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 (g) DME System
 (h) Engine Related Systems
 1) Engine Nacelle Thermal Anti-Icing.
 2) Engine Bleed Air Distribution System
 3) Fuel Flow Indicating System
 4) Engine Pressure Ratio (EPR) Indicating System
 5) Engine Tachometer System
 (i) Airframe Related Systems
 1) Air Cycle Pack System
 2) Triple-Slotted Trailing Edge Flap System
 3) Leading Edge Flap System
 (7)  All the systems and components that are operational during this
 test should be maintained at their normal operating conditions with
 the airplane on the ground, unless otherwise specified.
 (8)  The PMS monitors data and discretes from the interfacing systems,
 therefore these systems should be turned on before the PMS is
 turned on to avoid false malfunction codes.
 (9)  During the test procedures, under certain conditions it is possible
 that the PMS will generate malfunction codes and/or illuminate
 warn annunciators due to abnormal conditions. The warn and
 malfunction codes can be reset by setting the abnormal condition
 to normal and then repeatedly pressing the STS/TEST key on the PMS
 CDU until all malfunction codes are cleared.

 EFFECTIVITY

 AIRPLANES WITH PMS    07 Page 515  Apr 25/89

34-62-00
 (10)
 During the test procedures, the test conditions are verified on the control display unit (CDU) and/or on the limit indicator (LI) displays. The test procedures may show that a character 'X' is displayed. The 'X' indicates that the display on the CDU, or on the LI, could be any number/alphabet/symbol at this location and is not related to the test being performed.

 (11)
 For the PMS to be coupled with the autopilot or with the throttle system; the radio altitude must be above 2500 feet, a PMS limit mode must be selected (except take-off), and the INS must be in the ALIGN or NAV mode. Further, for PMS coupling with the throttle system; airplane gross weight must be entered into the PMS, and the flaps must be retracted to the full up position.

 (12)
 Gross weight must be entered into the PMS.  Lack of gross weight entry will cause the PMS CDU to display a 'PMS INHIBITED' message on the STS (status) page. In addition, lack of gross weight will cause a 'CHK GWT' message to appear in the title line of all PMS pages, and will also inhibit PMS coupling with the throttle system. When gross weight is entered into the PMS, and the PMS mode is selected (TURB/SPEED switch at PMS position), and fuel flow is zero; the 'CHK GWT' message will appear on all PMS pages. Under these conditions ignore the message unless a specified observation is required.

 (13)
 On airplanes with PMS command EPR (or N1) on pilot's EPR (or N1) indicator(s), if the command set knob on these indicator(s) is pushed-in for automatic command mode, when the PMS computer is without 115 volts ac power; the command index and counter on the indicator(s) will drive to full scale, causing wear on indicator servo mechanism. To prevent unnecessary wear on the indicator(s), pull-out indicator set knob to engage manual command mode.

 (14)
 The Prepare For Test procedure must be completed before the system test can be accomplished. However, the Prepare For Test procedure does not need to be repeated for each test if two or more tests are to be performed in sequence.

 (15)
 At the completion of the test(s) restore airplane to normal.

 B. Equipment and Materials
 (1)  
Cards containing airplane present position and waypoint information.

 (2)  
Pneumatic Test Unit (Refer to 34-11-00).

 (3)  
DME Ramp Test Set (Refer to 34-55-00).

 (4)  
Radio Altimeter Test Set Model Numbers:---- Bendix, AMT 5IA; Collins, 980N-1; TRT, AHV3/018; Honeywell, UG2559AB with calibration unit UG2926AA (as applicable).

 NOTE: Two Radio Altimeter test sets are required.
____
 C. Referenced Procedures
 (1)  
21-00-00, Air Conditioning

 (2)  
21-58-00, Rack-Mounted Equipment Cooling System

 (3)  
22-31-00, Auto Throttle System.

 (4)  
24-22-00, Manual Control (Electrical Power).

 EFFECTIVITY
 AIRPLANES WITH PMS    07 Page 516  Apr 25/89

34-62-00
 (5)  
27-51-00, Triple-Slotted Trailing Edge Flap System

 (6)  
27-81-00, Leading Edge Flap System

 (7)  
30-11-00, Wing Thermal Anti-Icing

 (8)  
30-21-00, Engine Nacelle Thermal Anti-Icing.
　
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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(145)