Preflight Exterior

7/27/2019 Preflight Exterior

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EXTERIOR PREFLIGHT



PREFLIGHT INSPECTION

Battery...............................................................................................CONNECTED

Engine Covers (4).................................................................................. REMOVED

Pitot Covers (3)...................................................................................... REMOVED

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Power Brake Accumulator Charge................................................. PER PLACARD



Placard Location

TEMP ˚F -65 10 50 70 95 130PRESS PSI 500 600 650 675 700 750

Refer to Normal Procedures, Cold Weather Operations, if the airplane has been exposed to ambient temperatures below –10˚C(+14̊ F) for a prolonged period.

If the brake system has been pressurized, the brakes can be bled down to precharge level by pressing the silver button circledabove to release fluid pressure.

EXTERIOR INSPECTION

During inspection, make a general check for security, condition and cleanliness of the airplane andcomponents. Check particularly for damage; fuel, oil, and hydraulic fluid leakage; security of accesspanels; and removal of keys from locks.

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Hot Items/Lights .............................................................................ON and CHECK

a. Left, Right and Standby Static Ports – CLEAR and WARMFor RSVM, the area around ports must be clean and free from debris. Paint must be smooth.

b. Left, Right and Standby Pitot Tubes – CLEAR and HOTc. True Airspeed Temperature Probe – CLEARd. Landing Lights – ALL ON (if not observed from cockpit)e. Recognition Lights – ALL ON (if not observed from cockpit)f. Angle-of-attack Vane – Free and HOTg. Ground Recognition Light – ON and FLASHING (if not observed from cockpit)h. Right Wing Inspection, Navigation, and Anti-collision Lights – ON (if not observed from cockpit)i. Tail Navigation Light – ON

j. Left Wing Inspection, Navigation, and Anti-collision Lights – ON (if not observed from cockpit)k. Hot Items/Lights and Battery Switches - OFF

NOTE• Expedite all checks with electrical power on and ensure that the air conditioner switch is OFF, if external power is not used

• If the Ground Recognition lights (strobes) can be verified to operate from the flight deck extinguish them before the walk

around to reduce ramp distractions.• Landing and navigation lights may be omitted if night flight is not anticipated.

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a. Brake Fluid Reservoir Sight Gauges – FLUID VISIBLE.

Brake &Pneumaticpressure

gauge

Left Nose.....................................................................................................CHECK

Fluid MAY be visible in the top sight when the system is not pressurized, but the lower window must ALWAYS indicate full.



b. Brake and Gear Pneumatic Pressure Gauge – PER PLACARD.

TEMP ˚F -40 0 70 100 130

PRESS PSI 1500 1650 1950 2000 2050

Check condition of “break away wire.” Confirms the blowdown bottle has not been used.

Viewed from above

Brake reservoir Antiskid Fault DisplayUnit (BITE indicator)

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Wire runs from here to here



c. Antiskid Fault Display Unit (BITE indicator) – CHECK and RESET if required.

The bottom picture simulates a “tripped” BITE indicator.To reset turn clockwise until the white disappears and release.

Verify Amber ANTISKID INOP annunciator extinguished during BEFORE STARTING ENGINES checklist.

d. Accessory Door – SECURE and LOCKED.

Four Locks for thiscompartment.

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e. Overboard Vent Lines – CLEAR.

Blowdown air outlet

f. Nose Gear, Doors, Wheel and Tire – CONDITION.

Maximum deflection when towing if torque link is in place is 60̊ .

g. Nose Gear Torque Link – CHECK CONDITION.

Also, notebonding strap

connections.

Right Nose and Fuselage Right Side.......................................................... CHECK

a. Accessory Door – SECURE and LOCKED.

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b. Oxygen Blowout Disc – GREEN.

Four Locks for thiscompartment.

Blowout Disc

c. Single Point Pressure Refuel Door – LATCHED AND LOCKED.

d. Top and Bottom Antennas – CONDITION and SECURE.

HF

TCAS IITransponder

ADF I & IIComm 1

ELT

Transponder 2

COM 2

DME 1DME 2Marker Beacon

Radar Altimeter

Transponder 1 Antenna located behind pitot tube on port side. Glideslope receiver in Nose cone.

e. Dorsal Fin Air Inlet – CLEAR.

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Also circled, directly in front of inlet is scoop for the APU Generator cooling.

Right Wing...................................................................................................CHECK

a. T1 and T0 Sensors (in right engine inlet) – CONDITION.

T1

T0Tfc

RAT is taken from the right engine’s T0 probe.Bullet nose is constantly deiced by bleed air outlet (circled above)

b. Engine Fan Duct and Fan – CONDITION.

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c. Wing Inspection Light - CONDITION.

d. Emergency Exit – CHECK CONDITION.

e. Anti-Ice Bleed Air Cooling Air Inlet – CLEAR.

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f. Fuel Quick Drains (5) – DRAIN and CHECK for contamination.

Pictured above are the left side fuel drains (located along aircraft centerline).Pictured below is the right side fuel drain (located outside wheel well).

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g. Main Gear Door, Wheel, Tire and Brake – CONDITION and SECURE.

Squat Switch

Uplock

Anti-skid brake

sensor lead.

Hydraulic brake line

Pneumatic brake line

Pressurized to 218 +2/-5 with weight on wheels at 70˚F.

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Bonding Strap

Brake Wear Indicators

Pneumaticbrake line

Hydraulicbrake line

Brake wear indicators can be operated down to where they are flush with the brake assembly.

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h. Vortex Generators (26) – CHECK (no more than 3 may be missing on entire airplane).

i. Boundary Layer Energizers (11) CHECK (none may be missing).

j. Heated Leading Edge – CONDITION and VENT CLEAR.

k. Fuel Filler Cap – SECURE.

Cover secured to capwith screws. Does

not come off.

Key in “locked”position

Latch seated,lid sealed andsecure.

l. Fuel Tank Vent – CLEAR.

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o. Aileron, Speed Brakes and Flaps – CONDITION and SECURE.

Aileron Hinges

Upper Speed Brake

Lower Speed Brake

Flap Rollers

Right Nacelle/Pylon.....................................................................................CHECK

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c. Generator and Alternator Cooling Air Exhaust – CLEAR.

Alternator

Generator

d. Engine Fluid Drain Mast – CLEAR.

e. Engine Exhaust and Bypass Ducts – CONDITION and CLEAR.

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f. Thrust Reverser Buckets – CONDITION and STOWED.

g. Pylon Heat Exchanger Door – CLOSED and AREA CLEAR.

Do not press

on this door.

outlet

Vent door located onbottom of the

engine pylon.

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Tailcone Compartment

a. Hydraulic Fluid Quantity – CHECK.

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b. Aft Junction Box Circuit Breakers – IN.

c. External Power Receptacle Circuit Breakers – IN.

GPU Breaker

d. ECS Indicators – CHECK and RESET if required. Verify engine(s) operate in AUTO MODEafter engine start.

Tripped ECS Fault Indication

e. Engine Chip Detector (if installed) – TEST.

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This boot bears the brunt of the APU exhaust, so it tends to show wear before the left side.

Check ConnectionsNav 2 Antenna

i. Right Elevator and Trim Tab – CONDITION. j. Rudder and Trim Tab – CONDITION.

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Baggage Compartment...............................................................................CHECK

a. Baggage Compartment – SECURE.

b. Baggage Compartment Light – OFF.

c. Baggage Compartment Access Door

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Cabin Entry..................................................................................................CHECK

a. Dorsal Fin Air Inlet – CLEAR.

b. Secondary Cabin Door Seal – CHECK for RIPS, TEARS and FOLDING.

Acoustic Seal

Primary seal

Secondaryseal

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Preflight Exterior