Brief Maintenance manual DAR-Solo rev...

Aeroplanes DAR ltd. Brief Maintenance Manual DAR-Solo

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Brief Maintenance Manual

DAR-Solo

Sofia 2009


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TABLE OF CONTENTS

Introduction 3Limitations and safety information 4General view of DAR-Solo prototype 7Technical Data 8Inspection before and after the flight 10Propeller Check 12Reduction gear check 13Check the exhaust system 14Nose wheel check 15Pitot tube check 15Check the landing gear-right side 16Brakes system and wheel check-right side 17Check the spar fixing to the body-right side 18Check the fixing of support to the wing-right side 18Check the wing-right 19Check the main tubes fixing to the central beam and to the car-right side 20Ailerons’ controls check-right side 21Check the ailerons’ control in the wing’s construction-right side 22Ailerons check-right side 23Flaps check-right side 24Cockpit inspection 25Check the rudders control cables 27Check the vertical stabilizer 28Check the rudder 29Check the assemblies for fixing the horizontal stabilizer 29Horizontal elevator check 30Check the vertical stabilizer-left side 31Check the main tubes fixing to the central beam and to the car-left side 31Check the ailerons’ control in the wing’s construction-left side 31Ailerons check-left side 31Flaps check-left side 31Check the wing-left 31Check the fixing of support to the wing-left side 31Brakes system and wheel check-left side 31Check the landing gear-left side 31Engine check 32Notes 33


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Introduction This Manual is intended for everyone who maintains the DAR-Solo airplane with one of the standard single cylinder, two-stroke engines: 26 HP F 200 UL by Flyengine or 28 HP F-33 BS by HirthFlugmotoren.

DAR-Solo aircraft is utilized according to its technical condition. That is why it is obligatory to constantly monitor the condition of all assemblies, parts and systems. These checks are included in the pre and after the flight inspections. The exact fulfilment of this advice will secure safe and flawless operation of the aircraft.


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Limitations and safety information

Limitations

DAR Solo is an aircraft that falls in the FAA FAR103 Category.

It is not designed to be used for any maneuvers except:

• Any maneuver incident to normal flying;

• Stalls (except whip stalls); and

• Lazy eights, chandelles, and steep turns, in which the angle of

bank is not more than 60 degrees.

The following limitations are imposed on the speeds and loading of

the airplane:

Vmin flaps 0° = 55 km/h

Vmax flaps11° = 90 km/h

Vmax flaps22° = 80 km/h

Vne = 130 km/h

• Do not overload the Airplane. The Max Gross Weight should

not exceed 220 kg.


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Safety

For your safety read this manual thoroughly and make sure you

understand the capabilities and limitations of the airplane.

If you have any additional questions contact the manufacturer

before operating the machine.

• Never fly when you don’t feel prepared for the conditions of

the flight!

• Never fly under influence of alcohol or drugs!

• Never fly if you have not performed a preflight inspection!

• Never exceed the limitations set by the manufacturer!

DANGER!

Always monitor your airspeed! Never fly close to stall speed or exceed Vne!


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The preflight inspection is one of the pilot’s most important

duties. A number of serious airplane accidents have been traced

directly to poor preflight inspection practices. The preflight

inspection should be a thorough and systematic means by which

the pilot determines that the airplane is ready for a safe flight.

IMPORTANT! THE EXPLOITATION OF

DAR-Solo AIRCRAFT DEPENDS ON ITS CONDITION

The construction of DAR-Solo and of all the aircraft of this series is a relatively simple one. A permanent and direct

control over all main assemblies is enabled in this way for a short period of time.

Thus the main principle of safe exploitation is accomplished :

CONTINUITY OF CONTROL!

You must not forget:


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NEVER COMPROMISE WITH SECURITY – YOURS OR OF THIRD PERSON!

PUT EVERYTHING BEYOND THE REACH OF CHANCE!

General view of DAR-Solo prototype


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Technical Data

Geometry Dimensions of the airplane Length 4.85 м Span 8.17 м Height 2.62 м Fuselage Length 4.85 м Height 1.55 м Width 0.70 м. Wing Wing area 10.76 м² Span 8.17 м Average aerodynamic hord 1200 мм Profile NACA 4412 Aspect ratio 6.63 Taper 1.0 Wing sweep 0° V – shaped wing +1° Wing twist (washout) 0° Angle of wing fixing +6.0° Ailerons area 2 x 0.49 m² Flaps area 2 x 0.4 m² Horizontal tail panels Stabilizer area 1.8 м² Span 2.4 m Stabilizer hord 740 мм Profile NACA 0009 Tail Aspect ratio 1.8 Tail taper 1.0 Tail sweep 0° Fixing stabilizer’s angle (adjusted on land) from +1° to -2.5° Elevator area 0.81 м² Trimmer area 0.05 м² Vertical tail panels Fin area 0.95 м² Height 1.05 м Average geometrical stabilizer chord 910 мм Profile NACA 0009 Aspect ratio 1.16 Taper 3.0 Fin and rudder sweep 25° Rudder area 0.60 м² Trimmer area 0.0 2м²


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Aerodynamics Maximum aerodynamical quality - 8.4 V – min, without flaps, solo Km/h 55 V – min, with flaps 11°, solo Km/h 50 V – min, with flaps 22°, solo Km/h 45 V – economical Km/h 80 V – cruise Km/h 95 V – max SA Km/h 120 V – maximum permissible (Vne) Km/h 150 Max. side wind upon landing M/s 5

Weight Maximum take-off weight kg 220 Empty weight kg 120 Relative construction gravity (this is empty/max weight) - 0.5 Payload kg 100 Relative wing load* Kg/м² 20,4 Estimated overload coefficients* - +6 /-3 Max permissible overload in flight - +4 /-2 Relative power load* Kg/HP 7,3 * at MTOW Completing the airplane parts The airplane, subject of this instruction, is completed with the standard equipment listed below. Each extra equipment is accompanied by its own documentation. The standard equipment of DAR-Solo includes: Engine F 200 UL 26 HP

Hirth F-33 BS 28 HP Propeller LL Prop – Wooden 2 blade 1.5m diameter Navigation instruments Air-speed Compass Inclinometer, (slip ball) Altimeter Variometer Engine instrument EM 002 – included Tachometer, CHT, EGT,

Hour meter, Volts


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Inspection before and after the flight

The inspections before and after the flight are done in one

and the same volume. The aircraft inspection is done in the classic way – from left to

right. Stand in front of the aircraft and make a visual assessment whether the decline is to the left or right. If there is an obvious deflection of more than 15-20 cm at the end of half wing you have to check the respective rubber bumper. Further the inspection goes on as per charts No1,2 and 3. During inspection you have to check the general condition of body skin, wings and tail surfaces. A special attention must be paid to mechanical damages near the main strength elements of the construction – enforced beams, spars and places for fixing ailerons and flaps. Chart No 1.


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Chart No 2.

Chart No 3.

Steps to be taken during the inspection before and after the flight


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1. Propeller Check - check blades for hits and cracks;

- check the fixing of propeller bush to the reduction gear flange;

- check spinner fixing (if any).

NB! Special attention must be paid to stop nuts and studs!

2. Reduction gear check

• check Belt - availability and condition • check Wheels – availability and condition

3. Check the exhaust system for - burns - availability and condition of cramps - availability and condition of the fixing springs - fixing the gas exhaust

4. Nose wheel and Brake system check:


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- Condition and fixing of nose wheel set (fork, bearings and wheel)

- condition and fixing of armed stings of brakes system - condition of brakes mechanism on the wheel - condition of brakes disk – check for burns - condition and fixing of stop nut - visual control to inflate the tire

A – Plastic 6-inch nose wheel

B – Aluminum 8-inch nose wheel


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6. Pitot tube check:

• deformations (to be oriented against air flow) • clogging of inlet of dynamic tube


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7. Check the landing gear for

- mechanical damages and distortions - condition and fixing of main composite force beams

8. Check the spar fixing to the body and the central beam - condition of connecting studs and fixing assembly to the

central beam - condition of connecting studs and fixing assembly to the

car


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9. Check the fixing of support to the wing for - mechanical damages and support distortions - the condition of the connecting stud and the fixing

assembly


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10. Check the wing for

- mechanical damages and support distortions

12. Ailerons’ controls check - the condition and fixing of hinges

- for splint pins on all knee-joints (hinges and cradle)


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15. Cockpit inspection - check of the pedals;

- condition and fixing of control elements to pedals;

- check of the sticks;

- condition and fixing of control tubes on mixer for flaperons control;


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- condition and fixing of flaps control;

- condition and fixing of doubled push-pull controls of elevator;

- condition and fixing of elements of throttle control;

- condition and fixing of elements of brakes system;


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- condition and fixing of seats and belts;

- check of the instruments;

- for leaks in the fuel tank; - condition and fixing of fuel lines; - condition and fixing of air vent on fuel tank;

- for the presence of foreign bodies.


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16. Check the rudders control Push-Pul cables 17. Check the vertical stabilizer and the rudder

- mechanical damages and support distortions - the condition of the connecting hinges - the condition of the fixing push-pullcables


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19. Check the assemblies for fixing the horizontal stabilizer and elevator

- condition and fixing of supports and connections - condition and fixing of small struts

- condition and fixing of controls push-pull cables - condition and fixing of hinges

21. Same as point 18 22. Same as point 11


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23. Same as point 13 24. Same as point 14 25. Same as point 15 26. Same as point 10 27. Same as point 9 28. Same as point 8 29. Same as point 7 30. Same as point 6


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31. Engine check:

- condition of fuel system, pump, lines and filter;

- condition of engine controls - carburetor, control throttle cable;

- condition of carburetor - fixing float camera, jetting, valve,

spring, adjustment screws, fixing to the engine and filter;

Bing Mikuni - condition of ignition system – electrical cables, sparks and

plugs;


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32. Electric system F200 electric system

condition of electric system - battery, electric starter, cables, connections, special attention for main connection “ground”. Electric schema F-200 engine

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