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In some aspects, an aircraft engine thrust reverser lock system includes a pin-capturing member. The pin-capturing member includes a body that is rotatable about an axis defined by a pivot extending through the body. The body includes an interior surface that defines a slot. The slot has an opening

In some aspects, an aircraft engine thrust reverser lock system includes a pin-capturing member. The pin-capturing member includes a body that is rotatable about an axis defined by a pivot extending through the body. The body includes an interior surface that defines a slot. The slot has an opening that is sized to receive a pin into the slot. One side of the slot includes a protruded sidewall surface that protrudes into the slot toward an another sidewall surface of the slot. The protruded sidewall surface defines an apex between the open and closed ends of the slot. Between the apex and the closed end of the slot, the protruded sidewall surface faces the rotational axis.

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1. An aircraft engine thrust reverser lock system comprising: a pin-capturing member comprising a body that is rotatable about a rotational axis, the rotational axis being defined by a pivot that extends through the body, the body including: an interior surface that defines a slot, the interior surf

1. An aircraft engine thrust reverser lock system comprising: a pin-capturing member comprising a body that is rotatable about a rotational axis, the rotational axis being defined by a pivot that extends through the body, the body including: an interior surface that defines a slot, the interior surface defining first and second fixed, opposing slot sides between an open end of the slot and a closed end of the slot, an opening between the first and second slot sides at the open end of the slot being sized to receive a pin into the slot;the first slot side including: an end wall surface that extends from the open end of the slot and faces the rotational axis;a first sidewall surface that extends from the end wall surface toward the closed end of the slot; andthe second slot side including a protruded sidewall surface that protrudes into the slot toward the first sidewall surface and defines an apex between the open and closed ends of the slot, the protruded sidewall surface facing the end wall surface between the apex and the open end of the slot, the protruded sidewall surface facing the rotational axis between the apex and the closed end of the slot, the protruded sidewall surface including a first side that faces the rotational axis and a second side that faces away from the rotational axis, the first and second sides of the protruded sidewall surface defining an acute angle with respect to the apex,the protruded sidewall surface configured to cause the body to rotate about the rotational axis in response to the pin passing over the protruded sidewall surface during movement of the pin toward the closed end of the slot, the apex located at a position on the protruded sidewall surface so that the pin comes to rest with clearance between the pin and the interior surface when the pin and pin-capturing member are in a locked configuration. 2. The aircraft engine thrust reverser lock system of claim 1, wherein the end wall surface comprises a first end wall surface, and the interior surface includes a second end wall surface at the closed end of the slot between the first and second slot sides. 3. The aircraft engine thrust reverser lock system of claim 2, wherein the first and second end wall surfaces face each other and define a depth of the slot. 4. The aircraft engine thrust reverser lock system of claim 2, wherein the first end wall surface extends from the opening and meets the first sidewall surface, the first sidewall surface extends from the first end wall surface and meets the second end wall surface, the second end wall surface extends from the first sidewall surface and meets the protruded sidewall surface, and the protruded sidewall surface extends from the second end wall surface to the opening. 5. The aircraft engine thrust reverser lock system of claim 1, wherein the protruded sidewall surface defines a radius at the apex. 6. The aircraft engine thrust reverser lock system of claim 1, the pin-capturing member further comprising a mass balance member extending from the body on an opposite side of the rotational axis. 7. The aircraft engine thrust reverser lock system of claim 1, wherein the body includes an outer surface exterior the slot, the outer surface extending from the first slot side and defining a radiused end of the body, extending from the radiused end to a protrusion that protrudes from the body to engage an actuator member. 8. The aircraft engine thrust reverser lock system of claim 1, further comprising a spring that contacts the body to bias the body toward a first direction of rotation about the rotational axis. 9. An aircraft engine thrust reverser locking system comprising: a pin secured to a thrust reverser door assembly and moveable between a captured position and a released position;a pin-capturing member being rotatable about a pivot between an up position and a down position, the pin-capturing member comprising a body that includes an interior surface that defines a slot and surrounds the pin in the captured position, the interior surface including first and second fixed, opposing slot sides that extend between an open end of the slot and a closed end of the slot, the first slot side including an end wall that faces the pivot and prevents the pin from moving to the released position from inside the slot when the pin-capturing member is in the down position, the second slot side including a protruded surface that defines an apex between the open and closed ends of the slot, the protruded surface including a first portion that faces the pivot between the apex and the closed end of the slot, the protruded surface including a second portion that faces away from the pivot between the apex and the open end of the slot, the first and second portions of the protruded surface defining an acute angle with respect to the apex,the protruded surface configured to cause the body to rotate about the pivot in response to the pin passing over both the protruded surface during movement of the pin from the released position to the captured position, the apex located at a position on the protruded surface so that the pin comes to rest with clearance between the pin and the interior surface when the pin reaches the captured position;an actuator that is moveable between a locked position and an unlocked position, the actuator in the locked position contacting the pin-capturing member to maintain the pin-capturing member in the down position; anda biasing member that biases the pin-capturing toward the up position. 10. The aircraft engine thrust reverser locking system of claim 9, wherein the pin-capturing member is made of precipitation hardening stainless steel. 11. The aircraft engine thrust reverser locking system of claim 9, wherein the biasing member rotates the pin-capturing member from the down position toward the up position when the actuator is in the unlocked position. 12. The aircraft engine thrust reverser locking system of claim 9, wherein the captured position of the pin corresponds to a stowed configuration of the thrust reverser door assembly, and the released position of the pin corresponds to a deployed configuration of the thrust reverser door assembly. 13. The aircraft engine thrust reverser locking system of claim 9, wherein the biasing member comprises a torsion spring about the pivot. 14. The aircraft engine thrust reverser locking system of claim 9, comprising a sensor plate extending from the actuator. 15. The aircraft engine thrust reverser locking system of claim 14, further comprising one or more proximity sensors operable to detect the position of the sensor plate. 16. The aircraft engine thrust reverser locking system of claim 9, further comprising a blocking member that limits the rotation of the pin-capturing member. 17. The aircraft engine thrust reverser locking system of claim 9, the pin-capturing member further comprising a mass balance member extending from the body on an opposite side of the pivot. 18. The aircraft engine thrust reverser locking system of claim 9, comprising an actuator assembly that includes: a shaft coupled to the actuator; anda solenoid operable to translate the shaft to move the actuator between the locked and unlocked positions. 19. An aircraft engine thrust reverser lock, comprising: a body having an outer boundary, the body including an inner surface defining a slot;the slot having an entry through the outer boundary, a closed end, and a clearance space, the slot being of fixed dimension; andthe inner surface of the body including a protrusion with two oppositely sloped sides joined at an apex, one of the sloped sides facing toward the entry such that a pin that moves into the slot through the entry rides along the sloped side facing the entry, over the apex, and into the clearance space without contacting the other of the sloped sides, and comes to rest with clearance between the inner surface and the pin when the pin reaches a captured position, the two oppositely sloped sides defining an acute angle with respect to the apex;the body having a pivot for rotational coupling of the body to a support structure.