SECTION IV NORMAL PROCEDURES TABLE OF CONTENTS

Transcription

1 .avllleon Aircraft SECTION IV NORMAL PROCEDURES TABLE OF CONTENTS Beech Super King Air 8200 & B200C SUBJECT PAGE Airspeeds For Safe Operation (12,500 Ibs) 4-3 Procedures By Flight Phase 4-3 Preflight Inspection Cabin/Cockpit Left Wing and Nacelle Nose Section Right Wing and Nacelle Right Aft Fuselage Tail Section 4-6 Left Aft Fuselage Before Engine Starting Engine Starting (Battery) 4-9 Engine Starting (External Power) Engine Clearing Before Taxi 4-11 Before Takeoff (Runup) 4-12 Before Takeoff (Final Items) 4-14 Takeoff Climb 4-15 Cruise Descent Before Landing Normal Landing Maximum Reverse Thrust Landing 4-16 Balked Landing After Landing Shutdown and Securing 4-17 Other Oxygen System Preflight Inspection 4-18 Heating/Cooling System Radiant Heat (if installed) 4-20 Defroster Air 4-20 Blending Anti-icing Additive to Fuel 4-21 Adding Biocide to Fuel 4-21 Use of Jet B, JP-4, and Aviation Gasoline 4-21 Nickel-Cadmium Battery Check (Ground Operation Only) 4-21 Cold Weather Procedures (Snow, Slush, and Ice) 4-22 Preflight Inspection 4-22 Taxiing 4-22 Before Takeoff 4-22 Takeoff 4-22A Landing 4-22A Shutdown and Securing 4-22A Icing Flight Before Takeoff (Runup) 4-23 In Flight 4-24 Before Landing 4-26 Practice Demonstration of V MCA Practice Landing Gear Manual Extension (Mechanical System) 4-27 May,

2 Beech Super King Air 8200 & B200C.aytllean Aircraft SECTION IV NORMAL PROCEDURES TABLE OF CONTENTS (CONT'D) SUBJECT PAGE Landing Gear Retraction After Practice Manual Extension (Mechanical System) 4-27 Practice Landing Gear Manual Extension (Hydraulic System) 4-27 Landing Gear Retraction After Practice Manual Extension (Hydraulic System) 4-27 Simulating One-Engine-Inoperative (Zero Thrust) 4-28 Noise Characteristics 4-28 Cabin Door Annunciator Circuitry Check (8200) 4-28 Cabin/Cargo Door Annunciator Circuitry Check (B200C) May, 2000

3 ~ft Super King Air B2001B200C Section IV All airspeeds quoted in this section are indicated airspeeds (las) and assume zero instrument error. AIRSPEEDS FOR SAFE OPERATION (12,500 LBS) Maximum Demonstrated Crosswind Component. 25 Knots Takeoff (Flaps Up). Rotation 95 Knots 50-ft Speed 121 Knots Takeoff (Flaps Approach) Rotation 94 Knots 50-ft Speed 106 Knots Two-Engine Best Angle-of-Climb (Vx) ~ 100 Knots Two-Engine Best Rate-of-Climb (Vy) 125 Knots Cruise Climb: Sea Level to 10,000 feet 160 Knots 10,000 to 20,000 feet 140 Knots 20,000 to 25,000 feet 130 Knots 25,000 to 35,000 feet 120 Knots Maximum Airspeed for Effective Windshield Anti-icing 226 Knots Maneuvering Speed (VA) 181 Knots. Turbulent Air Penetration 170 Knots For turbulent air penetration, use an airspeed of 170 knots. Avoid over-action on power levers. Turn off autopilot altitude hold. Keep wings level, maintain attitude and avoid use of trim. Do not chase airspeed and altitude. 'Penetration should be at an altitude which provides adequate maneuvering margins when severe turbulence is encountered. Landing Approach: Flaps Down Balked Landing Climb Intentional One-Engine-Inoperative Speed (VSSE) Air Minimum Control Speed (VMCA) 103 Knots 100 Knots 104 Knots 86 Knots PROCEDURES BY FLIGHT PHASE Refer to all applicable Beech Supplements and STC Supplements for flight phase procedures for optional equipment installed in the airplane. PREFLIGHT INSPECTION After the first flight of each day, the Preflight Inspection may be omitted except for items marked with a "+". Fuel tank caps and engine oil quantity and filler cap need not be checked unless system(s) were serviced. External inspections with flaps down may be conducted at intervals deemed appropriate by the pilot. CABIN/COCKPIT 1. Monogram Electric Toilet (if installed) - KNIFE VALVE OPEN + 2. Baggage - SECURE 3. Emergency Exit - SECURE AND UNLOCKED 4. Trim Tabs - SET TO "0" UNITS December,

4 Section IV ikechcmft Super King Air B200/B200C [~ The elevator trim system must not be forced past the limits which are indicated on the elevator trim indicator scale, either manually, electrically, or by action of the autopilot. 5. Condition Levers - FUEL CUT OFF 6. Landing Gear Control - DN 7. Control Locks - REMOVE 8. Parking Brake - SET 9. Ignition and Engine Start - ENSURE OFF 10. Battery - ON, CHECK 23 VOLT MINIMUM 11. Fuel Quantity - CHECK 12. Flap Control (if desired) - APPROACH, THEN DOWN (check indicator) 13. Battery - OFF 14. Oxygen System Preflight Inspection - COMPLETE (See OTHER NORMAL PROCEDURES.) LEFT WING AND NACELLE 1. Door Seal - CHECK 2. Flaps - CHECK 3. Oil Breather Vent - CLEAR + 4. Brake Lines, Brake Wear, Brake Deice Lines (if installed) - CHECK 5. Fire Extinguisher (if installed) - CHECK PRESSURE 6. Inverter Cooling Louver - CLEAR 7. Aileron and Tab - CHECK 8. Flush Outboard Wing Fuel Tank Sump - DRAIN 9. Static Wicks (4) - CHECK 10. Navigation, Recognition, & Strobe Ughts - CHECK Main Fuel Tank Cap - SECURE 12. Stall Warning Vane - CHECK Tiedown - REMOVED 14. Outboard Deice Boot and Stall Strip - CHECK 15. Ice Light - CHECK 16. Heated Fuel Vent - CLEAR 17. Ram Scoop Fuel Vent - CLEAR 18. Gravity Une Drain - DRAIN 19. Inverter Caoling Louvers - CLEAR 20. Wing Leading Edge Tank Sump - DRAIN Landing Gear (Doors, Wheel Well, Strut, Tires, Brakes) - CHECK Chock - REMOVE 23. Standby Pump Drain - DRAIN 24. Fuel Filter Strainer Sump - DRAIN Engine Oil - CHECK QUANTITY, CAP SECURE 26. Engine Compartment Door (Outbd) - SECURE, BLEED VALVE EXHAUST CLEAR 27. Exhaust Stack (Outbd) - CHECK FOR CRACKS 28. Top Cowling Locks (Outbd) - SECURE 29. Nacelle Cooling Ram Air Inlets - CLEAR 4-4 December, 1994

5 CReechcraft Super King Air B200/B200C Section IV Propeller - CHECK FOR NICKS, DEICE BOOT SECURE 31. Engine Intake - CLEAR 32. Top Cowling Locks (Inbd) - SECURE 33. Exhaust Stack (Inbd) - CHECK FOR CRACKS 34. Generator Cooling Inlet - CLEAR 35. Engine Compartment Door (Inbd) - SECURE, BLEED VALVE EXHAUST CLEAR 36. Heat Exchanger Inlet - CLEAR Auxiliary Fuel Tank Cap - SECURE 38. Hydraulic Landing Gear Service Door (if installed) - SECURE 39. Inboard Deice Boot - CHECK 40. Heat Exchanger Outlet - CLEAR - --_# Hydraulic Landing Gear Vent Lines (if installed) - CLEAR 42. Auxiliary Fuel Tank Sump - DRAIN 43. Lower-Antennas and Beacon - CHECK NOSE SECTION OAT Probe (Lower Fuselage) - CHECK 2. Avionics Panel - SECURE 3. Condenser Blower Outlet - CLEAR + 4. Nose Gear (Doors, Strut, Nose Gear Steering Stop Block, Tire, Wheel Well) - CHECK + 5. Chock - REMOVE 6. Landing and Taxi Lights - CHECK 7. Pitot Masts - COVERS REMOVED, CLEAR 8. Radome - CHECK 9. Windshield Wipers - CHECK 10. Ram Air Inlet - CLEAR 11. Avionics Panel - SECURE RIGHT WING AND NACELLE 1. Auxiliary Fuel Tank Sump - DRAIN 2. Battery Drain - CLEAR 3. Battery Air Inlet - CLEAR, VALVE FREE 4. Heat Exchanger Outlet - CLEAR 5. Inboard Deice Boot - CHECK 6. Battery Exhaust - CLEAR + 7. Auxiliary Fuel Tank Cap - SECURE 8. Heat Exchanger Inlet - CLEAR + 9. Engine Oil - CHECK QUANTITY, CAP SECURE 10. Engine Compartment Door (lnbd) - SECURE, BLEED VALVE EXHAUST CLEAR 11. Exhaust Stack (Inbd) - CHECK FOR CRACKS 12. Top Cowling Locks (Inbd) - SECURE 13. Nacelle Cooling Ram Air Inlets - CLEAR Propeller - CHECK FOR NICKS, DEICE BOOT SECURE 15. Engine Intake - CLEAR 16. Top Cowling Locks (Outbd) - SECURE 17. Exhaust Stack (Outbd) - CHECK FOR CRACKS December,

6 Section IV ~ft Super King Air B200/B200C 18. Generator Cooling Inlet - CLEAR 19. Engine Compartment Door (Outbd) - SECURE, BLEED VALVE EXHAUST CLEAR 20. Fuel Filter Strainer Sump - DRAIN 21. Standby Pump Drain - DRAIN Landing Gear (Doors, Wheel Well, Strut, Tires, Brakes) - CHECK 23. Fire Extinguisher (if installed) - CHECK PRESSURE Chock - REMOVE 25. Heated Fuel Vent - CLEAR 26. Ram Scoop Fuel Vent - CLEAR 27. Gravity Une Drain - DRAIN 28. Inverter Cooling Louvers - CLEAR 29. Wing Leading Edge Tank Sump - DRAIN External Power Door - CLOSED 31. Ice Light - CHECK 32. Outboard Deice Boot and Stall Strip - CHECK Tiedown - REMOVE 34. Flush Outboard Wing Fuel Tank Sump - DRAIN Main Fuel Tank Cap - SECURE 36. Navigation, Recognition, and Strobe Ughts - CHECK 37. Static Wicks (4) - CHECK 38. Aileron and Bendable Tab - CHECK 39. Flaps - CHECK 40. Inverter Cooling Louver - CLEAR Brake Lines, Brake Wear, Brake Deice Lines (if installed) - CHECK 42. Oil Breather Vent - CLEAR RIGHT AFT FUSELAGE 1. Lower Antennas - CHECK 2. Ventral Fin Drain Holes - CLEAR 3. Lower Aft Cabin Access Door - SECURE + 4. Tiedown - REMOVED 5. Oxygen Service Access Door - SECURE 6. Static Ports - CLEAR 7. ELT - ARMED 8. Cabin Air Exhaust - CLEAR 9. Access Panel - SECURE TAIL SECTION 1. Ventral Fin and Static Wick (1) - CHECK 2. VOR antennas (Right and Left) - CHECK 3. Rudder, Rudder Tab, Stinger and Static Wicks (4) - CHECK 4. Horizontal Stabilizer, Boots and Static Wick (Right and Left) - CHECK 5. Elevator, Tab, and Static Wicks (3 Each Side) - CHECK Verify Tabs are in "0" (Neutral) Position. 4-6 December, 1994

7 ~ft Super King Air B2001B200C Section IV The elevator trim tab "0" (neutral) position is determined by observing that the trailing edge of the elevator trim tab aligns with the trailing edge of the elevator when the elevator is resting against the down stops. 6. Position Light, Tail Floodlights (Left and Right If Installed) - CHECK LEFT AFT FUSELAGE 1. Access Panel - SECURE 2. Static Ports - CLEAR 3. Drains (Aft Compartment, Oxygen Discharge, Relief Tube) - CLEAR BEFORE ENGINE STARTING Items marked with an "." may be omitted at pilot's discretion after the first flight of each day. 1. Cabin Door (B200) or Cabin Door/Cargo Door (B200C) Circuitry Check - COMPLETE (See OTHER NORMAL PROCEDURES.) 2. Cabin Door (8200) or Cabin Door/Cargo Door (B200C) - LOCKED (See OTHER NORMAL PROCE DURES.) IWARNING I A crew member must close and lock the door. 3. Monogram Electric Toilet (if installed) - CONFIRM KNIFE VALVE OPEN 4. Load and Baggage - CONFIRM SECURE 5. Weight and C.G. - CHECKED 6. Seats - POSITIONED (SEATBACKS UPRIGHT, LATERAL-TRACKING SEATS - OUTBOARD POSI- TION) 7. Emergency Exit - CONFIRM SECURE AND UNLOCKED 8. Passenger Briefing - COMPLETE 9. Control Locks - CONFIRM REMOVED 10. Seats and Rudder Pedals ~ ADJUSTED 11. Seatbelts and Shoulder Harnesses - FASTENED 12. Oxygen System Ready - PULL ON 13. Oxygen System Preflight Inspection - CONFIRM COMPLETE (See OTHER NORMAL PROCEDURES.) 14. Fuel Panel Circuit Breakers - IN 15. Pilot's Instrument Panel - CHECK a. Compass Control - SLAVED b. Prop Sync Switch (if installed) TYPE I - OFF; TYPE II - ON 16. Pilot's Clock (Control Wheel) - CHECK AND SET 17. Pilot's Subpanel - CHECK a. Mic Selector Switch - NORMAL b. Parking Brake - CONFIRM SET c. Engine Ice Vane Switches - EXTEND December,

8 Section IV C?eechcmft Super King Air B200/B200C The engine ice vanes should be extended for all ground operations to minimize ingestion of ground debris. Turn engine anti-ice off, when required, to maintain oil temperature within limits. d. Pilot Air Control - AS REQUIRED e. Defrost Air Control - AS REQUIRED 1. Landing Gear Control - ON g. Landing Gear Relay Circuit Breaker - IN h. All Other Switches - OFF 18. Avionics Panel Switches - AS REQUIRED Radar - OFF OR STANDBY 19. Power Console - CHECK a. Power Levers -IDLE, FRICTION SET b. Propeller Levers - FULL FORWARD, FRICTION SET c. Condition Levers - FUEL CUT OFF, FRICTION SET d. Elevator, Aileron, and Rudder Trim Controls - SET e. Landing Gear Alternate Extension Handle - STOWED 20. Pedestal - CHECK a. EFIS Power Switches (if installed) - OFF b. EFIS Reversionary Switches (if installed) - NORMAL c. Cabin Pressure Switch - PRESS d. Rudder Boost Switch - ON e. Elevator Trim Switch - ON 1. Pressurization Controller - SET 21. Copilot's Instrument Panel - CHECK Compass Control - SLAVED * 22. Copilot's Clock (Control Wheel) - CHECK AND SET 23. Copilot's Subpanel - CHECK a. Cabin Sign - NO SMOKE & FSB b. Vent Blower Switch - AUTO c. Bleed Air Valve Switches - OPEN OR ENVIR OFF d. Cabin Temp Mode Control - OFF e. Cabin/Cockpit Air Control - AS REQUIRED f. Copilot Air Control - AS REQUIRED g. Mic Selector Switch - NORMAL h. Oxygen Pressure - CONFIRM i. All Other Switches - OFF 24. Copilot's Circuit Breaker Panel - CHECK * 25. Pilot's Static Air Source - NORMAL * 26. Fire Extinguisher (Under Copilot's Chair) - CHECK 27. Fuel Panel - CHECK a. Battery - ON (L & R FUEL PRESS, L & R ICE VANE EXT annunciators - ILLUMINATED) * b. Firewall Shutoff Valves - CLOSE * c. Standby Pumps - ON (Usten For Operation, L & R FUEL PRESS annunciators - ILLUMINATED) * d. Firewall Shutoff Valves - OPEN (L & R FUEL PRESS annunciators - EXTINGUISHED) 4-8 December, 1994

9 ~ft Super King Air B200/B200C Section IV * e. Standby Pumps - OFF (L & R FUEL PRESS annunciators - ILLUMINATED) * 1. Crossfeed - ALTERNATELY LEFT AND RIGHT (FUEL CROSSFEED annunciator -ILLUMINATED, L & R FUEL PRESS annunciators - EXTINGUISHED) * g. Crossfeed - OFF * h. Auxiliary Tank Transfer - AUTO * i. No Transfer Lights - PRESS TO TEST (if extinguished) j. Fuel Quantity (Main and Auxiliary) - CHECK * 28. Landing Gear Handle Lights - PRESS TO TEST * 29. Hydraulic Fluid Sensor (if installed) - TEST (HYD FLUID LOW annunciator ILLUMINATED) 30. Beacon - ON 31. DC VoltlLoadmeters - PRESS TO CHECK VOLTAGE (23 volt minimum) * 32. Annunciators - TEST * 33. Stall Warning - TEST * 34. Fire Detectors and Fire Extinguishers (if installed) - TEST ENGINE STARTING (BATTERY) 1. Right Ignition and Engine Start - ON (R FUEL PRESS annunciator - EXTINGUISHED) 2. Right Condition Lever - LOW IDLE (at 12% N1 or above) 3. ITT and N1 - MONITOR (1000 C maximum) If no ITT rise is observed within 10 seconds after moving the Condition Lever to LOW IDLE, move the Condition Lever to CUT OFF. Allow 60 seconds for fuel to drain and starter to cool, then follow ENGINE CLEARING procedures. 4. Right Oil Pressure - CHECK 5. Right Condition Lever - HIGH IDLE 6. Right Ignition and Engine Start - OFF (at 50% N1 or above) 7. Right Generator - RESET, (HOLD for 1 sec) then ON (charge battery until loadmeter reads approximately 50% or less) In order to turn the generator ON, the generator control switch must be held in the springloaded RESET position for a minimum of one second, then released to ON. The BATTERY CHARGE annunciator will illuminate approximately 6 seconds after the generator is on the line. If the annunciator does not extinguish within 5 minutes, refer to NICKEL CADMIUM BATTERY CHECK procedure (see OTHER NORMAL PROCEDURES). 8. Right Generator - OFF 9. Left Ignition and Engine Start - ON (L FUEL PRESS annunciator - EXTINGUISHED) 10. As Left N1 rpm accelerates thru 12%: a. Left Condition Lever - LOW IDLE b. Right Generator - ON 11. ITT and N1 - MONITOR (1000 C maximum) 12. Left Oil Pressure - CHECK December,

10 Section IV ~ft Super King Air B200/B200C 13. Left Ignition and Engine Start - OFF (at 50% N1 or above) 14. D.C. VoltlLoadmeters - PRESS TO CHECK VOLTAGE ( volts) 15. Left Generator - RESET, (HOLD for 1 sec) THEN ON 16. Right Condition Lever - REDUCE TO LOW IDLE or as required for air conditioner. ENGINE STARTING (EXTERNAL POWER) NEVER CONNECT AN EXTERNAL POWER SOURCE TO THE AIRPLANE UNLESS A BATTERY INDICATING A CHARGE OF AT LEAST 20 VOLTS IS IN THE AIRPLANE. If the battery voltage is less than 20 volts, the battery must be recharged, or replaced with a battery indicating at least 20 volts, before connecting external power. Only use an external power source fitted with an AN-type plug. When an external power source is used, it must be set to 28.0 to 28.4 volts and be capable of producing 1000 amperes momentarily and 300 amps continuously. The battery should be On to absorb transients present in some auxiliary power units. An EXT PWR annunciator is provided to alert the crew when an external DC power plug is connected to the airplane. 1. Avionics Master Switch - CONFIRM OFF 2. Left and Right Generator Switches - CONFIRM OFF 3. Battery - ON 4. External Power Source - TURN OFF, then CONNECT TO AIRPLANE 5. External Power Source - TURN ON 6. Voltmeter TO 28.4 VOLTS If the battery is partially discharged, the BATTERY CHARGE annunciator will illuminate approximately 6 seconds after the external power is on the line. If the annunciator does not extinguish within 5 minutes, refer to the NICKEL-CADMIUM BATTERY CHECK procedure (see OTHER NORMAL PROCEDURES). 7. Propeller Levers - FEATHER 8. Right Ignition and Engine Start - ON (R FUEL PRESS Annunciator - EXTINGUISHED) 9. Right Condition Lever - LOW IDLE (at 12% N1 or above) 10. ITT and N1 - MONITOR (1000 C maximum) If no ITT rise is observed within 10 seconds after moving the Condition Lever to LOW IDLE, move the Condition Lever to FUEL CUT OFF, Allow 60 seconds for fuel to drain and starter to cool, then follow ENGINE CLEARING procedures. 11. Right Oil Pressure - CHECK 12. Right Ignition and Engine Start - OFF (at 50% N1 or above) 13. Left Ignition and Engine Start - ON (L FUEL PRESS Annunciator - EXTINGUISHED) 14. Left Condition Lever - LOW IDLE (at 12% N1 or above) 4-10 December, 1994

11 Ci?eechcmft Super King Air B2001B200C Section IV 15. In and N1 - MONITOR (1000 C maximum) 16. Left Oil Pressure - CHECK 17. Left Ignition and Engine Start - OFF (at 50% N1 or above) 18. External Power Source - TURN OFF, DISCONNECT, SECURE DOOR 19. Left and Right Generators - RESET, (HOLD for 1 sec) THEN ON 20. Propeller Levers - FULL FORWARD ENGINE CLEARING The following procedure is used to clear an engine at any it is deemed necessary to remove internally trapped fuel and vapor, or if there is evidence of a fire within the engine. Air passing through the engine serves to purge fuel, vapor, or fire from the combustion section, gas generator turbine, power turbines and exhaust system. 1. Condition Lever - FUEL CUT OFF 2. Ignition and Engine Start - STARTER ONLY (for a maximum of 40 seconds) Do not exceed the starter time limits; see Section II, LIMITATIONS. 3. Ignition and Engine Start - OFF BEFORE TAXI Items marked with an "." may be omitted at pilot's discretion after the first flight of the day. If excessive llt's occur during anyone of the following conditions, adjust the condition levers to a higher N1 speed. - When high generator loads are required. - During operations at high ambient air temperatures. - During operations at high field elevations. If excessive ITI's are encountered, particularly if accompanied by a decreasing N1, the associated generator should be turned off prior to attempting to accelerate the engine. If the right ITT is high, also tum off the air conditioner by selecting the CABIN TEMP MODE switch to OFF. 1. Inverters CHECK (Volts/Freq = V/ Hz) a. Either Inverter - SELECT (Check Volts, Freq, INVERTER annunciator - EXTINGUISHED) b. Other Inverter - SELECT (Check Volts, Freq, INVERTER annunciator - EXTINGUISHED) 2. Inverter - SELECT NO. 1 OR NO.2 3. Loadmeters - PARALLEL WITHIN 10% 4. Avionics Master - ON 5. EFIS Power (if installed) - ON 6. External Lights - AS REQUIRED 7. Cabin Lights - AS REQUIRED 8. Bleed Air Valves - OPEN OR ENVIR OFF - AS REQUIRED 9. Cabin Temp Mode - AUTO December,

12 Section IV CReechcmft Super King Air B2001B200C 10. Cabin Temperature - AS REQUIRED 11. Instruments - CHECK (EFtS brightness at minimum required, if installed) Brake Deice (if installed) - CHECK a. Bleed Air Valves - OPEN b. Brake Deice - ON (BRAKE DEICE ON annunciator - ILLUMINATED) c. Condition Levers - HIGH IDLE (if Brake Deice is required) d. Brake Deice - OFF (BRAKE DEICE ON annunciator - EXTINGUISHED) e. Condition Levers - LOW IDLE Do not leave brake deice on longer than required to check function of annunciators at ambient temperatures above 15 C. Brake deice control valves may become inoperative if valves are not cycled periodically. One cycle of the valves is required daily regardless of the weather conditions. 13. Flight Controls - CHECK PROPER DIRECTION AND FREEDOM OF MOVEMENT 14. Flaps - CHECK AND SET 15. Brakes - RELEASED AND CHECKED Never taxi with a flat tire or flat shock strut. During taxi operations, particular attention should be given to propeller tip clearance. Extreme caution is required when operating on unimproved or irregular surfaces or when high winds exist. If operations produce a propeller rpm over 1600, retard propeller levers to the detent to limit rpm to 1600 to help reduce the possibility of ingestion of ground debris. BEFORE TAKEOFF (Runup) Items marked with an ".." may be omitted at pilot's discretion after the first flight of the day. 1. Avionics and Radar - CHECK 2. EFIS (if installed) - TEST 3. Pressurization - CHECK AND SET.. a. Cabin Altitude Selector Knob - ADJUST SO THAT "CABIN ALT" DIAL INDICATES AN ALTITUDE 1000 FEET BELOW FIELD PRESSURE ALTITUDE.. b. Rate Control Selector Knob - SET INDEX AT 12-0'CLOCK POSITION '* c. Cabin Pressurization Switch - HOLD IN TEST * d. Cabin Climb Indicator - CHECK FOR RATE OF DESCENT INDICATION.. e. Cabin Pressurization Switch - RELEASE TO PRESS WHEN PRESSURIZING IS CONFIRMED 1. Cabin Altitude Selector Knob - ADJUST SO THAT INNER SCALE (ACFT ALT) INDICATES PLANNED CRUISE ALTITUDE PLUS 1000 FEET (If this setting does not result in an outer scale (CABIN ALT) indication of at least 500 feet above take-off field pressure altitude, adjust as required.) 4-12 December, 1994

13 ~ft Super King Air B200/B200C Section IV 4. Autopilot - CHECK 5. Elevator Trim - CHECK a. Elevator Trim - ON b. Pilot's and Copilot's Switches - CHECK OPERATION c. Trim Quick Disconnect - CHECK (ELEC TRIM OFF annunciator - ILLUMINATED) d. Elevator Trim - OFF, THEN ON (ELEC TRIM OFF annunciator - EXTINGUISHED) I WARNING I Operation of the electric trim system should occur only by movements of pairs of switches. Any movement of the elevator trim wheel while depressing only one switch denotes a system malfunction. The elevator trim control switch must then be turned OFF and flight conducted only by manual operation of the trim wheel. 6. Trim Tabs - CONFIRM SET 7. Primary Governors, Overspeed Governors and Rudder Boost - TEST a. Rudder Boost - ON b. Prop Governor Test Switch - HOLD TO PROP GOV TEST c. Power Levers (Individually) - INCREASE UNTIL PROP IS STABILIZED AT 1830 TO 1910 RPM. d. Propeller Lever - RETARD TO DETENT, THEN FULL FORWARD (to check primary governor) e. Power Lever - CONTINUE TO INCREASE UNTIL RUDDER MOVEMENT IS D. (Observe ITT and Torque Limits) f. Power Lever - IDLE g. Repeat Steps c - f h. Prop Governor Test - RELEASE 8. Autofeather (if installed) - CHECK a. Power Levers - APPROXIMATELY 500 FT-LBS TORQUE b. Autofeather Switch - HOLD TO TEST (L & R AUTOFEATHER annunciators - ILLUMINATED) c. Power Levers - RETARD INDIVIDUALLY: 1) At Approximately 410 ft-ibs - OPPOSITE ANNUNCIATOR EXTINGUISHED 2) At Approximately 260 ft-ibs - BOTH ANNUNCIATORS EXTINGUISHED (Propeller Starts to Feather) Autofeather annunciator will cycle on and off with each fluctuation of torque as the propeller feathers. d. Power Levers - BOTH RETARDED (L & R AUTOFEATHER annunciators - EXTINGUISHED, neither propeller feathers) 9. Autofeather (if installed) - ARM 10. Propeller Feathering (Manual) - CHECK * 11. Vacuum and Pneumatic Pressure - CHECK a. Left Bleed Air Valve - INSTR & ENVIR OFF 1) L BL AIR OFF annunciator - ILLUMINATED 2) Gyro Suction Gage and Pneumatic Pressure Gage in Green Arc b. Right Bleed Air Valve - INSTR & ENVIR OFF 1) R BL AIR OFF, L & R BLEED FAIL annunciators - ILLUMINATED December,

14 Section IV Norma; Procedures CL?eechcraft Super King Air B200JB200C 2) Gyro Suction Gage and Pneumatic Pressure Gage -Zero c. Left Bleed Air Valve - OPEN 1) L BL AIR OFF, L & R BLEED FAIL annunciators - EXTINGUISHED 2) Gyro Suction Gage and Pneumatic Pressure Gage - IN GREEN ARC d. Right Bleed Air Valve - OPEN (R BL AIR OFF annunciator - EXTINGUISHED) 12. Engine Ice Vanes - CHECK (see OTHER NORMAL PROCEDURES) 13. Systems For Icing Flight - CHECK, IF REQUIRED (see OTHER NORMAL PROCEDURES) 14. Fuel Quantity, Flight and Engine Instruments - CHECK BEFORE TAKEOFF (Final Items) 1. Propeller Levers - CONFIRM FULL FORWARD 2. Flaps - CONFIRM SET 3. Trim - CONFIRM SET 4. Brake Deice (if installed) - OFF 5. Left and Right Bleed Air - OPEN 6. Aft Blower (if installed) - AS REQUIRED 7. Annunciators - EXTINGUISHED OR CONSIDERED 8. Ice Protection - ON, IF REQUIRED a. Auto Ignition - ON (L and R IGNITION ON annunciators - ILLUMINATED) b. Engine Ice Vanes - CONFIRM EXTENDED (L & R ENG ANTI-ICE annunciators - ILLUMINATED) c. Windshield Anti-ice - NORMAUHI d. Prop Heat - AUTO e. Left and Right Fuel Vent Heat - ON f. Stall Warning Heat - ON g. Left and Right Pitot Heat - ON Prolonged use of stall warning and pitot heat on the ground will damage the heating elements. 9. Generator Load - CHECK 10. Engine Ice Vanes (if not required) - CONFIRM RETRACTED 11. External Lights - AS REQUIRED 12. Transponder - ON 13. V1, VR, V2, and Minimum Takeoff Power - CONFIRM TAKEOFF 1. Brakes - HOLD 2. Power - SET (ensure minimum takeoff power is available) 3. Autofeather Annunciators (if installed) - ILLUMINATED 4. Brakes - RELEASED Increasing airspeed will cause torque and ITT to increase. 5. Landing Gear - UP (when positive climb established) 4-14 December, 1994

15 ~ft Super King Air B200lB200C Section IV 6. Flaps - UP (at blue line, 121 knots minimum) CLIMB 1. Vaw Damp - ON 2. Climb Power - SET 3. Propellers RPM 4. Prop Sync (if installed) ON 5. Autofeather (if inslalled) - OFF 6. Engine Instrumenls - MONITOR 7. Cabin Sign - AS REQUIRED 8. Pressurization - CHECK 9. Aft Blower (if inslalled) AS REQUIRED 10. Ughts - AS REQUIRED CRUISE I WARNING ~ Do not hll power levers in flight. 1. Cruise Power - SET PER CRUISE POWER TABLES OR GRAPHS 2. Engine Instruments - MONITOR 3. Auxiliary Fuel Gages - MONITOR (Ensure fuel is being transferred from the auxiliary tanks.) 4. Pressurization - MONITOR (Reset if cruise altitude changes by 1000 feet or more) DESCENT 1. Pressurization - SET a. Cabin Altitude Selector Knob - SET PER PRESSURIZATION CONTROllER SETTING FOR LANDING GRAPH, OR SO THAT CABIN ALl" DIAL INDICATES LANDING FIELD PRESSURE ALn TUDE PLUS 500 FEET. b. Rate Control Selector Knob - AS DESIRED 2. Altimeler SET 3. Cabin Sign - AS REQUIRED 4. Windshield Anti-ice - AS REQUIRED (NORMAL or HI well belore descenl into warm, moist air, to aid in defogging.) 5. Autolealher (II installed) - ARM 6. Fuel Balance - CHECK 7. Power - AS REQUIRED Approximately 75% Nt is required to maintain the pressurization schedule during descent. BEFORE LANDING I CAur!0N l Propeller operation in Ihe range of rpm sbo'd be avoided as it may cause ILS interference. December,

16 Section 4 Raytheon Aircraft Company Super King Air B200lB200C 1. Approach Speed - CONFIRM 2. Pressurization - CHECK 3. Cabin Sign NO SMOKE & FSB 4. Flaps - APPROACH 5. landing Gear - DN 6. lights - AS REQUIRED Under low visibility conditions, landing and taxi lights should be left off due to light reflections. 7. Prop Sync (TYPE I). OFF 8. Radar - AS REQUIRED 9. Surtace Deice - CYCLE (as required) If crosswind landing is anticipated, determine crosswind component from Section V. PERFORMANCE. Immediately priorto touchdown, lower upwind wing and align the fuselage with the runwayby use of rudder. During rollout, hold aileron control into the wind and maintain directional control with rudder and brakes. Use propeller reverse as desired. I NORMAL LANDING I 1. Flaps DOWN 2. Airspeed - NORMAL LANDING APPROACH SPEED 3. Yaw Damp - OFF 4. Power levers - IDLE 5. Propeller Levers - FULL FORWARD After Touchdown: ICAUTION I To ensure constant reversing characteristics, the propeller levers must be in the high rpm position. 6. Power Levers BETA RANGE OR REVERSE (AS REQUIRED) 7. Brakes- AS REQUIRED MAXIMUM REVERSE THRUST LANDING 1. Flaps - DOWN 2. Airspeed - NORMAL LANDING APPROACH SPEED 3. Yaw Damp- OFF 4. Condition Levers - HIGH IDLE 5. Propeller l evers - HIGH RPM After Touchdown: 6. Power Levers - LIFT AND REVERSE 4-16 April,2004

17 <i?eechcmft Super King Air B2001B200C Section IV 7. Brakes - AS REQUIRED 8. Condition Levers - LOW IDLE If possible, propellers should be moved out of reverse at approximately 40 knots to minimize blade erosion. Care must be exercised when reversing on runways with loose sand, dust, or snow on the surface. Flying gravel will damage propeller blades, and dust or snow may impair the pilot's visibility. BALKED LANDING 1. Power - MAXIMUM ALLOWABLE 2. Airspeed KNOTS (when clear of obstacles, establish normal climb) 3. Flaps - UP 4. Landing Gear - UP AFTER LANDING 1. Auto Ignition - OFF 2. Engine Ice Vanes - EXTEND The engine ice vanes should be extended for all ground operations to minimize ingestion of ground debris. Tum engine anti-ice off, when required, to maintain oil temperature within limits. 3. Lights - AS REQUIRED 4. Ice Protection - OFF 5. Transponder - STANDBY 6. Radar - STANDBY or OFF 7. Trim Tabs - SET 8. Flaps - UP SHUTDOWN AND SECURING 1. Parking Brake - SET 2. Standby Boost Pumps and Crossfeed - OFF 3. EFIS Power (if installed) - OFF 4. Avionics Master - OFF 5. Inverter - OFF 6. Autofeather (if installed) - OFF 7. Lights - OFF 8. Vent Blower - AUTO 9. Cabin Temp Mode - OFF 10. Aft Blower (if installed) - OFF 11. Radiant Heat (if installed) - OFF 12. Battery - CHARGED 13. ITT - STABILIZED AT MINIMUM TEMPERATURE FOR ONE MINUTE December,

18 Section IV Oeechcrnft Super King Air B200/B200C 14. Condition Levers - FUEL CUT OFF Monitor ITT during shutdown. If sustained combustion is observed, proceed immediately to the engine clearing procedure. During shutdown, ensure that the compressors decelerate freely. Do not close the firewall fuel valves for normal engine shutdown. 15. Propeller Levers - FEATHER 16. DC VoltlLoadmeters - CHECK VOLTAGE (No voltage indicates current limiter is out) 17. Overhead Panel Switches - OFF 18. Oxygen System Ready - PUSH OFF 19. Battery and Generator Switches - OFF (below 150/0 N1) 20. Control Locks - INSTALL 21. Emergency Exit - LOCKED N1 decreasing below 150/0 indicates the starter relay is not engaged. 22. Electric Toilet (if installed) - SERVICE AS REQUIRED 23. Tiedowns and Chocks - AS REQUIRED 24. External Covers - AS REQUIRED 25. Propeller Locks - AS REQUIRED 26. Oil Quantity Check - AS REQUIRED OTHER NORMAL PROCEDURES OXYGEN SYSTEM PREFLIGHT INSPECTION 1. Passenger Manual Drop Out - PUSH OFF 2. Oxygen System Ready - PULL ON 3. Crew Diluter Demand Masks - DON MASK, CHECK FIT AND OPERATION, AND STOW I WARNING I Beard and mustaches should be carefully trimmed so that they will not interfere with the proper sealing of an oxygen mask. The fit of the oxygen mask around the beard or mustache should be checked on the ground for proper sealing. Studies conducted by the military and the FAA conclude that oxygen masks do not seal over beards and mustaches. Hats and "earmuff" type headsets must be removed prior to donning crew oxygen masks. Headsets and eyeglasses worn by crew members may interfere with quick-donning capabilities. 4. Oxygen Duration - DETERMINE A bottle of 1850 psi at 15 C is fully charged (100 % capacity). Read duration directly from the table. a. Read the oxygen pressure from the gage December, 1994

19 ~ft Super King Air B200/B200C Section IV b. Read the IOAT. c. Determine the percent of usable capacity from the following graph (eg., 1100 psi at O C = 570/0). OXYGEN AVAILABLE WITH PARTIALLY FULL BOTTLE (f) o, w :: ::> (f) en w 0:: W (!) -c C) 500 o jill'" ". (vl- 0~ ~ ~-~~ ~q.:-t} ~ # ~ ~«) ~ ~ ~ ~'v<v, " o~ ~",...- ~ ~ ti' ~~ ~ v: ~~ :~ ~ ~~ ~ t' L...Il" ~ ~"... ~~...t' ~~ ~ ~~~ ~~~ a PERCENT OF USABLE CAPACITY.~\ brq \.'.0 bc> ~\ \..~'2.-.0 Q C9100~92 C d. Compute the oxygen duration in minutes from the table by multiplying the full bottle duration by the percent of usable capacity. eg., 1) Pilot and copilot with masks set at 1000/0 plus 6 passengers = 10 people using oxygen. Pilot and copilot are each counted as 2 people with diluter demand masks set at the 100% or NORMAL mode. 2) Cylinder volume = 115 cubic feet. 3) Duration with full bottle =73 minutes 4) Duration with 570/0 capacity =.57 x 73 = 41 minutes. December,

20 Section IV Cikechcmft Super King Air B2001B200C Stated Cylinder OXYGEN DURATION WITH FULL BOTTLE (100% CAPACITY) tnumber OF PEOPLE USING Size t16 t17 (Cu Ft) DURATION IN MINUTES or or n "'Will not meet oxygen requirements t For oxygen duration computations, count each diluter-demand crew mask in use as 2 (e.g., with 4 passengers and a crew of 2, enter the table at 8 people using). HEATING/COOLING SYSTEM 1. Bleed Air Valves - OPEN (ENVIR OFF for more efficient cooling on the ground.) 2. Cabin Temperature Mode - AUTO 3. Vent Blower - AUTO 4. Radiant Heat or Aft Blower (if installed) - AS REQUIRED (The radiant heat system should be used in conjunction with manual temp control mode only.) 5. Temperature Control - AS REQUIRED 6. Cabin Air Control - AS REQUIRED (to divert cabin air flow to the cockpit) With the Cabin Temp Mode switch in AUTO, MAN HEAT or MAN COOL, the ventilation blower operates in the low position. For increased air circulation, turn the Vent Blower Switch to HIGH: For maximum cooling, the ventilation blower should be in the HIGH mode and the aft blower (if installed) should be selected ON. With air conditioner on, maintain at least 60 0k N1 speed on the right engine. If below N1 minimum speed, the AIR COND N1 LOWannunciator will illuminate, and the air conditioner clutch will disengage. For maximum heating, the ventilation blowers should be selected to HIGH and the aft blower should be selected OFF. RADIANT HEAT (IF INSTALLED) Overhead radiant heat, operated by a switch in the environmental group, can be used in conjunction with an auxiliary power unit to warm the cabin prior to engine starting, and may be used for supplemental heat in flight, if required. DEFROSTER AIR 1. Windshield Defroster Air Control (right side of pilot's control column) - ON (pull) 4-20 December, 1994

21 Super King Air B200/B200C 2. Pilot, Copilot, and Cabin Air Controls - OFF (if increased defroster air flow is required) Section 4 BLENDING ANTI-ICING ADDITIVE TO FUEL The following procedure must be observed when blending anti-icing additive with fuel. 1. The additive must conform to specification MIL-I or MIL-I The concentration of the additive must be a minimum of 0.10% and a maximum of 0.15% by volume. Thus, a 20 oz. can of additive is sufficient for 105 to 155 gallons of fuel. 3. When blending the additive as the airplane is being refueled, use the following precautions: a. Refuel at a rate of 30 to 45 gallons per minute. A rate of less than 30 GPM may be used when topping off the tanks. b. Start additive after fuel flow starts, and stop before fuel flow stops. c. Ensure additive is directed into the flowing fuel stream. d. Do not allow concentrated additive to contact coated interior of fuel cells or airplane surfaces. ADDING BIOCIDE TO FUEL Refer to the Super King Air 200 Series Maintenance Manual and to the latest revision of Pratt & Whitney Canada Engine Service Bulletin No for concentrations to use, and for procedures, recommendations, and limitations pertaining to the use of biocidal/fungicidal additives in turbine fuels. USE OF JET B, JP-4, AND AVIATION GASOLINE Fuel quantity indicators will not indicate correctly when using Jet B, JP-4, or aviation gasoline due to the differences in their density and dielectric constants. The indicated fuel quantity should be corrected using the factors show below. These factors have been generalized in some cases for simplicity, thus results should be considered as approximations. When using Jet B or JP-4 multiply the indicated fuel quantity by.96 to obtain the corrected fuel quantity. When using aviation gasoline, multiply the indicated fuel quantity by.94 to obtain the corrected fuel quantity. NICKEL-CADMIUM BATTERY CHECK (GROUND OPERATION ONLY) Illumination of the BATTERY CHARGE annunciators indicates an above-normal charge current. Following an engine start, the battery recharge current is very high and causes the illumination of the BATTERY CHARGE anunciator. It should normally extinguish within five minutes. If it does not, or if it should reappear, the battery charge current should be monitored using the procedure shown below until it decreases to a level to extinguish the BATTERY CHARGE annunciator. Check the battery charge current every 90 seconds until the charge current decreases sufficiently to extinguish the annunciator. No decrease in charging current between checks indicates an unsatisfactory condition and the battery should be removed and checked by a qualified nickel-cadmium battery shop. Do not take off with annunciator illuminated unless a decreasing battery charge current is confirmed. 1. Either Generator - OFF 2. Voltmeter - ENSURE INDICATION OF 28 VOLTS 3. Battery Switch - OFF MOMENTARILY, NOTING DECREASE IN LOADMETER. If Decrease in Loadmeter Exceeds 2.5%: 4. Battery - CONTINUE TO CHARGE, REPEATING STEP 3 EVERY 90 SECONDS. February,

22 Beech Super King Air 8200 & B200C Section IV - Raytheon Aircraft 5. Battery Charge Annunciator - EXTINGUISHED WHEN DECREASE IN LOADMETER IS LESS THAN 2.50/0. COLD WEATHER PROCEDURES (SNOW, SLUSH, AND ICE) PREFLIGHT INSPECTION Verify that the tires are not frozen to the ramp, and that the brakes are free of ice contamination. Deicing or anti-icing solutions may be used on the tires and brakes if they are frozen. Solutions which contain a lubricant, such as oil, must not be used as they will decrease the effectiveness of the brakes. In addition to the normal exterior preflight inspection, special attention should be given all vents, openings, static ports, control surfaces, hinge points, and the wing, tail, and fuselage surfaces for accumulations of ice or snow. Removal of these accumulations is necessary prior to takeoff. Airfoil contours may be altered by the ice and snow to the extent that their lift qualities will be seriously impaired. Ice and snow on the fuselage can increase drag and weight. Frost that may form on the wing fuel tank bottom skins need not be removed prior to flight. Frost that may accumulate on other portions of the wing, the tail surfaces, or on any control surface, must be removed prior to flight. Inspect the propeller blades and hubs for ice and snow. Unless engine inlet covers have been installed during snow or icing conditions, the propellers should be turned by hand in the direction of normal rotation to make sure they are free to rotate prior to starting engines. The removal of frozen deposits by chipping or scraping is not recommended. A soft brush, squeegee, or mop may be used to clear snow that is not adhering to the surfaces. If use of deicing/anti-icing fluids are required to produce a clean airplane, special attention must be given to ensure that the pitot masts, static ports, fuel vents, cockpit windows and the area forward of the cockpit windows ~re free of the deicing/anti-icing solution. Both wings and both stabilizers must receive the same complete treatment. The type and concentration of deicing/anti-icing solution being applied and the rate of precipitation will affect the length of time the treatment will be effective. Refer to Chapter 12 of the Beech Super King Air200 Series Maintenance Manual and Section VIII of this manual for additional information on deicing and anti-icing of airplanes on the ground. See Section II, Limitations, for a list of approved fluids. Complete the normal preflight procedures, including a check of the flight controls for complete freedom of movement. After engine start, exercise the propellers through low- and high-pitch and into reverse range to flush any congealed oil through the system. If the optional brake deicing system is installed, turn it on prior to taxi if brakes require deicing. TAXIING Taxiing through deep snow or slush should be avoided when possible. Snow and slush can be forced into brake assemblies which may cause the brakes to freeze during a prolonged hold on the ground or during the subsequent flight. Keep flaps retracted during taxiing to avoid throwing snow or slush into flap mechanisms and to minimize damage to flap surfaces. Glaze ice can be difficult to see. Therefore, taxi slowly and allow more clearance from objects when maneuvering the airplane. BEFORE TAKEOFF After completion of the normal Before Takeoff checklist, verify that the airplane is still free of frozen contaminants. Ensure the runway is free from hazards such as snow drifts, glazed ice, and ruts May, 2000

23 Raytbeon Aircraft Beech Super King Air B200 & B200C Section IV - IWARNING, Ice, frost, or snow on top of deicing/anti-icing solutions must be considered as adhering to the airplane. Takeoff should not be attempted. If visible moisture will be encountered during the takeoff, engine ice vanes must be extended to reduce the possibility of ice being ingested into the engine air inlet. TAKEOFF Allow additional take-off distance when snow or slush is on the runway. Extra cycling of the landing gear when above 500 feet AGL may help clear any contamination from the gear system. When using FAA Approved SAE Type II or Type IV deicing/anti-icing fluids in the concentrated form, the control column force required to rotate for takeoff may temporarily increase approximately 20 pounds. The cruise, descent, approach and landing phases of flight are not affected by the use of these fluids. LANDING If it is possible that the brakes may be restricted by ice accumulations from previous ground or in-flight icing conditions, turn the brake deicing system (if installed) on during the descent. Braking and steering are less effective on slick runways. Also, hydroplaning may occur under wet runway conditions at higher speeds. Use the rudder to maintain directional control until the tires make solid contact with the runway surface. Selecting reverse thrust can effectively reduce stopping distances on slick runways; however, reverse thrust may cause snow or moisture to be thrown forward, temporarily reducing visibility. SHUTDOWN AND SECURING Avoid setting the parking brake, if possible. This will help reduce the possibility of freezing the brakes. Proper chocking can be used to prevent the airplane from rolling. May, A

24 Beech Super King Air 8200 & B200C Section IV - Raytbeon Aircraft THIS PAGE INTENTIONALLY LEFT BLANK May, 2000

25 CQeechcmft Super King Air B200/B200C 'Section IV ICING FLIGHT This airplane is approved for flight in icing conditions as defined in FAR 25, Appendix C. These conditions do not include, nor were tests conducted in, all conditions that may be encountered (e.g., freezing rain, freezing drizzle, mixed conditions, or conditions defined as severe). Some icing conditions not defined in FAR 25 have the potential of producing hazardous ice accumulations, which: 1) exceed the capabilities of the airplane's ice protection equipment; and/or 2) create unacceptable airplane performance. Flight into icing conditions which lie outside the FAR-defined conditions is not prohibited; however, pilots must be prepared to divert the flight promptly if hazardous ice accumulations occur. Refer to Section II for limitations relating to icing flight, and Section IliA for abnormal procedures associated with icing equipment malfunctions and procedures required by FAA AD I, WARNING I Due to distortion of the wing airfoil, ice accumulations on the leading edges can cause a significant loss in rate of climb and in speed performance, as well as increases in stall speed. Even after cyding deicing boots, the ice accumulation remaining on the boots and unprotected areas of the airplane can cause large performance losses. For the same reason, the aural stall warning system may not be accurate and should not be relied upon. Maintain a comfortable margin of airspeed above the normal stall airspeed.. In order to minimize ice accumulation on unprotected surfaces of the wing, maintain a minimum of 140 knots during operations in sustained icing conditions.. In the event of windshield icing, reduce airspeed to 226 knots or below. Prior to a landing approach, cycle the deicing boots to shed any accumulated ice. BEFORE TAKEOFF (RUNUP) 1. Auto Ignition - CHECK a. Power Levers - IDLE b. Auto Ignition - ARM (L & R IGNITION ON annunciators -ILLUMINATED) c. Power Levers - ADVANCE ABOVE FT-LBS TORQUE (L & R IGNITION ON annunciators - EXTINGUISHED) d.. Power Levers -IDLE (L & R IGNITION ON annunciators -ILLUMINATED) e. Auto Ignition - OFF (L & R IGNITION ON annunciators - EXTINGUISHED) 2. Engine Ice Vanes - CHECK (system initially on) a. Engine Ice Vanes - RETRACT (L& R ICE VANE EXT annunciators - EXTINGUISHED) b. Engine Ice Vanes (if required for takeoff) - EXTEND (L & R ICE VANE EXT annunciators - ILLU MINATED) 3. Windshield Anti-ice - CHECK a. Windshield Anti-ice - HI (Observe increase on left and right loadmeters.) b. Windshield Anti-ice - OFF, THEN NORMAL (Observe increase on left and right loadmeters.) c. Windshield Anti-ice - OFF 4. Electrothermal Propeller Deice - CHECK Do not operate propeller deice when the propellers are static. a. Automatic Prop Deice - AUTO b. Deice Ammeter - 14 to 18 amps July,

26 Section IV ~ Super King Air B200/B200C Monitor for 90 seconds to ensure automatic timer operation. On Airplanes Prior to : 2) Manual Propeller Deice Switch - MOMENTARILY HOLD IN "INNER" POSITION, THEN "OUTER" (Small loadmeter deflection on both meters in each position indicates the manual system is operating). On Airplanes and After, BL-37 and After: c. Manual Propeller Deice Switch - MOMENTARILY HOLD IN "MANUAL" POSITION (SmaJlloadmeter deflection on both meters indicates manual system is operating). Use of current for the manual (backup) system is not registered on the propeller deice ammeter; however, it will be indicated as part of the airplane's load on the loadmeters (small needle deflection) when the system is switched on. d. Automatic Propeller Deice Switch - OFF 5. Surface Deice System - CHECK a. Condition Levers - HIGH IDLE b. Pneumatic Pressure - CHECK c. Surface Deice Switch - SINGLE AND RELEASE 1) Pneumatic Pressure - Will Deaease Momentarily 2) Check boots visually, where possible, for inflation and hold down. 3) Inflation time is 6 seconds for wings, followed by 4 seconds for horizontal stabilizer. d. Surface Deice Switch - MANUAL AND HOLD 1) Pneumatic Pressure - Will Decrease Momentarily 2) Check boots visually, where possible, for inflation. e. Surface Deice Switch - RELEASE Check boots visually, where possible for hold down. 1. Condition Levers - LOW IDLE I WARNING I Do not cycle boots during takeoff. 6. Stall Warning and Pitot Heat - CHECK Prolonged use of stall warning and pitot heat on the ground will damage the heating elements. I IN FUGHT 1. Engine Ice Protection Before visible moisture is encountered at +5 C and below, or; At night when freedom from visible moisture is not assured at +5 C and below (Operation ofstrobe lights will sometimes show ice crystals not normally visible). a. Engine Ice Vanes - EXTEND (L & R ICE VANE EXT annunciators -ILLUMINATED) b. Check proper operation by noting torque drop September, 1995

27 geechcmft Super King Air B200/B200C I WARNING I Section IV If in doubt, extend the vanes. Engine icing can occur even though no surface icing is present. If freedom from visible moisture can not be assured, engine ice protection should be activated. Visible moisture is moisture of any form; clouds, ice crystals, snow, rain, sleet, hail or any combination of these. Operation of strobe lights will sometimes show ice crystals not normallly visible. If either engine's ice vane does not attain the selected position within 15 seconds, the appropriate L or R ICE VANE annunciator will illuminate. See ENGINE ICE VANE FAILURE in Section IliA, ABNORMAL PROCEDURES. 2. Auto Ignition Auto Ignition - ARM Auto Ignition must be ARMED for icing flight, precipitation, and operation during turbulence. To prevent prolonged operation of the ignitors with the system ARMED, do not reduce power levers below 500 ft-ibs torque. 3. Electrothermal Propeller Deice a. Automatic Prop Deice - AUTO (The system may be operated continuously in flight, and will function automatically until the switch is turned off.) b. Relieve propeller imbalance due to ice by increasing rpm briefly and returning to the desired setting. Repeat as necessary. If the deice ammeter does not indicate 14 to 18 amperes, or the automatic timer fails to switch, refer to Section IliA, ABNORMAL PROCEDURES. 4. Surface Deice I WARNING I All components of the surface deice system must be monitored during icing flight to ensure the system is functioning normally. These components include: Pneumatic Pressure Gage. The gage should indicate psi before boots are activated. The pressure will momentarily decrease when the boots are activated. Gyro Suction Gage. The gage should indicate in the area of the green arc corresponding to the airplane altitude. The vacuum will momentarily decrease when the boots are activated. Pneumatic Boots. Visually monitor the boots, where possible, to ensure ice is being removed. Operation of the surface deice system in ambient temperatures below -40 C can cause permanent damage to the deice boots. December,