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CAPF 70-5 Training

Module 6:

Aircraft Systems

Capt. Eric Choate, CAP

1st Lt. Marty Nicholes, CAP

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Why learn about aircraft systems?• To become a safer pilot!

• Troubleshoot issues on the ground and in the air

• Know the difference between an airworthy issue and

a “cosmetic” issue

• Know what systems are required for what operations

• Become aware of sights, sounds, and smells that

may indicate an issue

Introduction

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• Airframe

• Flight Controls

• Instrument Panel

• Wing Flaps

• Engine (High Performance)

• Propeller

• Fuel System

• Brake System

• Cabin Heating, Ventilating & Defrosting

• Pitot-Static System

• Vacuum System

• Stall Warning System

• Electrical System

• Avionics

Outline (Section 7 of Cessna 182T Nav III POH)

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“…an all metal, four-place, high wing, single engine, airplane

equipped with tricycle landing gear…”

• Inspect the airframe for corrosion

• Dented, deformed, cracked skin

• Missing screws, rivets

• Indications of hard landings

– Wrinkles in skin near tail hook

– Wrinkled firewall

Airframe

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Flight Controls

System of cables and pulleys connected to the yoke, rudder

peddles, and trim wheels that move the control surfaces.

• Ensure all control surfaces operate smoothly and correctly

• Ensure rudder and elevator do not interfere with each other

• Use a helper to perform a positive control check

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Instrument Panel

Primary Flight Display (PFD), Audio Panel, Multifunction Display

(MFD), Standby Instruments, Switches, Breakers, Engine Controls

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Wing Flaps

Electric flaps controlled by flap switch and protected by a 10-amp

circuit breaker. A single flap motor in the right wing activates both flaps

via cable.

• Operating Range:

• 10 degrees below 140 KIAS

• 10-20 degrees below 120 KIAS

• 20 degrees to full below 100 KIAS

• Visually confirm flaps deployed

• Prepare for no-flap landing with loss

of electrical system

• Check flap circuit breaker

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Engine (High Performance)

“…a horizontally opposed, six cylinder, overhead valve, air cooled,

fuel injected engine with a wet sump lubrication system…Lycoming

Model IO-540-AB1A5 rated at 230 horsepower at 2400 RPM.”

• Cooling baffle condition

• Cowl flaps open for taxi

takeoff, and climb

• Monitor CHTs

• Max 500 degrees

• CAP Recommends <400

• Operation not allowed

CHT #3 is inoperative

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Engine (Cont.)

The four-stroke combustion cycle consists of the intake, compression,

power, and exhaust strokes.

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Engine - Instruments

“The G1000 Engine Indicating System (EIS) provides graphical

indicators and numeric values for engine, fuel, and electrical

system…”

• Manifold Pressure

• Tachometer

• Fuel Flow

• Oil Pressure

• Oil Temperature

• Cylinder Head Temperature (CHT)

• Exhaust Gas Temperature (EGT)

The GEA-71 Engine and Airframe Unit receives signals from

engine/system sensors and provides the data to the EIS.

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Engine – Lubrication System

“The engine utilizes a full pressure, wet sump type lubrication

system…”

• Oil type: Phillips XC 20W-50

• Capacity: 9 quarts

• Minimum: 4 quarts

• To minimize loss of oil through the breather,

fill to 8 quarts

• Fill to 9 quarts for extended flights

• Inspect oil for color and smell

• Look for excessive oil leaks

• Be concerned if an engine uses more than 1 quart per hour

• Monitor oil pressure indication (especially on startup)

• Normal oil pressure 50-90 PSI

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Engine – Ignition System

“Engine ignition is provided by two engine-driven magnetos, and two

spark plugs in each cylinder. The right magneto fires the lower right

and upper left spark plugs, and the left magneto fires the lower left

and upper right spark plugs”

• Check RPM drop for L and R

mags during runup

(175 Max, 50 between mags)

• Excessive RPM drop can

indicate fouled sparks plugs

or a faulty Mag

• Properly lean during taxi to

avoid fouling spark plugs

• Test OFF position momentarily

before shutdown to ensure proper mag grounding

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Engine – Air Induction System

“The engine air induction system receives ram air through an intake

on the lower front portion of the engine cowling.”

• Air Filter

• Spring-loaded alternate air door (in the case of a blocked air filter)

• Ensure Air filter is clean and clear of obstruction

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Engine – Fuel Injection System

“The system is comprised of an engine-driven fuel pump, fuel/air

control unit, fuel manifold, fuel flow indicator, and air-bleed type

injector nozzles.”

• Fuel injected directly into

cylinders

• System under pressure

• Use Auxiliary fuel pump if

you suspect engine-driven

fuel pump failure or

you experience surging

• Hot starts can be difficult

• Vapor lock can be an issue

on hot days

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Propeller

“The airplane has an all-metal, three-bladed, constant speed,

governor regulated propeller.”

• Also called “Variable Pitch”

• Controlled with engine oil,

a piston, and a spring

• Look for leaks at base of blades

• Check propeller blades for nicks

or cracks

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Fuel System

“The airplane fuel system consists of two vented integral fuel tanks

(one in each wing)…and…”

• 13 Fuel Drains

• 2 Fuel vents

• Selector valve

• Engine-Driven fuel pump

• Electric Auxiliary fuel pump

• Fuel strainer

• Fuel/Air Control unit

• Fuel distribution unit

• 2 Fuel quantity sensors

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Fuel System (cont.)

Things you should know:

• Fuel Capacity: 92 Gallons Total, 87 Usable

• “Tabs”: 69 Gallons Total, 64 Usable

• CAP typically filled to 50 Gallons

• Fuel Type: 100LL (Blue)/100 (Green)

• Fuel quantity indications can not be relied upon during skids, slips

or unusual attitudes

• A fuel indication of “0” – 2.5 gallons of unusable fuel remain

• Do not take off with fuel indications in the yellow

• Reset/confirm your fuel totalizer before each flight

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Brake System

“…a single-disc, hydraulically-actuated brake on each main landing

gear wheel”

• Hydraulic lines connected to master cylinders behind rudder pedals

• Check for brake pad wear

• Rotor grooves, cracks, etc…

• Hydraulic leaks (typically red fluid)

• Minimize braking usage during taxi operations and landings

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Cabin Heating, Ventilating and Defrosting

• Cabin Heat, pull knob for on

• Cabin Air, pull knob for on

• Cabin Defrost, turning knob controls volume of air to the windshield

• WARNING: Carbon Monoxide potential! Cabin heat comes from

air directed through a shroud around the exhaust. A leaking

exhaust can bring CO into the cockpit!

• ENGINE FIRE: Cabin Heat and Air – OFF (except overhead vents)

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Pitot-Static System

• Pitot tube on left wing

• Two static ports (one on each side of the forward fuselage)

• Connected with tubes to the ADC (Air Data Computer)

• Also connected to the standby (analog) instruments

• Ensure pitot tube and static ports are clear before flight

• Ensure pitot heat and alternate static source work before flight

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Vacuum System and Instruments

• Engine-Driven Vacuum pump

• Vacuum regulator

• Standby Attitude Indicator

• Vacuum system air filter

• Vacuum transducer

• Check vacuum pressure indication

• Ensure standby attitude indicator is

indicating properly during taxi

• Low vacuum warning during low RPM

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Electrical System

1st Lt. Marty Nicholes, CAP

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Electrical System

“As easy as 1, 2, 6, 28…”

1

• 1 alternator

2

• 2 - 24 volt Batteries (Main and Standby)

6

• 6 electrical buses (also an additional CAP mission bus)

28

• 28 Volt system

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Electrical System

“The airplane is equipped with a

28-volt direct current (DC) electrical

system…”

• Belt driven alternator (60 or 95

amps)

• 24-volt main battery (8 or 10 AMP

HOUR)

• 1 power distribution module

• Standby battery (6.2 AMP HOUR)

Figure 7-7 from POH

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Electrical System (cont.)

A boatload of buses and electronics…

Bus assignments

• Electrical Bus 1 (master switch)– Aux fuel pump, flaps, lights

– Avionics bus 1

• Electrical Bus 2 (master switch)– Pitot/Stall heaters, lights

– Avionics bus 2

• Essential bus (STBY BATT switch)– PFD, ADC, AHRS, Nav1, Com1, GEA

– Standby battery (backup power)

• Avionics Bus 1 (dedicated switch)– PFD, Com1, Nav1, ADC, AHRS, GEA

• Avionics Bus 2 (dedicated switch)– MFD, Com2, Nav2, Transponder, Audio

Panel, Auto pilot,

• Crossfeed Bus

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Electrical System (cont.)

CAP Specific electrical items

• Mission bus (mission master switch)

– Becker unit

– CAP radio

– AUX power

– Circuit breakers

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Electrical System

ALTERNATOR CHECK (alternator

and alternator control unit)

Prior to night/instrument flight

• 1800 RPM

– Turn on electrical equipment

needed

– Ammeters show 0 or positive

current (amps)

– Voltmeters show 27 – 29 Volts

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Electrical System Failures

Watch for annunciators and

respond to all alerts!

Annunciators

• LOW VOLTS

– Volts < 24-volts

– Try cycling alternator1. MASTER Switch (ALT Only) - OFF

2. ALT FIELD Circuit Breaker - CHECK IN

3. MASTER Switch (ALT Only) - ON

– If still LOW VOLTS then shed

load and land!

– Can also use standby battery

to extend main battery life.

• STBY BAT

– Standby Batt drawing > 0.5A

– Standby battery should not

discharge in normal flight!

– Is alternator working?

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Electrical System Failures (cont.)

Monitor power supply system

M BATT AMPS and M BUS VOLTS

• Excess charging current– after 30 minutes of cruising flight, M

BATT AMPS should indicate less

than 5 amps of charging (+) current.

• Excessive voltage (>31.75V)

– HIGH VOLTS warning

– Alternator should have

disconnected

– Set MASTER switch ALT to

OFF

– Shed electrical load and land• Use main battery ammeter (M BUS AMPS)

to check discharge rate

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Electrical System Failure

If your alternator has failed and reset did not work,

think:

• What is my flight condition (VFR, IMC)

– VFR – can shutdown more equipment

– IMC – need to be more cautious about what equipment

to lose, if you hit VFR, try to stay there.

• How much time do you have?

– Battery condition, electrical load

• Nearest airport?

– G1000 nearest feature is your friend. Remember to use

direct to.

– Can airport fix the issue?

• Landing clearance?

– Light gun, or your cell phone (1-800-WX-BRIEF)

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Avionics

G1000 Main LRU (units)

• AHRS - Attitude/Heading Ref

• ADC - Air data computer

• GEA - Engine airframe

• GMU - Magnetometer

• GTX - Transponder

• GIA - Integrated Avionics Unit

• GMA - Audio panel

• GDL – data link

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Avionics failures

• PFD failure

– Reversionary mode

• AHRS failure

– Loss of attitude indicator

and eHSI

• Magnetometer failure

– Loss of heading

information

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Avionics failures (cont.)

• ADC Failure

– Loss of airspeed

– Altitude

– Vertical speed

– OAT

• Integrated Avionics Unit failure

– Loss of com1 and/or com2

– Loss of nav1 and/or nav2

– Loss of transponder

• Engine & Airframe Computer

failure

– Loss of engine instruments

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References

• G1000 Cockpit Reference Guide

• Cessna 182T Nav III POH

• https://www.boldmethod.com/learn-to-fly/aircraft-systems/what-

happens-when-your-alternator-fails-during-flight/Integrated

Avionics Unit failure

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• Read Section 3 of C182T POH

• Read CAPS 72-3

• Read CAPS 73-1

• Print POH pages 3-17 to 3-24 and p. 3-34

• Print CAP C182T Emergency Procedures Checklist

• Print CAP C182T Normal Procedures Checklist

Homework Assignment for Module 7