Kuwait DGCA ATPL Theory cheat sheet

ICAO Annex 2 classifies airspace as A to G; Class A permits IFR only and Class G is uncontrolled with no ATC clearance required.

Standard separation minima in radar-controlled en-route airspace: 5 NM lateral or 1000 ft vertical below FL290; 2000 ft vertical from FL290 to FL410 unless RVSM approval applies.

Semi-circular rule: magnetic tracks 000-179 use odd flight levels, 180-359 use even flight levels; applies to IFR cruising levels.

VMC minima below 10000 ft AMSL in Class C-E airspace: 5 km flight visibility, 1500 m horizontal and 1000 ft vertical distance from cloud.

Aircraft must carry documents: certificate of registration, certificate of airworthiness, crew licences, journey log, and radio licence; Kuwait DGCA requires these on board at all times.

Emergency frequency 121.5 MHz is monitored for distress; SQUAWK 7700 for emergency, 7600 for radio failure, 7500 for unlawful interference.

ATIS provides current aerodrome information on a discrete VHF frequency; pilots must acknowledge receipt of ATIS information letter on first contact with ATC.

Bleed air for air-conditioning and anti-icing is typically tapped from the HP compressor stages; loss of bleed air affects pressurisation and wing anti-ice.

Hydraulic system reservoirs are pressurised to prevent cavitation; typical system pressure is 3000 psi for transport aircraft.

A bus tie or cross-feed allows one generator to supply both main AC buses; loss of one generator leaves essential buses powered.

Fuel: Jet A-1 flash point approximately 38 °C; freezing point maximum -47 °C; specific gravity about 0.81.

Turbofan thrust = mass flow × (jet velocity - aircraft velocity); bypass ratio affects propulsive efficiency and specific fuel consumption.

Fire detection in engines uses continuous-loop or dual-loop sensors; a fire warning requires immediate shutdown and agent discharge.

Landing gear: oleo strut absorbs landing loads; shimmy damper prevents nose-wheel oscillation; anti-skid modulates brake pressure to prevent wheel lock.

Pitot-static: airspeed indicator uses total pressure from pitot and static pressure; altimeter and VSI use static pressure only.

Altimeter setting: QNH gives altitude above mean sea level; QFE gives height above reference datum; QNE (1013.25 hPa) gives pressure altitude.

Mach number = TAS / local speed of sound; speed of sound varies with temperature only (approximately 661 kt at ISA sea level).

Gyroscopic instruments: attitude indicator and heading indicator are space-referenced; turn coordinator is rate-referenced and electrically driven.

ILS: localiser provides lateral guidance on 108.10-111.95 MHz; glidepath on 329.15-335.0 MHz; marker beacons at outer, middle, inner positions.

TCAS II provides traffic advisories and resolution advisories; RA must be followed immediately unless it compromises safety.

EGPWS provides terrain alerts; Mode 1-4 alerts are inhibited below certain radio altitudes to prevent nuisance warnings during approach.

Maximum take-off mass = dry operating mass + traffic load + take-off fuel; maximum landing mass limits weight at touchdown.

Centre of gravity = sum of (mass × arm) / total mass; expressed as % MAC or inches from reference datum.

Forward CG limit increases stick force and reduces range; aft CG limit reduces stability and can cause pitch-up in stall recovery.

Zero fuel mass = take-off mass - fuel load; must not exceed maximum zero fuel mass.

Load sheet: LIZ (last item zero fuel) and LIT (last item take-off) values are used by flight crew to verify CG within limits.

Floor loading limits per unit area must be respected; heavy items secured to prevent shifting during turbulence.

Take-off distance available (TODA) = TORA + clearway; take-off run available (TORA) is the runway length available for ground run.

V1 is decision speed; VR is rotation speed; V2 is take-off safety speed ensuring minimum climb gradient with one engine inoperative.

Landing distance required must not exceed landing distance available; factored landing distance accounts for 1.67 (dry) or 1.92 (wet) factors.

Climb gradient requirements: second segment 2.4% for twin-engine, 2.7% for three-engine, 3.0% for four-engine aircraft.

Density altitude increases with high elevation, high temperature, and high humidity; reduces engine power and increases take-off distance.

Balanced field length: distance where accelerate-stop distance equals accelerate-go distance; used to determine V1 for a given runway.

Wind components: headwind decreases take-off distance; tailwind increases it; crosswind component = wind speed × sin(angle).

Fuel planning: taxi fuel + trip fuel + contingency (5% of trip) + alternate fuel + final reserve (30 min holding) + additional fuel.

True airspeed increases approximately 2% per 1000 ft altitude for a given IAS at constant temperature.

Great circle distance = 60 NM per degree of latitude; rhumb line is constant track and used for short legs on Mercator charts.

Wind triangle: heading = track ± drift; drift angle = arcsin(wind speed × sin(wind angle to track) / TAS).

Point of no return (PNR) is where time to return equals time to continue; equal time point (ETP) calculation uses groundspeeds outbound and inbound.

Flight plan must be filed at least 30 minutes before departure for IFR flights; changes require ATC notification.

Hypoxia symptoms begin around 10000 ft; time of useful consciousness at FL350 is 30-60 seconds; supplemental oxygen required above 10000 ft.

Spatial disorientation: somatogravic illusion causes false climb perception during acceleration; leans occur after prolonged turns without visual reference.

Circadian rhythm: lowest alertness typically 0300-0600 local; window of circadian low increases fatigue risk.

Crew resource management: assertiveness, situational awareness, and communication are core; authority gradient affects error reporting.

Hyperventilation causes hypocapnia and symptoms similar to hypoxia; treatment is controlled breathing and reassurance.

Alcohol: minimum 8 hours bottle-to-throttle; blood alcohol limit 0.02% in many jurisdictions; effects persist after blood levels normalise.

Decompression sickness from rapid altitude changes; avoid flying 24 hours after diving without pressurised cabin.

ISA: sea level temperature 15 °C, pressure 1013.25 hPa, lapse rate 1.98 °C per 1000 ft up to tropopause at 36089 ft.

QNH is pressure reduced to sea level; QFE is pressure at aerodrome; altimeter set to QNH reads elevation on the ground.

Thunderstorm life cycle: cumulus (updrafts), mature (updrafts and downdrafts, lightning, hail), dissipating (downdrafts dominate).

Icing: clear ice forms in large supercooled droplets (-0 to -10 °C); rime ice in small droplets; mixed ice most dangerous.

Wind shear on approach: increasing headwind causes airspeed increase and performance gain; decreasing headwind causes sink.

Cloud types: cumulonimbus indicates convective activity and severe turbulence; stratus indicates stable air and poor visibility.

METAR reports surface weather; TAF forecasts aerodrome conditions; SIGMET warns of significant hazardous weather.

VOR: radials are magnetic bearings from the station; CDI shows deviation from selected radial; TO/FROM indicator depends on aircraft position.

NDB/ADF: bearing is relative to aircraft heading; relative bearing + heading = magnetic bearing to or from station.

ILS: localiser frequency paired with glidepath; approach category determines decision height and visibility minima.

RNAV/GNSS: required navigation performance (RNP) specifies accuracy; RNP 0.3 for approach, RNP 1 for en-route.

Great circle track changes continuously; initial track and final track differ; rhumb line maintains constant heading.

Dead reckoning: track = heading + drift; ground speed = TAS ± wind component; position fixed by visual or radio aids.

Take-off briefing includes V speeds, engine failure procedure, emergency return, and rejected take-off decision.

Sterile cockpit: no non-essential activity below 10000 ft or during critical phases; only essential communication permitted.

Emergency descent: oxygen masks on, descent to 10000 ft or MSA, speed VMO/MMO, notify ATC with MAYDAY.

Engine failure after V1: maintain V2, climb to acceleration altitude, clean up, identify and secure failed engine.

Approach briefing: type of approach, minima, missed approach procedure, go-around decision, and runway conditions.

Checklist discipline: do-lists and challenge-response; never skip items; use of flow patterns followed by checklist verification.

Lift = ½ ρ V² S CL; induced drag decreases with speed, parasite drag increases with speed squared.

Critical angle of attack is fixed; stall occurs when exceeded regardless of speed or attitude.

Load factor increases in turns: n = 1/cos(bank); stall speed increases by √n.

Boundary layer: laminar flow has low friction; transition to turbulent increases skin friction but resists separation.

Mach critical: local airflow reaches sonic speed; shock waves form causing buffet and Mach tuck.

Dihedral provides lateral stability; sweepback improves high-speed performance but reduces low-speed lift.

Standard phraseology: "ROGER" means message received; "WILCO" means will comply; "AFFIRM" means yes.

Read-back required for clearances, runway assignments, altimeter settings, and frequency changes.

Distress call: MAYDAY (three times); urgency call: PAN-PAN (three times); emergency frequency 121.5 MHz.

Position report format: aircraft identification, position, time, flight level, next position and ETA.

VFR flight plan: must be filed for cross-country flights; position reports every 30 minutes or as required.

Frequency change: contact next ATC unit before leaving current frequency; maintain listening watch on 121.5 where practicable.