| (1) | The operator of a Class 1 helicopter shall ensure that, in the event of the critical power unit becoming inoperative at any point during flight, appropriate to the meteorological conditions expected for the flight, the helicopter can comply with the provisions of subregulation (2) or (3) at all times. |
| (2) | The operator shall ensure that, when it is intended that the flight will be conducted at any time out of sight of the surface, the mass of the helicopter permits at any time a rate of climb of at least 50 feet per minute with one engine inoperative at the obstacle clearance altitude computed in accordance with technical standard 91.07.2. |
| (3) | The operator shall ensure that— |
| (a) | the flight path permits the helicopter to continue flight from the cruising altitude to a height of 1 000 feet above the aerodrome where a landing can be made in accordance with regulation 128.08.5; |
| (b) | the flight path clears all obstacles vertically by at the obstacle clearance margins specified in technical standard 91.07.2; |
| (c) | the engine is assumed to fail at the most critical point during the flight: |
Provided that when it is intended that the flight will be conducted by day, VMC and in sight of the surface, only obstacles within 900 meters on either side of the helicopter flight path need to be considered.
| (4) | Account shall be taken of the effects of winds on the flight path. |
| (5) | When complying with the provisions of this regulation, the width margins referred to in subregulations (2) and (3) may be reduced to 9.3 kilometres, if a navigation accuracy equivalent to that required for performance-based navigation can be achieved. |
| (6) | In the event of any two power units becoming inoperative in the case of a helicopter having three or more power units, the helicopter shall be able to continue the flight to a suitable landing site and make a landing thereat. |
