TM 1-1520-238-10 3-62 Change 4 3. The on command test GO/NO-GO self test can be initiated any time the FDLS page is dis- played. It is not necessary to wait for an FDLS error message to be displayed before pressing the FDLS FAB to display the FDLS page. The GO/NO-GO self test is comprised of the follow- ing internal tests: a. PROM Check sum verification. b. RAM read/write test. c. Limited non-volatile memory retention check. d. Display hardware BIT. e. 1553B terminal BIT. 4. Initiate the On Command test as follows: a. TEST – Press. Observe that DNS SYSTEM TEST IN PROG is displayed until the test is complete and data is available for DNS test status. The GO or NO-GO status is then dis- played. The following is a list of possible NO-GO messages: (1) PITCH/ROLL FAIL (2) HDG or A.C. REF FAIL (3) SDCC PWR SUPPLY FAIL (4) SDCC CPU/MEMORY FAIL (5) SDCC WRAPAROUND FAIL (6) SDCC A/D FAIL (7) SDCC 1553 I/O FAIL (8) SDC FAIL (9) RTA FAIL (10) SDCC CMD FAIL If no failures are detected, the CDU displays the FDLS page as shown in figure 3-24. M01-218-18 TEST CDU / DNS GO END OF TEST H P R 120.0 005.0 000.5 Figure 3-24. FDLS Status Page – On-Command Test Results NOTE The heading, pitch and roll values are calcu- lated and displayed no more than five sec- onds after the GO message. b. NAV FAB – Press. Observe that the NAV top level present position page is displayed. 3.15.6 Stopping Procedures. 1. ADMIN – Press. Observe that the ADMIN page is displayed. 2. PWR ON – Press. Observe that PWR ON changes to PWR OFF. 3.16 INTEGRATED NAVIGATION SYSTEM NOTE The integrated navigation system (EGI) does not meet US ARMY require- ments to fly FAA approved GPS ap- proaches. All data contained paragraph 3.16 through paragraph 3.16.15 is applica- ble to FCC software only. The Integrated Navigation System is a software module in the FCC that uses data from all of the navigation sensors. The data for the Navigation System comes from the Em- bedded GPS Inertial (EGI) sensor, a five–channel GPS re- ceiver, the AN/ASN–137 Doppler Navigation System, the Heading Attitude Reference System and the Fire Control Computer. The Navigation System software resides in the FCC only. In the event of an FCC failure, the helicopter will automatically configure to the Non–Integrated Navigation System as described in paragraph 3.14, with the BBC as the bus controller.