Publication: Magyar Közlöny
Issue: MK-2009-104 (Year: 2009, Number: 104)
Era: 2004-2010
Section: 
Paragraph Index: 1424

4. Limitations resulting from performance 4.1 Operations in performance Class 1 4.1.1 Take-off 4.1.1.1 The take-off mass of the helicopter should not exceed the maximum take-off mass specified in the flight manual for the procedure to be used and to achieve a rate of climb of 100 ft/min at 60 m (200 ft) and 150 ft/min at 300 m (1 000 ft) above the level of the heliport with the critical engine inoperative and the remaining power-units operating at an appropriate power rating, taking into account the parameters specified in 2.2 (Figure A-1). 4.1.1.2 Rejected take-off The take-off mass should be such that the rejected take-off distance required does not exceed the rejected take-off distance available. 4.1.1.3 Take-off distance The take-off mass should be such that the take-off distance required does not exceed the take-off distance available. Note 1.— As an alternative, the requirement above may be disregarded provided that the helicopter with the critical power-unit failure recognized at TDP can, when continuing the take-off, clear all obstacles from the end of the take-off distance available to the end of the take-off distance required by a vertical margin of not less than 10.7 m (35 ft) (Figure A-2). Note 2.— For elevated heliports, the airworthiness code provides appropriate clearance from the elevated heliport edge (Figure A-3). 4.1.1.4 Backup procedures (or procedures with lateral transition) An operator should ensure that, with the critical power-unit inoperative, all obstacles below the backup flight path (the lateral flight path) are cleared by an adequate margin. Only the obstacles specified in 2.4.2 should be considered. 4.1.2 Take-off flight path From the end of the take-off distance required with the critical power-unit inoperative: 4.1.2.1 The take-off mass should be such that the climb path provides a vertical clearance of not less than 10.7 m (35 ft) for VFR operations and 10.7 m (35 ft) plus 0.01 DR for IFR operations above all obstacles located in the climb path. Only obstacles as specified in 2.4 should be considered. 4.1.2.2 Where a change of direction of more than 15 degrees is made, obstacle clearance requirements should be increased by 5 m (15 ft) from the point at which the turn is initiated. This turn should not be initiated before reaching a height of 60 m (200 ft) above the take-off surface, unless permitted as part of an approved procedure in the flight manual. 4.1.3 En route The take-off mass is such that it is possible, in case of the critical power-unit failure occurring at any point of the flight path, to continue the flight to an appropriate landing site and achieve the minimum flight altitudes for the route to be flown. Annex 6 — Operation of Aircraft Part III 22/11/07 ATT A-8 Figure A-1 PERFORMANCE CLASS 1 SURFACE LEVEL HELIPORT TAKE-OFF >10.7 m + 0.01 DR** (Obstacle) Normal take-off TDP One e ngi ne in op er at iv e VTOSS 10.7 m Rejected take-off distance required Take-off distance required Take-off distance available Rejected take-off distance available DR HELICOPTER CLEARWAY 7R, 10R, 300 m or 900 m * FATO SAFETY AREA * Half of the minimum FATO width defined in the HFM (or when no width defined, 0.75 D) + 0.25 D (or 3 m, whichever is greater) for VFR operations 1.5 D (or 30 m, whichever is greater) for IFR operations ** 10.7 m for VFR operations 10.7 m + 0.01 DR for IFR operations 10, 15 or 30% Attachment A Annex 6 — Operation of Aircraft ATT A-9 22/11/07 Figure A-2 * * Half of the minimum FATO width defined in the HFM (or when no width defined, 0.75 D) + 0.25 D (or 3 m, whichever is greater) for VFR operations 1.5 D (or 30 m, whichever is greater) for IFR operations ** 10.7 m for VFR operations 10.7 m + 0.01 DR for IFR operations SURFACE LEVEL HELIPORT (Alternative presented in Note 1 to 4.1.1.3) TAKE-OFF Take-off distance required Take-off distance available Rejected take-off distance available Normal take-off One engine inope rative Annex 6 — Operation of Aircraft Part III 22/11/07 ATT A-10 Figure A-3 * Half of the minimum FATO width defined in the HFM (or when no width defined, 0.75 D) + 0.25 D (or 3 m, whichever is greater) for VFR operations 1.5 D (or 30 m, whichever is greater) for IFR operations ** 10.7 m for VFR operations 10.7 m + 0.01 DR for IFR operations Normal take-off One engine inoperative Attachment A Annex 6 — Operation of Aircraft ATT A-11 22/11/07 4.1.4 Approach, landing and balked landing (Figures A-4 and A-5) The estimated landing mass at the destination or alternate should be such that:

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