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fuel pump.
52. On the back-rest on the right side.
56. On the instrument panel. If equipped with altitude compensating fuel pump.
53.
On the Instrument Panel.
54.
Adjacent to the flap controller.
VFE (T/O) 100 KTS.
VFE (LDG) 78 KTS.
57. On the instrument panel. If equipped with altitude compensating fuel pump.
2.16. DEMONSTRATED CROSSWIND COMPONENT
The maximum demonstrated crosswind component is 20 kts. (37 km/h).
2.17. TEMPERATURE LIMITS
CAUTION
FOR AIRCRAFT WITH OTHER THAN WHITE UNDERSIDES.
PARKING THE AIRCRAFT OVER A LIGHT COLOURED OR
REFLECTIVE SURFACE IN CONDITIONS OF BRIGHT
SUNLIGHT, PARTICULARLY AT HIGH OAT, IS NOT
RECOMMENDED.
Temperature limit of the structure for the operation of the airplane: Maximum T/O Temperature : 131°F (55°C)
Structural Temperature
CHAPTER 3
EMERGENCY PROCEDURES
3.1. INTRODUCTION...............................................................................................................2
3.2. AIRSPEEDS DURING EMERGENCY PROCEDURES....................................................2
3.3. EMERGENCY PROCEDURES - CHECKLISTS...............................................................3
3.3.1. Engine Failures................................................................................................3
3.3.2. Gliding .............................................................................................................6
3.3.3. Emergency Landing.........................................................................................6
3.3.4. Fire ..................................................................................................................8
3.3.5. Icing...............................................................................................................10
3.3.6. Recovery from Unintentional Spin.................................................................10
3.3.7. Landing with Defective Tire on Main Landing Gear.......................................11
3.3.8. Electrical Power Failure.................................................................................11
3.3.9. Flap System Failure.......................................................................................13
3.3.10. Starter Relay Failure......................................................................................13
3.3.11. Avionics System Failure................................................................................14
3.3.12. Trim System Failure ......................................................................................15
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