An emergency gravity free-fall landing gear deployment system for aircraft comprising: a landing gear assembly (10-N, 10-P, 10-S) moveable between retracted and extended positions; a landing gear door (12-N, 12-P, 12-S) having a closed condition when the landing gear assembly (10-N, 10-P, 10-S) is in the retracted position and movable into an opened condition to allow the landing gear assembly (10-N, 10-P, 10-S) to be moved into the extended position; a landing gear uplock mechanism (30-P) which includes an uplock actuator (30a-P) having a preset deadstroke limit (α1) such that movement of the uplock actuator (30a-P) within a range of the deadstroke prevents the landing gear uplock mechanism (30-P) from physically unlocking the landing gear assembly (10-N, 10-P, 10-S) and movement of the uplock actuator (30a-P) beyond the deadstroke limit unlocks the landing gear uplock mechanism (30-P) from the landing gear assembly (10-N, 10-P, 10-S); and a free-fall landing gear synchronization system (16-N, 16-P, 16-S) operatively connected to the landing gear uplock mechanism (30-P) and the landing gear door (12-N, 12-P, 12-S), wherein the free-fall landing gear synchronization system (16-N, 16-P, 16-S) includes: (i) a first operational sequence upon actuation of the free-fall landing gear synchronization system (16-N, 16-P, 16-S) during which the uplock actuator (30a-P) is moved within the deadstroke range (α1) while simultaneously the gear door (12-N, 12-P, 12-S) is allowed to gravity free-fall from the closed condition toward the open condition thereof, and (ii) a second operational sequence which is time-delayed relative to an onset of the first operational sequence during which the uplock actuator (30a-P) is moved beyond the deadstroke limit (α1) to allow the landing gear assembly (10-N, 10-P, 10-S) to gravity free-fall from the retracted position to the extended position thereof, whereby the first and second operational sequences of the free-fall landing gear synchronization system (16-N, 16-P, 16-S) allow the gear door (12-N, 12-P, 12-S) to be moved by gravity free-fall toward the open condition thereof in advance of movement by gravity free-fall of the landing gear (10-N, 10-P, 10-S) toward the extended position thereof. a landing gear assembly (10-N, 10-P, 10-S) moveable between retracted and extended positions; a landing gear door (12-N, 12-P, 12-S) having a closed condition when the landing gear assembly (10-N, 10-P, 10-S) is in the retracted position and movable into an opened condition to allow the landing gear assembly (10-N, 10-P, 10-S) to be moved into the extended position; a landing gear uplock mechanism (30-P) which includes an uplock actuator (30a-P) having a preset deadstroke limit (α1) such that movement of the uplock actuator (30a-P) within a range of the deadstroke prevents the landing gear uplock mechanism (30-P) from physically unlocking the landing gear assembly (10-N, 10-P, 10-S) and movement of the uplock actuator (30a-P) beyond the deadstroke limit unlocks the landing gear uplock mechanism (30-P) from the landing gear assembly (10-N, 10-P, 10-S); and a free-fall landing gear synchronization system (16-N, 16-P, 16-S) operatively connected to the landing gear uplock mechanism (30-P) and the landing gear door (12-N, 12-P, 12-S), wherein the free-fall landing gear synchronization system (16-N, 16-P, 16-S) includes: (i) a first operational sequence upon actuation of the free-fall landing gear synchronization system (16-N, 16-P, 16-S) during which the uplock actuator (30a-P) is moved within the deadstroke range (α1) while simultaneously the gear door (12-N, 12-P, 12-S) is allowed to gravity free-fall from the closed condition toward the open condition thereof, and (ii) a second operational sequence which is time-delayed relative to an onset of the first operational sequence during which the uplock actuator (30a-P) is moved beyond the deadstroke limit (α1) to allow the landing gear assembly (10-N, 10-P, 10-S) to gravity free-fall from the retracted position to the extended position thereof, whereby the first and second operational sequences of the free-fall landing gear synchronization system (16-N, 16-P, 16-S) allow the gear door (12-N, 12-P, 12-S) to be moved by gravity free-fall toward the open condition thereof in advance of movement by gravity free-fall of the landing gear (10-N, 10-P, 10-S) toward the extended position thereof. (i) a first operational sequence upon actuation of the free-fall landing gear synchronization system (16-N, 16-P, 16-S) during which the uplock actuator (30a-P) is moved within the deadstroke range (α1) while simultaneously the gear door (12-N, 12-P, 12-S) is allowed to gravity free-fall from the closed condition toward the open condition thereof, and (ii) a second operational sequence which is time-delayed relative to an onset of the first operational sequence during which the uplock actuator (30a-P) is moved beyond the deadstroke limit (α1) to allow the landing gear assembly (10-N, 10-P, 10-S) to gravity free-fall from the retracted position to the extended position thereof, whereby the first and second operational sequences of the free-fall landing gear synchronization system (16-N, 16-P, 16-S) allow the gear door (12-N, 12-P, 12-S) to be moved by gravity free-fall toward the open condition thereof in advance of movement by gravity free-fall of the landing gear (10-N, 10-P, 10-S) toward the extended position thereof.