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This SAE Aerospace Design Standard defines a coupling, which is installed in a high pressure (1850 to 2000 psig) oxygen system of a civil transport aircraft for the purpose of mating to ground oxygen replenishment facilities. Dimensions developed from AND10089, Detail Specification Sheet for Fitting End, Design Standard, For Cone Connection.
This SAE Aerospace Recommended Practice (ARP) provides technical and application information needed by the designers of aircraft electric systems and support equipment for the selection of overcurrent protective devices. It provides definitions to permit comparisons of various electric circuit protective devices. Included also are recommended procedures for periodic visual and mechanical inspection criteria.
This AIR points out that above a frequency called the “transition frequency,” variances associated with the shielding effectiveness measurements can become large. It includes the derivations to demonstrate this. This fact should be taken into account when designing shielding for use above the transition frequency.
This SAE Aerospace Recommended Practice (ARP) defines and establishes a standard presentation of data for gas turbine propulsion engine starter characteristics in graphs and curves. The data presentation applies to both pneumatic and hydraulic energy source starting systems.
This Aeronautical Standard covers four (4) basic types of direct indicating instruments as follows: TYPE I - Range 0-2000 feet per minute climb and descent TYPE II - Range 0-3000 feet per minute climb and descent TYPE III - Range 0-4000 feet per minute climb and descent TYPE IV - Range 0-6000 feet per minute climb and descent
This Aerospace Standard covers two basic types of temperature instruments as follows: TYPE I: Ratiometer type, actuated by changes in electrical resistance of a temperature sensing electrical resistance element; the resistance changes being obtained by temperature changes of the temperature sensing resistance element. TYPE II: Millivoltmeter type, operated and actuated by varying E.M.F. output of a thermocouple; the varying E.M.F. input to the instrument being obtained by temperature changes of the temperature sensing thermocouple.
The starters covered by this specification shall be designed to operate on compressed air from ground support equipment, engine interbleed or on board air supply, for the purpose of starting aircraft jet engines.
The purpose of this standard is to provide a method of evaluating helicopter fuel economy which accounts for the significant technical variables in helicopter and powerplant design.
This SAE Aerospace Recommended Practice (ARP) recommends a methodology to be used for the design, analysis and test evaluation of modern helicopter gas turbine propulsion system stability and transient response characteristics. This methodology utilizes the computational power of modern digital computers to more thoroughly analyze, simulate and bench-test the helicopter engine/rotor system speed control loop over the flight envelope. This up-front work results in significantly less effort expended during flight test and delivers a more effective system into service. The methodology presented herein is recommended for modern digital electronic propulsion control systems and also for traditional analog and hydromechanical systems.
This SAE Aerospace Information Report (AIR) defines the power spectrum during normal and emergency operations of a twin engine helicopter and thereby postulates suitable power plant rating structures. This document does not address the power requirements for single engine helicopters or those with more than two engines.
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