSPEED ………………………… 135 KTS
GLIDESLOPE INT
TORQUE …………………………… 800 LBS
GEAR ………………………………… DOWN
FLAPS ……………………………….. DOWN
PROPS ………………………………. FORWARD
YAW DAMP ………………………. OFF
MAXIMUM OBSERVED ITT (°C)
STARTING……………………………………………………. ____
TRANSIENT…………………………………………………. ____
TAKEOFF AND MAX CONTINUOUS…………. ____
CRUISE CLIMB and (NORMAL) …………………. ____
CRUISE……………………………………………………….. ____
MAXIMUM REVERSE…………………………………. ____
MAXIMUM OBSERVED ITT (°C)
Starting …………………………………………….. 1,000°C (5 SECS)
Transient …………………………………………… 850°C
Takeoff and Max Cont………………………. 800°C
Cruise Climb and (Normal) Cruise …… 770°C
Maximum Reverse ……………………………. 750°C
LANDING GEAR CYCLE LIMITS
Landing gear cycles (1 up —1 down)
Limited to:
1 every ……………. 5 minutes
Total ………………… 6 cycles
Followed by: …… 15-minute cool-down
LANDING GEAR MANUAL EXTENSION
LANDING GEAR MANUAL EXTENSION
AIRSPEED ……………………………………………… < 181 KTS
LDG GR CB (Pilot’s Subpanel) ……………… PULL
LANDING GEAR CONTROL …………………. DWN
ALTERNATE EXT HANDLE …………………… PUMP UP / DWN
(Until L / R / NOSE illum / further resistance felt)
ALTERNATE EXT HANDLE ………………….. STOW
NOTE: Ensure ALT EXT handle is in the full DWN position prior to placing it in the securing clip.
LIGHTING
What bus powers the air stair floodlight?
Hot battery bus
LIMITATIONS
What are the starter limits?
40 seconds ON, 60 seconds OFF
40 seconds ON, 60 seconds OFF
40 seconds ON, 30 minutes OFF
MASTER WARNING SYSTEM
When will a red annunciator light extinguish?
When the indicated fault is cleared
MAXIMUM OPERATING PRESSURE-ALTITUDE LIMITS
Normal Operation ……………………………………….. ____
Operation With Yaw Damp System Inop …… ____
MAXIMUM OPERATING PRESSURE-ALTITUDE LIMITS
Normal Operation ……………….. 35,000 feet
Y/D System Inop .. No limit….. Strakes installed.
MAXIMUM OUTSIDE AIR TEMPERATURE LIMITS
Sea Level to FL250 ……………………… ____
Above FL250 ………………………………. ____
MAXIMUM OUTSIDE AIR TEMPERATURE LIMITS
Sea Level to FL250 ………………….. ISA + 37°C
Above FL250 ……………………………. ISA + 31°C
MISSED APPROACH - SINGLE ENGINE
MISSED APPROACH - SINGLE ENGINE
POWER ……………………. MAX ALLOWABLE
POS RATE / GEAR ….. UP
FLAPS ……………………… UP
AIRSPEED ……………….. VYSE
500’ AGL / POWER …. SET
PROP ……………………….. 1900 RPM
MISSED APPROACH – TWO ENGINE
MISSED APPROACH – TWO ENGINE
POWER ………………………………… FULL
FLAPS …………………………………… UP
POS RATE - GEAR ……………….. UP
YAW DAMP ………………………….. ON
500’ ……………………………………… CLIMB POWER
PROPS …………………………………. 1900 RPM
NO FLAP LANDING
NO FLAP LANDING
DOWNWIND
TORQUE ……………………………. 800 LBS
PROPS ……………………………….. 1700 RPM
AIRSPEED ………………………….. 150 KTS
ABEAM
GEAR ………………………………….. DOWN
PROPS ……………………………….. FORWARD
AIRSPEED ………………………….. 135 KTS
BASE
TORQUE …………………………….. 500LBS
AIRSPEED …………………………… VREF +10
Y/D ……………………………………… OFF
FINAL
AIRSPEED …………………………… VREF
VSI ……………………………………….. 500-600 FPM
NON PRECISION APPROACH - SINGLE ENGINE
NON PRECISION APPROACH - SINGLE ENGINE
IAF
TORQUE ……………………………. 1600 LBS
AIRSPEED ………………………….. 150 KTS
FLAPS ………………………………… APPROACH
FAF
GEAR ………………………………….. DOWN
TORQUE …………………………….. 1400 LBS
PROPS ………………………………… FULL
YAW DAMP …………………………. OFF
NON PRECISION APPROACH - TWO ENGINE
NON PRECISION APPROACH - TWO ENGINE
IAF
TORQUE …………………………….. 800 LBS
AIRSPEED ………………………….. 150 KTS
FLAPS ………………………………… APPROACH
FAF
TORQUE ……………………………. 400 LBS
GEAR …………………………………. DOWN
FLAPS ………………………………… DOWN
PROPS ……………………………….. FULL
YAW DAMP ……………………….. OFF
OIL PRESSURE LIMITATIONS
OIL PRESSURE LIMITATIONS
60-85 psi - Power setting < 1100 ft-lb torque.
< 60 psi - Engine shut down, or land at the nearest suitable airport
NOTE: Minimum power +/- 10 psi fluctuations are acceptable
OIL TEMPERATURE
Starting ………………………………………. ____
Takeoff / Max Continuous ………… ____
Climb / (Normal) Cruise … ____
Transient …………………………………… ____
OIL TEMPERATURE
Starting …………………………. –40°C (Minimum)
Takeoff and Max Cont ….. 0°–99°C
(Minimum +55°C recommended for fuel heater operation at T/O power)
Climb / (Normal) Cruise … 0°–99°C
Transient. ……………………….. 0°–104°C (Values > 99°C limited to 10 minutes)
PNEUMATIC
Name the items on the Vacuum / Pneumatic system:
Name the items on the Vacuum / Pneumatic system:
- Door Seal
- Deice Boots
- LDG Gear Hyd Res
- Bleed Air Warning
- Hobbs Meter
- Brake Deice
- Outflow and Safety Valves
- Pressurization Controller
POWER LEVERS
POWER LEVERS
Do not lift power levers in flight. Lifting the power levers in flight, or moving the power levers in flight below the flight idle position, could result in a nose-down pitch and a descent rate leading to aircraft damage and injury to personnel.
POWERPLANT
During a ground start of the right engine, the IGNITION ON light should illuminate:
When the start switch is moved to the IGNITION and ENGINE START position.
POWERPLANT
After lift-off, if an auto-feather is initiated, the immediate requirement is to:
Continue andallow propeller to feather and stop.
POWERPLANT
After lift-off, if an auto-feather is initiated, the immediate requirement is to:
Continue to fly the airplane and allow the propeller to feather and stop.
POWERPLANT
When the AUTO-IGNITION switch is in the ARM position, ignition is:
Inactive but armed if torque is > 400 foot-lbs.
POWERPLANT
If a chip detector light illuminates, you must:
Check engine instruments
- If normal, no action required.
- Otherwise shut the engine down
- Land as soon as practical.
POWERPLANT
Which of the following is the most accurate definition of Engine Torque Readout?
Power delivered to the propeller
POWERPLANT
During a ground start of the right engine, the IGN ON light should illuminate:
When start switch is moved to IGN and ENG START position.
POWERPLANT
During ground operation at LO IDLE, you note that ITT is exceeding 750°C.
Reduce accessory load or increase N1 rpm
POWERPLANT
During ground operation at LOW IDLE, you note that ITT is exceeding 750°C. Which actions would you consider best to reduce ITT?
Reduce accessory load or increase N1 rpm
POWERPLANT
When using maximum reverse power at HI IDLE and full increase RPM, you would expect a maximum propeller rpm of:
1,900
POWERPLANT
As you start taxiing, the OAT is +38°C. You notice that the right engine N1 rpm is decreasing and ITT is rising rather fast.
Which of the following is the best action to take?
- Turn off the refrigerant compressor
* Adjust the condition lever to a higher N1
PRE-FLIGHT
ALTITUDE ALERT CHECK
PRE-FLIGHT
PILOT’S BARO……………… ADJUST - NEAREST 100’
ALT ALT ALERTER ………. MATCH ALTIMETER READING
PILOT’S BARO …………….. INC / DEC ALT 200’ FROM INITIAL ALT
[Aural warning horn - 2 seconds]
ALT ALERT ANNUN on pilot’s / co-pilot’s instrument panel and ALT pre-selector panel (illuminate)
PILOT’S BARO……………… ADJUST TO FIELD ELEV
ALT ALERT ANNUN …….(EXT) at 200’ from alert panel setting.
PREFLGHT CHECKS
FUEL SYSTEM
PREFLGHT CHECKS
SHUTOFF VALVES ………… CLOSE
STDBY PUMPS ………………. ON - (1 at a time. Listen for ops)
L / R FUEL PRESS (ILLUM)
SHUTOFF VALVES ………… OPEN - L / R FUEL PRESS (EXT)
STANDBY PUMPS …………. OFF - L / R FUEL PRESS (ILLUM)
X-FEED …………………………….ALT LH / RHX-FEED (ILLUM)
L / R FUEL PRESS (EXT)
X-FEED ……………………………. OFF
AUX TANK TRANSFER …… AUTO
NO TRANSFER LIGHT…….. PUSH TO TEST
PREFLIGHT
- AUTO-FEATHER CHECK
- AUTO-FEATHER CHECK
POWER LEVERS …………………………. 500 LBS TORQUE
AUTO-FEATHER SWITCH ………….. HOLD TO TEST
POWER LEVERS …………………………. RETARD INDIVID
410 LBS – OPPOSITE AUTO-FEATHER (EXT) 260 LBS – BOTH AUTO-FEATH (EXT) /
PROP FEATHERS RETURN TO 500 LBS AFTER TEST
POWER LEVERS ………………………… IDLE (EXT)]
AUTO-FEATHER SWITCH……………. RELEASE
PREFLIGHT
CHECKS AUTOPILOT CHECK
PREFLIGHT
ELEV TRIM ………………………. TAKEOFF POSITION
ELEC ELEV TRIM …………….. ON
ELEVATOR ……………………….. FORWARD
AUTOPILOT ……………………… ENGAGE YAW / AP – (ILLUM)
ELEC ELEV TRIM ……………… OPERATE BOTH DIRECT A/P disengages / YD remains engaged
ELEVATOR ……………………….. CENTERED
AUTOPILOT ……………………… ENGAGE
Pull back on elevator -Pitch trim moves nose down
Push forward on elevator – Pitch trim moves nose up
AUTOPILOT / TRIM DISC ….. DEPRESS – (1ST LEVEL) YAW DISC / AP DIS – (ILLUM) FLASHING, THEN (EXT)
REPEAT FOR CO-PILOT’S SIDE
PREFLIGHT
- BRAKE DEICE CHECK
BRAKE DEICE
BLEED AIR VALVES ………………………….. OPEN
BRAKE DEICE …………………………………… ON
BRAKE DEICE – (ILLUM)
BRAKE DEICE ………………………………….. OFF
BRAKE DEICE – (EXT)
PREFLIGHT CHECKS
ELECTROTHERMAL PROP DEICE CHECK
ELECTROTHERMAL PROP DEICE CHECK
(CAUTION – Do no operate prop deice when props are static)
AUTOMATIC PROP DEICE ………………. AUTO
DEICE AMMETER …………………………….. 18-24 AMPS
(Monitor 90 secs to ensure automatic timer operation)
MANUAL PROP DEICE ……………………. HOLD IN MANUAL
Small deflection on both loadmeters indicates manual system is operating.
Deice Ammeter ……………………………….. 0 Amps
Manual Prop Deice …………………………. RELEASE
Deice Ammeter ………………………………. 18-24 AMPS
Automatic Prop Deice ……………………. OFF
PREFLIGHT
ELEVATOR TRIM CHECK
PREFLIGHT
ELEC ELEVATOR TRIM ………………………ON
PILOT / CO-PILOT TRIM SWITCHES …CHECK
Move each switch fore and aft – verify trim INOP
Move both switches for and aft – verify trim OPERATES
Ensure pilot’s trim switch overrides copilot’s trim switch
A/P TRIM DISC ………………………………….. PRESS (2ND LEVEL)
ELEC TRIM OFF – (ILLUM)
ELECTRIC ELEVATOR TRIM ……….. OFF, THEN ON
ELEC TRIM OFF – (EXT)
PREFLIGHT CHECK
ENGINE ANTI-ICE
SYS……………………………………………. ON
ENG ANTI ACT………………………….. STBY
ENGINE ANTI-ICE…………………….. OFF
ENG ANTI-ICE ACTUATORS…….. MAIN
ENG ANTI-ICE……………………………. ON
PREFLIGHT CHECK
ICE VANES
Eng anti-ice actuators…..STDBY
Eng anti-ice……………………OFF
Eng anti-ice Actuators…..MAIN
Eng Anti-ice……………………ON
PREFLIGHT
PRESSURIZATION CHECK
PREFLIGHT
BLEED AIR VALVES …………….. OPEN
PRESS CONTROLLER …………. SET (1000’ BLW FLD ELEV)
RATE KNOB…………………………….12:00 POS
CABIN PRESS SWITCH ……….. HLD IN TEST POS
CABIN ALT / VSI………………….. CHK FOR DESC IND
CABIN PRESS SWITCH ……….. REL TO PRESS POS
PRESS CONTR …………………….. SET
PREFLIGHT CHECK
- PRIM GOV / OVERSPEED GOV / RUD BOOST CHECK
PREFLIGHT CHECK
- PRIM GOV / OVERSPEED GOV / RUD BOOST CHECK
BLEEDS ………………………………… ON
RUDDER BOOST …………………. ON
PROP GOV TEST SWITCH ….. HOLD TO TEST
PWR LVRS (Indiv) …………………. INC UNTIL STABLE (1800-1910 RPM)
PROP LEVER ……………………….. RET TO DET, THEN FULL FRWRD
(CHECKS PRIMARY GOV)
POWER LEVER ……………………. INC UNTIL RUD MOVEMENT
POWER LEVER ……………………. IDLE
• REPEAT STEPS 3-6 FOR OPPOSITE ENGINE
PREFLIGHT CHECK
SURFACE DEICE SYSTEM CHECK
SURFACE DEICE SYSTEM CHECK
CONDITION LEVERS ……………………….HIGH IDLE
PNEUMATIC PRESSURE ………………… CHECK
SURFACE DEICE SWITCH ……………… SINGLE / RELEASE
[Pneum Press – Decrease momentarily chk boots.
Inflation time - 6 secs - wings, 4 secs - horiz stabilizer]
SURFACE DEICE SWITCH ……………… MANUAL / HOLD
[Pneum Press – Decrease, chk boots - inflation]
SURFACE DEICE SWITCH ……………….RELEASE, chk boots
CONDITION LEVERS ………………………. LOW IDLE
STALL WARNING HEAT ………………….. CHECK
PITOT HEAT ………………………………………CHECK
PREFLIGHT CHECK
- VACUUM / PNEUMATIC PRESSURE CHECK
- VACUUM / PNEUMATIC PRESSURE CHECK
- Left Bleed Air Valve . INSTR & ENVIR OFF
a. L BL AIR OFF . ILLUMINATED
b. Gyro Suction Gauge and Pneumatic Pressure Gauge in Green
Arc. - Right Bleed Air Valve. INSTR & ENVIR OFF
a. R BL AIR OFF , L BL AIR FAIL &
R BL AIR FAIL . ILLUMINATED
b. Gyro Suction Gauge and Pneumatic Pressure Gauge . ZERO - Left Bleed Air Valve . OPEN
a. L BL AIR OFF , L BL AIR FAIL &
R BL AIR FAIL . EXTINGUISHED
b. Gyro Suction Gauge and Pneumatic Pressure Gauge in Green
Arc. - Right Bleed Air Valve. OPEN
R BL AIR OFF - EXTINGUISHED
RETURN TO PAGE N-15, BEFORE TAKEOFF (RUNUP), STEP 16
PREFLIGHT CHECKS YAW DAMP CHECK
PREFLIGHT CHECKS YAW DAMP CHECK
YAW DAMP …………………. ON YAW (ILLUM)
RUDDER PEDALS ………. CHECK ADDED RES
AP / TRIM DISC ………….. DEPRESS (1ST LEVEL)
YAW DIS (ILLUM) FLASHING, THEN (EXT)
• REPEAT FOR CO-PILOT’S SIDE
PREFLIGHT CHECKS
WINDSHIELD ANTI-ICE CHECK
PREFLIGHT CHECKS
(CHECK PILOT / CO-PILOT ONE AT A TIME)
WINDSHIELD ANTI-ICE …………….. HI
(Observe increase on LH / RH loadmeters)
WINDSHIELD ANTI-ICE …………….. OFF, THEN NORMAL
(Observe increase on LH / RH loadmeters)
WINDSHIELD ANTI-ICE …………….. OFF
PREFLIGHT CHECKS
- ENGINE ANTI-ICE
- ENGINE ANTI-ICE
ENGINE ANTI-ICE ACTUATORS ……………. STDBY
ENGINE ANTI-ICE ………………………………….. OFF
L / R ENG ANTI-ICE – (EXT)
ENGINE ANTI-ICE ACTUATORS …………… MAIN
ENGINE ANTI-ICE …………………………………. ON L / R
ENG ANTI-ICE - (ILLUM)
PRESSURIZATION LOSS
PRESSURIZATION LOSS
Oxygen System Ready …………. PULL ON (Verify)
Oxygen Masks ………………………. DON
Mic Selector ………………………….. OXYGEN MASK
Audio Speaker ……………………… ON
Passenger Manual Drop Out .. PULL ON
Descend as required
PROPELLER ROTATIONAL SPEED LIMITS
Reverse ……………………………………………………….. ____ rpm
All Other Conditions …………………………………… ____ rpm
Transients Not Exceeding 5 Seconds ……….. ____ rpm
PROPELLER ROTATIONAL SPEED LIMITS
Reverse ……………………………………………………….. 1,900 rpm
All Other Conditions …………………………………… 2,000 rpm
Transients Not Exceeding 5 Seconds ……….. 2,200 rpm
PROPELLER ROTATIONAL OVERSPEED LIMITS
> ____ RPM - Indicates failure of the primary governor.
____ RPM Torque is limited to 1,800 foot-lbs.
> ____ RPM Unapproved.
[Indicates failure of both primary and secondary governor.]
____ RPM (5 Secs) - Max propeller overspeed limit.
PROPELLER ROTATIONAL OVERSPEED LIMITS
>2000 RPM - Failure of the primary governor. 2000-2080 RPM - Torque is limited to 1,800 foot-lbs. >2080 RPM - Unapproved.
[Indicates failure of both primary and secondary governor.]
2200 RPM (5 Secs) - Max propeller overspeed limit.
PROPELLER RPM (N2)
Takeoff and Maximum Continuous ……… ____
Transient ……………………………………………….. ____
PROPELLER RPM (N2)
Takeoff and Max Continuous ……. 2000
Transient …………………………………….. 2200 FOR 5 SECS
RPM (% N1)
Takeoff / Maximum Cont…. ____
Transient …………………………… ____
RPM (% N1)
Takeoff / Max Cont…. 101.5%
Transient ………………….. 102.6% [10 SECS]
SEATS
AFT-FACING SEATS
SEATS
- Must be placarded on the leg cross member.
- If occupied, seatback must be in the upright position for takeoff / landing.
- The headrest should be positioned properly.
SPINS
SPINS
If a Spin is entered inadvertently:
Control Column... FULL FORWARD Full Rudder ......... OPPOSITE DIR OF SPIN Power Levers ..... IDLE Controls ............... NEUTRALIZE
WHEN ROTATION STOPS
Execute a smooth pullout
APPROACH TO STALL – ENROUTE
APPROACH TO STALL – ENROUTE
TORQUE ………………………… 200 LBS
PITCH ……………………………. 10°
AIRSPEED …………………….. REDUCE (100 KTS APPROX)
RECOVERY
POWER …………………………. AS NEEDED
ATTITUDE …………………….. REDUCE ANGLE OF ATTACH
AIRSPEED ……………………. INCREASE
APPROACH TO STALL – LANDING CONFIGURATION
APPROACH TO STALL – LANDING CONFIGURATION
TORQUE ……………………….. 200 LBS
FLAPS …………………………… APPROACH
GEAR ……………………………. DOWN
FLAPS ………………………….. FULL
PROPS …………………………… 1900 RPM
ALTITUDE …………………….. DESCEND (500 fpm)
AIRSPEED ……………………. 80 KTS
PITCH …………………………… 8°
RECOVERY
POWER ………………………… AS NEEDED
ATTITUDE ……………………. BREAK ANGLE OF ATTACK
AIRSPEED ……………………. 100 KTS
POS RATE / GEAR ………. UP
FLAPS ………………………….. UP
APPROACH TO STALL – TAKEOFF CONFIGURATION
APPROACH TO STALL – TAKEOFF CONFIGURATION
TORQUE ………………………….. 600 LBS
FLAPS ……………………………… APPROACH
GEAR ………………………………. DOWN
BANK ………………………………. 15° - 30°
AIRSPEED ………………………. 90 KTS
APPROX PITCH ……………… 8°
RECOVERY
POWER ………………………….. AS NEEDED
ATTITUDE …………………….. REDUCE ANGLE OF ATTACH
POS RATE / GEAR ………… UP
AIRSPEED ……………………… VYSE
FLAPS ……………………………. UP
STARTER LIMITS
40 seconds ON 60 seconds OFF
40 seconds ON 60 seconds OFF
40 seconds ON 30 minutes OFF
STEEP TURNS
STEEP TURNS
CONFIGURATION ………………………….. CLEAN
TORQUE …………………………………………. 1200 lbs.
PROPS ……………………………………………. 1700 RPM
AIRSPEED ……………………………………… 180 KTS
BANK ……………………………………………… 45°
PITCH …………………………………………… +4°
AFTER 30° BANK
TORQUE ……………………………………….. 1300 lbs.
TORQUE (FT-LBS)
TAKEOFF / MAX CONT… ____
TRANSIENT…………………….. ____
TORQUE (FT-LBS)
TAKEOFF / MAX CONT …. 2,230
TRANSIENT ……………………… 2,750 (5 SECS)
UNSCHEDULED RUDDER BOOST ACTIVATION
Rudder boost operation without a large variation of power between engines indicates system failure.
UNSCHEDULED RUDDER BOOST ACTIVATION
Direct Control ……. MAINTAIN USING RUDDER PEDALS
Rudder Boost ……. OFF
USE OF OXYGEN
USE OF OXYGEN
Oxygen System Ready …………… PULL ON (verify)
Oxygen Masks ………………………… DON
Mic Selector …………………………….. OXYGEN MASK
Audio Speaker ………………………… ON
Passenger Manual Drop Out ….. PULL ON
VISUAL APPROACH - SINGLE ENGINE
VISUAL APPROACH - SINGLE ENGINE
DOWNWIND
TORQUE ……………………………………………………. 1600 LBS.
AIRSPEED ………………………………………………….. 140 KTS FLAPS
APPROACH AIRSPEED ……………………………….130 KTS
ABEAM
GEAR ………………………………………………………….. DOWN
BASE
AIRSPEED ………………………………………………….. 130 KTS
PROPS ……………………………………………………….. FORWARD
YAW DAMP ……………………………………………….. OFF
CHECKLIST ……………………………………………….. COMPLETE
FINAL AIRSPEED ………………………………………. VREF + 10
VISUAL APPROACH – TWO ENGINE
VISUAL APPROACH – TWO ENGINE
DOWNWIND
TORQUE ……………………………. 800 lbs.
AIRSPEED …………………………. 150 KTS
FLAPS ……………………………….. APPROACH
AIRSPEED ………………………… 135 KTS
ABEAM
GEAR ………………………………… DOWN
BASE
FLAPS ………………………………. DOWN
PROPS ……………………………… FORWARD
YAW DAMP ………………………. OFF
CHECKLIST ……………………… COMPLETE
WEIGHT LIMITS
Maximum Ramp Weight ……….. ____
Maximum Takeoff Weight……… ____
Maximum Landing Weight ……. ____
Maximum Zero Fuel Weight….. ____
Maximum Ramp Weight …….. 12,590 pounds
Maximum Takeoff Weight ….. 12,500 pounds
Maximum Landing Weight …. 12,500 pounds
Maximum Zero Fuel Weight . 11,000 pounds
MAX WEIGHT – BAGGAGE COMPARTMENT
Equipped With Fold-Up Seats ……….. ____
Not Equipped With Fold-Up Seats … ____
MAX WEIGHT – BAGGAGE COMPARTMENT
Equipped With Fold-Up Seats ………. 510 lbs
Not Equipped With Fold-Up Seats .. 550 lbs
