Learjet 35 Reference Handbook Download | Manualshive

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4F-6

Developed for Training Purposes

Leerjet 35/36

October 2001

CAE SimuFlite

The fuselage fuel tank consists of two (

Learjet 35

) or four

(

Learjet 36

) bladder-type cells aft of the rear pressure bulk-

head. During fueling, the wing tank standby pumps are used to
fill the fuselage tank. As the engines consume fuel, an electric
transfer pump in the fuselage tank can transfer fuselage fuel
forward into the wing tanks. Each tank holds approximately 200
(

Learjet 35

) or 379 (

Learjet 36

) gallons.

A ram air scoop on the underside of the left and right wing pres-
surizes the fuel tanks during flight to ensure positive fuel flow to
the fuel pumps. Wing tanks are vented through vent tubes into
the tip tanks. As fuel level in the tip tanks rise, float valves in the
vent lines close to prevent fuel from entering the fuel venting
system. Vacuum and pressure relief valves in the tip tanks
assist the normal venting system if a negative pressure exists
or a tank overpressurizes because of fuel expansion.

Fuel Distribution

There are two distribution systems: one for each engine. The
fuel supply to the engine always comes from its respective
main wing tank. Fuel distribution is managed by the fuel control
panel on the center pedestal.

Each wing tank has two pumps: a jet pump and a standby elec-
tric pump. The jet pump uses motive flow fuel from the
enginedriven fuel pump to draw fuel from the tip tank to the
wing tank.

The standby pump provides fuel pressure to the engine-driven
pump during start and provides pressure during crossflow and
fuselage fill operations. The standby pump is also a backup for
the jet pump should it fail. The engine-driven fuel pump suction
feeds from its respective tank below 25,000 ft altitude.

In the event of an engine fire, pulling the FIRE PULL or ENG-
FIRE PULL T-handle on the glareshield provides DC power to
close the firewall shutoff valve. Power is also provided to open
the valve when the handle is pushed in.

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Summary of Contents for 35

Page 1: ...Learjet 35 36 Cockpit Reference Handbook FEBRUARY 2007 ...

Page 2: ...g purposes only It is not to be used as nor considered a substitute for the manufacturer s Pilot or Maintenance Manuals Copyright 2007 CAE SimuFlite Inc All rights reserved Excerpted materials used in this publication have been reproduced with permission of Learjet Inc Printed in the United States of America ...

Page 3: ...icipate actively in all training activities Through your involvement interaction and practice the full value of your training will be transferred to the operational environment As you apply the techniques presented through CAE SimuFlite training they will become second nature to you Thank you for choosing CAE SimuFlite We recognize that you have a choice of training sources We trust you will find ...

Page 4: ...1 2 Developed for Training Purposes Learjet 35 36 February 2004 CAE SimuFlite ...

Page 5: ...s The alphabetically arranged Systems chapter includes key data on particular systems and relevant color schematics The Flight Planning chapter includes maximum allowable takeoff and landing weight flow charts and a sample weight and balance form International flight planning information includes a checklist a glossary of frequently used international flight operation terms and sample flight plan ...

Page 6: ...1 4 Developed for Training Purposes Learjet 35 36 February 2004 CAE SimuFlite ...

Page 7: ...ocedures are addressed individually their smooth integration is critical to ensuring safe efficient opera tions Preflight Inspection contains an abbreviated checklist for the exterior inspection as well as preflight cockpit and cabin checks Standard Operating Procedures details Pilot Flying Pilot Monitoring callouts and verbal or physical responses Maneuvers contains pictorial representations of s...

Page 8: ...2 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 9: ...erior Walkaround 2A 2 Left Nose 2A 2 Right Nose 2A 3 Right Wing Root 2A 4 Right Wing Forward 2A 5 Right Tip Tank 2A 6 Right Wing Aft 2A 6 Right Nacelle Aft LWR Fuselage 2A 7 Aft Compartment Tailcone 2A 8 Empennage 2A 9 Left Nacelle 2A 10 Left Wing Aft 2A 11 Left Tip Tank 2A 11 Left Wing Forward 2A 12 Power On Checks 2A 15 Cabin Inspection 2A 15 ...

Page 10: ...der Static Port FC 200 CLEAR Pitot Static Shoulder Static Drain Valves DRAIN Nose Gear Wheel Well CHECK FOR HYDRAULIC LEAKS Normal Operations Strut Extension 2 5 TO 3 5 INCHES Doors SECURED Nose Wheel Tire CHECK CONDITION Chine 3 4 inch minimum from ground Tire pressure between 104 and 114 PSI loaded 105 5 PSI unloaded Nose Gear Uplock CHECK FORWARD Alcohol Discharge Port CLEAR Radome Erosion Shoe...

Page 11: ...C 530 REMOVE COVER CLEAR Total Temperature Probe if installed CLEAR Stall Warning Vane FREE AND DOWN Static Ports Shoulder Static Port FC 200 CLEAR Pitot Static Drain Valves DRAIN Pressurization Static Port CLEAR Oxygen Discharge Disk if installed CHECK IN PLACE Defog Outlet CLEAR Lower Fuselage Antennas Rotating Beacon CHECK Wing Inspection Light if installed CHECK ...

Page 12: ...DRAULIC LEAKS Normal Operations Strut Extension 2 5 to 3 5 INCHES Right Main Gear Landing Light CHECK Right Main Gear Wheels Brakes Tires CHECK Loaded Tire Pressures 17 000 lbs MTOGW 146 TO 156 PSI 18 000 lbs MTOGW 157 TO 167 PSI 18 300 lbs MTOGW 161 TO 171 PSI WARNING 1 If fan is windmilling stop by pressing on fan spinner Do not attempt to stop windmilling by grabbing blades 2 The wing flight co...

Page 13: ...Wing With Softflite Stall Strip Stall Fence CHECK Boundary Layer Energizers CHECK Century III Wing Without Softflite Vortex Generators CHECK Mark IV Wing Stall Strip Stall Fences CHECK Right Wing Heat Scupper CLEAR RAISBECK MARK IV WING CENTURY III WING WITHOUT SOFTFLITE VORTEX GENERATORS STALL STRIP STALL FENCE STRAKE STRAKE CENTURY III WING WITH SOFTFLITE STALL FENCE STALL STRIP BOUNDARY LAYER E...

Page 14: ...ight Tip Tank Right Tip Tank CHECK Recognition Light CHECK Sump Drain Valve DRAIN Fuel Cap CONDITION SECURE Navigation Strobe Lights CHECK Fin Static Discharge Wicks 2 CHECK Jettison Tube CHECK F Right Wing Aft Access Panels CHECK FOR FUEL LEAKS Aileron CHECK Spoiler CHECK Flap CHECK ...

Page 15: ...Bypass Valve Indicator CHECK NOT EXTENDED Engine Turbine Exhaust Area CLEAR Thrust Reverser CHECK Aeronca Check condition check blocker doors completely stowed Dee Howard Check condition of doors hinges strike plates remove safety pins and flags Engine Fuel Bypass Valve Indicator CHECK Fuel Vent Drain Valve COMPLETELY DRAIN Transfer Line Drain Valve if FUS VALVE installed DRAIN Fuel Drains 3 DRAIN...

Page 16: ... 750 PSI MIN Hydraulic Reservoir Sight Gage CHECK Fire Extinguisher Bottles CHECK PRESSURE 600 PSI normal 500 PSI minimum Current Limiters CHECK Compressor Motor Belt CHECK Dee Howard Thrust Reverser Accumulator CHECK PRESSURE Spare Tire if installed SECURE Compartment Light if installed OUT Drag Chute if installed CHECK FOR PROPER INSTALLATION See AFM supplement for appropriate instructions for p...

Page 17: ...led CHECK Vertical Stab Rudder Horizontal Stab Elevator CHECK Drain holes clear Rudder for Freedom of Movement Static Discharge Wicks 6 on elevators 1 above NAV light and 1 on ventral fin CHECK Vertical Fin Navigation Strobe Lights CHECK VLF H Field Antenna if installed CHECK Left VOR LOC Antenna CHECK Left ELT Antenna if installed CHECK Left Fuel Computer Drain Valve DRAIN WARNING The vertical an...

Page 18: ...ve Indicator CHECK NOT EXTENDED Engine Turbine Exhaust Area CLEAR Thrust Reverser CHECK Aeronca Check condition check blocker doors completely stowed Dee Howard Check condition of doors hinges strike plates remove safety pins and flags Engine Fuel Bypass Valve Indicator NOT EXTENDED Left Engine Oil CHECK Oil Tank Filler Cap Access Door CHECK SECURE ...

Page 19: ... Aft Spoiler CHECK Flap CHECK Aileron CHECK Access Panels CHECK FOR FUEL LEAKS L Left Tip Tank Jettison Tube CHECK Fin Static Discharge Wicks 2 CHECK Navigation Strobe Lights CHECK Fuel Cap CONDITION SECURE Sump Drain Valve DRAIN Erosion Shoe Recognition Light if installed CHECK Left Tip Tank CHECK ...

Page 20: ...Generators CHECK Mark IV Wing Stall Strip Stall Fences CHECK Left Wing Heat Scupper CLEAR Left Wing Access Panels CHECK FOR LEAKS Left Fuel Vent REMOVE PLUG CHECK CLEAR Left Main Gear Wheel Well CHECK FOR LEAKS Normal Operations Strut Extension 2 5 to 3 5 INCHES Left Main Gear Landing Light CHECK Left Main Gear Wheels Brakes Tires CHECK Unloaded Tire Pressures 17 000 lbs MTOGW 146 TO 156 PSI 18 00...

Page 21: ...ht Inspection Left Engine Inlet Fan CHECK CLEAR Cabin Door Seal CHECK WARNING 1 If fan is windmilling stop by pressing on fan spinner Do not attempt to stop windmilling by grabbing blades 2 The wing flight control surfaces and engine inlet must be free of frost snow and ice ...

Page 22: ...2A 14 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 23: ...t Switches ON TEST OFF Exterior Light Switches ON TEST OFF Battery Switches Both OFF Stall Warning System Test Standard Wing PERFORM See AFM for appropriate instructions for performing the Stall Warning System Test Cabin Inspection Baggage SECURE Cabin Air Damper Control Knob or Cabin Blower Switch AS REQUIRED Emergency Exit AISLE CLEAR HANDLE UNOBSTRUCTED Passenger Briefing COMPLETE ...

Page 24: ...2A 16 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 25: ...fore Starting Engines 2B 5 Starting Engines 2B 28 Before Taxi 2B 33 Taxi 2B 37 Before Takeoff 2B 41 Runway Lineup 2B 42 Takeoff 2B 42 After Takeoff 2B 43 Climb 2B 45 Cruise 2B 46 Descent 2B 46 Transition Level 2B 46 Approach 2B 47 Before Landing 2B 48 Landing 2B 49 Go Around Missed Approach 2B 49 After Landing Clearing Runway 2B 50 Shutdown 2B 51 Quick Turnaround 2B 53 Taxi 2B 53 Runway Lineup 2B ...

Page 26: ...B 60 Taxiing 2B 62 Storage 2B 63 Restoring After Storage 2B 72 Hot Weather Operations 2B 76 Exterior Inspection 2B 76 Engine Start 2B 76 Taxi 2B 77 Takeoff 2B 77 Shutdown and Postflight 2B 77 Cold Weather Operations 2B 78 Preflight Inspection 2B 78 Taxi 2B 81 Takeoff 2B 82 After Takeoff 2B 83 Before Landing 2B 83 Landing 2B 84 Crosswind Consideration 2B 84 After Clearing Runway 2B 85 Shutdown and ...

Page 27: ... g After Takeoff Gear RETRACT Yaw Damper ENGAGE Placing items in a flow pattern or series provides organization and serves as a memory aid A challenge response review of the checklist follows execution of the tasks the PM calls the item and the appropriate pilot responds by verifying its condition e g Engine Anti Ice challenge ON response Two elements are inherent in execution of normal procedures...

Page 28: ...hrough flight Checklist items fulfills a minimum preflight requirement The Through Flight Checklist may be used following an intermediate stop with both engines shutdown provided the fol lowing criteria have been satisfied during that stop There has been no change in flight crew personnel No maintenance has been performed on the aircraft Routine line servicing is not considered maintenance No more...

Page 29: ... switch the OFF position diverts airflow above headliners at all times except during auxiliary heating operation Emergency Exit AISLE CLEAR HANDLE UNOBSTRUCTED Oxygen Masks Valves Pressure 100 CHECKED Crew Masks ADJUST CHECK Ensure that the mask control selector valve is set to 100 On Scott ATO masks check harness inflation PASS MASK Valve AUTO PASS OXY Valve NORM OXYGEN PRESSURE Gage CHECK Verify...

Page 30: ...io Panel CHECKED Alternate Static Source Switch FC 200 CLOSED Pilot s Altimeter FC 200 NORM Static Source Switch FC 530 BOTH Avionics Master Switch if installed OFF Fuel Computers ON Batteries Main Aircraft Batteries OFF Emergency Power System CHECKED AND ON EMER PWR BAT 1 SwitchSTBY Check attitude gyro for starting and erection Amber EMER PWR annunciator illuminates EMER PWR BAT 2 Switch if insta...

Page 31: ... s extinguish BAT 2 Switch ON BAT 1 Switch OFF Check for proper voltage Both BAT Switches ON GPU if desired CONNECTED CHECKED Ensure unit is regulated to 28V DC and limited to 1 100A maximum and 500A minimum Inverters CHECKED PRIMARY ON PRI Inverter Switch ON Ensure the red PRI INV annunciator is extinguished and AC volts in green arc NOTE With lead acid batteries do not attempt a battery start wi...

Page 32: ...ON SEC Inverter Switch OFF Ensure the AUX INV annunciator is extinguished and AC volts in green arc PRI Inverter Switch ON SEC and AUX INVERTER Switches OFF In Normal Out Defog Knob if installed IN Anti Skid ON Emergency Air 1 800 PSI minimum CHECKED Hydraulic Pressure 1 000 PSI minimum CHECKED If less than 1 000 PSI HYD pump switch to ON Parking Brake SET Parking Brake annunciator if installed il...

Page 33: ...ning Test Mute Switch if installed TEST The three red unsafe lights illuminate and the warning horn sounds Right Thrust Lever Mute Switch if installed DEPRESS If the optional horn silence switch is installed depress it to cut out the gear horn while holding the gear warning test switch in TEST Fire Detect System CHECKED Rotary Test Switch FIRE DET Test Button DEPRESS Check that both the left and r...

Page 34: ...alve CLOSE The left fuel pressure annunciator illuminates Right Standby Pump OFF Right low fuel pressure annunciator illuminates Crossflow XFER FILL FUS VAL Switches CLOSED OFF OFF If external power not used One Engine START Go to Engine Start in Starting Engines checklist page 2B 28 Warning Systems Check COMPLETED Test the warning system using the rotary test switch Cabin Altitude Warning Rotary ...

Page 35: ... and overspeed warning ceases After approximately 1 2 additional second the puller and overspeed warning activate again and then cease On all S Ns through 35 670 and 36 063 after approximately another 1 2 second the overspeed warning sounds again to check the 300 KIAS speed switch in the ADU Test Button RELEASE Mach Trim Rotary Test Switch MACH TRIM Test Button DEPRESS AND HOLD Visually check the ...

Page 36: ...es briefly then stops The L STALL warning annunciator illuminates steadily just prior to or at pusher actuation After pusher stops the needle sweeps back and remains in the yellow or green segment Pusher release must occur or the test has failed Test Button RELEASE TEST Selector Switch R STALL Test Button DEPRESS AND HOLD The operation is identical to that of L STALL above except needle sweeps cop...

Page 37: ... ment As the needle passes the green yellow margin the shaker activates the nudger actuates and the L STALL warning annunciator flashes High frequency vibration of the control column signals shaker actuation Low frequency for ward movement if not opposed of the control column sig nals nudger actuation As the needle advances to the red segment the pusher activates briefly then stops The L STALL war...

Page 38: ...TEST Selector Switch R STALL Test Button DEPRESS AND HOLD Verify that the nudger and pusher do not actuate as the angle of attack indicator moves through the band The nudger monitor horn sounds if the needle stays in the yel lowsegment Test ButtonRELEASE Flaps DN Ensure that both angle of attack indicator needles make at least one significant shift in position as flaps are lowered STALLWARNING Swi...

Page 39: ...ion Cabin Rate of Climb SET The 9 o clock position provides approximately a 500 FPM cabin altitude cabin rate Temp Controls AS DESIRED Bleed Air Switches ON Emer Pressurization Switches if installed GUARD DOWN TOLD Data Bugs COMPUTED SET Ice Detect Lights CHECKED Emergency Gyro UNCAGED CVR TEST Drag Chute Handle if installed STOWED Trim Pitch Roll Yaw Switches CHECKED SET PRIMARY NOTE Check illumi...

Page 40: ...ming switches Q pedestal NOSE DN OFF NOSE UP switch Ensure that no trim motion occurs PITCH TRIM Switch PRI Pedestal NOSE DN OFF NOSE UP Switch NOSE UP NOSE DN Ensure trim motion does not occur Pilot Control Wheel Trim Switch OPERATE Without depressing arming button move switch NOSE UP NOSE DN LWD and RWD Check that trim motion does not occur Arming Button without displacing switch DEPRESS Ensure ...

Page 41: ...ion should cease while MSW is held Pilot Control Wheel Trim Switch NOSE DN Pilot MSW DEPRESS AND HOLD Trim motion should cease while MSW is held Copilot Control Wheel Trim Switch NOSE UP Copilot MSW DEPRESS AND HOLD Trim motion should cease while MSW is held Copilot Control Wheel Trim Switch NOSE DN Copilot MSW DEPRESS AND HOLD Trim motion should cease while MSW is held Yaw Trim Switch MOVE EACH H...

Page 42: ... in both directions Either MSW DEPRESS AND HOLD Trim NOSE UP or NOSE DN Ensure trim motion ceases Pilot Control Wheel Trim Switch NOSE UP NOSE DN While depressing arming button operate NOSE UP NOSE DN Ensure trim motion does not occur Copilot Control Wheel Trim Switch NOSE UP NOSE DN While depressing arming button operate NOSE UP NOSE DN Ensure trim motion does not occur PITCH TRIM Selector Switch...

Page 43: ... Ensure trim motion occurs in all directions Pilot MSW DEPRESS Ensure that while trimming NOSE UP and NOSE DN depressing pilot MSW stops trim motion Copilot MSWDEPRESS Ensure that while trimming NOSE UP and NOSE DN depressing copilot MSW stops trim motion Copilot Control Wheel Trim Switch OPERATE Without depressing arming button move switch NOSE UP NOSE DN LWD and RWD Check that trim motion does n...

Page 44: ...IM OVSP Ensure amber PITCH TRIM annunciator illuminates TRIM OVSP OFF TRIM MON Switch RELEASE Flaps DN Either Control Wheel Trim NOSE UP OR NOSE DN Ensure PITCH TRIM indicator needle moves faster with flaps down The trim in motion audio clicker does not sound On S Ns 35 408 506 and subsequent 36 054 and subsequent TEST Selector Switch TRIM OVSP Either Control Wheel Trim NOSE UP OR NOSE DN TEST But...

Page 45: ...T Button DEPRESS Ensure amber PITCH TRIM annunciator illuminates TEST Button RELEASE Either Control Wheel Trim Switch OPERATE With arming button depressed operate the switch to move PITCH TRIM indicator pointer through the entire T O seg ment The amber T O TRIM annunciator illuminates when ever the pointer is outside of T O segment Rudder Trim Switch CHECK Q Move each half of switch separately to ...

Page 46: ...VL annunciators illuminate The autopi lot then opposes movement of the flight controls TEST Button DEPRESS AND HOLD Control Wheel Trim Switch LWD Without depressing arming button move to LWD ROLL annunciator extinguishes and autopilot disconnect horn sounds within five seconds Hold wheel at wings level posi tion Trim Switch TEST Button RELEASE ENG Button DEPRESS TEST Button DEPRESS AND HOLD Contro...

Page 47: ...ch DEPRESS Check that autopilot pitch and roll disengage Autopilot Monitor FC 530 Autopilot The ADI and HSI flags do not have to be retracted to com plete this check AUTOPILOT Switch ON Ensure the PWR annunciator on the Autopilot Controller illu minates TST Button DEPRESS Check that all annunciators on the Autopilot Controller illu minate ENG and TST Buttons DEPRESSSIMULTANEOUSLY THEN RELEASE MON ...

Page 48: ...pers FC 200 autopilot Primary PWR TEST Button DEPRESS AND HOLD Check that the PWR TEST and PRI ENG lights illuminate Primary PWR TEST Button RELEASE Ensure the PWR TEST remains illuminated and that the PRI ENG light extinguishes Secondary PWR TEST Button DEPRESS AND HOLD Check that the PWR TEST and SEC ENG lights illuminate Secondary PWR TEST Button RELEASE Ensure the PWR TEST remains illuminated ...

Page 49: ...NG OFF Button DEPRESS Check that the SEC ENG light extinguishes and the yaw damper disengages PRI ENG Button DEPRESS Ensure PRI ENG light illuminates Rudder Pedals DEPRESS ONE THEN OTHER While holding the control wheel centered depress one rud der pedal and then the other It must be possible to depress each rudder pedal against the opposition of the yaw damper system The Yaw Force Indicator indica...

Page 50: ...t least five seconds for test cir cuit to reset SEC ENG Button DEPRESS Check that the SEC ENG annunciator illuminates Rudder Pedals DEPRESS ONE THEN OTHER While holding the control wheel centered depress one rud der pedal and then the other It must be possible to depress each rudder pedal against the opposition of the yaw damper system The Yaw Force Indicator indicates direction of input Flaps DN ...

Page 51: ...or illuminates Rudder Pedals DEPRESS ONE THEN OTHER While holding the control wheel centered depress one rud der pedal and then the other It must be possible to depress each rudder pedal against the opposition of the yaw damper system The Yaw Force Indicator indicates direction of input Control Wheel ROTATE TO FULL LEFT Rudder pedals should deflect to left Control Wheel ROTATE TO FULL RIGHT Rudder...

Page 52: ...ated to back the closer hooks off the upper door catches The upper door is an emergency exit L R Fuel Cmptr Switches ON L R Fuel Cmptr Lights CHECK OUT Batteries CHECK FOR MIN VOLTAGE Lead acid batteries show at least 24V DC ni cad batteries show at least 23V DC Inverters PRI ON Air Conditioning Aux Heat FAN OR OFF Do not use the Freon system or auxiliary heat during start This step reduces voltag...

Page 53: ...er IDLE Q AIR IGN annunciator illuminates Q Check Fuel Flow indicator visually for indication of fuel flow Q Observe ITT indicator for indication of combustion within five seconds after placing thrust lever in IDLE If SPR is used release the switch at 300 400 C ITT ITT must not be allowed to exceed 860 C on most starts it does not exceed 700 C Q Observe fan speed N1 increasing Q Observe oil pressu...

Page 54: ...starting second engine or if taxiing with single engine operating and ammeter reads less than 175A both battery switches to ON If only one engine is started at this time return to page 2B 9 and continue with Warning Systems Check If GPU used for start START GEN Switch OFF AT IDLE The AFM does not make a distinction between battery and GPU starts It is widely accepted however to leave the gen erato...

Page 55: ... is placed in GEN check the generator output for indication of DC volts and amps Engine Instruments CHECK Q Turbine RPM Idle 55 to 62 Q Fan RPM Idle 26 to 32 Q Oil Pressure L or R LO OIL annunciator extinguished and indication in green band on oil pressure gage In cold temperature an oil pressure transient above normal can be expected Q FUEL PRESS annunciator extinguished to indicate nor mal opera...

Page 56: ...CURRENT LIMITER R The green indicator annunciator illuminates if the right cur rent limiter is functional Repeat the Current Limiter test after both engines have been started On early model aircraft not equipped with CUR LIM annun ciator or rotary test switch CURRENT position Main Bus Tie CB PULL Left Generator Switch OFF Check ammeter indications right amp indication should double Left Generator ...

Page 57: ...p to the annunciator and T R control panel Lastly the pedestal is checked from the thrust lever quadrant down to the bottom All the equipment is turned on and systems are tested as encountered in the flow pattern When completed all aircraft systems have been checked and set for the taxi phase of flight and nearly all tests have been completed The PF calls for and the crew completes the Before Taxi...

Page 58: ...ared WSHLD OV HT Light MONITOR When moisture has cleared WSHLD HEAT ON OFF Switch OFF Fuel Control Governors CHECKED Left Thrust Lever IDLE If the engine accelerates uncontrolled during the following steps turn fuel computer on until engine stabilizes at idle then shut down and correct the problem L Fuel Computer OFF L FUEL CMPTR annunciator illuminates Engine RPM may increase or decrease slightly...

Page 59: ... LEFT Apply left aileron until AUG AIL annunciator illuminates then hold the control wheel stationary Observe the deflection angle Spoileron Reset Switch RELEASE Control Wheel CENTER Spoileron Reset Switch HOLD IN RESET Control Wheel ROTATE RIGHT Apply right aileron until AUG AIL annunciator illuminates then hold the control wheel stationary Observe the deflec tion angle it should be approximately...

Page 60: ...2 through 035 without SB35 36 27 7 Spoilers EXTEND The SPOILER annunciator illuminates Spoiler CB PULL The spoilers should slam down retract in less than one sec ond and the annunciator extinguishes Spoiler CB RESET The spoilers extend the annunciator illuminates Spoilers RETRACT The spoilers retract in approximately four seconds and the annunciator extinguishes Flaps 8 or 20 SET Hydraulic Press L...

Page 61: ...l blocker door switches have been installed the UNLOCK annunciators flash after a three second delay If the UNLOCK annunciators flash the operational check may be performed If the annunciator s do not flash the operational check should be accomplished after landing The reverser must be visually inspected after use to determine that they are properly stowed Thrust Reverser Operational Check L Thrus...

Page 62: ...rust reversers should stow and EMER STOW light illuminates Both Thrust Reverser Levers STOW Emergency Stow Switch NORMAL EMER STOW light extinguishes Both Thrust Reverser Levers IDLE DEPLOY When the reversers are deployed check that the thrust reverser levers are free to pull into reverse past a lock out pin that retracts when both reversers are deployed Both Thrust Reverser Levers STOW The revers...

Page 63: ...ators illuminate Thrust Reverser Control Switches ARM ARM annunciators illuminate Thrust Levers ADVANCE SLIGHTLY ARM annunciators extinguish Thrust Levers IDLE ARM annunciators illuminate Thrust Reverser Levers IDLE DEPLOY Both DEPLOY annunciators illuminate the reversers deploy and the lever lock out pins pull Thrust Reverser Levers STOW Both DEPLOY annunciators extinguish Thrust Reverser Control...

Page 64: ... RPM Nacelle Heat OFF Wing and Stabilizer Anti Ice Check Stab and Wing Heat ON The cabin rate of climb indicators shows a climb in cabin altitude Stab and Wing Heat OFF The cabin rate of climb indicators shows a descent in Cabin altitude Cabin Check COMPLETED NOTE Anti ice systems should be turned on prior to flight into visible moisture with OAT of 50 F 10 C or below If anti ice systems are requi...

Page 65: ... Cabin Air NORM OR ON Anti IcE AS REQUIRED Radar AS DESIRED Transponder TA RA Dee Howard Thrust Reversers ARMED WARNING The wings vertical and horizontal stabilizers flight controls surfaces and engine inlets must be free of frost snow and ice NOTE Anti ice systems should be turned on prior to flight into visible moisture with OAT of 50 F 10 C or below If anti ice systems are required during takeo...

Page 66: ...onditions it may be necessary to turn on stall warnings after initiating the takeoff roll Parking Brake RELEASED Landing Taxi Lights ON AS DESIRED Recognition Strobe Lights ON Steer Lock OFF Warning Lights EXTINGUISHED OR AS APPROPRIATE The annunciator panel is scanned and all annunciators should be extinguished except possibly the STEER ON NAC HT if installed and DH annunciator Takeoff Nosewheel ...

Page 67: ... airborne the PF calls for gear retraction and yaw damper engagement At the appropriate speed the PF calls for flap retraction and for the After Takeoff checklist Landing Gear UP When the gear is retracting monitor the annunciators for proper indications to detect a hydraulic failure Yaw Damp PRI or SEC ENGAGED S Ns with FC 200 autopilot The yaw damper must be on for all operations after lift off ...

Page 68: ...nition may be delayed The AIR IGN annunciators extinguish Landing Taxi Lights OFF Pressurization MONITORED Autopilot APPR Light OUT Hydraulic Pressure NORMAL Angle of Attack Indicators CROSS CHECKED CAUTION Even small accumulations of ice on the wing leading edge can cause aerodynamic stall prior to activation of the stick shaker and or pusher These ice accumulations can also cause AOA indicator i...

Page 69: ...AL Recognition Light OFF Leaving FL 250 Crew Masks 100 OXY QUICK DON POSITION S Ns 35 002 through 112 except 107 36 002 through 031 ZMR100 Series one crew member must wear oxygen mask around neck 6600214 Series crew masks must be in quick donning posi tion to allow donning within five seconds S N 35 107 113 and subsequent 36 032 and subsequent Crew masks must be in quick donning position to allow ...

Page 70: ...T FOR LANDING Anti Ice Systems AS REQUIRED FL 180 Transition Level Altimeters SET CROSS CHECKED Air Conditioner AS DESIRED Use of the air conditioner may reduce the amount of internal windshield fogging that occurs at low altitude Hydraulic Pressure CHECKED Recognition Light ON TOLD Card Bugs COMPUTED SET Cabin CHECKED Swivel Seats FORWARD OR AS PLACARDED Work Table and Toilet Doors if installed C...

Page 71: ...mergency Air Pressure CHECKED Radio Barometric Altimeters MINSSET CROSS CHECKED Fuel Balance CHECKED Avionics SET FOR APPROACH Crew Briefing Bugs COMPLETED SET It is recommended that if turbulence is anticipated due to gusty winds wake turbulence or wind shear the approach speed be increased For gusty wind conditions an increase in approach speed of one half the gust factor is recom mended ...

Page 72: ...ator is wired through the downlock switch Anti Skid ON LIGHTS EXTINGUISHED Landing Taxi Lights ON Dee Howard Thrust Reversers below 200 KIAS ARMED Cabin CHECKED Flaps DOWN Hydraulic Pressure CHECKED Air Ignition ON Autopilot DISENGAGED Yaw Damper DISENGAGED FC 200 autopilot The yaw damper should be disengaged in the landing flare FC 530 autopilot With full flaps the yaw damper disen gages through ...

Page 73: ... RETRACTED Flaps 20 Landing Gear Switch UP Climb APPROACH CLIMB SPEED When clear of obstacles Airspeed VREF 30 Flaps UP WARNING When the Fuel Quantity gage indicates 600 pounds or less remaining in either wing tank prolonged nose up attitude of 10 or more may cause fuel to be trapped in the aft area of the wing tank outboard of the wheel well Fuel starvation and engine flameout may occur For go ar...

Page 74: ...Anti Ice System AS REQUIRED Air Ignition OFF Stall Warnings OFF Landing Taxi Lights AS DESIRED Cabin Air OFF Recognition Strobe Lights OFF Unnecessary Avionics Radar OFF UNS OFF Transponder STANDBY OR OFF Spoilers RETRACTED Flaps AS REQUIRED Hydraulic Pressure CHECKED Trims RESET Dee Howard Thrust Reversers OFF ...

Page 75: ...le batteries are on If the battery switches are turned off before the fuel transfer switch is place in OFF the crossflow valve may remain open Fuel Valve CLOSED Emergency Lights if installed DISARMED If emergency lights are left armed and main batteries turned off the lights come on and drain the emergency light system batteries Coffee Oven Switches OFF Thrust Levers CUTOFF When shutting down the ...

Page 76: ...e is set use of flaps to bleed hydraulic system pressure does not affect parking brake pressure Batteries OFF Control Lock INSTALLED CAUTION On S Ns without SB 35 36 32 4 failure to bleed hydraulic pressure from the system before setting Battery switches off could result in nose gear retraction if landing gear selector valve malfunctions ...

Page 77: ...hes OFF OR FAN Engine if shut down START Start Gen Switch GEN DC Volts Amps CHECKED Starter Disengagement CHECKED Current Limiters CHECKED Circuit Breakers IN Avionics AS REQUIRED Coffee Oven Switches AS REQUIRED Anti Ice Systems AS REQUIRED Taxi Fuel Panel Balance CHECKED TOLD Card Bugs SET Nav Equipment SET Transponder TA RA Radar AS REQUIRED Spoilers Flaps Trim RETRACTED 8 OR 20 SET CHECKED Pre...

Page 78: ...all Warnings ON Parking Brake RELEASED Landing Taxi Lights ON AS DESIRED Recognition Strobe Lights ON Steer Lock OFF Warning Lights OUT OR AS APPROPRIATE After Takeoff Traffic Pattern Landing Gear UP Yaw Damper PRI or SEC ENGAGED Flaps UP Dee Howard Thrust Reversers below 200 kts OFF Air Ignition AS REQUIRED Landing Taxi Lights OFF Fuel Panel Balance CHECKED Radio Barometric Altimeters SET CROSS C...

Page 79: ...Flaps DOWN Hydraulic Pressure CHECKED Yaw Damper FC 200 autopilot DISENGAGED Parking Under normal weather conditions the aircraft may be parked and headed in a direction to facilitate servicing without regard to prevailing winds For extended parking head aircraft into the wind Aircraft PARK ON HARD LEVEL SURFACE Nose Wheel CENTERED Parking Brake SET Main Gear Wheels CHOCKED Flaps and Spoilers RETR...

Page 80: ...polypropylene ropes or equiva lent are attached to the nose gear and the main gear struts Figure 2B 1 This procedure requires that tie down eyelets be set into the apron there is no procedure for mooring at unprepared facilities Parking Procedure PERFORM Ropes ATTACH TO NOSE GEAR AND MAIN GEAR SECURE TO PARKING APRON Figure 2B 1 Mooring Points on Landing Gear MAIN GEAR NOSE GEAR ...

Page 81: ...Leerjet 35 36 Developed for Training Purposes 2B 57 December 1998 Expanded Normal Procedures Nose Steering Turning Radius Figure 2B 2 Nose Steering Turning Radius 37 8 33 9 26 6 21 2 ...

Page 82: ...2B 58 Developed for Training Purposes Leerjet 35 36 December 1998 CAE SimuFlite Tow Bar Turning Radius Figure 2B 3 Tow Bar Turning Radius 22 9 4 1 25 10 20 3 ...

Page 83: ...xi operations directional control is accomplished utilizing the nosewheel steering system The maximum turning radius for the nosewheel steering system is 45 either side of center Nose Gear Towing Tow Bar ATTACHED TO NOSE WHEEL Insert tow bar into nose wheel axle and secure Control Gust Lock REMOVED Grounding Cables REMOVED Tow Bar ATTACHED TO TOWING VEHICLE Wheel Chocks Mooring Ropes REMOVED Parki...

Page 84: ... gear strut as low as possible Wheel Chocks Mooring Ropes REMOVED Control Gust Lock REMOVED Grounding Cables REMOVED CAUTION When pushing aircraft backward with a towing vehicle perform all braking with the towing vehicle Brake application while the aircraft is being pushed backward other than by hand may cause damage to the brake com ponents Ensure that battery switches are set to OFF while towin...

Page 85: ...of sufficient length to allow towing vehicle to be at least 50 to 100 ft from air craft Parking Brakes RELEASED Wing Tail Walkers STATIONED OPTIONAL Aircraft TOW Use smooth starts and stops When Towing Operation Completed Nose Wheel CENTERED Parking Brake SET Controls Gust Lock INSTALLED Wheels CHOCKED Parking Brakes RELEASED Grounding Cables ATTACHED Ropes Chains or Cables REMOVED ...

Page 86: ...s REMOVED Engine Inlet and Exhaust Covers REMOVED Area CLEAR OF PERSONNEL AND EQUIPMENT Engine START Start one engine according to engine starting procedure Parking Brakes RELEASED Release the parking brake and start taxi roll using only suffi cient thrust to start roll After taxiing Parking Brake SET Engine SHUT DOWN Shut the engine down according to engine shutdown proce dure After the engine ha...

Page 87: ...following are generally performed Parking 0 to 7 Days If the engines are in a sheltered environment i e not exposed to excessive humidity or temperature changes no action need be taken beyond installing protective covers Flyable Storage 7 to 30 Days Parking Aircraft PARK Park aircraft in hangar if possible If aircraft is parked out side position on flat surface facing into the prevailing wind Main...

Page 88: ...NSTALLED Electrical System Grounding Cables ATTACHED Batteries DISCONNECT LEADS Exterior Fuselage Protective Covers INSTALLED ON PITOT TUBES AND DORSAL FIN INLET Tail Stand INSTALLED Access Doors and Panels CLOSED AND SECURED Cabin Door CLOSED AND LOCKED Attach red tag to cabin door handle with the following nota tion AIRCRAFT PREPARED FOR FLYABLE STORAGE 7 to 30 Days DATE OF STORAGE ...

Page 89: ...ngine Preservation Instructions Six Months or Less in the TFE731 2 2B Engine Light Maintenance Manual When preserving engines follow the special environmental preservation instructions if applicable Protective Covers INSTALLED Fuel System Fuel System Procedure PERFORMED Perform fuel system procedure as described for Flyable Storage Fuel Vents COVERED Cover fuel vents with barrier material and secu...

Page 90: ...xternal power source and operate refrigeration system every 30 days Hydraulic System CHECKED Fill hydraulic system to operational level and check for leaks Repair all leaks prior to storage Windshield and Windows Windshield and Windows CLEANED LH Windshield Cover INSTALLED Place LH windshield cover over LH windshield Using black tape secure and seal protective cover to fuselage Do not tape center ...

Page 91: ...ube and install pitot tube cover Static Ports SECURED Cut small pieces of barrier material and place them over the static ports Secure and seal them from the atmosphere by taping around the perimeter of barrier material Landing Gear Tires REPLACED Replace serviceable tires with unserviceable tires Brakes REMOVED AND PRESERVED Remove brakes and preserve in brake preservative accord ing to procedure...

Page 92: ...cturer s instructions to pump reservoir fluid into waste tank Empty and sanitize waste tank Disinfect toilet to prevent bacterial growth during storage Emergency Air Bottle DEPLETED Deplete emergency air bottle air charge ensure that charg ing valve is turned off Engine Fire Extinguisher System Fire Extinguisher Container SERVICED Gain access to fire extinguisher container and install a wire jumpe...

Page 93: ...s Exterior Fuselage Tail Stand INSTALLED Dorsal Fin Inlet CoveR INSTALLED Access Doors and Panels CHECK CLOSED AND SECURED Cabin Door CLOSED AND LOCKED Attach red tag to cabin door handle with the following nota tion AIRCRAFT PREPARED FOR PROLONGED STOR GE 31 DAYS TO 6 MONTHS DATE OF STORAGE ...

Page 94: ...ion instructions if applica ble Engine Fire Extinguisher System Engine Fire Extinguisher REMOVED AND STORED Remove engine fire extinguisher container and cartridge and store in accordance with the manufacturer s recom mended procedures Fuel System Sumps DRAINED Anti Ice Additive CHECKED Remove a pint of fuel from the wing filler and check that anti ice additive concentration in fuel meets minimum ...

Page 95: ...ft has been stored for 12 months remove barrier material from landing gear struts and actuators Wipe hydraulic fluid off struts and actuators and apply a fresh light coating of hydraulic fluid and wrap struts and actuators with new barrier material Secure and seal with black tape Replace tape that attaches barrier material to aircraft every six months Windshield and Windows REPLACE TAPE Every Six ...

Page 96: ...om Flyable Storage 7 to 30 Days Aircraft ExterioR CLEAN IF REQUIRED Protective Covers REMOVED Tail Stand REMOVED Controls Gust Locks REMOVED Batteries SERVICED AND CONNECTED Servicing CHECKED Check the following items and service if required Q hydraulic accumulator Q hydraulic reservoir Q nose and main landing gear and struts Q tires Q refrigeration system Q emergency air bottles Q alcohol anti ic...

Page 97: ...2B Light Engine Maintenance Manual Fuel System SERVICED Electrical System SERVICED Oxygen System SERVICED AND CHECKED FOR LEAKS Alcohol Anti Ice System SERVICED Environmental Systems OPERATIONALCHECKS PERFORMED Hydraulic System CHECKED FOR LEAKS Repair any leaks prior to flight Windshield and Windows PROTECTIVE COVERS REMOVED AND STORED Avionic Equipment SERVICED Install all avionic equipment remo...

Page 98: ...m SERVICED Remove electrical power from the aircraft Remove red tag and jumper between ground stud and fire extinguisher car tridge insulated terminal Restore electrical power to aircraft Flight Controls SERVICED Remove controls gust locks lubricate flight control system and perform operational systems checks See Maintenance Manual for details Exterior Fuselage CHECKED Interior CLEANED IF REQUIRED...

Page 99: ...required for restoring from Prolonged Storage the following are performed Engine Fire Extinguisher System CHECKED Hydrostatically test and service engine fire extinguisher con tainers and install engine fire extinguisher containers and cartridges See Maintenance Manual for details 400 Hour Inspection PERFORMED Perform 400 hour inspection as described in Maintenance Manual ...

Page 100: ...on PERFORMED Protective Covers REMOVED Q Clean dust and dirt from landing gear shock struts Check gear doors position switches and squat switches for con dition and operation Check tires and struts for proper inflation Q Check and remove dust and sand from engine inlet duct tail pipe and the visible components of the thrust revers ers During the inspection be particularly conscious of dust and san...

Page 101: ... and propwash of other airplanes Takeoff Ensure takeoff performance is adequate for the conditions and runway length Shutdown and Postflight Install all aircraft protective covers Do not allow sand or dust to enter fuel tanks while refueling Do not leave reflective objects in the cockpit or on the glareshield reflected heat can distort the windshield optical properties ...

Page 102: ... inlets Deicing fluid may be used to clean these areas providing it is thoroughly wiped clean before starting Q Remove ice snow and dirt from landing gear shock struts and wheel wells Check gear doors position switches squat switches wheels and tires Q Carefully inspect the engine inlet outlet and fan for ice buildup from freezing precipitation Look closely at the fan ice can form on the back of t...

Page 103: ...r proper operation of the instruments Engines The engines should be preheated prior to starting when the engines have been cold soaked at temperatures below 40 F 40 C Two 850 watt electric blowers can be used one in the inlet and one in outlet duct or a BT 400 ground heater unit NSN 4520 00 219 7969 or equivalent is recommended If the temperature is between 40 F and 65 F direct warm air into each ...

Page 104: ...the ITT increases rapidly due to the slower engine spool up If fan speed N1 does not rise with turbine speed N2 or stops dur ing the start attempt or if ITT is rising rapidly and appears likely to exceed the start limit abort the start Oil pressure can be expected to exceed the maximum allow able transients Do not exceed idle power with oil temperature below 30 C However if the outside temperature...

Page 105: ...UNWAY Avoid the exhaust wake or propwash of other aircraft and be alert for loose ice or crusted snow that can be ingested into the engines Many pilots use thrust reversers to aid directional control while taxiing on slick surfaces This is very risky and can easily cause foreign object damage to the engine Slick surfaces can cause nosewheel steering to be mar ginal Differential braking can be used...

Page 106: ...takeoff thrust Windshield heat is rarely used on takeoff because of the noise Wing anti ice should be used if freezing precipitation is present The take off distance and V1 speed is dramatically affected with full anti ice operating WARNING Do not takeoff with runway water or slush accumulation of 3 4 inch or more WARNING Even small accumulations of ice on the wing leading edge can cause aerodynam...

Page 107: ...snow covered runway use the following procedure to crack any ice that may have formed between the brake disks and wheels Landing Gear EXTEND NORMALLY Anti Skid Switch OFF Brakes PUMP HEAVILY 6 TO 10 TIMES Anti Skid Switch ON Anti Skid Lights OUT Landing Distance INCREASE Multiply the dry runway landing distance by 1 4 for a wet runway 1 7 for freezing runway If operating under FAR 135 multiply the...

Page 108: ... braking for the runway condition Consider the use of the drag chute if installed High reverse thrust can result in directional control difficul ties Be prepared to reduce power to idle reverse if direc tional control is adversely affected If snow or ice is present while applying moderate to heavy braking do not use nose wheel steering above 10 knots ground speed Crosswind Consideration On a slick...

Page 109: ...OCKED Do not set the parking brake If a large accumulation of snow fall is possible do not leave the aircraft with a full fuselage tank particularly if the wings are not full Snow accumulation on the tail can cause the air craft to fall back on its tail Remove ice and snow from the flap structure and retract Remove ice snow and dirt from the landing gear struts inboard doors gear microswitches and...

Page 110: ...mand to ensure the aircraft is free of snow ice or frost before takeoff Failure to adequately deice the aircraft can result in seriously degraded aircraft performance loss of lift and erratic engine and flight instrument indications Following extended high altitude flight frost can form at ambi ent temperatures above freezing on the wing s underside in the fuel tank areas Refueling the aircraft wi...

Page 111: ...ype II IV fluids also referred to as AEA Type II IV are used generally in Europe Type I fluids are unthickened glycol based fluids that are usu ally diluted with water and applied hot they provide limited holdover time Type II IV fluids are thickened glycol based fluids that are usu ally applied cold on a deiced aircraft they provide longer hold over times than Type I fluids Many factors influence...

Page 112: ... frost onto treated areas Start the deicing process by treating the horizontal stabilizer followed by the vertical stabilizer Con tinue by treating the fuselage top and sides Finally apply deic ing fluid to the wings Deicing fluid should not be applied to Q pitot static tubes static ports temperature probes AOA vanes or TAT probe Q gaps between control surfaces and airfoil NOTE Holdover time is th...

Page 113: ...eicing equip ment around aircraft Maintain adequate separation between equipment and aircraft Q A fine mist of deicing fluid applied two or three times pro vides better anti icing protection than a single heavy application Q Apply deicing fluid to lower surfaces if anticipating taxi and takeoff through snow Q Follow all deicing fluid manufacturer s recommendations and procedures CAUTION If engines...

Page 114: ...nd pose a serious fire hazard Do not use deicing fluid to deice engines Mechanically remove snow and ice from the engine inlet Check the first stage fan blades for freedom of movement If engine does not rotate freely deice engine with hot air CAUTION After deicing wings and empennage check flap wells for slush and or ice accumulations Ensure that all drain holes are clear CAUTION Check all primary...

Page 115: ...dome pitot tubes static ports AOA probes vanes air inlets and exhausts and antennas Q engine inlets and exhausts Q landing gear wheels brakes tires wheel wells and doors Taxi During taxi on ice or snow covered surfaces observe the fol lowing Q Maintain a greater than normal distance between aircraft Q Do not use reverse thrust If reverse thrust used rein spect the aircraft for snow ice and frost a...

Page 116: ...n up to highest practical thrust and observe stable engine operation before brake release Q After setting takeoff throttle verify that LP RPM and other engine indications are normal Approach and Landing During the descent approach observe the following Q Anticipate use of engine and wing anti icing Q After the ground spoilers and thrust reversers are actu ated immediately lower nose wheel to runwa...

Page 117: ... Approach and Landing 2C 11 Typical Non Precision Approach 2C 13 Go Around Missed Approach Balked Landing 2C 15 Circling Approach 2C 17 Visual Approach and Landing 2C 19 Engine Failure After V1 Takeoff Continued 2C 21 Single Engine Precision Approach and Landing 2C 23 Single Engine Go Around Missed Approach 2C 25 Partial Zero Flaps Approach and Landing 2C 27 Single Engine Visual Approach and Landi...

Page 118: ...2C 2 For training only Learjet 35 36 February 1998 ...

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Page 147: ...l Situations 2C 6 Aborted Takeoffs 2C 6 Critical Malfunctions in Flight 2C 7 Non Critical Malfunctions in Flight 2C 7 Radio Tuning and Communication 2C 7 Altitude Assignment 2C 8 Pre Departure Briefings 2C 8 Advising of Aircraft Configuration Change 2C 9 Transitioning from Instruments to Visual Conditions 2C 9 Phase of Flight SOP 2C 11 Holding Short 2C 11 Takeoff Roll 2C 12 Climb 2C 13 Cruise 2C 1...

Page 148: ...Flite Precision Missed Approach 2C 23 Precision Approach Deviations 2C 25 Non Precision Approach 2C 26 Non Precision Missed Approach 2C 31 Non Precision Approach Deviations 2C 33 Visual Traffic Patterns 2C 34 Landing 2C 36 L3CRH_SOP fm Page 2 Monday July 30 2007 10 51 AM ...

Page 149: ...ence it is the way CAE SimuFlite conducts its flight operations The procedures described herein are specific to the Learjet models 25 35 55 and apply to specified phases of flight The flight crew member designated for each step accomplishes it as indicated Definitions LH RH Pilot Station Designation of seat position for accom plishing a given task because of proximity to the respective control ind...

Page 150: ...signated on the checklist as PM or by his seat position are the PM s responsibility The PM accomplishes an item then responds orally to his own challenge In all cases the response by either pilot is confirmed by the other and any disagreement is resolved prior to continuing the checklist After the completion of any checklist the PM states _______ checklist is complete This allows the PF to maintai...

Page 151: ...hecklist The crewmember designated on the checklist accomplishes the checklist items with the appropriate challenge response The pilot designated to fly the aircraft i e PF does not perform tasks that compromise this primary responsibility regardless of whether he uses the autopilot or flies manually Both pilots must be able to respond to an emergency situation that requires immediate corrective a...

Page 152: ... passengers and or crew are in jeopardy remember three things Q FLY THE AIRCRAFT Maintain aircraft control Q RECOGNIZE CHALLENGE Analyze the situation Q RESPOND Take appropriate action Aborted Takeoffs The aborted takeoff procedure is a pre planned maneuver both crewmembers must be aware of and briefed on the types of malfunctions that mandate an abort Assuming that the crew trains to a firmly est...

Page 153: ...assigned to him Non Critical Malfunctions in Flight Procedures for recognizing and verifying a noncritical malfunc tion or impending malfunction are the same as those used for time critical situations use positive oral and graphic communi cation to identify and direct the proper response Time how ever is not as critical and allows a more deliberate response to the malfunction Always use the approp...

Page 154: ...inues to point to the altitude alerter until the PF confirms the altitude assignment and alerter setting Pre Departure Briefings The PIC should conduct a pre departure briefing prior to each flight to address potential problems weather delays safety considerations and operational issues Pre departure briefings should include all crewmembers to enhance team building and set the tone for the flight ...

Page 155: ...t path changes so there is always mutual understanding of the intended flight path Time permitting a PA announcement to the passengers pre cedes maneuvers involving unusual deck or roll angles Transitioning from Instruments to Visual Conditions If visual meteorological conditions VMC are encountered dur ing an instrument approach the PM normally continues to make callouts for the instrument approa...

Page 156: ...2C 10 Developed for Training Purposes Learjet 35 36 July 2004 CAE SimuFlite L3CRH_SOP fm Page 10 Monday July 30 2007 10 51 AM ...

Page 157: ... Type of Takeoff e g Rolling Standing Q initial heading course Q initial attitude Q airspeed limit if applicable Q clearance limit Q emergency return plan Q SOP deviations Consider the following Q impaired runway conditions Q weather Q obstacle clearance Q Instrument Departures Cleared for Takeoff CALL Runway Line up Takeoff checklist ACTION Complete Runway Line up Takeoff checklist CALL Before Ru...

Page 158: ...nitial Airspeed Indication CALL Airspeed alive ACTION Visually confirm positive IAS indication NWS RELEASED At 80 KIAS CALL 80 knots crosscheck At V1 CALL V1 ACTION Move hand from power levers to yoke At VR V2 CALL Rotate ACTION Rotate to a approx 9 pitch atitude for takeoff Go around position on V Bars L3CRH_SOP fm Page 12 Monday July 30 2007 10 51 AM ...

Page 159: ... yaw damper engaged After Gear Retraction ACTION Immediately accomplish attitude correlation check Q PF s and PM s ADI displays agree Q Pitch and bank angles are acceptable CALL Attitudes check Or if a fault exists give a concise statement of the discrepancy At VREF 30 KIAS and 400 ft above airport surface Minimum CALL V2 30 KIAS CALL Flaps UP CALL Flaps selected UP When flap indicator shows UP Fl...

Page 160: ...er Takeoff checklist CALL After Takeoff checklist complete At 10 000 ft CALL 10 000 feet ACTION No Smoke Fasten Seat Belt lights as required At Transition Altitude CALL 29 92 set Climb checklist CALL 29 92 set ACTION Complete Climb checklist CALL Climb checklist complete At 1 000 ft Below Assigned Altitude CALL _____ altitude for _____ altitude e g 9 000 for 10 000 CALL _____ altitude for _____ al...

Page 161: ...PF PM At Cruise Altitude CALL Cruise checklist ACTION Complete Cruise checklist CALL Cruise checklist complete Altitude Deviation in Excess of 100 ft CALL Altitude CALL Correcting Course Deviation in Excess of One Half Dot CALL Course CALL Correcting L3CRH_SOP fm Page 15 Monday July 30 2007 10 51 AM ...

Page 162: ... Altitude CALL _____ altitude for _____ altitude e g 10 000 for 9 000 CALL _____ altitude for _____ altitude e g 10 000 for 9 000 At Transition Level CALL Altimeter set _____ CALL Altimeter set _____ ACTION Complete Transition checklist CALL Transition checklist complete At 10 000 ft CALL 10 000 ft CALL Check Speed 250 knots Maintain sterile cockpit below 10 000 ft above airport surface L3CRH_SOP ...

Page 163: ... MAP non precision Q VDP Q special procedures DME step down arc etc Q type of approach lights in use and radio keying procedures if required Q missed approach procedures Q runway information conditions ACTION Brief the following Q configuration Q approach speed Q minimum safe altitude Q approach course Q FAF altitude Q DA MDA altitude Q field elevation Q VDP Q missed approach Q heading Q altitude ...

Page 164: ...egment CALL Flaps 8 or Flaps 20 CALL Flaps selected 8 or 20 When flaps indicate 8 or 20 Flaps indicate 8 or 20 After Initial Convergence of Course Deflection Bar CALL Localizer course alive CALL Localizer course alive At initial Downward Movement of Glideslope Raw Data Indicator CALL Glideslope alive CALL Glideslope alive When Annunciators Indicate Localizer Capture CALL Localizer captured CALL Lo...

Page 165: ...nunciator Indicates Glideslope Capture CALL Glideslope captured CALL Glideslope captured CALL Flaps DOWN CALL Flaps selected DOWN When Flaps indicate DOWN Flaps indicate DOWN If the VOR on the PM s side is used for crosschecks on the intermediate segment the PM s localizer and glideslope status calls are accomplished at the time when the PM changes to the ILS frequency This should be no later than...

Page 166: ...ACTION Q Start timing Q Visually crosscheck that both altimeters agree with crossing altitude Q Set missed approach altitude in altitude alerter Q Check PF and PM instruments Q Call FAF inbound CALL Outer marker or Final fix Altitude checks At 1 000 ft Above DA H CALL 1 000 ft to minimums CALL Check L3CRH_SOP fm Page 20 Monday July 30 2007 10 51 AM ...

Page 167: ...s than VREF or 0 6 AOA whichever is less Q no flight instrument flags with the landing runway or visual references not in sight Q landing configuration except for full flaps non precision or single engine approaches When within 500 ft above touchdown the aircraft must be within the approach window If the aircraft is not within this window a missed approach must be executed At 200 ft Above DA H CAL...

Page 168: ... reference ____ o clock CALL Going visual Land or Missed approach ACTION As PF goes visual PM transitions to instruments At DA H CALL Minimums Runway or visual reference ____ o clock ACTION Announce intentions CALL Going visual Land or Missed approach ACTION As PF goes visual PM transitions to instruments CALL 100 ft AGL CALL 50 ft AGL L3CRH_SOP fm Page 22 Monday July 30 2007 10 51 AM ...

Page 169: ... the nose to the flight director go around altitude ACTION Assist PF in setting power for go around CALL Flaps 8 or Flaps 20 CALL Flaps selected 8 or 20 When flaps indicate 8 or 20 Flaps indicate 8 or 20 At Positive Rate of Climb CALL Positive rate CALL Gear up Yaw Damper engaged CALL Gear selected up When gear indicates up Gear indicates up yaw damper engaged ACTION Announce heading and altitude ...

Page 170: ...Airport Surface Minimum CALL Flaps UP CALL Flaps selected UP When Flaps indicate UP Flaps indicate UP To ATC CALL Missed approach At 3 000 ft Above Airport Surface or Level Off which ever is lower CALL After Takeoff checklist ACTION Complete After Takeoff checklist CALL After Takeoff checklist complete L3CRH_SOP fm Page 24 Monday July 30 2007 10 51 AM ...

Page 171: ...ot Localizer CALL One half dot right left and increasing holding decreasing CALL Correcting VTGT ____________ CALL Speed plus or minus _____ knots and increasing holding decreasing CALL Correcting At or Below VREF CALL VREF or VREF minus _____ knots below VREF CALL Correcting Rate of Descent Exceeds 1 000 FPM CALL Sink _____ amount hundred and increasing holding decreasing CALL Correcting L3CRH_SO...

Page 172: ... complete After Level Off on Intermediate Approach Segment CALL Flaps 8 or Flaps 20 CALL Flaps selected 8 or 20 When flaps indicate 8 or 20 Flaps indicate 8 or 20 At Initial Convergence of Course Deviation Bar CALL Localizer course alive CALL Localizer course alive When Annunciators Indicate Course Capture CALL Localizer course captured CALL Localizer course captured L3CRH_SOP fm Page 26 Monday Ju...

Page 173: ... continued PF PM Prior to FAF CALL _____ number miles minutes from FAF CALL Gear down CALL Gear selected down When gear indicates down Gear indicates down CALL Landing checklist ACTION Complete Before Landing checklist except for full flaps autopilot and yaw damper L3CRH_SOP fm Page 27 Monday July 30 2007 10 51 AM ...

Page 174: ...TION Q Start timing Q Visually crosscheck that both altimeters agree Q Set MDA or nearest 100 ft above in altitude alerter Q Check PF and PM instruments Q Call FAF inbound CALL Flaps DOWN CALL Flaps selected DOWN When Flaps indicate DOWN Flaps indicate DOWN CALL Altimeters check At 1 000 ft Above MDA CALL 1 000 ft to minimums CALL Check L3CRH_SOP fm Page 28 Monday July 30 2007 10 51 AM ...

Page 175: ...s less Q no flight instrument flags with the landing runway or visual references not in sight Q landing configuration except for full flaps non precision or single engine approaches When within 500 ft above touchdown the aircraft must be within the approach window If the aircraft is not within this window a missed approach must be executed At 200 ft Above MDA CALL 200 ft to minimums CALL Check At ...

Page 176: ... Non Precision Approach continued PF PM At Point Where PM Sights Runway or Visual References CALL Runway or visual reference _____ o clock CALL Going visual Land or Missed approach CALL 200 ft AGL CALL 100 ft AGL CALL 50 ft AGL L3CRH_SOP fm Page 30 Monday July 30 2007 10 51 AM ...

Page 177: ...y rotate the nose to the flight director go around attitude ACTION Assist PF in setting power for go around CALL Flaps 8 or Flaps 20 CALL Flaps selected 8 or 20 When flaps indicate 8 or 20 Flaps indicate 8 or 20 At Positive Rate of Climb CALL Positive rate CALL Gear up Yaw Damper engaged CALL Gear selected up When gear indicates up Gear indicates up yaw damper engaged ACTION Announce heading and a...

Page 178: ... 400 ft Above Airport Surface Minimum CALL Flaps UP CALL Flaps selected UP When Flaps indicate UP Flaps indicate UP At 1 500 ft Minimum Above Airport Surface and Workload Permitting CALL After Takeoff checklist ACTION Complete After Takeoff checklist CALL After Takeoff checklist complete L3CRH_SOP fm Page 32 Monday July 30 2007 10 51 AM ...

Page 179: ... NDB Approach CALL _____ degrees off course right left and increasing holding decreasing CALL Correcting VTGT ____________ CALL Speed plus or minus _____ and increasing holding decreasing CALL Correcting At or Below VREF CALL VREF or VREF minus _____ knots below VREF CALL Correcting Rate of Descent Exceeds 1 000 FPM of Briefed Rate CALL Sink _____ amount hundred and increasing holding decreasing C...

Page 180: ...ecklist to slats and flaps CALL Approach checklist complete Downwind CALL Flaps 8 or Flaps 20 CALL Flaps selected 8 or 20 When flaps indicate 8 or 20 Flaps indicate 8 or 20 CALL Gear down Before Landing checklist CALL Gear selected down When gear indicates down Gear indicates down ACTION Complete Before Landing checklist except for full flaps autopilot and yaw damper L3CRH_SOP fm Page 34 Monday Ju...

Page 181: ...al Traffic Patterns continued PF PM At 1 000 ft Above Airport Surface CALL 1 000 ft AGL CALL Check At 500 ft Above Airport Surface CALL 500 ft AGL CALL Check At 200 ft Above Airport Surface CALL 200 ft AGL CALL Check CALL 100 ft AGL CALL 50 ft AGL L3CRH_SOP fm Page 35 Monday July 30 2007 10 51 AM ...

Page 182: ...ate DOWN or 40 Flaps indicate DOWN or 40 ACTION Disconnect autopilot prior to landing if on ACTION Continue with Q speed check Q vertical speed check Q callouts Q gear down verification Q flap verification CALL Final gear and flaps recheck Before Landing checklist complete At 100 ft Above Touchdown CALL 100 ft At 50 ft Above Touchdown CALL 50 ft At Landing Flare L2 L3 ACTION Yaw damper off with WM...

Page 183: ...s Landing continued PF PM At Touchdown ACTION Extend spoilers CALL Spoilers extended CALL Spoilers extended At Thrust Reverser Deployment CALL Two unlocked Two deployed At Thrust Reverser Idle Speed 60 70 KIAS CALL 60 knots L3 L5 or 70 kts L2 L3CRH_SOP fm Page 37 Monday July 30 2007 10 51 AM ...

Page 184: ...2C 38 Developed for Training Purposes Learjet 35 36 July 2004 CAE SimuFlite L3CRH_SOP fm Page 38 Monday July 30 2007 10 51 AM ...

Page 185: ... 3 4 Operational Limitations 3 7 Airspeed Mach Limitations 3 7 Standard Wing 3 6 Century III Wing FC 200 Autopilot RAS AAK 76 4 3 8 Century III Wing FC 530 Autopilot AAK 83 2 3 7 Weight Limitations 3 12 Center of Gravity Envelope 3 15 Takeoff and Landing Operational Limits 3 20 Enroute Operational Limits 3 21 Systems Limitations 3 23 Avionics and Communications 3 23 Drag Chute 3 24 Electrical and ...

Page 186: ...98 CAE SimuFlite Flight Controls 3 28 Fuel 3 31 Hydraulics 3 35 Ice and Rain Protection 3 35 Landing Gear and Brakes 3 36 Oxygen 3 36 Powerplant Garrett TFE731 2 B Turbofan 3 37 Thrust Reversers 3 42 AFM Supplement Limitations 3 45 United Kingdom Limitations 3 51 ...

Page 187: ...ions Certification Status FAR Part 25 Configuration The aircraft configuration must be as presented under Stan dard Performance Conditions in AFM Section V Maneuvers No aerobatic maneuvers including spins are approved Intentional stalls pusher actuations are prohibited above 18 000 feet with flaps and or landing gear extended Minimum Flight Crew Pilot and Copilot ...

Page 188: ...ti ice system off and all engine takeoff with takeoff thrust setting Thrust cutback was not required for compli ance Flap setting was 8 on aircraft Thrust cutback noise levels were obtained by initiating cutback at approxi mately 2 800 ft above runway for 18 000 lb 8 165 kg takeoff weight and approximately 2 750 ft for 18 300 8 300 kg takeoff weight Thrust cutback power settings were 85 5 N1 and 8...

Page 189: ...Leerjet 35 36 Developed for Training Purposes 3 5 February 1998 Limitations ...

Page 190: ...3 6 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Airspeed Mach Limits Standard Wing Figure 35 1 indicated Airspeed Knots ...

Page 191: ...ating Airspeed Sea Level to 14 000 Ft 307 KIAS Above 14 000 Ft 359 KIAS VA Maximum Maneuvering See Figure 3 1 VLE Maximum Landing Gear Extended 266 KIAS VLO Maximum Landing Gear Operating 202 KIAS VFE Maximum Flaps Extended Flaps 1 to 20 203 KIAS Flaps 21 to 40 152 KIAS VMCA Minimum Control Air 0 F 18 C 108 KIAS VMCG Minimum Control Ground 0 F 18 C at Sea Level 103 KIAS Turbulent Air Penetration A...

Page 192: ...Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite AirspeedMach Limits Century III Wing and FC 200 Autopilot Figure 35 2 Century III Wing and FC 200 Autopilot Indicated Airspeed Knots ...

Page 193: ...er Inoperative 0 74 MI VMO Maximum Operating Airspeed Sea Level to 14 000 Ft 307 KIAS Above 14 000 Ft 359 KIAS VA Maximum Maneuvering See Figure 3 2 VLE Maximum Landing Gear Extended 265 KIAS VLO Maximum Landing Gear Operating 202 KIAS VFE Maximum Flap Extended Flaps 1 to 8 198 KIAS Flaps 9 to 20 183 KIAS Flaps 21 to 40 153 KIAS VMCA Minimum Control Air 0 F 18 C 112 KIAS VMCG Minimum Control Groun...

Page 194: ...Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Airspeed Mach Limits Century III Wing and FC 530 Autopilot Figure 35 3 Century III Wing and FC 530 Autopilot Indicated Airspeed Knots ...

Page 195: ...IAS VA Maximum Maneuvering See Figure 3 3 VLE Maximum Landing Gear Extended 260 KIAS VLO Maximum Landing Gear Operating 200 KIAS VFE Maximum Flap Extended Flaps 1 to 8 200 KIAS S Ns 35 408 447 462 473 496 506 to 603 without FCN 85 6 S Ns 36 025 and 055 without FCN 85 6 Flaps 9 to 20 185 KIAS All other S Ns and aircraft with FCN 85 6 Flaps 9 to 20 200 KIAS Flaps 21 to 40 150 KIAS VMCA Minimum Contr...

Page 196: ...cable 18 250 35 001 to 044 with ECR 1495 or AAK 77 8 36 002 to 045 without AAK 80 2 18 500 35 002 to 344 with AAK 80 2 35 345 and subsequent with ECR 2234 36 002 to 045 with AAK 80 2 36 046 and subsequent WEIGHT LBS UNITS 17 000 35 002 and subsequent without ECR 1495 ECR 2234 AAK 77 8 or AAK 80 2 Model 36 Not Applicable 18 000 35 002 to 066 with AAK 76 4 and AAK 77 8 35 067 and subsequent with AAK...

Page 197: ... as determined from the applicable figure entitled Takeoff Distance in AFM Section V Q maximum takeoff weight for obstacle clearance as deter mined from the applicable Takeoff Flight Path and Climb Gradient figures in AFM Section V FAR 121 and 135 as applicable to U S registered aircraft Maximum Certified Landing Weight Perform Hard or Overweight Landing Inspection Chapter 5 Main tenance Manual if...

Page 198: ...ke energy limited for altitude and temperature as deter mined from the applicable figure entitled Landing Weight Limits in AFM Section V Zero Wing Tip Fuel Weight Maximum 13 500 LBS 6 124 KG All weights in excess of 13 500 lbs must consist of wing and tip tank except as follows Q Maximum zero wing and tip fuel weight may be increased to 14 000 lbs by adding up to 500 lbs of additional fuse lage fu...

Page 199: ...b takeoff weight Forward CG limit is fuselage station F S 366 31 5 MAC for all weights up to and including 10 000 lbs tapers through F S 375 96 16 66 MAC at 17 000 lbs to F S 376 31 17 09 MAC at 17 250 lbs The aft CG limit is F S 387 00 30 MAC for all weights Figure 35 1 17 000Lbs Center of Gravity Envelope Chart ...

Page 200: ...3 16 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 201: ...Center of Gravity Envelope 18 000 lb takeoff weight Forward CG limit is F S 366 31 5 MAC for all weights up to and including 10 000 lbs tapers through F S 377 34 18 83 MAC at 18 000 lbs to F S 377 69 18 76 MAC at 18 250 lbs Figure 35 2 18 000Lbs Center of Gravity Envelope Chart ...

Page 202: ...3 18 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 203: ... 18 300 lb takeoff weight Forward CG limit is F S 366 31 5 MAC for all weights up to and including 10 000 lbs tapers through F S 377 75 18 83 MAC at 18 300 lbs to F S 378 03 19 17 MAC at 18 500 lbs The aft CG limit is F S 387 00 30 MAC at all weights Figure 35 3 18 300Lbs Center of Gravity Envelope Chart ...

Page 204: ...Do not operate if water and or slush accumulation on the run way exceeds 3 4 inch 19 mm Do not take off or land with the cabin pressurized Maximum tip tank fuel for landing is 925 lbs 420 kg each tip tank Minimum 600 lbs 272 kg fuel in each wing are required for takeoff and intentional go around Seat belts and shoulder harnesses must be worn during takeoff and landing When OAT is below 25 C 13 F e...

Page 205: ...imits Flight Load Acceleration Limits Flaps Up 3 0 G to 1 0 G Flaps Down 2 0 G to 0 0 G These acceleration values limit the bank angle in a level coordi nated turn to 70 flaps up and 60 flaps down In addition pullups and pushovers must be limited to these values Maximum Operating Altitude 45 000 FT ...

Page 206: ...3 22 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 207: ...vere turbulence is encountered dis engage SPD V S ALT and G S modes and engage yaw damper LVL and SOFT modes Autopilot may not be used unless the pitch and roll monitors are checked and operational If upon retraction of flaps after takeoff APPR light stays on or illuminates in the clean configuration do not use the roll or pitch modes In maneuvers that involve the flaps beyond 13 ILS the complete ...

Page 208: ...lence encountered use attitude hold mode with SOFT mode engaged Autopilot may not be used in any axis that fails Autopilot Moni tor check Autopilot must be disengaged before switching static sources For VOR approach the flaps must be lowered to 8 or more Drag Chute Do not deploy Q in flight Q at speeds in excess of 150 KIAS Q simultaneously with thrust reversers if installed Demonstrated crosswind...

Page 209: ...ttery Current Limiter and Starter Disengagement Checks S Ns 35 002 to 389 except 370 without AMK 80 17 or AAK 81 1 36 002 to 047 without AMK 80 17 or AAK 81 1 The Battery Charging bus current limiter and starter disengage ment checks must be accomplished whenever an engine start using a starter has been performed Both engines must be operating to perform the check External Power Maximum amperage 1...

Page 210: ... operating one ammeter reads below 200 amps on 35 002 to 147 36 002 to 035 Q one engine operating one ammeter reads below 150 amps on 35 148 and subsequent 36 036 and subse quent Pressurization Limit Maximum differential pressure 10 0 PSI Information shown in italics is not included in the AFM Limitations chapter CAUTION Do not select MAX position of CABIN AIR switch while on the ground Do not per...

Page 211: ...orm extended engine operation above IDLE with CAB AIR switch on There is no ram airflow through the heat exchangers possible damage to air condi tioning components may occur CAUTION If not already operating do not turn on cooling system during landing with anti skid system operating Initial voltage drop may cause false signals in the anti skid system and dump brake pressure for two to three second...

Page 212: ...lights for both stall warning systems are inoperative when the generator and battery switches are off The systems may be turned off per emergency and abnormal procedures in AFM Sections III and IV and for stall warning system maintenance per Mainte nance Manual procedures To ensure proper stall warning system operation the Before Starting Engines and After Takeoff stall warning system opera tion a...

Page 213: ...rcraft flight operation WARNING On aircraft with FC 530 autopilot the action of the stick nudger verifies operation of the pitch torquer prior to pusher actuation If during ground test the shaker is not accompanied by the nudger the nudger monitor horn sounds do not dispatch If during flight the shaker is not accompanied by the nudger the nudger monitor horn sounds do not decelerate further WARNIN...

Page 214: ...uring the landing flare On aircraft with FC 530 autopilot one yaw damper must be on and operative for all flight conditions except takeoff and for trimming rudder For landing one yaw damper must be on except as permitted in Abnormal Procedures AFM Section IV For anticipated turbulence due to gusty winds wake turbu lence or wind shear increase the approach speed In gusty wind conditions an increase...

Page 215: ... anti icing additive blended at the refinery need no additional treatment However some fuels do not have the required additive blended at the refinery Prior to refueling check with the fuel supplier to determine if the fuel contains the required anti icing additive Any approved or emergency fuels not containing the required anti icing additive must have it blended during refueling The following pr...

Page 216: ...y fuel and mixed in any proportion with various approved jet kerosene based fuels Aviation gasoline may not be used in excess of 500 gallons per 100 hours of operation per engine CAUTION Ensure that anti icing additive is directed into the fuel stream and that additive flow starts after fuel flow starts and stops before fuel flow stops Do not allow concentrated additive to contact interior of fuel...

Page 217: ...British Fuel D ENG RD 2492 AVTUR 50 Canadian Fuel 3 GP 23 Chevron Jet Fuel A 1 Exxon Turbo A 1 Jet A 1 Kerosene Mobil Jet A 1 NATO F 34 Jet A 1 NATO F 35 Jet A 1 Richfield Jet A 1 Shell Jet A 1 Texaco Avjet A 1 Union Jet A 1 MIL T 83133 JP 8 EMS 53113 Jet B JP 4 EMS 53116 JP 5 ASTM Jet B Aircraft Turbine Fuel British Fuel D ENG RD 2486 AV TA G Canadian Fuel 3 GP 22 Chevron Jet Fuel B Chevron Jet F...

Page 218: ...ed safely in flight Information shown in italics is not included in the AFM Limitations chapter CAUTION When using any aviation gasoline in the fuel mixture limit operation as follows Q Do not take off with fuel temperature lower than 54 C 65 F Q Restrict aircraft flights to below 15 000 ft Q Both jet pumps and both standby pumps switchesmust be on and the pumps must be operating WARNING When the ...

Page 219: ...t exceed auxiliary hydraulic pump duty cycle of 3 minutes on then 20 minutes off Temperature When OAT is below 25 C 13 F engines should be operated for three minutes prior to takeoff to bring the hydraulic system up to normal operating temperature Ice and Rain Protection Windshield and Radome Anti Ice Fluid Methyl alcohol methanol per Federal Specification O M 232 Grade A is required Information s...

Page 220: ...be observed Aircraft 35 067 through 35 112 except 35 107 and aircraft 36 018 through 36 031 Above Flight Level 250 Q Aircraft with ZMR 100 Series Crew Masks One crew member must wear oxygen mask around his neck Q Aircraft with 6600214 Series Crew Masks Crew masks must be in the quick donning position which allows donning within 5 seconds Above Flight Level 410 Pilot copilot and passengers must wea...

Page 221: ...recommended specific gravity position listed in the engine log book for the type of fuel used If no entry made the following settings are to be observed Jet A Jet A 1 JP 5 POSITION 5 Jet B JP 4 POSITION 6 50 or more Aviation Gasoline POSITION 7 Fuel adjustment knob may be rotated one click either direc tion from the recommended fuel adjustment of positions 5 6 and 7 to compensate for individual en...

Page 222: ...does not require an engine log entry Maximum continuous limit is 832 C however for greatest engine life under normal conditions reduce engine power to an ITT of 795 C or less after 30 minutes of maximum continuous operation Engine Overspeed Limits The maximum overspeed limits of the engines are as follows 100 to 103 Turbine or Fan 1 MINUTE 103 to 105 Turbine or Fan 5 SECONDS If 105 turbine or fan ...

Page 223: ...Leerjet 35 36 Developed for Training Purposes 3 39 February 1998 Limitations Engine Operating Temperatures Figure 35 1 Engine Operating Temperatures ...

Page 224: ...onforming to Honeywell Specification EMS 53110 are approved for use Engines modified by AlliedSignal Service Bulletin TFE731 72 3596 require specific oil use Refer to the Honeywell Engine Light Maintenance Manual for engine oil service instructions Information shown in italics is not included in the AFM Limitations chapter After Start Attempt Wait 1 1 Minute 2 1 Minute 3 15 Minutes 4 1 Minute 5 1 ...

Page 225: ...o 140 Idle 25 to 46 30 to 140 Takeoff 5 Minutes 860 2 See chart in AFM Section V 100 38 to 46 30 to 140 Recommended Maximum Cruise Unrestricted 795 38 to 46 30 to 140 Maximum Continuous Unrestricted 832 See chart in AFM Section V 100 38 to 46 30 to 140 Overspeed Transient 1 Minute 100 to 103 100 to 103 55 30 to 140 Overspeed Transient 5 Seconds 103 to 105 103 to 105 30 to 140 Overspeed Over 105 Ov...

Page 226: ...ust reversers are limited to ground operations on paved surfaces Maximum reverse thrust usable at 60 KIAS or above is limited to fan speed N1 equal to takeoff power setting At 60 KIAS smoothly and deliberately return the thrust reverser levers to the reverse idle deploy position S Ns 35 001 to 153 and 36 001 to 038 with P N 210 1142 1 fuel computers Minimum turbine speed N2 above 40 000 ft is 86 R...

Page 227: ...rs to back up the aircraft Simultaneous use of reverse thrust and a drag chute if installed is prohibited Thrust reversers are limited to ground operations on paved sur faces Engine starts with reversers deployed are prohibited Time limit in reverse thrust is 30 seconds for each deployment WARNING When landing on snow covered runways apply reverse thrust with caution because visibility may be impa...

Page 228: ...3 44 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 229: ...004 1 HV Dual Antenna Array As plac arded operation of the ELT system in the RESET position is not to exceed five 5 seconds Landing Gear Tire Substitution When 10 ply tires are substituted for 12 ply tires on the main landing gear refer to Figure 3 5 page 3 47 for takeoff weight limits In no case is takeoff weight to exceed that as listed in AFM Section I Electrically Heated Windshield 350 Knot EC...

Page 230: ...3 46 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 231: ...Leerjet 35 36 Developed for Training Purposes 3 47 February 1998 Limitations Landing Gear Tire Substitution Figure 35 1 Landing Gear Tire Substitution Chart ...

Page 232: ...3 48 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 233: ...Leerjet 35 36 Developed for Training Purposes 3 49 February 1998 Limitations Electrically Heated Windshield 350 Knot ECRT 2498 S Ns 35 671 and Subsequent and 36 064 and Subsequent ...

Page 234: ...3 50 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 235: ...ft may however be restricted to another category and to a particular use and this is stated in the Certifi cate of Airworthiness Maximum Number of Occupants The total number of occupants must not exceed the lesser of 13 and the number of seats approved for takeoff and landing Children under the age of three years who are carried in the arms of the passengers may be left out of this count Performan...

Page 236: ... DURING EMERGENCY DESCENT VMCA Minimum Control Speed Air 112 KIAS 112 KCAS VMCG Minimum Control Speed Ground 103 KIAS 101 KCAS VMCL Minimum Control Speed Landing 105 KIAS 105 KCAS VMO MMO Maximum Operating Speed Below 8 000 ft 307 KIAS 300 KCAS Above 8 000 ft 359 KIAS 350 KCAS MMO with any BLEs Missing 0 78 MI Weight Limitations Maximum Zero Wing and Tip Fuel Weight 13 500 LBS Maximum ramp weight ...

Page 237: ...he aircraft shall not be flown for public transport or for any purpose except positioning Do not take off or land with the cabin pressurized Takeoff When OAT is below 35 C engine should be operated for three minutes prior to takeoff to bring hydraulic system up to normal operating temperature If OAT is below the lowest temperature shown on the performance charts use performance at the low est temp...

Page 238: ...tions Avionics and Communication The autopilot must not be engaged below 1 000 ft above the terrain enroute and not below 190 ft above runway threshold elevation when coupled to the ILS glideslope Electrical System Whenever an engine start using a starter has been performed accomplish the Battery Charging bus current limiter and starter disengagement checks as outlined in Starting Engines Starter ...

Page 239: ...lluminated do not exceed 0 74 MI Refer to AFM Section I Stick Puller If stick puller inoperative maximum Mach number is 0 74 MI Both yaw dampers must be operative One yaw damper must be on and operative for all flight conditions except takeoff and landing touchdown For a normal landing the following proce dures shall apply Q The airplane shall be configured for landing at least 500 ft AGL Q On air...

Page 240: ...ion per engine Maximum tip tank fuel for landing is 925 lbs each tip Jet A Jet A 1 and Jet B conforming to ASTM ES 2 74 Emer gency Standard Specification for Aviation Turbine Fuels may be used as temporary fuels until further notice Powerplant Starting 860 C ITT FOR 1 SECOND Takeoff 870 C ITT FOR 30 SECONDS 860 C ITT FOR 5 MINUTES 832 C ITT UNLIMITED Maximum Continuous 832 C ITT OR 100 N1 Overspee...

Page 241: ...Leerjet 35 36 Developed for Training Purposes 4A 1 February 1998 Avionics Avionics Pitot Static System without FC 530 Autopilot Pitot Static System withFC 530 Autopilot ...

Page 242: ...4A 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 243: ...Leerjet 35 36 Developed for Training Purposes 4A 3 February 2007 Avionics Pitot Static System Typical RVSM ...

Page 244: ...4A 4 Developed for Training Purposes Leerjet 35 36 February 2007 CAE SimuFlite ...

Page 245: ...tatic ports supply the copilot s altimeter airspeed indicator and vertical speed indicator VSI These static sources also supply the Mach trim Mach warning and overspeed warning altitude pressure and airspeed switches The unheated right aft static port and a static port in the nose compartment supply the pressurization module assembly Two shoulder static ports forward of the windshield supply stati...

Page 246: ...rt and an alternate static source supply the pressurization module Additional Instrumentation Airspeed Mach Indicator Pitot static inputs operate the pilot s and copilot s identical air speed indicators The instruments utilize a single rotating nee dle and dual scales for accurate Mach and airspeed indication The indicator face consists of a circular airspeed scale reading 0 to 400 kts a movable c...

Page 247: ...conventional barometric servo driven indicator that uses static pressure to indicate aircraft altitude Vertical Speed Indicators FC 200 autopilot without Rosemont probe two vertical speed indicators show vertical velocity up or down from 0 to 6 000 fpm On early aircraft the pilot s altimeter drives the single pointer rate of climb indicator Output from the altimeter is amplified and demodulated to...

Page 248: ...n the aircraft in hours and tenths of hours Optional True Airspeed Indicator The optional true airspeed TAS indicator displays true air speed in knots and static air temperature SAT in degrees Cel sius The indicator receives data from the air data sensor unit a heated temperature sensor probe and an SAT TAS com puter Emergency Attitude Gyro The emergency attitude gyro on the left instrument panel ...

Page 249: ...ividual audio selection by each pilot A three position switch SPKR PHONE PH EMER enables audio inputs to be selected Audio inputs from all com munications and navigation receivers can also be selected HF Communication Receiver The Learjet may have a single Collins HF 220 HF transceiver in the nose compartment and a CTL 220 control head on the cen tral pedestal or a single Collins 718 U 5 HF transc...

Page 250: ... MHZ and 40 paired glideslope frequencies from 329 15 to 335 00 MHZ Multiple outputs drive the flight director HSI RMIs autopilot course deviation indicator and R NAV if installed All the basic functions have built in test features Marker Beacon Receiver The Collins VIR 30A marker beacon receiver operates at a fre quency of 75 MHZ It indicates passage of marker beacon facil ities visually and aura...

Page 251: ...m and from navigational information from both VHF navigational receivers as well as the No 1 and No 2 ADF receiver if installed The copilot s RMI receives heading infor mation from the pilot s compass system and from navigational information from both VHF navigational receivers as well as the No 1 and No 2 ADF receiver if installed Automatic Flight Control System Automatic flight control systems A...

Page 252: ...pts the pri mary pitch trim Aircraft with FC 530 Depressing the wheel master switch dis engages the autopilot and yaw damper and interrupts the pri mary and secondary pitch trim stick pusher puller and nudger The autopilot is integrated with the flight director to automati cally control and direct aircraft flight Flight Director The flight director system consists of Q Collins FD 108 Integrated Fl...

Page 253: ...p or skid Q radio altitude Q decision height Q speed deviation The HSI 85 horizontal situation indicator displays Q position and heading with respect to magnetic or true north Q selected heading and selected course Q DME slant range Q groundspeed or elapsed time Q deviation from selected VOR localizer or other naviga tion course Q vertical deviation from glideslope Q TO FROM and bearing track poin...

Page 254: ...e Collins DME 40 provides the pilot with slant range distance information to the selected VORTAC as well as time to destina tion and ground speed readouts Two rotary switches select the desired information displayed by light bar readouts Weather Radar Standard equipment for the Learjet 35 36 is the RCA Primus 3 00S L weather radar The RCA Primus 400SL color radar is available as an option The digi...

Page 255: ...ntennas Continuous alti tude output signals are provided to the pilot s and copilot s flight director indicator and the radio altimeter Ground Proximity Warning System Some Learjet 35 36 aircraft have a ground proximity warning system GPWS installed to warn the crew of possible terrain danger The system receives navigation data from the encod ing altimeter radio altimeter navigation receiver nose ...

Page 256: ...4A 16 Developed for Training Purposes Leerjet 35 36 February 2007 CAE SimuFlite ...

Page 257: ...Leerjet 35 36 Developed for Training Purposes 4B 1 February 1998 Electrical System DC Electrical System S Ns 35 002 to 147 36 002 to 035 ...

Page 258: ...4B 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 259: ...Leerjet 35 36 Developed for Training Purposes 4B 3 February 1998 Electrical System DC Electrical System S Ns 35 148 to 201 205 36 036 to 040 ...

Page 260: ...4B 4 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 261: ...Leerjet 35 36 Developed for Training Purposes 4B 5 February 1998 Electrical System DC Electrical System S Ns 35 202 206 to 369 371 to 389 36 041 to 047 prior aircraft with AMK 78 13 ...

Page 262: ...4B 6 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 263: ...Leerjet 35 36 Developed for Training Purposes 4B 7 February 1998 Electrical System DC Electrical System S Ns 35 370 390 to 508 36 048 to 053 ...

Page 264: ...4B 8 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 265: ...Leerjet 35 36 Developed for Training Purposes 4B 9 February 1998 Electrical System DC Electrical System S Ns 35 509 and subsequent 36 054 and subsequent prior aircraft with AMK 85 1 ...

Page 266: ...4B 10 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 267: ...Leerjet 35 36 Developed for Training Purposes 4B 11 February 1998 Electrical System AC Electrical System ...

Page 268: ...4B 12 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 269: ... and equipment from electrical faults On aircraft 35 002 to 35 201 35 205 and 36 002 to 36 040 without AMK 78 13 the DC buses include Q Battery Charging bus Q Left and Right Battery buses Q Left and Right Main Power buses Q Left and Right Main buses Q Left and Right Generator buses Q Left and Right Essential buses On aircraft 35 202 to 35 204 35 206 and subsequent 36 041 and subsequent and prior a...

Page 270: ...arallel 28V DC circuit regulator power and the Freon compressor When both generators come on line the voltage regulator equalizer circuit energizes Both voltage regulators then work together to regulate their generator s output Each adjusts its generator field until a balanced condition exists between the generators If both generator ammeters are within 25A both generators are operating in paralle...

Page 271: ...T 160 annunciator illuminates Emergency Battery Single or dual emergency ni cad or lead acid battery packs provide 24V and 5V DC power for essential equipment i e emergency gyro lighting etc Depending on the module installed the battery pack s module provides 24V DC 115V AC and 26V AC power DC to AC inverter module or 24V and 5V DC DC to DC converter module The module used depends on the electrica...

Page 272: ...output then flows through the inverter paralleling control box to the Left and Right AC buses With both inverters operating the inverter paralleling control box equalizes the loads and frequency balance between the two inverters If an overload condition occurs the associated inverter s over load sensor circuit breaker opens to de energize the power relay When the power relay opens the inverter los...

Page 273: ... If an overvoltage condition occurs and GPU voltage exceeds approximately 33V the cutout circuit energizes the overvoltage cutout relay The cutout relay closes and disconnects external power from the aircraft by opening the external power relay On S N 35 618 and subsequent 36 056 and subsequent and previous aircraft with AMK 86 5 a five amp fuse pro vides additional external power protection If an...

Page 274: ...ight Essential bus Cabin Passenger Individual Switches Various General BRT OFF DIM Depressurization relay Left Main bus Entry LH forward cabinet switches Left Battery bus No Smoking Fasten Seatbelts NO SMOKE FASTEN SEAT BELT Left Main bus Baggage Compart ment LH forward cabinet switches Left Battery bus Maintenance Light Door Switches Right Battery bus Exterior Navigation NAV LT Laft Main bus Stro...

Page 275: ...two or three 110 130 AC output Emergency battery s Ground Power Unit 28V DC 1 100A out put Distribution DC with battery switches in BAT 1 2 and or generators operating Battery Battery Charging bus LH RH Hot Battery buses LH RH Generator buses LH RH Main buses LH RH Essential A B buses AC with main inverter switches in PRI SEC and or auxiliary inverter switch in ON LH RH AC bus 115V AC bus Spoilero...

Page 276: ...nverter switches Auxiliary bus switches if installed Emergency power switch es Monitor L R Gen annunciators L R DC ammeters DC voltmeter Battery temperature indicator if installed BAT 140 BAT 160 annunciators Starter engaged lights if installed PRI SEC INV annunciators AUX INV annunciator if installed AC voltmeter EMER PWR or EMER PWR 1 EMER PWR 2 annunciators CUR LIM annunciator if installed Curr...

Page 277: ...Leerjet 35 36 Developed for Training Purposes 4C 1 February 1998 Environmental Systems 450 Pneumatic System S Ns 35 002 to 35 106 35 108 to 35 112 36 002 to 36 031 without AMK 76 7 ...

Page 278: ...4C 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 279: ...Leerjet 35 36 Developed for Training Purposes 4C 3 February 1998 Environmental Systems 450 Pressurization System ...

Page 280: ...4C 4 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 281: ...Leerjet 35 36 Developed for Training Purposes 4C 5 February 1998 Environmental Systems 510 Pneumatic System S Ns 35 107 35 113 and subsequent 36 032 and subsequent ...

Page 282: ...4C 6 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 283: ...Leerjet 35 36 Developed for Training Purposes 4C 7 February 1998 Environmental Systems 510 Pressurization System ...

Page 284: ...4C 8 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Freon Air Conditioning Auxiliary Heating System ...

Page 285: ...nitor sys tem operation On S Ns 35 002 to 35 106 35 108 thru 35 112 and 36 002 to 36 022 i e 450 Pneumatic System low pressure LP and high pressure HP bleed air is regulated by the bleed air shut off and pressure regulator valve for use by nacelle inlet anti ice cabin air conditioning and pressurization windshield anti ice wing leading edge anti ice stabilizer leading edge anti ice Aeronca TFE731 ...

Page 286: ... 106 108 to 112 36 023 to 031 engine bleed air is routed directly to the heat exchanger where it is precooled in the heat exchanger by the passing ram air from the dorsal inlet The precooled air is then routed through the flow control valve and venturi into the cabin On aircraft S Ns 35 107 113 and subsequent 36 032 and subsequent with the BLEED AIR switches on and with the cabin air switch in ON ...

Page 287: ... selector knob to cruise altitude and the IN NOR MAL OUT DEFOG knob pushed in The cabin rate of climb may be set by varying the rate knob toward INCR or DECR Cabin altitude is monitored with the cabin altimeter which includes a cabin pressure differential scale 510 Pressurization System On aircraft with the 510 pressurization system normal pressur ization is controlled with the cabin pressure cont...

Page 288: ...rther at 11 500 1 500 ft the cabin altitude limiters cause both outflow valves to close Cabin Altitude Warning 450 Pressurization System If the cabin climbs above 10 000 500 ft the cabin altitude horn sounds and the pressurization system automatically switches to manual If the cabin continues to climb at 11 500 1 500 ft the cabin altitude limiters cause both outflow valves to close Emergency Press...

Page 289: ...s routed into the cabin With this event windshield wing and stabilizer anti ice bleed air is not available Freon Air Conditioning A Freon charged refrigeration system provides ground cooling in flight cooling at lower altitudes and cabin dehumidification A GPU or an engine driven generator must be used to power the system The COOL FAN switch on the copilot s lower panel controls the operation of t...

Page 290: ... HI both heating elements in the ducts energize With the switch set to LO only one heater ele ment energizes and the blower runs at 10 speed The cooling system blower runs at 100 after the heater elements heat to 150 F Each heating unit has a thermal switch that cycles the elements on at 125 F and off at 150 F ...

Page 291: ...ntrol valve Nacelle heat Emergency pressurization valves 35 107 113 and subsequent 36 032 and subsequent Bleed air manifold Air conditioning and heating system Windshield defog Wing and stabilizer leading anti ice Control L R modulating control valves L R BLEED AIR switches Cabin air switch 510 Pressurization system L R 9 500 ft cabin altitude aneroid switches L R emergency pressurization valves M...

Page 292: ...abin altitude limiter Outflow valve Control Squat switches Cabin air switch AUTO MAN switch UP DN altitude control Cabin altitude aneroid switch Emergency pressurization valves 9 500 ft cabin altitude pressure switches 35 107 113 and subsequent 36 032 and subsequent Monitoring L R BLEED AIR annunciators CAB ALT annunciator Cabin altitude warning Cabin climb gage Cabin altitude gage Protection CAB ...

Page 293: ...System Power Source Engine bleed air DC power DC RH ESS B bus Distribution Flow control valve H valve Heat exchanger Air distribution ducts Control Cabin air switch Climate control AUTO MAN COLD HOT selector Monitoring Cabin temperature indicator TEMP CONTROL indicator Protection CAB BLOW CB CABIN TEMP CB ...

Page 294: ...or Condenser Expansion valve Evaporator Air distribution system Control COOL OFF FAN switch Generator control circuits Monitoring Cabin temperature indicator Protection FREON CONT CB CABIN FLOW CB Compressor current limiter Power Source DC power DC RH MAIN bus Distribution Elements in aft cabin blower duct Control AUX HEAT HI OFF LOW switch Generator control circuits Monitoring Thermal switch Prot...

Page 295: ...Leerjet 35 36 Developed for Training Purposes 4D 1 February 1998 Fire Protection Fire Protection System ...

Page 296: ...4D 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 297: ...emperature around the engine accessory gearbox firewall and tailcone areas At normal operating temperatures the resistance of the sens ing elements is high and current does not flow across the sens ing element s core If the temperature in the accessory gearbox or firewall area reaches 410 F 210 C or 890 F 477 C in the tailcone area resistance of the affected sensing element decreases until current...

Page 298: ...i ated bottle s squib The squib detonates to break the bottle seal and release fire extinguishing agent to the affected engine nacelle Bottle discharge blows out the yellow discharge indica tor disc on the left rear fuselage After bottle discharge the selected ARMED switchlight extinguishes If fire warnings persist pressing the other illuminated ARMED switchlight discharges the second fire extingu...

Page 299: ...gine Control FIRE PULL ENG FIRE PULL T handle ARMED switchlights Monitoring FIRE PULL ENG FIRE PULL T handles ARMED switchlights Red thermal discharge indicator disk Yellow manual discharge indicator disk Fire bottle pressure gage Protection Thermal discharge valve on each bottle for overpressure relief Two one way check valves prevent extinguishing agent of one bottle from entering the other ...

Page 300: ...4D 6 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 301: ...TO DOWN POSITION R ESS B BUS FLAP POSITION SWITCH FUNCTION L R SWITCHES 3 STALL WARNING BIAS AUTOPILOT APPROACH BIAS FC530 AUTOPILOT TRIM SPEED AUDIO CLICKER FC530 AUTOPILOT 13 STALL WARNING BIAS AUTOPILOT APPROACH BIAS FC200 AUTOPILOT SPOILER LIGHT FLASH 25 STALL WARNING BIAS SPOILER AILERON AUGMENTATION AIRCRAFT EQUIPPED WITH 530 AUTOPILOT 25 YAW DAMPER FORCE REDUCTION LEFT GEAR SWITCH 25 GEAR W...

Page 302: ...GMENTATION SWITCH LEFT SPOILER RIGHT SPOILER LEFT SERVO VALVE RIGHT SERVO VALVE MANIFOLD TORQUE MOTOR RESTRICTOR BYPASS SOLENOID DE ENERGIZED SPOILER SELECTOR VALVE ENERGIZED TORQUE MOTOR ACTUATOR ACTUATOR SPOILERON COMPUTER AMPLIFIER SPOILER FOLLOW UP RIGHT AILERON FOLLOW UP RET EXT S P O I L E R R ESS B BUS 28V DC THIS DRAWING IS IN A LEFT AILERON AUGMENTATION MODE NOTE PRESSURE RETURN SPOILER O...

Page 303: ...he aircraft through the roll pitch and yaw axes The automatic flight control system AFCS moves the correspond ing control surface by electric servos through clutch pulleys and cables connected directly to the primary control system Ailerons Ailerons on the outboard trailing edge of each wing provide roll control of the aircraft mechanically through the control wheel or automatically by the autopil...

Page 304: ... trailing edge of the horizontal stabilizer provide pitch control of the aircraft mechanically through fore and aft movement of the control column or automatically by the autopilot pitch servo A closed loop cable assembly from the control column to the tail section and push pull tubes drive the elevators through a range of 16 0 30 up and 15 30 down Pitch Trim Pitch trim is accomplished by repositi...

Page 305: ...a two speed primary trim system The primary trim operates at slow speed with the flaps retracted and at high speed with the flaps extended beyond 3 The trim in motion audio clicker sounds with all trim inputs i e horizontal stabilizer movement when the flaps are retracted above the 3 flap switch Depressing the wheel mas ter switch stops or interrupts all pitch trim or servo inputs i e primary and ...

Page 306: ...stal shows the position of the rudder in units of travel right or left Yaw Damper The yaw damper provides automatic stabilization about the yaw axis by controlling transient yaw motion with rudder move ment A dual primary and secondary yaw damper system is installed on the Learjet 35 36 Both must be operational and one must be engaged for flight The yaw damper is engaged by depressing the PRI or S...

Page 307: ...flap switch labeled UP OFF DN allows the pilot flap control to any desired setting throughout their range of motion After attaining the desired flap setting placing the switch in the cen ter OFF position de energizes the control valve which cre ates a hydraulic lock holding the flaps in position A flap position indicator on the instrument panel provides a visual ref erence of flap position A pre s...

Page 308: ...right of the throttles Spoilers have a maximum extension of 47 7 0 and have a maximum travel differential of 6 A red FC 200 or amber FC 530 SPOILER annunciator on the glareshiel indicates spoiler extension In the event of a malfunction in the augmentation mode and or a mismatch of 6 between the aileron and spoileron a monitor circuit automatically disengages the augmentation system illu minates th...

Page 309: ...STALL light flashes If AOA continues to increase and the aircraft nears aerodynamic stall indicator needle reaches yellow red border the computer actuates the stick pusher to reduce the angle of attack and the red stall light illu minates steady On FC 530 aircraft a nudger is activated with the shaker If the nudger is inoperative a warning tone sounds to warn the pilot not to decelerate further Bo...

Page 310: ...d the autopilot not engaged Below 14 000 ft the overspeed horn sounds if the aircraft exceeds 307 KIAS If the aircraft exceeds 359 KIAS above 14 000 ft or 0 83M the overspeed horn sounds and the stick puller activates On aircraft with a typical RVSM1 or the FC 530 autopilot the overspeed horn also sounds if the speed exceeds 0 74M with the Mach trim system inoperative and the autopilot not engaged...

Page 311: ...mpers pedestal buttons Monitor Trim pedestal trim gages Autopilot autopilot force gages Dual yaw dampers pedestal lights and force indicators Protection Left CB Panel Pitch PITCH Primary STAB ACT Roll ROLL Aileron TRIM TAB Yaw YAW Rudder TRIM TAB Left stall warning L STALL WRN Primary yaw damper PRI YAW DAMPER Mach trim MACH TRIM Right CB Panel Tab and flap position TAB FLAP POSN Spoilers SPOILER ...

Page 312: ...plit condition SPOILER annunciator Steady not locked down Flashing flaps and spoilers extended Power Source Electrically controlled hydraulically operated Control Flap switch Monitor Flap indicator Protection Mechanical flap interconnect Power Source Left stall warning DC LH HOT BATTERY bus Right stall warning DC RH HOT BATTERY bus Control Mach overspeed Nudger 530 autopilot Nudger monitor 530 aut...

Page 313: ...mary L R yoke switch Trim switch pedestal PRI OFF SEC switch L R wheel master cutout L yoke overrides R yoke Two speed 530 autopilot only Flaps up slow Flaps 3 fast Mach trim computer above 0 69 MI RH 115V AC bus Secondary Secondary trim switch pedestal Trim switch pedestal PRI OFF SEC switch Autopilot Wheel master cutout 530 autopilot Monitor TO TRIM annunciator Trim indicator 530 autopilot TRIM ...

Page 314: ...4E 14 Developed for Training Purposes Leerjet 35 36 February 2007 CAE SimuFlite ...

Page 315: ...Leerjet 35 36 Developed for Training Purposes 4F 1 December 2001 Fuel System Fuel System S Ns 35 002 to 507 ...

Page 316: ...4F 2 Developed for Training Purposes Leerjet 35 36 October 2001 CAE SimuFlite ...

Page 317: ...Leerjet 35 36 Developed for Training Purposes 4F 3 December 2001 Fuel System Fuel System S Ns 35 508 and subsequent and 36 002 and subsequent ...

Page 318: ...4F 4 Developed for Training Purposes Leerjet 35 36 October 2001 CAE SimuFlite Fuel Vent System ...

Page 319: ...h tip tank holds approximately 175 U S gallons approxi mately 1 200 lbs or fuel refer to Servicing Baffles restrict fuel movement to prevent fuel sloshing that might cause sudden center of gravity shifts during maneuvering Each tip tank also has a fuel filler cap and an electrically operated fuel jettison valve A jet pump supplied with motive flow fuel from the engine driven fuel pump transfers fu...

Page 320: ... tanks assist the normal venting system if a negative pressure exists or a tank overpressurizes because of fuel expansion Fuel Distribution There are two distribution systems one for each engine The fuel supply to the engine always comes from its respective main wing tank Fuel distribution is managed by the fuel control panel on the center pedestal Each wing tank has two pumps a jet pump and a sta...

Page 321: ...s are required to jettison full tip tanks Control Indicating System The fuel control panel installed in the center pedestal provides the pilot with control and management of the fuel system lights and annunciators are provided for verification of system opera tion Nine fuel probes supply information to the fuel quantity indicator through the six position fuel quantity selector switch Fuel quantity...

Page 322: ...g tanks If the wing tanks are full fuel overflows through the vent tubes into the tip tanks When the fuselage tank is empty a pressure switch turns on the white EMPTY light to remind the crew to turn off the XFER FILL switch Operation Placing the START GEN switch to START energizes the standby pump This action moves fuel from the respective wing tank through the fuel filter and firewall shutoff va...

Page 323: ... pressure Distribution Tip tanks Wing tanks Standby pumps Transfer pump Optional gravity transfer line Engine motive flow Fuel jettison valves Jet or standby pump Distribution Motive flow valve JET PUMP switch STANDBY PUMP switches START GEN switch XFER FILL switch standby pumps XFER FILL switch transfer valve crossflow valve optional fuselage valve Right wing pressure switch Fuselage full float s...

Page 324: ...ghts EMPTY light FULL light Valve disagreement lights FUEL LOW level light Protection Firewall shutoff valve Fuel vent Negative pressure relief Two tip tank overpressure relief Wing tank overpressure relief center bulkhead Right wing pressure switch Left CB panel FUEL COMPTR A L JET PMP VAL B L STBY PMP B FUEL JTSN B Right CB panel R JET PMP VAL B R STBY PMP B FUEL QTY B FUEL JTSN B FUEL COMPTR A ...

Page 325: ... HYDRAULIC PUMP PRESSURE SWITCH CHARGE VALVE ACCUMULATOR AIRCRAFT EQUIPPED WITH DEE HOWARD THRUST REVERSERS AIR SUPPLY PRESSURE RETURN FILTER 1700 PSI 20 PSI ENG FIRE PULL BRAKE SYSTEM LANDING GEAR SELECTOR VALVE LANDING DOOR SELECTOR VALVE SPOILER SYSTEM FLAP SYSTEM ENG FIRE PULL 1 1 1 R ESS B BUS LOW HYD BATT CHARGING BUS GROUND SERVICE PORTS L ESS B BUS 17 PSI 0 5 PSI 0 4 GAL ...

Page 326: ...4G 2 Developed for Training Purposes Leerjet 35 36 October 2001 CAE SimuFlite ...

Page 327: ...engines running each engine driven hydraulic pump draws fluid from the pressurized reservoir through an electri cally operated firewall shutoff valve Pulling the associated FIRE PULL or ENG FIRE PULL handle electrically closes the shutoff valve Regulated bleed air pressurizes the reservoir to approximately 17 PSI to ensure positive fluid flow to the pumps and prevent pump cavitation If reservoir p...

Page 328: ...ed for ground operation of the parking brake and flaps In flight if the normal hydraulic system fails the auxiliary pump may be used for emergency operation of the flaps or brakes with anti skid upon landing The auxiliary pump does not operate the spoilers All of the fluid in the reservoir is available to the auxiliary hydraulic pump The bottom 0 4 gallons is not available to the engine driven pum...

Page 329: ...ne driven pumps Auxiliary hydraulic pump Control FIRE PULL ENG FIRE PULL T handles HYD PUMP switch Pressure switch System CBs Systems Powered Landing gear Spoilers Thrust reversers Dee Howard Flaps Brakes Monitor Direct reading pressure gage cockpit Accumulator precharge direct reading gage aft compartment LO HYD annunciator Protection Check valves Hydraulic fuses in brakes lines Auxiliary pump cu...

Page 330: ...4G 6 Developed for Training Purposes Leerjet 35 36 October 2001 CAE SimuFlite ...

Page 331: ...Leerjet 35 36 Developed for Training Purposes 4H 1 February 1998 Ice and Rain Protection Nacelle and Engine Spinner Anti Ice ...

Page 332: ...4H 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Wing and Horizontal Stab System ...

Page 333: ...Leerjet 35 36 Developed for Training Purposes 4H 3 February 1998 Ice and Rain Protection Early Windshield Defog and Anti Ice System Without AMK 76 7 S Ns 35 002 to 081 083 to 086 36 002 to 022 ...

Page 334: ...4H 4 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Late Windshield Defog and Anti Ice System S Ns 35 107 113 and subsequent 36 032 and subsequent ...

Page 335: ...Leerjet 35 36 Developed for Training Purposes 4H 5 February 1998 Ice and Rain Protection Early Alcohol System ...

Page 336: ...4H 6 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Late Alcohol System ...

Page 337: ...abilizer leading edge diffuser tubes After warming the leading edges bleed air exhausts overboard through scuppers underneath the wing and through the horizontal stabilizer tips Temperature sensors in the wing leading edge and horizontal stabilizer transmit a signal to the temperature indicators and thermoswitches located in the right wing and left horizontal sta bilizer leading edge areas provide...

Page 338: ...re reaches 2 PSI and turns off the ENG ICE annunciators Placing the NAC HEAT switches in the on position also sup plies 28V DC from the Left and Right Main buses to the engine Pt 2 Tt 2 probes Pitot Static Anti Ice With the BAT switches in the on position 28V DC from the Left and Right Essential buses powers the static port heating ele ments Placing the PITOT HEAT switches in the on position suppl...

Page 339: ...air to the external outlets or foot warmers S N 35 082 087 to 106 108 to 112 36 023 to 031 prior air craft with AMK 76 7 precooled engine bleed air is directed through ducting and control valves to the external outlets for ward of the windshield Operation of the system is the same as earlier aircraft see above description S N 35 107 113 and subsequent and 36 032 and subse quent precooled engine bl...

Page 340: ...e disabled However if either of the high limit thermoswitches detects an overheat the same sequence of events described previously occurs Radome and Windshield Alcohol Methanol protects the radome and serves as a backup for the pilot s windshield bleed air system On S N 35 002 to 106 108 to 112 and 36 002 to 031 when the system switch is set to RADOME a motor driven pump supplies methanol from a 2...

Page 341: ...dshield and radome When the methanol supply is depleted a float switch com pletes a ground circuit energizing the ALC AI annunciator Ice Detection Ice detection is performed by monitoring the wing heat indica tor horizontal stabilizer heat indicator windshield ice detection lights and wing inspection lights if installed Whenever the BAT switches are on 28V DC from the Left and Right Essential buse...

Page 342: ...4H 12 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 343: ...ng and horizontal stabilizer leading edges Methyl alcohol Methanol Pilot s windshield Radome Control BAT BAT 2 switches L R NAC HEAT switches L R PITOT HEAT switches STAB WING HEAT switch WING INSPECTION ON OFF pushbutton On S N 35 002 to 081 083 to 086 and 36 002 to 022 without AAK 76 7 WSHLD AUTO MAN switch IN NORMAL OUT DEFOG knob On S N 35 082 087 to 106 108 to 112 36 023 to 031 prior aircraft...

Page 344: ...itch On S N 35 002 to 106 108 to 112 36 002 to 031 WSHLD RADOME OFF RADOME switch On S N 35 107 113 and subsequent 36 032 and subsequent WSHLD RADOME RAD OFF switch Monitoring ALC AI annunciator Horizontal stabilizer temperature indicator L R ENG ICE annunciators PITOT HT annunciator s STAB OV HT annunciator WSHLD HT annunciator WING OV HT annunciator Wing temperature indicator WSHLD OV HT annunci...

Page 345: ...Leerjet 35 36 Developed for Training Purposes 4I 1 February 1998 Landing Gear and Brakes Landing Gear Up ...

Page 346: ...4I 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 347: ...Leerjet 35 36 Developed for Training Purposes 4I 3 February 1998 Landing Gear and Brakes Landing Gear Extended ...

Page 348: ...4I 4 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Landing Gear Emergency Extension ...

Page 349: ...AL PRESSURE RETURN EMERGENCY AIR SERVO SERVO SERVO R M A I N B U S ANTI SKID CONTROL BOX 2 PARKING BRAKE SERVO ANTI SKID VALVE 1 COPILOT BRAKE VALVE PILOT BRAKE VALVE PILOT BRAKE VALVE TO RESERVOIR SOLENOID SHUTOFF LH SQUAT SW COPILOT BRAKE VALVE ANTI SKID OFF ON SEE NOTE WARNING LIGHT CONTROL EFFECTIVE S N 35 231 AND SUBSEQUENT 36 045 AND SUBSEQUENT EFFECTIVE S N 35 034 AND SUBSEQUENT 36 017 AND ...

Page 350: ...INBOARD ANTI SKID GEN LH INBOARD ANTI SKID GEN ANTI SKID GEN L R NOSE STEER NOSE STEER COMPUTER AMPLIFIER FOLLOW UP STEER LOCK WHEEL MASTER BUTTONS PEDAL SYNCHRO MOTOR GEAR L A C B U S L M A I N SQUAT SWITCH RELAY BOX NOSE GEAR UP LOCK CONTROLS ENGAGE FUNCTION LEFT MAIN DOWN LOCK CONTROLS 28V DC CLUTCH POWER SQUAT SWITCH RELAY BOX CONTROLS AC TO RUDDER PEDAL SYNCHRO STEER ON ...

Page 351: ...sponse to rudder pedal movement The main landing gear has hydraulically operated disc brakes with electrically operated anti skid protection The anti skid sys tem provides maximum braking efficiency on all runway sur faces while minimizing wheel skid Landing Gear Squat switches on the main landing gear actuate with weigh ton wheels completing a circuit that prevents the landing gear selector valve...

Page 352: ...stem is enabled the inboard gear doors will not close and the landing taxi light for the respective gear will not operate If the nose gear down and locked switch does not sense a downand locked condition the aural warning system is enabled the nose gear UNSAFE light will not extinguish and the amber ENG SYNC light will not illuminate if the engine sync is on The landing gear aural warning horn sou...

Page 353: ...nd drives the doors to the open position This illuminates the two red UNSAFE main gear lights When the doors are fully open the door down switches energize the landing gear selec tor valve to the up position Through the landing gear selector valve hydraulic pressure flows to the nose and main landing gear actuators The gear actuators unlock the green LOCKED DN lights extinguish the red UNSAFE nose...

Page 354: ...t extinguishes The door control valve ener gizes to the up position the main landing gear doors close extinguishing the main gear UNSAFE lights Emergency Extension If the hydraulic system fails or an electrical fault occurs in the landing gear system an emergency air bottle supplies pneu matic pressure to extend the landing gear The landing gear selector should be in the DN position to prevent ina...

Page 355: ...t to the computer amplifier The computer amplifier in turn applies a clockwise or counterclockwise sig nal to the steering actuator The steering actuator clutch then engages the actuator gear train moves the nosewheel in the desired direction As groundspeed varies wheel speed inputs from the anti skid system modifies nosewheel steering authority At ground speeds less than 10 kts the system provide...

Page 356: ...espective pressure con trol valve to release braking pressure for that wheel This pre vents a possible skid When the wheel spins up and the rate of change voltage falls below the predetermined level the system reapplies braking pressure If a fault occurs in any of the anti skid system components the respective ANTI SKID GEN light illuminates to indicate the affe cted wheel s Emergency Braking If t...

Page 357: ...ke Pulling the PARKING BRAKE handle out with the toe brakes applied closes the mechanically operated parking brake valves Pressure trapped between the closed valves and the brake assemblies applies the parking brake During operation the antiskid disconnect switch opens to disable the anti skid sys tem ...

Page 358: ...4I 14 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 359: ...ency air bottle DC power Control Landing gear control handle Emergency gear extension handle TEST MUTE switch on landing gear panel SQUAT SW NOSE STEER and GEAR CBs Monitor LOCKED DN lights UNSAFE lights Landing gear horn Hydraulic pressure gage Emergency air pressure gage during pre flight Protection Circuit Breakers GEAR SQUAT SW NOSE STEER ...

Page 360: ... Data Power Source Hydraulic system Emergency air bottle DC power Control Brake pedals ANTI SKID switch Parking brake handle Emergency brake handle WRN LTS CB Monitor ANTI SKID GEN lights Hydraulic pressure gage Emergency air pressure gage during pre flight Protection Hydraulic fuses ANTI SKID CB ...

Page 361: ...Leerjet 35 36 Developed for Training Purposes 4J 1 October 2001 Oxygen System Oxygen System ...

Page 362: ...4J 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 363: ...ts overboard A contents discharge dislodges the green burst disc located on the right side of the nose or right side of the dorsal fin Mainte nance is required before flight if the disc is dislodged Distribution Oxygen flows under pressure from the oxygen cylinder s through the cylinder s pressure regulator and shutoff valve The regulator reduces normal cylinder pressure to approximately 60 to 80 ...

Page 364: ...ophone controlled by the OXY MIC ON OFF switch on the jack panel Passenger System With the PASS OXY knob in the NORM position and the PASS MASK knob in the AUTO position oxygen does not flow to the passenger oxygen masks at normal cabin altitudes If cabin altitude exceeds 14 000 750 ft the aneroid switch closes to supply 28V DC power to the oxygen solenoid valve The valve opens and oxygen flows at...

Page 365: ...Oxygen System Actual Time of Useful Consciousness Actual Altitude Time 15 000 to 18 000 ft 30 Minutes or More 22 000 ft 5 to 10 Minutes 25 000 ft 3 to 5 Minutes 28 000 ft 21 2 to 3 Minutes 30 000 ft 1 to 2 Minutes 35 000 ft 30 to 60 Seconds 40 000 ft 15 to 20 Seconds ...

Page 366: ...000 ft and 8 000 ft cabin altitude pro vides information for flight planning when supplemental oxygen is required To calculate oxygen duration for a less than fully charged system the following formula may be used Duration Duration from chart x system pressure 1 850 Cabin Altitude Available Time in Minutes 2 Crew 2 Crew 2 Pass 2 Crew 4 Pass 2 Crew 6 Pass 2 Crew 8 Pass 2 Crew 9 Pass 2 Crew 11 Pass ...

Page 367: ...t cabin altitude pro vides information for flight planning when supplemental oxygen is required To calculate oxygen duration for a less than fully charged system the following formula may be used Duration Duration from chart x system pressure 1 850 Cabin Altitude Available Time in Minutes 2 Crew 2 Crew 2 Pass 2 Crew 4 Pass 2 Crew 6 Pass 2 Crew 8 Pass 2 Crew 9 Pass 2 Crew 11 Pass 40 000 267 251 84 ...

Page 368: ...in altitude pro vides information for flight planning when supplemental oxygen is required To calculate oxygen duration for a less than fully charged system the following formula may be used Duration Duration from chart x system pressure 1 850 Cabin Altitude Available Time in Minutes 2 Crew 2 Crew 2 Pass 2 Crew 4 Pass 2 Crew 6 Pass 2 Crew 8 Pass 2 Crew 9 Pass 2 Crew 11 Pass 40 000 558 524 172 160 ...

Page 369: ...toff valve Oxygen solenoid valve Oxygen aneroid bypass shutoff valve Check valve long range and dorsal systems Crew mask NORM EMER selector Crew mask DILUTE 100 selector Crew mask NORMAL 100 selector Monitor Oxygen pressure gage s Overboard discharge indicator s Visual scan of passengers masks Crew oxygen flow indicator Visual monitoring of pressurization system Depressurization lighting Protectio...

Page 370: ...4J 10 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 371: ...Leerjet 35 36 Developed for Training Purposes 4K 1 February 1998 Garrett TFE731 2 2B Engine ...

Page 372: ...4K 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 373: ...Leerjet 35 36 Developed for Training Purposes 4K 3 February 1998 Powerplant Garrett TFE731 2 2B Engine Oil System ...

Page 374: ...4K 4 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 375: ...ectronic engine control EEC and the turbine temperature gauge Lubrication The engine driven oil pump s pressure element draws from the reservoir and provides it to the oil cooler under pressure through a pressure regulator and filter The pressure regulator maintains oil pressure at approximately 42 PSI The filter includes a bypass valve that opens at 30 to 40 PSID across the filter Filter bypass i...

Page 376: ...se After the oil lubricates cools and cleans the engine the oil pump scavenge elements draw oil from the bearing sumps cavities and casings and return it to the oil tank Ignition System With the STA RT GEN switch in STA RT advancing the throttle levers out of the cutoff position supplies 28V DC to the ignition exciter box through the throttle quadrant switch The ignition exciter box operates and s...

Page 377: ...r pin on the pump housing pops out The fuel computer provides the following functions Q start scheduling Q fuel scheduling Q ultimate overspeed protection Q surge valve control SPR manual fuel enrichment is a function of the fuel computer and is controlled by the SPR switch labeled Land R It is not available if the computer is in manual mode or is turned off Although SPR is not required for normal...

Page 378: ... mode the surge valve stays in the 1 3 open position Engine Controls The throttle levers are connected directly to the fuel control unit by flexible cable When the throttle is moved from CUTOFF to IDLE it mechanically opens the rotary shutoff valve in the fuel control unit The engine is also shut down in the same manner by moving the throttle lever from IDLE to CUTOFF With the fuel computer failed...

Page 379: ...owerplant Garrett TFE731 2 2B Monitor Fan speed N1 Turbine speed N2 Interstage turbine temperature ITT Oil pressure indicator Oil temperature gages Fuel flow indicator Annunciators LO OIL PRESS ENG CHIP FUEL CMPTR ENG SYNC light Starter engaged lights Protection Circuit breakers ...

Page 380: ...4K 10 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 381: ...EUMATIC LATCH SEQUENCING LATCH GEAR RACK TRANSLATING BEAM PNEUMATIC ACTUATOR ASSEMBLY FOLLOW UP NULLING CABLE TRANSLATING BEAM SPUR GEARBOX BLOCKER DOOR OPERATING ROD OUTBOARD PINION GEARBOX OUTBOARD PNEUMATIC LATCH GEAR RACK FOLLOW UP NULLING CABLE FLEXIBLE DRIVE SHAFT PRESSURE SWITCH PNEUMATIC LATCH VALVE BLEED VALVE HP BLEED AIR HP BLEED AIR ...

Page 382: ...4L 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 383: ...Leerjet 35 36 Developed for Training Purposes 4L 3 February 1998 Thrust Reversers Thrust Reverser System Dee Howard TR4000 ...

Page 384: ...4L 4 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 385: ... moving the ARM switches to the TEST position Illumination of the ARM annunciator indicates that the hydraulic isolation valve is operating correctly and hydraulic pressure is available to the control valve The system is armed when the aircraft is on the ground the throttle levers are at IDLE and the ARM switches are in the ARM position If these conditions are met pulling the thrust levers up and ...

Page 386: ...hold them closed The steady ARM light and the flashing DEPLOY light continue until one of the latches returns to a safe position or power is removed from the reverser system Automatic Throttle Retard The automatic throttle retard system is designed to minimize the effect of asymmetrical thrust should a thrust reverser deploy inadvertently in flight Anytime the stow solenoid valve is energized hydr...

Page 387: ...d drives the pinon gearboxes through a flexible drive shaft The pinon gearboxes then move the translating structure aft The reverser begins deploying When the translating structure reaches the full deployed position sequence latches disen gage from the gear racks The gear racks travel within the beam assemblies and are driven 5 5 inches farther aft The gear racks actuate the blocker doors to the c...

Page 388: ...e blocker doors move to the full open position As the gear racks enter their sequencing latches the latches engage to lock the translating beams and gear racks together The translating structure then continues moving forward toward the fully stowed position The latches engage and the nulling cable turns off bleed air to the pneumatic actuator The UNLOCK annunciators extinguish the thrust reverser ...

Page 389: ...lectrical power from the normal thrust reverser electrical system and applies power directly to both air on valves The valves open to supply bleed air pressure to the pneumatic actuators The pneumatic actuators then drive the translating structure to the stowed position With thrust levers in CUTOFF or above 70 power lever angle PLA the emergency stow system is inoperative ...

Page 390: ...4L 10 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 391: ... DC Control Thrust reverser levers Thrust reverser position and sequence switches Thrust reverser control valve ARM OFF TEST switches Squat switches Monitor Thrust reverser ARM and DEPLOY lights Reverse thrust lever position Protection Squat switches Thrust lever reverse idle deploy switches Thrust lever lockout solenoid ARM OFF TEST switches T R control and power CBs ...

Page 392: ...S Control Thrust reverser levers Squat switches Thrust lever switches Thrust reverser panel NORM EMER STOW and TEST switches Unlatched and deployed switches Bleed pressure switch Sequencing latches Follow up nulling cable Monitor BLEED AIR UNLOCK and DEPLOY lights Reverse thrust lever position Protection Squat switches Circuit breakers T R CONT T R EMER STOW T R POSN IND ...

Page 393: ...rative 5 6 Maximum Allowable Landing Gross Weight Determination Procedure 5 7 Maximum Allowable Landing Weight 5 8 Aircraft Loading Form 5 9 Weight and Balance Procedure 5 10 International Flight Planning 5 11 Frequently Used International Terms 5 11 International Operations Checklist 5 13 ICAO Flight Plan Form Completion Items 7 19 5 19 FAA Flight Plan Form Completion Instructions 5 29 ICAO Weath...

Page 394: ...5 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 395: ...Tel ___ _______ Hotel __________________________ Tel ___ _______ Catering _______________________ Tel ___ _______ FSS ___________________________ Tel ___ _______ Airport ________________________ Ident ___________ FBO ________________ Freq ______ Tel ___ _______ Hotel __________________________ Tel ___ _______ Catering _______________________ Tel ___ _______ FSS ___________________________ Tel ___ ...

Page 396: ... __________________________ Tel ___ _______ Catering _______________________ Tel ___ _______ FSS ___________________________ Tel ___ _______ Airport ________________________ Ident ___________ FBO ________________ Freq ______ Tel ___ _______ Hotel __________________________ Tel ___ _______ Catering _______________________ Tel ___ _______ FSS ___________________________ Tel ___ _______ Notes _______...

Page 397: ...f gross weight by the most restrictive of aircraft con ditions airport conditions and atmospheric conditions The flow chart below illustrates the steps to determine appropriate takeoff weight MAX LANDING WEIGHT PLUS FUEL BURN TO DESTINATION COMPARE AND SELECT LOWEST WEIGHT T O DISTANCE PERFORMANCE SECTION 5 MAX CERTIFIED T O WEIGHT LIMITATIONS SECTION 1 T O FLT PATH AND CLIMB GRADIENT OBSTACLE SEC...

Page 398: ...AKEOFF DISTANCE 1st SEGMENT GROUND ROLL BRAKE RELEASE REFERENCE ZERO GEAR UP 1500 FEET 400 FEET MINIMUM ENGINES BOTH ONE INOPERATIVE THRUST TAKEOFF THRUST MAX CONT THRUST AIRSPEED VARIABLE VARIABLE LANDING GEAR DOWN RETRACTED FLAPS TAKEOFF SETTING RETRACTION RETRACTED POSITIVE 2 4 1 2 MIN T O FLIGHT PATH CLIMB GRADIENTS V2 V1 VRVLOF V2 1500 FEET MINIMUM LEVEL 1 25 VSI 35 FEET TAKEOFF FLIGHT PATH 1...

Page 399: ...rfor mance landing field length requirements and approach speed values The flow chart below illustrates the steps to determining maximum allowable landing gross weight AIRPLANE CONDITIONS AIRPORT CONDITIONS ATMOSPHERIC CONDITIONS LANDING DISTANCE PERFORMANCE SECTION 5 LANDING WEIGHT LIMITS APPROACH CLIMB BRAKE ENERGY PERFORMANCE SECTION 5 MAXIMUM LANDING WEIGHT DESIGN STRUCTURAL LIMIT LIMITATIONS ...

Page 400: ...eight Landing Weight Limitation The maximum allowable landing weight is limited by the most restrictive of the fol lowing Structure Landing weight limit approach climb brake energy Landing distance LANDING DISTANCE EFFECTIVE RUNWAY LENGTH THRESHOLD APPROACH CLIMB ENGINE OUT 2 1 MIN GRADIENT 50 VREF 1 3 VSO ...

Page 401: ...00 MAC BASIC EMPTY WEIGHT Missing Additional Equipment Crew Provisions Fwd Provisions Mid Provisions Aft Provisions Toilet Water Miscellaneous BASIC OPERATING WEIGHT Baggage Fwd Baggage Aft Passenger Fwd Sidefacing Passenger Fwd Swivel Passenger Aft Swivel Passenger Divan ZERO FUEL WEIGHT Fuel Fuselage Tank ZERO WING TIPFUEL WEIGHT Fuel Wing Tanks Fuel Tip Tanks RAMP WEIGHT Taxi Burnoff Out of Tip...

Page 402: ...ight This ensures that the aircraft remains within limits as fuel is burned The following page numbers apply to Learjet 35A 36AAFM 102 and are only approximate for the 019 and 108 AFMs Action Where Record manufacturer s empty weight and moment 1 000 from aircraft weighing record AFM Weight and Balance page 1 or aircraft records Enter payload weights and moment AFM Payload Moments Charts Weight and...

Page 403: ...s Radio Service DEC General Declaration customs ETP Equal Time Point navigation FIC Flight Information Center FIR Flight Information Region GCA Ground Controlled Approach GEOMETER A clear plastic attachment to a globe that aids in making surface measurements and determining points on the globe IATA International Air Traffic Association IACO International Civil Aviation Organi zation MET See METAR ...

Page 404: ...ro feet when on the ground QNE Altimeter setting used at or above transition altitude FL 180 in U S this setting is always 29 92 QNH Altimeter setting that causes altime ter to read field elevation on the ground SITA Societe Internationale de Telecom munications Aeronautiques inter national organization provides global telecommunications network information to the air transport industry SPECI Avia...

Page 405: ...The IFIM is a collection of data from Aeronautical Information Publications AIP published by the civil aviation authorities CAA of various countries The following detailed checklist should be helpful in establish ing international operations requirements and procedures You may want to use it to prepare your own customized checklist for your organization s planned destinations I DOCUMENTATION PERSO...

Page 406: ...tenance records Certificates of insurance U S military and foreign Import papers for aircraft of foreign manufacture II OPERATIONS PERMITS Flight authorization letter Overflights Landing Advance notice Export licenses navigation equipment Military Customs overflight Customs landing rights SERVICES Inspection Customs forms Immigrations Agricultural disinfectant Ground Handling agents FBOs ...

Page 407: ...ets Maintenance Flyaway kit spares Fuel contamination check Financial Credit cards Carnets Letters of credit Banks Servicing air carriers Handling Fuelers Traveler s checks Cash COMMUNICATIONS Equipment VHF UHF HF SSB Headphones Portables ELTs etc Spares Agreements ARINC BERNA Switzerland SITA Stockholm ...

Page 408: ...rd computer update En route charts VFR IFR Plotting charts Approach charts area terminal NAT message current Flight plans Blank flight plans III OTHER PUBLICATIONS Operations manual International Flight Information Manual Maintenance manuals Manufacturer s sources World Aviation Directory Interavia ABC Airports International Directory MNPS NOPAC Customs Guide ...

Page 409: ...S Department of State o U S Department of Commerce o U S Customs Service o National Flight Data Center FAA Notams o FAA Office of International Aviation o FAA Aviation Security VI OTHER CONSIDERATIONS o Pre flight planner o Aircraft locks o Spare keys o Security devices o Commissary supplies o Electrical adapters razors etc o Ground transportation o Hotel reservations o NBAA International Feedback...

Page 410: ...5 18 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite IACO International Flight Plan Form ...

Page 411: ...es of one enter minutes of the other as well even if zeros Significant points should not be more than one hour apart Con sider entering overflight landing permissions after RMK in Item 18 Item 7 Aircraft Identification 7 characters maximum Insert A the aircraft registration marking or B aircraft operat ing agency ICAO designator followed by the flight identification A Insert only the aircraft regi...

Page 412: ...Specify in Item 15 Route the point s where a flight rules change is planned Type of Flight Insert one of the following letters to denote the type of flight when so required by the appropriate ATS author ity S if scheduled air service N if non scheduled air transport operation G if general aviation M if military X if other than the above Item 9 Number 1 or 2 characters and Type of Aircraft 2 to 4 c...

Page 413: ...following letters N if COM NAV approach aid equipment is not carried or is inoperative S if standard COM NAV approach aid equipment VHF RTF ADF VOR ILS or equipment prescribed by ATS authority is on board and operative and or insert one of the following letters to indicate correspond ing COMM NAV approach aid equipment is available and oper ative A not allocated O VOR B not allocated P not allocat...

Page 414: ...de and air craft ID transmission Item 13 Departure Aerodrome 4 characters and Time 4 characters Departure Aerodrome Insert one of the following ICAO four letter location indicator of the departure aero drome If no location indicator assigned insert ZZZZ then spec ify in Item 18 the name of the aerodrome preceded by DEP If flight plan submitted while in flight insert AFIL then specify in Item 18 th...

Page 415: ...es M 4 figures e g M0840 For uncontrolled VFR flights VFR Route Include changes of speed level and or flight rules For flights along designated ATS routes If the departure aerodrome is on or connected to the ATS route insert the designator of the first ATS route If the departure aerodrome is not on or connected to the ATS route insert the letters DCT followed by the point of joining the first ATS ...

Page 416: ...d not to exceed one hour s flight time Estab lish additional significant points as deemed necessary For flights operating predominantly in a north south direc tion define tracks by reference to significant points formed by the intersection of whole degrees of longitude with specified parallels of latitude that are spaced at 5 degrees Insert DCT between successive points unless both points are defi...

Page 417: ... 48N050W M082F290F350 C 48N050W M082F290PLUS C 52N050W M220F580F620 Item 16 Destination Aerodrome 4 charac ters Total Estimated Elapsed Time EET 4 characters Alternate Aerodrome s 4 char acters Destination aerodrome insert ICAO four letter location indica tor If no indicator assigned insert ZZZZ Total EET insert accumulated estimated elapsed time If no location indicator assigned specify in Item 1...

Page 418: ...o drome location indicator RIF DTA HEC KLAX Revised route subject to reclearance in flight Aircraft registration markings if different from aircraft I D in Item 7 REG N1234 SELCAL code SEL ________ Operator s name if not obvious from the aircraft I D in Item 7 OPR ________ Reason for special handling by ATS e g hospital air craft one engine inoperative STS HOSP STS ONE ENG INOP As explained in Ite...

Page 419: ... L life jackets with lights J life jackets with fluorescein ICAO Position Reporting Format Outside the U S position reports are required unless specifi cally waived by the controlling agency Initial Contact Frequency Change 1 Call sign 2 Flight level if not level report climbing to or descending to cleared altitude 3 Estimating next position at time GMT Position Report 1 Call sign 2 Position if po...

Page 420: ... TELEPHONE NUMBER AIRCRAFT HOME BASE 13 ALTERNATE AIRPORT S 12 FUEL ON BOARD HOURS MINUTES 18 COLOR OF AIRCRAFT CIVIL AIRCRAFT PILOTS FAR Part 91 requires you to file an IFR flight plan to operate under instrument flight rules in controlled airspace Failure to file could result in civil penality not to exceed 1 000 for each violation Section 901 of the Federal Aviation Act of 1956 as amended Filin...

Page 421: ...n IFR flight plan for flight in an air craft equipped with a radar beacon transponder DME equipment TACAN only equipment or a combination of both identify equipment capabil ity by adding a suffix to the AIRCRAFT TYPE preceded by a slant as follows X no transponder T transponder with no altitude encoding capa bility U transponder with altitude encoding capability D DME but no transponder B DME and ...

Page 422: ...DME DME and IRU position updating F FMS with DME DME position updating G Global Navigation Satelite System GNSS including GPS or Wide Area Augmentation Sys tem WAAS with enroute and terminal capabil ity R Required Navigational Performance The air craft meets the RNP type prescribed for the route segment s route s and or area con cerned J E with RVSM K F with RVSM L G with RVSM Q R with RVSM W RVSM...

Page 423: ...fier code or if unknown the airport name Include the city name or even the state name if needed for clarity Block 10 Enter estimated time enroute in hours and min utes Block 11 Enter only those remarks pertinent to ATC or to the clarification of other flight plan information such as the appropriate call sign associated with the designator filed in Block 2 or ADCUS Block 12 Specify the fuel on boar...

Page 424: ... that would normally have closed your flight plan Informa tion transmitted to the destination FSS consists only of that in Blocks 3 9 and 10 Estimated time enroute ETE will be converted to the cor rect estimated time of arrival ETA Optional Record a destination telephone number to assist search and rescue contact should you fail to report or cancel your flight plan within 1 2 hour after your estim...

Page 425: ...he following differences may remain in eff Horizontal visibility is reported in statute miles SM U S code and in meters in the ICAO code To avoid confusion the suffix SM follows the visibility value if it is reported U S code Additionally when forecast visibility in exceeds six statute miles the prefix P appears e g a visibility forecast greater than six statute miles Runway visual range RVR is re...

Page 426: ...t is in hectopascals millibars To avoid confusion a prefix is always assigned an A for a U S report or a Q for an ICAO report e g A2992 or Q1013 In the U S remarks RMKs precede recent RE weather and wind shear WS information reported at the end of METARs Low level windshear not associated with convective activity will appear in U S Canadian and Mexican TAFs ...

Page 427: ...300 27008KT 1 1 2SM SHRA BKN020 OVC040 TEMPO 0407 00000KT 1 2SM RABR VV004 FM1000 22010KT 1 2SM SHRA OVC020 BECMG 1315 20010KT P6SM NSW SKC KHPN ICAO location indicator The usual 3 letter identifiers we are familiar with are now preceeded by a K for the contigu ous United States Alaska and Hawaii will use 4 letter identifiers with PA and PH respectively Changes are planned to incorpo rate alphabet...

Page 428: ...refix indicates moderate If no significant weather is expected the group is omitted If the weather ceases to be significant after a change group the weather code is replaced by the code for no significant weather NSW BKN020CB Cloud coverage height type The first three letters indicate expected cloud coverage Cloud height is indicated by the second set of three digits these are read in hundreds of ...

Page 429: ... code for percent 40 is followed by a four digit code 2022 that indi cates a beginning time 20 and an ending time 22 to the nearest whole hour for probable weather conditions Only 30 and 40 probabilities are used less than these are not suffi cient to forecast 50 and above support the normal forecast TEMPO Temporary change followed by a four digit time Fore casts temporary weather conditions Indic...

Page 430: ...A BKN020 OVC040 Significant change expected from 2300 hours Surface winds 270 true direction at 8 kts Visibility one and one half statute mile Light showers of rain Broken clouds at 2 000 ft with a second overcast layer at 4 000 ft TEMPO 0407 00000KT 1 4SM RA BR VV004 Temporary between 0400 and 0700 hours Calm winds Visibility 1 4 statute mile Light rain and mist Indefinite ceiling vertical visibi...

Page 431: ...39 February 1998 Flight Planning BECMG 1315 20010KT P6SM NSW SKC Change to the forecast conditions between 1300 and 1500 hours Expected surface winds 200 true direction at 10 kts Visibility more than 6 statute miles No significant weather Clear skies ...

Page 432: ...or clouds TREND forecasts use many of the same codes as TAFs Most foreign countries may append a TREND to a METAR or SPECI In the U S however a TREND is not included in a METAR or SPECI The following example indicates how to read a METAR KHPN 201955Z 22015G25KT 2SM R22L 1000FT TSRA OVC010CB 18 16 A2990 RERAB25 BECMG 2200 24035G55 KHPN ICAO location indicator 201955Z Date and time of issuance METAR...

Page 433: ... degrees Celsius The first two digits 18 are observed air temperature the last two digits 16 are dew point temperature A temperature below zero is reported with a minus M prefix code e g M06 A2990 Altimeter setting In the U S A is followed by inches and hundredths in most other countries Q is followed by hec topascals i e millibars RERAB25 Recent operationally significant condition A two letter co...

Page 434: ...ing code BECMG is followed by a when sequence AT 2200 and the expected change e g surface winds at 240 true at 35 kts with gusts up to 55 kts NOTE For more information on METAR TAF consult the FAA brochure New Aviation Weather Format METAR TAF Copies may be obtained by writing to FAA ASY 20 400 7th Street S W Washington DC 20590 ...

Page 435: ...5 Fuel 6 6 Capacity 6 6 Aviation Gasoline 6 6 Approved Fuels 6 7 Fuel Additives 6 8 Electronic Fuel Computer Adjustment 6 10 Refueling 6 12 Hydraulic Fluid 6 16 Hydraulic Accumulator Preload 6 16 Landing Gear Struts 6 16 Landing Gear 6 17 Strut Extension 6 17 Tire Inflation 6 17 Oxygen 6 18 Windshield Anti Ice Fluid 6 18 Deicing Supplemental Information 6 19 Deicing 6 20 Post Deicing Procedures 6 ...

Page 436: ...6 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 437: ..._ _______ _______ _______ _______ _______ _______ _______ Engine Oil _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ Alcohol _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ ___...

Page 438: ...____ _______ _______ _______ _______ _______ _______ _______ _______ Oxygen _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ Other _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ _______ ______...

Page 439: ...0 Q Aeroshell Royco Turbine Oil 500 It is permissible to mix brands of approved oils Checking Adding Oil Oil should be checked shortly within one hour after engine shutdown If oil quantity seems overfilled motor engine 10 sec onds with starter Recheck If engine is cold and oil level appears low start engine and idle until stabilized Shutdown engine and recheck Access Door OPEN Filler Cap REMOVE Ta...

Page 440: ...ne Tank Learjet 35 35A Learjet 36 36A TOTAL USABLE TOTAL USABLE Tip without Recog Lt 182 8 GAL 691 8 L 181 3 GAL 626 2 L 182 8 GAL 691 8 L 181 3 GAL 626 2 L Tip with Recog L 176 9 GAL 669 6 L 175 3 GAL 663 5 L 176 9 GAL 669 6 L 175 3 GAL 663 5 L Wing 195 4 GAL 739 6 L 187 1 GAL 708 1 L 195 4 GAL 739 6 L 187 1 GAL 708 1 L Fuselage 201 5 GAL 762 7 L 200 0 GAL 757 0 L 380 4 GAL 1 439 8 L 379 4 GAL 1 ...

Page 441: ...ritish Fuel D ENG RD 2492 AVTUR 50 Canadian Fuel 3 GP 23 Chevron Jet Fuel A 1 Exxon Turbo A 1 Jet A 1 Kerosene Mobil Jet A 1 NATO F 34 Jet A 1 NATO F 35 Jet A 1 Richfield Jet A 1 Shell Jet A 1 Texaco Avjet A 1 Union Jet A 1 MIL T 83133 JP 8 EMS 53113 Jet B JP 4 EMS 53116 JP 5 ASTM Jet B Aircraft Turbine Fuel British Fuel D ENG RD 2486 AV TA G Canadian Fuel 3 GP 22 Chevron Jet Fuel B Chevron Jet Fu...

Page 442: ... gallons 397 4 liters of fuel Fuels having the required anti icing additive blended at the refinery need no additional treatment However some fuels do not have the required additive blended at the refinery Prior to refueling check with the fuel supplier to determine if the fuel contains the required anti icing additive Any approved or emergency fuels not containing the required anti icing additive...

Page 443: ...ntration is not to exceed 270 ppm CAUTION Ensure that anti icing additive is directed into the fuel stream and that additive flow starts after fuel flow starts and stops before fuel flow stops Do not allow concentrated additive to contact interior of fuel tank or aircraft painted sur faces WARNING Anti icing additive may be harmful if inhaled or swallowed Use adequate ventilation Avoid contact wit...

Page 444: ... fuel density adjustment selector has 11 positions num bered clockwise from lower left side of the dial The knob may be rotated one click either direction from the recom mended positions to compensate for individual engine char acteristics or installation effects WARNING Engine surge may occur if the recommended specific gravity adjustment is not adhered to If surge encountered refer to engine mai...

Page 445: ...ary 1998 Servicing Figure 6 1 Engine Electrical Fuel Computer NORMAL FUEL COMPUTER MODE SWITCH FUEL DENSITY ADJUSTMENT MANUAL FUEL SCHEDULING VIA ENGINE FUEL COMPUTERS ENGINE OVERSPEED PROTECTION WITH FUEL COMPUTERS NOT IN USE AV GAS 1 2 3 4 5 6 7 8 9 10 11 ...

Page 446: ...he fuselage tank Ensure aircraft in a designated fueling area fire equipment should be available Fuel Truck GROUND Aircraft BOND TO TRUCK Fuel Nozzle BOND TO AIRCRAFT Ground Cables CONNECT Tip Tank Filler Caps REMOVE WARNING Ground fuel truck to apron and to the nose gear uplatch spacer Ground fuel nozzle to tip tank ground jack prior to removing filler cap this precludes possible fire and or expl...

Page 447: ...Fuel Nozzle STOP FUEL FLOW Figure 6 2 Attaching Refueling Nozzle CAUTION Ensure additive is directed into the fuel stream Ensure the additive flow begins after the fuel flow starts Stop the additive flow before the fuel flow stops Do not allow con centrated additive to contact interior of fuel tank or aircraft painted surfaces BLENDER TUBE MUST BE ATTACHED SO THAT ADDITIVE DISCHARGES INTO THE FUEL...

Page 448: ...p Tank STOP AT 125 GAL Fuel to Opposite Tip Tank STOP AT 250 GAL Switch Sides STOP WITH FUEL IN BALANCE Filler Caps INSTALL Ground Cables REMOVE WARNING Do not completely fill one tank before adding fuel to the opposite side Fill both tanks simultaneously or main tain a maximum imbalance of 125 gallons between sides ...

Page 449: ... if installed CLOSE When desired quantity indicated or FULL light illuminated XFER OFF FILL Switch OFF Battery Switches OFF CAUTION Monitor filling operation If fuselage float switch does not stop fuel transfer into fuselage tank fuel overflows into the wing vent system and out through wing vent air scoops If this occurs Q stop fueling operation Q turn off transfer and battery switches Q drain fue...

Page 450: ...UID Reservoir Capacity 1 9 GALLONS 1 5 gallons available to engine driven pump 0 4 gallons available to auxiliary pump Hydraulic Accumulator Preload Type DRY AIR OR NITROGEN Hydraulic System 850 PSI Dee Howard Thrust Reverser 900 TO 1 000 PSI Landing Gear Struts Type DRY AIR OR NITROGEN AND MIL H 5606 HYDRAULIC FLUID ...

Page 451: ...ion Full Fuel No Baggage Passengers or Crew Main 3 TO 3 5 INCHES Nose 5 25 TO 5 75 INCHES Tire Inflation Unloaded Pressures Nose Wheel 100 TO 110 PSI Main Wheels 17 000 MTOGW 140 TO 150 PSI 18 000 MTOGW 151 TO 161 PSI 18 300 MTOGW 155 TO 165 PSI Loaded Pressures Add approximately 4 to above pressures ...

Page 452: ...Flite Oxygen Type MIL O 27210 TYPE I BREATHING OXYGEN Normal Pressure Range 1 500 TO 1 850 PSI Purge Required 0 PSI Windshield Anti Ice Fluid Type MIL O M 232 GRADE A METHYL ALCOHOL Electric Pump System Capacity 2 2 GALLONS Bleed Air Pressurized System Capacity 1 75 GALLONS ...

Page 453: ...ederal Aviation Regulations FARs prohibit takeoff with snow ice or frost adhering to the wings and control surfaces of the aircraft It is the responsibility of the pilot in command to ensure the aircraft is free of snow ice or frost before takeoff Failure to adequately deice the aircraft can result in seriously degraded aircraft performance loss of lift and erratic engine and flight instrument ind...

Page 454: ...luids Two types of anti icing deicing fluids are in commercial use SAE ISO Types I and II IV Type I fluids are used generally in North America Type II IV fluids also referred to as AEA Type II IV are used generally in Europe Type I fluids are unthickened glycol based fluids that are usu ally diluted with water and applied hot they provide limited holdover time Type II IV fluids are thickened glyco...

Page 455: ... direction Q operation on snow slush or wet surfaces Q operation near other aircraft equipment and buildings Q presence of deicing fluid and its type dilution strength and application method CAUTION Type II IV FPD generally should not be applied forward of the wing leading edges If used for deicing do not apply forward of cockpit windows Ensure that radome and cockpit windows are clean CAUTION If ...

Page 456: ...rcraft from top to bottom Avoid flushing snow ice or frost onto treated areas Start the deicing process by treating the horizontal stabilizer followed by the vertical stabilizer Con tinue by treating the fuselage top and sides Finally apply deic ing fluid to the wings Deicing fluid should not be applied to Q pitot static tubes static ports temperature probes AOA vanes or TAT probe Q gaps between c...

Page 457: ...ensure that they are free from ice snow and frost accumulations Q wing leading edges upper and lower surfaces Q vertical and horizontal stabilizer leading edges side pan els and upper and lower surfaces Q ailerons elevator and rudder Q flaps flap tracks and flap drive mechanisms Q ground and flight spoilers Q engine inlets and exhausts Q cockpit windows Q communication and navigation antennas Q fu...

Page 458: ...om sur faces or from between fixed and moveable surfaces or components Q Do not beat aircraft surface to loosen ice Q Avoid hot air temperatures above 200 F 93 3 C when using heat to melt snow ice or frost Q Use hot air carefully around windows Excessive temper atures on windows can crack or craze cold windows Q Exercise extreme care when using hot air to prevent damage to hoses painted surfaces a...

Page 459: ...e diluted deicing fluid for anti icing Melting snow will further dilute the solution and refreezing can occur Q After deicing the aircraft nose wipe all remaining traces of fluid from area in front of windshield CAUTION After deicing wings and empennage check flap wells for slush and or ice accumulations Ensure that all drain holes are clear CAUTION Check all primary flight control surfaces by han...

Page 460: ...adome pitot tubes static ports AOA probes vanes air inlets and exhausts and antennas Q engines inlet Q landing gear wheels brakes tires wheel well and doors Taxi During taxi on ice or snow covered surfaces observe the following Q Maintain a greater than normal distance between aircraft Q Do not use reverse thrust If reverse thrust used rein spect the aircraft for snow ice and frost accumulations Q...

Page 461: ...d observe stable engine operation before brake release Q After setting takeoff throttle verify that LP RPM and other engine indications are normal Q Rotate to normal takeoff attitude at VR and not before Approach and Landing During the descent approach observe the following Q Anticipate use of engine and wing anti icing Q Arm AUTO ground spoilers for landing At touchdown deploy manual speedbrakes ...

Page 462: ...6 28 Developed for Training Purposes Leerjet 35 36 February 2001 CAE SimuFlite ...

Page 463: ...eloped for Training Purposes 7 1 February 1998 Emergency Information Emergency Information Table of Contents The ABCs of Emergency CPR 7 3 Heart Attack 7 4 Choking 7 5 Emergency Equipment Record 7 6 Emergency Exits 7 7 ...

Page 464: ...7 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Airway Breathing Circulation Reproduced with permission MedAire Inc ...

Page 465: ...h over victim s mouth NOTE A pocket mask can be used instead but proper head position and air tight seal must be maintained CIRCULATION Q Locate carotid artery pulse hold 10 seconds If no pulse Q Begin external chest compressions by locating hand position two fingers above notch and placing heal of hand on breastbone Q Perform 15 compressions of 11 2 to 2 inches at a rate of 80 to 100 compressions...

Page 466: ...r pain in center of chest behind breastbone Q Sweating Q Nausea Q Shortness of breath Q Feeling of weakness Actions for Survival Q Recognize signals Q Stop activity and lie or sit down Q Provide oxygen if available Q If signals persist greater than two minutes get victim to medical assistance Reproduced with permission MedAire Inc ...

Page 467: ...r abdominal thrusts 1 stand behind victim wrap arms around victim s waist 2 place fist of one hand knuckles up in upper abdo men 3 grasp fist with opposite hand 4 press fist into upper abdomen with quick inward and upward thrusts 5 perform maneuver until foreign body is expelled Q provide supplemental oxygen if available If victim is pregnant or obese perform chest thrusts instead of abdominal thr...

Page 468: ...eerjet 35 36 February 1998 CAE SimuFlite Emergency Equipment Record EMERGENCY EQUIPMENT LOCATION DATE LAST SERVICED First Aid Kit Fire Extinguisher s Fire Axe Life Raft Life Vests Seat Pockets Theraputic Oxygen Overwater Survival Kit Other ...

Page 469: ...ward for quick egress Q To open an emergency exit from outside the aircraft push the release plate above the window The window unlocks and falls into the cabin Q To open an emergency exit from inside the aircraft pull the red release handle above the window The window unlocks and falls into the cabin A fabric handle facilitates evacuation ...

Page 470: ...7 8 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 471: ...ce Conversion 8 3 Meters Feet 8 3 Statute Miles Kilometers Nautical Miles 8 4 Kilometers Nautical Miles Statute Miles 8 5 Weight Conversion 8 6 Fuel Weight to Volume Conversion 8 7 Volume Conversion 8 8 Temperature Conversion 8 9 International Standard Atmosphere ISA 8 10 Altimeter Setting Conversion 8 11 Cabin Altitude 8 12 ...

Page 472: ...8 2 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite ...

Page 473: ... 2908 61 2 6 58 91 3 9 87 1 22 4 13 16 1 52 5 16 45 1 83 6 19 74 2 13 7 23 04 2 44 8 26 33 2 74 9 29 62 3 1 10 32 9 6 1 20 65 8 9 1 30 98 7 12 2 40 131 6 15 2 50 165 5 18 3 60 197 4 21 3 70 230 4 24 4 80 263 3 27 4 90 296 2 31 100 329 61 200 658 91 300 987 122 40 1316 152 500 1645 183 600 1974 213 700 2304 244 800 2633 274 900 2962 305 1000 3291 ...

Page 474: ... 3 1 62 2 49 4 2 16 3 11 5 2 70 3 73 6 3 24 4 35 7 3 78 4 97 8 4 32 5 59 9 4 86 6 21 10 5 40 12 43 20 10 80 18 64 30 16 20 24 85 40 21 60 31 07 50 27 00 37 28 60 32 40 43 50 70 37 80 49 71 80 43 20 55 92 90 48 60 62 14 100 54 00 124 27 200 107 99 186 41 300 161 99 248 55 40 215 98 310 69 500 269 98 372 82 600 323 98 434 96 700 377 97 497 10 800 431 97 559 23 900 485 96 621 37 1000 539 96 ...

Page 475: ... 7 41 4 4 60 9 26 5 5 75 11 11 6 6 90 12 96 7 8 06 14 82 8 9 21 16 67 9 10 36 18 52 10 11 51 37 04 20 23 02 55 56 30 34 52 74 08 40 46 03 92 60 50 57 54 111 12 60 69 05 129 64 70 80 56 148 16 80 92 06 166 68 90 103 57 185 20 100 115 08 370 40 200 230 16 555 60 300 345 24 740 80 40 460 32 926 00 500 575 40 111120 600 690 48 1296 40 700 805 56 1481 60 800 920 64 1666 80 900 1305 72 1852 00 1000 1150...

Page 476: ... 4 40 2 91 6 61 1 36 8 82 4 1 81 11 02 5 2 27 13 23 6 2 72 15 43 7 3 18 17 64 8 3 63 19 84 9 4 08 22 0 10 4 5 44 1 20 9 1 66 1 30 13 6 88 2 40 18 1 110 2 50 22 7 132 3 60 27 2 154 3 70 31 8 176 4 80 36 3 198 4 90 40 8 220 100 45 441 200 91 661 300 136 882 40 181 1102 500 227 1323 600 272 1543 700 318 1764 800 363 1984 900 408 2205 1000 454 ...

Page 477: ... 9 7 2 1 5 10 67 5 7 10 18 12 5 10 8 3 0 20 134 11 4 20 36 25 0 20 16 4 5 30 201 17 1 30 54 37 5 30 24 6 0 40 268 22 8 40 72 50 0 40 32 7 5 50 335 28 5 50 90 62 5 50 40 9 0 60 402 34 2 60 108 75 0 60 48 10 5 70 469 39 9 70 126 87 5 70 56 12 0 80 536 45 6 80 144 100 0 80 64 13 5 90 603 51 3 90 162 113 5 90 72 15 100 670 57 100 180 125 100 80 30 200 1340 114 200 360 250 200 160 45 300 2010 171 300 5...

Page 478: ...20 91 0 24 9 30 36 0 7 9 30 113 5 6 6 30 136 4 33 3 40 48 0 10 6 40 151 4 8 8 40 181 8 41 6 50 60 1 13 2 50 189 2 11 0 50 227 3 50 0 60 72 1 15 9 60 227 1 13 2 60 272 8 58 3 70 84 1 18 5 70 265 0 15 4 70 318 2 66 6 80 96 1 21 1 80 302 8 17 6 80 363 7 74 9 90 108 1 23 8 90 340 7 19 8 90 409 1 83 100 120 26 4 100 379 22 100 455 167 200 240 53 200 757 44 200 909 249 300 360 79 300 1136 66 300 1364 33...

Page 479: ...15 47 117 28 18 27 17 26 15 25 13 2 28 1 30 0 32 1 34 4 25 3 27 20 68 21 70 22 72 23 73 18 64 19 66 42 108 43 109 44 111 45 113 40 104 41 106 9 16 8 18 7 19 6 21 5 23 12 54 13 55 14 57 15 59 16 61 17 63 34 93 35 95 36 97 37 99 38 100 39 102 C F C F C F C F C F 40 40 39 38 18 0 17 1 4 39 5 41 26 79 27 81 48 118 49 120 38 36 37 35 16 3 15 5 6 43 7 45 28 82 29 84 50 122 51 124 36 33 35 31 14 7 13 9 8...

Page 480: ...00 13 0 12 000 8 8 23 000 30 5 2 000 11 0 13 000 10 7 24 000 32 5 35 000 54 2 3 000 9 1 14 000 12 7 25 000 34 5 4 000 7 1 15 000 14 7 26 000 36 5 37 000 56 5 5 000 5 1 16 000 16 7 27 000 38 4 38 000 56 5 6 000 3 1 17 000 18 7 28 000 40 4 39 000 56 5 7 000 1 1 18 000 20 6 29 000 42 4 40 000 56 5 8 000 0 8 19 000 22 6 30 000 44 4 41 000 56 5 9 000 2 8 20 000 24 6 31 000 46 3 42 000 56 5 10 000 4 8 2...

Page 481: ...7 55 27 58 27 61 27 64 27 67 27 70 27 73 940 27 76 27 79 27 82 27 85 27 88 27 91 27 94 27 96 27 99 28 02 950 28 05 28 08 28 11 28 14 28 17 28 20 28 23 28 26 28 29 28 32 960 28 35 28 38 28 41 28 44 28 47 28 20 28 53 28 56 28 58 28 61 970 28 64 28 67 28 70 28 73 28 76 28 79 28 82 28 85 28 88 28 91 980 28 94 28 97 29 00 29 03 28 06 29 09 29 12 29 15 29 18 29 21 990 29 23 29 26 29 29 29 32 29 35 29 38...

Page 482: ...8 12 Developed for Training Purposes Leerjet 35 36 February 1998 CAE SimuFlite Cabin Altitude ...

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