FCL.725 Requirements for the issue of class and type ratings

SYLLABUS OF THE THEORETICAL KNOWLEDGE FOR CLASS AND TYPE RATINGS I. TMGs, SE AND ME AEROPLANES

(a)Detailed listing for aircraft structure and equipment (as applicable), normal operation of systems and malfunctions:

(1)dimensions: minimum required runway width for 180 ° turn.

(2)engine, including auxiliary power unit:

(i)type of engine or engines;

(ii)in general, function of the following systems or components:

(A)engine;

(B)auxiliary power unit;

(C)oil system;

(D)storage and distribution system for fuel/energy;

(E)ignition system;

(F)starting system;

(G)engine/battery cooling system;

(H)fire-warning and fire-extinguishing system;

(I)generators and generator drives;

(J)power indication;

(K)reverse thrust;

(L)water injection.

(iii)for propeller engines, the functioning of the following systems:

(A)propeller system;

(B)feathering system.

(iv)engine/battery controls (including starter), engine instruments and indications in the cockpit, their function, interrelation and interpretation;

(v)engine operation, including APU, during engine start, start and engine malfunctions, procedures for normal operation in the correct sequence.

(3)fuel/energy system:

(i)location of the fuel tanks, fuel pumps, fuel lines to the engines, tank capacities, valves and measuring;

(ia)location of the batteries and integration into the aircraft systems;

(ii)location of the following systems:

(A)filtering;

(B)heating;

(C)fuelling and defueling/charging;

(D)dumping;

(E)venting;

(F)cooling.

(iii)in the cockpit:

(A)monitors and indicators of the fuel/energy system;

(B)quantity and flow indication, and interpretation.

(iv)procedures:

(A)fuelling/charging procedures. including distribution of fuel/energy into the various tanks/batteries;

(B)fuel supply, fuel temperature control, and fuel dumping.

(4)pressurisation and air conditioning:

(i)components of the system and protection devices;

(ii)cockpit monitors and indicators;

(iii)interpretation of the operational condition;

(iv)normal operation of the system during start, cruise, approach and landing, air-conditioning airflow and temperature control.

(5)ice and rain protection, windshield wipers and rain-repellent system:

(i)ice-protected components of the aircraft including engines, heat sources, controls and indications;

(ii)operation of the anti-icing or de-icing system during take-off, climb, cruise and descent, conditions that require the use of the protection systems;

(iii)controls and indications of the windshield wipers and rain-repellent system operation.

(6)hydraulic system:

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

(ii)controls, monitors and indicators in the cockpit, function and interrelation and interpretation of indications.

(7)landing gear:

(i)main components of the:

(A)main landing gear;

(B)nose landing gear;

(C)gear steering;

(D)wheel brake system, including anti-skid.

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

(iii)required tyre pressure, or location of the relevant placard;

(iv)controls and indicators including warning indicators in the cockpit in relation to the retraction or extension condition of the landing gear and brakes;

(v)components of the emergency extension system.

(8)flight controls and high-lift devices:

(i)(A) aileron system;

(B)elevator system;

(C)rudder system;

(D)trim system;

(E)spoiler system;

(F)lift devices;

(G)stall warning system;

(H)take-off configuration warning system;

(I)energy recuperation function.

(ii)components of the flight control system, including their functioning (from the cockpit controls to the flight control or surfaces);

(iii)controls, monitors and indicators, including warning indicators of the systems mentioned under (8)(i), interrelation and dependencies.

(9)electrical power supply:

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

(ii)location of the controls, monitors and indicators in the cockpit;

(iii)flight instruments, communication and navigation systems, main and backup power sources;

(iv)location of vital circuit breakers;

(v)generator/voltage level convertor operation and monitoring procedures of the electrical power supply.

(10)flight instruments, communication, radar and navigation equipment, autoflight and flight data recorders:

(i)visible antennae;

(ii)controls and instruments of the following equipment in the cockpit during normal operation:

(A)flight instruments;

(B)flight management systems;

(C)radar equipment, including radio altimeter;

(D)communication and navigation systems;

(E)autopilot;

(F)flight data recorder, cockpit voice recorder and data link communication recording function;

(G)TAWS;

(H)collision avoidance system;

(I)warning systems; and

(J)weather radar system, best practices for optimum use, interpretation of displayed information.

(11)cockpit, cabin and cargo compartment:

(i)operation of the exterior, cockpit, cabin and cargo compartment lighting and the emergency lighting;

(ii)operation of the cabin and cargo doors, stairs, windows and emergency exits;

(iii)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.

(12)emergency equipment operation and correct application of the following emergency equipment in the aircraft:

(i)handheld fire extinguisher;

(ii)first-aid kits;

(iii)portable oxygen equipment;

(iv)emergency ropes;

(v)life jacket;

(vi)life rafts;

(vii)emergency transmitters;

(viii)crash axes;

(ix)megaphones;

(x)emergency signals.

(13)pneumatic system:

(i)components of the pneumatic system, pressure source and actuated components;

(ii)controls, monitors and indicators in the cockpit and function of the pneumatic system;

(iii)vacuum system.

(b)Limitations:

(1)general limitations:

(i)certification of the aircraft, category of operation, noise certification and maximum and minimum performance data for all flight profiles, conditions and aircraft systems:

(A)maximum tail and crosswind-components at take-off and landing;

(B)maximum speeds for flap extension vfo;

(C)at various flap settings vfe;

(D)for landing gear operation vlo, Mlo;

(E)for extended landing gear vle, Mle;

(F)for maximum rudder deflection va, Ma;

(G)for tyres;

(H)one propeller feathered.

(ii)(A) minimum control air speed vmca;

(B)minimum control ground speed vmcg;

(C)stall speed under various conditions vso, vs1;

(D)maximum speed vne, Mne;

(E)maximum speed for normal operation vmo, Mmo;

(F)altitude and temperature limitations;

(G)stick shaker activation.

(iii)(A) maximum airport pressure altitude, runway slope;

(B)maximum taxi mass;

(C)maximum take-off mass;

(D)maximum lift-off mass;

(E)maximum landing mass;

(F)maximum zero fuel mass;

(G)maximum dumping speed vdco, Mdco, vdce, Mdce;

(H)maximum load factor during operation;

(I)certified range of centre of gravity.

(2)engine limitations (as applicable):

(i)operating data of the engines:

(A)time limits and maximum temperatures;

(B)minimum RPMs and temperatures;

(C)time limits and maximum values for take-off and go-around on pressure altitude or flight altitude and temperature for:

(1)maximum torque; and/or

(2)maximum power;

(D)piston engines: certified range of mixture;

(E)minimum and maximum oil temperature and pressure;

(F)maximum starter time and required cooling;

(G)time between two start attempts for engines and auxiliary power unit;

(H)for propeller: maximum RPM of the propeller for triggering the automatic feathering device.

(ii)certified oil grades.

(3)systems’ limitations (as applicable):

(i)operating data of the following systems:

(A)pressurisation, air conditioning maximum pressures;

(B)electrical power supply, maximum load of main power system (AC or DC);

(C)maximum time of battery power supply in case of emergency;

(D)Mach trim system and yaw damper speed limits;

(E)autopilot limitations of various modes;

(F)ice protection;

(G)speed and temperature limits of window heat;

(H)temperature limits of engine and wing anti-ice;

(I)maximum value of power recuperation.

(ii)fuel system: certified fuel specifications, minimum and maximum fuel pressures and fuel temperature.

(iii)energy system:

(A)minimum and maximum state of charge of the battery;

(B)effects of temperature on the battery and battery operating temperatures;

(C)minimum and maximum battery pack voltage;

(D)minimum state of battery health;

(E)maximum system power output with one or more batteries inoperative;

(F)maximum charging power.

(4)minimum equipment list.

(c)Performance, flight planning and monitoring (as applicable):

(1)performance calculation about speeds, gradients, masses in all conditions for take-off, en-route, approach and landing according to the documentation available (for example for take-off v1, vmbe, vr, vlof, v2, take-off distance, maximum take-off mass and the required stop distance) on the following factors:

(i)accelerate or stop distance;

(ii)take-off run and distance available (TORA, TODA);

(iii)ground temperature, pressure altitude, slope, wind;

(iv)maximum load and maximum mass (for example, ZFM);

(v)minimum climb gradient after engine failure or battery malfunction;

(vi)influence of snow, slush, moisture and standing water on the runway;

(vii)possible single or dual engine failure during cruise flight;

(viii)use of anti-icing systems;

(ix)failure of the water injection system or the anti-skid system;

(x)speeds at reduced thrust, v1, v1red, vmbe, vmu, vr, vlof, v2;

(xi)safe approach speed vref, on vmca and turbulent conditions;

(xii)effects of excessive approach speed and abnormal glideslope on the landing distance;

(xiii)minimum climb gradient during approach and landing;

(xiv)limiting values for a go-around with minimum fuel/energy;

(xv)maximum allowable landing mass and landing distance for the destination and alternate aerodrome on the following factors:

(A)landing distance available;

(B)ground temperature, pressure altitude, runway slope and wind;

(C)fuel/energy consumption to destination or alternate aerodrome;

(D)influence of moisture, snow, slush and standing water on the runway;

(E)failure of the water injection system or the anti-skid system;

(F)influence of thrust reverser and spoilers.

(2)flight planning for normal and abnormal conditions:

(i)optimum or maximum flight level;

(ii)minimum required flight altitude;

(iii)drift-down procedure after engine failure during cruise flight;

(iv)power setting of the engines during climb, cruise and holding under various circumstances, as well as the most economic cruising flight level;

(v)calculation of a short-range or long-range flight plan;

(vi)optimum and maximum flight level and power setting of the engines after engine failure;

(vii)effects of battery ageing on available energy and power.

(3)flight monitoring.

(d)Load and balance and servicing (as applicable):

(1)load and balance:

(i)load and trim sheet on the maximum masses for take-off and landing;

(ii)centre-of-gravity limits;

(iii)influence of fuel consumption on the centre of gravity;

(iv)lashing points, load clamping, maximum ground load.

(2)servicing on ground, servicing connections for:

(i)fuel/energy;

(ii)oil;

(iii)water;

(iv)hydraulic;

(v)oxygen;

(vi)nitrogen;

(vii)conditioned air;

(viii)electric power;

(ix)starter air;

(x)lavatory, galley and safety regulations.

(e)Emergency procedures (as applicable):

(1)recognition of the situation as well as immediate memory actions in the correct sequence, and for those conditions that are recognised as emergencies by the manufacturer and the competent authority for certification:

(i)engine failure/battery malfunction during take-off before and after v1, as well as in flight;

(ii)malfunctions of the propeller system;

(iii)engine/battery overheat, engine/battery fire on ground and in flight;

(iv)wheel-well fire;

(v)electrical smoke or fire;

(vi)rapid decompression and emergency descent;

(vii)air-conditioning overheat, anti-ice system overheat;

(viii)fuel pump/battery cooling system failure;

(ix)fuel freezing overheat;

(x)electric power failure;

(xi)equipment cooling failure;

(xii)flight instrument failure;

(xiii)partial or total hydraulic failure;

(xiv)failures at the lift devices and flight controls including boosters

(xv)cargo compartment smoke or fire.

(2)actions according to the approved checklist for abnormal and emergency procedures:

(i)engine restart in flight;

(ii)landing gear emergency extension;

(iii)application of the emergency brake system;

(iv)emergency extension of lift devices;

(v)fuel dumping;

(vi)emergency descent.

(f)Special requirements for ‘glass cockpit’ aircraft with EFIS additional learning objectives:

(1)general rules for aircraft computer hardware and software design;

(2)logic of all flight crew information and alerting systems and their limitations;

(3)interaction of the different aircraft computer systems, their limitations, the possibilities of computer fault recognition, and the actions to be performed on computer failures;

(4)normal procedures including all flight crew coordination duties;

(5)aircraft operation with different computer degradations (basic flying).

(g)Flight management systems.

II. SE AND ME HELICOPTERS

(a)Detailed listing for helicopters structure, transmissions, rotors and equipment, normal and abnormal operation of systems:

(1)dimensions.

(2)engine including aux. power unit, rotor and transmissions; if an initial type rating for a turbine engine helicopter is applied for, the applicant should have received turbine engine instruction:

(i)type of engine or engines;

(ii)in general, the function of the following systems or components:

(A)engine;

(B)auxiliary power unit;

(C)oil system;

(D)fuel system;

(E)ignition system;

(F)starting system;

(G)fire warning and extinguishing system;

(H)generators and generator drive;

(I)power indication;

(J)water or methanol injection.

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

(iv)engine operation, including APU, during engine start and engine malfunctions, procedures for normal operation in the correct sequence;

(v)transmission system:

(A)lubrication;

(B)generators and generator drives;

(C)freewheeling units;

(D)hydraulic drives;

(E)indication and warning systems.

(vi)type of rotor systems: indication and warning systems.

(3)fuel system:

(i)location of the fuel tanks, fuel pumps, fuel lines to the engines tank capacities, valves and measuring;

(ii)the following systems:

(A)filtering;

(B)fuelling and defuelling heatings;

(C)dumping;

(D)transferring;

(E)venting.

(iii)in the cockpit: the monitors and indicators of the fuel system, quantity and flow indication, interpretation;

(iv)fuel procedures distribution into the various tanks fuel supply and fuel dumping.

(4)air conditioning:

(i)components of the system and protection devices;

(ii)cockpit monitors and indicators; Note: interpretation about the operational condition: normal operation of the system during start, cruise approach and landing, air conditioning airflow and temperature control.

(5)ice and rain protection, windshield wipers and rain repellent:

(i)ice protected components of the helicopter, including engines and rotor systems, heat sources, controls and indications;

(ii)operation of the anti-icing or de-icing system during take-off, climb, cruise and descent, conditions requiring the use of the protection systems;

(iii)controls and indications of the windshield wipers and rain repellent system operation.

(6)hydraulic system:

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

(ii)controls, monitors and indicators in the cockpit, function and interrelation and interpretation of indications.

(7)landing gear, skids fixed and floats:

(i)main components of the:

(A)main landing gear;

(B)nose gear;

(C)tail gear;

(D)gear steering;

(E)wheel brake system.

(ii)gear retraction and extension;

(iii)required tyre pressure, or location of the relevant placard;

(iv)controls and indicators including warning indicators in the cockpit in relation to the retraction or extension condition of the landing gear;

(v)components of the emergency extension system.

(8)flight controls, stab- and autopilot systems: controls, monitors and indicators including warning indicators of the systems, interrelation and dependencies.

(9)electrical power supply:

(i)number, power, voltage, frequency and if applicable phase and location of the main power system (AC or DC) auxiliary power system location and external power system;

(ii)location of the controls, monitors and indicators in the cockpit;

(iii)main and back-up power sources flight instruments, communication and navigation systems, main and back-up power sources;

(iv)location of vital circuit breakers;

(v)generator operation and monitoring procedures of the electrical power supply.

(10)flight instruments, communication, radar and navigation equipment, autoflight and flight data recorders:

(i)antennas;

(ii)controls and instruments of the following equipment in the cockpit:

(A)flight instruments (for example air speed indicator, pitot static system, compass system, flight director);

(B)flight management systems;

(C)radar equipmentt, including radio;

(D)communication and navigation system (for example HF, VHF, ADF, VOR/DME, ILS, marker beacon) and area navigation systems;

(E)stabilisation and autopilot system;

(F)flight data recorder, cockpit voice recorder, data-link communication recording function and radio altimeter;

(G)collision avoidance system;

(H)TAWS;

(I)HUMSS;

(J)weather radar system, best practices for optimum use, interpretation of displayed information.

(11)cockpit, cabin and cargo compartment:

(i)operation of the exterior, cockpit, cabin and cargo compartment lighting and the emergency lighting;

(ii)operation of the cabin doors and emergency exits.

(12)emergency equipment:

(i)operation and correct application of the following mobile emergency equipment in the helicopter:

(A)portable fire extinguisher;

(B)first-aid kits;

(C)portable oxygen equipment;

(D)emergency ropes;

(E)life-jacket;

(F)life rafts;

(G)emergency transmitters;

(H)crash axes;

(I)megaphones;

(J)emergency signals;

(K)torches.

(ii)operation and correct application of the fixed emergency equipment in the helicopter: emergency floats.

(b)Limitations:

(1)general limitations, according to the helicopter flight manual;

(2)minimum equipment list.

(c)Performance, flight planning and monitoring:

(1)performance calculation about speeds, gradients, masses in all conditions for take-off, en-route, approach and landing:

(i)take-off:

(A)hover performance in and out of ground effect;

(B)all approved profiles, cat A and B;

(C)HV diagram;

(D)take-off and rejected take-off distance;

(E)take-off decision point (TDP) or (DPATO);

(F)calculation of first and second segment distances;

(G)climb performance.

(ii)en-route:

(A)air speed indicator correction;

(B)service ceiling;

(C)optimum or economic cruising altitude;

(D)max endurance;

(E)max range;

(F)cruise climb performance.

(iii)landing:

(A)hovering in and out of ground effect;

(B)landing distance;

(C)landing decision point (LDP) or (DPBL).

(iv)knowledge or calculation of: vlo, vle, vmo, vx, vy, vtoss, vne, vmax range, vmini.

(2)flight planning for normal and abnormal conditions:

(i)optimum or maximum flight level;

(ii)minimum required flight altitude;

(iii)drift down procedure after an engine failure during cruise flight;

(iv)power setting of the engines during climb, cruise and holding under various circumstances as well as at the most economic cruising flight level;

(v)optimum and maximum flight level and power setting after an engine failure.

(3)effect of optional equipment on performance.

(d)Load, balance and servicing:

(1)load and balance:

(i)load and trim sheet on the maximum masses for take-off and landing;

(ii)centre of gravity limits;

(iii)influence of the fuel consumption on the centre of gravity;

(iv)lashing points, load clamping, max ground load.

(2)servicing on the ground, servicing connections for:

(i)fuel;

(ii)oil, etc.;

(iii)and safety regulations for servicing.

(e)Emergency procedures.

(f)Special requirements for helicopters with EFIS.

(g)Optional equipment.

III. AIRSHIPS

(a)Detailed listing for airship structure and equipment, normal operation of systems and malfunctions:

(1)dimensions;

(2)structure and envelope:

(i)internal structure;

(ii)envelope;

(iii)pressure system;

(iv)gondola;

(v)empennage.

(3)flight controls;

(4)systems:

(i)hydraulic;

(ii)pneumatic.

(5)landing gear;

(6)fuel system;

(7)fire warning and extinguishing system;

(8)emergency equipment;

(9)electrical systems;

(10)avionics, radio navigation and communication equipment;

(11)instrumentation;

(12)engines and propellers;

(13)heating, ventilation and air-condition;

(14)operational procedures during start, cruise, approach and landing:

(i)normal operations;

(ii)abnormal operations.

(b)Limitations:

(1)general limitations:

(i)certification of the airship, category of operation, noise certification and maximum and minimum performance data for all flight profiles, conditions and aircraft systems;

(ii)speeds;

(iii)altitudes.

(2)engine limitations;

(3)systems limitations;

(4)minimum equipment list.

(c)Performance and flight planning:

(1)performance calculation;

(2)flight planning.

(d)Load and balance and servicing:

(1)load and balance;

(2)servicing.

(e)Emergency procedures:

(1)recognition of emergency situations;

(2)actions according

TRAINING COURSE FLIGHT INSTRUCTION FOR TYPE RATINGS: HELICOPTERS

(a)The amount of flight instruction depends on:

(i)complexity of the helicopter type, handling characteristics, level of technology;

(ii)category of helicopter (SEP or SE turbine helicopter, ME turbine and MP helicopter);

(iii)previous experience of the applicant;

(iv)the availibiliy of FSTDs.

(b)FSTDs In accordance with Appendix 9 to Part-FCL Section A paragraph 1 third subparagraph, the level of qualification and the complexity of the type will determine the amount of practical training that may be accomplished in FSTDs, including completion of the skill test. Before undertaking the skill test, a student should demonstrate competency in the skill test items during the practical training.

(c)Initial issue The flight instruction (excluding skill test) should comprise training time as specified in column 2 in the table below unless otherwise foreseen in the operational suitability data established in accordance with Annex I (Part 21) to Commission Regulation (EU) No 748/2012 (OSD). If, in accordance with Appendix 9 to Part-FCL Section A paragraph 1c, training is conducted in a combination of FSTDs (other than FFS) and the helicopter, the in-aircraft training time will depend on the specificities of the FSTD used. In such a case, in-aircraft training time should comprise, as a minimum, the training time given in column 3 of the table below unless otherwise foreseen in the OSD. The minimum training time given in column 2 may include the time of the take-off and landing training referred to in Appendix 9 to Part-FCL Section A paragraph 1a.

(d)Additional types The flight instruction (excluding the skill test) should comprise training time as specified in column 2 in the table below unless otherwise foreseen in the OSD. If, in accordance with Appendix 9 to Part-FCL Section A paragraph 1c, training is conducted in a combination of FSTDs (other than FFS) and the helicopter, the in-aircraft training time will depend on the specificities of the FSTD used. In such a case, in-aircraft training time should comprise, as a minimum, the time given in column 3 of the table below unless otherwise foreseen in the OSD. The minimum training time given in column 2 may include the time of the take-off and landing training referred to in Appendix 9 to Part-FCL Section A paragraph 1a.

MULTI-PILOT OPERATION IN SINGLE-PILOT AEROPLANES OR HELICOPTERS IN ACCORDANCE WITH ANNEX III (PART-ORO) TO REGULATION (EU) No 965/2012 Points FCL.725(d)(1)(iii)(B) and FCL.725(d)(da)(3) require pilots to exercise their type or class rating privileges for multi-pilot operation in single-pilot aeroplanes or helicopters only in accordance with the requirements of Part-ORO, to ensure that pilots conduct multi-pilot operation in single-pilot aircraft only in accordance with approved operational procedures of an operator that is subject to Part-ORO. As a consequence, an ATO that provides training for multi-pilot operation in single-pilot aeroplanes or helicopters will need to base that training on the operational procedures of the operator for which the pilot is flying. That ATO will either be an operator itself or will have an arrangement with an operator on behalf of which the training will be carried out.

The hours gained during the instruction flights for category 1 or 2 flight tests are not considered as flight tests related to development, certification or production.