(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 120% N1.
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(f)
Flight director (FD) pitch command bar on each ADI indicates a pitch up condition. (Pitch command bar above airplane symbol).
(g)
Glide slope pointer on each HSI indicates a vertical deviation of one dot (UP).
(h)
All throttle levers advance (in forward direction) at a rate of approximately 1./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 N1 tachometer indicator(s), to engage manual command mode.
2. System Test - Performance Management System
___________________________________________
A. General
(1)
The following procedure accomplishes a system test of the performance management system (PMS) and interfacing components. The system test provides a complete system checkout of the PMS and will normally be performed only at overhaul maintenance periods or when sufficient maintenance is accomplished as to leave the integrity of the total system in doubt.
(2)
The test procedure allows the testing of the entire performance management system including interface tests or it allows the performance of individual tests including:
(a)
PMS Control Display Unit (CDU) Test
(b)
Limit Indicator (LI) Test
(c)
Limit Select Panel (LSP) Test
(d)
Airplane Configuration and Software Part Number Verification
(e)
Inertial Navigation System (INS) Interface
(f)
Distance Measuring Equipment (DME) Interface
(g)
Low Range Radio Altimeter (LRRA) Interface
(h)
Air Data System Interface
(i)
Total Air Temperature (TAT) Probe Interface
(j)
Flap System Interface
(k)
Landing Gear System Interface
(l)
Wing Anti-Ice (WAI) System Interface
(m)
Fuel Flow (F/F) Indicating System Interface
(n)
Engine Pressure Ratio (EPR) Indicating System Interface
(o)
Engine Speed (N1) Indicating System Interface
(p)
Pneumatic Air Conditioning System Interface
(q)
Engine Bleed Air and Nacelle Anti-Ice Interface
(r)
PMS Select, Auto Throttle Engage, and Red/Amber warning.
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(3) The system installation, inspection and wiring continuity tests
shall have been completed, prior to performing these tests.
(4) Correct functioning of the following systems shall be confirmed
prior to performing this test.
(a) Electrical Power Distribution System
(b) Equipment Cooling System
(c) Instrument Dimming and Master Dim/Test Lighting System
(5) Proper completion of this test specification requires accurate
knowledge of airplane test location position expressed in degrees
and arc-minutes accurate to 0.1 arc-minutes of latitude.
(6) Proper completion of this test also requires that the following
systems or components be operational during the test.
CAUTION: ALL THE SAFETY PRECAUTIONS/WARNINGS REQUIRED TO BE_______
OBSERVED DURING OPERATION OF THE FOLLOWING AIRPLANE
SYSTEMS MUST BE ADHERED TO IN ORDER TO PREVENT DAMAGE
TO TEST EQUIPMENT, AIRPLANE SYSTEMS AND INJURIES TO
PERSONNEL.
(a) Autopilot/Flight Director Pitch Channel
(b) Auto Throttle System
(c) Central Air Data Computer System
(d) Air Data Pressure Instruments
(e) Low Range Radio Altimeter
(f) Inertial Navigation System
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航4(144)
