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B = lower limit for probability ratio in sequential analysis £=expected value of a function F-probability of failure G = probability of survival R= reliability or probability of successful performance 7"=time (fixed value) f=probability density of failure w=exponent in failure distribution n-number of samples or number of failures in a test p -probability density (general) r=reliability (instantaneous value) 5=number of components in a system intime (variable) z-conditional probability density of fail ure a=risk of rejecting good equipment /3=risk of accepting inadequate equip ment 0 =parameter in failure distribution SUBSCRIPTS 0 = design value (greater than acceptable minimum) 1= specified minimum d=minimum value e = expected value /s = arising from Flehinger-Lewis failure distribution m = mean value r = coefficient associated with random failure rate or removal time i=survivors /=coefficient associated with time varying rate* w-associated with Weibull failure dis tribution Synopsis: This paper describes a design and analog computer study of a hightemperature aircraft a-c electrical system. The study includes an extensive, nonlinear representation of the a-c alternator and shows the effects of temperature, load, and regulator and exciter nonlinear behavior on system stability and transient per formance. Torque-limiting techniques are evaluated and a computer approach for study of the reactive load division loop is developed.

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