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Standard

GUIDANCE FOR AIRCRAFT ELECTRICAL POWER UTILIZATION AND TRANSIENT PROTECTION

1989-10-01
CURRENT
ARIR413A
This standard provides guidance to airframe manufacturers concerning the utilization of aircraft electrical power. This standard covers the description of basic power characteristics, and detailed guidance concerning transient protection, interference control, and equipment installation considerations.
Standard

Hose Assemblies, Metal Medium Pressure, High Temperature, Metric

1989-10-01
CURRENT
MA2100
This specification covers metric medium pressure, high temperature, flexible metal hose assemblies suitable for continuous operation in liquid and pneumatic systems from 55 to 400°C, with short duration excursion to 650°C, and primarily for use on jet aircraft power plants.
Standard

AEROSPACE - HYDRAULIC SYSTEM FLUID CONTAMINATION - LOCATION OF SAMPLING POINTS

1989-10-01
HISTORICAL
ARP4268
The scope of this Aerospace Recommended Practice (ARP) covers where, when, and how often to sample hydraulic system fluid on aerospace vehicles for particulate contamination measurements. The measurement of hydraulic fluid particulate contamination is of concern to the aerospace community because of the critical importance of hydraulic equipment reliability. Contamination is always present in the system fluid, even in new unused fluid. Contamination must be below a level that will not adversely affect system operation. This ARP draws from aerospace industry experience and practice to establish criteria for fluid contamination sampling recommendations in aerospace vehicle hydraulic systems. Fluid samples can then be subjected to measurement of particulate contamination and of other harmful contaminants such as chlorinated solvents and water.
Standard

ENGINE EXHAUST SYSTEM DESIGN CONSIDERATIONS FOR ROTORCRAFT

1989-10-01
CURRENT
ARP4056
Turbine engines installed in rotorcraft have an exhaust system that is designed and produced by the aircraft manufacturer. The primary function of the exhaust system is to direct hot exhaust gases away from the airframe. The exhaust system may consist of a tailpipe, which is attached to the engine, and an exhaust fairing, which is part of the rotorcraft. The engine manufacturer specifies a baseline "referee" tailpipe design, and guaranteed engine performance is based upon the use of the referee tailpipe and tailpipe exit diameter. The configuration used on the rotocraft may differ from the referee tailpipe, but it is intended to minimize additional losses attributed to the installation. This Aerospace Recommended Practice (ARP) describes the physical, functional, and performance interfaces to be considered in the design of the aircraft exhaust system.
Standard

STANDARD FIRMWARE LOADER FOR AVIONICS SHOPS

1989-09-30
CURRENT
ARIR614
This standard describes the characteristics of a standard firmware loader for avionic shops. It is capable of copying digital information into memory devices installed in circuit card assemblies, Line Replaceable Modules (LRMs) and On-Board Replaceable Modules (OBRMs). It contains the recommendations of the air transport community concerning the design and development of firmware loader equipment.
Standard

PASSENGER EVACUATION DEVICES - CIVIL AIR TRANSPORT

1989-09-18
HISTORICAL
ARP495C
This Aerospace Recommended Practice (ARP) establishes criteria for design and installation of devices that will ensure rapid and effective occupant evacuation in the event of emergency.
Standard

Coupling Assembly, Hydraulic Self Sealing, Quick Disconnect

1989-09-05
HISTORICAL
AS1709
This specification covers the requirements for aircraft, hydraulic, self-sealing, quick disconnect couplings, for use in Type II hydraulic systems (-65 to +275 °F temperature range) as defined by MIL-H-5440.
Standard

Aircraft Fuel Weight Penalty Due to Air Conditioning

1989-09-01
HISTORICAL
AIR1168/8
The purpose of this section is to provide methods and a set of convenient working charts to estimate penalty values in terms of take-off fuel weight for any given airplane mission. The curves are for a range of specific fuel consumption (SFC) and lift/drag ratio (L/D) compatible with the jet engines and supersonic aircraft currently being developed. A typical example showing use of the charts for an air conditioning system is given. Evaluation of the penalty imposed on aircraft performance characteristics by the installation of an air conditioning system is important for two reasons: 1 It provides a common denominator for comparing systems in the preliminary design stage, thus aiding in the choice of system to be used. 2 It aids in pinpointing portions of existing systems where design improvements can be most readily achieved.
Standard

Aerothermodynamic Systems Engineering and Design

1989-09-01
CURRENT
AIR1168/3
This section presents methods and examples of computing the steady-state heating and cooling loads of aircraft compartments. In a steady-state process the flows of heat throughout the system are stabilized and thus do not change with time. In an aircraft compartment, several elements compose the steady-state air conditioning load.
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