turbo commander 690b checklist.pdf

Turbo Commander 690B

CHECKLIST

TURBOCOMMANDER 690B RG AVIATION

AIRCRAFT CHECKLIST

30/07/15 TURBOCOMMANDER 690B AIRCRAFT REV ORIGINAL Página 2 de 30

PREFLIGHT INSPECTION This preflight inspection is to be used with the Turbocommander 690B

models.

An essential part of the preparations made before any flight is the preflight

inspection. During this inspection, verify the aircraft's physical readiness. A

thorough preflight before the first flight of the day is critical to determine

airworthiness and provide for the highest degree of safety.

No detail should be overlooked during the first preflight of the day. Abnormal

conditions (e.g., low tire pressure) must be corrected prior to flight. Even

minor discrepancies should be rectified prior to flight to ensure safety.

The preflight inspection begins inside the aircraft where the initial cockpit

setup and essential functions are verified. The actual exterior inspection

follows; it begins at the cabin door, proceeds clockwise around the aircraft,

and ends at the left wing root.

Lastly, the pilot returns to the interior of the aircraft to check the passenger

compartment and cockpit for flight readiness.


AIRCRAFT CHECKLIST


CHECKLIST USAGE Tasks are executed in one of two ways:

� as a sequence that uses the layout of the cockpit controls and indicators as cues

(i.e., “flow pattern”).

� as a sequence of tasks organized by event rather than panel location (e.g., After

Takeoff, Gear – RETRACT, Flaps - UP).

The placing of items in a flow pattern or series provides organization and serves as

a memory aid.

A challenge-response review of the checklist follows execution of the tasks; the

pilot monitoring (PM) calls the item, and the appropriate pilot responds by verifying

its condition (e.g., Engine Anti-Ice [challenge] – ON [response]).

Two elements are inherent in the execution of normal procedures:

� use of either the cockpit layout or event cues to prompt the correct switch and/or

control positions.

� use of normal checklists as “done” lists.


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PREFLIGHT INSPECTION GENERAL All Surfaces . . . . . . . . . . . . . . . . FREE FROM SNOW/ICE/FROST

Protective Covers/Plugs . . . . . . . . . . . . . . . . REMOVED/STOWED

Remove safety covers from the engines, static ports, pitot probes, stall vanes,

angle-of-attack sensor and Rosemount probe. Remove keys from locks.

All Intakes/Exhausts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

NOTE: If night flight is anticipated, check actual operation of navigation and strobe lights.

INTERIOR INSPECTION Visual Inspection

1. Cabin Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

2. Airplane Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

3. Landing Gear Control Lever. . . . . . . . . . DOWN & LATCHED

4. Engine Control Switches . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

5. Overhead Panel Switches . . . . . . . . . . . . . . . . .AS REQUIRED

6. Battery Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

7. Parking Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

8. Fuel Quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

9. Trim Tabs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET TO ZERO

10. Lights and Ice Protection Heat . . . . . . . . . . . . . . . . CHECKED

If night IFR, or flight into icing conditions are anticipated, the following must be

physically or visually checked for proper orientation.

a. Left Pitot Heat

b. Right Pitot Heat

c. Static Source Heat

d. Right Wing Ice Light

e. Stall Warning Vane Heat

f. Right Landing Light

g. Right Fuel Vent Heat

h. Right Wing Tip Light

i. Tail Light

j. Left Wing Tip Light

k. Left Fuel Vent Heat

l. Left Landing Light

m. Left Wing Ice Light

n. Instrument Panel Lights


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o. Overhead Flood Lights Ground operation of ice protection electric heaters

must be limited to 30 seconds or less.

12. Battery Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

NOTE: Automatic over-temperature protection will prevent the fuel vent heaters from operation in

warm ambient temperatures.

CAUTION: Ground operation of ice protection electric heaters must be limited to 30 seconds or

less.


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PREFLIGHT INSPECTION

PREFLIGHT INSPECTION WALKAROUND PATH


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EXTERIOR INSPECTION (CLOCKWISE)

A LEFT WING AND FORWARD FUSELAGE

1. Upper Left Wing Surface . . . . . . . . . . . . . . . . . . . . . . . CHECK

(Fuel caps, general condition. May be accomplished by standing in main

door opening)

2. OAT probe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

3. Entry Door, Bayonets and Seal . . . . . . . . . . . . . . . . . . . CHECK

4. Left Pitot head. . . . . . . . . . .CHECK (cover removed and clear)

5. Left Windshield and Wiper . . . . . . . . . . . . . . . . . . . . . CHECK

6. Nose Access Door. . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

7. Nose Gear Doors and Wheel Well . . . . . . . . . . . . . . . . CHECK

8. Radome . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

9. Right Pitot Head . . . . . . . . .CHECK (cover removed and clear)

10. Right Windshield and Wiper . . . . . . . . . . . . . . . . . . . . CHECK

11. Emergency Exit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

12. Static Port . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CLEAR

B RIGHT ENGINE

1. Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Inlet Dust Cover . . . . . . . . . . . . . . . . REMOVE (if installed)

b. Prop and Spinner (Rotation and condition). Listen for unusual noises as prop

is hand rotated.

c. Engine Inlet, Compressor, Temp Sensor and Moisture Drain

d. Oil Quantity, Cap and Access Door

e. Outboard Cowling and Scoops

f. Engine Drains Clear

g. Oil Cooler Clear and Condition

2. Right Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Leading Edge, Ice Protection Boot and Stall Warning Vane

b. Landing Light Condition

c. Fuel Vent Clear

d. Wing Tip Condition

e. Aileron and Fixed Tab

f. Outboard Flap


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NOTE: The oil level should be in the upper half of the FULL to ADD OIL zone of the dip stick when

the oil is hot. If the oil is cold, do not add oil if the level is in the upper half of the FULL to ADD OIL

zone.

C RIGHT ENGINE TAILPIPE AND EMPENNAGE

1. Right Engine Tailpipe . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Remove Dust Cover, if installed

b. Condition and Clear

2. Right Wheel Well . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Fluid Lines and Control Cables

b. Uplock and Gear Doors

3. Right Strut, Wheel and Brake . . . . . . . . . . . . . . . . . . . . CHECK

(Condition and Wear)

4. Inboard Cowling and Scoops . . . . . . . . . . . . . . . . . . . . CHECK

5. Ejector Pump Exhaust Port . . . . . . . . . . . . . . . . . . . . . CLEAR

6. Fuel Sump and Vents . . . . . . . . . . . . . . . . DRAIN and CHECK

7. Battery Vents. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

8. Inboard Flap and Hinge Fairing . . . . . . . . . . . . . . . . . . CHECK

9. Right Fuselage Static Ports . . . . . . . . . . . . . . . . . . . . . . CLEAR

10. Oxygen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

(S/N 11209 and subsq. if external door in installed)

a. Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

b. Shutoff Valve . . . . . . . . . . . . . . . . .SAFETY WIRED OPEN

c. Access Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

11. Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

12. Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Vertical and Horizontal Ice Protection Boots

b. Elevators and Tabs

c. External Rudder Gust Lock . . . . . . . REMOVE (if installed)

d. Rudder and tab


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e. Rudder Horn/Heater . . . . . . . . . . . . . . . . . . . . CLEARANCE

f. Tail Cone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

NOTE: Attempt to move rudder.

Resistance to movement by the internal controls lock should be encountered. If there is no

resistance, the rudder control system may have been damaged by the wind.

D AFT LEFT FUSELAGE

1. Left Static Ports. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

2. Ram Air Outlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

3. Environmental Sys. Compartment & Access Door . . . CHECK

4. Battery Vents. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

5. APU Access Door. . . . . . . . . . . . . . . . CHECKED & SECURE

(S/N 11249,11269 and Subsq.)

6. Baggage Compartment . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Oxygen Pressure and shutoff valve safety wired OPEN (S/N 11100 through

11208)

b. Baggage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

c. Baggage Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

7. Inboard Flap and Hinge fairing. . . . . . . . . . . . . . . . . . . CHECK

NOTE: If an APU is connected, ensure that the door will be secured after start completed. Ensure

the APU is regulated at 26 V DC, and is capable of providing a minimum of 16 volts DC and 800

amps during the starting cycle. Observe APU ammeter during start.

CAUTION: Do not use an APU which produces in excess of 1000 amps during initial start

sequence.

Current greater than 1000 amps may produce arcing which can progress to damaged or stuck

starter-generator brushes.


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E LEFT ENGINE AND TAILPIPE

1. Left Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Oil Quantity, cap and access door

b. Inboard Cowling and Scoops

c. Engine Drains Clear

d. Oil Cooler, clear and condition

2. Left Strut, Wheel, Brake and Strut Switch . . . . . . . . . . CHECK

(Condition and Wear)

3. Left Wheel Well . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Fluid lines and control cables

b. Uplock and Gear Doors

c. Emergency Gear Extension Pressure 425 to 525 psi

d. Hydraulic Accumulator and Shutoff valves

4. Hydraulic Quantity, Cap and Access Door . . . . . . . . . . CHECK

5. Tail Pipe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Remove dust cover, if installed

b. Condition and Clear

6. Left Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Outboard Flap

b. Aileron and Adjustable Tab

c. Wing tip condition

d. Fuel vent clear

e. Landing Light Condition

f. Leading Edge and Ice Protection Boot

7. Outboard Engine Cowling and Scoops. . . . . . . . . . . . . CHECK

NOTE: Flaps must be retracted and system pressure zero for an accurate hydraulic quantity

check.


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F LEFT ENGINE

1. Left Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Inlet Dust Cover . . . . . . . . . . . . . . . . REMOVE, if installed

b. Engine Inlet, Compressor, Temp Sensor and Moisture Drain

2. Prop and Spinner . . . . . . . . . . CHECK (Rotation and Condition)

Listen for unusual noises as prop is hand rotated.


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NORMAL PROCEDURES Normal operating procedures for Turbocommander 690B are presented in

this section. In instances where the procedures vary model to model, the

differences are noted.

Limitations, cautions, and warnings are also included as applicable.

Requirements for cold weather operations are also addressed.


AIRCRAFT CHECKLIST


CHECKLIST USAGE Tasks are executed in one of two ways:

� as a sequence that uses the layout of the cockpit controls and indicators as cues

(i.e., "flow pattern").

� as a sequence of tasks organized by event rather than panel location (e.g., After

Takeoff, Gear – RETRACT, FLAPS - UP).

The placing of items in a flow pattern or series provides organization and serves as

a memory aid.

A challenge-response review of the checklist follows execution of the tasks; the

pilot monitoring (PM) calls the item, and the appropriate pilot responds by verifying

its condition (e.g., Engine Anti-Ice [challenge] – ON [response]).

Two elements are inherent in the execution of normal procedures:

� use of either the cockpit layout or event cues to prompt the correct switch and/or

control positions.

� use of normal checklists as "done" lists.


AIRCRAFT CHECKLIST


NORMAL PROCEDURES BEFORE STARTING ENGINES

1. Exterior Inspection . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE

2. Cabin Door . . . . . . . . . . . . . . . . . . . . . . CLOSED and LOCKED

3. Seat and Safety Belt . . . . . . . . . . . . . . . . . . . . . . . . . ADJUSTED

4. Internal Controls Lock . . . . . . . . . . . . . . . . . . . . . . . . REMOVES

5. Flight Controls Lock . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVES

6. Airspeed Static Selector. . . . . . . . . . . PRIMARY (if applicable)

7. Environmental System Controls . . . . . . . . . . . . . . . . . . . CHECK

a. Bleed Select Switch . . . . . . . . . . . . . . . . . . . . . . . . . NORMAL

b. Depressurize Switch . . . . . . . . . . . . . . . . . . . . . . . . . NORMAL

c. Max Flow/Ground Cool Switch . . . . . . . . . . . . . . . . NORMAL

d. Mode Selector Switch. . . . . . . . . . . . . . . . . . . . OFF/RAM AIR

e. Auto Temperature Selector . . . . . . . . . . . . . . . .AS REQUIRED

f. Pressurization Controller . . . . . . SET, Cabin Altitude and Rate

g. Pressurization Instruments

1. Cabin Rate of Climb . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO

2. Cabin Differential Pressure . . . . . . . . . . . . . . . . . . . . . ZERO

3. Cabin Altitude . . . . . . . . . . CHECK, Field Pressure Altitude

8. Landing Gear Control Lever . . . . . . . . DOWN and LATCHED

9. Horsepower Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . 700 HP

10. Engine Control Switches . . . . . . . . . . . . . . . . . . . . ENGINE OFF

11. Overhead Panel Switches . . . . . . . . . . . . . . . OFF or NORMAL

a. Parallel (PAR), when OAT is between 0°C and +32°C or starting warm

engines. Allow amperage to decrease to less than 250 amps before starting

second engine. Operating generator is left on.

b. Series (SER), when OAT is below 0°C or above +32°C. Series will

improve starting capability in cold and hot environmental conditions. Allow


AIRCRAFT CHECKLIST


amperage to decrease to less than 250 amps before starting second engine.

Second engine may be started in PAR.

12. External Power Switch . . . . . . . . . . . . . . . . . . . AS REQUIRED

Recommend an APU start be made when OAT is-12°C or below. Distribution bus

annunciators (2) illuminated.

NOTE: The switch may be labeled MAX HEAT/GND COOL. Function remains the same on all

aircraft.

NOTE: Cabin can pressurize on the ground when the bleed air is on if the CABIN DEPRESS circuit

breaker is tripped

CAUTION: Cooling Unit damage may result if the environmental system is operated on the ground

with the ground blower inoperative.

NOTE: Minimize electrical load prior to starting engines. All nonessential electrical equipment

should be off.

CAUTION: When making SERIES starts the operating generator must be OFF prior to starting the

second engine

13. Battery starts:

Battery Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Distribution bus annunciators (2) . . . . . . . . EXTINGUISHED

BAT HOT annunciator . . . . . . . . . . . . . . NOT ILLUMINATED

14. Generator Switches . . . . . . . . . . . . OFF, While Starting Engine GEN OFF

Annunciators Illuminated

15. Distribution and Control Bus Tie . . . . . . . . . . . . . . . . . . OPEN

16. Distribution and Control Bus Switches . . . . . . . . . . . . . . . . ON

Annunciators Extinguished

17. Annunciator Panel . . . . . . . . . . . . . TEST (Lights, Gear Horn, and Battery

Temp Monitor)

18. Hydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . . 470 to 605 PSI

19. Fuel Counter . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

20. Fuel Quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

21. Parking Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

22. Prop Sync Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF


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23. Flap Control Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

24. Circuit Breaker Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Two tie breakers tripped, remaining breakers set.

26. Oxygen System: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

(Flights at Altitudes >13.000 Ft.) (690B model).

a. Oxygen Regulator . . .SET (clockwise to 22,500 Ft. or higher).

b. Oxygen Mask . . . . . . . . . . . . . . . . . DON and set to 100 percent

(Inspect for damage) Inline pressure indicator should indicate green.

c. Oxygen Quantity Gage . . . . . . . . . . . . . . . . . . . . . . OBSERVE

Observe quantity gage for approximately 30 seconds. A steady drop in pressure

indicates a system malfunction.

d. Mask Microphone . . . . . . . . . . . . . . . .CONNECT and CHECK

e. Oxygen Regulator . . . . . . . . . . SET to expected cruise altitude and allow to

stabilize.

f. Mask . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOW.

STARTING ENGINES (690B MODEL)

1. External Power Switch . . . . . . . . . . . . . . . . . . . AS REQUIRED

2. Battery Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

3. If Custom Kit No. 139 is installed:

a. Press AUTO-lGN RELIGHT test switch to the left L IGN light shall illuminate

b. Press AUTO-IGN RELIGHT test switch to the right - R –IGN light shall

illuminate

4. Anti-Collision Light Switch . . . . . . . . . . . . . . . . . . . . . . . . . . ON

5. Inter Turbine Temperatures (ITT). . . . . . . . . . BELOW 300°C

The maximum ITT for initiating start is 300°C. It may be reduced by motoring the

engine with the fuel and ignition systems off. To motor engine proceed as follows:

a. Engine Control Switch . . . . . . . . . . . . . . . . . . . . . . . .ENG OFF

b. IGN OVRD/MOTOR switch . . . . MOTOR. Depress and Hold

c. Engine Control Switch . . . . . . . . . . . . . . . . GND-START RUN

d. ITT Gage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MONITOR

If ITT does not decrease below 300° prior to engine reaching 15% RPM,

discontinue motoring by returning Engine Control Switch to ENG OFF.


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e. Repeat steps b, c, and d above until ITT is below 300°C.

f. When ITT decreases below 300°C, return ENGINE control Switch to ENG

OFF, release MOTOR switch and proceed with normal start.

6. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOW RPM

7. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLT IDLE

a. Airplanes S/N 11350 through 11542 except 11431. FLT IDLE

b. Airplanes S/N 11431, 11543 and subsequent . . . . CENTERED BETWEEN

FLT IDLE and GND IDLE

8. Fuel and Hydraulic Shutoff Switches . . . . . . . . . . . . . . . NORM

9. Ignition Override/Motor Switch . . .NORM (ignition lights out)

10. Horsepower Limiting System. OFF (annunciator illuminated)

11. Propellers . . . . . . . . . . . . . . . . . CLEAR and UNFEATHERED

If feathered, proceed as follows:

a. Power Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERSE.

b. Engine Control Switch . . . . . . . . . . . . . . . . . AIR-START RUN

(Observe that propeller blades move from feathered to locked)

CAUTION: If engine is to be restarted within 10 to 45 minutes after shutdown, observe engine

compressor and slowly move propeller until compressor rotates one half (1/2) revolution. Propeller

tip will move approximately six (6) inches. This should be done approximately ten (10) minutes prior

to restart.

CAUTION: To prevent damage to start switching system, depress and hold IGN OVRD/MOTOR

switch in MOTOR switch in MOTOR position before moving Engine Control Switch out of ENG OFF

position.

NOTE: Observe starter duty cycle.

c. Engine Control Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

d. Power Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . FLIGHT IDLE

12. Engine Control Switch . . . . . . FUEL PUMP ON (15 PSI min)

13. NTS System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

(Complete the NTS system check prior to first flight of the day)

a. NTS Test Switch . . . . . . . . . . . . . . . . . . DEPRESS and HOLD

b. Engine Control Switch . . . . . . . . . . . . . . . . . AIR-START RUN

Observe illumination of NTS light


AIRCRAFT CHECKLIST


14. Engine Control Switch . . . . . . . . . . . . . . . . GND-START RUN

As start is initiated, observe that NTS light extinguishes indicating that the torque

sensor has moved to the negative torque position.

a. NTS Test Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE

15. Inter Turbine Temperature . . . . . . . . . . . . . . . . . . . . . MONITOR

� Dash 5 engine - Starting limit 1149°C

� Dash 10 engine (EGT) - Starting Limit 770°C

CAUTION: If the NTS is unsatisfactory, correct the fault before flight.

NOTE: The rotary switch must be depressed before it can be rotated to GND-START RUN

position. This position engages the starter. Ignition operation can be monitored by illumination of the

ignition annunciator light on the engine control panel.

If engine light off has not occurred by approximately 15 percent RPM, place the ignition

override/motor switch to IGN OVRD. Return the switch to NORM at 50 percent. If light off is not

indicated by a rise in ITT within approximately 10 seconds after ignition override is selected, abort

the start by placing the engine control switch to ENG OFF and returning the ignition override; motor

switch to NORM.

CAUTION: Limit starter duty cycle to three 60-sec. periods of operation, separated by a five-

minute off period. Cycle may be repeated after starter has cooled for 30 minutes.

CAUTION: As soon as the 1 engine control switch is placed in the GND START RUN position

and the propeller starts turning, the pilot’s hand should move to the condition lever for that engine.

The condition lever should be guarded for the remainder of the start. If RPM stops increasing prior

to 40 percent or if ITT is approaching 1149°C (start limit) and rising rapidly, immediately place

condition lever to ENGINE STOP AND EMERGENCY FEATHER, then place engine control switch

to ENG OFF. Exceeding 1149°C may damage engine.

CAUTION: Do not let engine RPM stabilize in 18 - 28 RPM range

16. Oil Pressure . . . . . . . . . . . CHECK (50 PSI min. at 70% RPM)

17. Fuel Pressure . . . . . . . . . . . . . . . . . . . . . . . . . 25 PSI MINIMUM

18. Hydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . . 900 to 1075 PSI

19. Vacuum Gage . . . . CHECK. Should indicate in the green arc

20. Generator . . . . . . . ON, operating engine (if PAR battery start)

21. Repeat steps 12 through 19 for starting second engine.

22. External Power Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

(If APU is utilized, generators will be inoperative until external power switch is off).


AIRCRAFT CHECKLIST


23. Generators . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON and charging

(Reset generators if necessary) - Ground Limit: 250 amperes per generator

24. Auxiliary Power Unit . . . . . . . . . . . . . . . . . . DISCONNECTED

Ensure access door secure.

25. Oil Temperature. . . . . . . . . . . . . . . . . . . . . . +55°C MINIMUM

Ensure minimum temperature reached before increasing RPM above 70% to avoid

the possibility of fuel icing, and in the interest of optimum lubrication.

CAUTION: If oil pressure is not indicated within 10 seconds after engine light off, shut down

engine.

CAUTION: During SER starts the operating generator must be OFF prior to starting the second

engine.

BEFORE TAXI

1. Overhead Switches . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED.

a. Electrical (cabin bus must be ON to operate right windshield wiper).

b. Lights

c. Avionics

2. Nav/Comm Equipment . . . . . . . . . . . . . . . . . . . AS REQUIRED

3. Flight Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

4. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

5. Environmental System . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

a. Bleed Selector Switch. . . . . . . . . . . . . . . . . . . . . . . . NORMAL

b. Depressurization Switch . . . . . . . . . . . . . . . . . . . . . . NORMAL

c. Max Flow/Ground Cool Switch . . . . . . . . . . . .AS REQUIRED

d. Mode Selector Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO

e. Auto Temp Control . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED

6. Circuit Breaker Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

7. NTS Check Valve Functional Test . . . . . . . . . . AS REQUIRED

This test should be accomplished prior to the first flight of the day.

It may be performed with the propeller start locks engaged or disengaged.

a. Power Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLT IDLE


AIRCRAFT CHECKLIST


b. Condition Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HI

c. NTS Test Switch . . . . . . . . . . . . . . . . .DEPRESS momentarily

The NTS light should not illuminate. Repeat the test on the opposite engine.

NOTE: The landing light annunciator, adjacent to the landing light control switches, illuminates

when the landing lights are out of retracted position.

NOTE: For S/N 11249, 11269 and subs. and 690 B model: Radio Master Switch No.1 must be ON

to operate Inverter No.1 and Radio Master Switch No. 2 must be ON to operate Inverter No.2.

NOTE: When ground cool is selected, regulated bleed air pressure and instrument vacuum may

drop below the green arc range. If GND COOL is operative and is selected, place auto temp control

to full cold position. If MAX FLO is selected position auto temp control as desired.

CAUTION: Selection of environmental functions on the ground is not recommended unless the

ground blower is known to be operating.

Visually observe a current increase on cabin ammeter for blower operation.

Severe overheating and damage of ducts, heat exchanger, and cooling unit is possible.

NOTE: After the first engine is started, the environmental system may be placed in operation by:

(1) Bleed Air Selector Switch - OPERATING ENGINE.

(2) Mode Selector Switch - AUTO.

Place the bleed selector in normal after the second engine is started.

CAUTION: If either NTS light illuminates correct the fault before flight.

8. Overspeed Governor Check . . . . . . . . . . . . . . . AS REQUIRED

The overspeed governor check should be performed prior to the first flight of the

day and when engine shutdown and air starts are anticipated, any maintenance or

adjustment has been performed, or there is any indication of malfunction.

690B Model:

a. With the propeller on the start locks:

1. Condition Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . HI RPM

Observe illumination of beta light, indicating positive torque.

2. Power Lever . . . . . . . . . . . . . . . . . ADVANCE slowly until further motion causes

no increase in fuel flow or RPM and then retard to GND IDLE.

RPM must stabilize at 104.5 to 105.5% on airplanes S/N 11350 through 11542,

except 11431 and at 103.0 to 105.0%t on airplanes S/N 11431, 11543 and

subsequent.

WARNING: When performing this check the immediate area ahead of the aircraft must be clear in

the event the propellers inadvertently unlatch.

CAUTION: Do not exceed 106%.

If this limit is exceeded, immediately move the power lever to ground idle and shutdown the engine.

The engine must be removed if the limit is exceeded.


AIRCRAFT CHECKLIST


NOTE: If the engine will not exceed approximately 100% RPM, and a significant horsepower rise is

noted, the propeller start locks are probably not engaged.

NOTE: For S/N 11431, 11543 and subs.: Do not dwell in 103.0 to 105.0% RPM range as engine

roughness may occur. This check is meant only to determine that the overspeed governor will limit

RPM to acceptable limits and is not typical of actual overspeed operation.

9. Propellers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNLOCK

a. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . ABOVE 85%

b. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GND IDLE.

Hold until beta lights illuminate

c. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERSE

Slowly retard power lever until an increase in fuel flow and horsepower are

noted.

d. Condition Levers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LO RPM

e. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GND IDLE

10. Annunciators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

11. Ice Protection Equipment . . . . . . . . . . . . . . . . . . . . CHECKED

If flight into icing conditions is anticipated the following should be checked.

a. Windshield Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Physically check and note slight rise in aircraft ammeter when either LOW or HIGH

Heat is selected.

b. Rudder Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Note slight increase in aircraft ammeter when heat is turned ON.

c. Engine Inlet Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Observe annunciators (ENG INLET) illuminate and a slight decrease in

horsepower and fuel flow when the heat is on.

d. Generator Inlet Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Hold the Ice Protection AMPS selector switch in the GEN position and observe 12

to 18 amperes with the heat on.

e. Propeller Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Observe 14 to 18 amperes on the Ice Protection ammeter with propeller heat on.

f. Regulated Pressure Gage . . . . . . . . . . . . . . . . . . . . . . . CHECK

Should indicate in, the GREEN arc.

g. Boots One Cycle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Observe inflation and deflation of boots.

h. Boots Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Observe inflation and deflation of boots.


AIRCRAFT CHECKLIST


12. Parking Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

WARNING: Ground operation of ice protection electric heaters must be limited to 30 seconds, or

less.

CAUTION: If either the generator or propeller heat checks indicate low amperage the possibility of

partial failure of the Ice Protection.

NOTE: Two minutes are required for the timer to cycle through both elements of both props.

During the cycle each element heats for approximately 30 seconds.

NOTE: Operation of the surface deice boots should be checked prior to encountering icing

conditions, while on the ground or in flight, when the OAT is above -40°F (-40°C).

NOTE: When operating through standing water or slush, at speeds below 40 KIAS, it may desirable to

use FLT IDLE rather than GND IDLE or REVERSE in order to minimize the possibility of water ingestion

due to splash from main wheel.

BEFORE TAKEOFF

1. Predicted HP and Fuel Flow . . . . . . . . . . . . . . . .DETERMINE

(See Section V - 690B of Pilot’s Operating Handbook).

2. Flight Controls . . . . . . . . . . . . . . . FREE and FULL TRAVEL

3. Trim Tabs . . . . . . . . . . . . . . . . . . SET for takeoff. Annunciator Light

Extinguished

4. Nav/Comm Equipment . . . . . . . . . . . . . . . . . . . AS REQUIRED

5. Flight Instruments . . . . . . . . . . . . CHECK and set for takeoff

6. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

7. Ground Cool/Max Flow Switch . . . . . . . . . . . . . . . . . NORMAL

8. Cabin Altitude . . . . . . . . . . . . . . . . . . . . . . . SET 1000 feet above destination

field elevation or higher.

9. Oxygen Regulator . . . . . . . . . . . . . . . . . . . . . . . . . . . RECHECK

Set to expected aircraft cruise altitude. (S/N 11100 thru 11248, 11250 thru 11268).

10. Oxygen Regulator . . . . . . . . . . . . . . . . . . . . . . . . . . . RECHECK

(S/N 11249, 11269 and Subs and B Model) set to expected cruise altitude when

flying between 22,500 feet and 31,000 feet. When flying below 22,500 feet, set to a

minimum of 22,500 feet.


AIRCRAFT CHECKLIST


11. Engine Control Frictions. . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

12. Prop Sync Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF


14. Horsepower Limiting System. . . . . . . . . . . . .CHECK and SET

System test should be accomplished at intervals of approximately 10 flight hours.

a. Condition Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI RPM

b. Power Lever . . . . . . . . . . . .ADVANCE (to obtain 100% RPM)

c. Horsepower Limit Switch. . . . . . . . . . . . . . . . . . . . . . . . . TEST

Depress momentarily until a reduction of fuel flow and RPM is noted. Do not allow

engine RPM to decay below 67 percent. Set switch ON or OFF as desired.

15. Emergency Locator Transmitter (ELT) . . . . . . . . . . . . . . ARM

NOTE: For Fwd. C G. Takeoff trim aircraft NOSE-UP until annunciator TRIM illuminates. Then trim

aircraft NOSE-DOWN until annunciator TRIM just extinguishes.

For Aft C.G. Takeoff trim aircraft NOSE-DOWN until annunciator TRIM illuminates. Then trim

aircraft NOSE-UP until annunciator TRIM just extinguishes.

CAUTION: Do not increase engine speed above 80 percent RPM until GND COOL (if operative)

and MAX FLO annunciators are extinguished.

(Approximately 40 seconds after switch is placed in NORMAL.)

NOTE: If an instrument departure is anticipated, allow several minutes of operation with the

Ground Cool/Max Flow Switch in the NORMAL position. This will allow the suction powered gyros to

come to their normal speed prior to takeoff.

CAUTION: Pressurization not permitted during takeoff and landing.

NOTE: If the test is unsatisfactory the system may be disabled by placing the horsepower limit

switch in the OFF position. Maximum power must be manually controlled.

LINE UP 1. Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED.

When the temperature is +5°C, or below and there is visible moisture present, all

appropriate ice protection must be turned on as follows:

a. Windshield Heat, Left and Right.

b. Rudder Heat.

c. Engine Inlet Heat, Left and Right.

d. Pitot - Fuel Vent Heat, Left and Right.

e. Generator Inlet Heat.

f. Propeller Heat.

g. Wing Ice Lights.


AIRCRAFT CHECKLIST


h. Defog Blower. - Check pilot and copilot side window for air flow.

2. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GND IDLE

3. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI-RPM

690B Model: 96.5 to 97.5% (Underspeed Governor Check)

4. Ignition Override . . . . . . . . . . . . . . . . . . . . . . ON, As Required

5. Power Levers . . . . . . . . . . . . . ADVANCE to maximum power

690B Model: 99.0 to 100.5% RPM - Observe 717.5 HP and/or 923°C limit(s).

Predicted horsepower and fuel flow should be attained.

6. Beta Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED

7. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

WARNING: A water or slush induced flame-out may occur if takeoffs are attempted on runways

with standing water, slush or loose powdery snow. Ignition override recommended ON. Observe

time limits.

NOTE: Boots should be operated ONE CY or MAN, in flight, whenever ice builds up to

approximately 1/2 inch.

CAUTION: Do not operate Ice Protection heat when ambient temperatures are above +5°C.

If defog blower fails, or if there is no air flow at either defog outlet, turn defog blower switch Off. If

aircraft equipped with side window defog heaters (factory installed S/N 11517 and subs.) failure to

turn blower switch off will result in heating overtemp.

Operation without air flow for longer than 4 to 5 minutes will result in smoke in the cockpit.

WARNING: Do not operate boots during takeoff and landing.

WARNING: If standing water, slush or loose powdery snow is observed on the runway, it is

recommended that the ignition override switch be placed in the ON position to minimize the

possibility of a flame-out during the takeoff.

Observe ignition override time limitations.

NOTE: Operation of the ignition system in conditions other than normal starting will reduce ignition

plug life.

TAKEOFF

1. Takeoff and Climb Speed . . . . . . . . . . . . . . . . . . . . . . . ATTAIN

2. Landing Gear Control Lever . . . . . . . . . . . . . . . . . . . . . . . . . UP


AIRCRAFT CHECKLIST


CLIMB

1. Climb Speed - 139 KIAS (to 5000 Ft.). Scheduled climb speed thereafter

(minus 1 KT per 1000 Ft. above 5000 ft.).

2. Ignition Override . . . . . . . . . . . . . . . . . . . . . OFF, As Applicable

3. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

A climb at Maximum Recommended Climb Power (MRCP) may be made at 717.5

HP/885°C ITT at 96 percent RPM.

4. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

5. Prop Sync Switch . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

6. Pressurization Instruments. . . . . . . . . . . . . . . . . . . MONITOR

Monitor cabin altitude and differential pressures periodically during climb and

cruise.

7. Oxygen System. . . . . . . Remove pilot and copilot oxygen mask

compartment doors when operating above 25,000 feet flight altitude

(S/N 11100 thru 11248, 11250 thru 11268)

8. Ground Cool/Max Flow Switch . . . . . . . . . . . . . . . . MAX FLO if additional

heat is required.

9. Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

WARNING: Abnormal cabin pressure fluctuations after takeoff (cabin rate of climb ± 1500 – 2000

FPM) indicate the possibility of a safety/outflow valve malfunction.

Immediately place Depressurization switch to DEPRESS and have valves inspected before further

pressurized flight. A dual valve failure can result in a cabin overpressure condition.

WARNING: CABIN LO PRESS light illuminated indicates lack or loss of pressurization for

operation within safe limits and emergency oxygen should be used immediately.


AIRCRAFT CHECKLIST


CRUISE (690B MODEL)


Maximum Recommended Cruise Power (MRCP) is 717.5 HP/ 905°C ITT at 96%

RPM.

2. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

3. Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED.

4. Oxygen System

To assure availability of emergency oxygen, the system may be used for

supplemental oxygen only when the oxygen pressure gage reads above 1,000 PSI.

The altitude adjusting valve must remain at 22,500 ft. minimum regulated setting.

CAUTION: In flight do not reduce engine RPM below 96%.

WARNING: If the oxygen system is depleted to 1000 PSI, an immediate emergency descent to

below 13,000 feet must be accomplished in the event of loss of cabin pressurization.

NOTE: If flight in severe turbulence is encountered or cannot be avoided, the following procedure

is recommended:

� Avoid control action which could give rapid changes in attitude, altitude or airspeed; whenever

possible, achieve steady flight conditions prior to entry into turbulence. Flaps should be fully

retracted and autopilot disengaged.

� Slow to VA speed, keep pilot control movements to a minimum and fly a straight course through

the turbulence, as far as practicable concentrating on attitude and disregarding altitude

CAUTION: In flight do not reduce engine RPM below 96%.

WARNING: If the oxygen system is depleted to 1000 PSI, an immediate emergency descent to

below 13,000 feet must be accomplished in the event of loss of cabin pressurization.

DESCENT

1. Cabin Altitude Control . . . . . . . . . . . SET 1000 feet above field elevation, or

higher


3. Annunciator Panel . . . . . . . . . . . . . . . TEST all indicator lights.

4. Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED.


AIRCRAFT CHECKLIST


BEFORE LANDING

1. Cabin Differential Pressure Gage. . . . . . . . . . . CHECK ZERO

2. Ground Cool/Max Flow Switch . . . . . . . . . . . . . . . . . NORMAL

3. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI RPM

4. Prop Sync Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

5. Landing Gear Control Lever . . . . . . . . DOWN and LATCHED.

200 KIAS maximum.

a. Gear Safe Lights . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED

b. Gear Unsafe Light. . . . . . . . . . . . . . . . . . . . . EXTINGUISHED

c. Gear Warning Horn . . . . . . . . . . . . . . . . . . . . . . . . . . . SILENT

6. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

7. Hydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . .900 to 1075 PSI

8. Ignition Override . . . . . . . . . . . . . . . . . . . . . . . . ON, as required

9. Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

WARNING: Power levers are not to be retarded aft of the flight idle stops in flight. The NTS

system and propeller governing are disabled when the power levers are aft of the flight idle stop.

CAUTION: Pressurization not permitted during takeoff and landing.

NOTE: It may be necessary to reduce the airspeed to less than 180 KIAS to allow the main landing

gear to complete its extension cycle. Landing gear extension may be initiated at 201 KIAS 690B.

NOTE: Limiting airspeed for flap selection and operation:

690B MODEL

� One Half Flaps (20°) 180 KIAS

� Full Flaps (40°) 140 KIAS

WARNING: If a significant amount of standing water, slush or loose powdery snow is anticipated

on the runway, the ignition override switch should be placed in the ON position to minimize the

possibility of a flame-out during landing.

Observe ignition override time limitations.


AIRCRAFT CHECKLIST


GO-AROUND (BALKED LANDING)

1. Power Levers . . . . . . . . . . . . . . ADVANCE to maximum power, 99.5 to

100.5% RPM

Observe 717.5 HP and/or 923°C limit(s).

2. Climb Speed . . . . . . . . . . . . . . . . . ATTAIN.

Best rate-of-climb speed 99 KIAS

3. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT

4. Landing Gear . . . . . . . . RETRACT (when definitely climbing)

Accelerate to twin engine climb speed and perform the takeoff and climb

checklists.

5. Ignition Override . . . . . . . . . . . . . . . . . . . . . OFF, as applicable

LANDING

1. Touchdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRMED

2. Power Levers . . . . . . . . .GND IDLE (condition lever HI RPM)

a. Beta Lights (2) . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED

3. Reverse Power . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

4. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

WARNING: Do not raise flight idle locks until after touchdown.

NOTE: Do not enter reverse range with beta light(s) extinguished.

CAUTION: Full reverse is limited to 500 HP at or above 95% RPM, with speed less than 90 KIAS

and OAT below +32°C.

Reduce max allowed airspeed 2 knots for each one degree above +32°C. Reduce reverse thrust

proportionally as aircraft speed decreases

CAUTION: Do not use reverse thrust to a full stop with brakes applied. Use reverse thrust with

caution when landing on dirt or snow covered runways due to the blinding effect of swirling dirt or

snow, especially at lower speeds.

Should this occur, discontinue reverse immediately. Damage to propeller blades may occur if

reverse is used on gravel or similar surfaces.


AIRCRAFT CHECKLIST


AFTER LANDING


2. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO RPM

3. Ignition Override . . . . . . . . . . . . . . . . . . . . . . OFF, as applicable


5. Hydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . .900 to 1075 PSI

6. Ice Protection Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

ENGINE SHUTDOWN

1. Parking Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

2. Environmental Mode Selector . . . . . . . . . . . . . OFF/RAM AIR

3. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO RPM

4. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GND IDLE

Operate at taxi power for at least 3 minutes (including taxi time), prior to shut down.

5. Generator Switch . . . . . . . . . OFF (for engine to be shutdown)

6. If Custom Kit No. 139 is installed:

a. Press AUTO-IGN RELIGHT test switch to the right. Turn RSTART switch to

“OFF” (verify the moment, within one or two seconds, the engine starts to decrease

in RPM. the R-IGN light illuminates.

b. Press AUTO-IGN RELIGHT test switch to the left. Turn LSTART switch to “OFF”

(verify the moment, within one or two seconds, the engine starts to decrease in

RPM, the L-IGN light illuminates.

7. Engine Control Switch . . . . . . . . . . . . . . . . . . . . . ENGINE OFF

(Shutdown engine started first)

8. Power Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL REVERSE

(Before RPM drops below 50%, to engage propeller blade start locks)

Monitor engine for unusual noises.


AIRCRAFT CHECKLIST


9. Hydraulic Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK

After propeller stops, rotating cycle flaps to check the adequacy of the operating

hydraulic pump; 900 to 1075 PSI.

10. Remaining engine . . . . . . . . . . . . . . . . . . . . . . . . . SHUTDOWN

(Repeat steps 5., 7. and 8.)

11. Overhead Switches . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

12. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLT IDLE

13. Parking Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

14. Battery Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

15. Oxygen Regulators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

16. Locks, Covers and Wheel Chocks. . . . . . . . . . . . . . . . INSTALL

Allow a minimum of 10 minutes cool-down before installing inlet dust covers.

NOTE: Turning engine control switch OFF before turning generator switch OFF will unnecessarily

break and make generator line and field relay contacts, thereby reducing contact service life.

CAUTION: Placing the engine control switch to the ENG OFF position following manual shutdown

(condition lever to FEATHER position), will result in a fuel accumulation in the plenum and may

result in smoke and a loud popping sound. It is recommended that the engine control switch not be

placed in the ENG OFF position until engine cools well below 300°C to prevent combustion.

NOTE: Engine RPM should increase approximately 5% with placement of the engine control

switch to the ENG OFF position, and then decrease when the manifold fuel is depleted.

NOTE: If power lever is not placed in reverse the propeller will feather.

NOTE: The battery switch must be OFF, or the cabin door switch must be placed in the UNLOCK

position before the cabin door can be opened. The door annunciator will illuminate if the battery is

ON and entry door is not secure or the door lock switch is in the UNLOCK position.

WARNING: Do not open the cabin door until the left propeller stops rotating.

CAUTION: If engine is to be restarted within 10 to 45 minutes after shutdown, observe engine

compressor and slowly move propeller until compressor rotates one half revolution. Propeller tip will

move approximately six (6) inches. This should be done approximately ten (10) minutes prior to

restart.

turbo commander 690b checklist.pdf

Documents

b checklist turbocommander

preflight inspection

b aircraft rev original

b models

night flight

flight readiness

right pitot heat

actual exterior inspection