Airframe & Systems Tutorial - PPSC

1228 Pages·2001·45.202 MB·English

021 AIRFRAME & SYSTEMS
© G LONGHURST 1999 All Rights Reserved Worldwide
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EDITION 2.00.00 2001
This is the second edition of this manual, and incorporates all amendments to previous editions, in
whatever form they were issued, prior to July 1999.
EDITION 2.00.00 © 1999,2000,2001 G LONGHURST
The information contained in this publication is for instructional use only. Every effort has been made to ensure
the validity and accuracy of the material contained herein, however no responsibility is accepted for errors or
discrepancies. The texts are subject to frequent changes which are beyond our control.
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TABLE OF CONTENTS
Airframe and Systems
Landing Gear Systems
Hydraulics
Air Conditioning & Pressurisation
Ice and Rain Protection
Fuel & Fuel Systems
Electrics-DC
Electrics-AC
Computer, Binary and Logics
Basic Radio Theory
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TABLE OF CONTENTS
Piston Engine Principles and Construction
Piston Engine Lubrication and Cooling
Piston Engine Ignition and Starting Systems
Piston Engine Fuel Supply
Piston Engine Power Augmentation and
Performance
Piston Engine Performance
Piston Engine Power Transmissions and
Propellers
Piston Engine Operation and Handling
© G LONGHURST 1999 All Rights Reserved Worldwide
TABLE OF CONTENTS
Gas Turbine Principles of Operation
Gas Turbine Construction Part 1 – The Cold
Section
Gas Turbine Construction Part 2 – The Hot
Section
Gas Turbine Engine Systems
Gas Turbine Engine Performance and
Operation
Auxiliary Power Units
Emergency Equipment-Aeroplane
© G LONGHURST 1999 All Rights Reserved Worldwide
021 Airframe & Systems
Airframe and Systems
Aircraft Structures
© G LONGHURST 1999 All Rights Reserved Worldwide
Airframe and Systems
Airframe and Systems
1
Aircraft Structures
1. The structure of the aircraft is known as the airframe and usually comprises five major units.
These are the fuselage, the wings, the stabilising surfaces (fin and tailplane), the landing gear and the
flying control surfaces. These major components, plus many others, are illustrated at Figure 1-1.
FIGURE 1-1
Aircraft Structure
Major
Components
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Airframe and Systems
2. Each of these airframe components must be sufficiently strong to withstand the forces acting
upon it during all stages of flight without distortion or failure. Also, they must be joined together by
bolts, screws, rivets, welding and so forth. Whichever method or combination of methods is used, it
must be of sufficient strength to withstand the loads to which these junctions will be subjected.
3. The wings support the aircraft in flight so they must be made of materials that are strong
enough to withstand the aerodynamic forces, without bending excessively or twisting. However, as
these forces vary at different flight speeds or during turbulence, the wings must be able to flex. The
same applies to the junction between wings and fuselage.
4. When the rudder or elevators are used, the forces acting upon them tend to twist or bend the
fuselage, which must be strong enough to resist this. Similarly, it is important that the wings, whilst
able to flex up and down, do not twist when the ailerons are used.
5. When the elevators are deflected up or down there is a twisting force (torque) applied to the
horizontal stabiliser and its attachment to the fuselage. Both must be strong enough to resist this
twisting force, but the stabiliser must be supple enough to flex, or bend, otherwise it might snap like
a dry twig. The same requirements exist for the fin, when the rudder is deflected left or right.
6. The landing gear must be strong enough not only to support the weight of the aircraft on the
ground, but also to withstand the shock of landing, the twisting loads when the aircraft turns during
taxiing and the bending loads at touchdown. All this applies equally, of course, to the points of
attachment of the landing gear to the airframe.
7. The aircraft designer must consider all these factors and produce an aircraft constructed of
materials strong enough to withstand all of the loads to which the airframe will be subjected. The
aircraft must be flexible where necessary to absorb changing loads and rigid where necessary to
prevent twisting.
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