Turbo Commander 690B Checklist.pdf
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Turbo Commander 690B
CHECKLIST
TURBOCOMMANDER 690B RG AVIATION
AIRCRAFT CHECKLIST
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.
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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 – Gear – RETRACT, RETRACT, Flaps - UP). The placing of items in a flow pattern or series provides organization and serves as a memory aid. A challenge-respons challenge-response e review of the checklist follows execution 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 – 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 Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK 2. Airplane Documents 3. Landing Gear Control Lever. . . . . . . . . . DOWN & LATCHED Control Switches Switches . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 4. Engine Control 5. Overhead Panel Switches . . . . . . . . . . . . . . . . .AS REQUIRED Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 6. Battery Switch. 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 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
AIRCRAFT CHECKLIST
(CLOCKWISE)
A LEFT WING AND FORWARD FUSELAGE 1.
2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12.
Upper Left Wing Surface . . . . . . . . . . . . . . . . . . . . . . . CHECK (Fuel caps, general condition. May be accomplished by standing in main door opening) OAT probe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Entry Door, Bayonets and Seal . . . . . . . . . . . . . . . . . . . CHECK Left Pitot head. . . . . . . . . . .CHECK (cover removed and clear) Left Windshield and Wiper . . . . . . . . . . . . . . . . . . . . . CHECK Nose Access Door. . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE Nose Gear Doors and Wheel Well . . . . . . . . . . . . . . . . CHECK Radome . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Right Pitot Head . . . . . . . . .CHECK (cover removed and clear) Right Windshield and Wiper . . . . . . . . . . . . . . . . . . . . CHECK Emergency Exit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE 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.
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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 – Gear – RETRACT, RETRACT, FLAPS - UP). The placing of items in a flow pattern or series provides organization and serves as a memory aid. A challenge-respons challenge-response e review of the checklist follows execution 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 – 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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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
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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 –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
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14. Engine Control Switch . . . . . . . . . . . . . . . . GND-START RUN As start is initiated, initiated, observe observe that NTS light extinguishes 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 fiveminute 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 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).
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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 Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLT IDLE
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b. Condition Lever 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 st arted, 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.
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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 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.
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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.
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11. Engine Control Frictions. . . . . . . . . . . . . . . . . . . . . . . . . . . . SET 12. Prop Sync Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 13. Flap Control Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP 14. Horsepower Limiting System. . . . . . . . . . . . .CHECK and SET System test should be accomplished at intervals of approximately 10 flight hours. a. Condition Lever 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.
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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
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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 1500 – 2000 2000 WARNING: Abnormal cabin pressure f luctuations after takeoff (cabin rate of clim b ± 1500 – 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.
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CRUISE (690B MODEL) 1. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED 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 2. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED 3. Annunciator Panel . . . . . . . . . . . . . . . TEST all indicator lights. 4. Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED.
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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 Lights . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED 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.
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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 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.
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AIRCRAFT CHECKLIST
AFTER LANDING 1. Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED 2. Condition Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO RPM 3. Ignition Override . . . . . . . . . . . . . . . . . . . . . . OFF, as applicable 4. Flap Control Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP 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.
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TURBOCOMMANDER TURBOCOMMANDER 690B AIRCRAFT
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TURBOCOMMANDER 690B RG AVIATION
AIRCRAFT CHECKLIST
9. Hydraulic Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK After propeller stops, rotating cycle flaps to check the adequacy 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 10 minutes cool-down cool-down before installing installing inlet dust covers. 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.
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TURBOCOMMANDER TURBOCOMMANDER 690B AIRCRAFT
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