The never exceed speed VNE of a helicopter as specified in the flight manual ?
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The part of the take off path during which in a helicopter of Performance Class 2 an engine failure would result in a forced landing must be flown in ?
The ratio in the same units and expressed as a percentage of 'Change in height' divided by 'Horizontal distance travelled' means ?
The responsibility ensuring that performance claimed a helicopter can be achieved belongs to Conditions of weather light in which a safe landing possible. The 'climb gradient' defined as ratio expressed as a percentage of change in geometric height divided the horizontal distance traveled gradient = (change in height/horizontal distance) x 100% for small angles of climb you can use rate of climb / true airspeed but this not exact definition of 'climb gradient'. 
The speed maximum endurance Is always lower than speed maximum specific range. The 'climb gradient' defined as ratio expressed as a percentage of change in geometric height divided the horizontal distance traveled gradient = (change in height/horizontal distance) x 100% for small angles of climb you can use rate of climb / true airspeed but this not exact definition of 'climb gradient'. 
The speed maximum rate of climb Will be higher than speed best angle of climb. The 'climb gradient' defined as ratio expressed as a percentage of change in geometric height divided the horizontal distance traveled gradient = (change in height/horizontal distance) x 100% for small angles of climb you can use rate of climb / true airspeed but this not exact definition of 'climb gradient'. 
Other factors remaining constant and not limiting how does increasing pressure altitude affect allowable take off mass Allowable take off mass decreases. Density decreases with altitude less density will reduce take off thrust available allowable take off mass will decrease. Question 98-8
The service ceiling of a helicopter Higher in translation than in hover out of ground effect (oge). Density decreases with altitude less density will reduce take off thrust available allowable take off mass will decrease. Question 98-9
What the correct statement concerning performance class 3 Ops are only conducted at daytime to/from helidecks elevated heliports. Density decreases with altitude less density will reduce take off thrust available allowable take off mass will decrease. Question 98-10
The take off weight the weight of helicopter At start of take off. Density decreases with altitude less density will reduce take off thrust available allowable take off mass will decrease. Question 98-11
The take off path of a helicopter from start of take off extends to a point above take off surface which At start of take off. Density decreases with altitude less density will reduce take off thrust available allowable take off mass will decrease. Question 98-12
The todrh the horizontal distance required between start of take off and point where take off safety speed reached as well as a height of 35 ft above take off surface a positive climb gradient in case of failure of critical engine. Density decreases with altitude less density will reduce take off thrust available allowable take off mass will decrease. Question 98-13
Tlof means An area touch down lift off. Density decreases with altitude less density will reduce take off thrust available allowable take off mass will decrease. Question 98-14
When calculating take off performaces of a performance class 2 helicopter without a precise wind measuring equipment following must be considered Maximum 5 % of reported headwind. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-15
Vx means speed Maximum 5 % of reported headwind. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-16
What the abbreviation the term 'never exceed spee Maximum 5 % of reported headwind. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-17
What does abbreviation 'oei' mean One engine inoperative. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-18
What does abbreviation 'vle' mean Maximum landing gear extended speed. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-19
What does abbreviation 'vlo' mean Maximum landing gear operating speed. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-20
What effect does temperature have on performance limited take off mass Rising temperatures will lower performance limited take off mass. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-21
What the abbreviation the term 'maximum landing gear extended spee Rising temperatures will lower performance limited take off mass. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-22
What the abbreviation the term 'maximum landing gear operating spee Rising temperatures will lower performance limited take off mass. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-23
The main difference between category a and category b helicopters Category a has guaranteed stay up capability category b has not. cat a definition a multi engined helicopter designed with engine system isolation features specified in applicable certification specification capable of operations using take off landing data scheduled under a critical engine failure concept that assures adequate designated surface area adequate performance capability continued safe flight or safe rejected take off in event of engine failure cat b definition a single engined or multi engined helicopter that does not meet category a standards category b helicopters have no guaranteed capability to continue safe flight in event of an engine failure unscheduled landing assumed. Question 98-24
What the abbreviation the term 'speed best rate of climb' Category a has guaranteed stay up capability category b has not. cat a definition a multi engined helicopter designed with engine system isolation features specified in applicable certification specification capable of operations using take off landing data scheduled under a critical engine failure concept that assures adequate designated surface area adequate performance capability continued safe flight or safe rejected take off in event of engine failure cat b definition a single engined or multi engined helicopter that does not meet category a standards category b helicopters have no guaranteed capability to continue safe flight in event of an engine failure unscheduled landing assumed. Question 98-25
What the abbreviation the term 'take off safety spee Category a has guaranteed stay up capability category b has not. cat a definition a multi engined helicopter designed with engine system isolation features specified in applicable certification specification capable of operations using take off landing data scheduled under a critical engine failure concept that assures adequate designated surface area adequate performance capability continued safe flight or safe rejected take off in event of engine failure cat b definition a single engined or multi engined helicopter that does not meet category a standards category b helicopters have no guaranteed capability to continue safe flight in event of an engine failure unscheduled landing assumed. Question 98-26
What the effect of tail wind on time to climb to a given altitude The time to climb does not change. cat a definition a multi engined helicopter designed with engine system isolation features specified in applicable certification specification capable of operations using take off landing data scheduled under a critical engine failure concept that assures adequate designated surface area adequate performance capability continued safe flight or safe rejected take off in event of engine failure cat b definition a single engined or multi engined helicopter that does not meet category a standards category b helicopters have no guaranteed capability to continue safe flight in event of an engine failure unscheduled landing assumed. Question 98-27
When allowing a helicopter to descend to a level which can be maintained on remaining power units this tecnique called The time to climb does not change. cat a definition a multi engined helicopter designed with engine system isolation features specified in applicable certification specification capable of operations using take off landing data scheduled under a critical engine failure concept that assures adequate designated surface area adequate performance capability continued safe flight or safe rejected take off in event of engine failure cat b definition a single engined or multi engined helicopter that does not meet category a standards category b helicopters have no guaranteed capability to continue safe flight in event of an engine failure unscheduled landing assumed. Question 98-28
When calculating landing weight of a performance class 2 helicopter with one engine inoperative following must be considered 5 % of forecast headwind. cat pol h 105 general c) when showing compliance with requirements of this section account shall be taken of following parameters 1) mass of helicopter 2) helicopter configuration 3) environmental conditions in particular i) pressure altitude temperature ii) wind a) except as provided in (c) take off take off flight path landing requirements accountability wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b) where take off landing with a tailwind component permitted in afm in all cases the take off flight path not less than 150% of any reported tailwind component shall be taken into account and c) where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing wind components in excess of 50% may be established the operator provided that operator demonstrates to competent authority that proximity to fato accuracy enhancements of wind measuring equipment provide an equivalent level of safety 4) operating techniques and 5) operation of any systems that have an adverse effect on performance. Question 98-29
When calculating performance of a class 2 helicopter with one engine inoperative on approach to land following must be considered The pressure altitude. annex 6 operation of aircraft (helicopter) to determine performance of helicopter account should be taken of at least following factors a) mass of helicopter b) elevation or pressure altitude temperature and c) wind take off landing accountability wind should be no more than 50 per cent of any reported steady headwind component of 5 knots or more where take off landing with a tailwind component permitted in flight manual not less than 150 per cent of any reported tailwind component should be allowed where precise wind measuring equipment enables accurate measurement of wind velocity over point of take off landing these values may be varied. Question 98-30
When considering take off path a helicopter with performance class 2 aircraft must clear all obstacles vertically The pressure altitude. cat pol h 210 take off flight path a) from end of todrh with critical engine failure recognised at tdp 1) the take off mass shall be such that take off flight path provides a vertical clearance above all obstacles located in climb path 'of not less than 10 7 m (35 ft) operations under vfr' 10 7 m (35 ft) + 0 01 x distance dr operations under ifr todrh take off distance required tdp take off decision point cows are moving obstacles. Question 98-31
When en route in a performance class 1 helicopter which has had an engine failure mass of aircraft must be such that a rate of climb may be achieved and maintained when not visual with surface that rate of climb 5 ft/min at an altitude of 2 ft in mountainous areas. cat pol h 210 take off flight path a) from end of todrh with critical engine failure recognised at tdp 1) the take off mass shall be such that take off flight path provides a vertical clearance above all obstacles located in climb path 'of not less than 10 7 m (35 ft) operations under vfr' 10 7 m (35 ft) + 0 01 x distance dr operations under ifr todrh take off distance required tdp take off decision point cows are moving obstacles. Question 98-32
When landing a performance class 2 helicopter with one engine inoperative aircraft must be able to carry out a balked landing and clear all obstacles vertically 5 ft/min at an altitude of 2 ft in mountainous areas. cat pol h 325 (pc2) to cat pol h 220 landing a) the landing mass of helicopter at estimated time of landing shall not exceed maximum mass specified in afm the procedure to be used b) in event of critical engine failure being recognised at any point at or before landing decision point (ldp) it possible either to land stop within fato or to perform a balked landing clear all obstacles in flight path a vertical margin of 10 7 m (35 ft) . Question 98-33
When landing at an elevated heliport a helicopter with performance class 1 and one engine inoperative must be able to land within ldah or if carrying out a balked approach must clear vertically fato 5 ft/min at an altitude of 2 ft in mountainous areas. the balked landing at an elevated heliport may be accomplished using drop down techniques in order to accelerate to vtoss as drop down carried out beyond dimensions of heliport an obstacle clearance margin of at least 15 ft required 15 ft = 4 5 m vtoss take off safety speed. Question 98-34
When planning landing a performance class 1 helicopter following information must be considered Any expected change in mass during flight. The mass of a helicopter will change when lifting carrying cargo dropping off or picking up passengers (in addition to decrease in mass due to fuel consumption). Question 98-35
When planning obstacle avoidance on take off path of a performance class 1 helicopter which has suffered an engine failure consideration need not be given to obstacles which are nearer than 7 x rotor radius (r) day operations. cat pol h 110 obstacle accountability c) obstacles may be disregarded if they are situated beyond 1) 7 x rotor radius (r) day operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 2) 10 x r night operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 3) 300 m if navigational accuracy can be achieved appropriate navigation aids or 4) 900 m in all other cases. Question 98-36
Where an official 'fuel flow chart' found In 'helicopter flight manua. cat pol h 110 obstacle accountability c) obstacles may be disregarded if they are situated beyond 1) 7 x rotor radius (r) day operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 2) 10 x r night operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 3) 300 m if navigational accuracy can be achieved appropriate navigation aids or 4) 900 m in all other cases. Question 98-37
Which of following factors has greatest effect on take off power In 'helicopter flight manua. cat pol h 110 obstacle accountability c) obstacles may be disregarded if they are situated beyond 1) 7 x rotor radius (r) day operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 2) 10 x r night operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 3) 300 m if navigational accuracy can be achieved appropriate navigation aids or 4) 900 m in all other cases. Question 98-38
Which of following groups of conditions are most favourable take off Low airfield elevation low humidity low temperature high atmospheric pressure. cat pol h 110 obstacle accountability c) obstacles may be disregarded if they are situated beyond 1) 7 x rotor radius (r) day operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 2) 10 x r night operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 3) 300 m if navigational accuracy can be achieved appropriate navigation aids or 4) 900 m in all other cases. Question 98-39
Why vne stated as an operating limitation 1 aerodynamic limitation2 engine performance limitation3 noise level related limitation4 structural limitation5 atc limitationwhich of following groups all correct answers Low airfield elevation low humidity low temperature high atmospheric pressure. cat pol h 110 obstacle accountability c) obstacles may be disregarded if they are situated beyond 1) 7 x rotor radius (r) day operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 2) 10 x r night operations if it assured that navigational accuracy can be achieved reference to suitable visual cues during climb 3) 300 m if navigational accuracy can be achieved appropriate navigation aids or 4) 900 m in all other cases. Question 98-40
With one engine inoperative a helicopter with performance class 1 when landing at an elevated heliport must be able to clear all obstacles vertically beyond fato Low airfield elevation low humidity low temperature high atmospheric pressure. cat pol h 220 landing b) in event of critical engine failure being recognised at any point at or before landing decision point (ldp) it possible either to land stop within fato or to perform a balked landing clear all obstacles in flight path a vertical margin of 10 7 m (35 ft) .
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