(c)  
The LOAD/1 performance-function provides a two-page display used for initial data entry. The LOAD pages are automatically displayed at system activation.

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F.  There are three data entry keys provided for loading data into the PDCS.
(1)  
SEL - advances the caret one data line each time it is pressed. It advances only to lines with an asterisk (*), denoting data that must be entered.

(2)  
ENT - loads keyed in data into the computer. The caret flashes prior to the entering of keyed in data.

(3)  
CLR - erases the data on the same line as the caret and causes the caret to flash, indicating data entry (ENT button) is to follow.

G.  A BRT knob on the CDU front panel controls the CRT display intensity.
H.  On GJ B-2509 and B-2510; The CDU is also used as a self-test display for the automatic flight control system, which includes autothrottle and flight control computers (Ref 22-11-01 and 22-31-01). The test is accessible in STBY mode, pages TEST 4-6 and TEST 5-6.
I.  Failure of the CDU usually results in the display going blank. CDU failure has no effect on command bugs and related flags if the computer is operating correctly.
3.  Performance Data Computer
A.  The performance data computer is a 112 ATR long case located on the electronic equipment rack E1, shelf No. 1. It contains a power supply, central processing unit, program memory, and analog-to-digital (A/D) and digital-to-analog (D/A) converters for input and output interface. An additional protected memory retains all entered data during power interruptions up to 10 seconds. Fault detection and isolation to the line replaceable unit occurs during self-tests. Built-in-test equipment (BITE) circuits and software operate continuously to check critical CDU, input/output circuits, main storage, and power supply operation and generate computer interrupts, set output levels and fault indicators as necessary.
B.  The controls and indicators on the front panel of the computer are a LAMP TEST switch, FAILURE lights, and INDEX NUMBER set switches. The failure lights indicate whether a fault is in the computer, CDU, or input signals. The failure lights, with the diagnostic codes on the CDU, aid in rapid fault isolation. The pushbutton switch, when depressed, tests the failure lights. The INDEX NUMBER switches represent the hundreds, tens and units digits for entering the flight index number. The switches are guarded to eliminate the possibility of inadvertent changing of the index number. The flight index number allows input of a weighting factor for the various operating expenses
C.  An hourmeter and a multipin electrical connector are located on the rear of the computer.
(1)  The electrical connector contains, among other pins, program pins used to define the system configuration interlock parameters. These parameters include system-operational options, such as English or metric unit display, and system configuration control, such as airplane engine model select code.
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4.  Mode Annunciators (Fig. 1)
A.  GJ ALL EXCEPT B-2509 and B-2510
(1)  
The mode annunciators indicate the flight mode driving the EPR indicator and Mach/Airspeed indicator command bugs. The appropriate mode light illuminates when a flight mode is selected and the ENGAGE or TURB button is depressed. Internal to the annunciator is a diode matrix that decodes selected mode binary coded data supplied by the computer.

(2)  
The annunciator contains replaceable lamps mounted in a heat sink. These lamps can be replaced from the front, after removing the legend plate.

B.  GJ B-2509 and B-2510
(1)  
The PDC mode annunciators indicate the flight mode engaged. The appropriate mode is displayed when a flight mode is selected and the ENGAGE or TURB button is depressed. Other controls and annunciators are used by the automatic flight control system (Ref 22-11-01, 22-31-01).

(2)  
Each mode annunciator display consists of a three-faced prism and two prism-driving solenoids. Two faces of the prism are engraved with an annunciator legend; the third face is blank and is in the display position when deactivated. The solenoid actuated by a mode signal (dc ground) drives the prism 120 degrees in the required direction to display the corresponding mode legend. When the solenoid loses the signal, the prism rotates to display a blank face. The second solenoid is used with another mode and drives the prism in the opposite direction. The prisms are illuminated constantly by background lights.
　
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