Aug 8, explanation of the Honeywell EGPWS. It contains a general What is the. EGPWS? The EGPWS is a Terrain Awareness and Alerting system. Oct 29, Altitude Correction, EGPWS Suppress and Glideslope Cancel Enhanced Ground Proximity Warning System (EGPWS), VAC. Jul 22, Honeywell Aerospace Electronic Systems. SYSTEM INSTALLATION MANUAL. MK XXI Helicopter EGPWS. DWD NO: MK XXI.
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Feb 23, Updated document to include MK XXII helicopter EGPWS and to include software changes for RAAS and newly introduced optional. Jun 13, Honeywell complies with RTCA/DOA and AC B for its processing of terrain and obstacle data in support of Synthetic Vision / IPFD. EGPWS Features. 1. Obstacles Database - Visual and aural alerts for flight into obstacles, i.e. towers. 2. Peaks Mode - Displays high terrain that is more than.
Two sub- approaches.
Two levels of alerting are provided. If modes, referred to as Mode 2A and 2B are defined.
EGPWS cockpit alert annunciations remain illuminated until the alert envelope is exited. The The menu selected advisory callouts are defined and database provides the means of accessing the records enabled in the installation configuration.
Only rural of runways closest to the current aircraft position. Terrain Alerting and Display Excessive bank Angle call out The bank angle callout feature provides callout The Terrain Alerting and Display TAD function annunciation for excessive bank angles based on monitors aircraft position with respect to local database cataloged terrain to provide rapid audio and altitude and bank angle limits defined by aircraft visual alerts when a terrain threat is detected.
Terrain type. It is intended to enhance situational awareness threats are recognized and annunciated when terrain during intentional or unintentional maneuvering and for protection against wing or engine strikes when violates specific computed envelope boundaries close to the runway.
The terrain database also includes obstacles when and where available Terrain Clearance Floor and Runway Field providing similar annunciations when cataloged Clearance Floor obstacles violate the same envelope boundaries.
It Either caution or warning alerts will initiate a specific creates an increasing terrain clearance envelope audio alert phrase. TCF also maintains a synthetic image of local terrain complements the existing Mode 4 protection by forward of the aircraft for display on Weather Radar providing an alert based on insufficient terrain Indicator. Generally all basic system occur near an airport, and the fact that aircraft operate suggested by Honeywell is being implemented and in closer proximity to terrain near an airport, higher scope exists for connection of stall warning system, resolution grids are used around airports.
Lower wiper system and decision height option in radio resolution grids are used outside of airport areas altimeter with enhanced ground proximity warning where aircraft altitude en route makes CFIT accidents system. In above diagram optional pin number 36 of unlikely and for which detailed terrain features are Enhanced Ground proximity warning computer has not important to the flight crew.
In recommended as a optional mode 6 low volume. The decision height option and same can be connected to process of acquiring, generating, assembling, and radio altimeter indicator.
Explanation of stall warning updating the database is governed by strict system, wiper system and radio altimeter system configuration controls to insure the highest level of installed on a multipurpose aircraft used for data integrity for generation of the EGPWS Terrain patrolling is given below Data base.
The Obstacle Database is a separate file included within the terrain database. The obstacle database is accessed by  a Stall Warning System The stall warning the EGPWC application software only if obstacle system is very important system for aircraft. The alerting is enabled by installation configuration. The main component of stall warning system is: I Lift Transducer ii Lift Computer iii Reference speed deviation indicator IV Flap Position Transmitter v Stall Warning Lamp and Horn System Operation The purpose of stall warning system is to give an audio and visual warning in cockpit in case aircraft losses its speed.
The lift transducer is fitted on the left wing and is electrically heated to prevent icing. If the left piton de-ice switch is switched on , when the Airplane is on the ground, a reduced voltage is Fig -2 EGPWS system connection diagram supplied to the lift transducer heater via resistor 3FW to prevent overheating, when the Airplane leaves the Typical block diagram developed by Honeywell is ground the right main landing gear switch 15 GA shown above.
EGPWS computer is the heart of the closes and completes the ground circuit for the coil of system. The relay energizes and its contacts computer.
The installation configuration is defined in shorts the resistor 3FW allowing the full 28V to a programmed configuration module installed in supply the transducer heater.
The flap position shaft by the gearboxes. When the switch is set to transmitter is connected to the flaps and supplies a OFF, the wiper will stop. Pushing the switch to signal to the lift computer depending upon the PARK energizes relay 7ME and applies 28V to the position of flaps.
The signals from the lift transducer motor via contacts B2-B1 and resistor 4ME. Contacts and flap position transmitter are supplied to the lift A2-A1 connects ground to the motor. The motor runs computer where they are processed in to a reference and when the motor PARK position is reached, the speed signal for the RSD indicator.
During flight the built in switch closes and shorts the armature, RSD indicator pointer may be anywhere between stopping the motor. If the Airplane speed deviates into the slow range, the lift Technical Data Wiper Motor computer supplies a discrete signal to illuminate the Type series wound stall warning lamp and sound the stall warning horn from pin M of lift computer.
Supply 28V DC The line diagram of stall warning system is shown as fig 1. Same pin is proposed to be connected to stall warning system. Power 92 W Wiper System  during heavy rains in order to Speed rpm have a clear vision through Aircraft canopy for pilot, Weight 1.
Wipers blades, wiper Motor, Relay and wiper switch Gearbox reduction ratio are the main components of Wiper system. Pin is grounded and hence motor. The wiper motor provides the drive for the normal volume is being heard during flying for windshield wipers.
This volume is just not sufficient motor and the airframe ensures a good ground for pilot during wiper motor operation. In order to connection. The motor is series wound and consists enhance the volume for EGPWS Warning during of a suppressor, thermal overload protection and a wiper motor operation, a 28V DC must be provided parking switch. They system switch. A resistor is located on Radio Altimeter System Presently most of aircraft relay support and is converted in series with the is fitted with radio altimeter.
As the name implies, motor when the wiper switch is set to PARK. Both these altimeter tells Enhanced Ground Proximity Warning System is the aircraft height with respect to mean sea level.
Radio altimeter tells height of aircraft controlled flight in to terrain. This change to the Mode 4 en- velopes further reduces the potential for nuisance alerts when the aircraft is not in the landing conguration.
Several Mode 4 alert envelope variations are dened as an option in the installation conguration. In the following Mode 4 discus- sions, the most common limits are provided with the alternates identied in parenthesis. For a specic application, refer to the installation documentation to obtain the dened conguration. This provides alerting during cruise for inadvertent ight into ter- rain where terrain is not rising signicantly, or the aircraft is not descending excessively.
It also provides alerting for protection against an unintentional gear-up landing. The airspeed limit is knots if the alternate airspeed conguration has been selected, and it is knots for turbofan bizjet aircraft.
If the alternate airspeed congura- tion has been selected, the slope begins at knots and ends at knots and feet AGL. For turbofan bizjet aircraft, the slope begins at knots and ends at knots and feet AGL. Unsafe terrain clearance gear up turboprop Rev. If the alternate airspeed conguration has been selected, the boundary is feet AGL and the airspeed limit is knots.
For turbofan bizjet aircraft, the boundary is feet AGL and its airspeed limit is knots. See following graphs Rev. This precludes or silences the Mode 4B ap alert until reset by the pilot. MODE 4C The Mode 4C alert is intended to prevent inadvertent controlled ight into the ground during takeoff climb into terrain that pro- duces insufcient closure rate for a Mode 2 alert.