Asymmetric thrust warning system for dual engine aircraft

Claim 1

An asymmetric thrust warning system for aircraft having at least two augmentable gas turbine engines comprising: first comparator means receiving a signal indicative of the compressor discharge pressure of a first one of said engines and receiving a signal indicative of the compressor discharge pressure of a second one of said engines; said first comparator means determining which of said first or second engines has the lower compressor discharge pressure and providing an actual pressure difference signal; second comparator means receiving said actual pressure difference signal from said first comparator means and receiving a maximum allowable pressure difference signal; said second comparator means providing a first asymmetric thrust warning signal if the level of said actual pressure difference signal exceeds the level of said maximum allowable pressure difference signal; third comparator means receiving a signal indicative of the position of the augmenter metering valve of said first engine and a signal indicative of the position of the augmenter metering valve of said second engine; said third comparator means providing a second asymmetric thrust warning signal when the augmenter metering valve of said first engine and the augmenter metering valve of said second engine are in different operating positions; thrust warning means; and gate means for coupling said first and second thrust warning signals to said thrust warning means.