Falcon 50 Checklist

8/10/2019 Falcon 50 Checklist

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Falcon 50


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Notice: This Falcon 50 Cockpit Reference Handbook is to be used for

aircraft familiarization and training purposes only. It is not to be used as,

nor considered a substitute for the manufacturers Pilot or Maintenance

Manuals.


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Introduction

Welcome to CAE SimuFlite!

Our goal is a basic one: to enhance your safety, proficiencyand professionalism within the aviation community. All of us

at CAE SimuFlite know that the success of our company

depends upon our commitment to your needs. We strive for

excellence by focusing on our service to you.

We urge you to participate actively in all training activities.Through your involvement, interaction, and practice, the full

value of your training will be transferred to the operational

environment. As you apply the techniques presented through

CAE SimuFlite training, they will become second nature to

you.

Thank you for choosing CAE SimuFlite. We recognize that

h h i f t i i W t t ill fi d

SimuFlite


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Introduction

Introduction

SimuFlite created this reference handbook for cockpit use. It isan abbreviated version of the SimuFlite Technical Manual and

includes international ight planning information. Please refer to

the front of each chapter for a table of contents.

The Procedures chapter contains four elements: Preight

Inspection, Expanded Normal Procedures, a sample StandardOperating Procedure (SOP), and Maneuvers.

The Limitations chapter contains general, operational, and

aircraft systems limitations.

The alphabetically arranged Systems chapter includes key

data on particular systems and relevant color schematics.The Flight Planning chapter includes maximum allowable

takeoff and landing weight ow charts and a sample weight and

balance form. International ight planning information includes

a checklist, a glossary of frequently used international ight

operation terms, and sample ight plan forms (ICAO and FAA)with completion instructions.

Th S i i h t t i i i i ti d


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Operating ProceduresThis chapter contains four sections: Preight Inspection,Expanded Normal Procedures, a sample Standard Operating

Procedure (SOP), and Maneuvers. Although these procedures

are addressed individually, their smooth integration is critical

to ensuring safe, efcient operations.

Preight Inspection contains an abbreviated checklist forthe exterior inspection as well as preight cockpit and cabin

checks.

Expanded Normal Procedurespresents checklists for normal

phases of ight. Each item, when appropriate, is expanded to

include cautions, warnings, and light indications.Standard Operating Proceduresdetails Pilot Flying/Pilot Not

Flying callouts and verbal or physical responses.

Maneuvers contains pictorial representations of specic

maneuvers.


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Preflight

Table of ContentsInterior Preight Inspection. . . . . . . . . . . . . . . . . . . . . .2A-3

Cockpit Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-3

Cabin Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-5

Exterior Walkaround . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-6

Preliminary Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-6

Left Nose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-6

Right Nose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-7

Forward Right Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-8

Aft Right Wing/No. 3 (Right) Engine . . . . . . . . . . . . . . . . .2A-9

Aft Fuselage/No. 2 (Center) Engine . . . . . . . . . . . . . . . . 2A-11

Aft Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-12

Lower Aft Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2A-14

No.1 (Left) Engine/Aft Left Wing . . . . . . . . . . . . . . . . . . .2A-15


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Preight Inspection

Interior Preight Inspection

Cockpit InspectionBatteries . . . . . . . . . . . . . . . . . . . . . CONNECTED

Documents . . . . . . . . . . . . . . . . . . . . . ON BOARD

registration certicate

airworthiness certicate

radio station license

aircraft log (with ight and inspection times)

Airplane Flight Manual

operating/performance manuals

systems pilot manuals.

Keys . . . . . . . . . . . . . . . . . . . CHECKED/STOWED

Smoke Goggles . . . . . . . . . . . . . CHECKED/STOWED

C and D Bus Switches . . . . . . . . . . . . . . . . . . TIED

Battery 1 and 2 Switches . . . . . . . . . . . . . . . . . . ON


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#2P.BK Annunciator . . . . . . . . . . . . . . . ON STEADY

Fuel Quantity Selector . . . . . . . . . . . . . . . . . . TOT

Total Fuel Quantity . . . . . . . . . . . . . . . . ADEQUATE

Fuel Quantity Selector . . . . . . . . . . . . . . . . . REAR

Horizontal Stabilizer Trim Indicator . . . . . GREEN BAND

Battery 1 and 2 Switches . . . . . . . . . . . . . . . . . OFF

Passenger Oxygen Selector . . . . . . . . . . . . NORMAL

Oxygen Pressure . . . . . . . . . . . . . . . . . . . . CHECK

Crew Only/Below 10,000 ft MSL . . . . 650 PSI MINIMUM

10 passengers/Up to FL410 . . . . . . . 700 PSI MINIMUM

For ight above FL 410, check Performance Manual,

Gen. Sup. I, or Operations Manual, Sec. 4, Subsect.

60.


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Falcon 50 2A-5

October 1997 Developed for Training Purposes Only

Preight Inspection

Cabin Inspection

Emergency Exit Security Devices . . . . . REMOVE/STOW

First Aid Kit . . . . . . . . . ON BOARD/CONTENTS VALID

Extinguishers . . . . . . . ON BOARD/VALID INSPECTION

Crash Ax (if on aircraft equipment list) . . . . . . STORED

Nose and Main Gear

Free Fall Extension Controls . . . . . . . . . . STOWED

ECU Inlet Door Control . . . . . . . . . . . . . . . . CHECK

Handle . . . . . . . . . . . . . . . . . . . . . . PUSHED IN

The door remains open except for ditching.

Fuel Transfer Shutoff

Valve Controls . . . . . . . . . . . . . . . . CHECK OPEN

Operating Tool . . . . . . . . . . . . . . . . . . . . STORED

Survival Equipment(overwater ight) . . . . . . . . . . . . . STORED/VALID

INSPECTION DATES

Passenger Seats/Belts . . . . SECURE/GOOD CONDITION

Galley and Lavatory . . . . . . . . . . . CLEAN/SECURED

Passenger Oxygen Masks . . . . . . . . . . . . . SECURE


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2A-6 Falcon 50

Developed for Training Purposes Only October 1997

Preight Inspection Walkaround Path

H

F

I

A

C

B

D

EG

D5_

PF_

001

.ai

Exterior WalkaroundObtain folding ladder from the baggage or aft compartment, a

ashlight, and a standard screwdriver to begin the exterior inspection.

For ease of reference, unfold the preight inspection diagram.

Note that segments identied by letters A through I match

the following checklists.

Preliminary CheckFuel Sump Drains . . . . . . . . . . DRAIN AS NECESSARY

Covers/Pins . . . . . . . . . . . . . . . . . . REMOVE/STOW

Ladder . . . . . . . UNFOLD/CONFIGURE AS NECESSARY

A Left Nose

Left Static Port . . . . . . . . . . . . . . . . . . . . . . CLEAR

Stall Vane . . . . . . . . . . FREE/HORIZONTAL POSITION

Emergency Static Port . . . . . . . . . . . . . . . . . . CLEAR

Left Pitot Tube . . . . . . . . . . . . . . . . UNOBSTRUCTED

Left Nose Cone Latches . . . . . . . . . . . . . . . . SECURE

Nose Cone . . . . . . . . . . . . . . . . . . . . UNDAMAGED

Left Windshield . . . . . . . . . . CLEAN/GOOD CONDITION

Wiper . . . . . . . . . . . . . . . . . . . . . . . . . PARKED

Temperature Probe . . . . . . . . . . . . . UNOBSTRUCTED


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Nose Gear . . . . . . . . . . . . . . . . . . . . . . . INSPECT

Tire Ination:

Bias Ply Tires . . . . . . . . APPROX 136 PSI (9.4 BAR)

Radial Tires . . . . . . . . APPROX 155 PSI (10.9 BAR)

Strut Extension (with full fuel) . . . . . . . . 2 TO 3 INCHES

Red Tire Slippage Marks . . . . . . . . CORRESPOND TO

YELLOW VALVE STEM

Taxi Light . . . . . . . . . . . . . . . . . . GOOD CONDITION

Nosewheel Steering Linkage Locking Pin . . . . INSTALLED

Bonding Wire . . . . . . . . . . . . . . . . . CONNECTED

Nose Gear Strut Doors/Linkage . . . . . GOOD CONDITION

Nosewheel Well/Doors . . . . . . . . . . GOOD CONDITION

B Right Nose

Right Pitot Tube . . . . . . . . . . . . . . . UNOBSTRUCTED

E St ti P t CLEAR


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C Forward Right Wing

Right Landing Light . . . . . . . . . . . CLEAN/UNDAMAGEDVent . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Park Brake Accumulator Sight Gage . . . . . . . . . . CHECK

Minimum Charge . . . . . . . . . . . . . . . . . . . 950 PSI

Normal Charge . . . . . . . . . . . . . . . . . . . 3,000 PSINormal Charge (standby pump) . . . . . . . . . . 2,150 PSI

Antennas . . . . . . . . . . . . . . . . . . GOOD CONDITION

Fuel Sumps . . . . . . . . . . . . . . CLOSED/NO LEAKAGE

Right Emergency Exit Door . . . . FLUSH WITH FUSELAGEOutside Access Red Button Cover . . . . . . . . IN PLACE

Right Wing Ice Inspection Light

(if installed) . . . . . . . . . . . . . . . GOOD CONDITION

Emergency Exit Ground Light . . . . . . .GOOD CONDITIONNo. 3 Engine Intake/Fan/Spinner . . . . . . . . UNDAMAGED


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Preight Inspection

D Aft Right Wing/No. 3 (Right) Engine

Right Wing Tip . . . . . . . . . . . . . . . . . . UNDAMAGEDNavigation/Strobe Lights . . . . . SECURE/UNDAMAGED

Right Aileron . . . . . . . . . . . . . . . . GOOD CONDITION

Actuator . . . . . . . . . . . . . . SECURE/NO LEAKAGE

CAUTIONThe carbon-ber reinforced plastic aileron requires special

care when cleaning. Consult the Maintenance Manual for

scouring and cleaning information.

Static Dischargers . . . . . . . . . . UNDAMAGED/SECURE

Note any missing static dischargers.

Flaps . . . . . . . . . . . . . . . . . . . . GOOD CONDITION

Airbrakes . . . . . . . . . . RETRACTED/GOOD CONDITION

Some creepage from stowed position is common.

Right Wing Underside . . . . . UNDAMAGED/NO LEAKAGE


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Strut Extension (full fuel) . . . . MORE THAN 2.5 INCHES

Wheel Well Door . . . . . . . . . . . . . . . . . . . . OPEN

Overheat Detection Loop . . . . . . . . . . . . INTEGRITY

Doors/Attachments . . . . . . . . . . . GOOD CONDITION

Aft Lavatory Service Door

(if installed) . . . . . . . . . . . . . . .CLOSED/SECURE

No. 3 Nacelle/Pylon . . . . . . . . . . . . . . . . . . INSPECT

Nacelle Drain . . . . . . . . . . . . . . . . . NO LEAKAGE

Engine Cowling . . . . . . . . . . . . . . . . . . LATCHED

Oil Level (sight gage) . . . . . . . . . OPERATING RANGE

Oil/Fuel Filter Bypass Pins . . . . . . . . . . . . . . . . . IN

Tailcone . . . . . . . . . . . . . . . . . GOOD CONDITION

Engine Exhaust Cover . . . . . . . . . . . . . . REMOVED

External Power Access Door . . . . . . . CLOSED/SECURE

No. 2 Hydraulic System

Ground Connection Door . . . . . . . . CLOSED/SECURE


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Preight Inspection

E Aft Fuselage/No. 2 (Center) Engine

No. 2 Engine Nacelle/Cowling . . . . . . . . . . . . INSPECT

Nacelle Drain . . . . . . . . . . . . . . . . . NO LEAKAGE

Cowling . . . . . . . . . . . . . . . . . . . . . . . . . OPEN

Oil/Fuel Bypass Indicators . . . . . . . . . . . . . . . . . IN

Oil Level . . . . . . . . . . . . . . . . OPERATING RANGE

Cowling . . . . . . . . . . . . CLOSE/LATCHES SECURE

Thrust Reverser Doors . . RETRACTED/GOOD CONDITION

Exhaust Cover . . . . . . . . . . . . . . . . . . . . REMOVED

Tailcone Area . . . . . . . . . . . . . . . GOOD CONDITION

Rear Static Discharger . . . . . . . . UNDAMAGED/SECURE

Aft Navigation Light . . . . . . . . . . . . . . . UNDAMAGED

Horizontal Stabilizer . . . . . . . . . . . . GOOD CONDITION

Static Dischargers . . . . . . . . . UNDAMAGED/SECURE

Vertical Fin . . . . . . . . . . . GOOD CONDITION/INSPECT


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F Aft Compartment

Aft Compartment Door . . . . . . . . . . . . . . . . . . OPENElectrical Panel . . . . . . . . . . . . . . . . . . . . INSPECT

Circuit Breakers (Figure 2A-1) . . . . . . . . . . . . . . . IN

See Systems, page 4-18, for a functional description of

these circuit breakers.Generator Switches . . . . . . . . . . . . . . . . GUARDED

Batteries . . . . . . . . . . . . . . . . . . . . . CONNECTED

Apply clockwise pressure to each connector knob to ensure

connector is seated.Hydraulic Reservoirs . . . . . GOOD CONDITION/LEAKAGE

Fluid Level (sight gages) . . . . . . . OPERATION RANGE

Standby Pump Selector . . . . . . . . . . . SAFETY-WIRED/

IN FLIGHT POSITION

Engine Fire Extinguisher Gages (3) . . . CHECK PRESSURE

Determine proper pressure according to information on the


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Preight Inspection

Circuit Breakers


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G Lower Aft Fuselage

Fire Extinguisher Blowout Discs . . . . . . . . ALL IN PLACEBaggage Compartment . . . . . . . . . . GOOD CONDITION

Baggage/Aft Compartment

Fire Bottle Indicators . . . . . . . . . . . . 575 TO 625 PSI

To open the baggage compartment door, push the ushtab forward of the handle. The handle pops out. Rotate the

handle clockwise to unlock the door. Lower the door gently

to full open.

To close the baggage compartment door, raise it to full

closed position. Firmly rotate the handle counterclockwiseas far as it will go. Be sure the tab forward of the handle is

ush with the skin; then stow the handle by pushing it in.

Observe the four visual indicators are properly aligned.

A missing disc and associated red indication meanNOTE:the associated bottle has discharged and must be

relled and disc replaced


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Airbrakes . . . . . . . . . . RETRACTED/GOOD CONDITION

Some creepage from stowed position is common.

Static Dischargers . . . . . . . . . . UNDAMAGED/SECURE

Note any missing static dischargers.

Left Aileron . . . . . . . . . . . . . . . . . GOOD CONDITION

Actuator . . . . . . . . . . . . . . SECURE/NO LEAKAGE

CAUTION

The carbon-ber reinforced plastic aileron requires special

care when cleaning. Consult the Maintenance Manual for

scouring and cleaning information.


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Preight Inspection

I Forward Left Wing

Left Wing Tip . . . . . . . . . . . . . . . . . . . UNDAMAGEDNavigation/Strobe Lights . . . . . SECURE/UNDAMAGED

Left Wing Underside . . . . . . UNDAMAGED/NO LEAKAGE

Left Wing Leading Edge Slats . . . . . . GOOD CONDITION

Gravity Fueling Port Fuel Cap . . . . . . . . . . . . SECURECheck for evidence of tampering.

Lifeline Attach Point . . . . . . . . . . . . . UNOBSTRUCTED

Left Emergency Exit Door . . . . . FLUSH WITH FUSELAGE

Outside Access Red Button Cover . . . . . . . .IN PLACEFolding Ladder . . SECURE TO FUSELAGE ATTACH POINTS

No.2 Engine Intake . . . . . . . . CLEAR/GOOD CONDITION

Folding Ladder . . . . . . . . . REMOVE FROM FUSELAGE

ATTACH POINTS

Verify ladder attach points (spring-loaded discs)NOTE:


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Left Landing Light . . . . . . . . . . . CLEAN/UNDAMAGED

Vent . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Left Wing Ice Inspection Light

(if installed) . . . . . . . . . . . . . . . GOOD CONDITION

Oxygen Filler Cover . . . . . . . . . . . . . . . . . . SECURE

Vent Disc . . . . . . . . . . . . . . . . . . VERIFY INTACT

Oxygen Pressure Gage . . . GREEN RANGE (SUFFICIENT

FOR PLANNED FLIGHT)

Standby Inverter CB

(forward of entry door, if installed) . . . . . . . . . . . . . IN

Cabin Door Seal . . . . . . . . GOOD CONDITION/ALIGNED

Entrance Stairs . . . . . . . . . . . . . . . . . . . . INSPECT

Step Storage Doors . . . . . . . . . . . CLOSED/SECURE

Handrail/Guide Arms/Door Hinges . . . . . . . . SECURE


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Preight Inspection

Interior/Passenger Loading

Baggage . . . . . . . . . . . . . . . . . . . . . . . SECUREDCabin Door . . . . . . CLOSED/LATCHED/UNOBSTRUCTED

Emergency Exits . . . . . . . . . . . . . . . ACCESS CLEAR

Passenger Brieng . . . . . . . . . . . . . . . . . COMPLETE

According to Part 91.519 requirements, the pilot-in-commandor a crewmember briefs the passengers on smoking, use of

safety belts, location and operation of the passenger entry

door and emergency exits, location and use of survival

equipment, and normal and emergency use of oxygen

equipment. For ights over water, the brieng should includeditching procedures and use of otation equipment.

An exception to the oral brieng rule is if the pilot-in-command

determines the passengers are familiar with the brieng

content. A printed card with the above information should be

available to each passenger to supplement the oral brieng.Passengers Seat Belts . . . . . . . . . . . . . . . FASTENED

K ON BOARD/STOWED


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Expanded Normal Procedures

Table of ContentsChecklist Usage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-3

Normal Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-4

Before Starting Engines. . . . . . . . . . . . . . . . . . . . . . . . . . .2B-4

Starting Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-18After Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-20

Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-25

Before Takeoff. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-26

Lineup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-27Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-28

Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-29

Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-30

Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-30Before Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2B-33


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Falcon 50 2B-3

October 1997 Developed for Training Purposes Only


Checklist Usage

Tasks are executed in one of two ways:

as a sequence that uses the layout of the cockpit controls and

indicators as cues (i.e., ow 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 ow pattern or series provides organization and

serves as a memory aid.

A challenge-response review of the checklist follows execution of

the tasks; the PNF calls the item, and the appropriate pilot responds

by verifying its condition (e.g., Engine Anti-Ice [challenge] ON

[response]).

Two elements are inherent in the execution of normal procedures:

use of either the cockpit layout or event cues to prompt the correct

switch and/or control positions

use of normal checklists as done lists.


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2B-4 Falcon 50

Developed for Training Purposes Only October 1997

Cockpit Flow Pattern

D5_

En_

001.a

i

Normal Procedures

Before Starting Engines

Power Off Cockpit Flow Check

Pilots Oxygen Mask . . . . . . . . . . . . . . . . CHECKED

Press the red button and listen for a hiss in the oxygen mask.

INS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

HF Radio . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Compass . . . . . . . . . . . . . . . . . . . . . . . . SLAVED

Pilots Audio Panel . . . . . . . . . . . . . . . . . . . . . SET

Audio (Listen) SPK, ST (Side Tone),

VHF1 and VHF2, and CPIT . . . . . . . . . DEPRESSED

Microphone Selectors VHF2 . . . . . . . . . DEPRESSED

Volume Control . . . . . . . . . . . . . . . . . AS DESIRED

VHF2 is usually the primary communication radio.

Floor Switch . . . . . . . . . . . . . . . . . . . . . . . . OFF

Check that pilots FLOOR heat switch is off.

Static Selector . . . . . . . . . . . . . . . . . . . . NORMAL

Clock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

Emergency Horizon . . . . . . . . . . . . . . . . . . CAGED

Parking Brake . . . . . . . . . . . INTERMEDIATE DETENT

Fire Handles . . . . . . . . . . . . . . . . . . . . . . . . . . IN

Extinguisher Switches (6) . . . . . . . . . ZERO/SAFETIED

Landing Gear Lever . . . . . . . . . . . . DOWN/LATCHED

EMERG Gear Pull Handle . . . . . . . . . . . . IN/LATCHED


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Pressurization Controller . . . . . . . . . . . . . . . . . SET

RATE Knob . . . . . . . . . . . . . . . . . . . . . DETENT

BARO Knob . . . . . . . . . . . GREEN MARKS ALIGNED

AT 29.92 IN.HG.

ALT Knob . . . . . . . . . . . . . . . . . . . FLIGHT LEVEL

(DESTINATION ELEVATION)

Move the pointer to intended ight level plus 1,000 ft ordestination eld elevation on the outer scale, whichever

results in a higher reading.

Pressurization Selector Switch . . . . . GUARDED/AUTO

Manual Pressurization Control . . . . . . . . . . . . . . DNTurn knob fully counterclockwise (i.e., arrow on the green

DN mark).

Thrust Reverser Switch . . . . . . . . . . . . . . GUARDED

Radar . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OF

Brake Switch . . . . . . . . . . . . . . . . . . . . . . . #1/ON

Standby Pump OFF


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Copilot Oxygen Mask . . . . . . . . . . . . . . . CHECKED

Press the red button and listen for a hiss in the oxygen mask;

observe no loss of pressure on the oxygen pressure gage.

Compass . . . . . . . . . . . . . . . . . . . . . . . . SLAVED

Copilots Audio Panel . . . . . . . . . . . . . . . . . . . SET

Audio (Listen) SPK, ST (Side Tone),

VHF1 and VHF2 . . . . . . . . . . . . . . . . DEPRESSED

Microphone Selectors VHF2 and CPIT . . . DEPRESSED

Volume Control . . . . . . . . . . . . . . . . . AS DESIRED

VHF2 is usually the primary communication radio.

Floor Switch . . . . . . . . . . . . . . . . . . . . . . . . OFF

Check that copilots and third crewmembers oor switch is

off.

Nose Cone Lever . . . . . . . . . . . . . . . . . . . . . OPEN

Oxygen Quantity . . . . . . . . . . . . . . . . . . CHECKEDThe pressure gage should indicate a maximum of 1,850 PSI

on a standard da For minim m press re refer to General


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Bleed Air Panel . . . . . . . . . . . . . . . . . . . . . . . SET

CABIN/CREW . . . . . . . . . . . . . . . . . . . . . . AUTO

BAG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

ISOLATION Valve . . . . . . . . . . . HORIZONTAL (TIED)

HP1, HP3, HP2, PRV . . . . . . . . . . . . . . . . . AUTO

Inverters/AC1 & AC2 . . . . . . . . . . . . . . . . . . . . OFF

Standby Inverter . . . . . . . . . . . . . . . . CENTER/OFF

XFR Pumps (3) . . . . . . . . . . . . . . . . . . . . . . . OFF

XFR INTERCOMS (2) . . . . . . . . . VERTICAL (CLOSED)

Booster Pumps (3) . . . . . . . . . . . . . . . . . . . . . OFF

X Feeds (2) . . . . . . . . . . . . . . . VERTICAL (CLOSED)

Windshield Heat Switches (3) . . . . . . . . . . . . . . OFF

Pitot Heat Switches (2) . . . . . . . . . . . . . . . . . . OFF

Start Selectors (3) . . . . . . . . . . . . . . . . GRD START

Engine Computer Switches (3) . . . . . . . . . . . . . . ON

Power Selector Switch (DC) . . . . . . . . . . . . NORMAL


36/401

Power On, Part 1

Batteries . . . . . . . . . . . . . . . . . . . . . ON/CHECKED

Turn the battery switches ON. Observe activation of aircraft

electrical systems. Observe BAT 1 and BAT 2 annunciators

extinguish on the Failure Warning Panel. Check that Left

and Right Main bus voltages are more than 24V. Observe

nominal load on ammeters.

Main Bus Tie (LH-RH Bus) Selector . . . . . . . . . . TIED

Observe illumination of the BUS TIED annunciator. Buses

must be tied for APU start.

C and D Bus Switches . . . . . . . . . . . . . . . . . . TIED

External Lights . . . . . . . . . . . . . . ON AS REQUIRED

Fire Warnings . . . . . . . . . . . . . . . . . . . . . TESTED

Press to test. Observe illumination of the three engine

FIRE PULL handle lights, the APU FIRE, WHEELS, FIRE

BAG COMPT, and FIRE AFT COMPT annunciators. There warning horn sounds. Silence the horn with the HORN

SILENCE button on the pedestal.


37/401


*Landing Gear Panel . . . . . . . . . . . . . . . . . TESTED

Press the TEST button on the landing gear control panel. Check

for the landing gear aural warning, and observe illumination ofthe:

red and green GEAR indicator lights

ashing light in the gear handle

SLATS red and green lightsAIR BRAKE light.

Silence the aural warning with the HORN SILENCE button.

*T/O CONFIG/NO. 2 ENG FAIL . . . . . . . . . . . . TESTED

Advance the No. 2 power lever to takeoff position. Observeillumination of the T/O CONFIG and the ENGINE 2 FAIL

annunciators; return the power lever to cutoff, and observe the

annunciators extinguish.

APU/GPU/No. 2 Engine . . . . . . . . . . . . . . . STARTED

APU Start:

No. 2 Booster Pump . . . . . . . . . . . . . ON/LIGHT OUT


38/401

APU . . . . . . . . . . . . . . . . . . . . . . . . . . . START

Press the APU MASTER button. Observe illumination of the

MASTER button. Press the GEN light switch, which ener-gizes the START button relays. Press the APU START but-

ton. Observe an increase in APU N1 RPM. Observe ignition

on the EGT gage when RPM exceeds 10%. Maximum EGT

during start is 975 C. Maximum stabilized EGT is 735C.

Stabilized RPM is 100%. To discontinue start and shutdownAPU, press the STOP/LOP button. If that fails, press the

MASTER button.

On aircraft with SBF50-0051, automatic APU shutdown occurs

for:

overtemperature

overspeed

low oil pressure

re detection

ight/ground relays inight

APU accessories overcurrent.


39/401


GPU Start (Maximum 1,000A at 28V):

If a ground power unit is used in lieu of the APU, stop at APU

START in the above checklist. A suitable ground power unit iscapable of producing 28V at 1,000A and has current protection

against loads higher than 1,000A.

Generators will not come on line until the externalNOTE:

power plug pin No. 3 is not powered.

Power Selector . . . . . . . . . . . . . . . . . EXT POWER

Set the power selector switch to EXT POWER position.

Battery Lights . . . . . . . . . . . . . . . . . . . . . . . ON

Observe the BAT 1 and BAT 2 annunciators illuminate.

Bus Voltage . . . . . . . . . . . . . . . . . . . . . . . . 28V

Check Main bus voltage on both voltmeters. Continue with

Before Start checks.


40/401

Engine No. 2 Gen . . . . . . . . . . . . . . . . . . . . . ON

Engine No. 2 Computer . . . . . . . . . . . . . . . . . . ON

Engine No. 2 Start Selector . . . . . . . . GROUND START

Engine No. 2 Start Button . . . . . . . . . . . . . . . PUSH

Hold the start button for approximately 2 seconds. Release.

Observe N2 rotation. At greater than 10% N

2, observe N

1

rotation.Batteries . . . . . . . . . . . . . . . . . . . CHARGE RATE

Power Lever (with N1 rotation) . . . . . . . . . . . . . IDLE

Observe the IGN light illuminates, then observe ignition by a

rise in ITT. Ignition must occur within 10 seconds of advancing

the power lever to IDLE. Observe oil pressure indications within

10 seconds of ignition indications. Observe idle stabilized within

50 seconds of ignition. Maximum allowable ITT during engine

start is 907C. If the following do not occur, abort start.

ITT should stay within maximum limit of 907C.

Both N1and N

2rise smoothly to their normal idle values.

Oil i ithi 10 d f i iti


41/401


Power On, Part 2

INVERTERS . . . . . . . . . . . . . . . . . . . CHECKED/ON

Check as follows.

AC 1 Switchlight . . . . . . . . . . . . . . . . . . . . . . ON

ST-BY Inverter Switch . . . . . . . . . . . . . . . . . . LEFT

AC 1 Light . . . . . . . . . . . . . . . . . . . . . . . . . OUT

AC Voltage . . . . . . . . . . . . . . . 115V (110 TO 120V)

AC 1 Inverter Switch . . . . . . . . . . . . . . . . . . . . ON

ST-BY Inverter Switch . . . . . . . . . . . . . . . CENTER

AC 1 Light . . . . . . . . . . . . . . . . . . . . . . . . . OUT

AC Voltage . . . . . . . . . . . . . . . 115V (110 TO 120V)

AC 2 Switchlight . . . . . . . . . . . . . . . . . . . . . . ON

ST-BY Switch . . . . . . . . . . . . . . . . . . . . . RIGHT

AC Voltage . . . . . . . . . . . . . . . 115V (110 TO 120V)

AC 2 Light . . . . . . . . . . . . . . . . . . . . . . . . . OUT

AC 2 Switch . . . . . . . . . . . . . . . . . . . . . . . . ON


42/401

EFIS Masters (if installed) . . . . . . . . . . . . . . . . . ON

INS/IRS . . . . . . . . . . . . . . . . . . . . . . STBY/ALIGN

FMS (if installed) . . . . . . . . . . . . . . . . . INITIALIZED

Seat Belt/No Smoke lights . . . . . . . . . . . . . . . . . ON

Emergency Exit Lights . . . . . . . . . CHECKED/ARMED

Place the emergency lights switch to ON. Observe illumination

of the cockpit dome lights, the entry door emergency light,the overwing hatch emergency lights, and the annunciator in

the overhead panel. Place the switch to ARMED and observe

that the lights and the annunciator extinguish.

Seats and Pedals . . . . . . . . . . . . . . . . . ADJUSTED

Pull the lever at the base of the instrument panel to position

the rudder pedals. Raise the lever under the outboard front

of the seat to adjust it fore and aft. A rocker switch on the

outboard side of the seat raises and lowers the seat. A but-

ton aft of the vertical adjustment switch allows adjustment

of the seat back.

Battery Temperature Indicators . . . . . . . . . . . TESTED


43/401


Fuel/Gross Weight Counters . . . . . . . . . ZEROED/SET

Pull the gross weight counter knob. The fuel used counter

zeroes automatically. Turn the same knob to + or to setgross weight. Pull the reset knob on each of the engine fuel

ow indicators to zero the counters.

FUEL TOT and REAR . . . . . . . . . . . . . . . CHECKED

Using TOT/REAR selector, check that fuel quantities are

correct in the feeder tanks (rear position) and in the feeder

tank and associated wing tank (position TOT). After checking

TOT, place switch in REAR position. This is the normal ight

position that permits a fast check for proper fuel transfer to

the three feeders.

Hydraulic Quantity . . . . . . . . . . . . . . . . . CHECKED

Quantity should be 3/4 or more to remain in the green after

start.

*Standby Pump . . . . . . . . . . . . . . . . . . . ON/AUTO

Move the standby pump switch to ON and observe hydraulicsystem 2 pressure rise to 2,150 PSI, then cycle between 1,500

d 2 150 PSI M th it h t AUTO d b ti d


44/401

*STALL 2 (and AUTO SLATS LIGHT

if SB F50-0166 installed) . . . . . . . . . . . . . . TESTED

Press the STALL 2 test button. The stall warning horn

sounds; it cannot be silenced. The three IGN lights

illuminate. Observe a red SLATS in transit light, then a

green SLATS extended light as the outboard slats are

automatically extended. Visually conrm slat extension.

Hold the button depressed ve seconds; the AUTO SLATSlight illuminates. Release the button. The stall warning

horn stops, the slat green light extinguishes and the slat

red light illuminates. The ignitor lights extinguish after ten

seconds. The outboard slats remain extended unless the

No. 2 engine is running.*Trims (5) . . . . . . . . . . . . . . . . . . . . CHECKED/SET

Individually activate the half switches for the three normal

trim systems (i.e., aileron, stabilizer, and rudder). Observe

no movement of the yoke/pedals and no movement of the

associated trim indicator. Activate the normal trim switchnose-up on the pilots yoke. While the trim is moving,


45/401


*Airbrakes . . . . . . . . . . . . . . . CYCLED/POSITION 0

Move the airbrake handle to position 1. Observe illumination of

the AIR BRAKE light on the landing gear panel; visually checkextension of the center panel on each wing. Move the handle

to position 2; visually check extension of all three airbrake

panels on each wing. Move the airbrake handle to position 0

(retracted). Observe the AIR BRAKE light extinguish; visually

check that all airbrake panels stow.*Standby Pump . . . . . . . . . . . . . . . . . . . . . . . OFF

Radar Altimeter . . . . . . . . . . . . . . . . . . . . TESTED

*Radio Master, Radios . . . . . . . . . . . . . . ON/TESTED

Obtain current ATIS information and ATC clearance.RMI Selectors . . . . . . . . . . . . . . . . . . . . . . . . SET

Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . SET

Altitude Alert (ASEL) . . . . . . . . . . . . . . . . . . . . SET

Pressurization . . . . . . . . . . . . . . . . . CHECKED/SETSet pressurization for cruise altitude if it was not set during

k it h k


46/401

Starting Engines

Parking Brake . . . . . . . . . FULL FORWARD/FULL AFTObserve the #2P.BK light extinguishes at forward position.

#2P. BK Light . . . . . . . . . . . . . . . . . . . ON STEADY

Cabin Warning Light . . . . . . . . . . . . . . . . . . . OUT

Fuel Booster Pumps . . . . . . . . . . . . . . . . . . . . ONSelect the No. 1 and 3 BOOSTER pumps on; select the No.

2 BOOSTER pump on. Check the FUEL 1, FUEL 2, and

FUEL 3 annunciators extinguish.

External Lights . . . . . . . . . . . . . . ON AS REQUIRED

Engines . . . . . . . . . . . . . . . . . . . . . . . . . START

Recommended start sequences are 2-3-1 or 3-2-1.

Start Button . . . . . . . . . HELD 2 SECONDS/RELEASED

Observe N2rotation.

At 12 to 15% N2and with N

1indicating rotation:

Power Lever . . . . . . . . . . . . . . . . . . . . . . . . IDLE


47/401


ITT does not rise within 10 seconds of ignition on (i.e., power

lever advanced to idle).

Oil pressure does not rise within 10 seconds after ignition.

ITT is rising rapidly toward the 907C limit.

N1or N

2does not rise rapidly and smoothly to idle RPM (57

to 62% N2).

Terminate the start sequence manually if the IGN light remainsilluminated with N

2RPM above 50%.

Aborted Engine Start

Power Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF

Start Selector . . . . . . . . . . . . . MOTOR-START-STOP

Dry Motoring

Power Lever . . . . . . . . . . . . . . . . . . . . . . CUTOFF

Start Selector . . . . . . . . . . . . . MOTOR-START-STOP

Start Button (15 seconds maximum) . . PUSH AND HOLD

ITT must be less than 200C for subsequent start


48/401


49/401


50/401

Windshield/Side Heat . . . . . . . . NORMAL/NORMAL/ON

Airframe Anti-Ice . . . . . . . . . . . . . . . . . . CHECKED

Check rst ight of day or if weather conditions warrant.

Airframe Anti-Ice Switch . . . . . . . . . . . . . . . . NORM

As soon as ITT rise is observed:

Airframe Anti-Ice Switch . . . . . . . . . . . . . . . . ST-BY

Observe that ITT continues to rise on engines No. 1 and 3.

Airframe Anti-Ice Switch . . . . . . . . . . . . . . . . . OFF

Observe ITT on engines No. 1 and 3 return to approximately

the values they were at before the check.

*Engine Anti-Ice . . . . . . . CHECKED/ON AS REQUIRED

Bleed Air PRV Switch . . . . . . . . . . . . . . . . . . OFF

Observe that engine No. 2 ITT decreases.

Engine Anti-Ice Switches . . . . . . . . . . . . . . . . . ON

Turn engine anti-ice switches for engines No. 1, 2, and 3

ON OBserve ITT rise on all three engines


51/401


52/401

Standby Pump . . . . . . . . . . . . . . . . . . . . . . . . ON

Cockpit Voice Recorder . . . . . . . . . . . . . . . TESTED

Flight Recorder (if installed) . . . . . . . . . . . CHECKED

Flight Recorder (if installed) Date and Time . . . . . . SET

Radios/Navs . . . . . . . . . . . . . . . . . . ON/CHECKED

*STALL 1 (and AUTO SLATS Light

if SBF50-0166 is installed) . . . . . . . . . . . . TESTED

Press the STALL 1 test button; the three IGN lights illuminate.

Observe sounding of the stall warning horn; the horn cannot

be silenced. Observe the red slats-in-transit light illuminate;

the red light extinguishes and the green slats extended light

illuminates. Visually check the outboard slats extended. With

SB F50-166 installed, hold the button depressed for ve

seconds; the AUTO SLATS light illuminates. Release the

button and observe the green slats extended light extinguish;

the red in-transit light illuminates then extinguishes when the

outboard slats are retracted. The three IGN lights extinguishin ten seconds.

E d d N l P d


53/401


TaxiTaxi Light . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Parking Brake . . . . . . . . . . . . . . . . FULL FORWARD

Steering . . . . . . . . . . . . . . . . . . . . . . . CHECKED

Depress the steering wheel and turn in each direction; observe

appropriate aircraft turns.

Brakes (#2 and #1) . . . . . . . . . . . . . . . . . CHECKED

Move brake selector switch to #2 position and push each

brake individually; observe the #2P.BK light illuminate and

the aircraft slowing. Move brake selector switch to #1/ON.

Push the brakes sufciently to verify the #1 brakes are again

functioning.

*Slats/Flaps . . . . . . . . . . . . . . . . . . . CYCLED/SET

Sequentially (i.e., one position at a time) set the SLAT/

FLAP handle to S + FLAPS 48, then back to S + FLAPS

20. Observe slat and ap extension and retraction on the

indicators. Check for proper indication at each stop of the

SLAT/FLAP handle. From the S + FLAPS 20 position,


54/401

Before Takeoff

Trims (3) . . . . . . . . . . . . . . . . . SET FOR TAKEOFFSlats/Flaps . . . . . . . . . . . . . . . . SET FOR TAKEOFF

Flight Controls . . . . . . . . . . . . . . . . . . . CHECKED

Move all three ight controls through full travel. Ensure that

they return to neutral, with no binding.

Cockpit Window . . . . . . . . . . . . . . CLOSED/LOCKED

Check that the green band on the release button is visible.

Crew Brieng . . . . . . . . . . . . . . . . . . . COMPLETE

In accordance with current SOP, brief rst assigned heading,

altitude, x and emergency intentions.

Flight Instruments . . . . . . . . . . . . SET FOR TAKEOFF

Check that avionics, radios, and ight instruments are properly

set for departure.

APU BLEED, GEN, MASTER . . . . . . . . . . . . . . . OFFAPU MASTER switch to off after APU N

1 is less than 1%



55/401


Lineup

Start Selectors (3) . . . . . . . . . . . . . . . . . AIR STARTIGN lights illuminate.

Pitot Heat Switches (2) . . . . . . . . . . . . . . . . . . . ON

The L PITOT and R PITOT annunciators extinguish.

Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . OFF (ON)Set as required according to weather conditions.

Exterior Lights . . . . . . . . . . . . . . ON AS REQUIRED

Warning Lights/Flags . . . . . . . . . . . . . . . . . CLEAR

Radar . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONTransponder . . . . . . . . . . . . . . . . . . . . . . . . . ON


56/401

Climb

Start Selectors (3) . . . . . . . . . . . . . . . . GRD STARTIGN lights extinguish.

Anti-Ice (Eng/Airframe) . . . . . . . . . . . . . . . OFF(ON)

Set as required by meteorological conditions.

Taxi Light . . . . . . . . . . . . . . . . . . . . . . . . . . OFFNo Smoking . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . UP

Slats/Flaps . . . . . . . . . . . . . . . . . . . . . . . CLEAN

Standby Pump . . . . . . . . . . . . . . . . . . . . . . AUTOPressurization/Temperature Controllers . . . . CHECKED

Check cabin altitude and differential PSI on the triple indicator

for proper operation. Adjust temperature controls as required

for passenger/crew comfort.

Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . ON

Above 10,000 Ft



57/401


Cruise

The following checklist should be accomplished on a formalbasis after level-off, at one hour intervals during cruise, and prior

to beginning descent.

Entrance Door Curtain . . . . . . . . . . . . . . . . CLOSED

Systems Checks . . . . . . . . . . . . . . . . COMPLETED

Circuit Breakers . . . . . . . . . . . . . . . . . . . ALL SET

Electrical Systems . . . . . . . . . . . . . . . . . . CHECK

Check Main bus voltage and generator and battery

loads. Check AC 1 and AC 2 volts.

Fuel System . . . . . . . . . . . . . . . . . . . . . . CHECKCheck quantities; regulation levels; maintain balance;

crosscheck fuel used counters.

Engines . . . . . . . . . . . . . . . . . . . . . . . . CHECK

Check all engine parameters.Hydraulic System . . . . . . . . . . . . . . . . . . . CHECK


58/401

Descent

Pressure/Temperature Controllers . . . . . . . . . . . SETSet landing eld elevation on the pressure controller. For

alternate setting procedures, see Maneuvers chapter.

Cockpit Curtain/Door . . . . . . . . . . . . . . . . . . OPEN

Entrance Door Curtain . . . . . . . . . . . . . . . . . OPEN

Anti-Ice Systems . . . . . . . . . . . . . . . . . . . ON (OFF)

Select anti-icing ON before entering icing conditions.

Altimeters (Transition Level) . . . . . . . . . . . . SET QNH

Exterior Lights . . . . . . . . . . . . . . ON AS REQUIRED

Turn landing lights, anti-collision lights, and ice inspection

lights on before passing FL 180 transition level.

Seat Belt/No Smoking . . . . . . . . . . . . . . . . . . . ON

Select on prior to passing 10,000 ft.

Approach



59/401


Crew Brieng . . . . . . . . . . . . . . . . . . COMPLETED

The crew brieng should be completed prior to 18,000 ft

when possible, and should include the following items.

Review TOLD card including weather, eld conditions,

and speeds.

Set bugs on both airspeed indicators.

If weather or runway conditions are adverse or any

aircraft systems are inoperative, discuss intentions and

special instructions.

Review the approach procedure:

approach to be executed

eld elevation

if a procedure turn, inbound course to the FAF, side of

procedure turn, and initial altitude.

inbound heading of the nal approach course.

nal approach course intercept altitudetiming


60/401



61/401


Before Landing

Landing Gear . . . . . . . . . . . . . . . . . . . . . . DOWNHydraulic Pressures/Quantities . . . . . . . . . CHECKED

Anti-Skid . . . . . . . . . . . . . . . . . . . . . . . . TESTED

Depress the brake pedals. The green L and R lights remain

extinguished. Press and release the ANTI-SKID test button.

The green L and R lights illuminate until the test button isreleased. After approximately one-half second, the green L

and R lights illuminate again for two seconds, then extinguish.

Release the brake pedals; observe the L and R lights remain

extinguished.

Start Selectors . . . . . . . . . . . . . . . . . . . AIRSTART

IGN lights illuminate.

*STALL 1 and STALL 2 . . . . . . . . . . . . . . . . TESTED

Press the STALL 1 and STALL 2 test buttons. No indication

hould occur. An active test indicates a failure in the ight/ground detection system. Test is not required if SB F50-0166

i i t ll d


62/401

After Landing

Main Bus Tie LH-RH Bus Selector . . . . . . . . . . . TIEDObserve BUS TIED light illuminated.

Start Selectors . . . . . . . . . . . . . . . . . . GRD START

Observe IGN lights extinguish.

Pitot Heat Switches . . . . . . . . . . . . . . . . . . . . OFFWindshield/Side Heat . . . . . . . . . . . . . . . . . . . OFF

Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . OFF/(ON)

In icing conditions, leave the engine anti-ice on.

Airframe Anti-Ice . . . . . . . . . . . . . . . . . . . . . . OFFAnti Collision Lights . . . . . . . . . . . . . . . . . FUS/RED

Landing Lights . . . . . . . . . . . . . . . . . . . . . . . OFF

Radar . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Transponder . . . . . . . . . . . . . . . . . . . . . STANDBY

Thrust Reverser . . . . . . . . . . . . . . . . . . . STOWED



63/401


Shutdown

Trims . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFFRadios/INS/IRS . . . . . . . . . . . . . . . . . . . . . . . OFF

FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Parking Brake . . . . . . . . . . . . . . . . . . . . FULL AFT

EFIS Masters (if installed) . . . . . . . . . . . . . . . . OFFInverters . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . OFF

Standby Horizon . . . . . . . . . . . . . . . . . . . . CAGED

Emergency Bat 2 Power (if installed) . . . . . . . . . . OFF

Standby Pump . . . . . . . . . . . . . . . . . . . . . . . OFF

Power Levers . . . . . . . . . . . . . . . . . . . . . CUTOFF

Transfer (XFR) Pumps (3) . . . . . . . . . . . . . . . . . OFF

Booster Pumps (3) . . . . . . . . . . . . . . . . . . . . . OFF

Exterior/Interior Lights . . . . . . . . . . . . . . . . . . OFF


64/401

Multiple Start Attempts

After an unsuccessful start attempt that did not exceed a durationof 40 seconds of starter operation, proceed as follows.

After a one-minute stop, perform a dry motoring for not more

than 15 seconds followed by a two-minute stop. Perform

another start attempt; interrupt it if start termination is not

reached within 30 seconds (instead of 40 seconds for the rstattempt). If unsuccessful, allow another two-minute stop, then

perform a second motoring (limited to 15 seconds) followed by

a one-minute stop. Perform a third and last start attempt (for

30 seconds); if unsuccessful, interrupt the start. During the

30-minute cooling cycle, attempt to identify the fault.

Attempt another start only if ITT drops to below 200C.

Limit start attempts to a maximum of three for the same engine.

After three attempted starts, observe a cooling period of 30

minutes, minimum. The delay between two successive start

attempts should be multiplied by two in hot weather conditions(temperatures above 30C [86F]).



65/401


Parking

Aircraft . . . . . . . . . . . . . . . . . . PARKED INTO WINDPark the aircraft in a laterally level condition. If the parking

area is pitched, level the lateral axis.

Battery Switches . . . . . . . . . . . . . . . . . . . . . . OFF

Parking Brake . . . . . . . . . . . . . . . . . . . . . . . . SET

Push the button on the PARK BRAKE handle to unlock, then

pull out to set to intermediate detent.

CAUTION

Do not set brakes permanently while they are heated.

Main Landing Gear Wheels . . . . . . . . . . . . CHOCKED

Park Brake . . . . . . . . . . . . . . OFF (FULL FORWARD)

There is no locking system for either the controlNOTE:surfaces or linkages. When the aircraft is parked

and engines sh t do n stored h dra lic press re


66/401

Postight

Protective Covers . . . . . . . . . . . . . . . . . INSTALLEDEntry, Aft and Baggage

Compartment Doors . . CLOSED/LOCK AS REQUIRED

Engine Oil Level . . . . . . . . . . . . . . . . . . CHECKED

Check oil level within one hour of shutdown.Engine Oil Filter and

Fuel Filter Bypass Pins . . . CHECKED NOT EXTENDED

General Postight Inspection . . . . . . . . . PERFORMED

MooringIn Severe Storm or Wind Conditions (30 kts or higher):

Main Landing Gear Wheels . . . . . . . . . . . . CHOCKED

Mooring Fitting Caps . . . . . . . . . . . . . . . REMOVEDTiedown Rings . . . . . . . . . . . . . . . . . . INSTALLED



67/401


Towing and Taxiing

Tow the aircraft forward or push aft with a manufacturer-ap-proved towbar attached to the nose gear. If the aircraft is towed

from soft sand, earth, or mud, or if nose gear towing exceeds

the towbars structural limitations, use the main gear to tow the

aircraft.

The minimum turning radius (Figure 2B-1, following page) isshown below.

With Steering Disconnected . . . . . . . . . . . . . 36.7 FT

With Steering Engaged (taxi only) . . . . . . . . . . 44.3 FT

A crewmember or qualied person must be in the cockpit during

towing operations to watch for hazardous conditions and to stopthe aircraft if the towbar disengages.

Nose Gear TowingCabin Door . . . . . . . . . . . . . . . . . . . . . . CLOSED

Steering Control . . . . . . . . . . . . . . DISCONNECTED

Towbar . . . . . . . . . . . . . . . . . . . . . . . ATTACHED


68/401

Turning and Towing Radius

0.365 M (1.19 FT.)

3.980 M (13.05 FT.)

60

p11

.2M(36.74

FT.)

S

TEERIN

GC

ONTR

OLRELE

ASED

TOWIN

GR

ADIU

S

p13

.5M

(44

.29FT.)

S

TEERIN

GCONTROL

ENGA

GED

TAXIING

RADIUS



69/401


Extrication From Soft Ground

The manufacturers extrication towing bridle and a tractor

towbarattached to the main gear removes the aircraft from soft

ground.

Aircraft . . . . . . . . . . . . . . . . . . . . . . .CENTERED

Defuel the aircraft if necessary to balance and/or reduce

weight.Baggage and Passenger

Compartments . . . . . . . .UNLOADED IF REQUIRED

Landing Gear . . . . . . . . . . . . . . . . . . . .CHECKED

Check the landing gear locking and install downlockingsafetydevices. Remove the tachometer generators and their

mountsfrom each main landing gear axle.

Extrication Tool . . . . . .INSTALLED ON MAIN WHEELS

Steering Control . . . . . . . . . . . . . .DISCONNECTED

Tractor Towbar . . . . . . . . . . . . . . . . . .INSTALLED

Aircraft TOWED STRAIGHT AHEAD ONLY


70/401



71/401


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73/401

p

Cold Weather Operations

PreightAircraft . . . . . . . . . SNOW, ICE, OR FROST REMOVED

Snow, ice, or frost accumulation on the aircraft may cause

serious aerodynamic disturbances and unbalanced ight

loads, which could damage the structure in ight. Such ac-

cumulations can adversely affect takeoff distance and climbperformance.

Control Surfaces . . . . . . . . . . . . CLEARED OF SNOW

OR FROZEN ACCUMULATION

To ensure proper travel, remove all traces of snow or other

frozen accumulation, and ensure no water refreezes after

deicing with heated air.

CAUTION

Do not spray deicing uid in areas where spray or uid can

enter the engine or APU inlets. If deicing uid is used to cleanthese areas, thoroughly wipe it clean before starting.


74/401

Slats, Brake Units, Struts, Actuators . . . . . . CHECKED

Check for hydraulic leaks. See the Operating Manual, Section

2 for strut ination.Cabin and Cockpit . . . . . . . . . . . . . . . . PREHEATED

Preheat these areas for passenger and crew comfort as well

as for proper operation of the cockpit instruments.

APU . . . . . . . . . PREHEATED IF BELOW -35C (-31F)The APU may be heated by placing an 850-watt heating

blower by the air intake.

Engines . . . . . . . . . . . . . PREHEATED IF REQUIRED

The engines may be heated with two 850-watt heating

blowers, one placed in the intake and the other in theexhaust.

Batteries . . . . . . . . . . . . . REMOVED AND WARMED

Prior to starting, remove and warm the aircraft batteries,

including the standby horizon battery as well as those forthe INS/IRS, Omega, VHF No. 3, and emergency battery 2

(if installed)



75/401

p

StartingFirst Engine Start . . . . . . . . . . USE LOW TEMP START

For the rst engine start in ambient temperatures lowerthan -15C (5F), use a LOW TEMP START (i.e., batteries

in series). Use SPR, if necessary, at the beginning of each

start cycle; press and hold the SPR button until ITT reaches

400C.

Minimum temperature for engine starting is -40CNOTE:

(-40F), which is the minimum oil temperature

limitation.

Depending on the ambient temperature, APU andNOTE:

engine can be slower than normal. Oil pressure

peaks may be observed during starts.


76/401

After StartControl Surfaces . . . . . . . . . . . . . TRAVEL CHECKED

Cold hydraulic uid in the servo actuators combined with

congealed grease in bearings may prevent full control

surface travel, especially the ailerons. Check carefully to

ensure the sluggishness is not due to snow or ice.

Any sluggishness should cease after all controls are exercised

and the hydraulic uid is cycled. With the engines running,

move each control surface until the sluggishness dissipates.

Check full travel of all controls and trims, as well as slats,

aps, and airbrakes.

Windshield/Cockpit Windows . . . . . . . . . PREHEATED

IF NECESSARY

If the airframe temperature is -15C or below, the windshield

and cockpit side and aft windows must be preheated for 15

minutes prior to taxiing from the ramp.

TaxiPrior to taxiing, check ramp, taxiway, and runway conditions



77/401

p

TakeoffRunway . . . . . . . . . . . . . . . CONDITIONS VERIFIED

Measure depth of standing water, slush, or snow in a sufcientnumber of places to be representative of the entire length of

the runway required, particularly the high-speed portion of

the takeoff roll.

Parking Brake . . . . . . . . . . . . . . . . . . . RELEASED

Verify parking brake is released prior to takeoff on an icy or

snow-covered runway.

Takeoff . . . . . . . . . . . . CONTINUOUS IGNITION USED

During takeoff on wet or snow-covered runways, use

continuous ignition (AIRSTART position).

For additional recommendations for takeoff onNOTE:

contaminated runways, see the SimuFlite Technical

Manual, Maneuvers chapter.

Aft T k ff


78/401

LandingLandings may be attempted with up to a maximum of 3/4- inch

of wet snow, water, or slush for a short distance on the runway(1/2-inch if runway is continuously covered).

Landing Gear . . . . . . . . . . . . . . . . . . . EXTENDED

Brake Selector . . . . . . . #1/OFF/TOE BRAKES PUMPED

If takeoff was made from a snow- or slush-covered runway,before landing and after the gear is extended, move the

brake selector to #1/OFF. Pump the toe brakes several times

to exercise them and to prevent landing with the wheels

locked due to the accumulation of frozen slush.

Brake Selector . . . . . . . . . . . . . . . . . . . . . . #1/ONSelect #1/ON for landing for anti-skid protection.

For additional recommendations for landing onNOTE:

contaminated runways, see the SimuFlite Technical

Manual, Maneuvers chapter.



79/401

After LandingNosewheel Steering . . . . . . . . . . . USE IMMEDIATELY

Elevator . . . . . . . . . . . . . . . . . . . . . . NOSE DOWN

Nosewheel steering effectiveness increases with forward

pressure on the yoke.

Ailerons . . . . . . . . NEUTRALIZED DURING ROLLOUT

Slats/Flaps . . . . . . . . . . . . . . . . . . . S + FLAPS 20After landing on a contaminated runway, do not raise slats

and aps above S + FLAPS 20 until a visual inspection of

the slat and ap wells conrms no ice has accumulated that

could damage surfaces during retraction.

Parking and Securing AircraftAircraft . . . . . . . . . . . . . . . . . . . . . . . INTO WIND

Wheels . . . . . . . . . . . . . . . . . . . . . . . . CHOCKED

Parking Brake . . . . . . . . . . . . . . . . . . . RELEASED

Lavatory . . . . . . . . . . . . . SERVICED AND DRAINED

Freezeable Liquids REMOVED/DRAINED


80/401

Expected Heavy SnowSnowfall on a parked aircraft can shift the CG aft. A four-inch

snow accumulation adds approximately 2,800 lbs to the aircraftweight. With unfavorable CG conditions (i.e., wing tanks empty

with feeders full), the aircraft can tip onto its tail. Hangar aircraft

if possible; otherwise, avoid parking with an aft fuel CG.

Aircraft . . . . . . . . . . . . . . . . MOORED/CUSHIONED

Use the tiedown ring attached to the nose jacking point.

If practicable, stack tires under the aircraft, forward of the

center engine lower cowling.

Forward Area of Aircraft . . . . . . . . . BALLAST ADDED

Fuel . . . . . . . . . . . . . . . . REFUELED AS REQUIREDRefuel as required to move the CG forward. Approximately

9,000 lbs of fuel results in a more favorable forward CG than

regulation level fuel.



81/401

Deicing Supplemental InformationThis section provides supplementary information on aircraft

deicing, anti-icing/deicing uids, deicing procedures, andaircraft operating procedures. Consult the AFM, Maintenance

Manual Chapter 12 Servicing, and FAA Advisory Circulars

for deicing procedures, holdover times, uid specications,

recommendations, and hazards.

Federal Aviation Regulations (FARs) prohibit takeoff with snow,ice, or frost adhering to the wings and control surfaces of the

aircraft. It is the responsibility of the pilot-in-command to ensure

the aircraft is free of snow, ice, or frost before takeoff.

Failure to adequately deice the aircraft can result in seriously

degraded aircraft performance, loss of lift, and erratic engineand ight instrument indications.

Following extended high-altitude ight, frost can form at ambient

temperatures above freezing on the wings underside in the fuel

tank areas. Refueling the aircraft with warmer fuel usually melts

the frost.


82/401

DeicingWhen necessary, use the following methods to deice the aircraft:

placing the aircraft in a warm hangar until the ice melts

mechanically brushing the snow or ice off with brooms,

brushes, or other means

applying a heated water/glycol solution (one-step procedure)

applying heated water followed by an undiluted glycol-baseduid (two-step procedure).

Two types of anti-icing/deicing uids are in commercial use:

SAE/ISO Types I and II. Type I uids are used generally in North

America. Type II uids, also referred to as AEA Type II, are used

generally in Europe.Type I uids are unthickened glycol-based uids that are usually

diluted with water and applied hot; they provide limited holdover

time.

Type II uids are thickened glycol-based uids that are usually

applied cold on a deiced aircraft; they provide longer holdover

times than Type I uids.



83/401

Many factors inuence snow, ice, and frost accumulation and

the effectiveness of deicing uids. These factors include:

ambient temperature and aircraft surface temperaturerelative humidity, precipitation type, and rate

wind velocity and direction

operation on snow, slush, or wet surfaces

operation near other aircraft, equipment, and buildingspresence of deicing uid and its type, dilution strength, and

application method.

CAUTION

Type II FPD generally should not be applied forward of thewing leading edges. If used for deicing, do not apply forward

of cockpit windows. Ensure that radome and cockpit windows

are clean.

CAUTION

If APU/engines are running when spraying of deicing uids


84/401

One-step deicing involves spraying the aircraft with a heated,

diluted deicing/anti-icing uid to remove ice, snow, or frost.

The uid coating then provides limited protection from furtheraccumulation.

Two-step deicing involves spraying the aircraft with hot water

or a hot water/deicing uid mixture to remove any ice, snow,

or frost accumulation followed immediately by treatment with

antiicing uid (usually Type II FPD uid).Deice the aircraft from top to bottom. Avoid ushing snow, ice, or

frost onto treated areas. Start the deicing process by treating the

horizontal stabilizer followed by the vertical stabilizer. Continue

by treating the fuselage top and sides. Finally, apply deicing uid

to the wings.Deicing uid should not be applied to:

pitot/static tubes, static ports, temperature probes, AOA

vanes, or TAT probe

gaps between control surfaces and airfoil

cockpit windows



85/401

Do not use deicing uid to deice engines. Mechanically remove

snow and ice from the engine inlet. Check the rst stage fan

blades for freedom of movement. If engine does not rotatefreely, deice engine with hot air.

After aircraft deicing and anti-icing, visually inspect the

following areas to ensure that they are free from ice, snow,

and frost accumulations:

wing leading edges, upper and lower surfacesvertical and horizontal stabilizer leading edges, side panels,

and upper and lower surfaces

ailerons, elevator, and rudder

aps, ap tracks, and ap drive mechanisms

ground and ight spoilers

engine inlets and exhausts

cockpit windows

communication and navigation antennas

fuselage


86/401



87/401


88/401

Standard Operating Procedures


89/401

General InformationSimuFlite strongly supports the premise that the disciplined

use of well-developed Standard Operating Procedures (SOP)is central to safe, professional aircraft operations, especially in

multi-crew, complex, or high performance aircraft.

If your ight department has an SOP, we encourage you to use

it during your training. If your ight department does not already

have one, we welcome your use of the SimuFlite SOP.

Corporate pilots carefully developed this SOP. A product of their

experience, it is the way SimuFlite conducts its ight operations.

The procedures described herein are specic to the Falcon 50

and apply to specied phases of ight. The ight crew member

designated for each step accomplishes it as indicated.

DenitionsLH/RH Pilot Station. Designation of seat position for

accomplishing a given task because of proximity to the

respective control/indicator. Regardless of PF or PNF role,the pilot in that seat performs tasks and responds to checklist


90/401

Flow patterns are disciplined procedures; they require pilots who

understand the aircraft systems/controls and who methodically

accomplish the ow pattern.A standardized ow pattern for the cockpit setup before starting

engines appears in the Expanded Normals chapter.

ChecklistsUse a challenge-response method to execute any checklist. After

the PF initiates the checklist, the PNF challenges by reading the

checklist item aloud. The PF is responsible for verifying that the

items designated as PF or his seat position (i.e., LH or RH) are

accomplished and for responding orally to the challenge. Items

designated on the checklist as PNF or by his seat position are the

PNFs responsibility. The PNF conrms the accomplishment ofthe item, then responds orally to his own challenge. In all cases,

the response by either pilot is conrmed by the other and any

disagreement is resolved prior to continuing the checklist.

After the completion of any checklist, the PNF states

___ checklist is complete. This allows the PF to maintainsituational awareness during checklist phases and prompts the



91/401

Challenge/No Response

If the PNF observes and challenges a ight deviation or critical

situation, the PF should respond immediately. If the PF doesnot respond by oral communication or action, the PNF must

issue a second challenge that is loud and clear. If the PF does

not respond after the second challenge, the PNF must ensure

the safety of the aircraft. The PNF must announce that he is

assuming control and then take the necessary actions to returnthe aircraft to a safe operating envelope.

Abnormal/Emergency ProceduresWhen any crewmember recognizes an abnormal or emergency

condition, the PIC designates who controls the aircraft, who

performs the tasks, and any items to be monitored. Following

these designations, the PIC calls for the appropriate checklist.

The crewmember designated on the checklist accomplishes the

checklist items with the appropriate challenge/response.

Control means responsible for flight control of theNOTE:aircraft, whether manual or automatic.


92/401

When a checklist procedure calls for the movement or manipulation

of controls or switches critical to safety of ight (e.g., throttles,

engine re switches, re bottle discharge switches), the pilotperforming the action obtains verication from the other pilot that

he is moving the correct control or switch prior to initiating the

action.

Any checklist action pertaining to a specic control, switch, or

equipment that is duplicated in the cockpit is read to include itsrelative position and the action required (e.g., Left Throttle

OFF; Left Boost Pump NORMAL).

Time Critical SituationsWhen the aircraft, passengers, and/or crew are in jeopardy,

remember three things.

FLY THE AIRCRAFT Maintain aircraft control.

RECOGNIZE CHALLENGE Analyze the situation.

RESPOND Take appropriate action.

Rejected TakeoffsThe rejected takeoff (abort) procedure is a preplanned maneuver;



93/401

Critical Malfunctions in FlightIn ight, the observing crewmember positively announces a

malfunction. As time permits, the other crewmember makesevery effort to conrm/identify the malfunction before initiating

any emergency action.

If the PNF is the rst to observe any indication of a critical failure,

he announces it and simultaneously identies the malfunction

to the PF by pointing to the indicator/annunciator.After verifying the malfunction, the PF announces his decision

and commands accomplishment of any checklist memory items.

The PF monitors the PNF during the accomplishment of those

tasks assigned to him.

Non-Critical Malfunctions in FlightProcedures for recognizing and verifying a non-critical malfunction

or impending malfunction are the same as those used for time

critical situations: use positive oral and graphic communication to

identify and direct the proper response. Time, however, is not as

critical and allows a more deliberate response to the malfunction.

Always use the appropriate checklist to accomplish the corrective


94/401

Monitor NDB audio output anytime the NDB is in use as the

NAVAID. Use the marker beacon audio as backup to visual

annunciation for marker passage conrmation.In tuning the VHF radios for ATC communication, the PNF

places the newly assigned frequency in the head not in use

(i.e., preselected) at the time of receipt. After contact on the new

frequency, the PNF retains the previously assigned frequency

for a reasonable time period.Altitude AssignmentThe PNF sets the assigned altitude in the altitude alerter and

points to the alerter while orally repeating the altitude. The PNF

continues to point to the altitude alerter until the PF conrms the

altitude assignment and alerter setting.

Pre-Departure BriengsThe PIC should conduct a pre-departure brieng prior to each

ight to address potential problems, weather delays, safety

considerations, and operational issues. Pre-departure briengsshould include all crewmembers to enhance team-building and set

the tone or the ight The brieng may be formal or informal but



95/401

Advising of Aircraft CongurationChange

If the PF is about to make an aircraft control or congurationchange, he alerts the PNF to the forthcoming change (e.g.,

gear, speedbrake, and ap selections). If time permits, he also

announces any abrupt ight path changes so there is always

mutual understanding of the intended ight path.

Time permitting, a PA announcement to the passengers precedesmaneuvers involving unusual deck or roll angles.

Transitioning from Instrument toVisual Conditions

If visual meteorological conditions (VMC) are encounteredduring an instrument approach, the PNF normally continues to

make callouts for the instrument approach being conducted.

However, the PF may request a changeover to visual trafc

pattern callouts.


96/401




97/401

Phase of Flight SOP

Holding Short

PF PNF

CALL: Before Takeoff

checklist.

Complete BeforeACTION:

Takeoff checklist.

CALL: Before Takeoff

checklist complete.

Takeoff Brieng

Brief the following:ACTION:

initial heading/

course

initial altitude

airspeed limit(if applicable)

l li it


98/401

Takeoff Roll

PF PNF

Setting Takeoff Power

ACTION: Max Power. CALL: Max power.

Initial Airspeed Indication

Move left hand toACTION:

yoke (unless nose

wheel steering needed

for crosswind).

My yoke.CALL:

CALL: Airspeed alive.

at 80 KIAS

80 kts crosscheck.CALL:

CALL Your yoke.CALL:At V

1



99/401

Climb

PF PNF

At Positive Rate of Climb

Only after PNFs call,

CALL: Gear up.

Positive rate.CALL:

CALL: Gear selected up.

When gear indicates

up, Gear indicates up.

After Gear Retraction

ACTION: Immediately

accomplish attitude

correlation check.

PFs and PNFs ADI

displays agree.

Pitch and bank anglesare acceptable.


100/401



101/401

Climb (cont.)

PF PNF

At 1,000 Ft Below Assigned Altitude

_____ (altitude) forCALL:

_____ (altitude).(e.g., 9,000 for 10,000.)

_____ (altitude) forCALL:

_____ (altitude).

(e.g., 9,000 for 10,000.)


102/401



103/401

Descent

PF PNF

Descent checklist.CALL:

Complete DescentACTION:

checklist.

CALL: Descent checklistcomplete.

At 1,000 Ft Above Assigned Altitude

CALL: (altitude) for

(altitude).

(e.g., 10,000 for 9,000.)

CALL: (altitude) for

(altitude).

(e.g., 10,000 for 9,000.)


104/401

Descent (continued)

PF PNF

At Appropriate Workload Time

REVIEW REVIEW

Review the following:

approach to be executed

eld elevation

appropriate minimum sector altitude(s)

inbound leg to FAF, procedure turn direction and altitude

nal approach course heading and intercept altitude

timing required

DA/MDA

MAP (non-precision)

VDP

special procedures (DME step-down, arc, etc.)

type of approach lights in use (and radio

keying procedures, if required)

missed approach procedures


105/401


106/401

Precision Approach (cont.)

PF PNF

At One Dot From Glideslope Intercept

CALL: Gear down.

Landing checklist.

CALL: One dot to go.

CALL: Gear selected down.

When gear indicates

down,

Gear indicates down.

ACTION: Complete Landing

checklist except for

full flaps and autopilot/

yaw damper

When Annunciator Indicates Glideslope Capture

CALL: Glideslope captured. Glideslope captured.CALL:



107/401


PF PNF

At FAF

Outer marker.CALL:

or Final fix.ACTION: Start timing.

Visually crosscheck

that both altimeters

agree with crossing

altitude.

Set missed ap-

proach altitude inaltitude alerter.

Check PF and PNF

instruments.

Call FAF inbound .

Outer marker. orCALL: Final x.

Altitude checks.


108/401


P i i A h ( t )


109/401


PF PNF

At Point Where PNF Sights Runway or Visual References

Going visual. Land.CALL:

or Missed approach.

Runway (or visualCALL:

reference) _____

oclock.

ACTION: As PF goes visual,

PNF transitions to

instruments.

At DA(H)

Announce intentions.ACTION:

Going visual. Land.CALL:

or Missed approach.

Minimums. RunwayCALL:

(or visual reference)

_____ oclock.

As PF goes visual,ACTION:

PNF transitions to

P i i Mi d A h


110/401

Precision Missed Approach

PF PNF

At DA(H)

Missed approach.CALL:

Apply power rmlyACTION:

and positively. Activatego-around mode and

initially rotate the nose

to the ight director

go-around attitude.

Flaps 20.CALL:

Minimums. MissedCALL:

approach.

Assist PF in settingACTION:

power for go-around.

Flaps selected 20.CALL:When aps indicate 20,

Flaps indicate 20.

At Positive Rate of Climb

Gear up.CALL:

Positive rate.CALL:

Gear selected up.CALL:


111/401

N P i i A h


112/401

Non-Precision Approach

PF PNF

Prior to Initial Approach Fix

Approach checklist.CALL:

Slats only.CALL:

Flaps 20.CALL:

Complete ApproachACTION:

checklist except for

slats and flaps.Slats selected.CALL:

When slat green

light illuminates,

Slats indicated.

Flaps selected 20.CALL:

When aps indicate 20,Flaps indicate 20.

Approach checklistCALL:

complete.

At Initial Convergence of Course Deviation Bar

Localizer/courseCALL: Localizer/courseCALL:


113/401

N P i i A h ( t )


114/401

Non-Precision Approach (cont.)

PF PNF

At FAF

Outer marker.CALL:

or Final x.

Outer marker orCALL:

Final x.

Start timing.ACTION:

Visually crosscheck

that both altimeters

agree.

Set MDA (or nearest

100 ft above) in altitude

alerter.

Check PF and PNF

instruments.

Call FAF inbound.

Altimeters check.CALL:

At 1,000 Ft Above MDA


Non Precision Approach (cont )


115/401

Non-Precision Approach (cont.)

PF PNF

At 500 Ft Above MDA

CALL: Check.

500 ft to minimums.CALL:

NOTE:An approach window has the following parameters:

within one dot CDI deection or 5 bearing

IVSI less than 1,000 fpm

IAS within VAP

10 kts target speed 10 kts

no flight instrument flags with the landing

runway or visual references not in sight

landing configuration, except for full flaps

When within 500 ft above touchdown, the aircraft must be within the

approach window. If the aircraft is not within this window, a missed

approach must be executed.

At 200 ft above MDA


116/401


Non Precision Missed Approach


117/401

Non-Precision Missed Approach

PF PNF

At MAP

CALL: Missed approach.ACTION: Apply power firmly

and positively. Activate

go-around mode and

initially rotate the nose

to the flight director

go-around attitude.CALL: Flaps 20.

CALL: Missed approach point.

Missed approach.

Assist PF in settingACTION:

power for go-around.


When aps indicate 20,

Flaps indicate 20.

At Positive Rate of ClimbPositive rate.CALL:

Non Precision Missed Approach (cont )


118/401

Non-Precision Missed Approach (cont.)

PF PNF

At VREF

+ 5 (Minimum) and 400 Ft Above Airport Surface (Minimum)

CALL: Slats only.

CALL: Slats selected.

When slats indicateslats only,Slats indicate.

At VREF

+ 20 KIAS (Minimum)

Clean wing.CALL:

Wing selected clean.CALL:When slat red lightgoes out, Wingindicates clean.

At 1,500 Ft (Minimum) Above Airport Surface and Workload


Non Precision Approach Deviations


119/401

Non-Precision Approach Deviations

PF PNF

One Dot Localizer/VOR

CALL: Correcting.

CALL: One dot (right, left)and (increasing,holding, decreasing).

5 At or Beyond Midpoint for NDB Approach

CALL: Correcting.

CALL: (degrees offcourse) (right, left)and (increasing,holding, decreasing).

VAP

10 kts

CALL: Speed (plus orminus) and

Visual Trafc Patterns


120/401

Visual Trafc Patterns

PF PNF

Before Pattern Entry/Downwind (1500 Ft Above Airport Surface)

CALL: Approach checklist.

Slats only.CALL:

Flaps 20.CALL:

ACTION: Complete approach

checklist.CALL: Slats selected.

When slat green

light illuminates,

Slats indicated.


When aps indicate 20,

Flaps indicate 20.

Approach checklistCALL:

complete.

Downwind


Visual Trafc Patterns (cont )


121/401

Visual Trafc Patterns (cont.)

PF PNF

At 1000 Ft Above Airport Surface

CALL: Check.

CALL: 1,000 AGL.


CALL: Check.

CALL: 500 AGL.


CALL: Check.

CALL: 200 AGL.

Landing


122/401

Landing

PF PNF

At Point on Approach When PF Sights Runway or Visual Reference

(On Final)

CALL: Going visual. Land.

Flaps FULL (or 48).

PACTION: ush autopilotdisconnect switch.

Autopilot/yawCALL:

damper off.

CALL: Flaps selected FULL (or

48).

When flaps indicate

48, Flaps indicate

FULL (or 48).

ACTION: Continue with:

speed check

vertical speed check

callouts

gear down verification

flap verification.


Landing (cont )


123/401

Landing (cont.)

PF PNF

At Thrust Reverser Deploy

Reverser deployed.CALL:

At 80 KIAS

CALL: 80 kts.


124/401

Maneuvers


125/401

Maneuvers

Table of ContentsNormal Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2D-3Rejected Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2D-5

Engine Failure at V1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2D-7

Steep Turns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2D-9Approach to Stalls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2D-11

Recovery from Unusual Attitudes . . . . . . . . . . . . . . . . . .2D-13

Precision Approach and Landing . . . . . . . . . . . . . . . . . . .2D-15

Non Precision Approach and Landing . . . . . . . . . . . . . . .2D-17

Non-Precision Approach and Landing

(Constant Rate Descent) . . . . . . . . . . . . . . . . . . . . . . . . .2D-19

Visual Approach / BalkedLanding . . . . . . . . . . . . . . . . . .2D-21

Circling Approach and Landing . . . . . . . . . . . . . . . . . . . .2D-23

Falcon 50 Checklist

Documents

Transcript of Falcon 50 Checklist