Kuwait DGCA CPL Theory cheat sheet

ICAO Annex 2 (Rules of the Air) applies to all aircraft; Kuwait DGCA Civil Aviation Regulations implement ICAO Annexes nationally, and the CPL holder is bound by both.

Controlled airspace classes: A = IFR only, all separated; B = IFR and VFR, all separated; C = IFR separated from all, VFR separated from IFR only; D = IFR separated from IFR, traffic info to VFR; E = IFR separated from IFR only; F and G uncontrolled.

Semicircular rule (cruising levels): magnetic track 000-179 use odd thousands (FL 090, 110...); 180-359 use even thousands (FL 100, 120...); applies above the transition altitude in IMC or when required.

Transition altitude is fixed per aerodrome in Kuwait (commonly 13,000 ft in the Gulf region); below it use QNH and altitude, above it use standard 1013.2 hPa and flight levels.

VMC minima below 10,000 ft: 5 km flight visibility, 1,500 m horizontal and 300 m (1,000 ft) vertical distance from cloud; at or above 10,000 ft: 8 km, 1,500 m horizontal, 1,000 ft vertical.

Position lights: red on left wingtip, green on right wingtip, white on tail; anti-collision beacons/strobes on at night and in reduced visibility.

Right-of-way: converging aircraft of the same category - the one on the right has priority; head-on - both turn right; overtaking - the overtaken aircraft has priority and the overtaker passes to the right.

A clearance is an authorisation to proceed under specified conditions; a pilot must read back runway, altitude, heading, frequency and transponder instructions and must request clarification if any part is unclear.

Semi-monocoque structure: skin carries most shear and tension, stringers and frames stabilise the skin and carry bending; a crack arrestor or fail-safe design limits crack propagation.

Hydraulic system pressure is typically 3,000 psi; a pressurised reservoir keeps fluid under positive head to prevent pump cavitation at altitude.

Electrical: 28 V DC and 115 V AC 400 Hz are standard; a bus tie allows one generator to feed both buses; battery provides emergency supply to essential buses only.

Aircraft batteries (lead-acid or NiCd) supply power for APU start and emergency DC; NiCd thermal runaway requires immediate disconnection of the battery from the bus.

Reciprocating engine: mixture is set lean of peak EGT for cruise economy; carburettor icing can occur at outside air temperatures between about -10 °C and +25 °C with high humidity.

Turbine engine: EGT, N1/N2 and fuel flow are the primary limits; a hung start (slow acceleration, high EGT) requires immediate fuel and ignition cut-off.

Fire detection uses rate-of-rise and fixed-temperature loops; a fire extinguisher bottle must be discharged into the affected zone after the engine or APU is shut down.

Emergency equipment: life jackets/vests, portable oxygen, first-aid kit, fire axe, crash axe and ELT are required items; the ELT transmits on 121.5, 243 and 406 MHz.

Pitot-static: ASI uses pitot (dynamic) pressure versus static; VSI uses a calibrated leak to measure rate of change of static pressure; altimeter uses static pressure against a set subscale.

Altimeter errors: position (static source) error, instrument error, temperature error - cold air makes the true altitude lower than indicated, so apply cold-temperature correction on approach.

ASI errors: position error, instrument/installation error, compressibility error (high speed/high altitude) and density error - IAS is not TAS.

TAS = IAS × (1 + 0.02 × altitude in thousands of feet) is a rough approximation; exact TAS uses density ratio: TAS = IAS / √σ.

Gyroscopic instruments: attitude indicator and heading indicator are space-referenced (rigidity in space); the turn coordinator is rate-referenced (precession) and shows rate of turn and slip/skid.

Vacuum-driven gyros fail if the vacuum pump fails; the electric turn coordinator and standby instruments provide partial redundancy.

Magnetic compass: deviation is aircraft-induced error shown on the compass card; variation is the angular difference between true and magnetic north at the location.

EFIS/glass cockpit failures: a display unit failure requires reversion to the remaining display or standby instruments; total electrical failure leaves the standby ASI, altimeter and compass.

Basic Empty Mass (BEM) = airframe + powerplant + fixed equipment + unusable fuel + full oil; Dry Operating Mass = BEM + crew + crew baggage + catering.

Take-off mass = DOM + traffic load (passengers + baggage + cargo) + take-off fuel; landing mass = take-off mass − trip fuel.

Moment = mass × arm (distance from datum); CG position = total moment / total mass; keep CG within the forward and aft limits for all phases.

Forward CG increases stability, increases stall speed, lengthens take-off run and reduces elevator authority; aft CG reduces stability and can cause pitch-up and spin recovery difficulty.

Maximum Zero Fuel Mass (MZFM) limits the load that can be carried above the operating mass without fuel; Maximum Take-off Mass and Maximum Landing Mass are structural limits.

Load sheet: LIZ (last item zero fuel mass) and LIR (last item landing mass) are used to check the CG envelope; last-minute changes must be reflected in the final load sheet.

Floor loading limits: maximum running load (kg per linear metre) and maximum load per unit area; heavy items must be spread and secured.

Fuel density varies with temperature; use the actual density (kg/L) to convert volume to mass - an error of 0.01 kg/L on 3,000 L is 30 kg.

Density altitude = pressure altitude + 120 × (OAT − ISA temperature at that level); high density altitude reduces engine power, propeller thrust and lift, increasing take-off and landing distances.

Take-off distance required = ground roll + airborne segment to 35 ft (or 50 ft for transport category); the balanced field length is where accelerate-stop distance equals take-off distance.

V1 is decision speed, VR rotation speed, V2 take-off safety speed (at least 1.13 VS1 in the take-off configuration); VREF is the landing reference speed at 1.3 VS0.

Climb gradient (%) = (change in height / horizontal distance) × 100; rate of climb (ft/min) = gradient × ground speed (kt) × 101.3 / 60.

Landing distance required must not exceed landing distance available; add 15% for dry runway planning in commercial operations and more for wet/contaminated runways.

Stall speed varies with the square root of the load factor: VS at load factor n = VS1g × √n; a 30° bank gives n = 1.15 and about a 7% increase in stall speed.

Wind effect: headwind decreases ground roll and increases climb gradient; tailwind increases both; use the wind component along the runway, not the reported wind.

Obstacle clearance: the net take-off flight path must clear all obstacles by 35 ft vertically (or specified margin) after the engine failure case is considered.

Trip fuel = fuel from take-off to landing at destination; contingency fuel is typically 5% of trip fuel; alternate fuel covers destination to alternate; final reserve is 30 minutes holding at 1,500 ft above the alternate.

Total fuel = taxi + trip + contingency + alternate + final reserve + extra; the minimum fuel on arrival at destination must not be less than final reserve.

Fuel flow (kg/h) = power setting fuel flow; fuel used = flow × time; specific range = TAS / fuel flow (nm per kg), maximised at the optimum cruise altitude.

Cruise altitude selection: higher is generally more efficient but limited by aircraft ceiling, turbulence, and the crossover altitude where a lower speed/Mach schedule changes.

Point of No Return (PNR) = the point from which it is equal time to return to departure or continue to destination; ETP (equal time point) uses the same principle with wind.

Critical Point (CP) = the point from which it is equal time to reach either destination or departure aerodrome; used for fuel planning on long sectors.

ISA deviation affects TAS and fuel flow; a temperature above ISA increases TAS but also increases fuel flow, so check the flight plan against actual conditions.

Flight plan monitoring: compare actual fuel against planned at each waypoint; a 5% or greater deviation requires review and possible diversion decision.

Hypoxia: symptoms appear typically above 10,000 ft without oxygen; time of useful consciousness at FL 350 is about 30-60 seconds; supplemental oxygen is required above 10,000 ft for crew.

Hyperventilation causes dizziness, tingling and visual disturbance; treatment is to slow the breathing rate, and it must be distinguished from hypoxia before giving oxygen.

Spatial disorientation: the somatogravic illusion (false pitch-up on acceleration) and the leans are vestibular illusions; trust the instruments, not sensations.

Cabin altitude and decompression: a rapid decompression at high altitude requires immediate oxygen mask use and an emergency descent to below 10,000 ft.

Fatigue and circadian rhythm: alertness is lowest between 02:00-06:00 and 14:00-16:00 local; duty and rest limits are set by the operator under DGCA rules.

Stress and workload: high stress narrows attention and increases error rate; use checklists, prioritise aviate-navigate-communicate and use crew resource management.

Vision: night vision is best with peripheral vision (rods), so use off-centre viewing at night; avoid bright white light to preserve dark adaptation.

Alcohol and drugs: standard limit is 0.00% blood alcohol for flight crew in most states, with a minimum bottle-to-throttle interval; any impairing medication requires aero-medical clearance.

ISA: sea level temperature 15 °C, pressure 1013.25 hPa, lapse rate 1.98 °C per 1,000 ft up to 36,090 ft (tropopause).

QNH is the pressure reduced to sea level; QFE is the pressure at the aerodrome; QNE is 1013.25 hPa used above the transition altitude.

Cloud types: cumulus and cumulonimbus indicate instability and convection; stratus indicates stable air; CB contains severe turbulence, icing and hail.

Icing: clear ice forms in large supercooled droplets (stratiform clouds, 0 to -10 °C); rime ice forms in small droplets (stratiform, -10 to -20 °C); mixed ice is a combination.

Wind: surface friction reduces wind speed and backs the wind direction near the surface; the geostrophic wind is parallel to isobars aloft.

Fronts: a cold front has a steep slope, narrow band of heavy showers and rapid passage; a warm front has a shallow slope, wide band of steady rain and gradual passage.

Thunderstorm life cycle: cumulus (updrafts), mature (updrafts and downdrafts, rain, lightning), dissipating (downdrafts); avoid the mature stage by at least 20 nm.

METAR/TAF: METAR reports actual conditions; TAF is a forecast valid for a stated period; SPECI is a special report issued on significant change.

Great circle is the shortest distance between two points on the Earth's surface; rhumb line is a constant track line, longer than the great circle except on the equator or a meridian.

1 minute of latitude = 1 nautical mile; 1 degree of latitude = 60 nm; longitude spacing decreases with the cosine of latitude.

Mercator projection: rhumb lines are straight lines, scale increases with latitude, great circles are curved (concave to the equator); used for plotting.

Lambert conformal conic: used for aeronautical charts at mid-latitudes; scale is constant along standard parallels.

Track and heading: heading = track − wind correction angle; drift = TAS × sin(wind angle) / TAS, and the wind triangle gives the wind correction angle.

Time (UTC) = local time − time zone offset; Kuwait is UTC+3; sunrise and sunset are computed in UTC and converted.

Magnetic variation east is subtracted from true to get magnetic (east is least); west is added (west is best).

Relative bearing = angle from the aircraft heading to the station; QDM is the magnetic bearing to the station; QDR is the magnetic bearing from the station.

VOR: 108.0-117.95 MHz, line-of-sight; the CDI shows the selected radial; TO/FROM indicates whether the selected course leads to or from the station.

NDB/ADF: 190-1750 kHz, ground wave and sky wave; the ADF needle points to the station; relative bearing + heading = magnetic bearing to the station.

DME: measures slant range in nautical miles; the error over the station is the aircraft altitude; DME is paired with VOR or ILS.

ILS: localiser 108.10-111.95 MHz (odd tenths) gives lateral guidance; glide path 329.15-335.0 MHz gives vertical guidance; the decision altitude is where a missed approach begins.

ILS categories: CAT I decision height 200 ft and RVR 550 m; CAT II 100 ft and 300 m; CAT III A 50 ft and 200 m, III B below 50 ft and 50 m.

Transponder: Mode A gives identity (squawk), Mode C adds altitude; squawk 7500 unlawful interference, 7600 radio failure, 7700 emergency.

GNSS/GPS: position from satellite ranging; RAIM monitors integrity; the receiver applies the WGS-84 datum; an approach with vertical guidance uses SBAS.

Radar: primary radar uses skin reflection; secondary surveillance radar (SSR) uses the transponder reply; radar separation minima depend on the radar type and range.

Take-off briefing includes engine failure actions, rejected take-off decision, emergency return, and the departure routing; the take-off minima must be met before commencing.

Approach briefing covers the type of approach, minima, missed approach, and the go-around call; the stabilised approach criteria must be met by 1,000 ft (500 ft in some operators).

Emergency: aviate, navigate, communicate; declare an emergency on 121.5 with callsign, position, nature of problem, intentions and persons on board.

Emergency descent: oxygen masks on, descend to 10,000 ft or MSA, broadcast on 121.5, and set the transponder to 7700.

Ditching and forced landing: brief passengers, secure loose items, transmit MAYDAY with position, and prepare for evacuation; life jackets are donned before impact.

Fuel: minimum fuel is a state where landing at destination below final reserve is possible; MAYDAY FUEL is declared when the fuel is expected to be below final reserve on landing.

Wake turbulence: generated by heavy aircraft on take-off and landing; stay above the preceding aircraft's flight path and wait at least 2 minutes behind a heavy aircraft on the same runway.

Runway incursion and line-up: obtain clearance before entering or crossing a runway; read back hold-short instructions and never cross an active runway without ATC clearance.

Bernoulli and Newton: lift is generated by pressure difference and by downward momentum change; lift L = ½ ρ V² S CL, so lift increases with the square of speed.

Angle of attack is the angle between the chord line and the relative airflow; the critical angle of attack (about 15-16°) is where the wing stalls regardless of speed.

Induced drag decreases with speed and increases with lift coefficient; parasite drag increases with the square of speed; total drag is minimum at the speed for best L/D.

Load factor n = L/W; in a level turn n = 1/cos(bank angle); at 60° bank n = 2, so stall speed increases by √2 = 41%.

Stability: positive static stability means the aircraft tends to return to equilibrium after a disturbance; the CG must be forward of the neutral point for positive longitudinal stability.

Control: elevator controls pitch, ailerons control roll, rudder controls yaw; adverse yaw is caused by increased induced drag on the rising wing and is countered by rudder.

Flaps increase lift and drag and lower the stall speed; they also shift the centre of pressure and can reduce longitudinal stability.

Mach effects: the critical Mach number is the free-stream Mach at which airflow first reaches sonic speed; above it shock waves form and cause drag rise and buffet.