Aircraft Systems

CT-142 Maximum Operating Altitude

25 000 ft ASL

Ct-142 Runway Limitations

Max Tailwind - 10kts
Max Crosswind - 36 kts

Air Recirculation

Improves cabin airflow and reduces conditioned bleed air demand

Pressurization System

Uses bleed air from the air conditioning system to provide cabin pressurization

Pressurization System Modes

Automatic and manual

APU Functions

Provides air conditioning and basic electrical power on the ground

APU Operation in Flight

Cannot be operated in flight

APU Fuel Source

Left fuel tank collector bay

APU Fire Protection

Has its own fire detection and extinguishing system

Microphone Selection

Boom or Mask

VHF Communication Range

118.0 to 151.975 MHz

UHF Communication Range

225.0 to 399.975 MHz

DC Power Sources

2 TRUs, 2 batteries, 2 starter generators, and external ground power

AC Power Sources

2 AC generators, 9 inverters, APU, and external ground power

Fuel System Tanks

Four wing tanks consisting of 2 main and 2 auxiliary tanks

Power Transfer Unit (PTU)

Hydraulic component that transfers power between hydraulic systems

De Icing System

Removes accumulated ice

Anti Icing System

Prevents ice accumulation

Alternate Extension System

Backup landing gear extension method

Bleed Air Uses

Air conditioning, pressurization, and pneumatic de icing

Cockpit O2 System

Provides oxygen for flight crew

Portable Full Face O2 System

Portable emergency oxygen system

NTS Console O2 System

Oxygen system for navigation training stations

VREF

Approach speed at 50 feet above the runway in landing configuration

V1

Takeoff decision speed at which the pilot may stop or continue the takeoff following an engine failure or other issue

Kinds of Operations

Day and night VFR, IFR, and icing

Maximum Rough Airspeed

180 KIAS in severe turbulence

Minimum Flight Crew

One pilot and one copilot

Maximum Operating Altitude

25,000 ft ASL

Maximum Tailwind Component

10 kt

Maximum Crosswind Component

36 kt

Minimum Runway Width

98 ft

Maximum Cabin Altitude

8,000 ft

Ground Evacuation

Emergency procedure for rapid aircraft evacuation on the ground

Pressurization Emergencies

Procedures for loss or malfunction of aircraft pressurization

Engine Airstart

Procedure to restart an engine in flight

Fuel Transfer Failure

Abnormal procedure for fuel system malfunction

Maximum Aircraft Weights

Ramp, takeoff, and landing weight limitations

Stalling Speeds

Minimum speeds before an aerodynamic stall occurs

Takeoff Climb Data

Performance data used for takeoff and climb calculations

Navigation Training Crew Fixed Oxygen System

Supplemental fixed oxygen system for NTS crew

Operation with Inoperative Autofeather System

Supplementary procedures when autofeather is unavailabl

Three Basic Aircraft Components

Fuselage, wings, and empennage

Fuselage

The main body structure to which all other aircraft components are attached

Wings

Fixed surfaces that produce lift under given conditions of flight

Empennage

The tail section, including the tail cone, horizontal stabilizer, vertical stabilizer, elevators, and rudder

Three Aircraft Motions

Roll, pitch, and yaw

Three Main Control Surfaces

Ailerons, elevators, and rudder

Ailerons

Wing control surfaces used in pairs to control roll

Spoilers

Plates on the upper wing surface that extend into the airflow, spoil airflow, and reduce lift over part of the wing

Ailerons and Spoilers

Control roll about the longitudinal axis

Roll

Aircraft movement about the longitudinal axis

Elevators

Control surfaces on the horizontal stabilizer that control pitch

Pitch

Aircraft movement about the lateral axis

Rudder

Control surface on the vertical stabilizer that controls yaw

Yaw

Aircraft movement about the vertical axis

Longitudinal Axis

The axis about which the aircraft rolls

Lateral Axis

The axis about which the aircraft pitches

Vertical Axis

The axis about which the aircraft yaws

Control Surfaces

Center of Gravity

The point where the longitudinal, lateral, and vertical axes intersect

Control Forces and Center of Gravity

All control forces are applied around the center of gravity

Aircraft Balance Point

At the center of gravity, the aircraft is in perfect balance

Force

Strength or energy exerted or brought to bear : cause of motion or change : active power

•At 402 Sqn we take this to mean:

•Energy to produce or defy motion

•May be either positive or negative

Four Forces Acting on an Aircraft

Lift, thrust, weight, and drag

Straight and Level Unaccelerated Flight

Occurs when lift, weight, thrust, and drag are in equilibrium

Newton's First Law

Law of Inertia: A body at rest remains at rest and a body in motion remains in motion unless acted upon by an external force

Newton's Second Law

Law of Acceleration: Acceleration is directly proportional to applied force and inversely proportional to mass. F= ma

Newton's Third Law

Law of Action and Reaction: For every action, there is an equal and opposite reaction

Two Pressures Within a Fluid

Static pressure and dynamic pressure

Static Pressure

Pressure exerted on an object by molecular activity within a fluid

P_static = Force / Area


EXAMPLE : at sea level, standard pressure is 14.7lbs/sq. in (the weight of a column of air above a certain area)

Static Pressure Energy Type

Potential energy

Static Pressure Formula

Static pressure equals force divided by area

Standard Sea Level Pressure

14.7 pounds per square inch


= 101.3 kPa

= 101,325 Pa

= 1013.25 hPa

= 1013.25 mb

= 1 atm

= 29.92 inHg

= 760 mmHg

Dynamic Pressure

A body immersed in a moving liquid will absorb the kinetic energy of that fluid (aircraft in the airstream)

P_dynamic = ½ (rho) v²

(rho) = air density
v = velocity of the fluid

Dynamic Pressure Energy Type

Kinetic energy

Dynamic Pressure Formula

P_dynamic = ½ (rho) v²

Velocity Used for Aircraft Dynamic Pressure

True airspeed

Total Pressure

The sum of static pressure and dynamic pressure

P_total = P_static + P_dynamic
P_total = (Force/Area) + ½ (rho) v²

Air Density (rho) relationship to Pressure, Temperature and Humidity

Air density varies directly with air pressure and inversely with temperature and humidity.

Bernoulli's Principle

An increase in dynamic pressure results in a corresponding decrease in static pressure

Describe what is happening.

Since there is an increase in velocity at point 2 there must be a corresponding increase in dynamic pressure and therefore a decrease in static pressure to maintain a constant pressure.

Airflow Over an Airfoil

The airfoil restricts airflow and increases velocity over its upper surface

Static Pressure Above an Airfoil

Static pressure is lower over the upper surface

Static Pressure Below an Airfoil

Static pressure on the lower surface remains unchanged

Lift Creation

The pressure imbalance between the upper and lower surfaces of an airfoil creates lift

Two Basic Ways to Increase Lift

Increase airspeed or increase airfoil camber:

To increase the camber, we use high lift devices – flaps (leading edge, trailing edge, fowler flaps, etc.)

How do Flaps affect Lift?

They are High lift devices used to increase the camber of an airfoil and increase lift.

Thrust

Fuel is fed into some kind of “engine” where, in burning, its’ chemical energy is changed into thermal energy which is converted into the mechanical work done in propelling the aircraft against the drag.

(used to climb/accelerate)

Thrust in Steady Level Flight

Thrust equals drag

What are the four main types of aircraft engines?

• Ram-Jet

• Turbo-Jet /

• Turbo-Fan

• Engine/Propeller Combination

  • (Reciprocating (Piston) Engine;

  • Turbine Engine;

  • Fixed Pitch Propeller;

  • Variable Pitch Propeller)

Engine and Propeller Propulsion

A propulsion system that gives a small acceleration to a large amount of air.

Driven by a reciprocating or turbine engine

Thrust and Momentum Principle

Thrust equals the rate at which momentum is given to the air

Turboprop Momentum

A turboprop gives a large mass of air a small acceleration

Turbojet or Turbofan Momentum

A turbojet or turbofan gives a small mass of air a large acceleration

Propulsion Efficiency at Lower Speeds

A propeller is more efficient than a jet at lower speeds

Propeller Function

Converts engine torque into a forward push or pull called thrust

Propeller Operation

Moves forward in a corkscrew motion and pushes air backward to produce forward thrust

Propeller Blade Cross Section

Similar to an airfoil or wing