B407_PCL_2_1

BELL 407

Revision 2.1—August 2013

ABBREVIATED PILOT CHECKL IST

Copyright © 2013, FlightSafety International, Inc. Unauthorized reproduction or distribution is prohibited. All rights reserved.

INSERT LATEST REVISED PAGE. DESTROY SUPERSEDED PAGES. LIST OF EFFECTIVE PAGES Dates of issue for srcinal and changed pages are:

Revision........0 .............MAY 2010 Revision........1 .............November 2010 Revision........1.1 ..........December 2010 Revision........2.0 ..........December 2011 Revision........2.1 ..........August 2013 NOTE For printing purposes, revision numbers in footers occur at the bottom of every page that has changed in any way (grammatical or typographical revisions, reflow of pages, and other changes that do not necessarily affect the meaning of the manual). TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 60, CONSISTING OF THE FOLLOWING: Page No.

*Revision No.

Page No.

*Revision No.

Title ....................................2.1

M-i – M-ii ...........................2.0

iiN-i......................................2.1 .........................................2.1 N-ii .....................................2.0 N-1.....................................2.1 N-2 – N-10.........................2.0 E-1 – E-16..........................2.0 ANN-i – ANN-ii ..................2.0 ANN-1 – ANN-8 .................2.0

M-1 M-2..........................2.0 P-i – –P-ii.............................2.0 P-1 – P-2 ...........................2.0 P-3 – P-6 ...........................2.1 P-7– P-9 ............................2.0 P-10 ...................................2.1 P11 – P-14.........................2.0

*Zero in this column indicates an srcinal page. These are suggested procedures only and in no way supersede current procedures outlined in the FAA-approved Flight Manual and any revisions thereto. In the case of conflict, the Flight Manual takes precedence.

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NORMAL PROCEDURES INTERIOR AND PRESTART CHECK......................................................N-1 ENGINE START ......................................................................................N-3 DRY MOTORING RUN ...........................................................................N-4 PRELIMINARY HYDRAULIC SYSTEMS CHECK ...................................N-5 ENGINE RUNUP.....................................................................................N-5 HYDRAULIC SYSTEMS CHECK............................................................N-6 BEFORE TAKEOFF ................................................................................N-6 TAKEOFF................................................................................................N-7 IN-FLIGHT OPERATIONS ......................................................................N-8 DESCENT AND LANDING......................................................................N-8 ENGINE SHUTDOWN ............................................................................N-9 POSTFLIGHT CHECK ..........................................................................N-10

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FOR TRAINING PURPOSES ONLY

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BELL 407 ABBREVIATED PILOT CHECKLIST

NOTES

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INTERIOR AND PRESTART CHECK 1. Cabin Interior .................................CLEAN, EQUIPMENT SECURED 2. Fire Extinguisher ...................................INSTALLED AND SECURED 3. Cabin Loading ...................................MAINTAIN CG WITHIN LIMITS 4. Passenger Seat Belts ........................................................SECURED 5. Copilot Seat Belt....... ........................................SECURED (IF SOLO) 6. Doors .................................................................................SECURED 7. EMERGENCY PEDAL STOP ............DOWN AND WITNESS WIRED 8. Throttle .................................................................................CLOSED 9. LDG LTS Switch ..........................................................................OFF 10. Communications Switches ..........................................................SET 11. Altimeter .......................................................................................SET 12. Instruments ................................................CORRECT INDICATIONS 13. Overhead Switches......................................................................SET 14. Overhead Circuit Breaker Switches ............................................OFF 15. Overhead Circuit Breakers..............................................................IN 16. Rotor Brake Handle (if installed)..........................UP AND LATCHED 17. GPU .............................................................CONNECTED (IF USED) 18. BATT Switch—ON for battery start, ON for GPU start, OFF for battery cart start. Observe the following: a. Low rotor audio horn activated. b. For 8 seconds, 1) Trend arcs on LCD instruments indicate full scale. 2) TORQUE and N G digits display 8188.8. 3) MGT and FUEL digits display 81888. 4) NR and NP needles move to 107% and 100% respectively.

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INTERIOR AND PRESTART CHECK (Cont) c. After 3 seconds; ENG OUT, FADEC DEGRADE, FADEC FAULT, RESTART FAULT, and ENGINE OVSPD lights illuminate with activation of engine out audio for 3 seconds. d. ENG OUT light re-illuminates with reactivation of engine out audio, after 3 seconds. 19. HORN MUTE Button..............................................PRESS TO MUTE 20. Caution Lights—ENG OUT, XMSN OIL PRESS, RPM, HYDRAULIC SYSTEM, GEN FAIL, L/FUEL BOOST, R/FUEL BOOST, L/FUEL XFR, and R/FUEL XFR will be illuminated. 21. PEDAL STOP PTT Switch Annunciator ..............................……TEST 22. Flight Controls—Loosen frictions; check travel and verify CYCLIC CENTERING light operation; position for start. Tighten friction as desired. 23. Throttle—Check freedom of travel and appropriate operation at OFF, I (idle), FLY and MAX positions. Return throttle to OFF position. 24. INSTR LT Rheostat........................................................AS DESIRED 25. CAUT LT Switch ............................................................AS DESIRED 26. FUEL BOOST/XFR Circuit Breaker Switches—LEFT (on) and RIGHT (on) and verify all boost and transfer caution lights extinguish. 27. FUEL Pressure .......................................................................CHECK 28. CAUTION LT TEST Button......................................PRESS TO TEST 29. INSTR CHK Button ...........................................PRESS AND CHECK FOR EXCEEDANCES 30. LCD TEST Button ..............................PRESS TO TEST, IF DESIRED 31. FADEC HORN TEST Button....................................PRESS TO TEST 32. FADEC MODE Switch...............................................................AUTO 33. FUEL VALVE Switch—ON, guard closed, FUEL VALVE light illuminates then extinguishes. 34. FUEL QTY ...................CHECK TOTAL AND FWD TANK QUANTITY 35. OAT/VOLTS Display..............…..CHECK OAT AND SELECT VOLTS Revision 2.0

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ENGINE START 1. Collective .......................................................................FULL DOWN 2. Cyclic and Pedals .....................................CENTERED AND CYCLIC CENTERING LIGHT EXTINGUISHED 3. Throttle ......................................................................IDLE POSITION 4. START Switch—Momentarily for approximately 1 second) and observe START andpress AUTO(hold RELIGHT lights are illuminated. 5. MGT ...................................................................................MONITOR 6. START Light .........................................EXTINGUISHED AT 50% NG (STARTER HAS DISENGAGED) 7. AUTO RELIGHT Light ...........................EXTINGUISHED AT 60% NG 8. ENG and XMSN OIL Pressur es..............................................CHECK 9. Idle...............................................................................63% ± 1% N G 10. BATT Switch .....................................................ON (IF APPLICABLE)

NOTE Ensure BATT switch is positioned to ON prior to disconnecting external power source. 11. EXTERNAL POWER.........………DISCONNECT AND CLOSE DOOR (IF APPLICABLE) 12. GEN Switch......................................................GEN (ON); OBSERVE GEN FAIL LIGHT EXTINGUISHES 13. Voltmeter................................................................28.5 ± 0.5 VOLTS 14. FLIGHT INSTR Circuit Breaker Switches (3) (if installed)............................DG, ATT AND TURN (ON)

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DRY MOTORING RUN 1. Throttle ...............................................................CLOSED POSITION 2. START Switch ................................................HOLD ENGAGED FOR 15 SECONDS, THEN RELEASE Follow ENGINE START procedure, once 0% NG is indicated.

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SYSTEMS CHECKS PRELIMINARY HYDRAULIC SYSTEMS CHECK 1. HYD SYS Switch .........................................................................OFF 2. HYDRAULIC SYSTEM Caution Light ..........................ILLUMINATED 3. HYD SYS Switch ........................................................HYD SYS (ON) 4. HYDRAULIC SYSTEM Caution Light .......................EXTINGUISHED

ENGINE RUNUP 1. Throttle—Increase smoothly to FLY detent position while maintaining torque below 40%. Check RPM warning light extinguished at 95% NR. 2. NR and NP Needles............................................CHECK MATCHING AND INDICATING 100% 3. AVIONICS MASTER Switch .......................AVIONICS MASTER (ON) 4. ELT (if installed)—Check for inadvertent transmission. 5. Flight Controls—Check freedom with minimum friction. 6. ENG ANTI ICE Switch—ENG ANTI ICE (on); check for MGT increase and illumination of ENGINE ANTI-ICE light (if installed). 7. ENG ANTI ICE Switch—OFF; check MGT returns to normal and ENGINE ANTI-ICE light (if installed) extinguishes; then ENG ANTI ICE (on) if required. 8. PITOT HEATER—Confirm operation (increase in ammeter load). 9. PART SEP Switch (if installed) ...................................AS REQUIRED

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HYDRAULIC SYSTEMS CHECK 1. Collective .......................................................................FULL DOWN 2. NR .....................................................................................100% RPM 3. HYD SYS Switch .........................................................................OFF 4. HYDRAULIC SYSTEM Caution Light ..........................ILLUMINATED 5. Cyclic ...............................................................................CENTERED 6. Cyclic Control—Check normal operation by moving cyclic forward and aft, then left and right (approximately 1 inch). Center cyclic. 7. Collective—Check normal operation by increasing collective slightly (1 to 2 inches). Repeat two to three times as required. Return to full down position. 8. Pedals—Check normal operation by displacing pedals slightly (1 inch). 9. HYD SYS Switch ........................................................HYD SYS (ON) 10. HYDRAULIC SYSTEM Caution Light .......................EXTINGUISHED 11. Cyclic and Collective Friction ................................SET AS DESIRED

BEFORE TAKEOFF 1. ENG ANTI ICE Switch. ................................................AS REQUIRED 2. PITOT HEAT................................................................AS REQUIRED 3. Light Switches ............................................................AS REQUIRED 4. INSTR LT Rheostat........................................................AS DESIRED 5. Radio(s) .........................................................CHECK AS REQUIRED 6. Flight Controls ............................................POSITION AND ADJUST FRICTIONS FOR TAKEOFF

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7. Throttle—Open to FLY detent position. Check 99 to 100% N R/NP. 8. Engine, Transmission, and Electrical Instruments ................................................WITHIN LIMITS 9. Flight and Navigation Instruments .........................................CHECK 10. FUEL QTY ............................................................NOTE INDICATION 11. FUEL QTY FWD TANK Button—Press, note fuel remaining in forward cell.

TAKEOFF 1. Rear Facing Seat Headrests ......................................ADJUSTED TO PROPER POSITION 2. Collective .......................................................INCREASE TO HOVER 3. Directional Control..............................AS REQUIRED TO MAINTAIN DESIRED HEADING 4. Cyclic........................................................APPLY AS REQUIRED TO ACCELERATE SMOOTHLY 5. Increase collective, up to 5% torque above hover power, to obtain desired rate of climb and airspeed. Once clear of the HV diagram shaded areas, adjust power and airspeed as desired. 6. PEDAL STOP PTT Switch ........CHECK ENGAGED ANNUNCIATOR ILLUMINATED ABOVE 55 ± 5 KIAS

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IN-FLIGHT OPERATIONS 1. Airspeed.........................................................................AS DESIRED (NOT TO EXCEED VNE AT FLIGHT ALTITUDE) 2. PEDAL STOP PTT Switch ........CHECK ENGAGED ANNUNCIATOR ILLUMINATED ABOVE 55 ± 5 KIAS 3. ENG ANTI ICE and PITOT HEATER Switches—ENG ANTI ICE and PITOT HEATER switches on in visible moisture when ambient temperature is at or below 5°C (40°F). 4. PITOT HEATER.............................................CONFIRM OPERATION (INCREASE AMMETER LOAD) 5. Altimeter.....................................................................WITHIN LIMITS 6. FUEL QTY FWD TANK Button—Press, note forward fuel tank indication.

DESCENT AND LANDING 1. Rear Facing Seat Headrests ......................................ADJUSTED TO PROPER POSITION 2. Flight Controls ...............................ADJUST FRICTION AS DESIRED 3. Throttle.........................................................FLY DETENT POSITION CHECK 99 TO 100% NP 4. Flight Path .....................AS REQUIRED FOR TYPE OF APPROACH 5. ENG ANTI ICE.............................................................AS REQUIRED 6. LDG LTS Switch ............................................................AS DESIRED 7. PEDAL STOP PTT Switch—Check ENGAGED annunciator extinguished below 50 ± 5 KIAS.

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ENGINE SHUTDOWN 1. Collective .......................................................................FULL DOWN 2. Cyclic and Pedals—Centered and CYCLIC CENTERING light extinguished. 3. Cyclic Friction—Increase so that cyclic maintains centered position. 4. LDG LTS Switch ..........................................................................OFF 5. Throttle—Reduce to idle stop. Check RPM warning light illuminated and audio on at 95% NR. 6. HORN MUTE Button..............................................PRESS TO MUTE 7. MGT........................................STABILIZE AT IDLE FOR 2 MINUTES 8. ENG ANTI ICE Switch..................................................................OFF 9. FLIGHT INSTR Circuit Breakers Switches (if installed) ...............OFF 10. FUEL BOOST/XFR LEFT Circuit Breaker Switch ........................OFF 11. ELT (if installed)—Check for inadvertent transmission. 12. AVIONICS MASTER Switch.........................................................OFF 13. GEN Switch .................................................................................OFF 14. OVSPD TEST Button .....................................IF REQUIRED; PRESS, HOLD 1 SECOND, AND RELEASE 15. IDLE REL Switch .................................................PRESS AND HOLD 16. Throttle—Closed; check MGT and N G decreasing, ENGINE OUT warning light illuminated and audio on at 55 ±1%. 17. HORN MUTE Button......... .....................................PRESS TO MUTE 18. Rotor Brake (if installed)—Apply full rotor brake at or below 40% NR. Return rotor brake handle to stowed position just prior to main rotor stopping. 19. FUEL VALVE Switch ....................................................................OFF 20. Pilot—Remain on flight controls until rotor has come to a complete stop. 21. ANTI COLL LT Switch ...................................................AS DESIRED 22. All Overhead Switches, Except HYD SYS Switch.......................OFF 23. BATT Switch...................................................OFF, WITH N G AT 0% Revision 2.0


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POSTFLIGHT CHECK If any of following conditions exist: •

Thunderstorms are in local area or forecasted.

•

Winds in excess of 35 knots or a gust spread of 15 knots exists or is forecasted.

•

Helicopter is parked within 150 feet or taxiing aircraft that are in excess of basic GWof ofhovering helicopter.

•

Helicopter to be left unattended.

Perform following: 1. Install main rotor blade tiedowns. 2. Secure tail rotor loosely to tailboom with tie down strap to prevent excessive flapping. 3. Install exhaust cover, engine inlet protective plugs and pitot cover.

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EMERGENCY PROCEDURES ENGINE FAILURE—HOVERING ENGINE FAILURE—IN-FLIGHT

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ENGINE RESTART IN FLIGHT—AUTOMATIC MODE ENGINE RESTART IN-FLIGHT—MANUAL MODE ENGINE UNDERSPEED

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ENGINE OVERSPEED ENGINE COMPRESSOR STALL ENGINE HOT START/SHUTDOWN ENGINE OIL PRESSURE LOW, HIGH, OR FLUCTUATING

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ENGINE OIL TEMPERATURE HIGH DRIVESHAFT FAILURE FADEC FAILURE ENGINE FIRE ON GROUND

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ENGINE FIRE DURING FLIGHT CABIN SMOKE OR FUMES ELECTRICAL FIRE COMPLETE LOSS OF TAIL ROTOR THRUST—HOVERING

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COMPLETE LOSS OF TAIL ROTOR THRUST—IN-FLIGHT FIXED PITCH FAILURES LOSS OF HYDRAULIC PRESSURE FLIGHT CONTROL ACTUATOR MALFUNCTION

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GENERATOR FAILURE EXCESSIVE ELECTRICAL LOAD DUAL FUEL TRANSFER FAILURE

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CYCLIC CAM JAM

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EMERGENCY/MALFUNCTION PROCEDURES

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ENGINE FAILURE—HOVERING 1. Maintain heading and attitude control. 2. Collective—Adjust to control N R and rate of descent. Increase prior to ground contact to cushion landing. 3. Complete helicopter shutdown.

ENGINE FAILURE—IN-FLIGHT 1. Maintain .................................HEADING AND ATTITUDE CONTROL 2. Collective—Adjust as required to maintain 85 to 107% N R. 3. Cyclic—Adjust to obtain desired autorotative AIRSPEED. 4. Attempt—Engine restart if ample altitude permits. 5. FUEL VALVE Switch ....................................................................OFF 6. At low altitude: a. Throttle ...........................................................................CLOSED b. Flare to lose airspeed. 7. Apply collective in flare. Upon ground contact, collective shall be reduced smoothly while maintaining cyclic in neutral or centered position. 8. Complete helicopter shutdown.

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ENGINE RESTART IN FLIGHT—AUTOMATIC MODE 1. Collective—Adjust to maintain 85 to 107% N R. 2. AIRSPEED.......................................................ADJUST AS DESIRED 3. FUEL VALVE Switch......................................................................ON 4. Throttle .................................................................................CUTOFF 5. START Switch.......................................HOLD TO START POSITION (START WILL LATCH AFTER THROTTLE IS PLACED TO IDLE) 6. NG ............................................................BETWEEN 12% AND 50% 7. Throttle ........................................................................................IDLE 8. MGT ...................................................................................MONITOR 9. Engine Oil Pressure................................................................CHECK 10. Throttle............ADVANCE SMOOTHLY TO FLY DETENT POSITION 11. If Unsuccessful .................................................THROTTLE CLOSED 12. FUEL VALVE Switch ....................................................................OFF 13. Accomplish autorotative descent and landing.

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ENGINE RESTART IN-FLIGHT—MANUAL MODE 1. Collective—Adjust to maintain 85 to 107% N R. 2. Airspeed..........................................................ADJUST AS DESIRED 3. Throttle .................................................................................CLOSED 4. FADEC MODE Switch ................................................................MAN 5. FUEL VALVE Switch......................................................................ON

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6. START Switch.......................................HOLD TO START POSITION (STARTER WILL NOT LATCH) 7. NG ...............................................................................................12% 8. Throttle—Slowly advance out of cutoff and stop advancing throttle at light off. 9. MGT .......................................................................ALLOW TO PEAK 10. Throttle—Increase fuel flow by modulating throttle to maintain MGT within limits. 11. START Switch.................................................RELEASE AT 50% N G 12. Engine Oil Pressure................................................................CHECK 14. Throttle—Advance smoothly and modulate to 100% N P. 15. Throttle (if unsuccessful) ......................................................CLOSED 16. FUEL VALVE Switch ....................................................................OFF 17. Accomplish autorotative descent and landing.

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ENGINE UNDERSPEED 1. Collective—Adjust to maintain 85 to 107% N R. 2. Throttle ..................................CONFIRM IN FLY DETENT POSITION 3. Throttle—Position throttle to the approximate bezel position that coincides with the gauge indicated N G. 4. FADEC MODE Switch ................................................................MAN 5. NR—Maintain 95 to 100% with Throttle and collective. 6. Land as soon as practical.

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ENGINE OVERSPEED 1. Throttle .................................................................................RETARD 2. NG or NP—Attempt to stabilize with throttle and collective. 3. FADEC MODE Switch ................................................................MAN 4. NR—Maintain 95 to 100% with throttle and collective.

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ENGINE COMPRESSOR STALL 1. Collective—Reduce power, maintain slow cruise flight. 2. MGT and N G ..........................CHECK FOR NORMAL INDICATIONS 3. ENG ANTI ICE Switch ...................................................................ON 4. PART SEP Switch (if installed) ......................................................ON 5. HEATER Switch (if installed) .........................................................ON If pilot elects to continue flight: 6. Collective—Increase slowly to achieve desired power level.

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7. MGT and N G .........................MONITOR FOR NORMAL RESPONSE 8. Land as soon as practical. If pilot elects to shut down engine: 9. Enter autorotation. 10. Throttle .................................................................................CLOSED 11. FUEL VALVE Switch ....................................................................OFF 12. Collective—Adjust as required to maintain 85 to 107% N R. 13. Cyclic—Adjust as required to maintain desired AIRSPEED. 14. Prepare for power-off landing.

ENGINE HOT START/SHUTDOWN 1. Throttle .................................................................................CLOSED 2. FUEL VALVE Switch ....................................................................OFF 3. STARTER Switch—Ensure starter is motoring engine until MGT stabilizes at normal temperature. 4. Shut down helicopter.

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ENGINE OIL PRESSURE LOW, HIGH, OR FLUCTUATING 1. Engine oil pressure below minimum. a. Monitor engine oil pressure and temperature. b. Land as soon as possible. 2. Engine oil pressure above maximum or fluctuating abnormally. a. Monitor engine oil pressure and temperature. b. Land as soon as practical.

ENGINE OIL TEMPERATURE HIGH 3 1. Land as soon as practical.

DRIVESHAFT FAILURE NOTE Engine overspeed trip system will activate at 118.5% NP causing fuel flow to go to minimum. After initial overspeed, FADEC will adjust fuel flow to maintain engine at 100% NP. 1. Maintain heading and attitude control. 2. Collective—Adjust as required to maintain 85 to 107% N R. 3. Cyclic—Adjust to obtain desired autorotative airspeed. 4. Landing—Complete autorotative landing. 5. Complete helicopter shutdown.

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FADEC FAILURE 1. Throttle—If time permits, match throttle bezel position to N G indication. 2. NR/NP—Maintain 95 to 100% with collective and throttle. 3. FADEC MODE Switch—Depress one time, muting FADEC fail audio. 4. Land as soon as practical. 5. Normal shutdown if possible.

ENGINE FIRE ON GROUND 4

1. Throttle .................................................................................CLOSED 2. FUEL VALVE Switch ....................................................................OFF 3. GEN Switch .................................................................................OFF 4. BATT Switch ................................................................................OFF 5. Rotor Brake (if installed) ......................................................ENGAGE 6. Exit helicopter.

ENGINE FIRE DURING FLIGHT 1. In-flight ..............................IMMEDIATELY ENTER AUTOROTATION 2. Throttle .................................................................................CLOSED 3. FUEL VALVE Switch ....................................................................OFF 4. If Time Permits ....................................................FUEL, BOOST/XFR CIRCUIT BREAKER SWITCHES OFF 5. Execute autorotative descent and landing. 6. BATT Switch ................................................................................OFF

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CABIN SMOKE OR FUMES In-flight ............................................................................START DESCENT 1. AIR COND BLO Switch (if installed) ............................................OFF 2. HEATER Switch (if installed ) ........................................................OFF 3. All Vents........... .........................................................................OPEN 4. Side Windows...........................................................................OPEN If time and altitude permits: 5. Source .................................ATTEMPT TO IDENTIFY AND SECURE 6. If Source Identified, Smoke Persists................................LAND AS SOON AS POSSIBLE 7. If Source Identified, Smoke Clears................................LAND AS SOON AS PRACTICAL

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ELECTRICAL FIRE 1. Vents/Side Windows .....................................OPEN, AS REQUIRED; VENTILATE CABIN 2. Begin descent.

NOTE Maintain possible. safe flight condition and land as soon as If source of smoke or fire can be positively identified, remove electrical power from the affected equipment by switching it off via switch or circuit breaker. If source of the smoke or fire cannot be positively identified: 3. GEN Switch .................................................................................OFF 4. Land as soon as practical.

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If smoke/fumes do not decrease: 5. Airspeed ............................................................60 KNOTS OR LESS 6. BATT Switch ................................................................................OFF 7. FUEL BOOST/XFR LEFT Circuit Breaker Switch ..............LEFT (ON) If smoke/fumes do not decrease: 8. Land as soon as possible. WARNING

PRIOR TO BATTERY DEPLETION, ALTITUDE MUST BE REDUCED BELOW 8000 FEET HP (JET B). UNUSABLE FUEL MAY BE AS HIGH AS 151.0 POUNDS AFTER THE BATTERY IS DEPLETED DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELLS.



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NOTE With battery and generator OFF, an 80% charged battery will operate left fuel boost pump and left fuel transfer pump for approximately 1.7 hours (2.8 hours with optional 28 amp-hour battery).

NOTE Pedal stop disengage with loss of electrical power. When throttle is repositioned to the idle stop (during engine shutdown), the PMA will go offline and the engine may flame out.

COMPLETE LOSS OF TAIL ROTOR THRUST— HOVERING 1. Close throttle and perform a hovering autorotation landing. A slight rotation can be expected on touchdown.

COMPLETE LOSS OF TAIL ROTOR THRUST— IN-FLIGHT 1. Reduce throttle to idle, immediately enter autorotation and maintain a minimum AIRSPEED of 55 KIAS during descent. Ensure there is no power to the main rotor during the flare.

NOTE When a suitable landing site is not available, vertical fin may permit controlled flight at low power levels and sufficient AIRSPEED. During final stages of approach, a mild flare should be executed, making sure all power to rotor is off. Maintain helicopter in a slight flare and smoothly use collective to execute a soft, slightly nosehigh landing. Landing on aft portion of skids will tend to correct side drift. This technique will, in most cases, result in a run-on type landing. Revision 2.0


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FIXED PITCH FAILURES Hovering 1. Do not close throttle unless a severe right yaw occurs. If pedals lock in any position at a hover, landing from a hover can be accomplished with greater safety under power-controlled flight rather than by closing throttle and entering autorotation.

In-Flight—Left Pedal Applied 1. In a high power condition, helicopter will yaw to left when power is reduced. Power and AIRSPEED should be adjusted to a value where a comfortable yaw angle can be maintained. If AIRSPEED is increased, vertical fin will become more effective and an increased left yaw attitude will develop. To accomplish landing, establish a power-on approach with sufficiently low AIRSPEED to attain a rate of descent with a comfortable sideslip angle. (A decrease in NP decreases tail rotor thrust.) As collective is increased just before touchdown, left yaw will be reduced.

In-Flight—Right Pedal Applied 1. In cruise flight or reduced power situation, helicopter will yaw to right when power is increased. A low power, run-on type landing will be necessary by gradually reducing throttle to maintain heading while adding collective to cushion landing. If right yaw becomes excessive, close throttle completely.

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LOSS OF HYDRAULIC PRESSURE 1. Reduce AIRSPEED ...................................................70 TO 100 KIAS 2. HYD SYSTEM Circuit Breaker ....................................................OUT (IF POWER NOT RESTORED, PUSH BREAKER IN) 3. HYD SYS Switch ..............................HYD SYS; OFF IF HYDRAULIC POWER IS NOT RESTORED 4. For extended flight set comfortable AIRSPEED, up to 120 KIAS. 5. Land as soon as practical. 6. A run-on landing at effective translational lift speed, approximately 15 knots is recommended.

FLIGHT CONTROL ACTUATOR MALFUNCTION 1. Attitude ..............................................................................MAINTAIN 2. HYD SYS Switch .........................................................................OFF 3. AIRSPEED...................................................SET TO 70 TO 100 KIAS 4. Land as soon as possible using procedure from LOSS OF HYDRAULIC PRESSURE.

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GENERATOR FAILURE 1. GEN FIELD and GEN RESET Circuit Breakers .................CHECK IN 2. GEN Switch.........................................................RESET; THEN GEN 3. If power not restored, place GEN Switch to OFF; land as soon as practical.

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EXCESSIVE ELECTRICAL LOAD 1. GEN Switch .................................................................................OFF 2. BATT Switch ................................................................................OFF 3. FUEL BOOST/XFR LEFT Circuit Breaker Switch ..............LEFT (ON) 4. Airspeed ................................................................60 KIAS OR LESS 5. Land as soon as practical.

DUAL FUEL TRANSFER FAILURE 1. LEFT and RIGHT FUEL BOOST/XFR Circuit Breaker Switches .................................................CHECK ON 2. Determine FUEL QTY in forward cell. 3. Subtract quantity of fuel trapped in forward cell from total to determine usable fuel remaining. 4. Plan landing accordingly.

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CYCLIC CAM JAM 1. Helicopter Pitch Attitude—Maintain normal pitch attitudes with forward or aft cyclic force.

CAUTION DO NOT TURN HYDRAULIC BOOST OFF. 2. Land as soon as practical.

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NOTES

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ANNUNCIATOR LIGHTS WARNING (RED) LIGHTS..................................................................ANN-1 CAUTION (AMBER) AND ADVISORY (WHITE/GREEN) LIGHTS ......ANN-2

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WARNING (RED) LIGHTS PANEL LIGHTS

FAULT CONDITION

CORRECTIVE ACTION

Battery overheating.

Turn BATT switch OFF and land as soon as practical. If BATTERY RLY light illuminates, turn GEN switch OFF if conditions permit. Land as soon as possible.

ENGINE OUT

NG less than 55 ± 1% a nd/or FADEC senses

Verify engine condition. Accomplish engine failure procedure.

ENGINE OVSPD

NP is greater than 102.1% for 2.5 seconds or 107.3% immediately.

Adjust throttle and collective as necessary. Determine if engine is controllable; if not shut down. Maintenance action required before next flight.

NG is greater than 110% or N P versus TORQUE is above maximum continuous limit (102.1% NP at 100% TORQUE to 108.6% NP at 0% TORQUE).

Adjust throttle and collective as necessary. Determine if engine is controllable; if not shut down. Maintenance action required before next flight.

FADEC has detected a

Close throttle immediately.

serious malfunction.

Engage starter to reduce MGT. Applicable maintenance action required prior to next flight.

FADEC has detected a serious malfunction. Dependent on flight profile (takeoff, climb, cruise, or descent) and power setting at time of failure, the transition to manual mode may result in an NR/NP overspeed or underspeed within 2 to 7 seconds following activation of FADEC fail horn and illumination of FADEC FAIL warning light. Any other FADEC related lights may be illuminated.

Accomplish FADEC FAILURE procedure. Applicable maintenance action required prior to next flight.

BATTERY HOT

(FADEC software Version 5.356) ENGINE OVSPD

(FADEC software Version 5.202)

FADEC FAIL (During start) FADEC FAIL

(In-flight)



ANN-1


WARNING (RED) LIGHTS (Cont) PANEL LIGHTS

FAULT CONDITION

CORRECTIVE ACTION

NR below 95%.

Reduce collective and ensure throttle is in FLY detent position. Light will extinguish and audio will cease when NR increases above 95%.

NR above 107%.

Increase collective and/or reduce severity of maneuver. Light will extinguish when NR decreases below 107%.

XMSN OIL PRESS

Transmission oil pressure is below minimum.

Reduce power; verify fault with gauge. Land as soon as possible.

XMSN OIL TEMP

Transmission oil temperature is at or above red line.

RPM

(with low RPM audio)

RPM

(without audio)

Reduce power; verify fault with gauge. Land as soon as practicle.

CAUTION (AMBER) AND ADVISORY (WHITE/GREEN) LIGHTS PANEL LIGHTS AUTO RELIGHT

FAULT CONDITION Engine igniter is operating.

CORRECTIVE ACTION None. NOTE AUTO RELIGHT light will be illuminated when ignition system is activated. Ignition system is activated:

1—during start sequence 2—in MANUAL mode with NG above 55% 3—with FADEC detection of engine out condition with NG above 50%. BAGGAGE DOOR

Baggage compartment door not securely latched.

Close door securely before flight. If light illuminates during flight, land as soon as practical.

Revision 2.0

ANN-2 FOR TRAINING PURPOSES ONLY

FlightSafety ®

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PANEL LIGHTS BATTERY RLY

CHECK INSTR

FAULT CONDITION

CORRECTIVE ACTION

Battery relay has malfunctioned to closed (ON) position with BATT switch OFF. Battery is still connected to DC BUSS.

If BATTERY HOT light is illuminated, turn GEN switch OFF if conditions permit. Land as soon possible.

TRQ, MGT, or NG is about to or has detected an exceedance. Flashing LCD trend arc

Reduce engine power if possible. Press INSTR CHK button to display magnitude of exceedance.

and digital display indicates Refer to BHT-407-MD-1. impending exceedance. Letter E in digital display indicates an exceedance has occurred. Cyclic stick is not centered.

Reposition cyclic stick to center position to extinguish CYCLIC CENTERING light.

ENGAGED

Information system status.

None.

ENGINE ANTI-ICE

ANTI-ICE switch ON. Engine receiving anti-icing air.

If light (if installed) remains illuminated with ENGINE ANTI-ICE switch OFF, avoid operations requiring maximum power.

ENGINE CHIP

Ferrous particles in engine

Land as soon as possible.

FADEC DEGRADED

FADEC ECU operation is degraded which may result in NR droop, NR lag, or reduced maximum power capability.

CYCLIC CENTERING

(In-flight)

oil. Remain in AUTO mode. Fly helicopter smoothly and nonaggressively. Land as soon as practical. NOTE It may be necessary to use FUEL VALVE switch to shut down engine after landing.

Applicable maintenance action required prior to next flight. FADEC DEGRADED

FADEC ECU has recorded a fault during previous flight or a current fault has

(With engine shutdown) been detected.

Position throttle to idle; if light extinguishes, fault is from previous flight. Applicable maintenance required prior to next flight.



ANN-3


CAUTION (AMBER) AND ADVISORY (WHITE/GREEN) LIGHTS (Cont) PANEL LIGHTS

FAULT CONDITION

CORRECTIVE ACTION

FADEC FAULT

PMA and/or MGT, NP or N G automatic limiting circuit(s) not functional.

Remain in AUTO mode. Land as soon as practical. Applicable maintenance action required prior to next flight.

FADEC MANUAL

FADEC is operating in MANUAL mode. No automatic governing is available. AUTO RELIGHT light will be illuminated when FADEC MODE switch is depressed.

Fly helicopter smoothly and nonaggressively. Maintain NR with coordinated throttle and collective movements. Land as soon as practical.

FLOAT ARM switch is ON. Float inflation solenoid is armed.

Normal operation for takeoff and landing over water. FLOAT ARM switch—OFF.Iflightremainsilluminated, FLOATS circuit breaker— out. Land as soon as practical.

FLOAT ARM

NOTE With float inflation solenoid armed, flight should not exceed 60 KIAS and 500 feet AGL. FLOAT TEST

Float system in test mode.

FUEL FILTER

Airframe fuel filter in impending bypass.

FUEL LOW

None. Land as soon as practical. Clean before next flight.

100 ±10 pounds of fuel remain Verify FUEL QTY. Land as soon inafttank. aspractical.

Revision 2.0


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PANEL LIGHTS R/FUEL BOOST

FAULT CONDITION Right fuel boost pump has failed.

CORRECTIVE ACTION If practical, descend below 8000 feet HP if fuel is Jet A or 4000 feet HP if fuel is Jet B to prevent fuel starvation if other fuel boost pump fails or has low output pressure. Land as soon as practical. WARNING

IF BOTH FUEL BOOST PUMPS FAIL, ALTITUDE MUST BE REDUCED TO BELOW 8000 FEET HP (JET A) OR 4000 FEET H P (JET B). LAND AS SOON AS POSSIBLE. L/FUEL BOOST

Left fuel boost pump has failed.

If practical, descend below 8000 feet H P if fuel is Jet A or 4000 feet HP if fuel is Jet B to prevent fuel starvation if other fuel boost pump fails or has low output pressure. Land as soon as practical.

FUEL VALVE

Fuel valve position differs from FUEL VALVE switch indication or FUEL VALVE circuit breaker out.

Check FUEL VALVE circuit breaker in. Land as soon as practical. If on ground, cycle FUEL VALVE switch.



ANN-5


CAUTION (AMBER) AND ADVISORY (WHITE/GREEN) LIGHTS (Cont) PANEL LIGHTS L/FUEL XFR

FAULT CONDITION Left fuel transfer pump has failed.

CORRECTIVE ACTION Land as soon as practical. CAUTION

If both fuel transfer pumps fail, unusable fuel may be as high as 151.0 pounds due to inability to transer fuel from forward cell. Land as soon as practical. NOTE

Under normal fuel transfer conditions, helicopters S/N 53000 through 53174 L/FUEL XFR and R/FUEL XFR lights will illuminate for 2.5 minutes and then extinguish. This indicates transfer is complete and transfer pumps have been automatically Helicopters S/Nturned 53175 off. and subsequent inhibit illumination of the lights. R/FUEL XFR

GEN FAIL

HEATER OVERTEMP

Right fuel transfer pump has failed.

Land as soon as practical.

Generator not conected to DCBUSS.

Verify fault with AMPS gauge. GENswitch—RESET,thenON. If GEN FAIL light remains illuminated, GEN switch—OFF. Land as soon as practical.

An overtemp condition has been deteccted by a temperature probe either under

Turn HEATER switch OFF immediately.

pilot seat, tunnel. copilot seat, or in vertical

Revision 2.0


FlightSafety ®

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PANEL LIGHTS

FAULT CONDITION

CORRECTIVE ACTION

Hydraulic pressure below limit.

Verify HYD SYS switch position. Accomplish Hydraulic System Failure procedure (refer to paragraph 3-6).

LITTER DOOR

Litter door not securely latched.

Close door securely before flight. If light illuminates during flight, land as soon as practical.

PEDAL STOP

Pedal Restrictor Control Unit has detected a failure of part of system.

V

HYDRAULIC SYSTEM

NE—60

KIAS.

PEDAL STOP emergency release—Pull. Land as soon as practical.

RESTART FAULT

FADEC ECU has detected a fault which will not allow engine to be restarted in AUTO mode.

Remain in AUTO mode. Plan landing site according. Applicable maintenance action required prior to next flight. NOTE

When throttle is repositioned to idle stop (during engine shutdown) the PMA will go offline and engine may flameout. START

Start relay is in START mode.

If START switch has not been engaged and there is zero indication on AMPS gage; START relay has malfunctioned and helicopter is on battery power. START circuit breaker—Out. Land as soon as practical.

T/R CHIP

Ferrous particles in tail rotor gearbox oil.


XMSN CHIP

Ferrous particles in transmission oil.


Revision 2.1


ANN-7


NOTES

Revision 2.0


MISCELLANEOUS FADEC MANUAL CHECK......................................................................M-1 ALTERNATE START—AUTO MODE .....................................................M-2

Revision 2.0


M-i

S U O E N A L L E C S I M

S U O E N A L L E C S I M


NOTES

Revision 2.0

M-ii FOR TRAINING PURPOSES ONLY

FlightSafety ®

international

FADEC MANUAL CHECK Every 150 hours a FADEC Manual Check is required (BHT-407-MM, Chapter 5). The purpose of this check is to ensure the engine responds to throttle movement while in MANUAL mode.

CAUTION Auto to manual transitions with NP/NR at 100% flat pitch will result in rapid NP/NR acceleration in approximately 7 seconds. To avoid possible overspeed condition, perform the FADEC Manual Check with the throttle at idle (63% NG).

NOTE Refer to the Rolls Royce 250-C47B Operation and Maintenance Manual, Publication CSP 21001 to do the FADEC Manual Check. Prior to positioning the FADEC mode switch to MANUAL for purposes of the check, ensure the throttle is positioned to idle and NG speed is at 63 ±1%.

NOTE The engine idle speed may reduce to the point where the engine out light and horn are activated. To prevent this from occurring, increase throttle as required to maintain 63% NG until the idle speed has stabilized.

NOTE If NG increases to more that 75% N G with throttle positioned in idle detent, maintenance action is required. Refer to the Rolls-Royce 250-C47B Operation and Maintenance Manual.



M-1


FADEC MANUAL CHECK (Cont) Once the FADEC mode switch is positioned to MANUAL, the FADEC MANUAL and AUTO RELIGHT lights will illuminate. In addition, the NG speed may change from 63 ±1%. An increase or decrease in N G speed may be noticed. The change in N G speed is due to the fact that the FADEC system is not temperature compensated in reguard to fuel flow in MANUAL mode. Engine load and HMU calibration will also play a part in determining if the NG speed will change. Once NG is stabilized, slowly increase throttle approximately 5 to 10% NG to ensure engine responds and then return throttle to idle position. Position FADEC Mode switch to AUTO and ensure FADEC MANUAL and AUTO RELIGHT light extinguish. Engine should return to a NG speed of 63 ±1%.

ALTERNATE START—AUTO MODE For helicopters that operate at temperatures of approximately 26.6°C (80°F) and above, or at high altitudes and experience a hot start abort event, the start procedure listed below is approved and has been demonstrated to overcome this issue in most instances. For hot and/or high altitude environments, and when prior troubleshooting has not revealed any engine maintenance issues, this procedure can be used to alleviate the possibility of aborted hot starts. With the collective in the full down position and the throttle in CUTOFF, the pilot can initiate the start by pressing the starter switch. This will energize the starter motor and turn on the ignition exciter (continue to hold starter switch). Once N1 has reached approximately 16%, the pilot is to move the throttle from CUTOFF to IDLE. Once throttle is moved to IDLE position, the starter will latch and the starter switch can be released once light off is detected. The engine will detect light off and smoothly accelerate to ground idle while limiting the MGT if necessary.

Revision 2.0

M-2 FOR TRAINING PURPOSES ONLY

PERFORMANCE/ WEIGHT & BALANCE DENSITY ALTITUDE CHART..................................................................P-1 POWER ASSURANCE CHECK ..............................................................P-2 HOVER CEILING—IN GROUND EFFECT ..............................................P-3 HOVER CEILING—IN GROUND EFFECT ..............................................P-4 HOVER CEILING—OUT OF GROUND EFFECT.....................................P-5 DOOR WEIGHTS AND MOMENTS (U.S.) ..............................................P-7 CABIN AND BAGGAGE LOADING (U.S.)...............................................P-8 FUEL LOADING (U.S.) ............................................................................P-9 WEIGHT AND BALANCE WORKSHEET (U.S.) ....................................P-10 GROSS WEIGHT LATERALCENTER OF GRAVITY LIMITS .................P-11 GROSS WEIGHT LONGITUDINALCENTER OF GRAVITY LIMITS ......P-12 BEFORE TAKEOFF BRIEFING (VFR)....................................................P-13

Revision 2.0


P-i

E / C EN CL A N AA MB R& OT FH RG EI PE W


NOTES

E / C EN CL A N AA MB R& OT FH RG EI PE W

Revision 2.0

P-ii FOR TRAINING PURPOSES ONLY

FlightSafety ®

international

DENSITY ALTITUDE CHART

Revision 2.0


P-1


E

K C E H C E C N A R U S S A R E W O P

T E L N I IC S A B

S MF S P F E R O L S R %C O0 / 0 E S 1 R P E M —T A E A E 5 N 3 IB H DR A U OT L R R E OW T O A P R E N E G

F F O E C -II T N A

IN G N E B ) 7 E 4 N V C - D 0 E 5 E 2 C E X C E Y O OT R T S O L N L — OS R IA —K K 50 C 1 E O H T C 5 E (8 C T N H G

.)T )C F °0 0 (1 0 T )C ,0 A ° 6 ) (E O 5 7 %D D E (6 0 UV T (7 T R I E G E T S M UL QA B E RE OL OR OB T UT A DS T W E S HO L V E IG L RR E P R A S OE M BT HU ONT M T W O IX A OT A T DY M R L A Y D L L A A HL E CA T NR RT E IC Z OO T R IR T NE E V ON : W E DH L E WO P E OD C M L P A OL O X R OR E P F D

I L R F A U L S E S V A E R L E R O WR OE P V 7 O 0 H 4 L E D O M

Revision 2.0

P-2 FOR TRAINING PURPOSES ONLY

FlightSafety ®

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HOVER CEILING—IN GROUND EFFECT TAKEOFF POWER ENGINE RPM 100% GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER) HEATER OFF / ANTI-ICE OFF BASIC INLET

GROSS WEIGHT - KG x 100

, 20

16

20,000 FT HD

0 00

00 ,0 8 1

,0 16

18

20

22

24

00

14

,0

AREA B -3 0

00

,0 12

-2

1 0

0

00

, 10

T A O M U M I N I M

-1

M A

0 00 0 00

M A X

IM U M

O

0

2 0

X

IM U M

O A

HP

-40

-20

0

°C

-40

0

50

00 20 A SE

-

0 4

00 40

T

T

3

T

AT

00 60

F

A

0

O

8

-

26

LE

V

B L 0 0 0 W5 G= X L A A MN R E T N I

EL

00 -2

20

OAT - °C

0

40

6 0 32

36

40

44

48

5 1.

52

B L 0 0 0 6 = L A N R E T X E

7

56

60

GROSS WEIGHT - LBS x 100

(Sheet 1 of 2)

Revision 2.1


P-3


HOVER CEILING—IN GROUND EFFECT MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 180 AMPS


GROSS WEIGHT - KG x 100 16

20,000 FT HD

00 ,0 20

18

20

22

24

00 ,0 18 00 ,0 16 , 14

AREA B

00

, 12

0 -4 0

00

, 10

T A O M

0

-1

M A

0 00 00

0

-40

-20

S

0

O A

2

O AT

T

-

°C

0

30

0

T

HP

0

4 0

5

00 20 F

-3 0 -2

10

00

0 40

-

X IM U M

AT

60

0

0

M A

X IM U M O

8

U M I N I M

26

E

A

LE

V

5

1 .7

0

0 -2

20

OAT - °C

00

40

60 32

36

40

B L 0 0 0 6 = L A N R E T X E

L A N R B E L T N I 0 0 0 W5 G= X A M

EL

44

48

52

56

60


(Sheet 2 of 2)

Revision 2.1


FlightSafety ®

international

HOVER CEILING—OUT OF GROUND EFFECT TAKEOFF POWER ENGINE RPM 100% GENERATOR 180 AMPS



, 20

16

20,000 FT HD

0 00

00 ,0 8 1

,0 16

18

20

22

24

00

14

,0

AREA B

00

,0 12 T A O M U IM N I M

1

00

0 0,

1 0

M A

00

00 80

M A

X IM U M

X

O

IM U M

-3 0

-2 0 2 0

O A

O -1

A

T

-

0

°C

0

30

T

AT

00 60

-4 4

00 40 00 20 -

F

T

S

HP

-40

26

-20

0

EA

LE

V


EL

0 -2

20

OAT - °C

00

40

60 32

36

40

44

48

0

0

B L 0 0 0 6 = L A N R E T X E

50 5

1.

7

52

56

60


(Sheet 1 of 2)

Revision 2.1


P-5


HOVER CEILING—OUT OF GROUND EFFECT MAXIMUM CONTINUOUS POWER ENGINE RPM 100% GENERATOR 180 AMPS



00 ,0 20

,0 18

18

20

22

24

26

00 ,0 16

00

, 14

00

12

0

,0

M A

0 00

00 80

6

IM U M

S

0

A

X IM U M

0

O

A

4

5 1 .7

00

EA

EL

00 -2

20

OAT - °C

T

-

°C

0 3

V

O A

2

T

T

LE

B L 0 0 0 6 = L A N R E T X E


10

00

T

HP

-20

M A

O

20 F

X

0 00 40

-

-4 0 -3 0 -2 0 -1 0

00

, 10

T A O M U IM IN M

-40

16

20,000 FT HD

0

0

5 0

0

40

60 32

36

40

44

48

52

56

60


(Sheet 2 of 2)

Revision 2.1


FlightSafety ®

international

DOOR WEIGHTS AND MOMENTS (U.S.) LONGITUDINAL DOOR

WEIGHT (LB)

CG (IN)

MOMENT (IN-LBS)

LATERAL CG (IN)

MOMENT (IN-LBS)

One crew door

13

64

832

±26

±338

Both crew doors

26

64

1664

0

0

One passenger door

15

125

1875

±27

±405

Both passenger doors

30

125

3750

0

0

Left passenger door and litter door

29

111

3219

–27

–783

Revision 2.0


P-7


CABIN AND BAGGAGE LOADING (U.S.) CABIN AND BAGGAGE COMPARTMENT TABLE OF MOMENTS INCH-POUNDS WEIGHT (LB) 10

MID-PASS. AFT-PASS. LITTER FRONT SEAT (FACING AFT) (FACING FWD) FS 65 FS 91 FS 129

PATIENT(S) FS 108

BAGGAGE FS 174

650

910

1290

1080

1740

20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200

1300 1950 2600 3250 3900 4550 5200 5850 6500 7150 7800 8450 9100 9750 10400 11050 11700 12350 13000

1820 2730 3640 4550 5460 6370 7280 8190 9100 10010 10920 11830 12740 13650 14560 15470 16380 17290 18200

2580 3870 5160 6450 7740 9030 10320 11610 12900 14190 15480 16770 18060 19350 20640 21930 23220 24510 25800

2160 3240 4320 5400 6480 7560 8640 9720 10800 11880 12960 14040 15120 16200 17280 18360 19440 20520 21600

3480 5220 6960 8700 10440 12180 13920 15660 17400 19140 20880 22620 24360 26100 27840 29580 31320 33060 34800

210 220 230 240 250 260 270 280 290 300 310 320 330 340 350

13650 14300 14950 15600 16250 16900 17550 18200 18850 19500 20150 20800 21450 22100 22750

19110 20020 20930 21840 22750 23660 24570 25480 26390 27300 28210 29120 30030 30940 31850

27090 28380 29670 30960 32250 33540 34830 36120 37410 38700 39990 41280 42570 43860 45150

22680 23760 24840 25920 27000 28080 29160 30240 31320 32400 33480 34560 35640 36720 37800

36540 38280 40020 41760 43500

Revision 2.0


FlightSafety ®

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FUEL LOADING (U.S.) LONGITUDINAL LONGITUDINAL JP-4 JP-5 QUANTITY WEIGHT CG MOMENT QUANTITY WEIGHT CG MOMENT (U.S. GAL) (LBS) (IN) (IN-LBS) (U.S. GAL) (LBS) (IN) (IN-LBS) 5 10 15

32.5 65.0 97.5

20 25 28.4∆ 30 35 40 45 50 50.6** 55 60 65 70 74.8 75 80 85 90 95 100 105 110 115 120 125 127.8

130.0 162.5 184.6 195.0 227.5 260.0 292.5 325.0 328.9 357.5 390.0 422.5 455.0 486.2 487.5 520.0 552.5 585.0 617.5 650.0 682.5 715.0 747.5 780.0 812.5 830.7

133.7 135.0 135.9 136.4 136.7 137.0 134.3 127.8 122.9 119.1 116.0 115.7 116.1 116.2 116.2 116.1 116.0 116.1 117.7 119.0 120.3 121.4 122.3 123.4 124.6 125.6 126.6 127.5 127.9

4,345 8,775 13,250

5 10 15

34.0 68.0 102.0

17,732 22,214 25,290 26,189 29,075 31,954 34,837 37,700 38,054 41,506 45,318 40,095 52,826 56,399 56,599 61,204 65,748 70,376 74,965 79,495 84,221 89,089 93,886 98,748 103,504 106,247

20 25 28.4∆ 30 35 40 45 50 50.6** 55 60 65 70 74.8 75 80 85 90 95 100 105 110 115 120 125 127.8

136.0 170.0 193.1 204.0 238.0 272.0 306.0 340.0 344.1 374.0 408.0 442.0 476.0 508.6 510.0 544.0 578.0 612.0 646.0 680.0 714.0 748.0 782.0 816.0 850.0 869.0

133.7 135.0 135.9 136.4 136.7 137.0 134.3 127.8 122.9 119.1 116.0 115.7 116.1 116.2 116.2 116.1 116.0 116.1 117.7 119.0 120.3 121.4 122.3 123.4 124.6 125.6 126.6 127.5 127.9

4,546 9,180 13,862 18,550 23,239 26,455 27,397 30,416 33,429 36,445 39,440 39,812 43,412 47,410 51,360 55,264 58,998 59,211 64,029 68,782 73,624 78,424 83,164 88,108 93,201 98,219 103,306 108,375 111,145

∆ CRITICAL FUEL FOR MOST AFT C.G. CONDITION ** MOST FORWARD FUEL C.G. CRITICAL FUEL FOR MOST FORWARD C.G. CONDITION FULL FUEL

Revision 2.0


P-9


WEIGHT AND BALANCE WORKSHEET (U.S.) LONGITUDINAL

LATERAL

WEIGHT ARM MOMENT ARM MOMENT (LBS) (IN) (IN-LBS) (IN) (IN-LBS) Empty Weight +Oil

13.0

205.0

2665

0.0

+Pilot +Forward Passenger

65.0

14.0

65.0

–11.1

+Mid Passenger (L)

91.0

–13.0

+Mid Passenger (R)

91.0

15.5

+Aft Passenger (L)

129.0

–16.8

+Aft Passenger (M)

129.0

0.0

+Aft Passenger (R)

129.0

16.8

0

+Baggage +Litter Gross Weight at Zero Fuel +Fuel

0.0

0

116.0

0.0

0

137.0

0.0

0

Takeoff Gross Weight Gross Weight at Zero Fuel +Critical Fuel for Most Forward Most Forward CG Condition Gross Weight at Zero Fuel +Critical Fuel for Most Aft Most Aft CG Condition Gross Weight at Zero Fuel +Fuel Remaining at Landing

0.0

0

Landing CG Condition

Revision 2.1


FlightSafety ®

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GROSS WEIGHT LATERAL CENTER OF GRAVITY LIMITS

Revision 2.0


P-11


GROSS WEIGHT LONGITUDINAL CENTER OF GRAVITY LIMITS

Revision 2.0


FlightSafety ®

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BEFORE TAKEOFF BRIEFING (VFR) NOTE The following briefing is to be completed during item 1 of the Before Takeoff checklist. The pilot flying will accomplish the briefing. 1. Review the departure procedure (route and altitude, type of takeoff, significant terrain features, etc.). 2. Review anything out of the ordinary. 3. Review required callouts, unless standard calls have been agreed upon, in which case a request for “Standard Callouts” may be used. 4. Review the procedures to be used in case of an emergency on departure. 5. As a final item, ask if there are any questions. 6. State that the Before Takeoff Briefing is complete.

Revision 2.0


P-13

B407_PCL_2_1

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