350 Flashcards
Maneuvering Speed (Va)
184 KIAS
Maximum Flap Extension/Extended Speed (Vfe)
Approach (<APP (white)) ……………202 KIAS
Full Down (<DN (white)) …………….158 KIAS
Maximum Landing Gear Operating Speed (VLO)
Extension……….184 KIAS
Retraction………166 KIAS
Maximum Landing Gear Extended Speed (VLE)
184 KIAS
Maximum Operating Speed (VMO)
Sea Level to 21,000 feet….._____
21,000 to 35,000 feet………._____-_____
Seal Level to 21,000 feet ……….263 KIAS
21,000 to 35,000 feet …………….263-194*KIAS
*0.58 Mach
Airspeed Indicator Display
Solid Red Bar (at bottom of airspeed indicator scale)
Maximum weight, flaps down & idle power _________
81 KIAS
Airspeed Indicator Display
Solid Red Bar (Bottom of AI)
Max weight, flaps approach, idle power ….._______
Max weight, flaps up, idle power …………….._______
Max weight, flaps approach, idle power …..89 KIAS
Max weight, flaps up, idle power ……………..96 KIAS
AIRSPEED INDICATOR DISPLAY
Blue Line One-Engine-Inoperative Best Rate-of-Climb Speed
__________
Blue Line One-Engine-Inoperative Best Rate-of-Climb Speed
125 KIAS
ENGINE OPERATING LIMITS
Maximum ITT °C
Starting ………._____
Idle………………_____
Takeoff……….._____
Max Cruise…._____
Max Reverse.._____
Starting ……….1000 degrees for 5 seconds
Idle………………750 C
Takeoff………..820 C
Max Cruise….820 C
Max Reverse..760 C
ENGINE OPERATING LIMITS
Gas Generator RPM % N1
Max Cruise.._____
Takeoff………_____
Max Cruise..104
Takeoff……..104
ENGINE OPERATING LIMITS
Oil Temperature Limits
Minimum ………………………………………….._____
Maximum …………………………………………._____
Limited to a maximum of 10 minutes .._____
Minimum …………………………………………..-40 C
Maximum ………………………………………….+110 C
Limited to a maximum of 10 minutes ..between 99 C and 110 C
EXTERNAL POWER LIMITS
Set to ____ - ____ volts
minimum of ____ amps momentarily
and ____ amps continuously
Set to 28.0- 28.4 volts
minimum of 1000 amps momentarily
and 300 amps continuously
GENERATOR LIMITS
Maximum sustained generator load is limited as follows:
In Flight:
Sea Level to 34,000 feet altitude……______
Above 34,000 feet altitude…………….______
Sea Level to 34,000 feet altitude………………………………….100%
Above 34,000 feet altitude…………………………………………….95%
GENERATOR LIMITS
Maximum sustained generator load is limited as follows:
Ground Operation:
N1 MAXIMUM GENERATOR LOAD
62% to 70% ………………..______
70% to 100%……………….______
N1 MAXIMUM GENERATOR LOAD
62% to 70% ……………………………. 75%
70% to 100% ………………………….. 100%
STARTER LIMITS
_________ ON, __________ OFF,
_________ ON, __________ OFF,
_________ ON, __________ OFF
30 seconds ON, 5 minutes OFF,
30 seconds ON, 5 minutes OFF,
30 seconds ON, 30 minutes OFF
LIMITATIONS ON THE USE OF AVIATION GASOLINE
What are the limitations on the use of aviation gasoline (AVGAS)?
- Operation is limited to 150 hours between engine overhauls.
- Operation is prohibited if either standby fuel pump is inoperative.
- Crossfeed capability is required for flight above 20,000 feet pressure altitude (FL200).
FUEL MANAGEMENT
USABLE FUEL (GALLONS X 6.7 = POUNDS)
Total Quantity…..___ gallons ( ____ pounds)
* Each Main Fuel Tank
System….………….___ gallons ( ____ pounds)
* Each Auxiliary Fuel Tank………………………………….___ gallons ( ___ pounds)
Total Quantity…539 gallons ( 3611 pounds)
* Each Main Fuel Tank
System….…………190 gallons ( 1273 pounds)
* Each Auxiliary Fuel Tank.……79.5 gallons ( 533 pounds)
FUEL MANAGEMENT
FUEL IMBALANCE
Maximum allowable fuel imbalance between the wing fuel system?
FUEL CROSSFEED
Permitted only for what circumstance?
FUEL IMBALANCE
Fuel imbalance between wing fuel systems is 300 pounds
FUEL CROSSFEED
Permitted only when one engine is inoperative
FUEL MANAGEMENT
FUEL GAGES IN THE YELLOW ARC
Do not take off if fuel quantity gauges indicate in yellow arc
or indicate less than ___ lbs of fuel in each wing system.
Do not take off if fuel quantity gages indicate in yellow arc
or indicate less than 265 lbs of fuel in each wing system.
FUEL MANAGEMENT
OPERATING WITH LOW FUEL PRESSURE
Operation with the [L FUEL PRES LO] /
[R FUEL PRES LO] illuminated is limited to _____ hours.
Operation with the [L FUEL PRES LO] / [R FUEL PRES LO] illuminated is limited to 10 hours.
PROPELLERS
PROPELLER ROTATIONAL SPEED LIMITS
Minimum idle speed……………………………………. _____________
PROPELLER AUTOFEATHER
Must be operable for ______ and must be armed for _______, _______, _______, and _______.
Minimum idle speed…………………………………………….. 1050 rpm
PROPELLER AUTOFEATHER - Must be operable for all flights and must be armed for
takeoff, climb, approach, and landing.
MISCELLANEOUS INSTRUMENT MARKINGS
PNEUMATIC PRESSURE GAUGE Green Arc (Normal Operating Range)
Green Arc (Normal Operating Range)…………………12 to 20 psi
MAXIMUM OPERATING ALTITUDE LIMITS
Normal Operation ….______
Normal Operation ………………35,000 feet
MAXIMUM OUTSIDE AIR TEMPERATURE LIMITS
Sea Level to 25,000 feet pressure altitude …… _____________
Sea Level to 25,000 feet pressure altitude ………….. ISA + 37°C
CABIN PRESSURIZATION LIMIT
Maximum Cabin Pressure Differential………._______
Maximum Cabin Pressure Differential ……. 6.6 psi
SYSTEMS AND EQUIPMENT LIMITS
RUDDER BOOST Must be operational for ________
RUDDER BOOST Must be operational for all flights
SYSTEMS AND EQUIPMENT LIMITS
LANDING GEAR CYCLE LIMITS
Limited to _____ every ________ for a total of ________, followed by a ________ cool-down period.
LANDING GEAR CYCLE LIMITS
Limited to one every 5 minutes for a total of 6 cycles, followed by a 15-minute cool-down period.
SYSTEMS AND EQUIPMENT LIMITS
BRAKE DEICE (IF INSTALLED) Is not to be operated above _____
BRAKE DEICE (IF INSTALLED) Is not to be operated above 15°C
ICING LIMITATIONS
Min ambient temp for operation of deicing boots…. ________
Min airspeed for sustained icing flight………………….. ________
Min ambient temp for operation of deicing boots…………-40°C
Min airspeed for sustained icing flight…………………..140 knots
ICING LIMITATIONS
[LENG ANTI-ICE] and [R ENG ANTI-ICE],
shall be ___ for operation in ambient temperatures of _____ or below
when ____________ _________ cannot be assured.
[LENG ANTI-ICE] and [R ENG ANTI-ICE],
shall be ON for operation in ambient temperatures of +5 C or below
when FLIGHT FREE OF VISIBLE MOISTURE cannot be assured.
ICING LIMITATIONS
[LENG ANTI-ICE] and [R ENG ANTI-ICE], shall be ____ for ______ _________________
in ambient temperatures of above______.
[LENG ANTI-ICE] and [R ENG ANTI-ICE], shall be OFF for TAKE-OFF OPERATIONS
in ambient temperatures of above +10 C.
AUTOPILOT
Minimum engage height after takeoff
Minimum use height during cruise
Minimum use height during approach
Minimum use height during steep approach
Minimum engage height after takeoff………………….. 400 ft AGL
Minimum use height during cruise……………………. 1000 ft AGL
Minimum use height during approach………………….. 79 ft AGL
Minimum use height during steep approach……….. 160 ft AGL
AUTOPILOT
What are the maximum coupled intercept angles?
Nav and Localizer …………. _____________
Back Course……………………_____________
What are the maximum coupled intercept angles?
Nav and Localizer ……………..Less than 90°
Back Course………………………70°
WEIGHTS
Maximum Ramp Weight………………………………. _____________
Maximum Ramp Weight ……15,100 lbs
WEIGHTS
Maximum Take-off Weight…………………………… _____________
Maximum Take-off Weight …….15,000 lbs
WEIGHTS
Maximum Landing Weight…………………………… _____________
Maximum Landing Weight ……15,000 lbs
WEIGHTS
Maximum Zero-Fuel Weight…………………………. _____________
Maximum Zero-Fuel Weigh …….12,500 lbs
WEIGHTS
Maximum Weight in Baggage Compartment: ________
Maximum Weight in Baggage Compartment: 550 lbs
EMERGENCY AIRSPEEDS
One-Engine-Inoperative
Best-Angle-of-Climb (VXSE)…._____
Best-Rate-of-Climb (VYSE)…._____
Enroute Climb….______
Best-Angle-of-Climb (VXSE)……………………………………125 Knots
Best-Rate-of-Climb (VYSE)……………………………………..125 Knots
Enroute Climb……………………………………………………..125 Knots
EMERGENCY AIRSPEEDS
Air Minimum Control Speeds (VMCA)
Flaps Up ….._____
Flaps Approach ….._____
Flaps Up ………………………………………………………………94 Knots
Flaps Approach ……………………………………………………93 Knots
EMERGENCY AIRSPEEDS
Emergency Descent ….._____
Maximum Range Glide ….._____
Emergency Descent ……………………………….184 Knots
Maximum Range Glide …………135 Knots
ENGINE FAILURE
ENGINE FIRE OR FAILURE IN FLIGHT
[ENG FIRE F/W PUSH CLOSED]
Affected Engine:
1. Condition Lever ………….. FUEL CUTOFF
2. Prop Lever …………………. FEATHER
3. Firewall Fuel Valve ……….CLOSE
4. Fire Extinguisher
(if fire warning persists) …ACTUATE
ENGINE FAILURE
ENGINE FIRE ON GROUND
[ENG FIRE F/W PUSH CLOSED]
Affected Engine:
1. Condition Lever…………FUEL CUTOFF
2. Firewall Fuel Valve…….CLOSE
3. Starter Switch………….. STARTER ONLY
4. Fire Extinguisher
(if fire warning persists) ….. ACTUATE
ENGINE FAILURE
EMERGENCY ENGINE SHUTDOWN ON THE GROUND
- Condition Levers………….FUEL CUTOFF
- Prop Levers ………………. FEATHER
- Firewall Fuel Valves …….CLOSE
- Master Switch (gang bar) ….OFF
- Battery Bus ………………..EMERG OFF
- ESIS Power ………………….OFF
ENGINE FAILURE
ENGINE FAILURE DURING TAKEOFF (AT OR BELOW V1) — TAKEOFF ABORTED
- Power Levers………………GROUND FINE
- Brakes ………………………..MAXIMUM
ENGINE FAILURE
ENGINE FAILURE DURING TAKEOFF (AT OR ABOVE V1) — TAKEOFF CONTINUED
- VR Speed
ROTATE TO APPROX. 10° PITCH ATTITUDE - Landing Gear (when positive climb established)……..UP
- Airspeed…..MAINTAIN V2 TO 400 FT AGL
- Propeller (inoperative engine)
VERIFY FEATHERED
ENGINE FAILURE
ENGINE FAILURE IN FLIGHT — BELOW AIR MINIMUM CONTROL SPEED (VMCA)
- Power ……………..REDUCE AS REQUIRED TO MAINTAIN CONTROL
- Nose ………………..LOWER TO ACCELERATE ABOVE VMCA
ENGINE FAILURE
ELECTRICAL SMOKE OR FIRE
- Oxygen Mask(s) ……………………DON
- Mask Selector Switch ……………EMERG
- Mic Switch(es)……………………….OXY
ENGINE FAILURE
ENVIRONMENTAL SYSTEM — SMOKE OR FUMES
- Oxygen Mask(s)……………………DON
- Mask Selector Switch ………..…EMERG
- Mic Switch(es) ……………………..OXY
AIRSTAIR DOOR/CARGO DOOR UNLOCKED [DOOR UNLOCKED]
If the [DOOR UNLOCKED] illuminates, or if an unlatched airstair door / cargo door is suspected:
- All Occupants……………………SEATED WITH SEAT BELTS SECURELY FASTENED
EMERGENCY DESCENT CHECKLIST
- Power Levers …………..IDLE
- Prop Levers ……………..FULL FORWARD
- Flaps (202 knots maximum)..APPROACH
- Landing Gear (184 knots maximum) DOWN
- Airspeed……….184 KNOTS MAXIMUM
GLIDE CHECKLIST
- Landing Gear ……………………UP
- Flaps…………………………………UP
- Prop Levers ……………………. FEATHERED
- Airspeed ………………………….135 KNOTS
ELECTRICAL
DUAL GENERATOR FAILURE
[L DC GEN] & [R DC GEN]
(yellow annunciator)
- Instrument Emergency Lights
(if required)…………………..ON - Generators …………….. RESET, THEN ON
If Either Generator Will Reset:
- Operating Generator Loadmeter ……………………………………..MONITOR
ELECTRICAL
DUAL GENERATOR FAILURE
[L DC GEN] & [R DC GEN]
(yellow annunciator)
(continued)
If Neither Generator Will Reset:
- ECS Mode…………………………..OFF
- Cockpit/Cabin Blower…………AUTO
- Non-essential Equipment…..OFF
ENVIRONMENTAL SYSTEMS
USE OF OXYGEN
CREW
- Oxygen Mask(s)…………………….DON
- Mic Switch(es)……………………….OXY
ENVIRONMENTAL SYSTEMS
PRESSURIZATION LOSS
[CABIN ALT HI] (red annunciator)
- Oxygen Mask(s)……………………..DON
- Mic Switch(es)………………………..OXY
- Passenger Manual Drop Out….PULL ON
- Descend……………………..…AS REQUIRED
ENVIRONMENTAL SYSTEMS
HIGH DIFFERENTIAL PRESSURE
[CABIN DIFF HI] (red annunciator)
- Bleed Air Valves…………….ENVIR OFF
- Oxygen (crew and passengers)…………….. AS REQUIRED
- Descend ……………………… AS REQUIRED
ENVIRONMENTAL SYSTEMS
AUTO-DEPLOYMENT OXYGEN SYSTEM FAILURE
[CABIN ALT HI] (red) ILLUMINATED,
[PASS OXYGEN ON] (white) EXTINGUISHED
- Passenger Manual Drop Out………………..PULL ON
ENVIRONMENTAL SYSTEMS
BLEED AIR FAIL
[L BLEED FAIL] OR [R BLEED FAIL] (red)
- Bleed Air Valve (affected engine)………… PNEU & ENVIR OFF
SPINS
- Control Column………….. FULL FORWARD, AILERONS NEUTRAL
- Full Rudder………………… OPPOSITE THE DIRECTION OF SPIN
- Power Levers……………….IDLE
- Rudder………………………..NEUTRALIZE WHEN ROTATION STOPS
- Execute a smooth pullout.
FLIGHT CONTROLS
UNSCHEDULED ELECTRIC PITCH TRIM ACTIVATION
- Airplane Attitude
MAINTAIN USING ELEVATOR CONTROL - AP/Trim Disconnect
DEPRESS FULLY & HOLD
FLIGHT CONTROLS
UNSCHEDULED RUDDER BOOST ACTIVATION
- AP/Trim Disconnect
DEPRESS TO 1ST LEVEL AND HOLD - Rudder Boost ………….OFF
If Condition Persists:
- YD/AP DISC
(on Flight Guidance Panel)…..PULL DOWN
AVIONICS
AUTOPILOT FAILURES AUTOPILOT MISTRIM [E] OR [A]
If A Mistrim Indication Continues For More Than A Few Seconds
- Flight Controls………………..HOLD FIRMLY
- AP ……………………………….…DISENGAGE
AVIONICS
AUTOPILOT TRIM FAIL [TRIM]
- Flight Controls……………….HOLD FIRMLY
- AP …………………………………DISENGAGE
AVIONICS
AUTOPILOT AUTOMATIC DISENGAGEMENT
If An Automatic Disengagement Occurs:
- Maintain airplane control.
- AP /TRIM Disconnect
DEPRESS TO 1ST LEVEL TO CANCEL HORN
AVIONICS
ENHANCED GROUND PROXIMITY WARNING SYSTEM
(EGPWS) (IF INSTALLED) In IMC Or At Night:
- Wings……………………………..LEVEL
- Power……………………….MAX ALLOWABLE
- Pitch………………………….INCREASE
* Promptly and smoothly increase pitch towards an initial pitch attitude of 20º to 25º.
- Adjust as required to avoid continuous buffeting and/or stall warning.
- Adjust to maintain 125 KIAS.
- Gear and Flaps…………………..UP
