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钻石20飞机飞行手册 DA 20 Airplane Flight Manual(20)

时间:2011-10-28 13:14来源:蓝天飞行翻译 作者:admin
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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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