(6)  
Slew each CDU display up until AP/FLT DIR #1 line is between entry line markers.

 (7)  
Press EXP pushbutton on each CDU.

 (8)  
Verify the following on each CDU display:

 T-DTK *[1] TK 22.5. XTK R 3.8. STR R .0.
 HDG 11.3. GS 450
 *[1] 49.7. on airplanes with LTN-72RL INS
 50.1. on airplanes with LTN-92 INS

 (9)  
Verify that the INS updating annunciators illuminate.

 (10)
 Verify the following on each HSI:

 (a)  
Compass card indicates 11.3. |1. when read against lubber line.

 (b)  
Desired track arrow indicates the following when read against compass card:

 49.7. |2 on airplanes with LTN-72RL INS 50.1. |2 on airplanes with LTN-92 INS

 (c)  
Drift angle marker indicates 11. |1.R.

 (d)  
Course deviation bar is 1 |0.2 dot left of airplane symbol.

 (e)  
MILES display reads 888.

 (f)  
Ground speed display reads 450,

 (g)  
Navigation warning flag is out of view.

 (h)  
Heading warning flag is out of view.

 (i)  
On airplanes with LTN-72RL INS,
 true heading annunciator is in view.
 On airplanes with LTN-92 INS,
 mag heading annunciator is in view.

 (11)
 Place INS transfer switch on captain's main insturment panel to CAPT 3 - F/O 2 position, and repeat step (8).

 (12)
 Place INS transfer switch to CAPT 1 - F/O 3 position, and repeat step (8).

 EFFECTIVITY
 AIRPLANES WITH LTN-72RL OR  CONFIG LTN-92 INS  01 Page 505  Apr 25/93

34-41-00
 (13)
 Press STS pushbutton on each CDU.

 (14)
 Return INS transfer switch to CAPT 1 - F/O 2 position.

 I. INS/ADI Attitude Interface Test
 (1)  
Ensure that present position coordinates are entered into each INS and that mode selector switch on each MSU is set to ALIGN. Verify that each INS is aligned to status 50 or a lower number.

 (2)  
On each ADI verify that attitude flag is out of view, and that attitude display is within one degree of airplane pitch attitude and within one degree of airplane roll attitude.

 (3)  
Place ATT/COMP STAB switch on captain's main instrument panel to CAPT 3 - F/O 2 position. Verify that captain's ADI attitude flag is out of view, and that attitude display is within one degree of airplane pitch attitude and within one degree of airplane roll attitude.

 (4)  
Place ATT/COMP STAB switch to CAPT 1- F/O 3 position. Verify that first officer's ADI attitude flag is out of view, and that attitude display is within one degree of airplane pitch attitude and within one degree of airplane roll attitude.

 (5)  
Return ATT/COMP STAB switch to CAPT 1 - F/O 2 position.

 J. Alignment Status Check.
 (1)  
Ensure that present position coordinates are entered into the INS and that mode selector switch on MSU is set to ALIGN.

 (2)  
To check INS alignment status press CDU STS pushbutton. Verify that SYS STS/TEST page appears on CDU display and that:

 (a)  The number on ALIGN line is the status number. (Status numbers start at 90 and decrement through 80, 70, 60, 50, 40, 10, and 2 as alignment sequence progress.)
 NOTE: The LTN-92 INS does not have status 40.
____
 (b)  The number on TIME line is minutes and tenths of minutes remaining in ALIGN.
 (3)  
On airplanes with LTN-72RL INS, verify that MSU READY NAV annunciator comes on when the INS aligns to status 2. On airplanes with LTN-92 INS, verify that MSU ALIGN annunciator goes out when the INS aligns to status 2.

 (4)  
On airplanes with LTN-72RL INS, when MSU READY NAV annunciator is on, place MSU mode selector switch to NAV, the READY NAV annunciator will go out. Verify that ALIGN line changes to NAV with a status number of 1, and TIME line changes to time in navigate mode. On airplanes with LTN-92 INS, when status 2 is reached, place MSU mode selector switch to NAV. Verify that ALIGN line changes to NAV with a status number of 1, TIME line changes to time in navigate mode, and the MSU ALIGN annunciator goes out.

 K. Restore Airplane to Normal
 EFFECTIVITY

 AIRPLANES WITH LTN-72RL OR  CONFIG LTN-92 INS  01 Page 506  Apr 25/93

34-41-00
 (1)  Place each INS mode selector switch in OFF POSITION.
 CAUTION: FAILURE TO MOVE MODE SELECTOR TO OFF WILL CAUSE INS TO
_______ AUTOMATICALLY SWITCH TO BATTERY POWER AND A WARNING HORN IN NOSE WHEEL WELL TO ACTUATE 30 |10 SECONDS AFTER POWER IS REMOVED FROM AIRPLANE.
　
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本文鏈接地址：747飛機(jī)維護(hù)手冊(cè)AMM CHAPTER 34 - NAVIGATION 第34章導(dǎo)航3(44)