giovedì 30 aprile 2015

Avionics Bending: VOR tuning panel

The VOR control panel provides selection of VOR frequency and course during the VOR manual mode. The VOR frequency is selected by the two left concentric knobs for manual tuning. The outer knob selects tens and units of MHz. The inner knob selects tenths and hundredths of MHz.

The VOR system is in the manual mode when the EFIS control panel is in the VOR or ILS mode settings. It is also in the manual mode when the EFIS control panel is in the MAP or PLAN mode settings and the AUTO-MAN switch on the VOR control panel is in the MAN setting.

VOR frequency is displayed in the window above the frequency select knob (FREQ). The 100 MHZ digit is fixed at 1. The other digits display the VOR frequency as selected manually by the VOR control panel or automatically by the FMC.

The VOR COURSE is selected on the ten-turn course select knob and is displayed by the three digit display above the knob.

The AUTO-MAN switch is used to select the tuning mode of the VOR/MKR receiver when the EFIS mode select switch is set to MAP or PLAN. Tuning the VOR in these modes is normally controlled by the FMC (automatic) except when the AUTO-MAN switch is set to MAN. The tuning is then accomplished manually at the VOR control panel. When the EFIS switch is in the ILS or VOR position, tuning is always manually done from the VOR control panel.

The captain's and first officer's VOR control panels are located on the left and right side of the glareshield (P55), respectively.

giovedì 23 aprile 2015

Avionics Bending: Engine Standby Indicator

Back-up display of N1, EGT, and N2 is provided by the Standby Engine Indicator (SEI) on the P1-3 panel.
Engine operating limits are indicated on overlimit placards mounted on the SEI face. Respective sensor signals are input directly to the SEI to assure display in the event the Engine Indication and Crew Alerting System (EICAS) display units or EICAS computers fail.

NOTE: The Standby Engine Indication operation makes it necessary to have either 28VDC aircraft power or the engine operate.
When the SEI switch is "ON", you will see the digital display whenever the SEI is powered. When the switch is in the "AUTO" position, you will see the digital display only when the EICAS has failed. The SEI can be tested using a screwdriver operated switch on the left side of the SEI.

venerdì 3 aprile 2015

Avionics bending: Fuel quantity indicator

The fuel quantity indicator shows these informations:

-Left fuel quantity
-Right fuel quantity
-Center fuel quantity
-Total fuel quantity
-Fuel Temperature

The indicator's display has a high contrasr, dual-cell liquid Crystal display set out from the indicator bezer for increased visibility and viewing angle.
The indicator has 4 separate circuits, one for each tank display to make sure that a failure in one of them won't affect the others.

The 3 fuel tank quanityt displays have a resolution of 0.1 and a max value of 99.9.
The total fuel quantity display has a resolution of 0.1 and a max value of 999.9.
Fuel quantity shows to a resolution of 100lbs/kgs (lbs or kgs selectable by a program pin)

The indicator receives fuel quantity information over one of two ARINC 429 digital data buses, A or B.
Bus A is normally used and is selected at start-up or after a circuit test is complete. If bus A information becomes unavailable, the indicator keeps bus A data and after 4 seconds changes to bus B.
If it doesn't receive data on bus B after 4 seconds, the receiver continues to cycle at a 4-second rate until valid data is recognized.
If both buses are inactive, the tank indicator(s) show letters -Ab to show a dual bus failure.

Here is a video of gauge power up with no ARINC data provided yet.

And this video shows startup with no ARINC data, then the unit is feeded with fuel quantity data per tank