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Refer to figure or Flight planning Manual SEP 1 Figure 2.3 Table 2.3.1.
Using the Power Setting Table, for the single engine aeroplane, determine the cruise TAS and fuel flow lb/hr with full throttle and cruise lean mixture in the following conditions:

Given:

OAT: 3°C
Pressure altitude: 6000 ft
Power: Full throttle / 21.0 in/Hg./ 2100 RPM

  • A
    134 kt and 55.7 lb/hr
  • B
    131 kt and 56.9 lb/hr
  • C
    125 kt and 55.7 lb/hr
  • D
    136 kt and 56.9 lb/hr

Refer to figure.
ISA at 6000 ft = 6 x (-2) + 15 = 3˚C
OAT = 3˚C
OAT = ISA

TAS and fuel flow = 134 kt and 55.7 lb/hr

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