(4)  
Initial Data Insertion Test

(a)  Present Position
1)  Turn DSS to POS. The CDU left display shall read 211 and right display shall show 30 XX (X's represent RPU software number).
NOTE:  Airplanes with E-FIELD antennas (ADF sense) may have RPU's with software number 30 03 or 30 04. Airplanes with H-FIELD antennas use RPU's with software number 30 04 only.
2)  Press either N2 for north latitudes or S8 for south latitudes. The left display will blank except for the last digit which will show either N or S. Using the keyboard enter the present latitude in degrees, minutes, tenths of minutes.
3)  Verify that display is correct and press ENT button.
4)  Enter longitude starting with either E or W, verify correct entry, and press ENT button.
5)  DR will turn on and ENT button will remain on.
5C8 
Jun 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-59-01 Page 503 

(b)  Time and data entry 1) Turn DSS to GMT DAT. Press GMT/L7 button on the keyboard. Verify that the left display blanks. 2) Insert Greenwich Mean Time in hours and minutes (for example: 23 hours 41
minutes is inserted as 2341). Press ENT button. It will remain on. 3) Press DAT/R9 button on the keyboard; verify that the right display blanks 4) Enter the current date by inserting the day (one or two digits), month (two digits)
and they year (two digits only). For example: Feb. 1, 1979 = 10279. 5) Verify entry is correct then press ENT button. The WRN annunciator shall turn off.
(5)  OMEGA Stations Status Check
(a)  
Turn DSS to DTK STS. Observe the system status number in the CDU right display. System status of 01 should occur within 8 minutes of entering present position. System alignment sequence is indicated below:

Status Code 90 System turn on until present position is entered. 80 RPU coming up to temperature (3 minutes minimum. 60 RPU synchronizing with received signals (up to 3 minutes). 30 RPU selecting Omega transmitters (0.5 to 1.5 minutes). 03 Dead Reckoning mode (up to 0.5 minutes). 02 VLF Navigation Mode 01 Navigation Mode

(b)  
Turn DSS to STA. The CDU shall display a sequence of digits representing the status of the Omega stations. Verify that a minimum of 3 stations are available for use.

CDU Display Station Status Steady Non-zero Digit Station is presently being used Flashing Non-zero digit Station is available, but not being used Steady Zero Station deselected by system Flashing Zero Station deselected by operator
(6)  
Check Heading Input

(a)  
Set DSS to MH/TAS

(b)  
Check that heading indicated by CDU left display is within 1 degree of the heading indicated by the Captain's RMI.

(7) 
 Check Airspeed Input

(a)  
Connect pitot-static test set to airplane pitot-static system.

NOTE:  Any pressure change shall be made such that the rate of climb or descent shall be less than 3,000 ft/min for the static system and 300 knots for the pitot system. Pitot line pressure shall always equal or exceed static line pressure and the difference shall never exceed 10 inches of mercury.

(b)  
Slowly apply pressure to the pitot-static system and monitor the pressure increase on the Mach/IAS indicator until 250 knots is indicated and is stable.

(c)  
Allow CDU display to stabilize. Right display shall read between 244 and 256.

(8)  
Check Autopilot Steering

(a)  
Engage the autopilot and select NAV mode on the autopilot controller.

(b)  
Turn DGS to AUX and WPT selector to 9.

(c)  
Set OFF-A-M-R switch to A. Control wheels shall roll to the left (300 left roll command).

(d)  
Set OFF-A-M-R switch to M. Control wheels shall return to center position (00 roll command)

(e)  
Set OFF-A-M-R switch to R. Control wheels shall roll to the right (300 right roll command).

(f)  
Return OFF-A-M-R switch to M. Disengage autopilot.

5C8 
34-59-01 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/85 

D.  Shutdown Procedure
(1)  
Turn OFF-A-M-R switch to OFF

(2)  
On GJ B-2501 thru B-2505, turn ADF No. 1 mode switch to OFF.

(3)  
Remove pitot static test equipment.

(4)  
Open circuit breakers in step B.(3)

(5)  
Turn off electrical power if no longer required

(6)  
Shut down APU if no longer required

5C8 
Jun 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-59-01 Page 505 
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 導航 NAVIGATION 2(108)