M7.19 Flashcards
At what altitudes are aircraft most likely to experience a lightning strike?
A. 8000 ft to 14,000 ft.
B. 5000 ft to 10,000 ft.
C. 20,000 ft to 30,000 ft.
A. 8000 ft to 14,000 ft.
At what frequency do lightning strikes occur on aircraft, on average?
A. Approximately every 3000 flying hours.
B. Approximately every 500 flying hours.
C. Approximately every 10,000 flying hours.
A. Approximately every 3000 flying hours.
What are the typical strike points when lightning strikes an aircraft?
A. One at the entrance point and one at the exit point.
B. One at the nose and one at the tail.
C. One on the wings and one on the fuselage.
A. One at the entrance point and one at the exit point.
What is direct damage caused by lightning strikes?
A. Direct damage is defined as metallic structures which are burned, melted, or show signs of metal distortion and non-metallic structures which are burned, punctured, or delaminated.
B. Direct damage refers to the disruption of electrical systems caused by large electrical transients.
C. Direct damage involves physical deformation of the aircraft’s exterior panels.
A. Direct damage is defined as metallic structures which are burned, melted, or show signs of metal distortion and non-metallic structures which are burned, punctured, or delaminated.
What is indirect damage caused by lightning strikes?
A. Indirect damage is identified as damage to electrical/electronic systems, wires, shielding, and shield terminations. This is caused by large electrical transients on the wiring, and it is evident by disruption to system operation.
B. Indirect damage refers to structural damage such as cracks or dents in the fuselage.
C. Indirect damage results in the ignition of fuel vapors due to a spark caused by lightning.
A. Indirect damage is identified as damage to electrical/electronic systems, wires, shielding, and shield terminations. This is caused by large electrical transients on the wiring, and it is evident by disruption to system operation.
Where does lightning usually enter the aircraft when it strikes?
A. The forward fuselage or engine nacelles.
B. The wing tips or horizontal stabilizer tips.
C. The landing gear or trailing edges of flap track fairing tips.
A. The forward fuselage or engine nacelles.
What must the flight crew do when they know or suspect that the aircraft has been affected by a lightning strike?
A. Report the incident via the tech log to ensure an inspection is carried out.
B. Perform an immediate emergency landing.
C. Disconnect all electrical systems to prevent further damage.
A. Report the incident via the tech log to ensure an inspection is carried out.
What causes indirect damage to electrical and electronic equipment during a lightning strike?
A. The electromagnetic field produced by a high-intensity lightning strike.
B. The direct impact of the lightning on wires and cables.
C. The disruption caused by fuel vapour.
A. The electromagnetic field produced by a high-intensity lightning strike.
What is protected from direct lightning strikes in the electrical systems of an aircraft?
A. The wires and cables are protected from direct strikes.
B. The electronic equipment in the cockpit.
C. The fuselage structure.
A. The wires and cables are protected from direct strikes.
Where are electrical cables and components particularly vulnerable to indirect damage caused by lightning strikes?
A. Within the unpressurized areas of the aircraft.
B. Inside the cockpit.
C. In the landing gear compartment.
A. Within the unpressurized areas of the aircraft.
What type of system should undergo a functional test if the aircraft has been struck by lightning?
A. The fly-by-wire flight control systems.
B. The aircraft electrical systems.
C. The emergency landing system.
A. The fly-by-wire flight control systems.
After a lightning strike, if there is a compass deviation, what must be done to correct it?
A. The aircraft must be degaussed, and a compass swing should be carried out.
B. The aircraft must undergo a thorough structural inspection.
C. The compass should be replaced immediately.
A. The aircraft must be degaussed, and a compass swing should be carried out.
What is the purpose of static dischargers on aircraft, and how are they affected by lightning strikes?
A. They dissipate static charge buildup, but they are frequently damaged by lightning strikes.
B. They prevent lightning strikes, but are unaffected by them.
C. They ensure the aircraft’s electrical system is grounded, and are unaffected by lightning strikes.
A. They dissipate static charge buildup, but they are frequently damaged by lightning strikes.
What is the purpose of the bonding leads/cables attached to flight control surfaces?
A. To provide a low-resistance path for lightning strike currents, preventing damage to bearings.
B. To connect flight control surfaces to the aircraft’s electrical system.
C. To reduce aerodynamic drag on the aircraft.
A. To provide a low-resistance path for lightning strike currents, preventing damage to bearings.
What does HIRF stand for in the context of aviation?
A. High Intensity Radiated Fields
B. High Internal Radiant Force
C. High Impact Radiated Frequency
A. High Intensity Radiated Fields
In what year were HIRF requirements and policies first introduced in aviation?
A. 1985
B. 1992
C. 2000
B. 1992
Which type of aircraft system is most vulnerable to HIRF-induced voltages?
A. Data bus systems, as they operate at very low power levels.
B. Hydraulic systems.
C. Engine control systems.
A. Data bus systems, as they operate at very low power levels.
What type of electromagnetic sources can cause HIRF to affect aircraft systems?
A. Lightning strikes or discharges in the vicinity of the aircraft.
B. Air turbulence caused by high-speed flight.
C. Exhaust gases from aircraft engines.
A. Lightning strikes or discharges in the vicinity of the aircraft.
How does an aircraft’s HIRF certification testing address potential interference issues?
A. Aircraft undergoes extensive testing, and any interference issues are addressed through modification or redesign.
B. HIRF testing is done only in the design phase and not after production.
C. The testing ensures that the aircraft is equipped with additional transmitters to cause interference.
A. Aircraft undergoes extensive testing, and any interference issues are addressed through modification or redesign.
What are the three primary areas to be considered for HIRF protection integrity?
A. Aircraft structure, electrical wiring installation protection, and equipment protection
B. Engine components, fuel system, and landing gear
C. Cabin safety, pressure seals, and avionics
A. Aircraft structure, electrical wiring installation protection, and equipment protection
What environmental factors can degrade electromagnetic protection on an aircraft?
A. Corrosion, mechanical vibrations, and damage repair
B. Temperature, altitude, and humidity
C. Engine performance and fuel efficiency
A. Corrosion, mechanical vibrations, and damage repair
What is the purpose of the electrical wiring installation protection in HIRF?
A. To provide solid or braided shielding connectors for the aircraft’s wiring
B. To increase the voltage of electrical systems
C. To prevent mechanical failure of the electrical components
A. To provide solid or braided shielding connectors for the aircraft’s wiring
What is the primary focus during an inspection after a pilot reports HIRF penetration?
A. Electrical bonding system, static dischargers, and built-in shielding
B. Aircraft fuel system and air conditioning units
C. Landing gear and flight control surfaces
A. Electrical bonding system, static dischargers, and built-in shielding
What must be done if aircraft magnetising is suspected following HIRF penetration?
A. The aircraft should be degaussed (demagnetised) followed by a calibration compass swing
B. The aircraft should undergo a full engine inspection
C. The aircraft’s fuel system should be inspected
A. The aircraft should be degaussed (demagnetised) followed by a calibration compass swing
What is the most easily detected sign of a heavy landing?
A. Wrinkled or creased wing skin
B. Engine vibration
C. Smoke from the fuselage
A. Wrinkled or creased wing skin
What is the definition of a “hard landing” in the context of aircraft inspections?
A. A landing in which the manufacturer’s touchdown limitation or ‘g’ loading value has been exceeded
B. A landing that does not involve any impact
C. A landing with no structural issues
A. A landing in which the manufacturer’s touchdown limitation or ‘g’ loading value has been exceeded
What is the primary purpose of a Phase I inspection after a hard landing?
A. To determine if further inspections are necessary
B. To perform a detailed inspection of all systems on the aircraft
C. To prepare the aircraft for routine maintenance
A. To determine if further inspections are necessary
What is one of the common signs of a heavy or hard landing?
A. Wrinkled or creased wing skin
B. Increased fuel efficiency
C. Clear sky visibility
A. Wrinkled or creased wing skin
What is a primary action during a Phase II inspection following a hard landing?
A. Inspecting only the cockpit systems
B. Ensuring shock strut hydraulic fluid levels are correct
C. Checking fuel efficiency and cabin pressure
B. Ensuring shock strut hydraulic fluid levels are correct
Why would a Phase II inspection be performed after a Phase I inspection of a hard landing?
A. To check for minor surface scratches and cosmetic damage
B. To assess the integrity of the structural components if Phase I found potential damage
C. To verify if the aircraft is still in warranty
B. To assess the integrity of the structural components if Phase I found potential damage
What is the definition of an overweight landing?
A. A landing made at a gross weight within the maximum design landing weight
B. A landing made at a gross weight in excess of the maximum design landing weight for a particular model
C. A landing made with normal weight but high wind conditions
B. A landing made at a gross weight in excess of the maximum design landing weight for a particular model
Which areas are commonly inspected during an overweight landing inspection?
A. Tires, landing gear components, and external lights
B. Wrinkled wing skin, fuel leakage, spar webs, and nacelle skin
C. Only the fuselage skin and wing roots
B. Wrinkled wing skin, fuel leakage, spar webs, and nacelle skin
What must happen if both a hard and overweight landing occur?
A. Only the overweight landing inspection needs to be performed
B. Both the hard landing inspection and the overweight landing inspection must be done
C. No special inspection is needed if the landing was smooth
B. Both the hard landing inspection and the overweight landing inspection must be done
What happens when an aircraft encounters an unpredicted gust condition?
A. The aircraft experiences a smooth flight
B. The load on the wings potentially exceeds the normal wing load supporting the aircraft weight
C. The aircraft loses altitude rapidly
B. The load on the wings potentially exceeds the normal wing load supporting the aircraft weight
What should be checked on the wing surfaces during an inspection after severe turbulence?
A. For cracks in the fuselage
B. For excessive buckles, wrinkles, and sheared rivet attachments
C. For scratches on the wing tips
B. For excessive buckles, wrinkles, and sheared rivet attachments
What is the general G-force range that may indicate damage to the airframe or engines during severe turbulence?
A. +0.5 Gs to +1.0 Gs
B. +6.0 Gs to +10.0 Gs
C. +2.5 Gs to +5.0 Gs
C. +2.5 Gs to +5.0 Gs
What additional tool on modern-day aircraft can provide an indication of loads sustained during severe turbulence?
A. Airspeed indicators
B. Accelerometers, flight data recorders, or fatigue meters
C. Fuel gauges
B. Accelerometers, flight data recorders, or fatigue meters
What should be considered when inspecting for fire damage on an aircraft?
A. Only visible damage to the aircraft structure needs to be repaired
B. Non-visible damage, such as structural degradation from heat, must also be considered even if no visible damage is apparent
C. Fire damage is only a concern for the aircraft’s engine components
B. Non-visible damage, such as structural degradation from heat, must also be considered even if no visible damage is apparent
How can the strength of an aircraft’s aluminium structure be further tested after a fire, even if no visible damage is seen?
A. By using a visual inspection only
B. Using an eddy-current conductivity tester or a Rockwell C hardness tester
C. By replacing all affected components without testing
B. Using an eddy-current conductivity tester or a Rockwell C hardness tester
What is the first step when inspecting an aircraft that has been submerged in water?
A. Conduct a visual inspection only
B. Replace all external components immediately
C. Disassemble, clean, dry, and treat affected parts with corrosion inhibitor
C. Disassemble, clean, dry, and treat affected parts with corrosion inhibitor
