ADS-10C-SP, AERONAUTICAL DESIGN STANDARD PRACTICE AIR VEHICLE TECHNICAL DESCRIPTION

ADS-10C-SP, AERONAUTICAL DESIGN STANDARD PRACTICE AIR VEHICLE TECHNICAL DESCRIPTION. This standard practice Aeronautical Design Standard specifies the air vehicle technical data necessary to perform a detailed analysis of the performance, handling qualities, rotor dynamics, airframe dynamics, and acoustics of proposed new development or derivative rotorcraft. It is the purpose of this standard to provide a clear technical description of the proposed air vehicle and its components at a level of detail consistent with the current stage of its design. To this end, the data requirements are divided into topics and the topics are divided into three levels: Level I, Level II, and Level III. Level I (minimum) requires sufficient information to conduct a basic performance and stability and control analysis including the aerodynamic effects of the rotor system and the fuselage. Level II (intermediate) requires all of the data required for Level I plus additional data required for more detailed rotor and fuselage aerodynamics and a basic dynamic analysis of the rotors and the fuselage. Level III (detailed) is intended to allow a very detailed aerodynamic and dynamic analysis.

ADS-13F-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK AIR VEHICLE MATERIALS AND PROCESSES

ADS-13F-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK AIR VEHICLE MATERIALS AND PROCESSES. This ADS handbook embodies the general guidelines of the Army Aviation and Troop Command (ATCOM) for the materials and processes utilized in the design and construction of Army aircraft. It is for guidance only and cannot be cited as a requirement. V it is so cited, the contractor does not have to comply.

ADS-1B-PRF, AERONAUTICAL DESIGN STANDARD ROTORCRAFT PROPULSION SYSTEM AIRWORTHINESS QUALIFICATION REQUIREMENTS GROUND AND FLIGHT TEST SURVEYS AND DEMO

ADS-1B-PRF, AERONAUTICAL DESIGN STANDARD ROTORCRAFT PROPULSION SYSTEM AIRWORTHINESS QUALIFICATION REQUIREMENTS GROUND AND FLIGHT TEST SURVEYS AND DEMONSTRATIONS. The Propulsion systems shall meet their allocated performance and operate in such a manner that the aircraft shall be able to be function safely throughout the operational envelope and meet the performance requirements as defined in the applicable weapon system specification. The following qualification requirements for the propulsion systems are required to verify compliance with the performance requirements of paragraph 1.1 above as applicable to the aircraft design configuration.

ADS-20-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK ARMAMENT AND FIRE CONTROL SYSTEM SURVEY FOR ARMY AIRCRAFT

ADS-20-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK ARMAMENT AND FIRE CONTROL SYSTEM SURVEY FOR ARMY AIRCRAFT. This handbook contains guidance for the performance of a "survey" on armament and fire control subsystems integrated on an aircraft. A survey is the act of collecting information to determine the current state of the design with respect to established performance requirements. The survey will consist primarily of ground and flight tests. Unless otherwise specified in the contract, the survey will be used to find needed improvements or problem areas that need resolution prior to commitment to the demonstration phase that verifies compliance with contract requirements. Surveys are normally conducted on new or major modifications to reduce program risk. At the discretion of the Government, surveys can be required for smaller armament and fire control modification programs. For purposes of this handbook, the terms "armament" and "weapon" are interchangeable.

ADS-27A-SP, REQUIREMENTS FOR ROTORCRAFT VIBRATION SPECIFICATIONS, MODELING, AND TESTING

ADS-27A-SP, AERONAUTICAL DESIGN STANDARD- STANDARD PRACTICE - REQUIREMENTS FOR ROTORCRAFT VIBRATION SPECIFICATIONS, MODELING, AND TESTING. This standard practice presents the vibration related requirements for the development and qualification of rotorcraft, rotor craft subsystems, and equipment to be installed on rotorcraft, including external stores. Gunfire induced vibration qualification, when appropriate, should be in accordance with the vibration tests of MIL-STD-810. The development process follows the engineering System Specification (system procurement) or Production Specification (item procurement). Prior to a Request for Proposal (REP) release, the Government defines its engineering specification based on MIL-STD-961. Competing contractors base their proposed engineering specification on the Government specification, their interpretation of the specification and the peculiarities of their proposed hardware. The contractual engineering specification is negotiated based on cost, technology, and specification considerations between contractors and Government prior to contract award. The companion document to the engineering specification is the Airworthiness Qualification Specification (AQS) which describes the analysis and testing required at each step of the development process to show that the contractor's design will be able to meet the intent of the engineering systems specification. The AQS is negotiated in concert with the engineering specification and should reflect state-of-the-art design, analysis, and testing techniques. Equipment to be developed and qualified requires different development and qualification strategies depending on the complexity of the system or item and trade-offs between development costs, production costs, rotorcraft weight penalties associated with over-design and performance and reliability penalties associated with under-design.

ADS-33E-PRF, AERONAUTICAL DESIGN STANDARD PERFORMANCE SPECIFICATION HANDLING QUALITIES REQUIREMENTS FOR MILITARY ROTORCRAFT

ADS-33E-PRF, AERONAUTICAL DESIGN STANDARD PERFORMANCE SPECIFICATION HANDLING QUALITIES REQUIREMENTS FOR MILITARY ROTORCRAFT. This specification contains the requirements for the flying and ground handling qualities of rotorcraft. It is intended that the specification should cover land based rotorcraft which have primary missions ranging from scout and attack to utility and cargo. Additional requirements or modified standards may be required for rotorcraft that have to operate from small ships in sea states resulting in more than small ship motion.

ADS-37A-PRF, AERONAUTICAL DESIGN STANDARD, ELECTROMAGNETIC ENVIRONMENTAL EFFECTS (E3) PERFORMANCE AND VERIFICATION REQUIREMENTS

ADS-37A-PRF, AERONAUTICAL DESIGN STANDARD, ELECTROMAGNETIC ENVIRONMENTAL EFFECTS (E3) PERFORMANCE AND VERIFICATION REQUIREMENTS. This document establishes electromagnetic environmental effects (E3)performance and verification requirements for aircraft systems.

ADS-39A-HDBK, HANDBOOK SOURCE APPROVAL AND ENGINEERING TEST REQUIREMENTS FOR ALTERNATE SOURCES OF HELICOPTER DRIVE SYSTEM ASSEMBLIES AND COMPONENTS

ADS-39A-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK SOURCE APPROVAL AND ENGINEERING TEST REQUIREMENTS FOR ALTERNATE SOURCES OF HELICOPTER DRIVE SYSTEM ASSEMBLIES AND COMPONENTS. This Aeronautical Design Standard (ADS) specifies Source Approval and Engineering Test requirements for alternate sources of helicopter drive system assemblies and components. These requirements are necessary to insure that an alternate source has the advanced manufacturing and assembly skills required to produce these complex parts. Completion of these requirements before contract award is necessary to reduce procurement risk associated with overcoming technical issues with first-time producers of these parts. Fielding of parts before the capabilities of the alternate source is substantiated could result in failures and/or early removals in the field, which may significantly impact the safety and reliability of the weapon systems they are used on. These requirements are based on the requirements used to qualify the original source of the part. The requirements specified in this ADS must be substantiate

ADS-40A-SP, AERONAUTICAL DESIGN STANDARD STANDARD PRACTICE AIR VEHICLE FLIGHT PERFORMANCE DESCRIPTION

ADS-40A-SP, AERONAUTICAL DESIGN STANDARD STANDARD PRACTICE AIR VEHICLE FLIGHT PERFORMANCE DESCRIPTION.This Standard Practice Aeronautical Design Standard specifies the flight performance data required to document the characteristics and capabilities of an air vehicle. It is the purpose of this standard to provide a clear and complete documentation of the air vehicle flight performance at a level of detail which is consistent with the current stage of design/development of the aircraft. The data requirements are divided into three levels: Level I, Level II, and Level III. Level I (the minimum requirement) addresses the level of detail which would be available during the late conceptual design or early preliminary design stage of the air vehicle. Level II addresses the level of detail which would be available during the late preliminary design or early detailed design stage. Level III addresses the level of detail which would be available during the late detailed design or flight test stage. Each level is intended to be consistent with the corresponding level in ADS-10C-SP, Air Vehicle Technical Description Selected sections of this standard may be added to or deleted. This standard is intended to prescribe a minimum quality of documentation at each Level.

ADS-43A-HDBK, HANDBOOK QUALIFICATION REQUIREMENTS AND IDENTIFICATION OF CRITICAL CHARACTERISTICS FOR AIRCRAFT ENGINE COMPONENTS

ADS-43A-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK QUALIFICATION REQUIREMENTS AND IDENTIFICATION OF CRITICAL CHARACTERISTICS FOR AIRCRAFT ENGINE COMPONENTS. Potential alternate manufacturing sources of aircraft engine parts, components, or assemblies are required to provide substantiation that the specific item offered meets or exceeds the identical item furnished by the original manufacturer in terms of service life, strength, durability, form, fit, and function. The substantiation requirements for alternate manufacturing source approval are included in this document. Candidates for alternate source approval are required to submit to Army Aviation and Troop Command (USAATCOM), Engineering Directorate a plan designed to meet the substantiation requirements. The USAATCOM Engineering Directorate will review the plan to insure that the proposed testing is sufficient to determine that the item to be manufactured will be equivalent to the original. The Engineering Test Table (ETT) in the Flight Safety Parts Information System (FSPIS) lists the testing that is normally required for alternate sources which use material, castings, forging, and process sources approved by the prime contractor or government for the item in question. Flight Safety Parts (FSP) and critical characteristics are identified. A potential alternate manufacturing source requesting approval is required to submit written substantiating data on a part, component, or assembly to become a qualified vendor. This data should include, but not limited to, the candidates capability to manufacture the item, a manufacturing plan (including sources for forging, castings, etc.), and a test plan to satisfy engineering test requirements. After USAATCOM engineering examines the data and determines that the alternate source is capable of manufacturing the item in accordance with all of the existing requirements, the alternate source will be added to the Potential Suppliers List. Should the alternate source bid successfully, all quality assurance requirements, qualification tests, and engineering tests must be completed prior to delivery of parts to the procuring agency. At the discretion of USAATCOM engineering, previous suppliers who have not completed the engineering test may be required to do so prior to the delivery of additional parts.

ADS-45-HDBK, HANDBOOK DATA AND TEST PROCEDURES FOR AIRWORTHINESS RELEASE

ADS-45-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK DATA AND TEST PROCEDURES FOR AIRWORTHINESS RELEASE FOR U.S. ARMY HELICOPTER ARMAMENT TESTING (GUNS, ROCKETS, MISSILES. This handbook establishes guidelines for data and test procedures, that should be completed prior to the issuance of a Contractor Flight Release (CFR) or Airworthiness Release (AWR) to conduct flight testing of armament on U.S. Amy aircraft. A CFRIAWR is required for aircraft ground firing tests with the rotors turning, and for aircraft flight tests, both non-fuing (captive carriage) and firing. The guidelines include documentation on armament configurationldesign, analyses, component tests and aircraft ground tests. The documentation is required so the Govenunent can conduct an airworthiness assessment in order to ensure that U.S. Amy aircraft are safe to flight test. The requirements should be tailored based on the nature, magnitude, complexity and integration risk associated with the new or modified armament system. The difference between an "airworthy" system and a "qualified" system is the degree to which the system meets specification requirements and provides the system "performance" expected by the user. For a tutorial on the overall helicopter airworthiness qualification process, including flight releases, see ADS-5 1- HDBK. For purposes of this handbook, the terms "armament" and "weapon" are interchangeable.

ADS-50-PRF, ROTORCRAFT PROPULSION PERFORMANCE AND QUALIFICATION REQUIREMENTS AND GUIDELINES.

ADS-50-PRF, ROTORCRAFT PROPULSION PERFORMANCE AND QUALIFICATION REQUIREMENTS AND GUIDELINES. This ADS establishes the performance and verification which constitute qualification requirements for rotorcraft propulsion systems. For the purposes of this ADS, propulsion systems includes engine and auxiliary power unit installations, start, fire detection/extinguishing, drive, fuel, environmental control, and hydraulic systems.

ADS-51-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK

ADS-51-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK ROTORCRAFT AND AIRCRAFT QUALIFICATION (RAQ) HANDBOOK. The purpose of this handbook is twofold. First, it is intended to serve as a tutorial for persons unfamiliar with the airworthiness qualification process. This includes Government and contractor personnel who are involved in development of requirements or members of the design team who are not directly involved in the qualification process. In this context the handbook provides an overview of the airworthiness process for developing requirements. It describes air vehicle and typical system requirements as a guide for airworthiness qualification. Second, it is intended to serve as a reference guide for those involved in preparing airworthiness qualification documentation. This includes persons who are responsible for generating and reviewing documentation that establishes the airworthiness of systems and subsystems. Requirements for and examples of airworthiness documentation are covered in the Appendices to this handbook.

ADS-61A-PRF, AERONAUTICAL DESIGN STANDARD PERFORMANCE SPECIFICATION FOR ARMY AIRCRAFT CLEANERS, AQUEOUS AND SOLVENT

ADS-61A-PRF, AERONAUTICAL DESIGN STANDARD PERFORMANCE SPECIFICATION FOR ARMY AIRCRAFT CLEANERS, AQUEOUS AND SOLVENT. This specification covers the requirements for cleaners used on Army aircraft.

ADS-62-SP, PRACTICE DATA AND TEST REQUIREMENTS FOR AIRWORTHINESS RELEASE FOR HELICOPTER SENSOR DATA AND TESTING REQUIREMENTS IN DEVELOPMENT STAGE

ADS-62-SP, AERONAUTICS DESIGN STANDARD STANDARD PRACTICE DATA AND TEST REQUIREMENTS FOR AIRWORTHINESS RELEASE FOR HELICOPTER SENSOR DATA AND TESTING REQUIREMENTS IN DEVELOPMENT STAGE. This standard establishes design and documentation requirements which shall be completed prior to issue of a Flight Release or Airworthiness Release (AWR) to conduct helicopter Flight Testing on Pilotage and Target Acquisition/Designator System Sensors. It includes statements, analyses and preliminary analyses presenting the Pilotage and Target Acquisition Designation System/subsystem and guarantees a certain safety standard. The requirements may be tailored for each test.

ADS-63-SP, RADAR SYSTEM AIRWORTHINESS QUALIFICATION AND VERIFICATION REQUIREMENTS

ADS-63-SP, AERONAUTICAL DESIGN STANDARD STANDARD PRACTICE RADAR SYSTEM AIRWORTHINESS QUALIFICATION AND VERIFICATION REQUIREMENTS. This document establishes the verification methods and qualification requirements for radar systems installed on U.S. Army aircraft. A combination of analyses, component testing, ground testing, and flight testing, will verify the design, installations and performance of the radar subsystem prior to the formal Airworthiness Qualification Release. The Airworthiness Qualification program encompasses: a. Design reviews. b. Engineering design substantiation analyses. c. Contractor development and airworthiness qualification tests, including component, subsystem and system testing. d. Government systems development and airworthiness qualification testing, including: (1) Preliminary Airworthiness Evaluation (PAE). (2) Airworthiness and Flight Characteristics Test (A&FC). e. Government Operational Testing (OT) if required by the approved Test Engineering Master Plan (TEMP).

ADS-65-HDBK, HANDBOOK AIRWORTHINESS QUALIFICATION AND VERIFICATION GUIDANCE FOR ELECTRO-OPTICAL AND SENSOR SYSTEMS

ADS-65-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK AIRWORTHINESS QUALIFICATION AND VERIFICATION GUIDANCE FOR ELECTRO-OPTICAL AND SENSOR SYSTEMS. This document establishes the guidance for airworthiness qualification and discusses the methods of verification for Electro-Optical (EO) and Sensor Systems (SS), mission sensor group, and any other targeting/pilotage systems installed on U.S. Army aircraft. It also establishes the guidance for ancillary equipment, including displays, lasers and targeting systems. The sensors and system-related EO equipment are collectively referred to as a “sensor system” in this document. A combination of analyses and testing is used to verify the design, installation and operation of the sensor system and to support airworthiness qualification.

ADS-66-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK GUIDANCE FOR DATA FOR SAFETY OF FLIGHT AIRWORTHINESS RELEASE FOR HELICOPTER AIRCRAFT SURVIVABILITY

ADS-66-HDBK, AERONAUTICAL DESIGN STANDARD HANDBOOK GUIDANCE FOR DATA FOR SAFETY OF FLIGHT AIRWORTHINESS RELEASE FOR HELICOPTER AIRCRAFT SURVIVABILITY EQUIPMENT (ASE). This handbook provides guidance for the ASE (Aircraft Survivability Equipment) data submittals, which will be completed prior to issue of a Safety of Flight (SOF) Release for testing of new/modified ASE equipment installed on U.S. Army aircraft. A combination of analyses, component testing, and ground testing will be used to issue the first release to test the system, which should be stipulated in each contract. The ADS-66 handbook would assist the contractor in determining the exact data/reports needed to assure airworthiness of the system.

ADS-68-IS, AERONAUTICAL DESIGN STANDARD INTERFACE STANDARD AIRCRAFT ELECTRICAL POWER CHARACTERISTICS

ADS-68-IS, AERONAUTICAL DESIGN STANDARD INTERFACE STANDARD AIRCRAFT ELECTRICAL POWER CHARACTERISTICS. The primary purpose of this standard is to provide the requisite information to promote compatibility between aircraft electrical power, external electrical power, and the airborne equipment that uses that power, with MIL-STD-704 serving as the governing document. Accordingly, the content of past versions of MIL-STD-704 is presented here to enable comparisons of the detailed requirements. To ensure that an individual piece of equipment will work satisfactorily in multiple types of aircraft, a worstcase set of electrical interface criteria should be developed from the applicable versions of MIL-STD-704 and subsequently imposed as an interface requirement for that equipment to ensure compatibility with the various types of aircraft being addressed.

ADS-69-PRF, AERONAUTICAL DESIGN STANDARD PERFORMANCE SPECIFICATION HYDRAULIC FLUID, PETROLEUM BASE; AIRCRAFT, MISSILE, AND ORDNANCE

ADS-69-PRF, AERONAUTICAL DESIGN STANDARD PERFORMANCE SPECIFICATION HYDRAULIC FLUID, PETROLEUM BASE; AIRCRAFT, MISSILE, AND ORDNANCE. This ADS describes the characteristics and provides the replacements for a petroleum base hydraulic fluid for use in the -54 deg C to +135 deg C temperature range.