| (1) | An air service operator shall not operate an aeroplane in accordance with IFR, unless such aeroplane is equipped with— |
| (b) | an accurate time-piece showing the time in hours, minutes and seconds; |
| (c) | two sensitive pressure altimeters with subscale settings, calibrated in hectopascals, adjustable any barometric pressure setting likely to be encountered during flight. These altimeters must have counter drum-pointer or equivalent presentation; |
[Regulation 121.05.3(1)(c) substituted by regulation 19 of Notice No. R. 535, GG 36712, dated 30 July 2013 (Fourth Amendment to the Civil Aviation Regulations, 2013)]
| (d) | an airspeed indicator system with heated pitot tube or equivalent means for preventing malfunctioning due to either condensation or icing, including a warning indicator of pitot heater failure; |
| (e) | a vertical-speed indicator; |
| (f) | a turn-and-slip indicator or a turn co-ordinator, incorporating a slip indicator; |
| (g) | an attitude indicator; |
| (h) | a stabilised direction indicator; |
| (i) | a means of indicating on the flight deck the outside air temperature in degrees Celsius; |
| (j) | an alternate source of static pressure for the altimeter and the airspeed and verticalspeed indicators; |
| (k) | a chart holder in an easily readable position which can be illuminated, if to be operated at night; |
| (I) | a means of indicating whether the power supply to the gyroscopic instrument is adequate; |
| (m) | in the case of a multi-engine aeroplane, at least two independent electrical generating systems each operated by separate engines and individually capable of powering all required instruments and equipment necessary for safe emergency operation of the aeroplane; and |
| (n) | in the case of the pressure altitude reporting transponder specified in regulation 91.04.5(1)(l)— |
| (i) | all aeroplanes for which the individual certificate of airworthiness is first issued after 1 January 2009 shall be equipped with a data source that provides pressure-altitude information with a resolution of 25 ft or better; and |
| (ii) | after 1 July 2012, all aeroplanes shall be equipped with a data source that provides pressure-altitude information with a resolution of 25ft or better; |
| (o) | communication, navigation and surveillance equipment as prescribed in regulations 91.05.1 and 91.05.2; |
[Regulation 121.05.3(1)(o) inserted by regulation 13(g) of Notice No. R. 432, GG 40846, dated 19 May 2017 (Sixteenth Amendment of the Civil Aviation Regulations, 2017)]
| (2) | The second-in-command's station shall be equipped with— |
| (a) | a sensitive pressure altimeter with a subscale setting, calibrated in hectopascals, adjustable for any barometric pressure setting likely to be encountered during flight, which may be one of the two altimeters required under subregulation (1)(c); |
| (b) | an airspeed indicator system with heated pilot tube or equivalent means for preventing malfunction due to either condensation or icing; |
| (c) | a vertical-speed indicator; |
| (d) | a turn-and-slip indicator or a turn coordinator, incorporating a slip indicator; |
| (e) | an altitude indicator; and |
| (f) | a stabilised direction indicator. |
| (3) | In addition to the flight and navigation equipment referred to in subregulations (1) and (2), an aeroplane shall be equipped with a single standby attitude indicator, capable of being used from either pilot's station which— |
| (a) | is powered continuously during normal operation and, after a total failure of the normal electrical generating system is powered from a source independent of the normal electrical generating system; |
| (b) | 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; |
| (c) | operates independently of any other attitude indicating system; |
| (d) | is operative automatically after total failure of the normal electrical generating system and provides a clear indication on the instrument panel that the attitude indicator(s) is or are being operated by emergency power; and |
| (e) | is appropriately illuminated during all phases of operation, |
Provided that if the standby attitude instrument system is capable of being used through flight attitudes of 360° of pitch and roll, the turn-and-slip indicators may be replaced by slip indicators.
| (4) | Where the standby attitude indicator referred to in subregulation (3) has its own dedicated power supply, there shall be an associated indicator, either on the instrument or instrument panel, when such power supply is in use. |
| (5) | Instruments that are used by any pilot shall be so arranged as to permit the pilot to see their indications readily from his or her station with the minimum practicable deviation from the position and line of vision normally assumed when looking forward along the flight path. |
