Student must himself give a complete detailled briefing including all the systems applicable to the training aircraft used.

The briefing should include:
1 Aeroplane structure and equipment, normal operation of systems and malfunctions

1.1 Dimensions
minimum required runway width for 180&amp;deg; turn

1.2 Engine including auxiliary power unit

1.2.1 type of engine/engines

1.2.2 in general, function of the following systems or components:
&amp;ndash; engine
&amp;ndash; auxiliary power unit
&amp;ndash; oil system
&amp;ndash; fuel system
&amp;ndash; ignition system
&amp;ndash; starting system
&amp;ndash; fire warning and extinguishing system
&amp;ndash; generators and generator drives
&amp;ndash; power indication
&amp;ndash; reverse thrust
   water injection

on piston or turbine-propellor engines additonally:

&amp;ndash; propeller system
&amp;ndash; feathering system

1.2.3 engine controls (including starter), engine instruments and indications in the cockpit, their function,
interrelation and interpretation

1.2.4 engine operation, including APU, during engine start, start and engine malfunctions, procedures for
normal operation in the correct sequence

1.3 Fuel system

1.3.1 location of the fuel tanks, fuel pumps, fuel lines to the engines, tank capacities, valves and
measuring

1.3.2 location of the following systems:
&amp;ndash; filtering
&amp;ndash; heating
&amp;ndash; fuelling and defuelling
&amp;ndash; dumping
&amp;ndash; venting

 
1.3.3 in the cockpit

the monitors and indicators of the fuel system,
quantity and flow indication, interpretation

1.3.4 procedures

fuel procedures distribution into the various tanks
fuel supply, temperature control and fuel dumping


1.4 Pressurisation and air conditioning

1.4.1 components of the system and protection devices

1.4.2 cockpit monitors and indicators
interpretation with regard to the operational condition
1.4.3 normal operation of the system during start, cruise, approach and landing, air conditioning airflow
and temperature control

1.5 Ice and rain protection, windshield wipers and rain repellent

1.5.1 ice protected components of the aeroplane including engines, heat sources, controls and indications

1.5.2 operation of the anti-icing/de-icing system during take-off, climb, cruise and descent, conditions
requiring the use of the protection systems

1.5.3 controls and indications of the windshield wipers and rain repellent systems operation

1.6 Hydraulic system

1.6.1 components of the hydraulic system(s), quantities and system pressure, hydraulically actuated
components associated to the respective hydraulic system

1.6.2 controls, monitors and indicators in the cockpit, function and interrelation and interpretation of
indications

1.7 Landing gear

1.7.1 main components of the
&amp;ndash; main landing gear
&amp;ndash; nose gear
&amp;ndash; gear steering
&amp;ndash; wheel brake system, including anti-skid

1.7.2 gear retraction and extension (including changes in trim and drag caused by gear operation)

1.7.3 required tyre pressure, or location of the relevant placard

1.7.4 controls and indicators including warning indicators in the cockpit in relation to the
retraction/extension condition of the landing gear and brakes

1.7.5 components of the emergency extension system

1.8 Flight controls and high lift devices

1.8.1 &amp;ndash; aileron system
&amp;ndash; elevator system
&amp;ndash; rudder system
&amp;ndash; rim system
&amp;ndash; spoiler system
&amp;ndash; lift devices
&amp;ndash; stall warning system
&amp;ndash; take-off configuration warning system

1.8.2 flight control system from the cockpit controls to the flight control/surfaces

1.8.3 controls, monitors and indicators including warning
indicators of the systems mentioned under 1.8.1, interrelation and dependencies

1.9 Electrical power supply

1.9.1 number, power, voltage, frequency and location of the main power system (AC or DC), auxiliary
power system location and external power system

1.9.2 location of the controls, monitors and indicators in the cockpit

1.9.3 flight instruments, communication and navigation systems, main and back-up power sources

1.9.4 location of vital circuit breakers

1.9.5 generator operation and monitoring procedures of the electrical power supply

1.10 Flight instruments, communication, radar and navigation equipment, autoflight and flight recorder

1.10.1 visible antennae

1.10.2 controls and instruments of the following equipment in the cockpit during normal operation:
&amp;ndash; flight instruments
&amp;ndash; flight management systems
&amp;ndash; radar equipment, including radio altimeter
&amp;ndash; communication and navigation systems
&amp;ndash; autopilot
&amp;ndash; flight recorder, voice recorder
&amp;ndash; ground proximity warning system
&amp;ndash; collision avoidance system
&amp;ndash; warning systems

1.11 Cockpit, cabin and cargo compartment

1.11.1 operation of the exterior, cockpit, cabin and cargo compartment lighting and the emergency lighting

1.11.2 operation of the cabin and cargo doors, stairs, windows and emergency exits

1.11.3 main components of the oxygen system and their location, oxygen masks and operation of the
oxygen systems for the crew and passengers, required amount of oxygen by means of a table or diagram

1.12 Emergency equipment operation and correct application of the following emergency equipment in
the aeroplane:
&amp;ndash; portable fire extinguisher
&amp;ndash; first aid kits
&amp;ndash; portable oxygen equipment
&amp;ndash; emergency ropes
&amp;ndash; life vest
&amp;ndash; life rafts
&amp;ndash; emergency transmitters
&amp;ndash; crash axes
&amp;ndash; megaphones
&amp;ndash; emergency signals

1.13 Pneumatic system

1.13.1 components of the pneumatic system, pressure source, actuated components

1.13.2 controls, monitors and indicators in the cockpit, function of the system

1.13.3 vacuum system

2 LIMITATIONS

2.1 General Limitations

2.1.1. certification of the aeroplane, category of operation, noise certification and maximum and minimum
performance data for all flight profiles, conditions and a/c systems,

&amp;ndash; maximum tail and crosswind-components at take-off and landing,
&amp;ndash; maximum speeds for flap extension Vfo
&amp;ndash; at various flap settings Vfe
&amp;ndash; for landing gear operation Vlo, Mlo
&amp;ndash; for extended landing gear Vle, Mle
&amp;ndash; for maximum rudder deflection Va, Ma
&amp;ndash; for tyres
&amp;ndash; one propeller feathered

2.1.2 &amp;ndash; minimum control speed air Vmca

&amp;ndash; minimum control speed ground Vmcg
&amp;ndash; stall speed under various conditions Vso,Vs1
&amp;ndash; maximum speed Vne, Mne
&amp;ndash; maximum speed for normal operation Vmo, Mmo
&amp;ndash; altitude and temperature limitations
&amp;ndash; stick shaker activation

2.1.3 &amp;ndash; maximum airport pressure altitude, runway slope

&amp;ndash; maximum taxi mass
&amp;ndash; maximum take-off mass
&amp;ndash; maximum lift off mass
&amp;ndash; maximum landing mass
&amp;ndash; zero fuel mass
&amp;ndash; maximum dumping speed Vdco, Mdco, Vdce, Mdce
&amp;ndash; maximum load factor during operation
&amp;ndash; certificated range of centre of gravity

2.2 Engine Limitations

2.2.1 Operating data of the engines

&amp;ndash; time limits and maximum temperatures
&amp;ndash; minimum RPMs and temperatures
&amp;ndash; torque
&amp;ndash; maximum power for take-off and go-around with respect to pressure altitude/flight altitude and
temperature
&amp;ndash; piston engines: certified range of mixture
&amp;ndash; minimum and maximum oil temperature and pressure
&amp;ndash; maximum starter time and required cooling
&amp;ndash; time between two start attempts for engines and auxiliary power unit
&amp;ndash; for propeller: maximum RPM of propeller triggering of automatic feathering device.

2.2.2 Certified oil grades

2.3 Systems limitations

2.3.1 Operating data of the following systems:

&amp;ndash; pressurisation, air conditioning maximum pressures
&amp;ndash; electrical power supply, maximum load of main power system (AC or DC)
&amp;ndash; maximum time of power supply by battery in case of emergency
&amp;ndash; mach trim system and yaw damper speed limits
&amp;ndash; auto pilot limitations of various modes
&amp;ndash; ice protection
&amp;ndash; speed and temperature limits of window heat
&amp;ndash; temperature limits of engine and wing anti-ice

2.3.2 Fuel system
Certified fuel specifications, minimum and maximum pressures and temperature of the fuel

2.4 Minimum equipment list



3 PERFORMANCE, FLIGHT PLANNING

3.1 Performance

Performance calculation concerning speeds, gradients, masses in all conditions for take off, en route, approach
and landing according to the documentation available, e.g. for take-off V1, Vmbe, Vr, Vlof, V2, take-off distance,
maximum take-off mass and the required stop distance with respect to the following factors:

&amp;ndash; accelerate/stop distance
&amp;ndash; take-off run and distance available (TORA, TODA)
&amp;ndash; ground temperature, pressure altitude, slope, wind
&amp;ndash; maximum load and maximum mass (e.g. ZFM)
&amp;ndash; minimum climb gradient after engine failure
&amp;ndash; influence of snow, slush, moisture and standing water on the runway
&amp;ndash; possible single and/or dual engine failure during cruise flight
&amp;ndash; use of anti-icing systems
&amp;ndash; failure of water injection system and/or antiskid system
&amp;ndash; speeds at reduced thrust, V1, V1red, Vmbe, Vmu, Vr, Vlof, V2
&amp;ndash; safe approach speed Vref, with respect to Vmca and turbulent conditions
&amp;ndash; effects of excessive approach speed and abnormal glideslope with respect to the landing distance
&amp;ndash; minimum climb gradient during approach and landing
&amp;ndash; limiting values for a go around with minimum fuel
&amp;ndash; maximum allowable landing mass and the landing distance for the destination and alternate
aerodrome with respect to the following factors:
&amp;ndash; available landing distance
&amp;ndash; ground temperature, pressure altitude, runway slope and wind
&amp;ndash; fuel consumption to destination or alternate aerodrome
&amp;ndash; influence of moisture on the runway, snow, slush and standing water
&amp;ndash; failure of the water injection system and/or the anti skid system
&amp;ndash; influence of thrust reverser and spoilers

3.2 Flight planning

Flight planning for normal and abnormal conditions

&amp;ndash; optimum/maximum flight level
&amp;ndash; minimum required flight altitude
&amp;ndash; drift down procedure after an engine failure during cruise flight
&amp;ndash; power setting of the engines during climb, cruise and holding under various circumstances, as
well as the most economic cruising flight level
&amp;ndash; calculation of a short range/long range flight plan
&amp;ndash; optimum and maximum flight level and power setting of the engines after engine failure

4 LOAD AND BALANCE AND SERVICING

4.1 Load and Balance

&amp;ndash; load and trim sheet with respect to the maximum masses for take-off and landing
&amp;ndash; centre of gravity limits

4.1.1 influence of fuel consumption on the centre of gravity

4.1.2 lashing points, load clamping, maximum ground load

4.2 Servicing

Servicing connections for:

&amp;ndash; fuel
&amp;ndash; oil
&amp;ndash; water
&amp;ndash; hydraulic
&amp;ndash; oxygen
&amp;ndash; nitrogen
&amp;ndash; conditioned air
&amp;ndash; electric power
&amp;ndash; start air
&amp;ndash; toilet and safety r&amp;eacute;gulations

5 EMERGENCY PROCEDURES

5.1 Recognition of the situation as well as immediate memory actions in correct sequence and for those

conditions recognised as emergencies by the manufacturer and certification authority:

&amp;ndash; engine failure during take off before and after V1, as well as inflight
&amp;ndash; malfunctions of the propeller system
&amp;ndash; engine overheat, engine fire on ground and inflight
&amp;ndash; wheel well fire
&amp;ndash; electrical smoke and/or fire
&amp;ndash; rapid decompression and emergency descent
&amp;ndash; air-conditioning overheat, anti ice system overheat
&amp;ndash; fuel pump failure
&amp;ndash; fuel freezing/overheat
&amp;ndash; electric power failure
&amp;ndash; equipment cooling failure
&amp;ndash; flight instrument failure
&amp;ndash; partial or total hydraulic failure
&amp;ndash; failures at the lift devices and flight controls including boosters
&amp;ndash; cargo compartment smoke and/or fire

5.2 Actions according to the approved abnormal and emergency checklist

&amp;ndash; engine restart inflight
&amp;ndash; landing gear emergency extension
&amp;ndash; application of the emergency brake system
&amp;ndash; emergency extension of lift devices
&amp;ndash; fuel dumping
&amp;ndash; emergency descent