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(10)
Place the Captain's and F/O's VOR-ILS/INS switches (on the P10 panel) to the INS position.
(11)
Push-in the command set knob on EPR indicator(s), to engage
automatic command mode.
(12)
Position all engine throttle levers to the forward limit.
(13)
Press the PMS CDU STS/TEST key. Press the CDU line select 1 key, verify the key illuminates.
(14)
Press and hold the PMS CDU STS/TEST key and verify the following:
(a)
VERT ALERT (amber) annunciator on the pilot's panels illuminate.
(b)
PMS (amber) annunciator on the pilot's center instrument panel illuminates.
(c)
A/T (amber) annunciator illuminates (steady), on each FMA.
(d)
On airplanes incorporating SB 34-2193, PATH ARM (amber), PATH (green), SPD ARM (amber), SPEED (green) and T/HOLD (green) annunciators illuminate, on each PMS mode annunciator module (P72 panel).
(e)
On each EPR indicator; the EPR command index and EPR command counter, display an EPR command of 1.20 EPR.
(f)
Flight director (FD) pitch command bar on each ADI indicates a pitch down condition. (Pitch command bar below airplane symbol).
(g)
On airplanes incorporating SB 34-2193, glide slope pointer on each HSI indicates a vertical deviation of one dot (DOWN).
(h)
All throttle levers retard (in aft direction) at a rate of approximately 1.8./second.
(15)
Release the CDU STS/TEST key.
(16)
Verify that the glide slope pointer on each HSI is biased out of view.
(17)
Return the following switches on the A/P-F/D MSP to the positions shown.
Captain's and F/O's FLT DIR switches to OFF
TURB/SPEED switch to OFF
A/T Engage switch to OFF
(18)
Position the throttle levers to the aft limit.
(19)
Pull-out the command set knob on EPR indicator(s), to engage manual command mode.
(20) If the PMS is no longer required, restore airplane to normal. AN. Throttle Retard and Pitch Down Command (AF Airplanes).
(1)
If required prepare for test as described in paragraph D.
(2)
Ensure that all engines are not operating.
EFFECTIVITY
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(3)
Ensure that the trailing edge (TE) flaps and the leading edge (LE) flaps are retracted to the full up position.
(10)
Place the Captain's and F/O's VOR-ILS/INS switches (on the P10 panel) to the INS position.
(11)
Push-in the command set knob on N1 tachometer indicator(s), to engage automatic command mode.
(12)
Position all engine throttle levers to the forward limit.
(13)
Press the PMS CDU STS/TEST key. Press the CDU line select 1 key, verify the key illuminates.
(14)
Press and hold the PMS CDU STS/TEST key and verify the following:
(a)
VERT ALERT (amber) annunciator on the pilot's panels illuminate.
(b)
PMS (amber) annunciator on the pilot's center instrument panel illuminates.
(c)
A/T (amber) annunciator illuminates (steady), on each FMA.
(d)
PATH ARM (amber), PATH (green), SPD ARM (amber), SPEED (green) and T/HOLD (green) annunciators illuminate, on each PMS mode annunciator module (P72 panel).
(e)
On each N1 tachometer indicator; the N1 command index and N1 command counter, display an N1 command of 90% N1.
(f)
Flight director (FD) pitch command bar on each ADI indicates a pitch down condition. (Pitch command bar below airplane symbol).
(g)
Glide slope pointer on each HSI indicates a vertical deviation of one dot (DOWN).
NOTE:____ For trailing edge flap operation refer to 27-51-00,
Maintenance Practices. For leading edge flap operation
refer to 27-81-00, Maintenance Practices).
(4) Open LRRA-1 and LRRA-2 system circuit breakers to simulate a
radio altitude above 2500 feet, on LRRA-1 and LRRA-2 respectively.
(5) Ensure that present position latitude and longitude coordinates
are entered into each INS (Refer to 34-41). Verify that the mode
selector switch, on each INS MSU, is set to ALIGN.
(6) Ensure that gross weight of airplane is entered into the PMS.
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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4(160)
