Question 128-1 : What does the abbreviation 'oei' mean ? [ Preparation civilian ]

Question 128-2 : What does the abbreviation 'vle' mean ?

Maximum landing gear extended speed.

Question 128-3 : What does the abbreviation 'vlo' mean ?

Maximum landing gear operating speed.

Question 128-4 : What effect does temperature have on the performance limited take off mass ?

Rising temperatures will lower the performance limited take off mass.

Question 128-5 : What is the abbreviation for the term 'maximum landing gear extended speed' ?

Vle.

Question 128-6 : What is the abbreviation for the term 'maximum landing gear operating speed' ?

Vlo.

Question 128-7 : The main difference between category a and category b helicopters is ?

Category a has guaranteed stay up capability category b has not.

Cat a definition a multi engined helicopter designed with engine and system isolation features specified in the applicable certification specification and capable of operations using take off and landing data scheduled under a critical engine failure concept that assures adequate designated surface area and adequate performance capability for continued safe flight or safe rejected take off in the 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 the event of an engine failure and unscheduled landing is assumed

Question 128-8 : What is the abbreviation for the term 'speed for best rate of climb' ?

Vy.

Question 128-9 : What is the abbreviation for the term 'take off safety speed' ?

Vtoss.

Question 128-10 : What is the effect of tail wind on the time to climb to a given altitude ?

The time to climb does not change.

Question 128-11 : When allowing a helicopter to descend to a level which can be maintained on the remaining power units this tecnique is called ?

Drift down.

Question 128-12 : When calculating the landing weight of a performance class 2 helicopter with one engine inoperative the following must be considered ?

50% of the forecast headwind.

Catpolh105 general c when showing compliance with the requirements of this section account shall be taken of the following parameters 1 mass of the helicopter 2 the helicopter configuration 3 the environmental conditions in particular i pressure altitude and temperature ii wind a except as provided in c for take off take off flight path and landing requirements accountability for wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b where take off and landing with a tailwind component is permitted in the afm and in all cases for 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 the point of take off and landing wind components in excess of 50% may be established by the operator provided that the operator demonstrates to the competent authority that the proximity to the fato and accuracy enhancements of the wind measuring equipment provide an equivalent level of safety 4 the operating techniques and5 the operation of any systems that have an adverse effect on performance

Question 128-13 : When calculating the performance of a class 2 helicopter with one engine inoperative on the approach to land the following must be considered ?

The pressure altitude.

Annex 6 operation of aircraft helicopter to determine the performance of the helicopter account should be taken of at least the following factors a mass of the helicopter b elevation or pressure altitude and temperature andc wind for take off and landing accountability for wind should be no more than 50 per cent of any reported steady headwind component of 5 knots or more where take off and landing with a tailwind component is permitted in the 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 the point of take off and landing these values may be varied

Question 128-14 : When considering the take off path for a helicopter with performance class 2 the aircraft must clear all obstacles vertically by ?

35 ft in vfr.

Catpolh210 take off flight path a from the end of the todrh with the critical engine failure recognised at the tdp1 the take off mass shall be such that the take off flight path provides a vertical clearance above all obstacles located in the climb path 'of not less than 107 m 35 ft for operations under vfr' and 107 m 35 ft + 001 x distance dr for operations under ifrtodrh take off distance requiredtdp take off decision point 702cows are moving obstacles

Question 128-15 : When en route in a performance class 1 helicopter which has had an engine failure the mass of the aircraft must be such that a rate of climb may be achieved and maintained when not visual with the surface that rate of climb is ?

50 ftmin at an altitude of 2000 ft in mountainous areas.

Question 128-16 : When landing a performance class 2 helicopter with one engine inoperative the aircraft must be able to carry out a balked landing and clear all obstacles vertically by ?

35 ft.

Catpolh325 pc2 to catpolh220 landing a the landing mass of the helicopter at the estimated time of landing shall not exceed the maximum mass specified in the afm for the procedure to be usedb in the event of the critical engine failure being recognised at any point at or before the landing decision point ldp it is possible either to land and stop within the fato or to perform a balked landing and clear all obstacles in the flight path by a vertical margin of 107 m 35 ft 694

Question 128-17 : When landing at an elevated heliport a helicopter with performance class 1 and one engine inoperative must be able to land within the ldah or if carrying out a balked approach must clear vertically the fato by ?

45 m.

Img692the balked landing at an elevated heliport may be accomplished using drop down techniques in order to accelerate to vtoss as the drop down is carried out beyond the dimensions of the heliport an obstacle clearance margin of at least 15 ft is required15 ft = 45 mvtoss take off safety speed

Question 128-18 : When planning for landing a performance class 1 helicopter the 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 the decrease in mass due to fuel consumption

Question 128-19 : When planning obstacle avoidance on the 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 for day operations.

Catpolh110 obstacle accountability c obstacles may be disregarded if they are situated beyond 1 7 x rotor radius r for day operations if it is assured that navigational accuracy can be achieved by reference to suitable visual cues during the climb 2 10 x r for night operations if it is assured that navigational accuracy can be achieved by reference to suitable visual cues during the climb 3 300 m if navigational accuracy can be achieved by appropriate navigation aids or4 900 m in all other cases

Question 128-20 : Where is an official 'fuel flow chart' found ?

In the 'helicopter flight manual'.

Question 128-21 : Which of the following factors has the greatest effect on take off power ?

Density altitude.

Question 128-22 : Which of the following groups of conditions are the most favourable for take off ?

Low airfield elevation low humidity low temperature high atmospheric pressure.

Question 128-23 : Why is vne stated as an operating limitation 1 aerodynamic limitation2 engine performance limitation3 noise level related limitation4 structural limitation5 atc limitationwhich of the following groups all the correct answers ?

1 and 4.

Question 128-24 : 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 the fato by ?

35 ft.

Catpolh220 landing b in the event of the critical engine failure being recognised at any point at or before the landing decision point ldp it is possible either to land and stop within the fato or to perform a balked landing and clear all obstacles in the flight path by a vertical margin of 107 m 35 ft 692

Question 128-25 : The heightvelocity diagram or unsafe area ?

Is independent of the altitude at which the helicopter is operating.

Question 128-26 : Maximum endurance for a helicopter depends on ?

True airpseed.

Maximum endurance is achieved in unaccelerated level flight with minimum fuel flowthe speed to fly for maximum endurance is the speed at the lowest fuel flow per unit of time

Question 128-27 : A helicopter in performance class 3 must be certified in ?

Category a or b.

Question 128-28 : At night operations in performance class 3 helicopters are ?

Never carried out.

Question 128-29 : For take off with a tail wind component in class 2 performance an operator must take account of at least ?

150% of the reported tail wind component.

Catpolh105 general c when showing compliance with the requirements of this section account shall be taken of the following parameters 1 mass of the helicopter 2 the helicopter configuration 3 the environmental conditions in particular i pressure altitude and temperature ii wind a except as provided in c for take off take off flight path and landing requirements accountability for wind shall be no more than 50% of any reported steady headwind component of 5 kt or more b where take off and landing with a tailwind component is permitted in the afm and in all cases for 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 the point of take off and landing wind components in excess of 50% may be established by the operator provided that the operator demonstrates to the competent authority that the proximity to the fato and accuracy enhancements of the wind measuring equipment provide an equivalent level of safety 4 the operating techniques and5 the operation of any systems that have an adverse effect on performance

Question 128-30 : When planning for one engine inoperative in the cruise a helicopter of performance class 2 must be able to maintain a rate of climb of at least ?

50 ftmin at 2000 ft in mountainous areas.

Question 128-31 : Define the term 'performance class 2' ?

Performance class 2 operations are those operations such that in the event of critical power unit failure performance is available to enable the helicopter to safely continue the flight except when the failure occurs early during the take off manoeuvre or late in the landing manoeuvre in which cases a forced landing may be required.

Question 128-32 : In class 2 performance with one engine failed and the others operating a helicopter's weight at the estimated landing time must allow it to climb at least at ?

150 ftmin at 1000 ft above the destination and the alternate heliports.

Question 128-33 : Performance class 2 helicopters shall have a maximum approved seating configuration of ?

19 or less but more than 9.

Question 128-34 : In class 1 performance with one engine failed and the others operating a helicopter's weight at the estimated landing time must allow it to climb at least at ?

150 ftmin at 1000ft and 100 ftmin at 200 ft above the destination and the alternate heliports.

Question 128-35 : Define the term 'performance class 1' ?

Performance class 1 operations are those with performance such that in the event of failure of the critical power unit the helicopter is able to land within the rejected take off distance available or safely continue the flight to an appropriate landing area depending on when the failure occurs.

Question 128-36 : A helicopter of performance class 1 must achieve on take off a rate of climb of ?

100 ftmin at 200 ft.

Question 128-37 : As a cause of accidents the human factor ?

Is cited in approximately 70 80 % of aviation accidents.

Question 128-38 : Analysis of accidents involving the human factor in aviation shows that ?

There is hardly ever a single cause responsible.

Question 128-39 : To avoid wrong decisions by the pilot an aircraft system should at least be able to ?

Report its malfunction.

When the system malfunctions it should report the unservicability to the pilot the pilot can see what the 'deviation' is and correct for it but he needs to know that it is the result of a system malfunction

Question 128-40 : When can a system be said to be tolerant to error when ?

The consequences of an error will not seriously jeopardise safety.