The landing gear system is a major and safety critical airframe system that needs to be integrated efficiently to meet the overall aircraft program goals of minimizing the penalties of weight, cost, dispatch reliability and maintenance. As the landing gear system business develops and large-scale teaming arrangements and acquisitions become increasingly common, it may be desirable in some instances to procure an Integrated Landing Gear System. This document provides guidelines and useful references for developing an integrated landing gear system for an aircraft. The document structure is divided into four sections:
• Landing Gear System Configuration Requirements (Section 3)
• Landing Gear System Functional Requirements (Section 4)
• Landing Gear System Integrity Requirements (Section 5)
• Landing Gear System Program Requirements (Section 6)
The landing gear system encompasses all landing gear structural and subsystem elements. Structural elements include shock struts, truck beams, torsion links, braces, fittings, pins, wheels, tires, and brakes. The subsystem elements include the retraction/extension system (both normal and alternate), the steering system, the braking system (both normal and alternate, manual and automatic), the indication and monitoring systems and control systems (mechanical, hydraulic, electrical and electronic).
Revision A incorporates the latest information and state of the art in the landing gear industry, and conveys the information as a reference to assist in the creation of an integrated landing gear system specification for new designs. It is intended as information only, and should not be used as a mandatory requirement specification.