A&P - Airframe

An aircraft magnetic compass is swung to up-date the compass correction card when. an annual inspection is accomplished on the aircraft. the compass is serviced. equipment is added that could effect compass deviation.

Which of the following operating mechanisms would be found in a hydraulic pressure gauge?. Bourdon tube. Pressure diaphragm. Evacuated bellows.

What is the fixed line mark attached to the compass bowl of a magnetic compass called?. Reeder line. Lubber line. Reference line.

(1) Aircraft instruments are color-coded to direct attention to operational ranges and limitations. (2) Aircraft instruments range markings are not specified by Title 14 of the Code of Federal Regulations but are standardized by aircraft manufacturers. Regarding the above statements,. only No. 1 is true. only No. 2 is true. both No. 1 and No. 2 are true.

Which of the following will cause inaccuracies in a magnetic compass that may be compensated for by an aircraft mechanic?. Deviation. Current. Variation.

What will be the result if the instrument static pressure line becomes disconnected inside a pressurized cabin during cruising flight?. The altimeter and airspeed indicator will both read low. The altimeter and airspeed indicator will both read high. The altimeter will read low and the airspeed indicator will read high.

The maximum deviation (during level flight) permitted in a compensated magnetic direction indicator installed on an aircraft certificated under Federal Aviation Regulation Part 23 is. 6°. 8°. 10°.

Magnetic compass bowls are filled with a liquid to. retard precession of the float. reduce deviation errors. dampen the oscillation of the float.

Instrument static system leakage can be detected by observing the rate of change in indication of the. airspeed indicator after suction has been applied to the static system to cause a prescribed equivalent airspeed to be indicated. altimeter after pressure has been applied to the static system to cause a prescribed equivalent altitude to be indicated. altimeter after suction has been applied to the static system to cause a prescribed equivalent altitude to be indicated.

The maximum altitude loss permitted during an unpressurized aircraft instrument static pressure system integrity check is. 50 feet in 1 minute. 200 feet in 1 minute. 100 feet in 1 minute.

Which statement regarding an aircraft instrument vacuum system is true?. Dry-type vacuum pumps with carbon vanes are very susceptible to damage from solid airborne particles and must take in only filtered air. Vacuum systems are generally more effective at high altitudes than positive pressure systems. If the air inlet to each vacuum instrument is connected to a common atmospheric pressure manifold, the system generally will be equipped with individual instrument filters only.

When an aircraft altimeter is set at 29.92" Hg on the ground, the altimeter will read. pressure altitude. density altitude. field elevation.

Which of the following instrument discrepancies could be corrected by an aviation mechanic? 1. Red line missing. 2. Case leaking. 3. Glass cracked. 4. Mounting screws loose. 5. Case paint chipped. 6. Leaking at line B nut. 7. Will not adjust. 8. Fogged. 1, 4, 6. 3, 4, 5, 6. 1, 4, 5, 6.

Which of the following instrument discrepancies would require replacement of the instrument? 1. Red line missing. 2. Case leaking. 3. Glass cracked. 4. Mounting screws loose. 5. Case paint chipped. 6. Leaking at line B nut. 7. Will not zero out. 8. Fogged. 2, 3, 7, 8. 1, 4, 6, 7. 1, 3, 5, 8.

Which instrument condition is acceptable and would not require correction? 1. Red line missing. 2. Case leaking. 3. Glass cracked. 4. Mounting screws loose. 5. Case paint chipped. 6. Leaking at line B nut. 7. Will not zero out. 8. Fogged. 1. 5. None.

A barometric altimeter indicates pressure altitude when the barometric scale is set at. 29.92" Hg. 14.7" Hg. field elevation.

A Bourdon tube instrument may be used to indicate 1. pressure. 2. temperature. 3. position. 1 and 2. 1. 2 and 3.

A turn coordinator instrument indicates. the longitudinal attitude of the aircraft during climb and descent. the need for corrections in pitch and bank. both roll and yaw.

Aircraft temperature thermocouple leads may. not be altered and are designed for a specific installation. be installed with either lead to either post of the indicator. be repaired using solderless connectors.

A synchro transmitter is connected to a synchro receiver. mechanically through linkage. electromagnetically without wires. electrically with wires.

The operation of an angle-of-attack indicating system is based on detection of differential pressure at a point where the airstream flows in a direction. not parallel to the true angle of attack of the aircraft. parallel to the angle of attack of the aircraft. parallel to the longitudinal axis of the aircraft.

Turbine engine exhaust gas temperatures are measured by using. iron/constantan thermocouples. chromel/alumel thermocouples. ratiometer electrical resistance thermometers.

Fuel flow transmitters are designed to transmit data. mechanically. electrically. utilizing fluid power.

Which of the following causes of aircraft magnetic compass inaccuracies may be compensated for by mechanics?. Deviation. Magnetic compass current. Variation.

Who is authorized to repair an aircraft instrument? 1. A certified mechanic with an airframe rating. 2. A certificated repairman with an airframe rating. 3. A certificated repair station approved for that class instrument. 4. A certificated airframe repair station. 1, 2, 3, and 4. 3 and 4. 3.

What does a reciprocating engine manifold pressure gauge indicate when the engine is not operating?. Zero pressure. The differential between the manifold pressure and the atmospheric pressure. The existing atmospheric pressure.

The requirements for testing and inspection of instrument static systems required by Section 91.411 are contained in. Type Certificate Data Sheets. AC 43.13-1A. Part 43, appendix E.

Which condition would be most likely to cause excessive vacuum in a vacuum system?. Vacuum pump overspeed. Vacuum relief valve improperly adjusted. Vacuum relief valve spring weak.

Data transmitted between components in an EFIS are converted into. digital signals. analog signals. carrier wave signals.

The function of a CRT in an EFIS is to. allow the pilot to select the appropriate system configuration for the current flight situation. display alphanumeric data and representations of aircraft instruments. receive and process input signals from aircraft and engine sensors and send the data to the appropriate display.

The function of a symbol generator (SG) in an EFIS is to. display alphanumeric data and representations of aircraft instruments. allow the pilot to select the appropriate system configuration for the current flight situation. receive and process input signals from aircraft and engine sensors and send the data to the appropriate display.

The function of a display controller in an EFIS is to. display alphanumeric data and representations of aircraft instruments. allow the pilot to select the appropriate system configuration for the current flight situation. receive and process input signals from aircraft and engine sensors and send the data to the appropriate display.

A radar altimeter determines altitude by. transmitting a signal and receiving back a reflected signal. receiving signals transmitted from ground radar stations. means of transponder interrogation.

A radar altimeter indicates. flight level (pressure) altitude. altitude above sea level. altitude above ground level.

Resistance-type temperature indicators using Wheatstone bridge or ratiometer circuits may be used to indicate the temperatures of which of the following? 1. Free air. 2. Exhaust gas temperature. 3. Carburetor air. 4. Coolant (engine). 5. Oil temperature. 6. Cylinder head temperature. 1, 2, 3, 4, 5, and 6. 1, 3, 4, and 5. 1, 2, 3, and 6.

When flags such as NAV, HDG, or GS are displayed on an HSI, the indication is. that function is inoperative. that function is operating. to call attention to deviation from the desired setting, or flight path, or heading, etc.

Instrument panel shock mounts absorb. high energy impact shocks caused by hard landings. low frequency, high-amplitude shocks. high G shock loads imposed by turbulent air.

Which procedure should you use if you find a vacuum-operated instrument glass loose?. Mark the case and glass with a slippage mark. Replace the glass. Install another instrument.

Which instruments are connected to an aircraft's pitot-static system? 1. Vertical speed indicator. 2. Cabin altimeter. 3. Altimeter. 4. Cabin rate-of-change indicator. 5. Airspeed indicator. 1, 2, 3, 4, and 5. 1, 2, and 4. 1, 3, and 5.

Which of the following instruments will normally have range markings?. Altimeter. Cylinder head temperature gauge, airspeed indicator. Altimeter, airspeed indicator.

How would an airspeed indicator be marked to show the best rate-of-climb speed (one engine inoperative)?. A red radial line. A blue radial line. A green arc.

The green arc on an aircraft temperature gauge indicates. the instrument is not calibrated. the desirable temperature range. a low, unsafe temperature range.

What must be done to an instrument panel that is supported by shock mounts?. Bonding straps must be installed across the instrument mounts as a current path. The instrument mounts must be grounded to the aircraft structure as a current path. The instrument mounts must be tightened to the specified torque required by the maintenance manual.

What marking color is used to indicate if a cover glass has slipped?. Red. White. Yellow.

Aircraft instrument value should be marked and graduated in accordance with. the instrument manufacturer's specifications. both the aircraft and engine manufacturers' specifications. the specific aircraft maintenance or flight manual.

Aircraft instrument panels are generally shock-mounted to absorb. all vibration. low-frequency, high-amplitude shocks. high-frequency, high-amplitude shocks.

The method of mounting aircraft instruments in their respective panels depends on the. instrument manufacturer. design of the instrument case. design of the instrument panel.

How is a flangeless instrument case mounted in an instrument panel?. By four machine screws which extend through the instrument panel. By an expanding-type clamp secured to the back of the panel and tightened by a screw from the front of the instrument panel. By a metal shelf separate from and located behind the instrument panel.

Cases for electrically operated instruments are made of. Aluminum or composite cases. Iron or steel cases. Bakelite or plastic cases.

When installing an instrument in an aircraft, who is responsible for making sure it is properly marked?. The aircraft owner or pilot. The mechanic installing the instrument. The manufacturer of the instrument.

Where may a person look for the information necessary to determine the required markings on an engine instrument? 1. Engine manufacturer's specifications. 2. Aircraft flight manual. 3. Instrument manufacturer's specifications. 4. Aircraft maintenance manual. 2 or 4. 1 or 4. 2 or 3.

A certificated mechanic with airframe and powerplant ratings may. perform minor repairs to aircraft instruments. perform minor repairs and minor alterations to aircraft instruments. not perform repairs to aircraft instruments.

The red radial lines on the face of an engine oil pressure gauge indicates. minimum engine safe RPM operating range. minimum precautionary safe operating range. minimum and/ or maximum safe operating limits.

A certificated mechanic may perform. minor repairs to instruments. 100-hour inspections of instruments. instrument overhaul.

An aircraft instrument panel is electrically bonded to the aircraft structure to. act as a restraint strap. provide current return paths. aid in the panel installation.

How many of the following are controlled by gyroscopes? 1. Attitude indicator. 2. Heading indicator. 3. Turn needle of the turn-and-slip indicator. Three. Two. One.

The lubber line on a directional gyro is used to. represent the nose of the aircraft. align the instrument glass in the case. represent the wings of the aircraft.

Which instruments are connected to an aircraft's static pressure system only? 1. Vertical speed indicator. 2. Cabin altimeter. 3. Altimeter. 4. Cabin rate-of-change indicator. 5. Airspeed indicator. 1 and 3. 2, 4, and 5. 2 and 4.

When an unpressurized aircraft's static pressure system is leak checked to comply with the requirements of Section 91.411, what aircraft instrument may be used in lieu of a pitot-static system tester? 1. Vertical speed indicator. 2. Cabin altimeter. 3. Altimeter. 4. Cabin rate-of-change indicator. 5. Airspeed indicator. 1 or 5. 2 or 4. 3.

If a static pressure system check reveals excessive leakage, the leak(s) may be located by. pressurizing the system and adding leak detection dye. isolating portions of the line and testing each portion systematically starting at the instrument connections. removing and visually inspecting the line segments.

When performing the static system leakage check required by Section 91.411, the technician utilizes. static pressure. positive pressure. negative pressure.

At sea level, when the average atmospheric pressure is 14.7 PSI, the barometric pressure is. 29.92 Hg. 29.92 Mb. 1013.25 Hg.

A certificated mechanic with at least an airframe rating may perform. minor internal repairs to aircraft instruments. major repairs to aircraft instruments. inspections and function checks on aircraft instruments.