The thickness of a flange on an aircraft component is uniformly distributed between 0.2050 and 0.2150 micrometers. Determine the following: Proportion of flanges that exceeds 0.2125 micrometers in flange thickness Mean and variance of flange thickness a. P(X > 0.2125) = 0.75, E(X) = 0.2100, V(X) = 8.33 x 10-6 b.P(X > 0.2125) = 0.25, E(X) = 0.2100, V(X) = 8.33 x 10-6 c. NONE d. P(X <= 0.2125) = 0.25, E(X) = 0.2100, V(X) = 8.33 x 10-6

Algebra & Trigonometry with Analytic Geometry
13th Edition
ISBN:9781133382119
Author:Swokowski
Publisher:Swokowski
Chapter7: Analytic Trigonometry
Section7.6: The Inverse Trigonometric Functions
Problem 94E
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The thickness of a flange on an aircraft component is uniformly distributed between 0.2050 and
0.2150 micrometers. Determine the following:
Proportion of flanges that exceeds 0.2125 micrometers in flange thickness
Mean and variance of flange thickness
a. P(X > 0.2125) = 0.75, E(X) = 0.2100, V(X) = 8.33 x 10-6
b.P(X > 0.2125) = 0.25, E(X) = 0.2100, V(X) = 8.33 x 10-6
c. NONE
d. P(X <= 0.2125) = 0.25, E(X) = 0.2100, V(X) = 8.33 x 10-6
Transcribed Image Text:The thickness of a flange on an aircraft component is uniformly distributed between 0.2050 and 0.2150 micrometers. Determine the following: Proportion of flanges that exceeds 0.2125 micrometers in flange thickness Mean and variance of flange thickness a. P(X > 0.2125) = 0.75, E(X) = 0.2100, V(X) = 8.33 x 10-6 b.P(X > 0.2125) = 0.25, E(X) = 0.2100, V(X) = 8.33 x 10-6 c. NONE d. P(X <= 0.2125) = 0.25, E(X) = 0.2100, V(X) = 8.33 x 10-6
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