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| MIL-D-23222A(AS)
3.10.3.2
(Cont)
(3) Climb at airspeed for maximum rate of climb.
Data obtained during the test shall include the following, as appli-
cable.
(4) Condition of loading.
(5) Weight at start of flight.
(6) Fuel and oil on board at start of flight.
(7) Fuel and oil on board at end of flight.
(8) Kind of fuel and oil used.
(9) At five minute intervals during the run:
Standard pressure altitude.
(a)
Air temperature at above altitude.
(b)
Airspeed indicator reading.
(c)
Engine RPM.
(d)
Tail pipe total gas temperature.
(e)
(f)
oil pressure.
Oil inlet and outlet temperature across heat
(g)
exchanger.
Rear bearing temperature.
(h)
Fuel manifold pressure.
(i)
Fuel flow.
(j)
Air flow.
(k)
Tail pipe total pressure.
(l)
Compressor inlet total temperature.
(m)
(n)
Compressor inlet total pressure.
Exhaust nozzle position.
(0)
Torquemeter reading.
(P)
(q)
Temperature of primary structural members
subjected to temperatures greater than 200F.
Main fuel pump inlet pressure.
(r)
Main fuel pump discharge pressure.
(s)
(t)
Emergency fuel pump discharge pressure.
(u)
Turbine inlet temperature.
Compressor discharge pressure.
(V)
(w)
Engine control lever position.
(x)
Time.
(y)
Engine installation vibration data.
Fuel temperature (into engine)
(z)
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