CAT.IDE.A.130 Operations under IFR or at night – flight and navigational instruments and associated equipment

Aeroplanes operated under VFR at night or under IFR shall be equipped with the following equipment, available at the pilot’s station:

(a)A means of measuring and displaying:

(1)Magnetic heading;

(2)Time in hours, minutes and seconds;

(3)Indicated airspeed;

(4)Vertical speed;

(5)Turn and slip, or in the case of aeroplanes equipped with a standby means of measuring and displaying attitude, slip;

(6)Attitude;

(7)Stabilised heading;

(8)Outside air temperature; and

(9)Mach number whenever speed limitations are expressed in terms of Mach number.

(b)Two means of measuring and displaying barometric altitude.

(c)A means of indicating when the supply of power to the required flight instruments is not adequate.

(d)A means for preventing malfunction of the airspeed indicating systems required in (a)(3) and (h)(2) due to condensation or icing.

(e)A means of annunciating to the flight crew the failure of the means required in (d) for aeroplanes:

(1)issued with an individual CofA on or after 1 April 1998; or

(2)issued with an individual CofA before 1 April 1998 with an MCTOM of more than 5 700 kg, and with an MOPSC of more than nine.

(f)Except for propeller-driven aeroplanes with an MCTOM of 5 700 kg or less, two independent static pressure systems.

(g)One static pressure system and one alternate source of static pressure for propeller-driven aeroplanes with an MCTOM of 5 700 kg or less.

(h)Whenever two pilots are required for the operation, a separate means of displaying for the second pilot:

(1)Barometric altitude;

(2)Indicated airspeed;

(3)Vertical speed;

(4)Turn and slip;

(5)Attitude; and

(6)Stabilised heading.

(i)A standby means of measuring and displaying attitude capable of being used from either pilot’s station for aeroplanes with an MCTOM of more than 5 700 kg or an MOPSC of more than nine that:

(1)is powered continuously during normal operation and, after a total failure of the normal electrical generating system, is powered from a source independent from the normal electrical generating system;

(2)provides reliable operation for a minimum of 30 minutes after total failure of the normal electrical generating system, taking into account other loads on the emergency power supply and operational procedures;

(3)operates independently of any other means of measuring and displaying attitude;

(4)is operative automatically after total failure of the normal electrical generating system;

(5)is appropriately illuminated during all phases of operation, except for aeroplanes with an MCTOM of 5 700 kg or less, already registered in a Member State on 1 April 1995 and equipped with a standby attitude indicator in the left-hand instrument panel;

(6)is clearly evident to the flight crew when the standby attitude indicator is being operated by emergency power; and

(7)where the standby attitude indicator has its own dedicated power supply, has an associated indication, either on the instrument or on the instrument panel, when this supply is in use.

(j)A chart holder in an easily readable position that can be illuminated for night operations.