Diamond Aircraft DV 20 KATANA, Maintenance Manual

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AIRCRAFT
DV 20 KATANA AMM
Navigation and Pitot Static
Doc # 4.02.02
Rev. 13
34-12-00
Page 1
15 Dec 2018
Section 34-12
STALL WARNING SYSTEM
1. Description
The airplane is equipped with a stall warning system as part of the standard equipment. The sensor
works pneumatically and is located in the left wing. The stall warning system should warn the pilot
acoustically using a horn shortly before reaching the maximum angle of attack. The horn is located in
the left hand section of the instrument panel.
A hose connects the horn to the seal chamber and bore in the left wing. This bore is marked with a red
circle. The system is maintenance free and can be checked by applying slight negative pressure to
the sensor.
2. Adjustment
The stall warning system is designed to warn the pilot approx. 5 to 10 knots before the stall in case of
slow deceleration (see table below). Upon slow acceleration the warning must stop at that airspeed.
Table of Stall Warning Speeds (IAS) at Maximum Flight Mass (MTOW)
Flap
Position
Stall Warning Threshold
Maximum Minimum
km/h kts. km/h kts.
UP 106 57.2 95 51.3
T/O 97 52.4 86 46.4
LDG 95 48.6 84 45.4
If this value is not reached, first check the system for leaks.
Adjustment can be done as follows:
)
If the stall warning is activated at a too high airspeed, the bore in the wing must be enlarged on its
lower edge with a key file in steps of approx. 1 mm (0.05 in.).
)
If the stall warning is activated at a too low airspeed, the bore in the wing must be enlarged on its
upper edge with a key file in steps of approx. 1 mm (0.05 in.).