Henry wrote;
NASA TN D-7143, the Apollo Experience Report on LM descent propulsion, mentions
all flight engines undergoing an acceptance firing -- length not specified --
before delivery. (The flight pressure sensors had to be installed after that,
else residual oxidizer caused some etching of the sensor diaphragms, which
messed up calibration.)
I recall the concern regarding propellant corrosion. The transducer switch
makes sense. Does the citation indicate to what extent purging was carried out
(a lot to consider in practice) and what the duration of the test was?
Anthony J. Cesaroni
President/CEO
Cesaroni Technology/Cesaroni Aerospace
http://www.cesaronitech.com/
(941) 360-3100 x101 Sarasota
(905) 887-2370 x222 Toronto
