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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
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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
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Leerjet 35/36 Developed for Training Purposes 2B-3February
2004
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.
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2B-4 Developed for Training Purposes Leerjet 35/36February
2004
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.
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Leerjet 35/36 Developed for Training Purposes 2B-5February
2007
Expanded Normal Procedures
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.
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2B-6 Developed for Training Purposes Leerjet 35/36February
2007
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.
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Leerjet 35/36 Developed for Training Purposes 2B-7February
2004
Expanded Normal Procedures
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.
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2B-8 Developed for Training Purposes Leerjet 35/36February
2007
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
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Leerjet 35/36 Developed for Training Purposes 2B-9February
2007
Expanded Normal Procedures
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.
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2B-10 Developed for Training Purposes Leerjet 35/36February
2007
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
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Leerjet 35/36 Developed for Training Purposes 2B-11February
2007
Expanded Normal Procedures
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.
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2B-12 Developed for Training Purposes Leerjet 35/36February
2004
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
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Leerjet 35/36 Developed for Training Purposes 2B-13February
2004
Expanded Normal Procedures
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.
-
2B-14 Developed for Training Purposes Leerjet 35/36February
2004
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-15February
2007
Expanded Normal Procedures
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.
-
2B-16 Developed for Training Purposes Leerjet 35/36February
2004
CAE SimuFlite
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-17February
2004
Expanded Normal Procedures
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.
-
2B-18 Developed for Training Purposes Leerjet 35/36February
2004
CAE SimuFlite
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-19February
2004
Expanded Normal Procedures
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.
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.
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.
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 MSW . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . DEPRESSEnsure that while trimming NOSE UP and NOSE
DN,depressing copilot MSW stops trim motion.
-
2B-20 Developed for Training Purposes Leerjet 35/36February
2002
CAE SimuFlite
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
Expanded Normal Procedures
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.
-
2B-22 Developed for Training Purposes Leerjet 35/36February
2002
CAE SimuFlite
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-23December
1998
Expanded Normal Procedures
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
CAE SimuFlite
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-25December
1998
Expanded Normal Procedures
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
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.
Control Wheel Master Switch (MSW) . . . . . . . . . .
DEPRESS
Ensure that the PRI ENG light extinguishes and the yawdamper
disengages.
-
2B-26 Developed for Training Purposes Leerjet 35/36December
1998
CAE SimuFlite
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.
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 depresseach rudder
pedal against the opposition of the yaw dampersystem. The Yaw Force
Indicator indicates direction of input.
Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . DN
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 depresseach rudder
pedal against the opposition of the yaw dampersystem. The Yaw Force
Indicator indicates direction of input.
-
Leerjet 35/36 Developed for Training Purposes 2B-27December
1998
Expanded Normal Procedures
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 Button . . . . . . . . . . . . . . . . . . . . . . . . .
DEPRESS
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
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.
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
-
2B-28 Developed for Training Purposes Leerjet 35/36February
2004
CAE SimuFlite
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
-
Leerjet 35/36 Developed for Training Purposes 2B-29February
2004
Expanded Normal Procedures
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).
-
2B-30 Developed for Training Purposes Leerjet 35/36December
1998
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
-
Leerjet 35/36 Developed for Training Purposes 2B-31December
1998
Expanded Normal Procedures
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.
-
2B-32 Developed for Training Purposes Leerjet 35/36December
1998
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-33February
2007
Expanded Normal Procedures
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.
-
2B-34 Developed for Training Purposes Leerjet 35/36February
2007
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
-
Leerjet 35/36 Developed for Training Purposes 2B-35December
1998
Expanded Normal Procedures
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
-
2B-36 Developed for Training Purposes Leerjet 35/36December
1998
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
Expanded Normal Procedures
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
-
Leerjet 35/36 Developed for Training Purposes 2B-39February
2004
Expanded Normal Procedures
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
-
2B-40 Developed for Training Purposes Leerjet 35/36February
2004
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-41February
2007
Expanded Normal Procedures
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.
-
2B-42 Developed for Training Purposes Leerjet 35/36December
1998
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-43December
1998
Expanded Normal Procedures
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.
-
2B-44 Developed for Training Purposes Leerjet 35/36December
1998
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-45February
2004
Expanded Normal Procedures
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.
-
2B-46 Developed for Training Purposes Leerjet 35/36February
2004
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
-
Leerjet 35/36 Developed for Training Purposes 2B-47February
2004
Expanded Normal Procedures
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.
-
2B-48 Developed for Training Purposes Leerjet 35/36December
1998
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-49February
2004
Expanded Normal Procedures
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.
-
2B-50 Developed for Training Purposes Leerjet 35/36February
2007
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
-
Leerjet 35/36 Developed for Training Purposes 2B-51December
1998
Expanded Normal Procedures
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
-
2B-52 Developed for Training Purposes Leerjet 35/36February
2007
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.
-
Leerjet 35/36 Developed for Training Purposes 2B-53February
2007
Expanded Normal Procedures
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
-
2B-54 Developed for Training Purposes Leerjet 35/36December
1998
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
-
Leerjet 35/36 Developed for Training Purposes 2B-55December
1998
Expanded Normal Procedures
Before LandingSpoilers. . . . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . RETRACTEDFlaps . . . . . . . . . . . . . . .
. . . . . . . . . AS DESIRED (8 OR 20)Landing Gear . . . . . . . .
. . . . . . . . . . .