(b)  
CDU displays PDC part number, 10-61962-XXX-YY with appropriate dash numbers.

(c)  
CDU ENGAGE switch light extinguished, and mode annunciator blank.

(5)  
Adjust CDU BRT dimming knob and verify CDU display brightness is controllable. Set knob for optimum readabiiity.

(6)  
Press forward PAGE and verify page CONFIG 2-3 indicates airplane model; whether weight parameters are in pounds or kilograms, and engine type installed.

(7)  
Press forward PAGE and verify page SELF TEST 3-3 indicates VALID.

NOTE:  If a system failure is detected, the CDU displays INVALID followed by an error code. The error code can be used to isolate the cause of system failure.

(8)  
Verify ENGAGE light is illuminated. Using BRT/DIM/TEST switch, check that ENGAGE light dims.

(9)  
With VALID self-test page, press ENGAGE key, and verify that:

(a)  
EPR command bugs drive to 2.40 EPR, then stow at 1.00 EPR.

(b)  
During slewing process, EPR bug flags retract, then return into view.

(c)  
On GJ ALL EXCEPT B-2509 and B-2510, target airspeed bug drives from 440 knots down to 110 knots then stows at 440.

(d)  
Mode annunciator unit legends illuminate sequentially, starting and ending with no display.

(e)  
During test, ENGAGE key light is extinguished, then illuminates when test is complete.

(10)
Open PDCS circuit breaker on P18 panel, and verify CDU screen blanks. After 20 seconds, close circuit breaker and verify CDU displays:

LOAD 1-2 OAT 0C ??? OAT 0F ????* D ELV ?????* RSV+ALT ????* ZFW ?????*

(11)
Press SEL (Select) and verify caret ( ) moves to next line. Repeat until caret returns to line two.

(12)
Press CLR (clear) and verify question marks disappear from lines two and three, and caret flashes.

(13)
Key in outside air temperature (OAT) of 150C. Verify caret still flashes. Press ENT (enter) and verify caret stops flashing and moves to fourth line. Verify third line indicates 590F computed from 150C entry.

(14)
Press CLR (clear), verify question marks disappear from line four and caret flashes. Key in destination elevation (D ELV) of 1100 feet. Verify caret still flashes. Press ENT (enter), verify caret stops flashing and moves to next line.

(15)
Repeat previous step to enter fuel reserves plus alternate fuel (RSV + ALT) of 3500 LBS, and zero fuel weight (ZFW) of 88,200 LBS. If weights in kilograms, enter 1600 KG for RSV

+ ALT and 40,000 KG for ZFW. All weights are displayed X1000.

(16)
Press forward PAGE and verify following:

5C8 
34-18-0 Page 502  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/88 

LOAD  2-2 
INDEX  XXX 
BELOW FL  100* 
MAX IAS  250*  (or NONE*) 
T/R ALT  1500* 

Where XXX is airline's INDEX number. Value of INDEX number may be changed using INDEX NUMBER switches on PDC front. Value of INDEX number set on PDC may be overridden using CDU keyboard.
5C8 
Jun 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-18-0 Page 503 

(17)
Press reverse PAGE and verify LOAD 1-2 displays.

(18)
Open PDCS circuit breaker on P18 panel for less than 5 seconds. Close circuit breaker and verify LOAD data is unchanged.

(19)
If system test is to be performed proceed to step 4.C. of system test. If system is not to be performed, proceed to Shutdown Procedures.

C.  Shutdown Procedures
(1)  
Pull command bug set knobs on EPR indicators to the out position.

CAUTION:  WITH THE PDCS INOPERATIVE OR TURNED OFF, SET EPR INDICATOR COMMAND BUGS TO MANUAL MODE OR EXCESSIVE WEAR TO THE COMMAND INDEX CLUTCH WILL OCCUR.

(2)  
Open PDCS and PDC MODE ANN circuit breakers on P18 panel.

(3)  
Circuit breakers associated with systems as specified in par. 3.A.(2) should be opened if no longer required.

(4)  
Move mode selector to STBY.

(5)  
Set all air conditioning and anti-ice system bleed air switches to off.

(6)  
Remove electrical power from airplane if no longer required.

4.  Performance Data Computer System Test
A.  Equipment and Materials
(1)  
Air pressure and vacuum source - 5-40 inches of mercury absolute, with adapter hose for connection to pitot head, and gage for measuring differential pressure

(2)  
Air pressure and vacuum source - 5-30 inches of mercury absolute with fittings for connection to static line test or drain fittings and gage for measuring static absolute pressure
　
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