Document ID: chunk:federal_register_of_legislation:F2025C00050:body:0:p325
Version: federal_register_of_legislation:F2025C00050
Segment Type: other
Provision Reference: 
Character Range: 1130869–1134561

point.

Unit 1.9.7                                   COPH:  CPL operations, performance and planning – helicopter

     1.                    Reserved

1.                       Operational knowledge
1.1                    Helicopter limitations
1.1.1              Describe the reason for following operational limitation on helicopter performance:
(a)           maximum rotor RPM – power on;
(b)           maximum rotor RPM – power off;
(c)           minimum rotor RPM – power on;
(d)           minimum rotor RPM – power off;
(e)           never exceed speed – power on;
(f)             never exceed speed – power off;
(g)           maximum sideways speed;
(h)           maximum rearward speed;
(i)             maximum take-off weight;
(j)             maximum all up weight;
(k)           minimum operating weight;
(l)             maximum positive and negative flight load factors.
1.2                    Helicopter landing sites (HLS)
1.2.1              Recall the requirements of basic and secondary HLS in respect to:
(a)           physical specifications;
(b)           operational requirements;
(c)           general conditions for use.
1.3                    Take-off and landing weight
1.3.1              Select from a list the statement which best describes:
(a)           the effect of the following variables on the take-off and/or landing performance of a helicopter:
(i)             weight;
(ii)            power;
(iii)          ground effect;
(iv)          density altitude;
(v)           ambient wind component;
(b)           the easiest way of determining pressure altitude from a sensitive altimeter.
1.3.2              Determine hover performance in and out of ground effect given the following:
(a)           gross weight;
(b)           pressure altitude;
(c)           temperature;
(d)           flight manual performance charts.
1.4                    Forward climb performance
1.4.1              Given graphical or tabular information typical of that provided in a flight manual for a single-engine helicopter extract:
(a)           the best rate of climb for various conditions of pressure altitude, temperature and weight;
(b)           the service ceiling for various conditions of pressure altitude, temperature and weight.
1.5                    Cruise performance
1.5.1              Given graphical or tabular information typical of that provided in a flight manual for a single-engine helicopter, calculate:
(a)           maximum payload which may be carried after determining the fuel requirements and the nature of the operation;
(b)           endurance for holding or search for various combinations of helicopter weight and fuel;
(c)           the maximum range, given weight, fuel carried and cruising altitude.
1.6                    Weight and balance
1.6.1              Recall the meaning of the following terms used in the computation of weight and balance data:
(a)           datum;
(b)           arm;
(c)           moment;
(d)           station;
(e)           centre of gravity range;
(f)             lateral centre of gravity range;
(g)           empty weight;
(h)           operating weight;
(i)             maximum take-off weight (MTOW).
1.6.2              Given a typical manual for a single-engine helicopter:
(a)           extract the following weight and balance information:
(i)             MTOW;
(ii)            capacity and arm of the baggage lockers;
(iii)          capacity, arm, grade and specific gravity of the fuel;
(iv)          location and arms of the seating;
(b)           determine the forward, aft and lateral limits of the CG for a given weight in the case of the above helicopter;
(c)           determine whether the helicopter