| (1) |
An air service operator shall not operate the aeroplane in accordance with IFR or at night, 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 for any barometric pressure setting likely to be encountered during flight. These altimeters must have counter drum-pointer or equivalent presentation; |
[Regulation 135.05.3(1)(c) substituted by regulation 278 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; |
[Regulation 135.05.3(1) substituted by regulation 17(f) of Notice No. R. 1349, GG 40376, dated 28 October 2016 (Fourteenth Amendment of the Civil Aviation Regulations, 2016)]
| (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) |
chart holder in an easily readable position which can be illuminated, if to be operated at night; |
| (I) |
a power-failure warning device or vacuum indicator to show the power available for gyroscopic instruments from each power source; |
| (m) |
a pressure altitude reporting transponder with a capability of providing pressure-altitude information with a resolution of 25 ft or better— |
| (i) |
for all aeroplanes for which the individual certificate of airworthiness is first issued after 1 January 2009; and |
| (ii) |
for all large turbine-engine aeroplanes after 1 January 2014; and |
| (n) |
communication, navigation and surveillance equipment as prescribed in regulations 91.05.1 and 91.05.2. |
[Regulation 135.05.3(n) inserted by regulation 16(g) of Notice No. R. 432, GG 40846, dated 19 May 2017)]
| (2) |
The operator shall not operate an aeroplane in IMC, unless such aeroplane is equipped with— |
| (a) |
in the case of a single-engine aeroplane, as provided in regulation 135.07.5; |
| (b) |
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 |
| (c) |
for all aeroplanes, at least 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 aeroplane 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 aeroplane must be on a different engine; |
| (3) |
The operator shall not operate aeroplanes required by these Regulations or the type certificate of the aeroplane to be operated by two pilots unless such aeroplanes are equipped as provided in regulation 135.05.2(2). |
| (4) |
In addition to the flight and navigation equipment referred to in subregulations (1), (2) and (3), a large aeroplane shall be equipped with a single standby attitude indicator, capable of being used from either pilot's station which— |
[Words preceding regulation 135.05.3(4) substituted by regulation 17(g) of Notice No. R. 1349, GG 40376, dated 28 October 2016 (Fourteenth Amendment of the Civil Aviation Regulations, 2016)]
| (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; |
[Regulation 135.05.2(4)(c) substituted by regulation 17(h) of Notice No. R. 1349, GG 40376, dated 28 October 2016 (Fourteenth Amendment of the Civil Aviation Regulations, 2016)]
| (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 |
[Regulation 135.05.2(4)(d) substituted by regulation 17(h) of Notice No. R. 1349, GG 40376, dated 28 October 2016 (Fourteenth Amendment of the Civil Aviation Regulations, 2016)]
| (e) |
is appropriately illuminated during all phases of operation: Provided that if the standby altitude instrument system is capable of being used through flight altitudes of 3600 of pitch and roll, the tum-and-slip indicators may be replaced by slip indicators. |
| (5) |
Where the standby altitude indicator referred to in subregulation (4) 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) |
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. |
Contingency Fees Act, 1997
