초록 ▼

An aircraft door latch arm rotation limiting device incorporates a flexible strap having a proximal end and distal end. The distal end is insertable through a loop eye proximate to an aircraft door. An elongate sleeve is disposed on the proximal end of the flexible strap and the sleeve is received o

An aircraft door latch arm rotation limiting device incorporates a flexible strap having a proximal end and distal end. The distal end is insertable through a loop eye proximate to an aircraft door. An elongate sleeve is disposed on the proximal end of the flexible strap and the sleeve is received over a rotatable latch arm of an aircraft door. A first receiving element intermediate the proximal and distal ends of the flexible strap releasably engages the distal end of the flexible strap to establish a first predetermined looped strap length restricting rotation of the lever beyond a partially open position. A second receiving element is disposed between the first receiving element and the proximal end on the flexible strap to releasably engage the distal end to establish a second predetermined looped strap length preventing rotation of the lever from a closed position.

대표청구항 ▼

1. A system for limiting rotation of an aircraft door latch arm, said system comprising: an aircraft door having a rotatable latch arm having a first position that locks the aircraft door closed, and a second position that allows the door to move to a partially opened position, and a third position

1. A system for limiting rotation of an aircraft door latch arm, said system comprising: an aircraft door having a rotatable latch arm having a first position that locks the aircraft door closed, and a second position that allows the door to move to a partially opened position, and a third position that allows the door to be fully opened;a flexible strap having a proximal end and a distal end, said distal end having a securing element configured to be inserted through a loop eye on a cabin wall adjacent the aircraft door;a single elongate sleeve rotatably attached to the proximal end of the flexible strap such that the single elongate sleeve rotates relative to the proximal end of the flexible strap, said single elongate sleeve configured to be received over the rotatable latch arm of the aircraft door;a first receiving element disposed at a first position on the flexible strap intermediate the proximal end and the distal end of the flexible strap, said first receiving element releasably engaging the securing element on the distal end of the flexible strap when looped through the loop eye, wherein when the securing element is looped through the loop eye and engaged with the first receiving element with the single elongate sleeve received over the rotatable latch arm of the aircraft door, the flexible strap establishes a first predetermined looped strap length restricting rotation of the rotatable latch arm beyond the second position; anda second receiving element disposed at a second position on the flexible strap between the first receiving element and the proximal end on the flexible strap, releasably engaging the securing element on the distal end when looped through the loop eye, wherein when the securing element is looped through the loop eye and engaged with the second receiving element with the single elongate sleeve received over the rotatable latch arm of the aircraft door, the flexible strap establishes a second predetermined looped strap length preventing rotation of the rotatable latch arm beyond the first position. 2. The system of claim 1 wherein the single elongate sleeve is disposed on the proximal end transverse to a longitudinal axis of the flexible strap with the first receiving element engaging the distal end. 3. The system of claim 1 wherein the single elongate sleeve is disposed on the proximal end substantially parallel to a longitudinal axis of the flexible strap with the second receiving element engaging the distal end. 4. The system of claim 1 wherein the single elongate sleeve incorporates a flap extending therefrom for attachment to the proximal end of the flexible strap. 5. The system of claim 4 further comprising a pivot pin securing the proximal end of the flexible strap to the flap. 6. The system of claim 1 wherein the first receiving element and the second receiving element comprise ladder lock buckles receiving the distal end of the flexible strap. 7. The system of claim 6 further comprising indicia proximate the first receiving element and the second receiving element annotating length of the distal end as received through the ladder lock buckles to achieve the first predetermined looped strap length and the second predetermined looped strap length. 8. The system of claim 1 wherein the first receiving element and the second receiving element comprise receiving buckles and the securing element comprises a blade received in the receiving buckles. 9. The system of claim 1 wherein the first receiving element and the second receiving element comprise side squeeze receiving buckles and the securing element comprises side squeeze tabs received in the side squeeze receiving buckles. 10. The system of claim 1 wherein the first receiving element and the second receiving element comprise a first moiety of a hook and loop fastener and the securing element comprises a mating moiety for the hook and loop fastener. 11. A method of using the system of claim 1 to restrain rotation of a rotatable latch arm to limit aircraft door position comprising: engaging the single elongate sleeve attached to the proximal end of the flexible strap over the rotatable latch arm;looping the distal end of the flexible strap through the loop eye on the cabin wall adjacent the aircraft door;engaging the first receiving element with the distal end of the flexible strap establishing the first predetermined looped length of the flexible strap; and,restraining rotation of the rotatable latch arm beyond the second position. 12. The method of using the system of claim 1 to restrain rotation of a rotatable latch arm to limit aircraft door position as defined in claim 11 further comprising rotating the single elongate sleeve transverse to an axis of the flexible strap. 13. The method of using the system of claim 1 to restrain rotation of a rotatable latch arm to limit aircraft door position as defined in claim 11 further comprising: alternatively engaging the second receiving element with the distal end of the flexible strap, establishing the second predetermined looped length of the flexible strap; and,restraining rotation of the rotatable latch arm from the first position. 14. The method of using the system of claim 1 to restrain rotation of a rotatable latch arm to limit aircraft door position as defined in claim 13 further comprising rotating the single elongate sleeve substantially parallel to the axis of the flexible strap. 15. The method of using the system of claim 1 to restrain rotation of a rotatable latch arm to limit aircraft door position as defined in claim 13 wherein the step of engaging the second receiving element comprises engaging the securing element in the second receiving element. 16. The method of using the system of claim 1 to restrain rotation of a rotatable latch arm to limit aircraft door position as defined in claim 15 wherein the second receiving element and the securing element are selected from the set of a buckle and blade, a side squeeze receiving buckle and side squeeze tabs, and a first moiety of a hook and loop fastener and a mating moiety for the hook and loop fastener. 17. The method of using the system of claim 1 to restrain rotation of a rotatable latch arm to limit aircraft door position as defined in claim 11 wherein the step of engaging the first receiving element comprises engaging the securing element in the first receiving element. 18. The method of using the system of claim 1 to restrain rotation of a rotatable latch arm to limit aircraft door position as defined in claim 17 wherein the first receiving element and the securing element are selected from the set of a buckle and blade, a side squeeze receiving buckle and side squeeze tabs, and a first moiety of a hook and loop fastener and a mating moiety for the hook and loop fastener.