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|  MIL-S-85419 (AS)
a.
Date of test
b.
Unit model designation
Unit serial number
Size of flywheel used
Ambient temperature (F)
e.
Ambient pressure (IN Hg Abs.)
f.
Oil Temperature (F)
g.
Actual weight of unit, Dry (lbs)
h.
Maximum unit vibration
Starter exhaust gas temperature, Maximum (F)
k.
Starter output torque at 1000 rpm and 2000 rpm
output shaft speed
l.
Cutoff speed (rpm)
APU performance at 3KVA and 6KVA
m.
4.5.21.2 Examination of Product. The starter/APU shall be
subjected to inspection to insure that all dimensions are within
specification and drawing limits and that all parts are correctly
assembled.
4.5.21.3 High Speed Components. Prior to conducting any
operational starter tests, the following shall be accomplished on
all high speed components:
Subject each part to x-ray inspection in accordance with
MIL-STD-453.
Any cracks or occulsions that will adversely affect
starter performance or life shall be cause for rejection.
b. Subject each part to flourescent penetrant inspection in
accordance with MIL-I-6866. Any cracks or occulsions that will
adversely affect starter performance or life shall be cause for
rejection.
c. Proof spin each turbine wheel for a minimum of 15 seconds
at room temperature at the proof speed.
d. Upon completion of a, b, and c above, subject each
turbine wheel to x-ray inspection to determine the extent of
deformity, structural damage, growth of cracks or occlusions, or
any new cracks shall be cause for rejection.
4.5.21.4 Leakage. Any leakage of liquids or gases from the
starter, other than normal drainage, during acceptance cycling or
overrunning shall be cause for rejection.
4.5.21.5 Performance. The starter/APU shall be subjected to one
40 second crank, two regular start cycles, one hour APU
operation, and one translation cycle, as described in paragraph
4.5.2. The performance shall meet or exceed the requirements of
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