(10)
Push-in the command set knob on N1 tachometer indicator(s), to engage automatic command mode.
(11)
Position all engine throttle levers to the forward limit.
(12)
Press the PMS CDU STS/TEST key. Press the CDU line select 1 key, verify the key illuminates.
(13)
Press and hold the PMS CDU STS/TEST key and verify the following:
(a) VERT ALERT (amber) annunciator on the pilot's panels illuminate.
EFFECTIVITY
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(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).
(h)
All throttle levers retard (in aft direction) at a rate of approximately 1.8./second.
(14)
Release the CDU STS/TEST key.
(15)
Verify that the glide slope pointer on each HSI is biased out of view.
(16)
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
(17) Position the throttle levers to the aft limit.
M. Throttle Advance and Pitch Up Command (IB Airplanes)
(1)
Ensure that all engines are not operating.
(2)
Ensure that the trailing edge (TE) flaps and the leading edge (LE) flaps are retracted to the full up position.
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.
(3)
Open LRRA-1 and LRRA-2 system circuit breakers to simulate a radio altitude above 2500 feet, on LRRA-1 and LRRA-2 respectively.
(4)
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.
(5)
Ensure that gross weight of airplane is entered into the PMS.
(6)
Select CRZ limit mode on the PMS limit select panel (LSP). Verify that the PMS limit indicator (LI) displays CRZ and some value of EPR limit (no dashes or blank display) indicating a valid EPR limit condition.
(7)
Verify that the Captain's and F/O's FLT DIR CMPTR select switches are set to 'A'.
EFFECTIVITY
AIRPLANES WITH PMS 10 Page 511 Apr 25/89 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航4(142)
