FAA Commercial Pilot Airplane (CAX)

A. To automatically adjust the propeller blade angle to maintain a pilot-selected RPM

The governor senses RPM through flyweights and meters oil pressure to change propeller blade angle, holding RPM constant at the value selected by the pilot regardless of airspeed or power changes.

B. The load remained within the airplane's limit load factor, and no structural damage should occur

Since 3.5G is less than the airplane's positive limit load factor of 3.8G, the structure remains within its design limits and no permanent deformation or damage should occur. The limit load factor represents the maximum load the structure can sustain without permanent damage, while the ultimate load factor (typically 1.5× limit) is the point of structural failure.

B. Failed turbocharger center bearing/oil seals allowing engine oil to enter the induction and exhaust system

Blue exhaust smoke with high oil consumption but normal manifold pressure points to a turbocharger bearing/seal failure, which allows engine oil to leak past the seals into the exhaust and induction airstream where it is burned. A stuck wastegate, pop-off valve, or failed density controller would instead cause abnormal manifold pressure readings (overboost or underboost), not oil-related smoke.

C. No, because the required three night takeoffs and landings to a full stop must have occurred within the preceding 90 days

14 CFR 61.57(b) requires three takeoffs and landings to a full stop during the period beginning 1 hour after sunset and ending 1 hour before sunrise within the preceding 90 days to carry passengers at night. Since the pilot's currency lapsed 5 days ago, the pilot is not current for this flight.

C. 5.25°/second

Rate = (1,091 × tan(30°))/120 = (1,091 × 0.577)/120 = 629.5/120 ≈ 5.25°/second. This is slightly faster than a standard-rate turn of 3°/second.

A. Flaps increase the maximum coefficient of lift the wing can produce, lowering the stall speed

Flaps increase wing camber, which raises the maximum coefficient of lift (CLmax) the wing can generate before stalling. Since stall speed is inversely related to the square root of CLmax, a higher CLmax allows a lower stall speed.

B. Confirmation bias

Confirmation bias occurs when a person selectively focuses on information that supports a preexisting belief or desired outcome (wanting the weather to be good) while disregarding contradictory data, such as the thunderstorm forecast.

D. 2,400 feet

r = 180²/(11.26 × 1.19) = 32,400/13.4 ≈ 2,418 feet, which rounds to approximately 2,400 feet.

D. region of reverse command

The region of reverse command, also called flying "behind the power curve," occurs at airspeeds below L/D max where total drag increases as speed decreases, requiring more power (not less) to maintain altitude. This is the opposite of normal flight, where reducing speed reduces required power.

A. Approximately 60 KIAS, essentially unchanged from the sea level value

Indicated airspeed is derived from dynamic pressure, which already accounts for air density. For a given weight and configuration, the wing always stalls at the same critical angle of attack and therefore the same indicated (calibrated) airspeed, regardless of altitude — although true airspeed at the stall increases with altitude.

D. Negative pressure relief valve

The negative pressure relief valve prevents a structurally dangerous situation where outside pressure exceeds cabin pressure (which can happen during a rapid descent when the cabin can't depressurize fast enough) by letting outside air flow in. The outflow valve controls normal cabin pressure regulation, the positive pressure relief valve prevents excessive cabin pressure buildup, and the rate-of-climb controller manages the speed of cabin pressure changes, not pressure differential direction.

A. 70.7 knots

Accelerated stall speed is calculated as Vs × √n, where n is the load factor. Here, Vs = 50 × √2 = 50 × 1.414 = 70.7 knots. This shows that even in a straight pull-up (not just a turn), increased load factor raises the stall speed.

D. Reduced susceptibility to induction icing since fuel is injected directly into the cylinders or intake ports rather than vaporized in a venturi

Float carburetors vaporize fuel in a venturi, which cools the incoming air and can cause carburetor icing even in relatively warm, humid conditions. Fuel-injected engines meter fuel directly to each cylinder or intake port, avoiding the venturi cooling effect and greatly reducing susceptibility to induction icing.

C. 2,000 feet

r = V²/(11.26 × tan(45°)) = 150²/(11.26 × 1.0) = 22,500/11.26 ≈ 1,998 feet, which rounds to approximately 2,000 feet.

D. March 31 of this year

14 CFR 91.409(a) requires an annual inspection within the preceding 12 calendar months. A calendar month runs to the end of the month, so an inspection completed in March of last year is due by the end of March of the following year.

A. The pilot must receive and log ground and flight training on that aircraft's systems and procedures, then receive a logbook endorsement of competency

14 CFR 61.55 requires a pilot who does not hold a type rating for the aircraft to receive and log ground and flight training on that specific aircraft's systems, procedures, and flight characteristics, and to obtain an endorsement in their logbook certifying they are competent to act as SIC, before serving in that role.

D. To confirm sufficient satellites are available to detect a position error along the route and at the destination

Receiver Autonomous Integrity Monitoring (RAIM) verifies that enough satellites are in view with adequate geometry to detect a faulty signal, ensuring position integrity for IFR operations along the planned route and at the destination.

B. Impulsivity

Impulsivity is the tendency to act quickly without adequately thinking through a situation, exactly as shown by wanting to skip a required calculation and 'figure it out later.' The antidote is 'Not so fast, think first.'

C. the wing must reach the same lift-off indicated airspeed at a higher true airspeed, while the engine and propeller produce less thrust in the thinner air

Indicated airspeed for lift-off stays essentially the same because it directly reflects dynamic pressure on the wing, but at high density altitude the true airspeed needed to reach that same indicated airspeed is higher, meaning the airplane must accelerate to a greater groundspeed. Simultaneously, the thinner air reduces engine power output and propeller efficiency, both factors combining to lengthen the takeoff roll.

B. Progressive inspection program

A progressive inspection program, authorized under 14 CFR 91.409(d), allows an owner or operator to divide the inspection requirements into smaller segments performed at shorter, more frequent intervals so that the entire aircraft is inspected progressively, avoiding the need for one lengthy annual inspection.

A. Permitted; the flight is within the 10-hour overflight allowance, and the next inspection is due at 1,400.0 hours

14 CFR 91.409(c) allows the 100-hour limit to be exceeded by not more than 10 hours to fly the aircraft to a place where the inspection can be done. Here, the aircraft is 1.5 hours over at departure, and the 3.5-hour flight brings total overflight to 5.0 hours (1,301.5+3.5=1,305.0), which is within the 10-hour allowance. Importantly, the excess time is counted toward the next 100 hours, so the next inspection remains due at the original due date plus 100 hours (1,300.0+100=1,400.0), not based on the point at which the aircraft actually landed.

D. The owner or operator of the aircraft

14 CFR 91.403(a) places primary responsibility for maintaining an aircraft in an airworthy condition, including compliance with applicable airworthiness directives, on the owner or operator. Mechanics perform and certify the work, but the regulatory duty to ensure compliance rests with the owner/operator.

D. Power idle, ailerons neutral, rudder full opposite rotation, elevator forward to break the stall

The standard spin recovery procedure (often remembered as PARE) is: Power to idle, Ailerons neutral, Rudder applied opposite the direction of rotation, and Elevator moved forward to reduce angle of attack and break the stall, followed by neutralizing rudder and gently recovering from the dive.

D. Plan continuation bias

Plan continuation bias (often called 'get-there-itis') is the tendency to continue with an original plan despite changing conditions that should trigger a new decision, such as diverting when a personal minimum is exceeded.

A. 242°

East variation is subtracted from true course to get magnetic course: 250° − 8° = 242°. The memory aid 'East is least' applies when converting from true to magnetic.