Helicopter Systems

Private Pilot Course

Lesson 1 Helicopter Systems

Lesson 1: Helicopter Systems Objectives

After completion of this lesson you will be able to describe these specifics of the R-22: Helicopter Components Flight Controls Electrical System Fuel and Fuel System Oil and Oil System Instruments

1 Lesson 1: Helicopter Systems Recommended Study Material

Rotorcraft Flying Handbook Chapters 1-4

Robinson R-R-2222 POH Sections 1,2,7

ASA Private Pilot Test Prep Chapter 11--22

Lesson 1: Helicopter Systems Table of Contents

Helicopter Components Terminology Main rotor Tail rotor Engine Drive system Landing Gear Flight Controls Electrical Systems Fuel and Fuel System Oil and Oil System Instruments

2 Helicopter Components Terminology

An airfoil is any surface, such as an airplane wing or a helicopter rotor blade, which provides aerodynamic force when it interacts with a moving stream of air.

Rotorcraft Flying Handbook: Ch. 2

Helicopter Components Terminology

The leading edge is the firs t part of th e airfoil to meet the oncoming air

Rotorcraft Flying Handbook: Ch. 2

3 Helicopter Components Terminology

The trailing edge is the rear -most edge of the airfoil.

Rotorcraft Flying Handbook: Ch. 2

Helicopter Components Terminology The chord line is the imaginary straight line drawn from the leading edge to the trailing edge

Rotorcraft Flying Handbook: Ch. 2

4 Helicopter Components Terminology

Camber is the curvatfthture of the airfoil’s upper and lower surfaces

Rotorcraft Flying Handbook: Ch. 2

Helicopter Components Terminology

There are two types of airfoils: Symmetrical have an equal upper and lower camber Symmetrical AAtilsymmetrical have an unequal upper and lower Asymmetrical camber.

Rotorcraft Flying Handbook: Ch. 2

5 Helicopter Components Terminology

There are three types of Rotor Systems: SemiSemi--RiRigid: R-R-2222 Rigid Fully Articulated

Each system is configured to allow the rotor bla des to move in spec ific ways: Flapping Feathering Lead / Lag Rotorcraft Flying Handbook: Ch. 5

Helicopter Components Terminology A semi-semi-rigidrigid rotor system is able to: FFtheather FlapFlap

Movement of blade along span wise axis

Feather Bearings Occurs through feather bearing

Rotorcraft Flying Handbook: Ch. 5

6 Helicopter Components Terminology SemiSemi--RigidRigid is able to: Feather Flap Teetering Hinge Hub is attached to the rotor mast by a teetering hinge

Allows the blades to flap as a single unit ((rigidrigid inin--planeplane)

Underslung configuration

. Rotorcraft Flying Handbook: Ch. 5

Helicopter Components RR--2222 Main Rotor

Two all metal blades Honeycomb construction on the interior Stainless steel leading edge SemiSemi--rigidrigid system Symmetrical airfoil

R-22 POH: Section 1 & 7

7 Helicopter Components RR--2222 Main Rotor

Feather (pitch change) Blades flap as a unit UnderUnder--slungslung on a Teeter Hinge Coning Hinges at bla de a ttac hmen t hub

R-22 POH: Section 1 & 7

Helicopter Components RR--2222 Main Rotor

25 feet, 2 inches diameter 7.2 inch chord line 8 degree washout (twist) Tip speed 672 FPS at 100% RPM Rotor RPM 530 at 104%

R-22 POH: Section 1 & 7

8 Helicopter Components RR--2222 Main Rotor

The swash plate assembly transfers control inputs from the collective and cyclic controls to the main rotor blades

Rotorcraft Flying Handbook: : Ch. 5

Helicopter Components RR--2222 Main Rotor

The swash plate assembly is composed of many parts: pitch horns (x2)

bearing pitch links (x2) rotating plate

stationary plate control rods (x3) .

R-22 POH: Section 1 & 7

9 Helicopter Components RR--2222 Tail Rotor

Two all metal blades Honeycomb construction on the interior Aluminum skin Semi-Rigid system Asymmetrical airfoil

R-22 POH: Section 1 & 7

Helicopter Components RR--2222 Tail Rotor

Offset Delta Hinge to allow for bl a de flapping Both blades flap as a single unit Fixed coning angle

R-22 POH: Section 1 & 7

10 Helicopter Components RR--2222 Tail Rotor 3 feet 6 inch diameter 4 inch chord line Tip speed 599 FPS at 100% RPM Tail rotor RPM 3396 at 104%

R-22 POH: Section 1 & 7

Helicopter Components Engine

Lycoming O-O-360360--J2AJ2A (Beta II) 361 cubic inches displacement 180 BHP de-de-ratedrated to 145 BHP @ 2700 RPM 124 BHP @ 2652 RPM (104%) maximum continuous rating. 131 BHP @ 2652 RPM (104%) five minute taketake--offoff rating R-22 POH: Section 1 & 7

11 Helicopter Components Engine

Four cylinders Horizontally opposed Direct drive Air cooled Carbureted Normally aspirated

R-22 POH: Section 1 & 7

Helicopter Components Engine

Two magnetos Start er Alternator Shielded ignition 2200 hours between overhauls (TBO)

R-22 POH: Section 1 & 7

12 Helicopter Components Engine

Direct drive Squirrel Cage cooling fan Wet sump oil system Oil cooler Induction air filter 4-6 Quart oil fill range

R-22 POH: Section 1 & 7

Helicopter Components Drive System

Main Rotor Hub Main Rotor

Tail Rotor Upper Sheave Tail Rotor Drive Shaft Upper Bearing Tail Rotor Free wheeling unit Gear Box Swash Plate (Sprague Clutch) (3:2 Ratio) Yoke Flanges (1 pair - 3 places)

Main Rotor Drive Shaft

Main Rotor Delta Gear Box Flex Plate Damper Delta (11:47 Ratio) (3 places) Hinge

Drive Belts Engine 2652 RPM Clutch Actuator @ 104% Clutch Actuator Tail Rotor

Lower Sheave

Cooling Fan Lower Bearing

R-22 POH: Section 1 & 7

13 Helicopter Components Drive System

Main Rotor Hub Main Rotor Main rotor gear box: Single stage

Swash Plate spiralspiral--bevelbevel gear set Main Rotor Drive Shaft Splash lubricated

Main Rotor Gear Box Air cooled (11:47 Ratio)

R-22 POH: Section 1 & 7

Helicopter Components Drive System

Tail rotor gear box:

Single state spiralTail Rotor Gear Box bevel gear set (3:2 Ratio) Splash lubricated Air cooled Delta Hinge

Tail Rotor

R-22 POH: Section 1 & 7

14 Helicopter Components Landing Gear

Spring and Yield Skid Shoes Ground Handling Wheels

R-22 POH:. Section 7

15 Lesson 1: Helicopter Systems Table of Contents

Helicopter Components Flight Controls Electrical Systems Fuel and Fuel System Oil and Oil System Instruments

Flight Controls General Cyclic Throttle

Pedals

R-22 POH: Sec. 7 Collective Rotorcraft Flying Handbook: Ch. 4

16 Flight Controls Cyclic

Function: tilt the main rotor disc in the direction of desired horizontal flight. While in flight, turns are accomplished by right and left movement of the cyclic. Airspeed is controlled primarily with the cyclic. Dual controls (left side controls removable)

R-22 POH: Sec. 7 Rotorcraft Flying Handbook: Ch. 4

Flight Controls Collective

When the collective control is raised, pitch is increased on both main rotor blades. Dual controls

Collective

R-22 POH: Sec. 7 Rotorcraft Flying Handbook: Ch. 4

17 Flight Controls Throttle

Twist Grip CorrelatorCorrelator-- Mechanical linkage More RPM Raise Collective = Increase Power Lower Collective = Decrease Power GovernorGovernor-- Electronically maintains RPM LRPMLess RPM Only active above 80% RPM Can be manually overridden

R-22 POH: Sec. 7 Rotorcraft Flying Handbook: Ch. 4

Flight Controls Pedals

The Pedals control the pitch on the Tail Rotor thereby adding more or less thrust. Purpose: Counteract torque of Main Rotor Control heading in a hover Maintain trim in flight Dual controls

R-22 POH: Sec. 7 Rotorcraft Flying Handbook: Ch. 4

18 Lesson 1: Helicopter Systems Table of Contents

Helicopter Components Flight Controls Electrical Systems Fuel and Fuel System Oil and Oil System Instruments

19 Electrical Systems Battery

Left side of engine compartment 12 volt – 25 ampamp--hourhour Supplies power for engine starting Secondary purpose: supply nominal voltage to the alternator Master Battery switch on the console

R-22 POH: Sec.7

Electrical Systems Alternator

Located at the rear of the engine compartment 14 volt – 60 amp Primary source of power to electrical systems during normal operations Alternator switch, Ammeter, and Alternator light on console

R-22 POH: Sec.7

20 Electrical Systems Circuit Breakers

Located on a ledge in front of the passenger seat. PushPush--toto--resetreset type. If a breaker pops soon after being reset, do not reset a second time. All breakers should be checked to be pushed down before each flight.

R-22 POH: Sec.7

Electrical Systems Ignition

Ignition system is independent of the electrical system .

. R-22 POH: Sec.7

21 Electrical Systems Ignition

Dual magnetos Provides voltag,ge to distributor, then directed to spark plugs Two spark plugs per cylinder

R-22 POH: Sec.7

22 Lesson 1: Helicopter Systems Table of Contents

Helicopter Components Flight Controls Electrical Systems Fuel and Fuel System Fuel types Diagram and operations Contamination Improper fuel Oil and Oil System Instruments

Fuel and Fuel System Fuel Types

Available Fuel Grades

80/87 aviation fuel Red

100LL aviation fuel Blue

100/130 aviation fuel Green

Jet A fuel Straw Approved Fuel Grade for R-R-2222 Beta II

100LL When any two grades of aviation fuel are combined, the mixture turns clear

R-22 POH: Sec. 2 & 7 Rotorcraft Flying Handbook: Ch.5

23 Fuel and Fuel System Diagram and Operations

Tank Vents Auxiliary Tank Main Tank

Aux Tank Drain

Sample Point (Right Belly Panel) Main Tank Drain Sample Point Cross-Feed fuel line (Left Side Fuselage) Fuel Shut Off Valve Gascolator Drain & Sample Point Carburetor R-22 POH: 2 & 7 Rotorcraft Flying Gascolator Handbook: Ch.5

Fuel and Fuel System Diagram and Operations

MAIN Tank

Total Capacityy - 19.8 US ggal

Useable Capacity - 19.2 US gal AUX Tank

Total Capacity - 10.9 US gal

Useable Capacity - 10.5 US gal Fuel Gaggpes operated b y floatfloat--ttype sensors in . each tank. Low Fuel warning light activates with approximately one gallon of fuel remaining.

R-22 POH: Sec. 2 & 7 Rotorcraft Flying Handbook: Ch.5

24 Fuel and Fuel System Contamination

Types of Contamination

Water

Debris – Solids Prevention

Fill Tanks at the end of the day

Filler Cap on

Store aircraft in clean dry area Elimination

Drain into fuel tester

Private Pilot Test Prep: Ch 2

Fuel and Fuel System Improper Fuel

Detonation

Cause: Using low grade fuel or improper air- fuel mixture

Result: Spontaneous explosion of mixture in the cylinder & extreme heat Preignition

Cause: Premature burning of air-fuel mixture leading to carbon or lead deposits.

Result: Mixture ignites in advance of normal ignition

Private Pilot Test Prep:. Ch 2

25 Lesson 1: Helicopter Systems Table of Contents

Helicopter Components Flight Controls Electrical Systems Fuel and Fuel System Oil and Oil System Description Wet S ump vers u s Dry Su mp Oil Type and Quantity Instruments

. .

26 Oil and Oil Systems Description

Lubricates, cools and cleans the engine Oil temp and pressure monitored by gauges on the instrument panel Wet sump, oil pump (pressure ) feed , sp lashlash-- lubricated crankshaft, airair--cooledcooled system

Jeppesen Private Pilot:. Ch. 2

Oil and Oil Systems Wet Sump vs. Dry Sump

In a wet sump oil system , oil is carried pumped directly from the oil pan.

In a dry sump oil is contained in a separate tank.

Jeppesen Private Pilot:. Ch. 2

27 Oil and Oil Systems Oil Type and Quantity

Type

AAhlshless Dispersan tGt Gra de

100W SAE50 for all average ambient air temperatures Quantity

4 to 6 Quarts

R-22 POH: Section .2

28 Lesson 1: Helicopter Systems Table of Contents The Drive System Flight Controls Electrical Systems Fuel and Fuel System Oil and Oil System Instruments Dual tachometers Low RPM Warning System Manifold Pressure Pitot Static System Magnetic Compass .

Instruments Dual Tachometers

Display RPM of engine and main rotor.

Will continue to register even if engine is not running and master battery switch is off.

R-22 POH: Sec. 2

29 Instruments Low RPM Warning System

Consists of a warninggg light and audible horn Activates when main rotor RPM is 97% or less System check as part of prepre--flightflight

. R-22 POH: Sec. 7

Instruments Manifold Pressure

Displays amount of power being produced by the engine

Reflects changes in position of collective

R-22 POH: Sec. 2

30 Instruments Pitot Static System

The pitot static system measures differential air pressure.

STATIC SOURCE

PITOT TUBE

Rotorcraft Flying Handbook: Ch. 12

Instruments Pitot Static System Pitot tube supplies pressure only to Air Speed Indicator

Static source supplies pressure to the Altimeter, Vertical Speed Indicator, AND the Air Speed Indicator

PITOT TUBE AIR VERTICAL SPEED SPEED ALTIMETER INDICATOR INDICATOR

STATIC SOURCE

Rotorcraft Flying Handbook: Ch. 12

31 Instruments Pitot Static System

Airspeed indicator displays indicated airspeed in knots (KIAS). Indicated airspeed is the speed of helicopter relative to air moving past pitot tube. Airspeed is controlled ppyyrimarily with cyclic. Changes in the collective position will have a secondary effect.

R-22 POH: Sec. 2 Rotorcraft Flying Handbook: Ch 12

Instruments Pitot Static System

Altimeter displays indicated altitude.

Rotorcraft Flying Handbook: Ch. 12

32 Instruments Pitot Static System

Changes in altitude are determined by measuring changes in barometric pressure.

Rotorcraft Flying Handbook: Ch. 12

Instruments Pitot Static System

Adjustment knob allows you to set local altimeter setting in the “Kollsman” window on the right. Keep setting current as you fly 0.1 inch in Kollsman changes indication by 100 fee t.

Rotorcraft Flying Handbook: Ch. 12

33 Instruments Pitot Static System Tens of The altimeter uses three ‘hands’ to display Thousands the indicated altitude.

The value shown here is 14,730 feet

Hundreds

Thousands

Rotorcraft Flying Handbook: Ch. 12

Instruments Pitot Static System

The vertical speed indicator, or VSI,,py displays rate of climb or descent.

Rotorcraft Flying Handbook: Ch. 12

34 Instruments Pitot Static System

Vertical speed is: Determined by measuring the rate of change of barometric pressure. Controlled primarily by changes in Collective position and secondarily by changes in Cyclic.

Rotorcraft Flying. Handbook: Ch. 12

Instruments Pitot Static System

Reading the VSI:

The value shown here is 250 FPM Climb

Rotorcraft Flying Handbook: Ch. 12

35 Instruments Magnetic Compass

The magnetic compass displays the heading of the he licop ter re la tive to magne tic nor th.