| (1) | The operator shall not operate a helicopter in accordance with IFR, unless such helicopter is equipped with— |
| (b) | an accurate time-piece on board indicating the time in hours, minutes and seconds; |
| (c) | two sensitive pressure altimeters with subscale settings, calibrated in hectopascals, adjustable for any barometric pressure setting likely to be encountered during flight; |
| (d) | in the case of a helicopter having a maximum certificated mass exceeding 3 180 kilograms or a maximum passenger seating configuration of more than 9 seats, a radio altimeter with an audio warning operating below a pre-set height and a visual warning capable of operating at a height selectable by the pilot; |
| (e) | 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; |
| (f) | a vertical-speed indicator; |
| (g) | a turn-and-slip indicator or in lieu thereof, an additional attitude indicator powered by a power source separate from that of the main attitude indicator; |
| (h) | an attitude indicator; |
| (i) | a single standby attitude indicator, capable of being used from either pilot's station, which— |
| (i) | 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; |
| (ii) | 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; |
| (iii) | operates independently of any other attitude indicating system; |
| (iv) | is operative automatically after total failure of the normal electrical generating system; and |
| (v) | 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;
| (j) | a stabilised direction indicator; |
| (k) | a means of indicating on the flight deck the outside air temperature in degrees Celsius; |
| (l) | an alternate source of static pressure for the altimeter and the airspeed and vertical speed indicators; and |
| (m) | a chart holder in an easily readable position which can be illuminated, if to be operated by night. |
| (n) | communication, navigation and surveillance equipment as prescribed in regulations 91.05.1 and 91.05.2. |
[Regulation 127.05.3(1)(n) inserted by regulation 14(a) of Notice No. R. 432, GG 40846, dated 19 May 2017 (Sixteenth Amendment of the Civil Aviation Regulations, 2017)]
| (2) | The operator shall not operate a helicopter in IMC while carrying passengers, unless such helicopter is a multi-engine helicopter certified for IMC operations and equipped with— |
| (a) | a power-failure warning device or vacuum indicator to show the power available for gyroscopic instruments from each power source; |
| (b) | two independent sources of energy (with means of selecting either), of which at least one is an engine-driven pump or generator, which are both able to drive all required gyroscopic instruments powered by, or to be powered by, that particular source and installed in such a manner that failure of one instrument or source does not interfere with the energy supply to the remaining instruments or the other energy source except where the rate-of-turn indicator of a single-engine helicopter involved in all-cargo operations only, has a source of energy separate from the bank and pitch and direction indicators. For the purpose of this subregulation, each engine-driven source of energy of a multi-engine helicopter must be on a different engine; and |
| (c) | at least two generators or alternators of which any combination of one-half of the total number are rated sufficiently to supply the electrical loads of all required instruments and equipment necessary for safe emergency operation of the helicopter (both units may be mounted on the main rotor drive train); or |
| (d) | either airborne weather radar equipment or other equipment, approved by the Director, capable of detecting thunderstorms and other potentially hazardous weather conditions. |
| (3) | If two pilots are required to operate the helicopter, other than training or testing, the second pilot'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 pitot tube or equivalent means for preventing malfunction due to either condensation or icing, including a warning indicator of pitot heater failure; |
| (c) | a vertical-speed indicator; |
| (d) | a turn-and-slip indicator, or in lieu thereof, an additional attitude indicator powered by a power source separate from that of the main attitude indicator; |
| (e) | an altitude indicator; and |
| (f) | a stabilised direction indicator. |
| (4) | In complying with the provisions of paragraph (1)(i) it shall be clearly evident to the flight crew members when such standby altitude indicator is being operated by emergency power. |
| (5) | Where the standby altitude indicator referred to in paragraph (1)(i) 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. |
| (6) | When a helicopter is operated with a single pilot in terms of regulation 127.02.1(8) while carrying passengers at night or in IMC, the helicopter shall furthermore be equipped with— |
| (a) | IFR-approved area navigation equipment that provides immediate identification and heading to the nearest suitable diversion; |
| (b) | an approved stability augmentation or automatic flight control management system; and |
| (c) | if the helicopter is fitted with a turbine engine— |
| (i) | an auto-ignition system or use of continuous ignition during take-off, landing and flight during heavy precipitation; and |
| (ii) | a manual throttle that bypasses the governing section of the fuel control unit, and permits continued unrestricted operation of the engine in the event of a fuel control unit failure. |
| (7) | With effect from 31 January 2018 helicopters operating under IFR with a maximum certificated take-off mass in excess of 3 175 kg, a maximum passenger seating configuration of more than 9, shall be equipped with a ground proximity warning system which has a forward-looking terrain avoidance function. |
