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FENIX B-200 > CHECKRIDE > Flashcards

CHECKRIDE Flashcards

1
Q

BLEED AIR LINE FAILURE

A

BLEED AIR LINE FAILURE

BLD-Air Valve (affected eng)…….. INSTR / ENVIR OFF

[L BL AIR OFF] or [R BL AIR OFF] – (ILLUM)

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2
Q

CABIN DOOR/CARGO DOOR UNLOCKED

If the CABIN DOOR annunciator illuminates, or if an unlatched airstair/cargo door is suspected:

A

CABIN DOOR/CARGO DOOR UNLOCKED

All Occupants ………… SEATED /SEAT BELTS FASTENED

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3
Q

CABIN PRESSURIZATION LIMIT

Max Cabin Press Differential …….. ____

A

CABIN PRESSURIZATION LIMIT

Max Cabin Press Differential …… 6.6 psi

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4
Q

CFIT

A

CFIT

POWER ………………………………………. MAX

ATTITUDE ………………………………….. WINGS LEVEL

PITCH …………………………………………. 15°

CONFIGURATION ……………………… LEAVE AS IS

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5
Q

CIRCLING

A

CIRCLING

IAF

TORQUE …………………………… 800 LBS

FLAPS ……………………………….. APPROACH

FAF

TORQUE …………………………… 400 LBS

GEAR ………………………………… DOWN

LEAVING MDA

FLAPS ……………………………….. FULL

PROPS ………………………………. FORWARD

YAW DAMP ……………………….. OFF

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6
Q

ELECTRICAL

Why should the BATT switch be left on during use of external power?

A

To protect against voltage spikes

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7
Q

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?

A

Land at nearest suitable airport

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8
Q

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?

A

Land at nearest suitable airport

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9
Q

ELECTRICAL

Why should the BATT switch be left on during use of external power?

A

To protect against voltage spikes

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10
Q

ELECTRICAL

If the amber BATTERY CHG annunciator illuminates in flight, what initial action does the checklist say to do?

A

Turn the battery switch OFF

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11
Q

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?

A

Land at nearest suitable airport

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12
Q

ELECTRICAL

Where is the battery located?

A

In the right wing center section

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13
Q

ELECTRICAL

What is the rating for the battery?

A

B. 24-volt, 34/36 ampere-hour

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14
Q

ELECTRICAL

What is the rating for the battery?

A

24-volt, 34/36 ampere-hour

POH 7-34

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15
Q

ELECTRICAL

What are the functions of the GEN CONTROL UNIT?

A
  • 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.
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16
Q

EXTERNAL POWER LIMITS

Set to _____ volts Capable of generating a minimum of ____ amps momentarily and ____ amps continuously.

A

EXTERNAL POWER LIMITS

Set to 28.0–28.4 volts Capable of generating a minimum of 1000 amps momentarily and 300 amps continuously

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17
Q

ELECTRICAL

What indication is provided to alert the operator that an external power plug is connected to the airplane?

A

An EXT PWR light

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18
Q

ELECTRICAL

To protect the battery from damage, the external power voltage must not go over what value for more than two minutes?

A

30 volts

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19
Q

ELECTRICAL

How much continuous current should the external power unit be capable of supplying?

A

300 amperes

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20
Q

ELECTRICAL SYSTEMS

Where is the external power connector located?

A

Under the right wing, outboard of the engine nacelle

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21
Q

ELECTRICAL SYSTEMS

Where is the external power connector located?

A

Under the right wing, outboard of the engine nacelle

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22
Q

ELECTRICAL

What is the minimum required battery voltage before using an external power unit?

A

20 volts

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23
Q

ELECTRICAL

What is the minimum required battery voltage before using an external power unit?

A

20 volts

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24
Q

SYSTEMS ELECTRICAL

When an engine is being started, in what position should its GEN switch be?

A

OFF

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25
Q

GENERATOR LIMITS

Maximum sustained generator load is limited as follows:

Sea Level - 31,000 Feet Altitude ……. ____

Above 31,000 Feet Altitude ……………. ____

Ground Operation …………………………… ____

A

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%

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26
Q

ELECTRICAL

What is the individual generator rating?

A

28-volt, 250-ampere

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27
Q

ELECTRICAL

What is the individual generator rating?

A

28-volt, 250-ampere

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28
Q

ELECTRICAL

Which items are on the Hot Batt Bus?

A

Which items are on the Hot Batt Bus?

  • Exterior entry light / Threshold lights
  • Firewall Shutoff Valves
  • Clocks
  • EXT PWR Sensing
  • BATT Relay
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29
Q

ELECTRICAL

What is the rating of each inverter?

A

115-volt and 26-volt, 400 Hz

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30
Q

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?

A

50% (.50 )

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31
Q

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?

A

50% (.50 )

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32
Q

ELECTRICAL

To protect the battery from damage, the external power voltage must not go over what value for more than two minutes?

A

30 volts

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33
Q

ELECTRICAL SMOKE OR FIRE

A

ELECTRICAL SMOKE OR FIRE

Oxygen System Ready …………. PULL ON (Verify)

Oxygen Masks ………………………. DON (100% position)

Mic Selector …………………………… OXYGEN MASK

Audio Speaker ………………………. ON

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34
Q

EMERGENCY

Simulated One-engine INOP

A

Propeller …………… 1600 RPM

Power Lever ……… 120 ft - lbs Torque

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35
Q

EMERGENCY DESCENT

A

EMERGENCY DESCENT

Power Levers ……………. IDLE

Propeller ……………………. FULL FORWARD

Flaps ………………………….. APPROACH

Landing Gear …………….. DWN

Airspeed …………………….. 181 KNOTS MAX

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36
Q

EMERGENCY DESCENT

A

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

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37
Q

EMERGENCY ENGINE SHUTDOWN

A

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

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38
Q

ENGINE FAILURE - GROUND ROLL

A

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)
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39
Q

ENGINE FAILURE AFTER LIFT-OFF

A

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)

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40
Q

ENGINE FAILURE AFTER TAKEOFF

A

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

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41
Q

ENGINE FIRE ON GROUND

A

ENGINE FIRE ON GROUND

Affected Engine:

Condition Lever …………………….. CUT OFF

Firewall Shutoff Valve …………… CLOSED

Ignition …………………………………… STARTER ONLY

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42
Q

ENGINE FLAMEOUT (2nd ENGINE)

A

ENGINE FLAMEOUT (2nd ENGINE)

Power Lever ………………. IDLE

Propeller Lever ………….. DO NOT FEATHER

Condition Lever …………. FUEL CUT OFF

Air Start Procedure ……. CONDUCT

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43
Q

SMOKE OR FUMES

A

SMOKE OR FUMES

Oxygen System Ready ………… PULL ON (Verify)

Oxygen Masks ……………………… DON (100% position)

Mic Selector ………………………….. OXYGEN MASK

Audio Speaker ……………………… ON

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44
Q

FIRE DETECTION

What does a “L ENG FIRE” (ILLUM) light on the Master Caution Warning Panel indicate?

A

Fire in Left Engine Compartment

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45
Q

UNSCHEDULED ELECTRIC ELEVATOR TRIM

A

UNSCHEDULED ELECTRIC ELEVATOR TRIM

Attitude ……………………………… MAINTAIN

Cont Wheel Disc Switch ….. DEP FULLY (2nd Level)

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46
Q

FLOWS - AFTER LANDING

A

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

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47
Q

FLOWS - AFTER START (SINGLE PILOT)

A

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

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48
Q

FLOWS - AFTER TAKEOFF (SINGLE PILOT)

A

FLOWS - AFTER TAKEOFF (SINGLE PILOT)

YAW DAMP………………………………..ON

PROPS………………………………………..1900

WINDSHIELD / ANTI-ICE…………..AS REQ

PRESSURIZATION…………………….CHECK

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49
Q

FLOWS - BEFORE TAKEOFF (SINGLE PILOT)

A

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

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50
Q

FLOWS - DESCENT

A

FLOWS - DESCENT

PRESSURIZATION ………….. SET

FUEL BALANCE ……………… CHECK

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51
Q

ENGINE START – [EXTERNAL POWER]

A

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

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52
Q

FLOWS - LANDING

A

FLOWS - LANDING

AUTOFEATHER………………….ARM

GEAR………………………………….DWN

FLAPS…………………………………SET

PROPS………………………………..FORWARD

A/P / YAW DAMP………………..OFF

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53
Q

FLOWS - PARKING

A

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

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54
Q

FLOWS - PREFLIGHT - (SINGLE PILOT)

A

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

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55
Q

FLOWS - STARTING

A

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

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56
Q

FUEL SYSTEM

Fuel is heated prior to entering the fuel control unit by:

A

Engine oil, through an oil-to-fuel heat exchanger

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57
Q

AUXILIARY FUEL

Do not put any fuel into the ____ tanks unless the ____ tanks are full.

A

AUXILIARY FUEL

Do not put any fuel into the auxiliary tanks unless the main tanks are full

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58
Q

FUEL SYSTEM

When is cross-feed use authorized?

A

For single-engine operation

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59
Q

FUEL SYSTEM

Which of the following is not affected when the cross-feed switch is moved to the right or left?

A

The override function for auxiliary fuel transfer

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60
Q

FUEL SYSTEM

Which of the fuel pumps is electrically powered?

A

Standby boost pump

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61
Q

EMERGENCY ENGINE FUELS

CommAviation Grades….. ____

Military Aviation Grades…. ____

A

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
62
Q

FUEL GAUGES

Do not take off if:

  • Fuel quantity gauges indicate _____
  • Less than _____
A

FUEL GAUGES

In the yellow arc or 
Less than 265 lbs of fuel in each main tank system
63
Q

FUEL SYSTEM

The fuel panel check tests electrical continuity to which items?

A
  • Firewall Shutoff Valves
  • Standby boost pumps
  • Cross-feed valve
64
Q

FUEL SYSTEM

Operation of the engine with the FUEL PRESS light illuminated is limited to:

A

10 hours - main engine fuel pump overhaul or replacement.

65
Q

FUEL SYSTEM

Which limitations applies to operation with aviation gas?

A
  • Max FL200with 1 standby pump inop
  • 150 hours between overhauls
    < FL200 in X-feed INOP
  • Flight above FL310 prohibited
66
Q

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.

A

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.

67
Q

FUEL IMBALANCE

Max Fuel Imbalance Between Wings…… _______

A

FUEL IMBALANCE

Max Allowable Fuel Imbalance … 1,000 LBS

68
Q

FUEL

Name the 4 fuel pumps

A

Name the 4 fuel pumps

  • Engine driven pump - accessory case prior to FCU.
  • Engine driven boost pump
  • Electric standby boost pump
  • Transfer jet pump.
69
Q

FUEL

Fuel System Description

A

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
70
Q

FUEL CROSS-FEED

Cross-feeding of fuel is permitted:

A

one engine is inoperative

71
Q

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.

A

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.
72
Q

FUEL LIMITS APPROVED ENGINE FUELS

Commercial Grades……… ____

Military Grades……………… ____

A

FUEL LIMITS APPROVED ENGINE FUELS

Commercial Grades

Jet A

Jet A-1

Jet B

Military Grades

JP-4

JP-5

JP-8

73
Q

FUEL PRESSURE LOW

A

ENGINE FLAMEOUT (2nd ENGINE)

Standby Pump (failed side) ………… ON

74
Q

FUEL SYSTEM

Which of the following is a function of the electric standby boost pump?

A
  • Primary boost pump failure
  • Aviation gas - climbs above FL200
  • X-feed operation
75
Q

FUEL MANAGEMENT USABLE FUEL (Gallons x 6.7 = Pounds)

Total Usable Fuel ………………….. ____

Each Main Fuel Tank …………….. ____

Each Auxiliary Tank ……………….. ____

A

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)

76
Q

GENERAL

What is the width of gear?

A

17’ 2”

77
Q

GENERAL

Total Oil capacity?

A

14.2 quarts

POH 1-10

78
Q

GENERAL

Oil operating range?

A

Full - 4.0 Qts LOW

79
Q

GENERAL

What is the hightto top of tail?

A

14’ 10”

80
Q

GENERAL

What is the outside turning radius?

A

39’ 10”

81
Q

GENERAL

What is the length from wingtip to wingtip?

A

54’ 6”

82
Q

GLIDE

A

GLIDE

Landing Gear ………………….. UP

Flaps ……………………………….. UP

Propellers ……………………….. FEATHERED

Airspeed …………………………. 135 KNOTS

83
Q

HIGH DIFFERENTIAL PRESSURE

Cabin Differential Pressure Exceeds 6.6 PSI

A

HIGH DIFFERENTIAL PRESSURE

Bleed-Air Valves …………………………….. ENVIR OFF

Oxygen (Crew and Passengers) …… AS REQUIRED

Descend …………………………………………. AS REQUIRED

84
Q

ICING LIMITATIONS

Ice Vanes Extended ……………… ____

Ice Vanes Retracted ……………… ____

Manual Override System………. ____

A

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.

85
Q

ICING LIMITATIONS

Min Ambient Temp for Operation of Deicing Boots ____

Min Airspeed for Sustained Icing Flight ……………. ____

Flaps extended in sustained icing conditions ….. ____

A

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

86
Q

ILS - SINGLE ENGINE

A

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

87
Q

ILS - TWO ENGINE

A

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

88
Q

MAXIMUM OBSERVED ITT (°C)

STARTING……………………………………………………. ____

TRANSIENT…………………………………………………. ____

TAKEOFF AND MAX CONTINUOUS…………. ____

CRUISE CLIMB and (NORMAL) …………………. ____

CRUISE……………………………………………………….. ____

MAXIMUM REVERSE…………………………………. ____

A

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

89
Q

LANDING GEAR CYCLE LIMITS

A

Landing gear cycles (1 up —1 down)

Limited to:

1 every ……………. 5 minutes

Total ………………… 6 cycles

Followed by: …… 15-minute cool-down

90
Q

LANDING GEAR MANUAL EXTENSION

A

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.

91
Q

LIGHTING

What bus powers the air stair floodlight?

A

Hot battery bus

92
Q

LIMITATIONS

What are the starter limits?

A

40 seconds ON, 60 seconds OFF

40 seconds ON, 60 seconds OFF

40 seconds ON, 30 minutes OFF

93
Q

MASTER WARNING SYSTEM

When will a red annunciator light extinguish?

A

When the indicated fault is cleared

94
Q

MAXIMUM OPERATING PRESSURE-ALTITUDE LIMITS

Normal Operation ……………………………………….. ____

Operation With Yaw Damp System Inop …… ____

A

MAXIMUM OPERATING PRESSURE-ALTITUDE LIMITS

Normal Operation ……………….. 35,000 feet

Y/D System Inop .. No limit….. Strakes installed.

95
Q

MAXIMUM OUTSIDE AIR TEMPERATURE LIMITS

Sea Level to FL250 ……………………… ____

Above FL250 ………………………………. ____

A

MAXIMUM OUTSIDE AIR TEMPERATURE LIMITS

Sea Level to FL250 ………………….. ISA + 37°C

Above FL250 ……………………………. ISA + 31°C

96
Q

MISSED APPROACH - SINGLE ENGINE

A

MISSED APPROACH - SINGLE ENGINE

POWER ……………………. MAX ALLOWABLE

POS RATE / GEAR ….. UP

FLAPS ……………………… UP

AIRSPEED ……………….. VYSE

500’ AGL / POWER …. SET

PROP ……………………….. 1900 RPM

97
Q

MISSED APPROACH – TWO ENGINE

A

MISSED APPROACH – TWO ENGINE

POWER ………………………………… FULL

FLAPS …………………………………… UP

POS RATE - GEAR ……………….. UP

YAW DAMP ………………………….. ON

500’ ……………………………………… CLIMB POWER

PROPS …………………………………. 1900 RPM

98
Q

NO FLAP LANDING

A

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

99
Q

NON PRECISION APPROACH - SINGLE ENGINE

A

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

100
Q

NON PRECISION APPROACH - TWO ENGINE

A

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

101
Q

OIL PRESSURE LIMITATIONS

A

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

102
Q

OIL TEMPERATURE

Starting ………………………………………. ____

Takeoff / Max Continuous ………… ____

Climb / (Normal) Cruise … ____

Transient …………………………………… ____

A

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)

103
Q

PNEUMATIC

Name the items on the Vacuum / Pneumatic system:

A

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
104
Q

POWER LEVERS

A

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.

105
Q

POWERPLANT

During a ground start of the right engine, the IGNITION ON light should illuminate:

A

When the start switch is moved to the IGNITION and ENGINE START position.

106
Q

POWERPLANT

After lift-off, if an auto-feather is initiated, the immediate requirement is to:

A

Continue andallow propeller to feather and stop.

107
Q

POWERPLANT

After lift-off, if an auto-feather is initiated, the immediate requirement is to:

A

Continue to fly the airplane and allow the propeller to feather and stop.

108
Q

POWERPLANT

When the AUTO-IGNITION switch is in the ARM position, ignition is:

A

Inactive but armed if torque is > 400 foot-lbs.

109
Q

POWERPLANT

If a chip detector light illuminates, you must:

A

Check engine instruments

  • If normal, no action required.
  • Otherwise shut the engine down
  • Land as soon as practical.
110
Q

POWERPLANT

Which of the following is the most accurate definition of Engine Torque Readout?

A

Power delivered to the propeller

111
Q

POWERPLANT

During a ground start of the right engine, the IGN ON light should illuminate:

A

When start switch is moved to IGN and ENG START position.

112
Q

POWERPLANT

During ground operation at LO IDLE, you note that ITT is exceeding 750°C.

A

Reduce accessory load or increase N1 rpm

113
Q

POWERPLANT

During ground operation at LOW IDLE, you note that ITT is exceeding 750°C. Which actions would you consider best to reduce ITT?

A

Reduce accessory load or increase N1 rpm

114
Q

POWERPLANT

When using maximum reverse power at HI IDLE and full increase RPM, you would expect a maximum propeller rpm of:

A

1,900

115
Q

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?

A
  • Turn off the refrigerant compressor

* Adjust the condition lever to a higher N1

116
Q

PRE-FLIGHT

ALTITUDE ALERT CHECK

A

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.

117
Q

PREFLGHT CHECKS

FUEL SYSTEM

A

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

118
Q

PREFLIGHT

  • AUTO-FEATHER CHECK
A
  • 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

119
Q

PREFLIGHT

CHECKS AUTOPILOT CHECK

A

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

120
Q

PREFLIGHT

  • BRAKE DEICE CHECK
A

BRAKE DEICE

BLEED AIR VALVES ………………………….. OPEN

BRAKE DEICE …………………………………… ON

BRAKE DEICE – (ILLUM)

BRAKE DEICE ………………………………….. OFF

BRAKE DEICE – (EXT)

121
Q

PREFLIGHT CHECKS

ELECTROTHERMAL PROP DEICE CHECK

A

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

122
Q

PREFLIGHT

ELEVATOR TRIM CHECK

A

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)

123
Q

PREFLIGHT CHECK

ENGINE ANTI-ICE

A

SYS……………………………………………. ON

ENG ANTI ACT………………………….. STBY

ENGINE ANTI-ICE…………………….. OFF

ENG ANTI-ICE ACTUATORS…….. MAIN

ENG ANTI-ICE……………………………. ON

124
Q

PREFLIGHT CHECK

ICE VANES

A

Eng anti-ice actuators…..STDBY

Eng anti-ice……………………OFF

Eng anti-ice Actuators…..MAIN

Eng Anti-ice……………………ON

125
Q

PREFLIGHT

PRESSURIZATION CHECK

A

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

126
Q

PREFLIGHT CHECK

  • PRIM GOV / OVERSPEED GOV / RUD BOOST CHECK
A

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

127
Q

PREFLIGHT CHECK

SURFACE DEICE SYSTEM CHECK

A

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

128
Q

PREFLIGHT CHECK

  • VACUUM / PNEUMATIC PRESSURE CHECK
A
  • VACUUM / PNEUMATIC PRESSURE CHECK
  1. Left Bleed Air Valve . INSTR & ENVIR OFF
    a. L BL AIR OFF . ILLUMINATED
    b. Gyro Suction Gauge and Pneumatic Pressure Gauge in Green
    Arc.
  2. 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
  3. 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.
  4. Right Bleed Air Valve. OPEN
    R BL AIR OFF - EXTINGUISHED
    RETURN TO PAGE N-15, BEFORE TAKEOFF (RUNUP), STEP 16
129
Q

PREFLIGHT CHECKS YAW DAMP CHECK

A

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

130
Q

PREFLIGHT CHECKS

WINDSHIELD ANTI-ICE CHECK

A

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

131
Q

PREFLIGHT CHECKS

  • ENGINE ANTI-ICE
A
  • 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)

132
Q

PRESSURIZATION LOSS

A

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

133
Q

PROPELLER ROTATIONAL SPEED LIMITS

Reverse ……………………………………………………….. ____ rpm

All Other Conditions …………………………………… ____ rpm

Transients Not Exceeding 5 Seconds ……….. ____ rpm

A

PROPELLER ROTATIONAL SPEED LIMITS

Reverse ……………………………………………………….. 1,900 rpm

All Other Conditions …………………………………… 2,000 rpm

Transients Not Exceeding 5 Seconds ……….. 2,200 rpm

134
Q

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.

A

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.
135
Q

PROPELLER RPM (N2)

Takeoff and Maximum Continuous ……… ____

Transient ……………………………………………….. ____

A

PROPELLER RPM (N2)

Takeoff and Max Continuous ……. 2000

Transient …………………………………….. 2200 FOR 5 SECS

136
Q

RPM (% N1)

Takeoff / Maximum Cont…. ____

Transient …………………………… ____

A

RPM (% N1)

Takeoff / Max Cont…. 101.5%

Transient ………………….. 102.6% [10 SECS]

137
Q

SEATS

AFT-FACING SEATS

A

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.
138
Q

SPINS

A

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
139
Q

APPROACH TO STALL – ENROUTE

A

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

140
Q

APPROACH TO STALL – LANDING CONFIGURATION

A

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

141
Q

APPROACH TO STALL – TAKEOFF CONFIGURATION

A

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

142
Q

STARTER LIMITS

A

40 seconds ON 60 seconds OFF

40 seconds ON 60 seconds OFF

40 seconds ON 30 minutes OFF

143
Q

STEEP TURNS

A

STEEP TURNS

CONFIGURATION ………………………….. CLEAN

TORQUE …………………………………………. 1200 lbs.

PROPS ……………………………………………. 1700 RPM

AIRSPEED ……………………………………… 180 KTS

BANK ……………………………………………… 45°

PITCH …………………………………………… +4°

AFTER 30° BANK

TORQUE ……………………………………….. 1300 lbs.

144
Q

TORQUE (FT-LBS)

TAKEOFF / MAX CONT… ____

TRANSIENT…………………….. ____

A

TORQUE (FT-LBS)

TAKEOFF / MAX CONT …. 2,230

TRANSIENT ……………………… 2,750 (5 SECS)

145
Q

UNSCHEDULED RUDDER BOOST ACTIVATION

Rudder boost operation without a large variation of power between engines indicates system failure.

A

UNSCHEDULED RUDDER BOOST ACTIVATION

Direct Control ……. MAINTAIN USING RUDDER PEDALS

Rudder Boost ……. OFF

146
Q

USE OF OXYGEN

A

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

147
Q

VISUAL APPROACH - SINGLE ENGINE

A

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

148
Q

VISUAL APPROACH – TWO ENGINE

A

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

149
Q

WEIGHT LIMITS

Maximum Ramp Weight ……….. ____

Maximum Takeoff Weight……… ____

Maximum Landing Weight ……. ____

Maximum Zero Fuel Weight….. ____

A

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

150
Q

MAX WEIGHT – BAGGAGE COMPARTMENT

Equipped With Fold-Up Seats ……….. ____

Not Equipped With Fold-Up Seats … ____

A

MAX WEIGHT – BAGGAGE COMPARTMENT

Equipped With Fold-Up Seats ………. 510 lbs

Not Equipped With Fold-Up Seats .. 550 lbs

FENIX B-200 (5 decks)

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