Airworthiness Certification Criteria - AF
MIL-HDBK-516B Expanded Version26 Sep 2005Superceding 20 Apr 2005ASC/ENAirworthiness Certification CriteriaExpanded Version ofMIL-HDBK-516B26 Sep 2005Document POC:Kathleen WilsonASC/ENSIASC.EN.516B@wpafb.af.milDISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited.(Case 88ABW-2010-6398, 6 December2010)0
MIL-HDBK-516B Expanded – 26 Sep 2005FOREWORDThis document is for the use of Air Force programs to aid in the development of TailoredAirworthiness Certification Criteria (TACC) or Modified Airworthiness Certification Criteria(MACC) documents.It contains all sections (1 – 20 plus Appendices) from the MIL-HDBK-516B, 26 Sep 2005publication. The criteria and references (sections 4 through 20) contain the addition ofrecommended standards and methods of compliance for each of the criterion.The criteria contained herein are qualitative in nature. More specific guidance and backgroundfor specific criteria may be found in the appropriate Joint Service Specification Guides (JSSG)and Title 14, Code of Federal Regulations referenced herein. Also, note that each sectioncontains a list of typical certification source data that may be referenced for evaluating systemcompliance with that section’s criteria. Terms such as "acceptable" used in the criteria areparameters whose specific definition must be determined and documented by the implementingoffice in the context of each unique air system.This document is forms the basis for the USAF Airworthiness Certification Criteria future updateto MIL-HDBK-516B currently in writing, and may be updated as the standards and methods ofcompliance sections for each criterion are further developed.Note that in electronic versions, the blue highlighted paragraph headings or text in handbooksections 4 through 19 are internal hyperlinks to bookmarks in the appendix Technical Points ofContact table. Clicking the mouse cursor on the blue jumps you to the referenced location inthe table. To return from the Technical Points of Contact table to your jump point in thehandbook, use the back arrow key on the menu bar (enable View-Toolbars-Web for the backarrow tool). Gray shaded internal cross-references within the document perform similarly.Any questions regarding this document may be directed to the POC at the MIL-HDBK-516Bmailbox:ASC.EN.516B@wpafb.af.milTo use this document:Criteria are either applicable or nonapplicable. Justification must be provided fornonapplicability.Standards and methods of compliance may be tailored to the needs of the program for theapplicable criterion.References are for guidance in understanding the criterion and tailoring the standards andmethods of compliance.i
MIL-HDBK-516B Expanded – 26 Sep 2005CONTENTSParagraphPage1.SCOPE.11.1Purpose. .11.2Applicability. .11.3Cross references and technical points of contact. .21.4Information sources. .22.APPLICABLE DOCUMENTS .42.1General. .43.DEFINITIONS & ABBREVIATIONS .173.1Definitions.173.2Abbreviations and acronyms. .214.SYSTEMS ENGINEERING .254.1Design criteria. .264.2Tools and databases. .274.3Materials selection. .274.4Manufacturing and quality. .274.5Operator's and maintenance manuals/technical orders. .294.6Configuration identification. .304.7Configuration status accounting. .315.STRUCTURES .325.1Loads.335.2Structural dynamics. .405.3Strength. .455.4Damage tolerance and durability (fatigue). .495.5Mass properties.535.6Flight release. .546.FLIGHT TECHNOLOGY .566.1Stability and control. .576.2Vehicle control functions (VCF). .866.3Aerodynamics and performance. .1417.PROPULSION AND PROPULSION INSTALLATIONS.1547.1Propulsion safety management. .155ii
MIL-HDBK-516B Expanded – 26 Sep 2005CONTENTS - ContinuedParagraphPage7.2Gas turbine engine applications. .1577.3Alternate propulsion systems. .1818.AIR VEHICLE SUBSYSTEMS .1938.1Hydraulic and pneumatic systems. .1938.2Environmental control system (ECS). .1978.3Fuel system. .2028.4Fire and hazard protection. .2098.5Landing gear and deceleration systems. .2178.6Auxiliary/emergency power system(s) (APS/EPS). .2408.7Aerial refueling system. .2478.8Deleted - Propulsion installations moved to section 7.2.5 .2648.9Mechanisms.2648.10External cargo hook systems (rotary wing). .2708.11External rescue hoist (rotary wing). .2728.12Fast rope insertion/extraction system (FRIES) (rotary wing). .2739.CREW SYSTEMS .2749.1Escape and egress system. .2749.2Crew stations and aircraft interiors. .2789.3Air vehicle lighting. .2829.4Human performance. .2859.5Life support systems. .2889.6Transparency integration. .2919.7Crash survivability. .2949.8Air transportability and airdrop. .2989.9Lavatories, galleys, and areas not continuously occupied. .30310.DIAGNOSTICS SYSTEMS .30610.1Failure modes. .30610.2Operation. .30711.AVIONICS .30911.1Avionics architecture. .30911.2Avionics subsystems. .31811.3Avionics air vehicle installation. .323iii
MIL-HDBK-516B Expanded – 26 Sep 2005CONTENTS - ContinuedParagraphPage12.ELECTRICAL SYSTEM .32512.1Electric power generation system. .32512.2Electrical wiring system, including power distribution. .33113.ELECTROMAGNETIC ENVIRONMENTAL EFFECTS (E3) .33713.1Component/subsystem E3 qualification. .33713.2System-level E3 qualification. .33814.SYSTEM SAFETY .34314.1System safety program.34314.2Safety design requirements. .34614.3Software safety program. .34915.COMPUTER RESOURCES .35115.1Air vehicle processing architecture. .35115.2Functional design integration of processing elements. .35515.3Subsystem/processing element. .35616.MAINTENANCE .36416.1Maintenance manuals/checklists.36416.2Inspection requirements.36617.ARMAMENT/STORES INTEGRATION .36817.1Gun/rocket integration and interface.36917.2Stores integration. .37017.3Laser integration and interface. .37217.4Safety interlocks. .37418.PASSENGER SAFETY .37518.1Survivability of passengers.37518.2Fire resistance. .38018.3Physiology requirements of occupants. .38119.MATERIALS .38319.1Properties and processes. .38419.2Corrosion. .38519.3Nondestructive inspection. .38519.4Wear and erosion. .38620.OTHER CONSIDERATIONS .387iv
MIL-HDBK-516B Expanded – 26 Sep 2005CONTENTS - ContinuedParagraphPage20.1Mission/test equipment and cargo/payload safety. .38721.NOTES .38921.1Changes from previous issue. .38921.2Subject term (key word) list. .389A.1.SCOPE.390A.2.TECHNICAL POINTS OF CONTACT .390A.3.CROSS-REFERENCE TABLE OF MAJOR SECTION CHANGESFROM MIL-HDBK-516A TO MIL-HDBK-516B .394v
MIL-HDBK-516B Expanded – 26 Sep 2005AIRWORTHINESSCERTIFICATION CRITERIAThis document is approved for use by all Departments and Agenciesof the Department of Defense.1.SCOPE1.1 Purpose.This document establishes the airworthiness certification criteria to be used in the determinationof airworthiness of all manned and unmanned, fixed and rotary wing air vehicle systems. It is afoundational document to be used by the system program manager, chief engineer, andcontractors to define their air system’s airworthiness certification basis.This handbook is for guidance only. This handbook cannot be cited as a requirement. If it is,the contractor does not have to comply.1.2 Applicability.These criteria should be tailored and applied at any point throughout the life of an air vehiclesystem when an airworthiness determination is necessary, especially whenever there is achange to the functional or product baseline.Rotary wing air vehicle and unmanned aerial vehicle/remotely operated aircraft (UAV/ROA)features demand unique safety-of-flight (SOF) system requirements. Therefore, unique criteriaare included for these types of systems to ensure that minimum levels of design for safeoperation and maintenance are established. The UAV/ROA operating system can be built intothe vehicle or be part of the control station for remotely operated aircraft. The UAV/ROA systemcomprises the control station, data links, flight control system, communications systems/links,etc., as well as the air vehicle. UAV/ROAs vary greatly in size, weight, and complexity.Because they are unmanned, SOF risks associated with loss of aircrew may not apply.However, as with manned air vehicles, SOF risk associated with personnel, damage toequipment, property, and/or environment must be considered. As such, the airworthinesscriteria may be tailored for this unique application, including when a UAV/ROA is designed to be“expendable” or where the UAV/ROA will conduct missions with “minimum life expectancy.”Consideration should be given to the environment in which the UAV/ROA will be operated(controlled test range, national airspace, fleet usage, including ship based applications), to theairframe life for which the air vehicle is designed, and to the “expendability” of the UAV/ROA inclose proximity to the control system, personnel, property, or other equipment.Similarly, air vehicles intended for use aboard ship have unique requirements in areas such asstructural integrity, propulsion system dynamic response and tolerance to steam ingestion,control systems response to approach and landings in high turbulence conditions,electromagnetic environmental effects, deck handling, support and servicing, and pilot field ofview.Commercial derivative aircraft (CDA) are initially approved for safety of flight by the FederalAviation Administration (FAA) and may have an FAA approved Certificate of Airworthiness. Anynon-FAA approved alteration to a CDA may render all FAA certifications invalid. Whilealterations to CDA are covered by rules unique to each branch of service, the operating servicealways has the responsibility for the airworthiness certification approval under public aircraft1
MIL-HDBK-516B Expanded – 26 Sep 2005rules. Therefore, when planning any alterations to an FAA certified CDA, the modifier shouldcontact the FAA Military Certification Office (MCO) in Wichita, KS at the earliest opportunity.Agreements for reimbursement for military service work performed by the FAA are in place, andin many cases MCO assistance on these alterations may be accomplished without additionalcost.In all instances, complete and accurate documentation of both applicability and system specificmeasurable criteria values is critical to ensuring consistent, timely, and accurate airworthinessassessments.1.2.1 Tailoring to create the certification basisNot all of the airworthiness criteria apply to every type of air vehicle; also, platform-unique,previously undefined criteria may need to be added to fully address safety aspects of uniqueconfigurations. Therefore, tailor the total set of criteria to identify a complete (necessary andsufficient) subset of applicable airworthiness criteria, creating the system’s certification basis.This certification basis should be fully documented and maintained under strict configurationcontrol.Tailoring rules are as follows:a. Identify each criterion as either applicable or nonapplicable, considering system orproduct complexity, type, data, and intended use. Document the rationale for identifying anycriteria as nonapplicable.b. Applicable criteria may not be deleted or modified in any manner. However, if a portionof otherwise applicable criteria does not apply, identify the applicable and nonapplicableportions, and document the rationale.c. Supplement applicable criteria with specific measurable parameters, where appropriate(i.e., they add value to the definition of airworthiness requirements).d. Develop additional criteria, as appropriate, for any capabilities or systems not fullyaddressed by the criteria contained in this handbook.1.3 Cross references and technical points of contact.The criteria included in this document are written with the intent that an experienced engineer,trained in the specific technical area under consideration, should be able to interpret, tailor,apply, and evaluate a particular system’s compliance with the criteria. To assist in this effort,military and civil references are included with the specific criteria.For additional assistance in interpreting or applying the criteria, call the appropriate sectiontechnical point of contact, or the FAA MCO, provided at appendix A.2.1.4 Information sources.Each section in the Airworthiness Certification Criteria is matched with corresponding Title 14,Code of Federal Regulations reference (14CFR reference) and Joint Service SpecificationGuides (JSSG). In addition, the complete listing of 14CFR reference advisory circulars wasconsulted for appropriate guidance in airworthiness certification.The FAA Title 14 Code of Federal Regulations Part (i.e., 23, 25, 27, 29) referenced isdependant on airplane type, and must be consistent with airplane size and usage. The listshown is not all inclusive, and the user is cautioned to only look at the reference material as aguide, and not for purposes of citing requirements. The user is also advised to use additionalFAA Advisory Circulars or other FAA Policy documents, such as Orders and Notices that maybe found on the FAA website, to assist in understanding the FAA's implementation of theregulatory requirements.2
MIL-HDBK-516B Expanded – 26 Sep 20053
MIL-HDBK-516B Expanded – 26 Sep 20052.APPLICABLE DOCUMENTS2.1 General.The documents listed below are not necessarily all of the documents referenced herein but arethose necessary to understand the information provided by this handbook. Refer to the currentversion of these documents, unless otherwise indicated.2.1.1 Government specifications, standards, and handbooks.The following specifications, standards, and handbooks form a part of this document to theextent specified herein.DEPARTMENT OF DEFENSE SPECIFICATIONSJoint Service Specification Guides (JSSG):JSSG-2000Air SystemJSSG-2001Air VehicleJSSG-2005Avionic Subsystem, Main BodyJSSG-2006Aircraft StructuresJSSG-2007Engines, Aircraft, TurbineJSSG-2008Vehicle Control and Management System (VCMS)JSSG-2009Air Vehicle SubsystemsJSSG-2010Crew SystemsClick the link below to view the unlimited distribution JSSGs(http://engineering.wpafb.af.mi
(controlled test range, national airspace, fleet usage, including ship based applications), to the airframe life for which the air vehicle is designed, and to the “expendability” of the UAV/ROA in close proximity to the
Certification and Continuing Airworthiness, včetně Amendmentu 1. Dokument ICAO Airworthiness Manual (Doc 9760), Volume II byl vytvořen na základě materiálů obsažených v dokumentech Manual of Procedures for an Airworthiness Organization (Doc 9389), Continuing Airworthiness Manual (Doc 9642) a Airworthiness Techn
airworthiness criteria MIL-HDBK-516 [Airworthiness Certification Criteria] was created in October 1st 2002. Civil and military airworthiness processes both rely upon managing and mitigating risk. Civil type certification relies upon minimum flight safety standards. Military
Continued airworthiness standards The current international standards for the continued airworthiness of aircraft are defined in the ICAO Airworthiness Manual (Doc 9760) published in 2001 and in Annex 6 - Operation Footnote 3 With t
mit icaticat federal aviation regulations y part 1 - definitions and abbreviations y part 11 - general rulemaking procedures y part 21 - certification procedures for products and parts y part 23 - airworthiness standards: normal, utility, acrobatic, and commuter category airplanes y part 25 - airworthiness standards: transport category airplanes y part 27 - airworthiness standards: normal .
MIL-HDBK-516B w/CHANGE 1 29 February 2008 SUPERSEDING MIL-HDBK-516B 26 September 2005 DEPARTMENT OF DEFENSE HANDBOOK AIRWORTHINESS CERTIFICATION CRITERIA THIS HANDBOOK IS FOR GUIDANCE ONLY. DO NOT CITE THIS DOCUMENT AS A REQUIREMENT. DISTRIBUTION STATEMENT A. Approved f
based on the US MIL-HDBK-516 — Airworthiness Certifi cation Criteria, to address the objective of common certifi cation and design codes. The new European Military Aircraft Certifi cation Criteria (EMACC) handbook contains harmonised certifi cation criteria developed to addres
– MIL-HDBK-516 is the ‘DoD Handbook containing the airworthiness certification criteria. It is important that there be a means to trace 516 criteria/standards/MOCs and data artifacts to the DEL EDEF (EDRAP Data Evaluation Form) One page word document produced to support the r
(STANAG 4746) Airworthiness, “Lite” UAS (STANAG 4703) Airworthiness, Rotary Wing (STANAG 4702) Airworthiness, Fixed Wing (STANAG 4671) Weapons Integ. (STANAG 4737) Interoperability, (STANAG 4586) Data Link (STANAG 4660) Command & Control . C2 . ISR Data NATO Standardization Activities.
