This document provides information on the Diamond DA 20 C1 aircraft, including: 1. General performance specifications and limitations, such as maximum takeoff weight, airspeed limits, fuel capacity, and engine specifications. 2. Descriptions of key aircraft systems like the flight controls, landing gear, engine, and cockpit controls. 3. Standard operating procedures for taxi, takeoff, landing and other normal flight operations. 4. Emergency procedures for issues like engine failure, electrical fires, and cabin fires. 5. Details on aircraft performance, mass and balance specifications, and the instrument panel layout.

1. DIAMOND-20 C1

2. GENERAL DESCRIPTION:
1 - DA 20 COURSE:
. SEP (land) ACFT MODEL: DIAMOND SA-20 C1 (DV 20)
. Material: AFM http://www.diamondaircraft.com/technical-publications/
2 - PERFORMANCE EXERCISES.
3 - TEST.

3. INDEX:
1- GENERAL.
2 - OPERATING LIMITATIONS.
3 - DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS.
4 - NORMAL OPERATING PROCEDURES.
5 - EMERGENCY PROCEDURES.
6 – PERFORMANCE.
7 - MASS AND BALANCE .
8 – INSTRUMENT PANEL.

4. GENERAL:
• Certification JAR-23.
• Overall Dimensions:
Span : appr. 10.89 m appr. 35 ft 9 in
Length : appr. 7.24 m appr. 23 ft 9 in
Height : appr. 2.16 m appr. 7 ft 1 in
• Landing Gear: tricycle non-retractable
• Fiber monocoque, seats normal 2.
• Reciprocating single-engine.
• Garmin 430

5. GENERAL:

6. VA
up to 800kg
106
KIAS
106
KIAS
VNO
118 KIAS
VNE
164 KIAS
VFE
LDG: 78
KIAS
T/O: 100
KIAS
White arc 34 KIAS - 78 KIAS
OPERATING
LIMITATIONS

7. OPERATING LIMITATIONS
POWER-PLANT LIMITATIONS (2.4)
•Engine: CONTINENTAL IO-240
•Max. take-off RPM : 2800 RPM
•Max. continuous RPM : 2800 RPM
•Manifold pressure limitation: FULL throttle
•Oil quantity:
Minimum : 4 qts.
Maximum : 6 qts
•During the first 50 hours of operation of a new or newly overhauled engine,
or after replacement of a cylinder, airplane engine oil should be used
according to the following table:
•Page 2 - 6

9. MASS AND BALANCE (2,7)
MTOW
Normal
Category
800 kg
MLW
Original
MLG strut
800 kg
Max. load standard baggage
compartment
20 kg
Max. load extended compartment 20 kg

10. MASS & BALANCE (2.7)
• Exceeding the mass limits will lead to an overstressing of the airplane as
well as to a degradation of flight characteristics and flight performance.
• The maximum landing mass is the highest mass for landing conditions at
the maximum descent velocity. This velocity was used in the strength
calculations to determine the landing gear loads during a particularly hard
landing.
• In some countries the beginning of a flight is defined by starting the
engine. In those countries a maximum ramp mass 3 kg above the
maximum take-off mass is approved. At the time of lift-off the maximum
permitted take-off mass must not be exceeded.

11. APPROVED MANEUVERS
Normal Category:
- All normal flight maneuvers.
- Stalling (with the exception of dynamic stalling).
- Lazy Eights, Chandelles, steep turns and similar maneuvers.
MAX bank 60°.
CAUTION
If bank > 60° DG and ADI is affected by Lazy Eights, Chandelles,
steep turns and similar.

12. OPERATING ALTITUDE
• The maximum demonstrated operating altitude 13,120 ft (4000m)

13. FUEL (2.14)
Fuel Grade:
AVGAS 100LL / AVGAS 100/130LL (ASTM D910)
AVGAS 100 / AVGAS 100/130 (ASTM D910)
Fuel Quantity:
24.0 US gallons/91 liters
0.5 US gallons/2 liters

14. FUEL (2.14)
2.4 POWER-PLANT LIMITATIONS
2.4.1 Engine
(a) Engine Manufacturer : Continental Motors
(b) Engine Type Designation : IO-240-B
(c) Engine Operating Limitations
Max. T/O Power (5 min.) : 125 BHP / 93.2 kW
Max. Permissible T/O RPM : 2800 RPM
Max. Continuous Power : 125 BHP / 93.2 kW
Max. Permissible Continuous RPM : 2800 RPM
(d) Oil pressure
Minimum : 10 psi (1.5 bar)
Maximum : 100 psi (6.9 bar)
Ambient temperature below
32°F (0°C), Full power operation
oil pressure 70 psi max
Normal Operating : 30 psi (2.1 bar) to 60 psi (4.1 bar)

15. DESCRIPTION OF THE
AIRPLANE AND ITS SYSTEMS
FLIGHT CONTROLS (7.2)
The ailerons, elevator and wing flaps are operated through control rods, while the
rudder is controlled by cable. the flaps are electrically operated.
The flaps are driven by an electric motor and have 3 settings:
- Cruise (UP), totally retracted
- Take-off (T/O), and
- Landing (LDG).
- When the upper light (green) is illuminated, the flaps are in the Cruise position (UP);
- When the center light (white) is illuminated, the flaps are in Take-off position (T/O);
- When the lower light (white) is illuminated, the flaps are in Landing position (LDG).

16. DESCRIPTION OF THE
AIRPLANE AND ITS SYSTEMS
LANDING GEAR
The landing gear consists of a main landing gear of sprung steel struts, and a
free-castering nose wheel which is sprung by an elastomer package.
Wheel Brakes
Hydraulically operating disk brakes act on the wheels of the main landing gear. The wheel
brakes are individually operated by means of toe pedals.
Parking Brake
The lever is located on the small center console under the instrument panel, and is in
the upper position when the brakes are released. To operate the parking brake pull the
lever downwards until it catches. Brake pressure is built up by multiple operation of the
toe brake pedals.

17. DESCRIPTION OF THE AIRPLANE
AND ITS SYSTEMS

18. DESCRIPTION OF THE
AIRPLANE AND ITS SYSTEMS
ENGINE, GENERAL:
•Continental Motors IO-240-B
•Air-cooled
•Four-cylinder four-stroke engine. Horizontally-opposed
•Direct-drive engine
•Fuel injection and underslung exhaust.
•Max. power: 125 BHP (93.2 kW) at 2800 RPM at sea level and ISA.
•Max. continuous power: 125 HP (93.2 kW) at 2800 RPM at sea level and ISA.

21. DESCRIPTION OF THE
AIRPLANE AND ITS SYSTEMS

22. OPERATING CONTROLS:
Throttle
- Left hand lever with large grey knob.
This lever is used to set the RPM. When the throttle is furthest forward,
the engine is being provided with extra fuel for high performance settings.
Lever forward (MAX PWR) = Full throttle, higher RPM
Lever to rear (IDLE) = Idle, low RPM
Fixed pitch propeller, therefore there is no propeller control lever.
DESCRIPTION OF THE
AIRPLANE AND ITS SYSTEMS

23. OPERATING CONTROLS:
Mixture Control Lever
•
Right hand lever with red handle and lock to
avoid inadvertent operation.
This lever is used to set the proportions in the
fuel-air mixture which is supplied to the
engine.
Lever forward (RICH) = Mixture rich (in fuel)
Lever to rear (LEAN) = Mixture lean (in fuel)
If the lever is at the forward stop, extra fuel is being supplied to the engine which at higher
performance settings contributes to engine cooling. To shut off the engine the mixture control
lever is pulled to the rear stop.

24. DESCRIPTION OF THE
AIRPLANE AND ITS SYSTEMS
OPERATING CONTROLS:
Alternate Air
In the event of the loss of manifold pressure => draw air from the engine
compartment.
Located under the instrument panel to the left of the center console.
To open alternate air the lever is pulled to the rear. Normally, alternate air is
closed, with
the lever in the forward position.

25. NORMAL PROCEDURES:
AFM RECOMMENDED SPEEDS FOR NORMAL PROCEDURES

30. NORMAL PROCEDURES:

31. NORMAL PROCEDURES:
STARTING THE ENGINE
Do not overheat the starter motor
Do not operate the starter motor for more than 10 seconds
After operating the starter motor, let it cool off for 20 seconds.
After 6 attempts to start the engine, let the starter cool off for half an hour

36. NORMAL PROCEDURES:
FLOODED ENGINE

37. NORMAL PROCEDURES:
TAXIING
•Steering procedure: differential brakes.
•Avoid excessive use of brakes during taxiing (use throttle idle if required)
•Following extended operation on the ground, or at high ambient temperatures, the
following indications of fuel vapour lock may appear:
- Arbitrary changes in idle RPM and fuel flow.
- Slow reaction of the engine to operation of throttle.
- Engine will not run with throttle in IDLE position.

38. NORMAL PROCEDURES:

39. NORMAL PROCEDURES:

40. NORMAL PROCEDURES:

41. NORMAL PROCEDURES:

42. NORMAL PROCEDURES:

43. EMERGENCY PROCEDURES:
3.2. AIRSPEEDS DURING EMERGENCY PROCEDURES
VIAS
kts
Engine failure after take-off with flaps in T/O position…………………………………….... 60
Manoeuvring Speed ………………………………………………………………………………………….. 106
Airspeed for best glide angle (Wing Flaps UP, 800 kg)………………………………………. 73
Precautionary Landing (with power and Wing Flaps in landing position) …………… 55
Emergency landing with engine off (Wing Flaps in T/O) …………………………………….. 60
Emergency landing with engine off (Wing Flaps in LDG) ……………………………………. 55
Emergency landing with engine off (Wing Flaps UP) …………………………………………. 64

44. EMERGENCY PROCEDURES:

45. EMERGENCY PROCEDURES:

46. EMERGENCY PROCEDURES:
NOTE: DO NOT START THE ENGINE IF PROPELLER IS WINDMILLING.
ENGINE DAMAGE MAY RESULT!!!
- The propeller will continue to windmill as long as the airspeed is at least 60 KIAS.

47. EMERGENCY PROCEDURES:
(a) Engine Fire during Engine-Start-Up on the Ground
1. Fuel Shut-off Valve…………………… CLOSED
2. Cabin heat ………………………………..CLOSED
3. Mixture……………………………………...IDLE CUT-OFF
4. GEN/BAT Master Switch …………....OFF
5. Ignition Switch …………………………..OFF
6. Evacuate Airplane immediately
3.3.3. Fire
(b) Engine Fire during Flight
1. Fuel Shut-off Valve ………..CLOSED
2. Cabin Heat …………………….CLOSED
3. Airspeed (VIAS) ……………….73 kts
4. Flaps ………………………………T/O
5. Electric Fuel Pump ………….OFF
6. Perform emergency landing with engine
off according to paragraph 3.3.2

48. EMERGENCY PROCEDURES:
(c) Electrical Fire including Smoke during Flight
1. GEN/BAT Master Switch ………….OFF
2. Cabin Air ………………………………...OPEN
3. Fire Extinguisher …………….. use only if smoke
development continues.
IF FIRE EXTINGUISHER IS USED, THE CABIN MUST BE VENTILATED
In case the fire is extinguished and electric power is required for continuation of
the flight:
4. Avionics Master Switch ………………………OFF
5. Electrically Powered Equipment …………OFF
6. CIRCUIT BREAKERS……………………………...Push all circuit breakers
7. CIRCUIT BREAKERS ……………………………..Push BATTERY
8. GEN/BAT Master Switch ………………………ON BAT ½ only
9. Circuit breakers …………………………………..Push GEN & GEN CONTROL
10. GEN/BAT MAster Switch ……………………ON
11. Circuit Breakers ………………………………...Push AVIONICS and AVIONICS MASTER
12. Avionics Master Switch ……………………….ON
13. Circuit Breakers ………………………………....Push to activate systems as required
14. Radio ………………………………………………….ON
15. Land as soon as possible.

49. (d) Electrical Fire including Smoke on the Ground
1. GEN/BAT Master Switch …………………………..OFF
If engine running:
2. Throttle …………………………………………………..IDLE
3. Mixture …………………………………………..IDLE CUT-OFF
3. Fuel Shut-off Valve……………………………. CLOSED
4. Ignition Switch …………………………………………OFF
5. Canopy …………………………………………………..open
6. Fire Extinguisher deploy ………….......as required
EMERGENCY PROCEDURES:
(e) Cabin Fire during Flight
1. GEN/BAT Master Switch……………..OFF
2. Cabin Air ………………………………….OPEN
3. Cabin Heat ……………………………CLOSED
4. Fire Extinguisher deploy ….as required
5. Land ……………………as soon as possible

50. PERFORMANCE:

51. PERFORMANCE:

52. PERFORMANCE:

54. MASS AND BALANCE:

55. MASS AND BALANCE:

56. INSTRUMENT PANEL:

57. INTENCIONADAMENTE EN BLANCO