Beechjet 400A Operating Handbook

1. Pitot Mast . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 2. Landing Light Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SECURE 3. Cabin Air Discharge Duct . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 4. Pitot and Static Drain Ports (2) . . . . . . . . . . . . . . . . . . . . . . . . .CLOSED 5. Oxygen Blowout Disc . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GREEN 6. Avionics Compartment Door . . . . . . . . . . . . . . . . . . . . . . . . . .SECURE 7. Windshield Wiper (if installed) . . . . . . . . . . . . . CONDITION, SECURE 8. Angle-of-Attack Sensor . . . . . . . . . . . . . . . . . . . . . . . . LEAR, ROTATES 9. Static Ports (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR D Right Wing 1. Emergency Exit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SECURE 2. Dorsal Fin Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 3. Wing Inspection Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONDITION 4. Wing Leading Edge Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 5. Center Fuselage Tank Drain (daily) . . . . . . . . . . . . . . DRAIN, SECURE 6. Fuel Quick Drains (3) (daily) . . . . . . . . . . . . . . . . . . . . DRAIN, SECURE 7. Wing Leading Edge and Upper Surface . . . . . . . . . . . . . . . . . CHECK, FREE OF FROST OR OTHER CONTAMINANTS 8. Fuel Filler Cap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SECURE 9. Fuel Tank Vent Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 10. Sniffle Valves (2) (daily). . . . . . . . . PUSH, PULL, CHECK FOR LEAKS 11. Wing Tip Vent Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 12. Navigation and Strobe Lights . . . . . . . . . . . . . . . . . . . . . . . CONDITION 13. Wing Anti-Ice Exhaust Port . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 14. Roll Trim Tab, Static Wicks (3), Spoilers, Flaps . . . . . . . . CONDITION 15. Main Gear, Doors, Tire, Brake . . . . . . . . . . . . . . . . . . . . . . . CONDITION 16. Center Tank Vent Outlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 17. Mixer Bay Vent Outlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 18. Fuel Filter Drain (daily) . . . . . . . . . . . . . . . . . . . . . . . . DRAIN, SECURE 19. Lower Fuselage Vent Outlets (2) . . . . . . . . . . . . . . . . . . . . . . . . CLEAR E Right Nacelle 1. Cowling Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK, SECURE 2. Engine Fan Duct and Fan . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION 3. Engine Inlet . . . . . . . . . . . . . . . . . CHECK FOR MISSING FASTENERS 4. Generator Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 5. Oil Level and Filler Door . . . . . . . . . . . . . . . . . . . . . . CHECK, SECURE 6. Drain Lines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 7. Thrust Reverser . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION 8. Engine Exhaust and Bypass Duct . . . . . . . . . . . . . . . . . . . CONDITION Preflight Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 P-3 F Empennage 1. Fuselage Fuel Filler Sniffle Valve (daily) . . . . . . PUSH, PULL, CHECK FOR LEAKS 2. Fuselage Fuel Filler Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SECURE 3. Upper Aft Fuselage Vent Outlet (right). . . . . . . . . . . . . . . . . . . . CLEAR 4. Cooling Air Discharge Duct . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 5. Aft Fuselage Vent Inlet (right) . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 6. Fuel Vent Ports (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 7. Stabilizer Trim, Elevator, Static Wicks (4) . . . . . . . . . . . . . CONDITION 8. Rudder, Trim Tab, Static Wicks (2) . . . . . . . . . . . . . . . . . . . CONDITION 9. Navigation and Strobe Lights . . . . . . . . . . . . . . . . . . . . . . . CONDITION 10. Temperature Sensor (if installed) . . . . . . . . . . . . . . . . . . . . . . . .CHECK 11. Aft Fuselage Vent Inlet (left) . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 12. Fire Extinguisher Relief Indicator . . . . . . . . . . . . . . . . . . . . . . . . . RED 13. Upper Aft Fuselage Vent Outlet (left) . . . . . . . . . . . . . . . . . . . . . CLEAR G Aft Baggage Compartment 1. Hydraulic Fluid Reservoir Sight Gauge . . . . . . . . . . . . FLUID VISIBLE 2. Fire Bottle Pressure Gauges (2) . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 3. Aft Compartment Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 4. Access Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SECURE 5. External Power Service Door (GPU not used) . . . . . . . . . . . .SECURE H Left Nacelle 1. Cowling Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK, SECURE 2. Engine Exhaust and Bypass Duct . . . . . . . . . . . . . . . . . . . CONDITION 3. Thrust Reverser . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION 4. Drain Lines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 5. Oil Level and Filler Door . . . . . . . . . . . . . . . . . . . . . . CHECK, SECURE 6. Generator Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 7. Engine Inlet . . . . . . . . . . . . . . . . . CHECK FOR MISSING FASTENERS 8. Engine Fan Duct and Fan . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION Preflight Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 P-4 I Left Wing 1. Brake System Accumulator Pressure . . . . . . . . . . . . . . . . . . . .CHECK 2. Fuel Filter Drain (daily) . . . . . . . . . . . . . . . . . . . . . . . . . RAIN, SECURE 3. Main Gear, Doors, Tire, Brake . . . . . . . . . . . . . . . . . . . . . . . CONDITION 4. Flaps, Spoilers, Static Wicks (3), Roll Trim Tab . . . . . . . . CONDITION 5. Wing Anti-Ice Exhaust Port . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 6. Navigation and Strobe Lights . . . . . . . . . . . . . . . . . . . . . . . CONDITION 7. Wing Tip Vent Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 8. Sniffle Valves (2) (daily). . . . . . . . . PUSH, PULL, CHECK FOR LEAKS 9. Fuel Tank Vent Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 10. Fuel Filler Cap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SECURE 11. Wing Leading Edge and Upper surface . . . . . . . . . . . . . . . . . . INANTS 12. Fuel Quick Drains (3) (daily) . . . . . . . . . . . . . . . . . . . . DRAIN, SECURE 13. Center Fuselage Tank Drain (daily) . . . . . . . . . . . . . . DRAIN, SECURE 14. Wing Leading Edge Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 15. Wing Inspection Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION 16. Dorsal Fin Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR Preflight Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 P-5 Preflight Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 P-6 his pge iiteitioipaaly aeet apink
BEFORE STARTING ENGINES
Caution:
If operation of the vent blower fan is desired prior to starting engines, do not attempt to open cabin door or emergency exit until vent blower has been turned off for at least 45 seconds. 1. Oxygen System Ready Control . . . . . . . . . . . . . . . . . . . . . . . PULL ON 2. Oxygen Mask (pilot and copilot) . . . . . . . . . . CHECK, SELECT 100%
Caotonn:
Beards 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 and mustache should be checked on the ground for proper sealing. Studies conducted by the military and FAA conclude that oxygen masks do not seal over beards and mustaches. 3. Circuit Breakers and Guarded Switch (C.B. Panels) . . . . . . . . . . .SET 4. Nonessential Bus Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 5. Radio Master Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 6. Defog Blower (pilot and copilot) . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 7. AHRS Battery Test Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH (HOLD FOR 5 SECONDS. CHECK FOR ANY ILLUMINATION OF AHRS BAT TEST ANNUNCIATOR WITHIN THE 5 SECONDS). 8. Hydraulic Pressure Switch . . . . . . . . . . . . . . . GUARD DOWN (NORM) 9. Emergency Landing Gear Door Close Handle . . . . . . . . . . SAFETIED 10. Emergency Landing Gear Down Handle . . . . . . . . . . . . . . . SAFETIED 11. Engine Start Select . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 12. Thrust Levers. . . . . . . . . . . . . . . . . FREE MOVEMENT, THEN CUTOFF 13. Roll Trim Select Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BOTH 14. Roll and Rudder Trim Disconnect Switch . . . . . . . . . . . . . . . . .NORM 15. Pitch Trim Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 16. Engine Synchronizer Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 17. Flap Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0º 18. Landing Select Switch. . . . . . . . . . . . . . . GUARD DOWN (FLAPS 30º) 19. Emergency Brake Handle . . . . . . . . . . . . . . . . . . . . . . . . . . SAFETIED 20. Landing Gear Handle. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN 21. Cabin Dump Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SAFETIED 22. Cabin Pressure Source Selector . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 23. Cockpit Temperature Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET 24. Manual Pressurization Control Knob. . . . . . . . . . . . . . . . . . . FULL INC 25. Cabin Temperature Control. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET 26. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 27. Fuel Counter. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..ZERO 28. Master Generator Switches . . . . . . . . . . . . . . GUARD DOWN (NORM) 29. Indicator Lights Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED 30. Instrument Light Switches . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-1 continued on next page 31. Exterior Light Switches. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 32. Landing Light Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RET/OFF 33. Anti-Ice/Deice Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 34. Heater Switches. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 35. Wiper Switches (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 36. Inverter Switches. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 37. Ignition Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY 38. Jet Pump Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 39. Fuel Crossfeed Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 40. Standby Power. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON (STBY PWR ILLUMINATES ON) 41. Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON (STBY PWR ANNUNCIATION MAY BE EITHER ON OR ARM) 42. Battery Feed Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH (STBY PWR ILLUMINATES ON, FDR FAIL LIGHT ILLUMINATES) 43. Battery . . . . . . . EMER, THEN ON (FDR FAIL LIGHT EXTINGUISHES) (STBY PWR ANNUNCIATION MAY BE EITHER ON OR ARM) 44. SPKR Switches . . . . . . . . . . . . . . . . . . . . . . . . .ON OR DON HEADSET 45. INTPH Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 46. Emergency Lights . . . . . . . . . . . . . . . . . . . . . . GUARD UP (TEST/OFF) 47. Master Test (All Except Generators) . . . . . . . . . . . . . . . . . . . . . . TEST oiutn:
When checking the stall warning systems, the master test switch must remain in the L or R STALL position until the column shaker and stall annunciator lights/horn actuate twice to check the altitude compensator. The second shaker actuation will occur at a higher AOA indication than the first actuation due to the high altitude bias. The stall annunciator lights/horn will actuate when the AOA indication approaches full travel. Observation of the two different shaker actuations and illumination of the green pass test light identify a successful test of the stall warning system. It is permissible to recheck the STBY PWR during theTAXI procedures if the No-Go light illuminates during the initial standby power check. It will be necessary to reset a generator if the master test switch is rotated out of the OFF position subsequent to engine starting. 48. Airspeed/Landing Gear Aural Warnings . . . . . . . . . . . . . . . . . . TEST 49. Indicator Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST 50. Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (N-16) 51. Boost Pumps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO 52. Fuel Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON MOMENTARILY, CHECK THAT BOTH PUMPS OPERATE AND THEN POSITION SWITCHES TO AUTO 53. Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (N-16) Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-2 continued from previous page continued on next page 54. Trim System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK(N-18) 55. Cockpit Voice Recorder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST If BEFORE STARTING ENGINES procedures are not to be immediately followed by STARTING ENGINES: 56. Standby Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 57. Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF STARTING ENGINES A GPU start is recommended at ambient temperatures below approximately - 15ºC. External power requirements are 28 VDC, 1,000 to 1,500 Amps output.
Caotonn:
Verify cabin door security by attempting to turn the handle to the unlocked position without depressing the release button. Confirm the eight lock pins on the forward and aft sides of the door are properly engaged as indicated by the white flags fully covering the red background. Only a crew member should close and lock the door. 1. Cabin Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCKED 2. Passenger Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE 3. Control Lock. . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVE AND STOW 4. Seats, Belts, and Shoulder Harnesses (pilot and copilot). . . . . . . . . . . . . . . . . . . FASTENED AND ADJUSTED 5. Parking Brake. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET oiutn:
When the engines are not running, the parking brake must be set from the pilot's side only. 6. Standby Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 7. Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 8. SPKR Switches . . . . . . . . . . . . . . . . . . . . . . . . .ON OR DON HEADSET 9. INTPH Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 10. DC Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 22 V MINIMUM FOR BATTERY START, 28 V FOR GPU START 11. Navigation Lights. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 12. Rotating Beacon . . . . . . . . . . . . . . . . . . . . . . . . GUARD DOWN (ARM) 13. Generator Reset Switches . . . . . . . . . . . . . . . . . . . . . SET FOR START 14. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 15. Engine EFCs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 16. Engine Start Select . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT L OR R 17. EFC AUX PWR ON Annunciator . . . . . . . . . . . . . . . . . . . ILLUMINATED 18. Engine Start Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS 19. Thrust Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IDLE AT 8% N2 20. ENG EFC OFF Annunciator. . . . . . . . EXTINGUISHED ABOVE 26% N2 Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-3 continued from previous page continued on next page
Caution:
Check starter disengagement approximately 35% N2. If starter has not disengaged b 45% N2, place thrust lever in CUT OFF position and remove all electrical power. If engine does not start within 10 seconds, place thrust lever in CUT OFF position, place ignition switch in OFF position, motor engine for 15 seconds, then press START DISENGAGE button. Maximum ITT limitations are: 550 to 600ºC for 4 seconds 600 to 700ºC for 2 seconds Maximum starter limitations are: 30 seconds on, 5 minutes off, 30 seconds on, 15 minutes off, 30 seconds on, one hour off. 21. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . MONITOR (52-54% N2) 22. Engine Start Select . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 23. Hydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORMAL 24. Cabin Pressure Source . . . . . . . . . . . . . . . . . . . . OPERATING ENGINE 25. Operating Generator (if battery start) . . . . . CHECK CURRENT LESS THAN 150 Amps 26. Engine Start Select . . . . . . . . . . . . . . . . . . . .SELECT OTHER ENGINE 27. FUEL PRESS LO Annunciator (other engine) . . . . . . . .ILLUMINATED 28. Other Engine . . . . . . . . . . . . . . . . . . . . . . . . . . REPEAT STEPS (18-23) 29. EFC AUX PWR ON Annunciator . . . . . . . . . . . . . . . . . .EXTINGUISHED 30. Ignition and Boost Pump Lights . . . . . . . . . . . . . . . . .EXTINGUISHED 31. FUEL/H PMP PRESS LO Annunciators . . . . . . . . . . . .EXTINGUISHED 32. Ground Power Unit (if used) . . . . . . . . . . . . . . . . . . . . . . DISCONNECT 33. Generator Reset Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 34. DC Amperes and Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 35. Standby Power Annunciator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-4 continued from previous page BEFORE TAXI
Caution:
Engine anti-ice systems must be ON for taxi and take-off when in visible moisture at 5ºC or colder. Except for a preflight check, do not operate system during ground operations at temperatures above 10ºC. oiutn:
Do not taxi until AHRS ALIGNING - DO NOT TAXI annunciators extinguish on both pilot's and copilot's panels. For maximum heating or cooling, the cabin pressure source selector should be in the BOTH HIGH position. Except during taxi conditions invisilble moisture at 5ºC or colder, the engine EFC system may be selected OFF during ground operations provided the engine speed is manually maintained at a minimum of 46% N2. With the EFC system selected OFF, a potential exists for the generators to drop off line with the thrust levers at idle. 1. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . .AS REQUIRED 2. Radio Masters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 3. AC Voltages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 4. Standby Gyro . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNCAGE 5. Cabin Pressure Source . . . . . . . . . . . . . BOTH HIGH OR BOTH NORM 6. Master Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . L/R GENERATORS 7. Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 8. Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF OR LOW oiutn:
In misting conditions on airplanes without windshield wipers, Windshield Anti-Ice on LOW will improve visibility. 9. Cabin Sign . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SAFETY 10. Galley Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 11. Flight Management System . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-5 TAXI 1. Wheel Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 2. Speedbrakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (N-18) 3. Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 4. Anti-Skid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (N-18) 5. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (N-19) 6. Jet Pumps. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (N-19) 7. Fuel Transfer (if fuel in fuselage tanks) . . . . . . . . CHECK TRANSFER PUMPS OPERATING 8. Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 9. Fuel Quantity and Balance . . . . . . . . . . . . . . . . . . . . . . . . . . RECHECK 10. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 11. Flight Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 12. Cabin Pressure Control. . . . . . . . . . . . . . . . . . SET CRUISE ALTITUDE 13. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF 14. Rudder Boost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (N-20) 15. Autopilot . . . . . . . . . . . . . . . . . . . . . . CHECK AND DISENGAGE (N-20) 16. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF 17. Engine EFC System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST (N-21) 18. Engine EFCs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED 19. Anti-Ice/Deice Systems (if required) . . . . . . . . . . . . . . . CHECK (N-22) 20. Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET 21. V1, VR, V2, AOA, N1, Flap Setting . . . . . . . . . . . . . . . . . . . . . .CONFIRM 22. Crew Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE BEFORE TAKEOFF 1. Engine EFCs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON oiutn:
Check for N2 of 52% to 54% and ENG EFC OFF annunciators extinguished. 2. Anti-Collision Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 3. Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 4. Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 5. Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOW 6. AOA Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 7. Pitot Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 8. Static Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 9. Ignitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 10. Annunciators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 11. Radar. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 12. Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 13. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 14. Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-6 continued on next page If ECS OFF takeoff is planned: 15. Cabin Pressure Source . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 16. Rate Control . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 O'CLOCK POSITION 17. Manual Pressure Control . . . . . . . . . . . . . . . . . . . . . FULL DECREASE 18. Vent Blower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON oiutn:
When taking off at an airport above 9,000 ft pressure altitude, CABIN PRESSURE LO annunciator may be illuminated. After takeoff, the cabin altitude should be set to extinguish the light. TAKEOFF 1. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPROXIMATELY 90% N1 2. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 3. Wheel Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASE 4. Thrust . . . . . . . . . . . . . TAKEOFF THRUST SET PRIOR TO 80 KNOTS 5. Nose Up Pitch Attitude at Rotation (VR) . . . . . . . . . . 13-15º DESIRED AFTER TAKEOFF 1. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP 2. Yaw Damp . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 3. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0º 4. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET MCT 5. Engine Sync . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 6. Recognition Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 7. Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RET/OFF 8. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY 9. Anti-Ice/Deice Systems (above 400 ft. AGL) . . . . . . . . .AS REQUIRED 10. Cabin Sign . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 11. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . .AS REQUIRED oiutn:
If takeoff was made on a snow or slush covered runway, cycle landing gear one or two times at a safe altitude to shed any ice accumulation. If ECS (OFF) Takeoff Was Made and Above 400 ft AGL: 12. Cabin Pressure Source . . . . . . . . . . . . . BOTH HIGH OR BOTH NORM 13. Vent Blower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 14. Manual Pressure Control . . . . . . . . . . . . . . . . . . . . . .FULL INCREASE oiutn:
Operate manual pressure controller slowly to avoid sudden cabin pressure changes. Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-7 continued from previous page MAXIMUM CONTINUOUS THRUST (N1) ECS ON/Anti-Ice OFF PA/RAT -40 -30 -20 -10 0 10 20 30 40 10,000 103.7 102 100.6 99.2 98 96.8 95.6 94.5 93.5 5000 92 94 95.9 97.7 98 96.8 95.6 94.5 93.5 SL 86.6 88.3 90.1 91.9 93.7 95.4 95.6 94.5 93.5 Engine Anti-Ice ON/ECS ON PA/RAT -40 -30 -20 -10 0 10 20 30 40 10,000 100.8 98.7 97.2 96.1 95.2 94.4 – – – 5000 92 94 95.9 96.1 95.2 94.4 – – – SL 86.6 88.3 90.1 91.9 93.7 94.4 – – – Engine and Wing Anti-Ice ON/ECS ON PA/RAT -40 -30 -20 -10 0 10 20 30 40 10,000 98.8 96.7 95.4 94.2 93.4 92.7 – – – 5000 92 94 95.4 94.2 93.4 92.7 – – – SL 86.6 88.3 90.1 91.9 93.4 92.7 – – – ECS OFF and Anti-Ice OFF PA/RAT -40 -30 -20 -10 0 10 20 30 40 10,000 104 102.6 101.2 99.9 98.6 97.4 96.3 95.2 94.1 5000 92 94 95.9 97.7 98.6 97.4 96.3 95.2 94.1 SL 86.6 88.3 90.1 91.9 93.7 95.4 96.3 95.2 94.1 ANTI-ICE/DEICE SYSTEM (IN-FLIGHT OPERATION)
Caution:
Do not operate anti/deice systems at Ram Air Temperatures greater than 10ºC unless in icing conditions, as indicated by illumination of the ICING annunciator (if installed) or airframe ice accumulation. Ice protection systems should be on prior to encountering icing conditions. Turn systems off when clear of icing conditions. Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-8 continued on next page GENERAL Engine icing conditions are defined as: • llumination of the ICING annunciator • Airframe ice accumulation • At all altitudes and RAT of 10ºC or less in visible moisture (Any obstruction to visibility should be considered visible moisture unless it can be determined to be smoke, dust or ash) • Above 20,000 ft MSL and at RAT of 10ºC or less and any of the following conditions: - Within approximately 5,000 ft. above visible moisture associated with convective activity - Within approximately 10 NM horizontally of visible moisture associated with convective activity - In visible moisture - At any time that the conditions listed above cannot be verified oiutn:
Industry studies indicate that engine icing may be encountered in flight conditions with no indication of airframe icing, especially at high altitude in the vicinity of convective weather activity. There is no lower temperature limit for the operation of anti- ice systems. Do not assume ice formation is not possible at very low ambient temperatures (i.e. -30°C or colder). Airframe icing conditions are defined as: • Illumination of the ICING annunciator • Airframe ice accumulation Engine and Wing Anti-Ice System Operation 1. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90% N1 OR LOWER 2. Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 3. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. AS REQUIRED 4. ENGINE ICE TEMP LO Annunciators . . . . . . . . . . . . . . . ILLUMINATED MOMENTARILY 5. Engine Anti-Ice Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED 6. Ignition Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED Wing Anti-Ice System (If Desired) 1. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90% N1 OR LOWER 2. Wing Anti-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 3. Engine ITTs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK INCREASE 4. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 5. Wing Anti-Ice Light . . . . . . . . . . . . . . . ILLUMINATED, AFTER WINGS HEAT TO TEMPERATURE Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-9 continued from previous page continued on next page Horizontal Stabilizer Deice System Operation 1. H Stab Deice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 2. H Stab Deice Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED CLIMB (FL 180) 1. Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET 2. Cabin Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 3. Cabin Pressure Source . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED oiutn:
The cabin pressure source selector may be kept in the BOTH HIGH position until cabin temperature comfort is achieved, then select BOTH NORM. 4. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 5. Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 6. Recognition Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 7. Anti/Deice Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED oiutn:
Ignition should be turned ON for turbulence and/or precipitation conditions. Flight below column shaker onset speed should be avoided. Intentional operation at speeds approaching the onset of stall buffet may result in engine compressor stalls. CRUISE 1. Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MONITOR FUEL MANAGEMENT PROCEDURES Fuel Crossfeed NORM for takeoff and landing. 1. Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . L TANK OR R TANK AS REQUIRED TO BALANCE FUEL a. Monitor wing and fuselage fuel quantity indicators to verify fuel transfer from fuselage tanks to engine feed tanks. DESCENT 1. Seat Belts/Shoulder Harnesses . . . . . . . . . . . . . . . . . . . . . FASTENED 2. Cabin Sign . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 3. Recognition Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 4. Anti/Deice Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED
Caution:
If icing conditions are anticipated during descent and approach, turn ice protection systems ON as early as possible prior to penetrating icing conditions. Maintain wing anti/deice operation light ON (approximately 70% N2) ring descent to assure proper wing anti-ice operation. 5. Cabin Pressure Control. . . . . . . . . . . SET FIELD ELEVATION +500 FT 6. Windshield Defog . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 7. Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET 8. Refrigeration Air Conditioning below FL 180 . . . . . . . .AS REQUIRED Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-10 continued from previous page APPROACH 1. Crew Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE 2. Fuel Management . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 3. VREF, VAC, N1, AOA, LDG DIST. . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM 4. Cabin Sign . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SAFETY 5. Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOW 6. Hydraulic/Nitrogen Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 7. Engine Sync . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 8. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10º
Caotonn:
During flight in icing conditions, wait at least 15 seconds after selecting 10º flaps before selecting 30º flaps. This delay provides the stabilizer deice system the time required to remove any ice accumulation from the stabilizer leading edge. If icing conditions are encountered for more than 20 min after initial selection of 10º flaps, land using 10º flaps. If a missed approach is executed and the flight is diverted to an alternate airport, the landing must be made using 10º flaps, unless a Ram Air Temperature of 5ºC or greater is observed during APPROACH and BEFORE LANDING. Do not operate anti/deice systems at Ram Air Temperatures greater than 10ºC unless in icing conditions, as indicated by illumination of the ICING annunciator or airframe ice accumulation. APPROACH AND APPROACH CLIMB SPEEDS WEIGHT X 1000 (LBS) FLAPS 16.3 16.1 15.7 15 14 13 12 VREF at 30º 119 118 117 114 110 106 102 VAC at 10º 141 140 139 136 132 128 124 BEFORE LANDING 1. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN 2. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 3. Recognition Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 4. Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. AS REQUIRED 5. Ignition Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 6. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30º 7. Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . NORMAL, BEFORE LANDING 8. Yaw Damp . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF oiutn:
Increase final approach speed to VREF + 5 Kts for autopilot coupled approaches. Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-11 LANDING 1. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 2. Brakes (After touchdown) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY 3. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DEPLOY 4. Reverser Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VERIFY 5. Reverse Thrust. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 6. Speed Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTEND oiutn:
If a go-around becomes necessary after the thrust reversers are deployed, place the reverser levers to the stow position before advancing the thrust levers. BALKED LANDING 1. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAKEOFF N1 2. Climb Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF When positive climb is established : 3. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10º 4. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP 5. Yaw Damp . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 6. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0º 7. Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RET/OFF AFTER LANDING 1. Engine EFCs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED 2. Anti-Collision Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 3. Anti/Deice Systems: a. Wing, Engine and H Stab . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF b. Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF OR LOW oiutn:
In misting conditions on airplanes without windshield wipers, Windshield Anti-Ice on LOW will improve visibility. 4. AOA Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 5. Pitot Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 6. Static Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 7. Ignitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY 8. Radar. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY 9. Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY 10. Speed Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT 11. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0º 12. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF 13. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . .AS REQUIRED Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-12 SHUTDOWN 1. Parking Brake. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED oiutn:
If the engines are not running, the parking brake must be set from the pilot's side only. 2. Standby Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 3. Standby Gyro . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAGE 4. Cabin Pressure Source . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 5. Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 6. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 7. Exterior Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 8. Emergency Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . GUARD UP (OFF) 9. Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 10. Galley Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 11. Radio Masters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 12. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CUTOFF 13. Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 14. Control Lock. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INSTALL Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-13 TURNAROUND Prior to Enplaning or Deplaning: 1. L Thrust Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CUTOFF 2. Cabin Pressure Source . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . R ENG 3. Check Brake Energy and Turnaround Charts SEE PERFORMANCE 4. Left and Right Wing Leading Edges and Upper Surfaces . . . CHECK, FREE OF FROST OR OTHER CONTAMINANTS
Caotonn:
Ice and frost accumulations have been observed on the upper inboard wing root sections after extended flight at high altitude followed by rapid descent and landing in areas of high humidity conditions. During rapid turnarounds, upper wing surfaces should be inspected. If ice or frost is present, it must be removed prior to departure. Restarting L Engine: 5. Radio Masters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 6. Left Engine EFC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF, THEN ON 7. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 8. Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 9. Perform STARTING ENGINE Procedures. Before Taxi: 10. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . .AS REQUIRED 11. Radio Masters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 12. Cabin Pressure Source . . . . . . . . . . . . . BOTH HIGH OR BOTH NORM 13. Engine EFCs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED 14. Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 15. Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF OR LOW oiutn:
In misting conditions on airplanes without windshield wipers, Windshield Anti-Ice on LOW will improve visibility. Taxi: 16. Wheel Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 17. Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 18. Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 19. Fuel Quantity and Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 20. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 21. Flight Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 22. Cabin Pressure Control. . . . . . . . . . . . . . . . . . SET CRUISE ALTITUDE 23. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF 24. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF 25. Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET 26. V1, VR, V2, N1, AOA, Flap Setting . . . . . . . . . . . . . . . . . . . . . .CONFIRM 27. Crew Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE 28. Perform BEFORE TAKEOFF procedures. Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-14 LOCAL TRAINING BEFORE TAKEOFF 1. Anti/Deice Systems (Wing and H Stab) . . . . . . . . . . . . . . . . . . . . . OFF 2. Speed Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT 3. Flight Management System . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 4. Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 5. Fuel Quantity and Balance . . . . . . . . . . . . . . . . . . . . . . . . . . RECHECK 6. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 7. Flight Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK 8. Cabin Pressure Control. . . . . . . . . . . . . . . . . . SET CRUISE ALTITUDE 9. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF 10. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF 11. Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET 12. V1, VR, V2, N1, AOA, Flap Setting . . . . . . . . . . . . . . . . . . . . . .CONFIRM 13. Crew Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE 14. Engine EFC's . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 15. Anti-Collision Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 16. Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 17. Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 18. Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOW 19. AOA Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 20. Pitot Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 21. Static Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 22. Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 23. Annunciators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR 24. Radar. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 25. Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 26. Refrigeration Air Conditioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 27. Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK If ECS OFF takeoff is planned: 28. Cabin Pressure Source . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 29. Rate Control . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 O’CLOCK POSITION 30. Manual Pressure Control . . . . . . . . . . . . . . . . . . . . . FULL DECREASE 31. Vent Blower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-15 EXPANDED NORMALS FUEL SYSTEM 1. FUEL PRESS LO Annunciators . . . . . . . . . . . . . . . . . . . ILLUMINATED 2. Left Fuel/Hydraulic Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE CLOSE LIGHT ILLUMINATES 3. Left Boost Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON, L AND R FUEL PRESS LO ANNUNCIATORS REMAIN ILLUMINATED, L BOOST PUMP LIGHT ILLUMINATES 4. Left Fuel/Hydraulic Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN, OPEN LIGHT ILLUMINATES, L FUEL PRESS LO ANNUNCIATOR EXTINGUISHES, R FUEL PRESS LO ANNUNCIATOR REMAINS ILLUMINATED 5. Left Boost Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO, L AND R FUEL PRESS LO ANNUNCIATORS ILLUMINATE, L BOOST PUMP LIGHT EXTINGUISHES 6. Repeat steps 2 through 5 for right engine. RETURN TO PAGE N-2, FUEL SYSTEM CHECK FUEL CROSSFEED oiutn:
Delay 3-5 seconds between changing fuel crossfeed modes. 1. Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .L TANK 2. Check the following : a. L BOOST PUMP light illuminates. b. R JET PUMP transit light illuminates momentarily. c. XFEED light illuminates momentarily. d. FUEL XFEED light illuminates. 3. FUEL PRESS LO Annunciators. . . . . . . . . . . . . . . . . . .EXTINGUISHED 4. Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 5. Check the following : a. FUEL XFEED light extinguishes. b. XFEED light illuminates momentarily. c. R JET PUMP light illuminates momentarily. d. L BOOST PUMP light extinguishes. 6. FUEL PRESS LO Annunciators. . . . . . . . . . . . . . . . . . . . ILLUMINATED 7. Repeat steps 1 through 6 for right tank RETURN TO PAGE N-2, FUEL CROSSFEED CHECK Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-16 TRIM SYSTEM Pitch Trim: 1. Copilot Depress Trim Arming Button for 5 Seconds. . . . . . . . . . . CHECK FOR NO MOTION AND CHECK AURAL TONE SOUNDS 2. Pilot Repeats Step 1 On Pilot's Side. 3. Copilot Not Depressing Trim Arming Button, Move Trim Switch to NOSE UP for 5 Seconds . . . . . . . . . . . . . CHECK FOR NO MOTION AND CHECK AURAL TONE SOUNDS 4. Pilot Repeats Step 3 On Pilot's Side. 5. Copilot Not Depressing Trim Arming Button, Move Trim Switch to LWD and RWD . . . . . . . . . . CHECK FOR NO MOTION 6. Pilot Repeats Step 5 On Pilot's Side. 7. Copilot Move Trim to NOSE UP and Hold . . . . . . . . . . . . . CHECK NOSE UP MOVEMENT 8. Pilot Move Trim to NOSE DOWN and Hold . . . . . . . . . CHECK NOSE DOWN MOVEMENT a. Copilot Push TRIM INT/AP DISENG Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FOR NO MOTION b. Copilot Release TRIM INT/AP DISENG Switch; then Pilot Select PITCH TRIM EMER . . . . . . . . . . . . . . . . . CHECK FOR NO MOTION 9. EMER PITCH TRIM Switch . . . . . . . . . . . . . . . . . . . . N. DN AND N. UP, CHECK FOR MOTION 10. PITCH TRIM Selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM 11. PITCH TRIM SPEED TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST 12. Pitch Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF Roll Trim: 13. Copilot Move Trim to RWD . . . . . . . . . . . . . . . . .CHECK FOR MOTION a. Pilot Push TRIM INT/AP DISENG Switch . . . . . . . . . . . . . . . . . . . . CHECK FOR NO MOTION 14. Pilot Move Trim to LWD . . . . . . . . . . . . . . . . . . . .CHECK FOR MOTION a. Copilot Push TRIM INT/AP DISENG Switch . . . . . . . . . . . . . . . . . . . . CHECK FOR NO MOTION 15. Pilot Move Trim to RWD, and Copilot Select ROLL and RUD TRIM DISC . . . . . . . . . . . . . CHECK FOR NO MOTION 16. ROLL and RUD TRIM DISC Switch . . . . . . . . . . . . . . . . . . . . . . . .NORM 17. Roll Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET NEUTRAL Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-17 continued on next page Rudder Trim: 18. RUD TRIM Knob Centered . . . . DEPRESS,CHECK FOR NO MOTION 19. Without Depressing, Turn RUD TRIM Knob . . . . . . . . . . . . . . . . . . . . . . . . NOSE L AND R, CHECK FOR NO MOTION 20. Depress and Turn RUD TRIM Knob . . . . . . . . . . NOSE L AND R, CHECK TRIM MOTION 21. Push TRIM INT/AP DISENG Switch When Trim is In-transit . . . . . . . .CHECK INTERRUPTION OF TRIM MOTION 22. Place ROLL and RUD TRIM DISC Switch to DISC While Rudder Trim is In-transit . . . . . . . . . . . . . . . . . . . . . . .CHECK INTERRUPTION OF TRIM MOTION 23. ROLL and RUD TRIM DISC Switch . . . . . . . . . . . . . . . . . . . . . . . .NORM 24. RUD Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET NEUTRAL RETURN TO PAGE N-3, TRIM SYSTEM CHECK SPEED BRAKES 1. Speed Brake Emer Retract . . . . . . . . . . . . . . GUARD UP (EMER RET) 2. Speed Brakes . . . . . . . . . . . . . . . . . . .EXTEND, NOTE NO MOVEMENT 3. Speed Brake Emer Retract . . . . . . . . . . . . . . . GUARD DOWN (NORM) 4. Speed Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTE EXTENSION 5. SPD BRAKE EXT Annunciator . . . . . . . . . . . . . . . . . . . . ILLUMINATED 6. Speed Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT RETURN TO PAGE N-6, SPEED BRAKES CHECK ANTI-SKID 1. Wheel Brakes . . . . . . . . . . . . . . . . . . . . . . . . . APPLY WHILE ROLLING 2. Anti-Skid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST, CHECK FOR BRAKE RELEASE, THEN OFF. RECOVER BRAKE EFFECTIVENESS. CHECK FOR ILLUMINATION OF ANTISKID FAIL ANNUNCIATOR.
Caution:
When turning the anti-skid switch from TEST to ON, pause momentarily in OFF to allow for system cycling. The antiskid test should not be performed in a congested area. 3. Anti-Skid . . . . . . . . . . . . . . . . . . . . . . . . . . .ON,CHECK ANTI-SKID FAIL ANNUNCIATOR EXTINGUISHED AND NORMAL BRAKING. RETURN TO PAGE N-6, ANTI-SKID CHECK Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-18 continued from previous page THRUST REVERSERS oiutn:
Thrust reversers must be checked on the first flight of the day, and on any flight that is predicated on the use of thrust reversers for performance. 1. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DEPLOY 2. Check ARM, UNLOCK, and DEPLOY Annunciators . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED 3. EMER STOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH 4. Check: a. EMER STOW Lights . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED b. UNLOCK and DEPLOY Annunciators. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTINGUISHED 5. EMER STOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH 6. Check: a. EMER STOW Lights . . . . . . . . . . . . . . . . . . . . . . . . .EXTINGUISHED b. ARM, UNLOCK and DEPLOY Annunciators . . . . . . . ILLUMINATED 7. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STOW 8. Check all Thrust Reverser Lights and Annunciators. . . . . . . . . . . . . . . . . . . . . . .EXTINGUISHED oiutn:
It is desirable to perform thrust reverser check into the wind. Do not exceed five seconds with the buckets deployed. RETURN TO PAGE N-6, THRUST REVERSERSCHECK JET PUMPS 1. Jet Pumps. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. Jet Pump Lights . . . . . . . . . . . . . . . . . . ILLUMINATED MOMENTARILY 3. FUEL PRESS LO Annunciators . . . . . ILLUMINATED MOMENTARILY 4. Boost Pump Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED 5. FUEL PRESS LO Annunciators . . . . . . . . . . . . . . . . . .EXTINGUISHED 6. Jet Pumps. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM 7. Jet Pump Lights . . . . . . . . . . . . . . . . . . ILLUMINATED MOMENTARILY 8. Boost Pumps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF, THEN AUTO 9. Boost Pump Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTINGUISHED 10. FUEL PRESS LO Annunciators . . . . . . . . . . . . . . . . . .EXTINGUISHED RETURN TO PAGE N-6, JET PUMPS CHECK Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-19 RUDDER BOOST 1. Rudder Boost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. Verify RUD BST FAIL Annunciator . . . . . . . . . . . . . . . . . ILLUMINATED 3. Rudder Boost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM 4. Verify RUD BST FAIL Annunciator . . . . . . . . . . . . . . . .EXTINGUISHED RETURN TO PAGE N-6, RUDDER BOOST CHECK AUTOPILOT oiutn:
TRIM FAIL annunciations may occur during this preflight test if the autopilot drives the trim to full travel. If this occurs, disengage the autopilot, neutralize the trim and continue the preflight check. 1. Engage the autopilot. Verify that the pilot's PFD displays the following messages: a. ROLL (Green) b. PTCH (Green) c. ALTS (White) d. AP ← (Green) 2. Actuate the center button on the pilot's control wheel trim switch. Verify AP disconnect with YD remaining engaged. Re-engage the autopilot. 3. Depress the pilot's A/P DISENG pushbutton. Verify AP and YD disconnect. Re-engage the autopilot. 4. Actuate the center button on the copilot's control wheel trim switch. Verify AP disconnect with YD remaining engaged. Re-engage the autopilot. 5. Depress the copilot's A/P DISENG push button. Verify AP and YD disconnect. 6. Depress the GO AROUND button. Verify AP disconnect with YD remaining engaged. 7. Reset all trims to the takeoff position.
Caotonn:
During normal preflight checks, it is likely that the pitch and roll trims will be run to their extreme positions. Therefore, all trims must be returned to the proper settings prior to takeoff. 8. Move the primary flight controls through the full range of travel in pitch, roll and yaw axis. Verify proper movement and freedom of travel. RETURN TO PAGE N-6, AUTOPILOT CHECK Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-20 ENGINE EFC SYSTEM Conduct this test procedure on the first flight of the day. 1. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70% N2 2. Engine EFC Test . . . . . . . . . . . . . . . . . . PUSH, CHECK ENG EFC OFF ANNUNCIATORS ILLUMINATE 3. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE 4. Engine EFCs. . . . . . . . . . . . . . .OFF, THEN ON, CHECK ENG EFC OFF ANNUNCIATORS EXTINGUISH oiutn:
When observing the EFC test, differing amounts of N2 rollback may be noted along with variations in the speed at which rollback takes place. At high field elevations, minimal rollback may be observed. These differences are considered normal. RETURN TO PAGE N-6, ENGINE EFC SYSTEM CHECK Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-21 ANTI/DEICE SYSTEM PREFLIGHT CHECK Engine and Wing Anti-ice Systems Check 1. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60-70% N2 2. Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 3. Wing Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 4. Engine ITT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK INCREASE 5. ENG ICE TEMP LO Annunciators . . . . ILLUMINATED MOMENTARILY 6. Engine Anti-Ice Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED 7. Ignition Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED 8. Wing Anti-Ice Light . . . . . . . ILLUMINATED, AFTER WINGS HEAT TO TEMPERATURE 9. Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED 10. Wing Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 11. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE Horizontal Stabilizer Deice System Check 1. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0º 2. H Stab Deice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TEST AND HOLD 3. H STAB ICE FAIL Annunciator . . . . . . . . . . . . . . . . . . .EXTINGUISHED 4. H Stab Deice Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED After Approximately 10 Seconds: 5. H STAB ICE FAIL Annunciator . . . . .ILLUMINATED FOR 3 SECONDS 6. H Stab Deice Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTINGUISHED 7. H STAB ICE FAIL Annunciator . . . . . . . . . . . . . . . . . . .EXTINGUISHED 8. H Stab Deice Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED 9. H Stab Deice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 10. H Stab Deice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TEST AND HOLD 11. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SELECT 30° 12. LDG FLAP DELAY Annunciator . . . . . . . . . . . . . . . . . . . ILLUMINATED 13. Flaps Travel . . . . . . . . . . . . . . FLAPS STOP AT APPROXIMATELY 10° 14. H Stab Deice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 15. LDG FLAP DELAY Annunciator . . . . . . . . . . . . . . . . . .EXTINGUISHED 16. Flap Travel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAPS MOVE TO 30° 17. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF RETURN TO PAGE N-6, ANTI-ICE/DEICE SYSTEM PREFLIGHT CHECK Normal Procedures Beechjet 400A Operating Handbook For Training Purposes Only February 2013 N-22 TAKEOFF DATA FOR SPEEDS AND FIELD LENGTH TABLES 1. Takeoff Field Length values, obtained from the following tables, must be adjusted using the Takeoff Field Length Correction graph if any of the following conditions are true: a. Runway gradient is not zero. b. Headwind/tailwind component is not zero. c. Anti-Skid is OFF. d. Engine Anti-Ice is ON. 2. Combined selection of ECS OFF and engine Anti-Ice ON is not approved. 3. Obtain V1, VR, and V2 from the Takeoff Field Length Tables and adjust V1, using the Takeoff Decision Speed (V1) Correction graph. 4. For takeoff weights below 12,000 lbs, use the 12,000 lbs. takeoff field length and speeds. 5. The fan RPM values are valid only for Engine Anti-Ice OFF/ECS ON conditions. Target fan speeds for any other conditions must be obtained from the Takeoff Thrust Setting chart. 6. Do not interpolate between Fan RPM Values marked by an asterisk (*). Consult the Takeoff Thrust Setting chart for target fan speeds in these regions. ASSOCIATED CONDITIONS: Thrust. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Takeoff Runway . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Paved, Dry Surface Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .0°, 10° or 20° Obstacle Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 ft. SIMPLIFIED TAKEOFF PERFORMANCE (TAB DATA) Many situations will allow the pilot to use a simplified method for determining takeoff performance. Regions of the Takeoff Speeds and Field Length tables have red-colored values. If weight/pressure altitude/ temperature conditions fall within the black-colored values and if all of the following conditions are true: a. Runway gradient is zero b. No tailwind c. ECS is ON d. Engine anti-ice is OFF e. Anti-skid is ON then (1) takeoff climb requirements will be met, and (2) brake energy limitations will not be exceeded. Under these circumstances, there is no need to consult the Maximum Takeoff Weight to Achieve Takeoff Climb Requirements or Maximum Takeoff Weight Limited by Maximum Brake Energy charts. If any of the above conditions are not true, then these charts must be consulted. There are no Brake Energy Limitations for 20° flaps. Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-1 WIND COMPONENTS EXAMPLE: WIND SPEED 10 Kts ANGLE BETWEEN WIND DIRECTION AND FLIGHT PATH 20° HEADWIND COMPONENT 9.4 Kts CROSSWIND COMPONENT 3.4 Kts Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-2 TAKEOFF THRUST SETTING TAKEOFF, APPROACH AND LANDING CLIMB EXAMPLE: 1 RAT 3O° C FIELD PRESSURE ALTITUDE 6,OOO FT ECS OFF ANTI-ICE ENGINE OFF TARGET FAN SPEED 99.0% EXAMPLE: 2 RAT -1O° C FIELD PRESSURE ALTITUDE 2,OOO FT ECS ON ANTI-ICE ENGINE ON TARGET FAN SPEED 95.8% Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-3 MAXIMUM CONTINUOUS THRUST SETTING FINAL SEGMENT AND ENROUTE CLIMB EXAMPLE: 1 RAT 3O° C FIELD PRESSURE ALTITUDE 6,OOO FT ECS OFF ANTI-ICE OFF ECS 95.2% EXAMPLE: 2 RAT -1O° C FIELD PRESSURE ALTITUDE 2,OOO FT ECS ON ANTI-ICE ENGINE + WING ON ECS 94.0% Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-4 MAXIMUM TAKE-OFF WEIGHT - ECS (ON) - FLAPS 0º TO ACHIEVE TAKE-OFF CLIMB REQUIREMENTS ASSOCI ATED CONDITIONS: THRUST . . . . . . . . . .. . . . .. . . . . . . . . . . . . . . . . . TAKE-OFF LANDING GEAR . . . . . . . . . . . . . . . SELECTED UP AT 35 FT EXAMPLE: FIELD PRESSURE ALTITUDE . . . . . . . 6,OOO FT OAT. . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . 3O° C MAXIMUM TAKE-OFF WEIGHT. . . . . .15,636 LBS NOTE: WITH ENGINE ANTI-ICE (ON), SUBTRACT 1,5OO LBS FROM THE WEIGHT READ FROM THIS GRAPH. 10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 19,000 MAXIMUM TAKE-OFF WEIGHT ~ POUNDS 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 FIELD PRESSURE ALTITUDE ~ FEET 4500 5000 5500 6000 6500 7000 7500 8000 8500 MAXIMUM TAKE-OFF WEIGHT ~ KILOGRAMS OUTSIDE AIR TEMPERATURE 20°C 25°C 30°C 35°C 40°C 15°C ISA+35°C STRUCTURAL LIMIT ( 16,300 LBS ) RKAACL009B 45°C 10°C 5°C 0°C -5°C -10°C 10,000 SL F L A P S 0° Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-5 MAXIMUM TAKE-OFF WEIGHT - ECS (OFF) - FLAPS 0º TO ACHIEVE TAKE-OFF CLIMB REQUIREMENTS ASSOCI ATED CONDITIONS: THRUST . . . . . . . . . .. . . . . . . . . . . . . . . TAKE-OFF LANDING GEAR . . . .. . SELECTED UP AT 35 FT ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF EXAMPLE: FIELD PRESSURE ALTITUDE . . . 6,OOO FT OAT. . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . 3O° C MAXIMUM TAKEOFF WEIGHT. . . . . .16,OO2 LBS NOTE: COMBINED SELECTION OF ECS (OFF) AND ANTI-ICE (ON) IS NOT APPROVED. 10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 MAXIMUM TAKE-OFF WEIGHT ~ POUNDS 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 FIELD PRESSURE ALTITUDE ~ FEET 4500 5000 5500 6000 6500 7000 7500 8000 MAXIMUM TAKE-OFF WEIGHT ~ KILOGRAMS OUTSIDE AIR TEMPERATURE 20°C 25°C 30°C 35°C 40°C 15°C ISA+35°C STRUCTURAL LIMIT ( 16,300 LBS ) RKAACL006A 10,000 SL F L A P S 0° Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-6 UP DOWN RUNWAY GRADIENT ~ % 2 1 0 1 0 10 20 30 WIND COMPONENT ~ KTS OFF ON ENGINE ANTI-ICE 13,000 13,500 14,000 14,500 15,000 15,500 16,000 16,500 17,000 17,500 18,000 MAXIMUM TAKE-OFF WEIGHT ~ POUNDS 6000 6500 7000 7500 8000 MAXIMUM TAKE-OFF WEIGHT ~ KILOGRAMS MAXIMUM TAKE-OFF WEIGHT LIMITED BY MAXIMUM BRAKE ENERGY FLAPS 0 O NOTES: 1. ALL ANTI-ICE SYSTEMS EXCEPT ENGINE ANTI-ICE MUST BE OFF DURING TAKEOFF. 2. COMBINED SELECTION OF ECS (OFF) AND ENGINE ANTI-ICE (ON) IS NOT APPROVED. STRUCTURAL LIMIT REFERENCE LINE REFERENCE LINE REFERENCE LINE RKAATO004D -40 -30 -20 -10 0 10 20 30 40 50 OUTSIDE AIR TEMPERATURE ~ o C FIELD PRESSURE ALTITUDE ~ FEET 10,000 8000 6000 4000 2000 SL ISA TAILWIND HEADWIND ASSOCIATED CONDITIONS: ECS ......... (ON) OR (OFF) ANTI-SKID ... (ON) OR (OFF) EXAMPLE: OAT ....................... 15 o C FIELD PRESSURE ALTITUDE ... 9OOO FT RUNWAY GRADIENT ........... 1% DN HEADWIND COMPONENT ........ 1O KTS ENGINE ANTI - I CE . . . . . . . . . . . OFF MAXIMUM TAKE-OFF WEIGHT:... 14,676 LBS F L A P S 0° Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-7 UP DOWN RUNWAY GRADIENT ~ % 90 95 100 105 110 115 120 125 130 UNCORRECTED TAKE-OFF DECISION SPEED (V 1) ~ KIAS 1 0 1 2 90 95 100 105 110 115 120 125 CORRECTED TAKE-OFF DECISION SPEED (V 1) ~ KIAS ANTI-SKID (OFF) 90 95 100 105 110 115 120 125 130 CORRECTED TAKE-OFF DECISION SPEED (V 1) ~ KIAS ANTI-SKID (ON) TAKE-OFF DECISION SPEED (V 1) CORRECTION - FLAPS 0 o REFERENCE LINE REFERENCE LINE RKAATO007C OFF ON ENGINE ANTI-ICE NOTES: 1. OBTAIN THE UNCORRECTED DECISION SPEED (V 1 ) FROM THE "TAKE-OFF SPEEDS AND FIELD LENGTH - FLAPS O o " TABLES. ENTER THE GRAPH BELOW WITH THAT VALUE, AND DETERMINE THE DECISION SPEED (V 1 ) CORRECTED FOR RUNWAY GRADIENT, ENGINE ANTI-ICE, AND ANTI-SKID. 2. THE EFFECTS OF ECS (OFF) AND WINDS ON V 1 ARE BOTH NEGLIGIBLE. 3. IF THE CORRECTED V 1 IS GREATER THAN V R , THE VALUE OF VR MUST BE USED FOR V 1 . EXAMPLE: UNCORRECTED TAKE-OFF DECISION SPEED, V 1 .... 114 KIAS RUNWAY GRADIENT............................ 1.O% DN ENGINE ANTI-ICE............................ ON CORRECTED TAKE-OFF DECISION SPEED, V 1 : ANTI-SKID (ON)........................... 114.1 KIAS ANTI-SKID (OFF).......................... 1O1.6 KIAS F L A P S 0° Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-8 UP DOWN RUNWAY GRADIENT ~ % UNCORRECTED TAKE-OFF FIELD LENGTH ~ FEET 2 1 0 1 2000 3000 4000 5000 6000 7000 8000 9000 10,000 11,000 12,000 13,000 14,000 15,000 0 10 20 30 WIND COMPONENT ~ KNOTS OFF ON ENGINE ANTI-ICE ON OFF ANTI-SKID TAKE-OFF FIELD LENGTH ~ FEET 500 1000 1500 2000 2500 3000 3500 4000 4500 TAKE-OFF FIELD LENGTH ~ METERS 2000 3000 4000 5000 6000 7000 8000 9000 10,000 11,000 12,000 13,000 14,000 15,000 TAKE-OFF FIELD LENGTH CORRECTION - FLAPS 0 o TAILWIND HEADWIND REFERENCE LINE REFERENCE LINE REFERENCE LINE REFERENCE LINE RKAATO010B EXAMPL E: UNCORRECTED TAKE-OFF FIELD LENGTH....4141 FT RUNWAY GRADIENT......................1.O% DN HEADWIND COMPONENT...................1O KTS ENGI NE ANTI - I CE . . . . . . . . . . . . . . . . . . . . . . OF F TAKE-OFF FIELD LENGTH: ANTI-SKID (ON).............3848 FT ANTI-SKID (OFF)............6O61 FT ASSOCIATED CONDITIONS: THRUST............TAKE-OFF RUNWAY............PAVED, DRY SURFACE OBSTACLE HEIGHT...35 FT ECS...............(ON) OR (OFF) NOTES: 1. OBTAIN V1, VR, AND V2 FROM THE "TAKE-OFF SPEEDS AND FIELD LENGTH" TABLE AND "TAKE-OFF DECISION SPEED (V1) CORRECTION" GRAPH. 2. FOR RUNWAY GRADIENTS GREATER THAN 1% UP, USE DIFFERENT TAKE-OFF FLAP SETTING. F L A P S 0° Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-9 RK00D 080825AA.AI F L A P S 0° Flight Planning Beechjet 400A Operating Handbook For Training Purposes Only March 2013 F-10