公开(公告)号：US20240002040A1

公开(公告)日：2024-01-04

申请号：US18345749

申请日：2023-06-30

Applicant: Textron Aviation Inc.

Inventor： Donald Edward Hill ,  Michael R. DePinto ,  Matthew J. Allmond ,  Michael Troy Heeren ,  Dennis Scarberry

IPC: B64C25/20

CPC classification number: B64C25/20

Abstract: A pneumo-mechanical landing gear deployment system includes a dual-stage handle operatively connected to a pressurized tank, a nose landing gear pneumatically connected to the pressurized tank, and a main landing gear pneumatically connected to the pressurized tank. Actuation of the dual-stage handle to a first position opens the pressurized tank thereby deploying the nose landing gear. Actuation of the dual-stage handle to a second position causes further opening of the pressurized tank thereby deploying the main landing gear. The system may be employed as a backup landing gear deployment system in the case of a primary landing gear system failure.

公开(公告)号：US12280866B2

公开(公告)日：2025-04-22

申请号：US18345749

申请日：2023-06-30

Applicant: Textron Aviation Inc.

Inventor： Donald Edward Hill ,  Michael R. DePinto ,  Matthew J. Allmond ,  Michael Troy Heeren ,  Dennis Scarberry

IPC: B64C25/20 ,  B64C25/26 ,  B64C25/30

Abstract: A pneumo-mechanical landing gear deployment system includes a dual-stage handle operatively connected to a pressurized tank, a nose landing gear pneumatically connected to the pressurized tank, and a main landing gear pneumatically connected to the pressurized tank. Actuation of the dual-stage handle to a first position opens the pressurized tank thereby deploying the nose landing gear. Actuation of the dual-stage handle to a second position causes further opening of the pressurized tank thereby deploying the main landing gear. The system may be employed as a backup landing gear deployment system in the case of a primary landing gear system failure.

公开(公告)号：US20230110798A1

公开(公告)日：2023-04-13

申请号：US17934706

申请日：2022-09-23

Applicant: Textron Aviation Inc.

Inventor： Alec Charles Willford ,  Ronald J. Parker ,  Michael R. DePinto

IPC: B64D31/04 ,  F02C7/00

Abstract: Disclosed is an automatic throttle arrangement utilizing a servo which receives commands from a controller on an aircraft and responsively rotates a mechanical device that is linked by a cable arrangement with the aircraft’s throttle lever enabling automated throttle control. The mechanical device can be fixed to the throttle lever assembly using rivets designed to fail in case the servo/cable arrangement jams. This leaves the lever able to continue manual function.