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基本信息

【标准号】: AIR5451
【中文名称】: A Guide to Landing Gear System Integration
【英文名称】: A Guide to Landing Gear System Integration
【发布时间】
【实施时间】: 2010-06-01
【有效性】: 有效
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【自动关键词】

【范围】

The landing gear system is a major airframe system that needs to be integrated very efficiently to minimize 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 and is divided into four sections: Landing Gear Configuration Requirements (Section 3) Landing Gear Functional Requirements (Section 4) Landing Gear System Integrity Requirements (Section 5) Landing Gear Program Requirements (Section 6) The landing gear system encompasses all landing gear structural and subsystem elements. Structural elements include shock struts, 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 systems and control systems (mechanical, hydraulic, electrical and electronic). 1.1 Purpose: The purpose of this document is to provide an airframe manufacturer or procuring agency with a framework from which a specification for an Integrated Landing Gear System may be developed and to provide guidance in the development of an integrated landing gear system. This document is not intended to be an all inclusive detail design document or to duplicate other existing SAE landing gear documents. Rather, the intent is to provide guidance in writing and managing the top-level integration requirements. 1.2 Field of Application: In the past, it has been common for airframe manufacturers to procure the landing gear and its associated systems as separate elements, and to integrate these elements into the overall aircraft design. Using this approach, the airframe manufacturers have written separate specifications for each element and have assembled the landing gear from components delivered separately by different suppliers. In some instances the landing gear supplier simply performs the assembly work and delivers a “dressed gear” that has been built up from components procured by the airframer. In other instances, the airframe manufacturer subcontracts the design of the landing gear, including the specification and procurement of the associated systems, to an integrator. This document includes landing gear systems for both small and large, commercial and military aircraft as well as helicopters.strRefField

【与前一版的变化】

包含缩略语

AC：
AIR：
ARP：
AS：
BOM：
CCA：
CDR：
CE：
CG：
DD：
DFMA：
F：
FAA：
FAR：
FHA：
FMEA：
FMECA：
fps：
FTA：
HIRF：
JAA：
JAR：
LRU：
MA：
MTOW：
NATO：
NLG：
OEM：
OSP：
O&S：
PDR：
psig：
RTO：
SAE：
SSA：
TAS：
TBD：
U.S.：
V 1：
V2：
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被引文件

AIR5829: Air in Aircraft Hydraulic Systems
ARP1311C: Landing Gear Structures and Mechanisms
ARP1493B: Wheel and Hydraulically Actuated Brake Design and Test Requirements for Military Aircraft
ARP1907B: Automatic Braking Systems
AIR5699: A Guide for the Damaging Effects of Tire and Wheel Failures