Learjet 35 Learjet3 05 Exnorm

Leerjet 35/36 Developed for Training Purposes 2B-1February 2004

Expanded NormalsTable of ContentsChecklist Usage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-3

Normal Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-4Through-Flight Procedures(Both Engines Shut Down) . . . . . . . . . . . . . . . . . . . . . . . 2B-4

Before Starting Engines . . . . . . . . . . . . . . . . . . . . . . . . . 2B-5Starting Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-28Before Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-33Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-37Before Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-41Runway Lineup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-42Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-42After Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-43Climb. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-45Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-46Descent. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-46Transition Level. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-46Approach. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-47Before Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-48Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-49Go-Around/Missed Approach . . . . . . . . . . . . . . . . . . . . 2B-49After Landing/Clearing Runway . . . . . . . . . . . . . . . . . . 2B-50Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-51Quick Turnaround . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-53Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-53Runway Lineup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-54

2B-2 Developed for Training Purposes Leerjet 35/36February 2004

CAE SimuFlite

After Takeoff/Traffic Pattern . . . . . . . . . . . . . . . . . . . . . 2B-54Before Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-55Parking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-55Mooring. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-56Towing/Turning Radius . . . . . . . . . . . . . . . . . . . . . . . . . 2B-58Towing/Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-59Nose Gear Towing . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-59Main Gear Towing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-60Taxiing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-62Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-63Restoring After Storage. . . . . . . . . . . . . . . . . . . . . . . . . 2B-72

Hot Weather Operations . . . . . . . . . . . . . . . . . . . . . . . . 2B-76Exterior Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-76Engine Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-76Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-77Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-77Shutdown and Postflight . . . . . . . . . . . . . . . . . . . . . . . . 2B-77

Cold Weather Operations . . . . . . . . . . . . . . . . . . . . . . . 2B-78Preflight Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-78Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-81Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-82After Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-83Before Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-83Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2B-84Crosswind Consideration . . . . . . . . . . . . . . . . . . . . . . . 2B-84After Clearing Runway . . . . . . . . . . . . . . . . . . . . . . . . . 2B-85Shutdown and Postflight . . . . . . . . . . . . . . . . . . . . . . . . 2B-85Deicing Supplemental Information . . . . . . . . . . . . . . . . 2B-86


Expanded Normal Procedures

Checklist UsageNormal ProceduresTasks are executed in one of two ways:

as a sequence that uses the layout of the cockpit controls and indicators as cues (i.e., flow pattern)

as a sequence of tasks organized by event rather than panel location (e.g., After Takeoff, Gear RETRACT, Yaw Damper ENGAGE).

Placing items in a flow pattern or series provides organizationand serves as a memory aid.

A challenge-response review of the checklist follows executionof the tasks; the PM calls the item, and the appropriate pilotresponds by verifying its condition (e.g., Engine Anti-Ice (challenge) ON (response).

Two elements are inherent in execution of normal procedures:

use of either the cockpit layout or event cues to prompt correct switch and/or control positions

use of normal checklist as done lists.


CAE SimuFlite

Normal ProceduresThrough-Flight Procedures(Both Engines Shut Down)Normal preflight procedures (all checklist items) must beaccomplished prior to takeoff at the original departure point of aflight. At each intermediate stop of flight, where both enginesare shut down, the Through-Flight Checklist may be used forpreflight provided certain criteria are met during a stop. In thefollowing section, procedures marked with this symbol ()denote through-flight checklist items. When permitted, accomplishment of all through-flight Checklist items fulfills aminimum 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 than three (3) hours have elapsed between engine shutdown and engine start.

Extreme weather conditions (heavy precipitation, ice, snow, extreme cold, etc.) have not occurred which would change the preflight status of the aircraft.

For intermediate stops with one or no engine shut down, com-pletion of the Quick Turnaround Procedure (2B-53) in this sec-tion provides the minimum preflight requirements.



Before Starting EnginesUpon entering the cockpit, the following switch positions shouldbe verified before starting any checks:

Start-Gen Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFLanding Gear Switch . . . . . . . . . . . . . . . . . . . . . . . . . . DOWNFuel Jettison Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFCabin Air Damper Control Knob/Switch . . . . . AS DESIREDThe damper must be in the closed position for the optional aux-iliary heat to work and to allow the Freon air conditioner to re-circulate cool air in the passenger compartment. On aircraftwith Cabin Blower switch, the OFF position diverts airflowabove headliners at all times except during auxiliary heatingoperation.

Emergency Exit . . . . . . . . . . . . . . . . . . . . . . . AISLE CLEAR/ HANDLE UNOBSTRUCTED

Oxygen Masks/Valves/Pressure . . . . . . . . . 100%/CHECKEDCrew Masks . . . . . . . . . . . . . . . . . . . . . . . . ADJUST/CHECKEnsure that the mask control selector valve is set to 100%.On Scott ATO masks, check harness inflation.

PASS MASK Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTOPASS OXY Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORMOXYGEN PRESSURE Gage . . . . . . . . . . . . . . . . . . .CHECKVerify that pressure is in the green band on the indicator(1550-1850 PSI).

Circuit Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDThe left and right circuit breaker panels should be checkedvisually and not by rubbing the hand across the row ofbreakers. Always use a flashlight at night.

NOTE: Accomplish flow pattern checks, then use the Before Starting Engines checklist as a done list.


CAE SimuFlite

Control Lock. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOWEDRemove and stow.

Seat Belts/Harnesses/Seats . . . . . . . SECURED/ADJUSTEDAdjust the seat belt for a snug fit. Ensure the shoulder har-ness are latched to the buckle. Ensure seat is adjusted sothat full travel can be obtained to reach all controls.

Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDEnsure that shoes do not hinder movement of pedals duringfull rudder pedal movements.

Audio Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDAlternate Static Source Switch (FC 200) . . . . . . . . CLOSEDPilots Altimeter (FC 200) . . . . . . . . . . . . . . . . . . . . . . NORMStatic Source Switch (FC 530) . . . . . . . . . . . . . . . . . . . BOTHAvionics Master Switch (if installed) . . . . . . . . . . . . . . . OFFFuel Computers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Batteries (Main Aircraft Batteries) . . . . . . . . . . . . . . . . . . OFFEmergency Power System . . . . . . . . . . .CHECKED AND ON

EMER PWR BAT 1 SwitchSTBYCheck attitude gyro for starting and erection. AmberEMER PWR annunciator illuminates.

EMER PWR BAT 2 Switch (if installed) . . . . . . . . . . . . . . ONCheck both amber EMER PWR annunciators illuminateand that equipment powered by second emergency battery is on.

EMER PWR BAT 1 Switch . . . . . . . . . . . . . . . . . . . . . . . . ONCheck attitude gyro for operation. Amber EMER PWRannunciator and green gear LOCKED DN lights illuminate.



Both EMER PWR Switches . . . . . . . . . . . . . . . . . . . . . . . ONCheck attitude gyro for starting and erection.

Batteries (Main Aircraft Batteries) . . . . . . . . . . . . CHECKED AND ON

Setting battery switches to ON also energizes the windshield ice detect annunciators. Check turbine temperature (ITT), fan speed (N1), and turbine speed(N2) to ensure red OFF flags are retracted.

BAT 1 Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONCheck for proper voltage. Amber EMER PWR annuncia-tor(s) extinguish.

BAT 2 Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONBAT 1 Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Check for proper voltage.

Both BAT Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONGPU (if desired) . . . . . . . . . . . . . . . CONNECTED/CHECKED

Ensure unit is regulated to 28V DC and limited to 1,100Amaximum and 500A minimum.

Inverters . . . . . . . . . . . . . . . . . . . . . CHECKED/PRIMARY ONPRI Inverter Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Ensure the red PRI INV annunciator is extinguished andAC volts in green arc.

NOTE: With lead-acid batteries, do not attempt a battery start with less than 24V DC on each battery at 70F (21C) or below, or less than 25V DC on each battery at 110F (43C) or above. Interpolate for temperature seen 70F (21C) and 110F (43C).With nickel-cadmium batteries, do not attempt a battery start with less than 2V DC each battery.


CAE SimuFlite

AC Bus Switch . . . . . . . . . . . . . . . . . . . . . . . PRI THEN SECCheck AC volts in green arc in both positions. The ACvoltage does not change if the circuit is functioning prop-erly

SEC Inverter Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONPRI Inverter Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Check the SEC INV annunciator is extinguished and ACvolts in green arc.

Aircraft with auxiliary inverter:AUX INVERTER Switch . . . . . . . . . . . . . . . . . . . . . . . . . . ONSEC Inverter Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Ensure the AUX INV annunciator is extinguished and ACvolts in green arc.

PRI Inverter Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONSEC and AUX INVERTER Switches. . . . . . . . . . . . . . . . OFF

In Normal/Out Defog Knob (if installed) . . . . . . . . . . . . . . INAnti-Skid. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONEmergency Air (1,800 PSI minimum) . . . . . . . . . . CHECKEDHydraulic 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) illuminates.Emer Brake. . . . . . . . . . . . . . . . . . . . . . . . . . PULL/CHECKED

Pull the handle out of the recess then return. DO NOT pushthe handle downward, as it may introduce emergency brakeair into the hydraulic system.

Hydraulic Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF



Warning Light Test Switch . . . . . . . . . . . . . . . . DEPRESSEDCheck annunciators, MSTR WARN, ENG FIRE PULL T-handle, ARMED, ANTI-SKID, GEN, AIR IGN, STARTENGAGED, and fuel panel lights illuminate. Check the auto-matic warning light dimming by covering the photoelectriccells during daylight and with a flashlight in darkness.

Landing Gear Switch/Warning . . . . . . . . . . .DOWN/TESTEDGear Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWNEnsure three green lights illuminate.

Gear Warning Test/Mute Switch (if installed) . . . . . . . . TESTThe three red unsafe lights illuminate and the warning hornsounds.

Right Thrust Lever Mute Switch (if installed) . . . . DEPRESSIf the optional horn silence switch is installed, depress it tocut out the gear horn while holding the gear warning testswitch in TEST.

Fire Detect System . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDRotary Test Switch . . . . . . . . . . . . . . . . . . . . . . . . . FIRE DETTest Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSCheck that both the left and right ENG FIRE PULL T-handlelights flash. This indicates continuity of the detect system.

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASEFuel Balance/Quantities . . . . . . . . . . . . . . . . . . . . CHECKEDFuel Counter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZEROJet Pumps. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONStandby Pumps/Crossflow . . . . . . . . . . . . . . . . . . CHECKED

Left Standby Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONCheck that the left low fuel pressure annunciator extin-guishes.


CAE SimuFlite

Crossflow Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPENCheck that the amber disagreement light cycles properly,the right low fuel pressure annunciator extinguishes, andfuel crossflow annunciator illuminates.

Right Standby Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONEnsure light in switch (if applicable) illuminates.

Left Standby Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFBoth fuel pressure annunciators remains extinguished andlight in switch (if applicable) extinguishes.

Crossflow Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSEThe left fuel pressure annunciator illuminates.

Right Standby Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFRight low fuel pressure annunciator illuminates.

Crossflow/XFER-FILL/FUS VAL Switches . . . . . . . CLOSED/ .................................................................... ........... OFF/OFFIf external power not used:One Engine. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START

Go to Engine Start in Starting Engines checklist, page 2B-28.

Warning Systems Check. . . . . . . . . . . . . . . . . .COMPLETEDTest the warning system using the rotary test switch.

Cabin Altitude Warning:Rotary Test Switch . . . . . . . . . . . . . . . . . . . . . . . . CABIN ALTTest Button . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS/HOLDThe cabin altitude warning horn sounds.

Horn Silence Switch . . . . . . . . . . . . . . . . ON MOMENTARILYThe cabin altitude warning horn ceases for approximately 60seconds.

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASEMach Warning/Stick Puller:

Rotary Test Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . .MACH



Check pitch trim within takeoff segment on pitch trim indica-tor.

Left Stall Warning Switch . . . . . . . . . . . . . . . . . . . . . . . . . ONAn inverter must be on.

Test Button . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLD

FC 200 Autopilot:Hold the control column at mid-travel. The overspeed warning sounds and the stick puller moves the control column aft with an approximate 18 lbs force.

FC 530 Autopilot:Control column moves aft with approximately 18 poundsforce and the aural overspeed warning sounds. Afterapproximately 1/2 second, the puller and overspeed warning-ceases. After approximately 1/2 additional second, the pullerand overspeed warning activate again and then cease. Onall S/Ns through 35-670 and 36-063, after approximatelyanother 1/2 second, the overspeed warning sounds again tocheck the 300 KIAS speed switch in the ADU.

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASE

Mach Trim:Rotary Test Switch . . . . . . . . . . . . . . . . . . . . . . .MACH TRIMTest Button . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDVisually check the pitch trim indicator. Depress and hold thetest button. The pitch trim system runs nose-up for one tothree seconds and then stops. The Mach trim annunciatorilluminates and the overspeed warning horn sounds.Release the test button. Mach trim annunciator extinguishesand horn ceases.

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASE

Stall Warning:Aircraft with Standard Wing, refer to AFM for check.


CAE SimuFlite

With FC 200 Autopilot:During heavy wind conditions, it may be necessary to headaircraft into the wind to prevent wind from blowing stall warning vanes up.

Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPSTALLWARNING Switches. . . . . . . . . . . . . . . . . . . . . . . . ONTEST Selector Switch. . . . . . . . . . . . . . . . . . . . . . . . L STALLTest Button . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDThe pilots angle-of-attack indicator needle begins to sweepfrom the green segment to the red segment. As the needlepasses the green-yellow margin, the shaker actuates andthe L STALL warning annunciator flashes. As the needleadvances to the red segment, the pusher activates briefly,then stops. The L STALL warning annunciator illuminatessteadily just prior to or at pusher actuation. After pusherstops, the needle sweeps back and remains in the yellow orgreen segment. Pusher release must occur or the test hasfailed.

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASETEST Selector Switch. . . . . . . . . . . . . . . . . . . . . . . . R STALLTest Button . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDThe operation is identical to that of L STALL above exceptneedle sweeps copilots angle-of-attack indicator, and the R STALL warning annunciator flashes.

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASEWith STALL WARNING switches in ON, steady illuminationof the L or R STALL warning annunciator indicates a malfunction except during pusher actuation or system test.

Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DNCheck that both angle-of-attack indicators shift positionthree times as flaps are lowered to full down.

STALL WARNING Switches . . . . . . . . . . . . . . . . . . . . . . OFF



With FC 530 Autopilot:

During heavy wind conditions, it may be necessary to head aircraft into the wind to prevent wind from blowing stall warning vanes up.Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPSTALL WARNING Switches . . . . . . . . . . . . . . . . . . LEFT ONEnsure L STALL annunciator extinguishes.

STALL WARNING Switches . . . . . . . . . . . . . . . . . LEFT OFFSTALL WARNING Switches . . . . . . . . . . . . . . . . . RIGHT ONEnsure R STALL annunciator extinguishes

STALL WARNING Switches . . . . . . . . . . . . . . . . . . LEFT ONTEST Selector Switch . . . . . . . . . . . . . .ROTATE TO L STALLTEST Button . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDThe nudger monitor horn sounds for approximately one sec-ond and then the pilots angle-of-attack indicator needlebegins to sweep from the green segment to the red seg-ment. As the needle passes the green-yellow margin, theshaker activates, the nudger actuates, and the L STALLwarning annunciator flashes. High-frequency vibration of thecontrol 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 redsegment, the pusher activates briefly, then stops. The LSTALL warning annunciator illuminates steadily just prior toor at pusher actuation. After pusher stops, the needlesweeps back and remains in the yellow or green segment.

WARNING: The action of the nudger verifies operation ofthe pitch torquer prior to pusher actuation. If, during groundtest, the shaker is not accompanied by the nudger (thenudger monitor horn will sound) do not dispatch. If, dur-ing flight, the shaker is not accompanied by the nudger (thenudger monitor horn will sound) do not decelerate fur-ther.


CAE SimuFlite

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASETEST Selector Switch. . . . . . . . . . . . . ROTATE TO R STALLTest Button . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDThe operation is identical to that of L STALL above exceptneedle sweeps copilots angle-of-attack indicator, and the R STALL warning annunciator flashes.

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASEWith STALL WARNING switches in ON, steady illuminationof the L or R STALL warning annunciator indicates a mal-function except during pusher actuation or system test.

With either control wheel master switch (MSW) depressed:TEST Selector Switch. . . . . . . . . . . . . . . . . . . . . . . . R STALLTest Button . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDVerify that the nudger and pusher do not actuate as theangle-of-attack indicator moves through the band. Thenudger monitor horn sounds if the needle stays in the yel-lowsegment.

Test ButtonRELEASEFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DNEnsure that both angle-of-attack indicator needles make atleast one significant shift in position as flaps are lowered.

STALLWARNING Switches. . . . . . . . . . . . . . . . . . . . . . . OFFCurrent Limiter (if installed):

Rotary Test Switch . . . . . . . . . . . . . . . CURRENT LIMITER LTest Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSThe green indicator light illuminates if the left current limiteris functional.

Rotary Test Switch . . . . . . . . . . . . . . . CURRENT LIMITER RThe green indicator light illuminates if the right current limiteris functional. Repeat the Current Limiter test after bothengines have been started.



No Smoking/Seat Belt Sign. . . . . . . . . . . . . . . . . . . . . . . . ONCabin Air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFPressurization . . . . . . . . . . . . . AUTO/ALTITUDE/RATE SET

AUTO-MAN Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTOThe switch is normally in AUTO unless a malfunction hasoc-curred.

Cabin Altitude Controller . . . . . . . . . . . . . . . . . . . . . . . . . SETSet controller to the cruise flight level. If on a short leg, setcabin altitude to landing field elevation.

Cabin Rate-of-Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . SETThe 9 oclock position provides approximately a 500 FPMcabin altitude cabin rate.

Temp Controls . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIREDBleed Air Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONEmer Pressurization Switches (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . GUARD DOWNTOLD Data/Bugs . . . . . . . . . . . . . . . . . . . . .COMPUTED/SETIce Detect Lights . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED

Emergency Gyro . . . . . . . . . . . . . . . . . . . . . . . . . . UNCAGEDCVR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TESTDrag Chute Handle (if installed) . . . . . . . . . . . . . . . STOWEDTrim/Pitch, Roll, Yaw/Switches . . . . . . . . . . .CHECKED/SET/.............................................................................. PRIMARY

NOTE: Check illuminated by placing an object between the lights and windshield. Use care to prevent scratching wind-shield when checking ice detect lights.

NOTE: Refer to AFM for minimum trim systems preflight check.


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Trim Check (FC 200 Autopilot):PITCH TRIM Selector Switch . . . . . . . . . . . . . . . . . . . . . SECPedestal NOSE DN-OFFNOSE

UP Switch . . . . . . . . . . . . . . . . . . . . . . . HOLD TO NOSE UP/............................................................. .THEN TO NOSE DNCheck for horizontal stabilizer movement in both directions.Stabilizer movement is at approximately one-half the rate ofPRI trim.

Either Control Wheel Trim Switch . . . . OPERATE NOSE UP/.................................................................. THEN NOSE DNTrim motion should not occur.

PITCH TRIM Selector Switch . . . . . . . . . . . . . . . . . . . . . OFFACTUATE the following:Q pilot and copilot control wheel trimQ trim arming switchesQ pedestal NOSE DN-OFF-NOSE UP switchEnsure that no trim motion occurs.

PITCH TRIM Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRIPedestal NOSE DN-OFF-NOSE UP Switch . . . . . NOSE UP/. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . NOSE DNEnsure trim motion does not occur.

Pilot Control Wheel Trim Switch . . . . . . . . . . . . . . .OPERATEWithout depressing arming button, move switch NOSE UP,NOSE DN, LWD, and RWD. Check that trim motion doesnot occur.

Arming Button (without displacing switch . . . . . . . DEPRESSEnsure trim motion does not occur.

Pilot Control Wheel Trim Switch . . . . . . . . . . . . . . .OPERATEWhile depressing arming button, move switch NOSE UP,NOSE DN, LWD, and RWD. Ensure trim motion occurs in alldirections.

Copilot Control Wheel Trim Switch . . . . . . . . . . . . .OPERATEWithout depressing arming button, move switch NOSE UP,NOSE DN, LWD, and RWD. Ensure trim motion does notoccur.



Arming Button (without displacing switch) . . . . . . DEPRESSEnsure trim motion does not occur.

Copilot Control Wheel Trim Switch . . . . . . . . . . . . OPERATEWhile depressing arming button, move switch NOSE UP,NOSE DN, LWD, and RWD. Ensure trim motion occurs in alldirections.

Copilot Control Wheel Trim Switch . . . . . . . . . . . . . . . . .TRIMPilot Control Wheel Trim Switch . . . . . . . . . TRIM OPPOSITEEnsure pilots trim overrides copilots trim. Repeat for eachtrim position.

Pilot Control Wheel Trim Switch . . . . . . . . . . . . . . . . NOSE UPPilot MSW . . . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLD

Trim motion should cease while MSW is held.Pilot Control Wheel Trim Switch . . . . . . . . . . . . . . . .NOSE DNPilot MSW . . . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLD

Trim motion should cease while MSW is held.Copilot Control Wheel Trim Switch . . . . . . . . . . . . . . NOSE UPCopilot MSW . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLD

Trim motion should cease while MSW is held.Copilot Control Wheel Trim Switch . . . . . . . . . . . . . .NOSE DNCopilot MSW . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLD

Trim motion should cease while MSW is held.Yaw Trim Switch . . . . . . . . MOVE EACH HALF SEPARATELY. . . . . . . . . . . . . . . . . . . TO NOSE LEFT AND NOSE RIGHT

Ensure that trim motion does not occur.Yaw Trim Switch . . . . . . . . . . . . . . . . . .MOVE BOTH HALVES ............................SIMULTANEOUSLY TO EACH POSITION

Ensure that trim motion occurs.Trim . . . . . . . . . . . . . . . . . . . . . . . . . . SET ALL FOR TAKEOFF

Ensure amber T.O. TRIM annunciator not illuminated. On S/Ns 35-146 and subsequent; 36-046 and subsequent;prior aircraft with AAK 83-8, determine Stabilizer Trim Set-ting.


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Trim Check (FC 530 Autopilot):Throughout the following check, verify the trim-in-motionaudio clicker sounds approximately 1/4 second after initiatingpitch trim with the flaps up. The trim-in-motion audio clickerdoes not sound when flaps are lowered beyond 3. Ensurethat the amber PITCH TRIM annunciator illuminates whenever either control wheel master switch (MSW) isdepressed.

Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPPITCH TRIM Selector Switch . . . . . . . . . . . . . . . . . . . . . SECNOSE DN-OFF-NOSE UP Switch . . . . NOSE UP/NOSE DNEnsure trim motion occurs in both directions.

Either MSW. . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDTrim NOSE UP or NOSE DN. Ensure trim motion ceases.

Pilot Control Wheel Trim Switch . . . . . . NOSE UP/NOSE DNWhile depressing arming button, operate NOSE UP/NOSEDN. Ensure trim motion does not occur.

Copilot Control Wheel Trim Switch . . . . NOSE UP/NOSE DNWhile depressing arming button, operate NOSE UP/NOSEDN. Ensure trim motion does not occur.

PITCH TRIM Selector Switch . . . . . . . . . . . . . . . . . . . . . OFFPedestal NOSE DN-OFF-NOSE UP Switch . . . . . NOSE UP/. . . . . . . . . . . . . . . . . . . . . . . . . . NOSE DNEnsure trim motion does not occur.

Pilot Control Wheel Trim Switch . . . . . . NOSE UP/NOSE DNWhile depressing arming button, operate NOSE UP/NOSEDN. Ensure trim motion does not occur.

Copilot Control Wheel Trim Switch . . . . NOSE UP/NOSE DNWhile depressing arming button, operate NOSE UP/NOSEDN. Ensure trim motion does not occur.



PITCH TRIM Selector Switch . . . . . . . . . . . . . . . . . . . . . . . PRIPedestal NOSE DN-OFF-NOSE UP Switch . . . . . NOSE UP/.......................................................................... .NOSE DNEnsure trim motion does not occur.

Pilot Control Wheel Trim Switch . . . . . . . . . . . . . . OPERATEWithout depressing arming button, move switch NOSE UP,NOSE DN, LWD, and RWD. Check that trim motion doesnot occur.


Pilot Control Wheel Trim Switch . . . . . . . . . . . . . . OPERATEWhile depressing arming button, move switch NOSE UP,NOSE DN, LWD, and RWD. Ensure trim motion occurs in alldirections.

Pilot MSW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSEnsure that while trimming NOSE UP and NOSE DN,depressing pilot MSW stops trim motion.Copilot MSWDEPRESSEnsure that while trimming NOSE UP and NOSE DN,depressing copilot MSW stops trim motion.

Copilot Control Wheel Trim Switch . . . . . . . . . . . . OPERATEWithout depressing arming button, move switch NOSE UP,NOSE DN, LWD, and RWD. Check that trim motion doesnot occur.


Copilot Control Wheel Trim Switch . . . . . . . . . . . . OPERATEWhile depressing arming button, move switch NOSE UP,NOSE DN, LWD, and RWD. Ensure trim motion occurs in alldirections.

Copilot MSW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSEnsure that while trimming NOSE UP and NOSE DN,depressing copilot MSW stops trim motion.


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Trim Speed Check:The trim speed monitor compares pitch trim rate with flapposition. During ground test, a flaps down signal is appliedto the trim speed controller and a flaps up signal applied totrim speed monitor to simulate the high trim rate with trimspeed monitor in low rate.

On aircraft with AAK 83-2:Either Control Wheel Trim. . . . . . . . NOSE UP OR NOSE DNTRIM OVSP-OFF-TRIM MON Switch. . . . . . . . . TRIM OVSPEnsure amber PITCH TRIM annunciator illuminates.

TRIM OVSP-OFF-TRIM MON Switch. . . . . . . . . . .RELEASEFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DNEither Control Wheel Trim. . . . . . . . NOSE UP OR NOSE DNEnsure PITCH TRIM indicator needle moves faster withflaps 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 OVSPEither Control Wheel Trim. . . . . . . . NOSE UP OR NOSE DNTEST Button . . . . . . . . . . . . . .DEPRESS WHILE TRIMMINGEnsure amber PITCH TRIM annunciator illuminates.

TEST Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASEFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWNEither Control Wheel Trim. . . . . . . . NOSE UP OR NOSE DNEnsure PITCH TRIM indicator needle moves faster withflaps down and the trim-in-motion audio clicker does notsound.

Leerjet 35/36 Developed for Training Purposes 2B-21December 1998


Trim Monitor:During ground test, a signal simulates an electrical fault tothe trim monitor.

On aircraft with AAK 83-2:TRIM OVSP-OFF-TRIM MON Switch. . . . . . . . . . TRIM MONEnsure amber PITCH TRIM annunciator illuminates.

TRIM OVSP-OFF-TRIM MON Switch. . . . . . . . . . .RELEASEOn S/N 35-408, 506 and subsequent; 36-054 and subsequent:

TEST Selector Switch . . . . . . . . . . . . . . . . . . . . . . TRIM MONTEST Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSEnsure amber PITCH TRIM annunciator illuminates.

TEST Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASEEither Control Wheel Trim Switch . . . . . . . . . . . . . OPERATEWith arming button depressed, operate the switch to movePITCH 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. . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKQ Move each half of switch separately to NOSE LEFT and

NOSE RIGHT. Ensure trim motion does not occur.Q Move both halves simultaneously to NOSE LEFT and

NOSE RIGHT. Check that trim motion occurs.

Trim. . . . . . . . . . . . . . . . . . . . . . . . . SET ALL FOR TAKEOFFEnsure amber T.O. TRIM annunciator not illuminated.


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Autopilot Monitor. . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDAutopilot Monitor (FC 200 Autopilot):

AUTOPILOT Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONEnsure the PWR annunciator on the Autopilot Controllerilluminates.

TEST Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSCheck that all annunciators on the Autopilot Controller illu-minate.

ADI/HSI Flags . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKEnsure that all flags have disappeared to indicate that verti-cal and directional gyros have been energized long enoughto time-out erection cycles (approximately 90 seconds).

ENG Button. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSROLL, PITCH, and LVL annunciators illuminate. The autopi-lot then opposes movement of the flight controls.

TEST Button . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDControl Wheel Trim Switch . . . . . . . . . . . . . . . . . . . . . . . LWDWithout depressing arming button, move to LWD. ROLLannunciator extinguishes and autopilot disconnect hornsounds within five seconds. Hold wheel at wings level posi-tion.

Trim Switch/TEST Button . . . . . . . . . . . . . . . . . . . .RELEASEENG Button. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSTEST Button . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDControl Wheel Trim Switch . . . . . . . . . . . . . . . . . . . . . . .RWDWithout depressing arming button, move to RWD. ROLLannunciator extinguishes and autopilot disconnect hornsounds within five seconds. Hold wheel at wings level posi-tion.

Trim Switch/TEST Button . . . . . . . . . . . . . . . . . . . .RELEASEENG Button. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSROLL, PITCH, and LVL annunciators illuminate. The autopi-lot then opposes movement of the flight controls.



TEST Button . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLDControl Wheel Trim Switch . . . . . . . . . . . . . . . . . . .NOSE DNWithout depressing arming button, move to NOSE DN whileholding moderate pull force on control column. PITCHannunciator extinguishes; autopilot disconnect horn soundswithin six seconds. Normally, roll axis disengages along withthe pitch. If such disengagement does not occur, disregardbecause roll axis disengagement is not required.

ENG Button. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSControl Wheel Master Switch . . . . . . . . . . . . . . . . DEPRESSCheck 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONEnsure the PWR annunciator on the Autopilot Controller illu-minates.

TST Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSCheck that all annunciators on the Autopilot Controller illu-minate.

ENG and TST Buttons . . . . DEPRESS SIMULTANEOUSLY/ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .THEN RELEASEMON, PITCH, and ROLL annunciators illuminate, then extin-guish. Disengage tone sounds. The ROLL annunciatorextinguishes in approximately eight seconds and the PITCHannunciator extinguishes in approximately 11 seconds. TheLVL ON annunciator illuminates when the ROLL annunciatorextinguishes. PWR and LVL ON annunciators remain illumi-nated.

2B-24 Developed for Training Purposes Leerjet 35/36December 1998

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If test fails: the failed axis (PITCH and/or ROLL) annuncia-tors flash. The MON annunciator remains illuminated. Cyclethe AUTOPILOT switch to extinguish the annunciators.Autopilot must not be used in any axis that fails the autopilotmonitor check. If it is intended to use autopilot with a failedaxis, the failed axis DC CB (AFCS PITCH or AFCS ROLL)must be pulled.

Yaw Dampers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDYaw Dampers (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 and that theSEC ENG light extinguishes.

Yaw Force Indicator . . . . . . . . . . . . . . . . . . . . . . . . .CENTER

Rotate control wheel to center.

SEC ENG Button . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS

Ensure SEC ENG light illuminates.

Rudder Pedals . . . . . . . . . . . DEPRESS ONE/THEN OTHER

NOTE: Significantly lower rudder pedal force required to overpower yaw damper.



While holding the control wheel centered, depress one rud-der pedal and then the other. It must be possible to depresseach rudder pedal against the opposition of the yaw dampersystem. 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 pedals should deflect to right.

SEC ENG OFF Button . . . . . . . . . . . . . . . . . . . . . DEPRESS

Check that the SEC ENG light extinguishes and the yawdamper disengages.

PRI ENG Button . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS

Ensure PRI ENG light illuminates.

Rudder Pedals . . . . . . . . . . .DEPRESS ONE/THEN OTHER






Control Wheel Master Switch (MSW) . . . . . . . . . . DEPRESS

Ensure that the PRI ENG light extinguishes and the yawdamper disengages.


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Yaw Dampers (FC 530 autopilot):Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

PRI and SEC PWR Buttons . . . . . . . . . . . . . . . . . DEPRESS

Check that the PRI and SEC ON annunciators illuminate.

Yaw Force Indicator . . . . . . . . . . . . . . . . . . . . . . . . .CENTER

Rotate control wheel to center.

TST Button . . . . . . . . . . . . . . . . . . . . .DEPRESS AND HOLD

Ensure PRI and SEC ENG annunciators illuminate and thatboth yaw damper force indicators deflect right and thenslowly deflect left.

TST Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASE

If retesting is decided, wait at least five seconds for test cir-cuit to reset.


Check that the SEC ENG annunciator illuminates.



Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DN










Check that the SEC ENG annunciator extinguishes and theyaw damper disengages. The disengage aural tone sounds.

PRI ENG Button . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS

Ensure PRI ENG annunciator illuminates.

Rudder Pedals . . . . . . . . . . .DEPRESS ONE/THEN OTHER






Control Wheel Master Switch (MSW) . . . . . . . . . . DEPRESS

Ensure that the PRI ENG annunciator extinguishes and theyaw damper disengages. Disengage aural tone sounds.

Emer Lt Switch (if installed) . . . . . . . . . . . . TESTED/ARMED


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Starting EnginesThe Starting Engines checklist is completed prior to enginestart. Both engines should be started prior to taxi.

Passengers/Baggage . . . . . . . . . . . . . . BRIEFED/SECUREDCabin Door . . . . . . . . . . . . . . . . TWO HANDLES FORWARD/

LIGHT OUTThe DOOR annunciator does not extinguish until all doorlatch pins are in place and the door actuator motor is oper-ated to back the closer hooks off the upper door catches.The upper door is an emergency exit.

L/R Fuel Cmptr Switches . . . . . . . . . . . . . . . . . . . . . . . . . ONL/R Fuel Cmptr Lights . . . . . . . . . . . . . . . . . . . . CHECK/OUTBatteries . . . . . . . . . . . . . . . . . . .CHECK FOR MIN VOLTAGE

Lead-acid batteries show at least 24V DC; ni-cad batteriesshow at least 23V DC.

Inverters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRI ONAir Conditioning/Aux Heat . . . . . . . . . . . . . . . . FAN OR OFF

Do not use the Freon system or auxiliary heat during start.This step reduces voltage draw and amperage spike cre-ated when the starter switch is placed in the generator posi-tion.

Rotating Beacon . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONExternal Lighting . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDThrust Levers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CUTOFFParking Brake. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SETHydraulic Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF



Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STARTThe following sequence is performed without the use of achecklist:

Start-Gen Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STARTThe red starter engaged light (if installed) comes on as longas the starter is powered.

SPR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD IN L OR RUse of SPR is recommended at ambient temperature of 0F(-17.8C) or below. Do not energize SPR at any time otherthan during engine start; SPR is not required when OAT isabove 0F.

Turbine RPM (N2) . . . . . . . . . . . . . 10% MIN/FAN ROTATION10% N2 takes approximately six seconds and fan rotationappears at slightly above 10% N2.

Thrust Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLEQ 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 isused, release the switch at 300-400C ITT. ITT must notbe allowed to exceed 860C (on most starts, it does notexceed 700C).

Q Observe fan speed (N1) increasing.Q Observe oil pressure indicator; oil pressure should begin

to register at approximately 25% N2 and within 10 sec-onds of ignition.

Q Observe engine parameters while engine is spooling upto operating speed.

Q Observe that the START and AIR IGN annunciatorsextinguish at 45 to 50% turbine RPM. If the annunciatorsdo not extinguish and the engine is running normally,refer to Abnormal Procedures (Starter Engaged LightRemains Illuminated).


CAE SimuFlite

Q If engine does not start, observe the starter coolingrequirements below:

This cycle may be repeated

If batteries used for start:

START-GEN Switch . . . . . . . . . . . . . . . . . . . . . GEN AT IDLEOn S/Ns 35-002 through 147; 36-002 through 035:

Prior to START-GEN Switch to GENBAT 1 or 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFPrior to starting second engine or if taxiing with singleengine operating and ammeter reads less than 175A, bothbattery switches to ON.

(If only one engine is started at this time, return to page2B-9 and continue with Warning Systems Check.)If GPU used for start:

START-GEN Switch . . . . . . . . . . . . . . . . . . . . . OFF AT IDLEThe AFM does not make a distinction between battery andGPU starts. It is widely accepted, however, to leave the gen-erators off after starting until the GPU has been discon-nected.

START ATTEMPT WAIT

1 1 Minute

2 1 Minute

3 15 Minutes

4 1 Minute

5 1 Minute

6 1 Hour



A problem associated with turning the generators off occursduring the second engine start when the GPU may drop off-line for any number of reasons. If the use of the GPU is nec-essary because of low battery power, start the secondengine with the operating generator on. This minimizes thechance of a hot start occurring in the critical phase of start-ing. If the GPU drops out during the start with low batteries,the 275A current limiter may fail because of the demand onthe operating generator. The pilot must exercise more carewhen starting the engines with low batteries, particularly bychecking the current limiters after both engines started.After the STA RT-GEN switch is placed in GEN, check thegenerator output for indication of DC volts and amps.

Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKQ 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 coldtemperature, an oil pressure transient above normal canbe expected.

Q FUEL PRESS annunciator extinguished to indicate nor-mal operation of the jet pumps. If for any reason, the JETPUMP switch is off and the engine is operating, establishsteady engine operation at or above 80% fan speed (N1)before setting the JET PUMP switch to ON. Use caution;this is a very high thrust setting.

Starter Disengagement Lights. . . . . . . . . . . . . . . CHECKEDWith COOL-FAN and AUX HT switches OFF, turn BATswitches to OFF. If amps less than 100A, turn both BATswitches to ON. If amps greater than 100A, shut enginedown.

Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . CHECKED GPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISCONNECTED

Battery voltage is indicated after the GPU is disconnected ifthe generators are off.


CAE SimuFlite

Generators/DC Volts and Amps . . . . . . . . . . . ON/CHECKEDCheck generator output, DC volts, and amps.

Current Limiters. . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDCUR LIM Annunciator . . . . . . . . . . . . . . . . . EXTINGUISHED

If CUR LIM annunciator not installed:

Rotary Test Switch . . . . . . . . . . . . . . . CURRENT LIMITER L

Test Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS

The green indicator annunciator illuminates if the left currentlimiter is functional.

Rotary Test Switch . . . . . . . . . . . . . . . CURRENT LIMITER R

The green indicator annunciator illuminates if the right cur-rent limiter is functional. Repeat the Current Limiter test afterboth 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 shoulddouble.

Left Generator. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Right Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Left ammeter indication should double.

Right Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Main Bus Tie CB . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET

If ammeter indications do not change during test, a currentlimiter has failed. Do not fly the aircraft until corrected.



Before TaxiNext, complete a flow pattern using exactly the same path usedwith Before Starting Engines checklist. The objective of thesecond flow pattern is to turn on the aircraft equipment in prep-aration for flight and to test each system or component that wasnot tested previously.

Beginning at the anti-ice switch panel, the flow progressesacross the lower switch panel, from left to right, to the rightaudio panel. The right, center, and left instrument panels arechecked up to the annunciator and T/R control panel. Lastly,the pedestal is checked from the thrust lever quadrant down tothe bottom.

All the equipment is turned on, and systems are tested asencountered in the flow pattern. When completed, all aircraftsystems have been checked and set for the taxi phase of flightand nearly all tests have been completed.

The PF calls for and the crew completes the Before Taxi check-list. Very little is done while reading the checklist because itwas accomplished during the flow.

Inverters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ALL ON Avionics/Avionics Master. . . . . . . . . . . . . . . . . . . . . . . . . ON Radar . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STANDBY Radio Altimeter/Autopilot/Emer Power . . . . . . . . . . . . ON UNS . . . . . . . . . . . . . . . . . . . . . . . . . . . ON/PROGRAMMED GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TESTED TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TESTED

NOTE: On aircraft with auxiliary inverter, turn all three inverters on during normal operations to obtain maximum inverter life.


CAE SimuFlite

Windshield Heat. . . . . . . . . . . . . . . . . . . . . . . . . . . . PURGEDAircraft with 450 pressurization:

In-NORMAL/Out-DEFOG Knob . . . . . . . . . . . . . . PULL OUTWSHLD HEAT-MAN-AUTO Switch. . . . . . . . . . . . . . . . AUTOUntil water has cleared.

WSHLD OV HT Light . . . . . . . . . . . . . . . . . . . . . . .MONITORWhen moisture has cleared:

WSHLD HEAT AUTO-MAN Switch. . . . . . . . . . . . . . . . . MANWSHLD HEAT ON-OFF Switch . . . . . . . . . . . . . . . . . . . OFFHold until airflow stops.

In-NORMAL/Out-DEFOG Knob . . . . . . . . . . . . . . . .PUSH INAircraft with 510 pressurization:

WSHLD HEAT ON-OFF Switch . . . . . . . . . . . . . . . . . . . . ONUntil water has cleared.

WSHLD OV HT Light . . . . . . . . . . . . . . . . . . . . . . .MONITORWhen moisture has cleared:

WSHLD HEAT ON-OFF Switch . . . . . . . . . . . . . . . . . . . OFFFuel Control Governors . . . . . . . . . . . . . . . . . . . . CHECKED

Left Thrust Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLEIf the engine accelerates uncontrolled during the followingsteps, turn fuel computer on until engine stabilizes at idle,then shut down and correct the problem.

L Fuel Computer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFL FUEL CMPTR annunciator illuminates. Engine RPM mayincrease or decrease slightly and then stabilize.

When RPM stabilizes:

Left Thrust Lever. . . . . . . . . . . . . . ADVANCE AND RETARDAdvance thrust lever and watch for an increase in turbineRPM and that turbine speed follows the thrust lever. If tur-bine speed fails to respond to thrust lever, shut down engineand correct the problem



L Fuel Computer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONL FUEL CMPTR annunciator extinguishes and engine RPMstabilizes.

Right Thrust Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLEThe right fuel control governor check is the same as the left.

Anti-Skid . . . . . . . . . . . . . . . . . . ON/LIGHTS EXTINGUISHEDSpoileron/Spoilers . . . . . . . . . . . . . . . . . . . . . CHECKED/RETFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DN

Aileron Augmentation Check:Control Wheel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CENTERSpoileron Reset Switch . . . . . . . . . . . . . . . . HOLD IN RESETControl Wheel . . . . . . . . . . . . . . . . . . . . . . . . . ROTATE LEFTApply left aileron until AUG AIL annunciator illuminates, thenhold the control wheel stationary. Observe the deflectionangle.

Spoileron Reset Switch . . . . . . . . . . . . . . . . . . . . . .RELEASEControl Wheel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CENTERSpoileron Reset Switch . . . . . . . . . . . . . . . . HOLD IN RESETControl Wheel . . . . . . . . . . . . . . . . . . . . . . . . ROTATE RIGHTApply right aileron until AUG AIL annunciator illuminates,then hold the control wheel stationary. Observe the deflec-tion angle; it should be approximately the same angle as theleft.

Spoileron Reset Switch . . . . . . . . . . . RESET AND RELEASEControl Wheel . . . . . . . . . . . . . . .ROTATE LEFT AND RIGHTThe controls should be rotated full deflection left and right;the AUG AIL annunciator should not illuminate.

Spoiler Check:

Spoilers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTEND


CAE SimuFlite

The SPOILER annunciator illuminates and flashes andspoilers extend in one to two seconds. If possible, check thespoilers visually.

Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPThe SPOILER annunciator stops flashing at 13 and stayson steady.

Spoilers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTThe spoilers retract in approximately six seconds and theSPOILER annunciator extinguishes.

Spoiler Slamdown Test (S/Ns 35-002 through 142; 36-002through 035 without SB35/36-27-7):

Spoilers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTENDThe SPOILER annunciator illuminates.

Spoiler CB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULLThe spoilers should slam down (retract in less than one sec-ond) and the annunciator extinguishes.

Spoiler CB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESETThe spoilers extend; the annunciator illuminates.

Spoilers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTThe spoilers retract in approximately four seconds and theannunciator extinguishes.

Flaps (8 or 20) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SETHydraulic Press/Low Hydraulic Light . . . . . . . . . CHECKEDLighting. . . . . . . . . . . . . . . . . . . . . . . . . . . ON/AS REQUIRED

Do not use strobe lights when taxiing in the vicinity of otheraircraft. Navigation lights should be on for all night opera-tions.

Coffee/Oven . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONCircuit Breakers. . . . . . . . . . . . . . . . . . . . . . . . . CHECKED INParking Brake. . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASED

Leerjet 35/36 Developed for Training Purposes 2B-37October 2001


TaxiBrakes and Steering . . . . . . . . . . . . . CHECKED/ENGAGED

Wheel Master . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS

Rudder Pedals . . . . . . . . . . . . . . .STEER LEFT AND RIGHT

Operation is smooth and prompt; no stepping or growlingoccurs.

Steer Lock . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED

Toe Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDAeronca Thrust Reversers:

Thrust Reverser Test Switch . . . . . . . . . . . . . . . . . DEPRESS

The BLEED VALVE annunciators illuminate. If the optionalblocker door switches have been installed, the UNLOCKannunciators flash after a three second delay. If theUNLOCK annunciators flash, the operational check may beperformed. If the annunciator(s) do not flash, the operationalcheck should be accomplished after landing. The reversermust be visually inspected after use to determine that theyare properly stowed.

Thrust Reverser Operational Check

L Thrust Reverser Lever . . . . . . . . . . . . . . . . . IDLE DEPLOY

The thrust reverser does not respond; the engine acceler-ates slightly.

L Thrust Reverser Lever . . . . . . . . . . . . . . . . . . . . . . . STOW

R Thrust Reverser Level . . . . . . . . . . . . . . . . . IDLE DEPLOY

The thrust reverser does not respond; the engine acceler-ates slightly.

2B-38 Developed for Training Purposes Leerjet 35/36October 2001

CAE SimuFlite

Both Thrust Reverser Levers . . . . . . . . . . . . . IDLE DEPLOY

The UNLOCK annunciators illuminate first. Next, theDEPLOY annunciators illuminate and the UNLOCK annun-ciators extinguish.

Emergency Stow Switch . . . . . . . . . . . .EMERGENCY STOW

The thrust reversers should stow and EMER STOW lightilluminates.

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 thrustreverser levers are free to pull into reverse past a lock-outpin that retracts when both reversers are deployed.

Both Thrust Reverser Levers . . . . . . . . . . . . . . . . . . . .STOW

The reversers should stow and the annunciators extinguish.

BLEED VALVE Annunciators . . . . . . . . . . . EXTINGUISHED



Dee Howard TR4000 Thrust Reversers:Warning Lights Test Switch . . . . . . . . . . . . . . . . . . DEPRESSThe ARM and DEPLOY annunciators illuminate. If anythrust reverser annunciators fail to operate during test,repairs must be accomplished or CBs for both thrust revers-ers must be pulled prior to flight.

Thrust Reverser Control Switches . . . . . . . . . . . . . . . . TESTARM annunciators illuminate.

Thrust Reverser Control Switches . . . . . . . . . . . . . . . . . ARMARM annunciators illuminate.Thrust Levers. ADVANCESLIGHTLYARM annunciators extinguish.

Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLEARM annunciators illuminate.

Thrust Reverser Levers . . . . . . . . . . . . . . . . . IDLE DEPLOYBoth DEPLOY annunciators illuminate, the reversersdeploy, and the lever lock-out pins pull.

Thrust Reverser Levers . . . . . . . . . . . . . . . . . . . . . . . .STOWBoth DEPLOY annunciators extinguish.

Thrust Reverser Control Switches . . . . . . . . . . . . . . . . . OFFARM annunciators extinguish.

Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDFlight Instruments . . . . . . . . . . . . . . . . . . . . . . . . NO FLAGS/ ALT,HEADING,VERIFIEDNav Equipment/Radios . . . . . . . . . . . . . . . . . . . . . . . ON/SETSpoilers/Flaps/Trim . . . . . . . . . . . . .RETRACTED, 8 OR 20 SET/CHECKEDPressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED


CAE SimuFlite

Cabin Air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM OR ONAnti-Ice Systems . . . . . . . . . . . . . CHECKED/AS REQUIREDEngine Anti-Ice Check:

Nacelle Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONThe left and right engine ice annunciators illuminatemomentarily and then extinguish. The ITT rises slightly.

L/R Engine Ice Annunciators . . . . . . . . . . . . . . . . . . . . . OFFIf the annunciators do not go out, increase thrust. Theannunciators must go out by 60% fan RPM.

Nacelle Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFWing and Stabilizer Anti-Ice Check:

Stab and Wing Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONThe cabin rate-of-climb indicators shows a climb in cabinaltitude.

Stab and Wing Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFThe cabin rate-of-climb indicators shows a descent in Cabinaltitude.

Cabin Check. . . . . . . . . . . . . . . . . . . . . . . . . . . .COMPLETED

NOTE: Anti-ice systems should be turned on prior to flight into visible moisture with OAT of 50F (10C) or below. If anti-ice systems are required during takeoff, they should be turned ON prior to setting takeoff power.

WARNING: The wings, vertical and horizontal stabilizers,flight controls surfaces, and engine inlets must be free of frost,snow, and ice.



Before TakeoffThe Before Takeoff checklist is accomplished with the aircraftstopped.

Crew Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . .COMPLETEDReview takeoff data and bugs set.

Fuel Balance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDCabin Air. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM OR ONAnti-IcE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

Radar . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIREDTransponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TA/RADee 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 50F (10C) or below. If anti-ice systems are required during takeoff, they should be turned ON prior to setting takeoff power.


CAE SimuFlite

Runway Line-UpPitot Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED/ON

The PITOT HEAT annunciators extinguish.

Air Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONThe AIR IGN annunciators illuminate.

Stall Warnings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONThe STALL annunciators should extinguish. In gusty windconditions, it may be necessary to turn on stall warningsafter initiating the takeoff roll.

Parking Brake. . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASEDLanding/Taxi Lights . . . . . . . . . . . . . . . . . . . ON/AS DESIREDRecognition/Strobe Lights . . . . . . . . . . . . . . . . . . . . . . . . ONSteer Lock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFWarning Lights. . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED/ OR AS APPROPRIATE

The annunciator panel is scanned and all annunciatorsshould be extinguished except possibly the STEER ON,NAC HT (if installed), and DH annunciator.

TakeoffNosewheel Steering. . . . . . . . . . . . . . . . RELEASE AT FIRST INDICATION OF AIRSPEED

Use as required for heading control.



After TakeoffThe After Takeoff checklist is not accomplished until the aircraftis safely airborne and the crew has had time to clear the areafor traffic. It is accomplished after the aircraft is at least 1,500 ftAGL (if workload permits). Should the aircraft remain within theairport traffic area, complete the After Takeoff checklist afterestablishing the aircraft in level flight. Each pilot should advisethe other when the checklist is begun so that visual traffic sepa-ration is maintained.

After safely airborne, the PF calls for gear retraction and yawdamper engagement. At the appropriate speed, the PF calls forflap retraction and for the After Takeoff checklist.

Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPWhen the gear is retracting, monitor the annunciators forproper indications to detect a hydraulic failure.

Yaw Damp PRI or SEC. . . . . . . . . . . . . . . . . . . . . . ENGAGEDS/Ns with FC 200 autopilot: The yaw damper must be onfor all operations after lift-off until just prior to touchdown.

Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPThe flaps may be retracted at V2 +30 and must be retractedprior to VFE.

Dee Howard Thrust Reversers (prior to 200 KIAS). . . . OFFAnti-Ice Systems . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

Anti-ice systems should be turned on prior to flight into visi-ble moisture and RAT of 10C or below. If the anti-ice sys-tems are activated, monitor for proper indications mentionedpreviously during systems check.


CAE SimuFlite

Air Ignition . . . . . . . . . . . . . . . . . . . . AS REQUIRED OR OFFBefore turning the ignition off, visually scan the area for birds. Ifin rain or icing conditions, turning off air ignition may bedelayed. The AIR IGN annunciators extinguish.

Landing/Taxi Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFPressurization . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOREDAutopilot APPR Light . . . . . . . . . . . . . . . . . . . . . . . . . . . OUTHydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . . . . NORMALAngle-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 information to be unreliable.



ClimbAt 10,000 ft:No Smoking/Seat Belt Sign. . . . . . . . . . . . . . AS REQUIREDAt FL 180 or Transition Level:Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29.92Cool/Fan Switch (if applicable). . . . . . . . . . . . . FAN OR OFF

The air conditioner should not be used above 18,000 ft toprevent arcing in the compressor motor (except for S/Nswith FCN89-1, which increase altitude to FL 350).

Emer Press Switches (if installed) . . . . . . . . . . . . NORMALRecognition Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFLeaving FL 250:Crew Masks . . . . . . . . . . 100% OXY/QUICK DON POSITIONS/Ns 35-002 through 112 except 107; 36-002 through 031:

ZMR100 Series: one crew member must wear oxygen maskaround 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 don-ning within five seconds.

At FL 350:Cool/Fan Switch (with FCN 89-1) . . . . . . . . . . . FAN OR OFFAbove FL 410:S/Ns 35-002 through 112 except 107; 36-002 through 031:Crew/Passenger Oxygen Masks. . . . . . . . . . . . . . . . . . DON

Ensure lanyards have been pulled on passenger masks inuse.


CAE SimuFlite

CruisePressurization . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOREDEngine Instruments . . . . . . . . . . . . . . . . . . . . . . MONITOREDAutopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIREDWindshield Heat. . . . . . . . . . . . . . . . . . . . . . . . . AS DESIREDFuel Management . . . . . . . . . . . . . . . . . . . . . . . MONITORED

DescentWindshield Heat/Windshield Defog/Aux Defog. . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDPressurization . . . . . . . . . . . . . . . . . . . . .SET FOR LANDINGAnti-Ice Systems . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

FL 180/Transition LevelAltimeters . . . . . . . . . . . . . . . . . . . . . SET/CROSS CHECKEDAir Conditioner. . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED

Use of the air conditioner may reduce the amount of internalwindshield fogging that occurs at low altitude.

Hydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDRecognition Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONTOLD Card/Bugs . . . . . . . . . . . . . . . . . . . . .COMPUTED/SETCabin. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDSwivel Seats . . . . . . . . . . . . FORWARD OR AS PLACARDEDWork Table and Toilet Doors(if installed). . . . . . . . . . . . . . . . . . . . . . . . . CHECK STOWEDEmergency Exit . . . . . . CHECK ISLE CLEAR AND HANDLE UNOBSTRUCTEDSeat Belt/No Smoking Sign. . . . . . . . . . . . . . . . . . . . . . . . ON



ApproachCircuit Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDAeronca Thrust Reversers . . . . . . . . . . . . . . . . . . . . TESTED

TEST Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS

Hydraulic/Emergency Air Pressure . . . . . . . . . . . CHECKEDRadio/Barometric Altimeters . . . . . . . . . . . . . . . . MINS SET/ . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECKEDFuel Balance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDAvionics . . . . . . . . . . . . . . . . . . . . . . . SET FOR APPROACHCrew Briefing/Bugs . . . . . . . . . . . . . . . . . .COMPLETED/SET

It is recommended that if turbulence is anticipated due togusty winds, wake turbulence, or wind shear, the approachspeed be increased. For gusty wind conditions, an increasein approach speed of one half the gust factor is recom-mended.


CAE SimuFlite

Before LandingSpoilers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTEDFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED 8 or 20Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWNEngine Sync . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

If the engine sync is on and gear extended, the ENG SYNCannunciator illuminates when nose gear is down and locked.The ENG SYNC annunciator is wired through the downlockswitch.

Anti-Skid. . . . . . . . . . . . . . . . . . ON/LIGHTS EXTINGUISHEDLanding/Taxi Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONDee Howard Thrust Reversers(below 200 KIAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARMEDCabin. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWNHydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDAir Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONAutopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGEDYaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGED

FC 200 autopilot: The yaw damper should be disengagedin the landing flare.

FC 530 autopilot: With full flaps, the yaw damper disen-gages through the squat switch relay at touchdown. Withflaps other than full down, disengage the yaw damper priorto landing.



LandingAfter touchdown:

Spoilers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTENDEDBrakes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDThrust Reversers or Drag Chute . . . . . . . . . . . AS DESIREDBelow 45 kts:

Nosewheel Steering. . . . . . . . . . . . . . . . . . . . AS REQUIRED

Go-Around/Missed ApproachAutopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGEDThrust Levers . . . . . . . . . . . T.O. POWER OR AS REQUIREDSPOILER Switch . . . . . . . . . . . . . . . . . . . . . . . . RETRACTEDFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20Landing Gear Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPClimb. . . . . . . . . . . . . . . . . . . . . . APPROACH CLIMB SPEEDWhen clear of obstacles:Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF + 30Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

WARNING: When the Fuel Quantity gage indicates 600pounds or less remaining in either wing tank, prolongednose-up attitude of 10 or more may cause fuel to betrapped in the aft area of the wing tank outboard of thewheel well. Fuel starvation and engine flameout may occur.For go-around conditions with low fuel, on first steady indi-cation by the LOW FUEL warning light, reduce climb atti-tude and thrust to minimum required.


CAE SimuFlite

After Landing/Clearing RunwayAnti-Ice System . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDAir Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFStall Warnings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFLanding/Taxi Lights . . . . . . . . . . . . . . . . . . . . . . AS DESIREDCabin Air. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFRecognition/Strobe Lights . . . . . . . . . . . . . . . . . . . . . . . OFFUnnecessary Avionics/Radar . . . . . . . . . . . . . . . . . . . . . OFFUNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFTransponder . . . . . . . . . . . . . . . . . . . . . . . STANDBY OR OFFSpoilers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTEDFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDHydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDTrims . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESETDee Howard Thrust Reversers . . . . . . . . . . . . . . . . . . . . OFF



ShutdownChocks/Parking Brake. . . . . . . . . . . . . . . . . . AS REQUIREDAnti-Ice Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFEmer Power/Standby Gyro . . . . . . . . . . . . . . . . OFF/CAGEDPanel Switches/Avionics. . . . . . . . . . . . . . . . . . . . . . . . . OFFCrossflow . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED

Close the crossflow valve. If valve is left open, the fuel maygravity flow to the lowest wing and cause the aircraft to tipover on the ramp.

Fuel Tank XFER-FILL. . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFAlways stop the fuel transfer process while batteries are on.If the battery switches are turned off before the fuel transferswitch is place in OFF, the crossflow valve may remainopen.

Fuel Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSEDEmergency Lights (if installed). . . . . . . . . . . . . . DISARMED

If emergency lights are left armed and main batteries turnedoff, the lights come on and drain the emergency light systembatteries.

Coffee/Oven Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFThrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CUTOFF

When shutting down the engines, check the hydraulicpumps. Operate a hydraulic load (spoilers or flap) after shut-ting down one engine. If operating pressure is maintained,the pump on the operating engine is functioning.

External Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFInverters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFGenerators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF


CAE SimuFlite

Hydraulic Pressure (if applicable) . . . . . . . . . . . . . . . . ZEROIf the parking brake is set, use of flaps to bleed hydraulicsystem pressure does not affect parking brake pressure.

Batteries . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFControl Lock. . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSTALLED

CAUTION: On S/Ns without SB 35/36-32-4, failure tobleed hydraulic pressure from the system before settingBattery switches off could result in nose gear retraction iflanding gear selector valve malfunctions.



Quick Turnaround(One or No Engine Shutdown)

Cabin Door-Closed and Locked . . . . . . . DOOR LIGHT OUTNo Smoking/Seat Belt Switch. . . . . . . . . . . . . . . . . . . . . . ONCool Fan/Aux Heat Switches . . . . . . . . . . . . . . OFF OR FANEngine (if shut down) . . . . . . . . . . . . . . . . . . . . . . . . . STARTStart-Gen Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENDC Volts/Amps . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDStarter Disengagement . . . . . . . . . . . . . . . . . . . . . CHECKEDCurrent Limiters. . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDCircuit Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INAvionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDCoffee/Oven Switches . . . . . . . . . . . . . . . . . . AS REQUIREDAnti-Ice Systems . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

TaxiFuel Panel/Balance . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDTOLD Card/Bugs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SETNav Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SETTransponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TA/RARadar. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDSpoilers/Flaps/Trim . . . . . . . . RETRACTED, 8 OR 20 SET/ . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKEDPressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SETCabin Air. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM OR ON


CAE SimuFlite

Dee Howard Thrust Reversers . . . . . . . . . . . . . . . . ARMEDCabin Check/Passenger Briefing . . . . . . . . . . .COMPLETEDCrew Takeoff Briefing . . . . . . . . . . . . . . . . . . . .COMPLETED

Runway LineupPitot Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED/ONAir Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONStall Warnings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONParking Brake. . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASEDLanding/Taxi Lights . . . . . . . . . . . . . . . . . . . ON/AS DESIREDRecognition/Strobe Lights . . . . . . . . . . . . . . . . . . . . . . . . ONSteer Lock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFWarning Lights. . . . . . . . . . . . . .OUT OR AS APPROPRIATE

After Takeoff/Traffic PatternLanding Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPYaw Damper PRI or SEC . . . . . . . . . . . . . . . . . . . . ENGAGEDFlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPDee Howard Thrust Reversers (below 200 kts). . . . . . . OFFAir Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDLanding/Taxi Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFFuel Panel/Balance . . . . . . . . . . . . . . . . . . . . . . . . CHECKEDRadio/Barometric Altimeters . . . . . SET/CROSS CHECKEDApproach Briefing/Bugs . . . . . . . . . . . . . .COMPLETED/SET



Before LandingSpoilers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTEDFlaps . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED (8 OR 20)Landing Gear . . . . . . . . . . . . . . . . . . .

Learjet 35 Learjet3 05 Exnorm

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