(a) Present position coordinates are inserted only at the INS CDU. These coordinates may be loaded into the INS, when the INS is in either the PMS waypoint control mode or the INS waypoint control mode. The inertial position is used by the PMS during the INS ALIGN mode to verify proper ramp coordinates.
(7)
Loading Waypoints Defined by Latitude and Longitude Coordinates.
(a)
When the INS is in the PMS waypoint control mode, waypoints defined by latitude and longitude coordinates must be loaded at the PMS CDU.
(b)
One waypoint page (on the CDU display) is reserved for each of 36 possible waypoints. The pages are arranged in the sequence of waypoint numbers (1A through 9A, 1B through 9B, 1C through 9C, and 1D through 9D), which is the sequence that the waypoints will be used during flight.
(8)
Loading Waypoints Defined by Radio Navigation Stations.
(a) A waypoint, usually defined by latitude and longitude coordinates can also be located in terms of a range (in nautical miles) and bearing (in degrees) from a VORTAC radio navigation station. Using VORTAC station locations from a list of radio-navigation data within its memory, the PMS computer can redefine such range/bearing information to obtain normal latitude/longitude coordinates for the waypoint. The range in nautical miles and the bearing in degrees, are loaded through the PMS CDU. However, the correct VORTAC station data must first be loaded into the computer memory, and the PMS must have waypoint control.
(9)
Loading DME Data
(a) Navigation aid data, including VORTAC station frequency, latitude, longitude, magnetic variation, and elevation must be loaded through the PMS CDU into the PMS computer unit. This data once loaded, remains in the computer memory until reloaded.
(10)
Displaying Performance Data
EFFECTIVITY
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(a) Performance data pages (on the CDU) are used to display fuel flow, N1 percent RPM (and EPR on airplanes with PW engines), anti-ice and air conditioning operation, airspeed, altitude and ambient air data, flap position, and DME slant range; as provided to the PMS computer unit. Such data is useful for engine performance monitoring.
(11)
Navigation Data
(a) Navigation information is displayed on the PMS CDU using the PMS Nav Data pages. The navigation information includes; heading, desired track angle, drift angle, cross track distance, FROM/TO waypoints, ground speed, wind, and INS present position.
(12)
PMS Mode of Operation - Engagement of Vertical Steering and Thrust Commands.
(a)
The PMS mode of operation is selected at the A/P-F/D mode select panel, by placing the TURB/SPEED switch to the PMS position.
(b)
When the PMS mode of operation is selected; placing the AUTOPILOT ENGAGE switch to COMMAND (CMD) and/or placing the FLT DIR switch to ON, causes the A/P-F/D pitch computers to receive vertical (pitch) steering from the PMS. Also, when the PMS mode is selected; placing the auto throttle engage switch to ON causes the throttle servomotor to receive thrust commands from the PMS.
(c)
Before the PMS mode of operation can be selected, a PMS limit mode must first be selected (except take-off), the INS must also be in the ALIGN or NAV mode, and the radio altitude must be above 2500 feet. (If the PMS mode of operation is inhibited, the PMS cannot be coupled with the A/P-F/D or with the throttle servomotor.) However, when the PMS mode of operation is selected (TURB/SPEED switch to PMS), airplane gross weight must be entered into the PMS and the flaps must be retracted to the full up position; before attempting to place the auto throttle engage switch to the ON (engaged) position. (If gross weight is not entered, and if flaps are not full up; the auto throttle engage switch will not be retained in the engaged position).
NOTE: When the PMS mode of operation is selected, and
____ airplane gross weight is entered into the PMS; zero fuel flow will cause a 'CHK GWT' message to appear on all PMS pages.
(d)
When the PMS is engaged to provide vertical steering to the A/P-F/D, and thrust commands to the throttle servomotor; the PMS will normally maintain motions in progress at the time of engagement. For example, if the airplane is climbing the PMS continues the climb at the same rate. If conditions for climb mode operation are present the PMS then eases into the preselected climb.
(e)
Couple PMS with A/P-F/D and Throttle Servomotor.
EFFECTIVITY
AIRPLANES WITH PMS 02 Page 65 Aug 25/83 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 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(134)
