ASA eléctronicos

When must the emergency locator transmitter (ELT) battery be replace (other than reading the replacement date)?. When the transmitter has been in use for more than one cumulative hour. Must be replaced annually or if the five G switch has been activated. When the transmiter has been tested more than ten times.

An emergency locator transmitter (ELT) battery must be capable of furnishing power for signal transmission for at least. 48 hours. 72 hours. 36 hours.

An emergency locator transmitter (ELT) is normally activated by an inertial switch or equivalent mechanism if subjected to a force of a prescribed intensity and duration. It must activate when the force is applied. parallel to the longitudinal axis of the aircraft. paraller to the vertical axis of the aircraft. in any direction relative to the aircraft axis.

How may the battery replacement date be verifies for an emergency locator transmitter (ELT)?. By observing the battery replacement date marked on the outside of the transmitter. By activating the transmitter and measuring the signal strength. By removing the batteries and testing them under a measured load to determine if 50 percent of the useful kife remains.

The preferred location of an ELT is. as far aft as possible, but forward of the vertical fin. as far aft as possible. where it is readily accessible to the pilot or a member of the flight-crew while the aircraft is in flight.

How may the operation of an installed emergency locator transmitter (ELT) be verified during aircraft inspection?. By tuning a communications receiver to the civil emergency frequency and activating the ELT momentarily within five minutes after the hour. By moving the deactiviting switch from the DISARM position to the ARM position while monitoring the civil emergency frequency with a communications receiver at five minutes after the hour. By activating the 5 g switch and turning the unit on at five minutes after the hour.

Installed radio equipment is protected from damage due to jolts and vibration by. shock mounts. spring and/or vicsoud damper mounted racks. rubber of foam cushioning material between circuit chassis and case.

(1) Use solder to attach bonding jumpers on radio equipment. (2) Radio equipment is bonded to the aircraft in order to provide a low-impedance ground and to minimize radio interference from static electrical charges. Regarding the above statements. only No. 2 is true. only No. 1 is true. both No. 1 and No. 2 are true.

When must the radio station license be displayed in an aircraft equipped with a two-way radio?. When the aircraft is operated outside the U.S. When the aircraft is returned to service. When the aircraft is certified for IFR flight.

Part of the ADF system used on aircraft includes. sense and loop antennas. RMI indicator antenna. marker beacon antenna.

When installing coaxial cable, it should be secured firmly along its entire length. at 2-foot intervals. at 1-foot intervals. wherever the cable sags.

Static discharges help eliminate radio interference by dissipating static electricity into the atmosphere at. low current levels. high voltage level. high current level.

Long Range Navigation (LORAN) sistems fetermine aircraft location by. measuring the inertial acting on the aircraft. means of pulsed signals transmitted from ground stations. means of signals transmitted to and from navigation satellites.

An aircraft antenna installation must be grounded. to the airframe. to the engine. to the radio rack.

VHF radio signals are commonly used in. both VOR navigation and ATC communications. ATC communications. VOR navigation.

On modern large aircraft, what electronic device parameters and performs autopilot functions?. Flight management computer. Transponder. Control/display unit.

In the landing configuration GPWS typically monitor the radio (radar) altimeter; air data computer; instrument landing system; and. landing gear and flap positions. aileron, rudder, and elevator positions. spoiler, slat and stabilizer positions.

In general, the purpose of an aircraft transponder is to. receive an interrogation signal from a ground station and automatically send a reply back. continually transmit heading, speed, and rate of climb/decent etc. information to ATC. monitor aircraft speed, heading, altitude, and attitude whenever the autopilot system is engaged.

When an antenna is installed, it should be fastened. so that loads imposed are transmitted to the aircraft structure. to the primary strucutre at the approximate intersection of the three aircraft axes. with a reinforcing doubler on each side of the aircfrat skin.

After an automatic direction finding antenna has been installed, the. loop must be calibrated. antenna must be grounded. transceiver must be compesated.

Doublers are used when antennas are installed to. reinstate the structural strength of the aircraft skin. eliminate antenna vibration. transceiver the structural trength of the aircraft skin.

One antenna can be used for the radio range and standard broadcast bands in light aircraft because the. two ranges are close together. antenna is omnidirectional. antenna length may be electronically adjusted.

What characteristics of the installation of a rigid antenna on a vertical stabilizer should be evaluated?. Flutter and vibration. Polarization and impedance. Impedance and interference.

A gasket or sealant is used between the antenna mast and fuselage skin. to prevent the entry of moisture. for aircraft pressurization only. to prevent abrasion between the antenna mast and fuselage skin.

The preferred location of a VOR antenna on light aircraft is on. top of the cabin with the apex of the V pointing forward. the bottom of the fuselage and as far forward as possible. top of the vertical stabilizer.

(Refer to figure 1) What is the appproximate drag load on an antenna with frontal area of .125 square feet installed on an aircfrat with a speed of 275 MPH?. 2.069 pounds. 2.073 pounds. 2.080 pounds.

(Refer to figure 1) What is the appproximate drag load on an antenna with frontal area of .137 square feet installed on an aircfrat with a speed of 275 MPH?. 3.387 pounds. 3.741 pounds. 3.592 pounds.

A DME antenna should be located in a position on the aircraft that will. not be blanked by the wing when the aircraft is banked. permit interrptions in DME operation. eliminate the possibility of the DME locking on a station.

When installing a DME antenna, it should be aligned with the. centerline on the airplane. null position. angle of incidence.

(Refer to figure 2) which of the antennas shown is a typical DME antenna?. 1. 2. 4.

(Refer to figure 2) which of the antennas shown is a typical glideslope antenna?. 2. 3. 4.

The addition of avionics and associated antenna systems forward of the CG limit will affect. empty weight and useful load. CG limits and useful load. useful load and maximum gross weight.

How much clearance from the seat bottom is required when installing radio equipment under a seat?. 1 inch with the seat occupied and subjected to maximum downward seat spring deflection. 3 inches with the seat unoccupied. No set minimum as long as the equipment receives adequate cooling and damage protection.

The purpose of a glideslope system is to. assist the pilot in making a correct angles of descent to the runways. provide for automatic altitude reporting to air traffic control. indicate the distance the airplane is from the end of the runway.

The purpose of a localizer is to. align the airplane with the center of the runway. set the airplane on the proper approach angle to the runway. indicate the distance the airplane is from the end the runway.

When bending coaxial cable, the bend radius should be at least. 10 times the diameter of the cable. 15 times the diameter of the cable. 20 timed the diameter of the cable.