飞行翻译_公务机_公务航空_Business Jet_Business Aviation

NOTE
If ADG deployment is caused by a double engine failure, ACMP 3B will provide emergency hydraulic power to the primary flight controls, while all other pumps are inoperative or load shed.

NOTE
To ensure priority to the primary flight controls, a spring-loaded-closed priority valve cuts off hydraulic system 3 pressure to the landing gear selector valves, if hydraulic system 3 pressure drops below 2,100 psi. Alternate landing gear extension will be required in this case.

Accumulator and Reservoirs
System 3 has an accumulator that stores nominal hydraulic pressure to satisfy instantaneous demands of aircraft systems, and dampen pressure surges within the system. The accumulator is precharged with nitrogen to 1,500 psi.
System 3 reservoir is the largest of the three hydraulic systems, with a capacity of 11.14 liters
(2.94 U.S. gal). It is filled via the ground service panel, located in the right main wheel well.
During preflight, a visual inspection should include a check for accumulator pressure at 1,500 psi. With the exception of the accumulator gauge, system 3 components are not readily accessible with the wheel well bins installed.

 HYDRAULIC POWER Description  Vol. 2  13.10.8 
Oct 05/06 

Hydraulic System 3 Accumulator Gauge
Figure 13.10.6

CONTROLS AND INDICATORS
The HYDRAULIC panel provides the system controls; the HYDRAULIC synoptic page provides a pictorial representation of the system status, and the EICAS page provides the system caution and advisory messages respectively (see Figure 13.10.7 to Figure 13.10.9, and EICAS Messages table).

 HYDRAULIC POWER Description  Vol. 2  13.10.9 
Oct 05/06 

HYDRAULIC Panel
Figure 13.10.7

 HYDRAULIC POWER Description  Vol. 2  13.10.10 
Oct 05/06 

HYDRAULIC Synoptic Page Color Coding (1 of 2)
Figure 13.10.8

 HYDRAULIC POWER Description  Vol. 2  13.10.11 
Oct 05/06 

HYDRAULIC Synoptic Page Color Coding (2 of 2)
Figure 13.10.9

 HYDRAULIC POWER Description  Vol. 2  13.10.12 
Oct 05/06 

MEANING
Respective engine-driven pump pressure is less than 1,800 psi.
Respective AC motor pump pressure is less than 1,800 psi.
Respective hydraulic shutoff valve is not closed after actuation of the respective ENG FIRE PUSH switch/light.
Respective system temperature is greater than 96°C, or greater than 107°C for 4 minutes after takeoff power is applied.
Respective system pressure is less than 1,800 psi.
Respective hydraulic shutoff valve has closed after actuation of the respective ENG FIRE PUSH switch/light.
CL.605 Flight Crew Operating Manual
PSP 605.6