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D.  Because the antenna is not an easily substitutable unit, temporary taping of a known-good antenna to the airplane skin and using a cable external to the airplane should be used prior to actual replacement of the antenna.
2.  Prepare for Trouble Shooting
A.  Provide airplane electrical power from APU and verify that external power cord is disconnected from airplane.
NOTE:  With electrical power provided from the APU and when either one or both electrical hydraulic pumps are turned on, the CDU would change to display status code 60; this condition is considered normal. Airplane parking ramps which contain a large amount of metal can reduce signal levels. Electrical interference can be induced into the airplane through the external power cord.
B.  Check that electronic equipment cooling blower is operating.
C.  Check that the following systems are on and operating normally, COMPASS No. 1, AIR DATA COMPUTER No. 1, and on GJ B-2501 thru B-2505 ADF No. 1.
D.  Perform listed procedure for applicable fault in the following trouble shooting chart. Substitute known serviceable units for indicated component then recheck. If substitution of components does not correct fault check system wiring using wiring diagram manual.
E.  Close OMEGA NAV circuit breaker and select CDU OFF/ON switch to ON.
F.  Enter present position, GMT, and date (Ref D&O). System will synchronize in approximately five minutes.
5C8 
Oct 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-59-01 Page 101 

 

TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
No CDU displays illuminate when system is ON CDU display is faulty is during self-test BITE indicator on RPU is set CDU WRN annunciator is steadily illuminated CDU WRN annunciator flashes  CDU or RPU CDU RPU RPU RPU Multiple inputs selected  RPU, ADF antenna coupler 1 or antenna  Check APU power supply monitor lights Check for 28V DC power to the CDU across pins A and B of connector D1555 If CDU receiving power If CDU not receiving power Set display selector switch to DSTK STS and note action code. Press HOLD key and note malfunction code is: 01,02,03,04, or 05 06 07  Replace CDU Replace RPU Replace CDU Replace RPU Replace RPU Replace RPU Check wiring of pin 15 on connector D1559A at RPU for correct wiring. If OK, replace RPU Replace RPU. If not OK,  1 Replace ADF antenna coupler 1 ADF antenna 2 H-FIELD ACU 
 GJ B-2501 thru B-2505

 

 GJ ALL EXCEPT B-2501 thru B-2505
5C8 34-59-01 Jun 20/85 Page 102
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
No airspeed input No heading input No airspeed or heading input Power Interrupt RPU will not synchronize RPU Antenna Missing parameters  10 11 12 13 14; Place display selector switch to DSTK STS and check display for station status If display indicates 3 or more, steady nonzero digits If display indicates 3 or more, steady nonzero digits, check that airplane is away from large amounts of metal and external power cord is not being used 15  Provide airspeed input Provide heading input Provide airspeed and heading input Enter GMT Replace RPU Replace antenna Enter present position, GMT, and/or date 

554 
May 15/79  34-59-01 
Page 103 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5C8 
34-59-01 Page 104  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/85 

 

OMEGA NAVIGATION SYSTEM - ADJUSTMENT/TEST
1.  OMEGA System Test
A.  Equipment and Material
(1)  
Portable pressure equipment to simulate 0 to 400 knots airspeed

(2)  
Pitot Static Probe Adapter - Allen Aircraft Radio Inc. P/N PSS 22300-4( )-( )

B.  Prepare to Test OMEGA System.
(1)  
Connect pitot static test equipment to airplane systems (Ref 34-11-0).

CAUTION:  OBSERVE CAUTIONS LISTED IN 34-11-0 FOR APPLICATION AND REMOVAL OF PITOT STATIC PRESSURES. EXCESSIVE RATES AND PRESSURES MAY DAMAGE EQUIPMENT.

(2)  
Provide airplane electrical power from APU, disconnect external power cord and energize buses on P6 and P18 panels.

NOTE:  With electrical power provided from the APU and when either one or both electrical hydraulic pumps are turned on, the CDU would change to display status code 60; this condition is considered normal.
Airplane parking ramps which contain a large amount of metal can reduce signal levels. Electrical interference can be induced into the airplane through the external power cord.
　
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