The scope of this report is first to establish applicable definitions and general specification and terms prior to considering the application domain and use cases in HVDC applications. Then it will describe the methods of protection and system level coordination to and define different coordinated protection schemes to consider for aerospace application.
The turbine-engine-inlet flow distortion descriptors summarized in this document apply to the effects of inlet total-pressure, planar-wave, and total-temperature distortions. Guidelines on stability margin, destabilizing influences, types and purposes of inlet data, AIP definition, and data acquisition and handling are summarized from AIR5866, AIR5867, ARP1420, and AIR1419. The degree to which these recommendations are applied to a specific program should be consistent with the complexity of the inlet/engine integration. Total-pressure distortion is often the predominant destabilizing element that is encountered and is often the only type of distortion to be considered, i.e, not all types of distortion need to be considered for all vehicles.
The purpose of this SAE Recommended Practice is to provide guides toward standard conditions for operating marine hydraulic transmissions where push-pull cable control is applicable. For control cable information see SAE J917.
The purpose of this SAE Recommended Practice is to provide guides toward standard conditions for operating marine engine throttles (gasoline or diesel) where push-pull cable control is applicable. For control cable information see SAE J917.
This ARP describes methods that are known to have been used by aircraft manufacturers to evaluate aircraft aerodynamic performance and handling effects following application of aircraft ground deicing/anti-icing fluids (“fluids”), as well as methods under development. Guidance and insight based upon those experiences are provided, including: Similarity analyses. Icing wind tunnel tests. Flight tests. CFD and other numerical analyses. This ARP also describes: The history of evaluation of the aerodynamic effects of fluids. The effects of fluids on aircraft aerodynamics. The testing for aerodynamic acceptability of fluids for SAE and regulatory qualification performed in accordance with AS5900.
This procurement specification covers tubular-shaped, slotted spring pins made of a corrosion and moderate heat resistant, martensitic iron base alloy of the type identified under the Unified Numbering System as UNS S42000 and heat treated to permit flexure when inserted into a hole.
This procurement specification covers rivets made from an aluminum alloy designated as 2117-T4, solution treated. The following specification designations and their rivet coatings are covered:
This specification covers an aluminum alloy in the form of sheet 0.020 to 0.126 inch (0.51 to 3.20 mm), inclusive, in nominal thickness, with fine grain structure (see 8.5).
This specification covers a titanium alloy in the form of bars, wire, flash-welded rings 4.000 inches (101.60 mm) and under in nominal diameter or least distance between parallel sides and 16 square inches (103 cm2) and under in cross-sectional area, and stock of any size for flash-welded rings (see 8.7).
This SAE Standard applies to all forestry machines exposed to the hazard of objects penetrating the front of the operator station (other than the roof). This would include:
This procurement specification covers aircraft-quality solid rivets made from a corrosion- and heat-resistant cobalt alloy of the type identified under the Unified Numbering System as UNS R30605.
This procurement specification covers aircraft-quality solid rivets and tubular end rivets made from a corrosion- and heat-resistant nickel alloy of the type identified under the Unified Numbering System as UNS N06002.
This procurement specification covers split cotter pins with optional ends (see Figure 1), made from a corrosion resistant steel of the type identified under the Unified Numbering System as UNS S30200.