EFFECTIVITY AIRPLANES WITH PMS

704 Page 106
34-62-00
Dec 25/82
 PERFORMANCE MANAGEMENT SYSTEM - ADJUSTMENT/TEST
_______________________________________________
 1. Operational Test - Performance Management System
________________________________________________
 A. General
 (1)  
The operational test of the performance management system (PMS) is similar to the preflight procedure used to prepare a PMS for flight. This test requires no special tools.

 (2)  
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)  
Central Air Data Computer System

 (c)  
Low Range Radio Altimeter

 (d)  
Inertial Navigation System

 (3)  
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.

 (4)  
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.

 (5)  
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.

 (6)  
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.

 B. Reference Procedures
 (1)  
21-58-00, Rack Mounted Equipment Cooling System Blower

 (2)  
24-22-00, Manual Control - Maintenance Practices (Apply Power)

 EFFECTIVITY
 AIRPLANES WITH PMS    03 Page 501  Aug 25/85

34-62-00
 (3)  
33-11-00, Pilots Panel Lights

 (4)  
34-41-00, Inertial Navigation System

 C. Prepare for Test
 (1)  
Set the altitude selector on the autopilot flight director mode select panel (A/P-F/D MSP) to zero altitude.

 (2)  
On the A/P-F/D MSP, place the AUTOPILOT ENGAGE switch to the OFF position.

 (3)  
Ensure that the TURB/SPEED switch on the A/P-F/D MSP is not in the PMS position.

 (4)  
Provide electrical power. Refer to 24-22-00.

 (5)  
Check for proper operation of pilots' panel illumination, indicator lamps and annunciator lights using master test and dim control. Refer to 33-11-00.

 (6)  
Provide cooling air to electronic equipment. Refer to 21-58-00.

 CAUTION: ENSURE EQUIPMENT COOLING IS OPERATING BEFORE TURN ON OF
_______ ELECTRONIC SYSTEMS, OR DAMAGE TO EQUIPMENT MAY RESULT. EQUIPMENT COOLING SYSTEM MUST BE SET FOR NORMAL COOLING AS DESCRIBED IN 21-58-00.
 (7)  Provide cooling air to INS equipment. Refer to 21-58-00.
 CAUTION: ENSURE THAT COOLING AIR IS AVAILABLE TO INS NAVIGATION
_______ UNITS BEFORE OPERATING INS. FAILURE TO PROVIDE ADEQUATE AIR SUPPLY WILL RESULT IN FAILURE OF INS NAVIGATION UNITS.
 (8)  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.
 NOTE: If the INS has been in the NAV mode, cycle the INS through
____ the STANDBY back to ALIGN and reload present position.
　
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