ASTM F3060-20

Standard Terminology for Aircraft

SCOPE
1.1 This terminology contains a listing of terms, abbreviations, acronyms, and symbols related to aircraft covered by ASTM Committees F37 and F44 airworthiness design standards. It is intended to ensure the consistent use of terminology throughout all ASTM light aircraft standards.  
1.2 Units—The definitions of units will be as defined in NIST SP 330 and will not be duplicated in this document. NIST SP 330 is available on the internet. The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in nonconformance with the standard.  
1.3 Source References—The listed document(s) was/were the original source for the definition. However, the definition may have been edited for use in this document and the F37 and F44 standards, and may not completely match the original in every respect.  
1.4 A definition adapted from a particular standard within the ASTM aircraft collection of standards is not limited to use within only those standards.  
1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.6 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

General Information

• Status: Published
• Publication Date: 31-Dec-2019
• ICS: 01.040.49 - Aircraft and space vehicle engineering (Vocabularies)
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F44 - General Aviation Aircraft
• Drafting Committee: F44.91 - Terminology

Relations

• Replaces: ASTM F3060-16a - Standard Terminology for Aircraft
• Effective Date: 01-Jan-2020
• Replaces: ASTM F2626-12 - Standard Terminology for Light Sport Aircraft (Withdrawn 2018)
• Effective Date: 07-Nov-2018
• Refers: ASTM F2249-24 - Standard Specification for In-Service Test Methods for Temporary Grounding Jumper Assemblies Used on De-Energized Electric Power Lines and Equipment
• Effective Date: 01-Jan-2024
• Refers: ASTM F3116/F3116M-23a - Standard Specification for Design Loads and Conditions
• Effective Date: 01-Oct-2023
• Refers: ASTM F3061/F3061M-23b - Standard Specification for Systems and Equipment in Aircraft
• Effective Date: 01-Oct-2023
• Refers: ASTM F3061/F3061M-19a - Standard Specification for Systems and Equipment in Small Aircraft
• Effective Date: 01-Nov-2019
• Refers: ASTM F3061/F3061M-19 - Standard Specification for Systems and Equipment in Small Aircraft
• Effective Date: 01-Jun-2019
• Refers: ASTM F2799-14(2019) - Standard Practice for Maintenance of Aircraft Electrical Wiring Systems
• Effective Date: 01-Jun-2019
• Refers: ASTM F3093/F3093M-19 - Standard Specification for Aeroelasticity Requirements
• Effective Date: 15-Feb-2019
• Refers: ASTM F3062/F3062M-19 - Standard Specification for Aircraft Powerplant Installation
• Effective Date: 01-Feb-2019
• Refers: ASTM F2427-05a(2018) - Standard Specification for Required Product Information to be Provided with Lighter-Than-Air Light Sport Aircraft
• Effective Date: 01-Nov-2018
• Refers: ASTM F2242-05(2018) - Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft
• Effective Date: 01-Nov-2018
• Refers: ASTM F2356-05a(2018) - Standard Specification for Production Acceptance Testing System for Lighter-Than-Air Light Sport Aircraft
• Effective Date: 01-Nov-2018
• Refers: ASTM F3117/F3117M-18c - Standard Specification for Crew Interface in Aircraft
• Effective Date: 01-Nov-2018
• Refers: ASTM F3116/F3116M-18 - Standard Specification for Design Loads and Conditions
• Effective Date: 01-Nov-2018

Overview

ASTM F3060-20: Standard Terminology for Aircraft, developed by ASTM International, provides a comprehensive listing of terms, abbreviations, acronyms, and symbols relevant to aircraft under the jurisdiction of ASTM Committees F37 and F44. This standard ensures the uniform use of terminology across all ASTM light aircraft standards, promoting clarity and consistency in airworthiness design and regulatory compliance.

By providing consistent definitions for key aircraft-related terms, ASTM F3060-20 supports organizations, manufacturers, regulators, and aviation professionals working with light sport aircraft (LSA), general aviation, and other segments where ASTM standards are applicable. It references internationally recognized units as defined in the NIST SP 330, ensuring clear measurements and preventing confusion in both SI and inch-pound systems.

Key Topics

• Terminology Consistency: Establishes harmonized definitions for technical terms, making communication and documentation clear for all stakeholders in the aviation industry.
• Scope of Terms: Covers aircraft terminology, abbreviations, acronyms, and relevant symbols, addressing everything from airworthiness directives to maintenance practices.
• Unit Standardization: Aligns unit definitions with NIST SP 330, requiring separate application of SI and inch-pound units to avoid nonconformance.
• Referenced Sources: Provides source references for each definition, ensuring traceability and allowing adaptation from previous standards, regulations, and authoritative organizations.
• Regulatory Alignment: Designed to align with international standardization principles, supporting global interoperability and compliance.

Applications

ASTM F3060-20 is vital for:

• Aviation Standards Development: Used by committees and working groups involved in drafting and revising standards for aircraft design, construction, and operation, especially for light sport and general aviation categories.
• Certification and Compliance: Supports regulatory authorities and manufacturers in certifying compliance by providing clear, universally accepted terminology for documentation, audits, and regulatory submissions.
• Technical Documentation: Assists technical writers, maintenance organizations, and product developers in producing accurate manuals, maintenance documents, and operational guides by utilizing standardized terms.
• Training and Education: Serves as a resource for aviation training programs and educational institutions, promoting understanding and use of standard aircraft terminology for students and professionals.

Related Standards

Several related ASTM standards enhance and reference ASTM F3060-20, providing broader context and applicability, including:

• ASTM F2245: Specification for Design and Performance of a Light Sport Airplane
• ASTM F2483: Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
• ASTM F2317/F2317M: Specification for Design of Weight-Shift-Control Aircraft
• ASTM F2352: Specification for Design and Performance of Light Sport Gyroplane Aircraft
• ASTM F2746: Specification for Pilot's Operating Handbook (POH) for Light Sport Airplane
• ASTM F3116/F3116M: Specification for Design Loads and Conditions
• ASTM F3341: Terminology for Unmanned Aircraft Systems

These referenced documents, along with international materials such as ICAO Annex 8 and EASA Certification Specifications, provide the foundation for a comprehensive, globally recognized aircraft terminology framework.

Practical Value

By implementing ASTM F3060-20, stakeholders in the aviation industry can:

• Ensure clear, accurate communication across international and multidisciplinary teams
• Support industry best practices in documentation, compliance, and safety standards
• Minimize misunderstandings and nonconformance due to inconsistent terminology
• Streamline certification processes and support regulatory submissions

ASTM F3060-20 is a critical resource for anyone involved in the design, manufacture, maintenance, regulation, or operation of aircraft, underpinning the integrity and interoperability of airworthiness standards worldwide.

Standards Content (Sample)

This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation: F3060 − 20
Standard Terminology for
Aircraft
This standard is issued under the fixed designation F3060; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 2.1 ASTM Standards:
F2241 SpecificationforContinuedAirworthinessSystemfor
1.1 This terminology contains a listing of terms,
Powered Parachute Aircraft
abbreviations, acronyms, and symbols related to aircraft cov-
F2242 Specification for ProductionAcceptance Testing Sys-
ered by ASTM Committees F37 and F44 airworthiness design
tem for Powered Parachute Aircraft
standards. It is intended to ensure the consistent use of
F2243 Specification for Required Product Information to be
terminology throughout all ASTM light aircraft standards.
Provided with Powered Parachute Aircraft
1.2 Units—The definitions of units will be as defined in
F2244 Specification for Design and Performance Require-
NIST SP 330 and will not be duplicated in this document.
ments for Powered Parachute Aircraft
NIST SP 330 is available on the internet. The values stated in
F2245 Specification for Design and Performance of a Light
eitherSIunitsorinch-poundunitsaretoberegardedseparately
Sport Airplane
as standard. The values stated in each system may not be exact
F2249 Specification for In-ServiceTest Methods forTempo-
equivalents;therefore,eachsystemshallbeusedindependently
rary Grounding Jumper Assemblies Used on De-
of the other. Combining values from the two systems may
Energized Electric Power Lines and Equipment
result in nonconformance with the standard.
F2279 Practice for QualityAssurance in the Manufacture of
Fixed Wing Light Sport Aircraft (Withdrawn 2014)
1.3 Source References—The listed document(s) was/were
the original source for the definition. However, the definition F2295 Practice for Continued Operational Safety Monitor-
ing of a Light Sport Aircraft (Withdrawn 2019)
may have been edited for use in this document and the F37 and
F44 standards, and may not completely match the original in F2317/F2317M Specification for Design of Weight-Shift-
Control Aircraft
every respect.
F2352 Specification for Design and Performance of Light
1.4 A definition adapted from a particular standard within
Sport Gyroplane Aircraft
theASTM aircraft collection of standards is not limited to use
F2354 SpecificationforContinuedAirworthinessSystemfor
within only those standards.
Lighter-Than-Air Light Sport Aircraft
1.5 This standard does not purport to address all of the
F2355 Specification for Design and Performance Require-
safety concerns, if any, associated with its use. It is the
ments for Lighter-Than-Air Light Sport Aircraft
responsibility of the user of this standard to establish appro-
F2356 Specification for ProductionAcceptance Testing Sys-
priate safety, health, and environmental practices and deter-
tem for Lighter-Than-Air Light Sport Aircraft
mine the applicability of regulatory limitations prior to use.
F2411 Specification for Design and Performance of an
1.6 This international standard was developed in accor- 3
Airborne Sense-and-Avoid System (Withdrawn 2014)
dance with internationally recognized principles on standard-
F2415 Practice for Continued Airworthiness System for
ization established in the Decision on Principles for the
Light Sport Gyroplane Aircraft
Development of International Standards, Guides and Recom-
F2425 SpecificationforContinuedAirworthinessSystemfor
mendations issued by the World Trade Organization Technical
Weight-Shift-Control Aircraft
Barriers to Trade (TBT) Committee.
F2426 Guide onWing Interface Documentation for Powered
Parachute Aircraft
2. Referenced Documents
F2427 Specification for Required Product Information to be
NOTE 1—All terms will reference the source of the definition. Any
Provided with Lighter-Than-Air Light Sport Aircraft
terms not referencing their source will be considered for deletion.
1 2
ThisterminologyisunderthejurisdictionofASTMCommitteeF44onGeneral For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Aviation Aircraft and is the direct responsibility of Subcommittee F44.91 on contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
Terminology. Standards volume information, refer to the standard’s Document Summary page on
Current edition approved Jan. 1, 2020. Published February 2020. Originally the ASTM website.
approved in 2014. Last previous edition approved in 2016 as F3060–16a. DOI: The last approved version of this historical standard is referenced on
10.1520/F3060–20. www.astm.org.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
F3060 − 20
F2449 Specification for Manufacturer Quality Assurance DO-304 Guidance Material and Considerations for Un-
Program for Light Sport Gyroplane Aircraft (Withdrawn manned Aircraft Systems
2014) European Aviation Safety Agency (EASA) “Definitions and
F2457 Specification for Required Product Information to be abbreviations used in Certification Specifications for
Provided withWeight-Shift-Control Aircraft products, parts and appliances; CS-Definitions,”Annex to
F2483 Practice for Maintenance and the Development of ED Decision 2007/016/R, Amendment 2, December 23,
Maintenance Manuals for Light Sport Aircraft 2010
F2490 Guide forAircraft Electrical Load and Power Source GAMA Specification No. 1 Specification for Pilot’s Operat-
Capacity Analysis ing Handbook
F2506 Specification for Design and Testing of Light Sport International Civil Aviation Organization (ICAO) Interna-
Aircraft Propellers tional Standards and Recommended Practices,Annex 8 to
F2507 Specification for Recreational Airpark Design the Convention on International Civil Aviation, “Airwor-
F2512 Practice for QualityAssurance in the Manufacture of thiness of Aircraft: Part 1, Definitions,” eleventh edition,
3 9
Light Unmanned Aircraft System (Withdrawn 2016) July 2010
F2563 Practice for Kit Assembly Instructions of Aircraft J3016 Surface Vehicle Recommended Practice—Taxonomy
Intended Primarily for Recreation and Definitions for Terms Related to Driving Automation
F2564 Specification for Design and Performance of a Light Systems for On-Road Motor Vehicles (2009)
Sport Glider NIST SP 330 The International System of Units
F2584 Practice for Maintenance and Development of Main- TCCA CanadianAviation Regulations (CARs) 2012-1, Sub-
tenance Manuals for Light Unmanned Aircraft System part 1, “Interpretation,” revised December 1, 2011
(UAS) (Withdrawn 2015)
3. Terminology
F2626 Terminology for Light Sport Aircraft (Withdrawn
2018) 3.1 Terms and Definitions:
F2639 Practice for Design, Alteration, and Certification of
100-hour inspection, n—inspection used when the aircraft is
Aircraft Electrical Wiring Systems
carrying any person for hire including flight instruction.
F2745 Specification for Required Product Information to be
(F2483)
Provided with an Airplane
DISCUSSION—Same as an annual condition inspection, except the
F2746 Specification for Pilot’s Operating Handbook (POH)
interval of inspection is 100 hours of operation instead of twelve
for Light Sport Airplane
calendar months. “Annual condition inspection” is a term used for U.S.
F2799 PracticeforMaintenanceofAircraftElectricalWiring
experimental aircraft. The term “annual airworthiness inspection” is
used when considering certified aircraft. While similar, the two
Systems
inspections differ by who is authorized to do the inspections and make
F2930 Guide for Compliance with Light Sport Aircraft
log book entries.
Standards
F2972 Specification for Light SportAircraft Manufacturer’s
abnormal electrical power operation, n—occurs when a
Quality Assurance System
malfunction or failure in the electric system has taken place
F3035 Practice for Production Acceptance in the Manufac-
and the protective devices of the system are operating to
ture of a Fixed Wing Light Sport Aircraft
remove the malfunction or failure from the remainder of the
F3061/F3061M Specification for Systems and Equipment in
system before the limits of abnormal electrical power
Small Aircraft
operation are exceeded. (F2490)
F3062/F3062M Specification forAircraft Powerplant Instal-
accelerate-go distance, n—horizontal distance from the start
lation
of the takeoff to the point where the airplane reaches the
F3082/F3082M Specification for Weights and Centers of
prescribed screen height above the takeoff surface with the
Gravity of Aircraft
critical engine having failed at the designated speed.
F3093/F3093M Specification for Aeroelasticity Require-
(AC 120-62)
ments
F3116/F3116M Specification for Design Loads and Condi-
accelerate-stop distance, n—horizontal distance from takeoff
tions
to the point where the airplane is stopped in the runway or
F3117/F3117M Specification for Crew Interface in Aircraft
F3341 Terminology for Unmanned Aircraft Systems
Available from RTCA, 1150 18th NW, Suite 910, Washington, DC 20036,
https://www.rtca.org.
2.2 Other Standards:
Available from the European Aviation Safety Agency, Konrad-Adenauer-Ufer
ARP 4107 Aerospace Glossary for Human Factors Engi-
3, D-50668 Cologne, Germany, https://www.easa.europa.eu/.
neers
Available from the General Aviation Manufacturers Association (GAMA),
CFR, Title 14 Aeronautics and Space
1400 K St. NW, Suite 801, Washington, DC 20005-2485, https://gama.aero/.
Available from the International Civil Aviation Organization, http://
www.intlaviationstandards.org/Documents/
AircraftMakeModelSeriesBusinessRules1.pdf
4 10
Available from SAE International (SAE), 400 Commonwealth Dr.,Warrendale, Available from National Institute of Standards and Technology (NIST), 100
PA 15096, http://www.sae.org. Bureau Dr., Stop 1070, Gaithersburg, MD 20899-1070, http://www.nist.gov.
5 11
Available from the U.S. Government Publishing Office, 732 N. Capital St. NW, Available from Transport Canada, 330 Sparks St., Ottawa, ON K1A 0N5,
Washington, DC 20401, https://www.gpo.gov. Canada, https://www.tc.gc.ca/.
F3060 − 20
runway and stopway, when the stop is initiated at VI, and aircraft operating instructions, AOI, n—provide methods
completed using the approved procedures and specified and procedures to operate the aircraft safely (F2243, F2427,
conditions. (AC 120-62) F2457, F2564, F2746)
DISCUSSION—For LSA, the AOI specify those parameters (for
acceptable means of compliance, AMC, n—method deter-
example, weight, stall speed, and maximum speed) that show the
mined to be acceptable by a CivilAviationAuthority (CAA)
aircraft make and model meets the LSA definition. The AOI may also
as a means to establish compliance with a regulation. (F44)
be referred to as a POH.
DISCUSSION—The acceptable means is usually defined in CAA
guidance or industry standards or both. There may be multiple means aircraft popular name, n—name used by the aircraft manu-
to determine compliance with any regulation accepted by the CAA.
facturer to market or otherwise distinguish a particular
aircraft model or series or both or the name used by a
aerobatic maneuver, n—intentional maneuver involving an
national military or armed force to distinguish a particular
abrupt change in an aircraft’s attitude, an abnormal attitude,
aircraft model or series or both. (CICTT)
or abnormal acceleration, not necessary for normal flight.
DISCUSSION—An aircraft model or series or both may have more than
(14 CFR Part 91.303)
one popular name. It is normally not the legal identification of the
aircraft and, when found on the type certificate or type certificate data
Aeronautical Radio, Incorporated, ARINC, n—aeronautical
sheet, it is supplementary information. Examples would be the Cessna
standards body made up of Airlines Electronic Engineering
Skyhawk or Sovereign, which are popular names but not the legal
Committee, (AEEC), Avionics Maintenance Conference
identification. Popular names can be changed without affecting the type
(AMC), and Flight Simulation, Engineering, and Mainte-
data of the aircraft.
nance Committee, (FSEMC) and organized by ARINC to
airplane configuration, n—particularcombinationofthefixed
establish cooperatively consensus-based, voluntary aviation
technical standards that no one organization could develop components including wing(s), fuselage, empennage, pro-
pulsion system, and landing gear along with the positions of
independently.
the moveable elements, such as wing flaps, cowl flaps,
Agência Nacional de Aviação Civil, ANAC, n—national civil
landing gear, and equipment, software configuration, and so
aviation authority of Brazil. (ANAC)
forth that affects the aerodynamic or operational character-
istics of the airplane. (F44)
aircraft make, n—name assigned to the aircraft by the aircraft
manufacturer when each aircraft was produced (F2930,
airplane positive gust limit load factor, n , n—airplane
CICTT)
positive gust limit load factor at V . (14 CFR 23, App A,
C
DISCUSSION—In most cases, aircraft make is the name of the aircraft
Par. A23.3)
manufacturer, such as Cub Crafters, Quest, Piper, and so forth.
airship, n—power-driven lighter-than-air aircraft that can be
aircraft manufacturer, n—organization that has been recog-
steered. (F2354, F2355, F2356, F2427)
nized by its certifying authority as having manufactured the
aircraft, at the time of completion. (CICTT)
airworthiness design standards, ADS, n—standards that
identify acceptable means of compliance to the regulatory
aircraft master model, n—grouping of similar aircraft models
for analytical purposes and to identify aircraft models that requirements for aircraft design for certified aircraft or the
consensus standards such as ASTM F37, F38, or F39 for
share airworthiness properties; the master model is the first
model in a series of that aircraft make. (CICTT) non-certified aircraft.
aircraft mechanic, n—person who performs maintenance on
airworthiness directive, AD, n—regulation issued by the
aircraft, engines, propellers, appliances, and other aircraft
CAA that applies to aircraft, aircraft engines, propellers, or
components within the scope of their authorization by the
appliances when an unsafe condition exists and that condi-
applicable authority or regulation. tionislikelytoexistordevelopinotherproductsofthesame
DISCUSSION—An aircraft mechanic may go by different titles under
design. (F2639)
different authorities. The common name for an aircraft mechanic in
DISCUSSION—Airworthiness Directives (ADs) are legally enforceable
some countries is Licensed Aircraft Maintenance Engineer and in
regulations issued by the CAA to correct an unsafe condition in a
others it may be Airframe and Powerplant (A&P) mechanic. For some
product. Each CAA will have its own guidance on ADs. For FAA-
authorizations a mechanic’s license or certificate issued by an authority
issued Ads, this follows the guidance in 14 CFR 39.
is required while for LSA aircraft authorization by the manufacturer
may be required.
airworthiness limitation, n—limitation applicable to an air-
craft or article installed on an aircraft in the form of a life
aircraft model, n—aircraft manufacturer’s designation for an
limit or a maintenance task that is mandatory to maintain the
aircraft. (F2930, CICTT)
aircraft in airworthy condition. (F44)
DISCUSSION—The aircraft model is: (1) listed in the aircraft type
certificate, (2) the designation used by the aircraft manufacturer to
alteration, n—modification of a product to establish a new
legally distinguish a particular aircraft, or (3) the designation used by a
airworthy configuration. (F44)
national military or armed force to distinguish a particular aircraft. It is
usually a model number that may be part of a series of similar models.
American Institute of Aeronautics and Astronautics, AIAA,
If an aircraft manufacturer is amateur construction, in most cases, the
n—world’s largest technical society dedicated to the global
aircraft model would be the name designated by the organization
responsible for design. aerospace profession. (F44)
F3060 − 20
DISCUSSION—Calibrated airspeed is equal to true airspeed in standard
American Society ASTM International, ASTM, n—globally
atmosphere at sea level.
recognized leader in the development and delivery of inter-
national voluntary consensus standards. (F44)
center of gravity, CG, n—point at which the entire weight of
a body may be considered as concentrated so that if
annual condition inspection, n—detailed inspection accom-
supportedatthispointthebodywouldremaininequilibrium
plished once a year on an aircraft in accordance with the
in any position. (TCCA, F2245, F2352, F2564)
applicable instructions for continued airworthiness.
(F2483, F44)
certificate of airworthiness, CofA, n—a CAA document
DISCUSSION—The purpose of the inspection is to look for any wear,
which grants authorization to operate an aircraft in flight.
corrosion, or damage that would cause an aircraft to not be in a
(F44)
condition for safe operation.
chord, c, n—straight line distance joining the leading and
appliance, n—any instrument, mechanism, equipment, part,
trailing edges of an airfoil. (F2245)
apparatus, appurtenance, or accessory, including communi-
cations equipment, that is used or intended to be used in
civil aviation authority, CAA, n—governmental agency re-
operating or controlling an aircraft in flight; is installed in or
sponsible for regulation of civil-aviation-related activities in
permanently attached to the aircraft; and is not part of an
a country or jurisdiction, such as Agência Nacional de
airframe, engine, or propeller. (F2639, 14 CFR Part 1)
Aviação Civil (ANAC) of Brazil, or Transport Canada Civil
arc fault circuit breaker, n—circuit breaker specifically de- Aviation (TCCA). (F2425, F2563, F2507)
signed to open when arcing faults are detected. (F2639) DISCUSSION—In some countries, only certain parts of the aviation
activities are the responsibility of the CAA. For the purposes of this
aspect ratio, AR, n—wing span (b) squared divided by the
terminology, the activities are those related to aircraft, engine, and
wing area (S), b /S. (F2245, F2564) propeller certification and continued operational safety.
auxiliary power unit, APU, n—any power unit delivering
commercial part, n—part that is listed on an approved
rotating shaft power, compressed air, or both, that is not commercial parts list included in a design approval holder’s
intended for direct propulsion of an aircraft. (F44) instructions for continued airworthiness and for which:
(1) The failure of the commercial part, as installed in the
average design surface load, w, n—load divided by area.
product, would not degrade the level of safety of the product;
(F2564)
and
(2) The part is produced only under the commercial part
balanced field length, BFL, n—for airplanes with more than
manufacturer’s specification and marked only with the com-
one engine, it is the minimum allowable runway length for a
mercial part manufacturer’s markings. (14 CFR 21.1(b)(3),
given airplane weight, configuration and atmospheric con-
21.50(c)(2))
ditions as per field limitations. (FAA AC 120-62)
DISCUSSION—It corresponds to the point where the accelerate-go
compliance package, n—set of documents that provides
performance required is equal to (“balances”) the accelerate-stop
objective, verifiable evidence for compliance to CAA regu-
performance required.
lations using CAA accepted means of compliance which
balloon, n—lighter-than-air aircraft that is not engine-driven
may be industry consensus standards or applicant developed
and sustains flight through the use of either gas buoyancy or
means of compliance. (F44)
an airborne heater or both. (F2354, F2355, F2356, F2427)
compliance program, n—set of activities planned for,
best angle of climb, n—climb angle which produces the most
executed, and for which results are reviewed against CAA
altitude gain with least distance traveled horizontally (F44)
accepted industry consensus standards or applicant devel-
oped means of compliance for the purpose of declaring
best angle of climb speed, V , n—the speed at which the
x
compliance to a particular standard. (F2930, F44)
aircraft will obtain the highest altitude in a given horizontal
distance. (F2317/F2317M)
consensus standard, n—for the purpose of certificating
DISCUSSION—This best angle-of-climb speed normally increases
aircraft, an industry developed standard that applies to
slightly with altitude.
aircraft design, production, and airworthiness.
best rate of climb, n—climb rate that produces the most (14 CFR Part 1.1)
altitude gain in the least amount of time. (F44)
DISCUSSION—It includes, but is not limited to, standards for aircraft
design and performance, required equipment, manufacturer quality
best rate of climb speed, V , n—speed at which the aircraft
y assurance systems, production acceptance test procedures, operating
will obtain the maximum increase in altitude per unit of
instructions, maintenance and inspection procedures, identification and
recording of major repairs and major alterations, and continued
time. (F2317/F2317M)
airworthiness.
DISCUSSION—This best rate-of-climb speed normally decreases
slightly with altitude.
continuing airworthiness, n—set of processes by which an
calibrated airspeed, CAS, n—indicated airspeed of an aircraft aircraft, engine, propeller, or part complies with the appli-
corrected for position and instrument error. (FAA Part 1, cable airworthiness requirements and remains in a condition
EASA CS1) for safe operation throughout its operating life. (ICAO)
F3060 − 20
conventional fixed pitch propeller, n—one-piece fixed pitch drag coefficient,C , n—nondimensional number whose value
D
propeller that is constructed of material such as wood or represents a relative magnitude of the resistance force of a
metalthathasnoabruptchangesinmaterialpropertiesasthe bodyagainstamovingfluidenvironment,forexample,tothe
blades transition through the hub area. (F2506) freestreamairflowinthecaseofanaircraft. (F2245, F2564,
F44)
creepage, n—conduction of electrical current along a surface
between two points at different potentials. (F2639) dynamic pressure,Qorq, n—pressure that would be exerted
byamovingairflowagainstabodyifitwerebroughttorest.
critical engine failure takeoff speed,V , n—speed at which
EF
(F2245, F2564, F44)
the critical engine is assumed to fail during takeoff.
electrical wiring interconnection system, EWIS, n—any
cruise, n—condition during which the aircraft is in level flight
wire, wiring device, or combination of these, including
or making altitude changes between the take-off and climb
termination devices, installed in any area of the aircraft for
phase and the descent to landing phase. (F2490)
the purpose of transmitting electrical energy between two or
more intended termination points. (F2799)
demonstrated flight dive speed, V /M , n—maximum
DF DF
speed at which it has been demonstrated there is an absence
electronic engine control system, EECS, n—engine control
of excessive buffet, vibration, or controllability problems
system in which the primary functions are provided using
(V ≤ V ). (14 CFR Part 1, F2317/F2317M, F2245,
DF D
electronics. (EASA CS1)
F2564)
DISCUSSION—It includes all the components (for example, digital,
electrical, electronic, hydro-mechanical, and pneumatic) necessary for
design and performance specification, n—used herein to
the control of the engine and may incorporate other control functions
refer to Specifications F2245 and F2564. (F3035)
where desired.
design cruising speed,V , n—maximum speed for which the
C
emergency electrical power operation, n—condition that
aircraft has been designed for cruise flight. (14 CFR Part 1,
occurs following a loss of all normal electrical generating
F2245, F2564)
power sources or another malfunction that results in opera-
tion on an alternate electrical power source only or both.
design dive speed,V /M , n—maximum speed for which the
D D
(F2490)
structure has been designed. (FAA Part 1, F2245, F2564)
empty weight, n—theemptyweightoftheaircraftincludesthe
design flap speed, V , n—maximum speed at which the
F
combined weight of the airframe, propulsion system, re-
aircraft can be flown at the selected flap deflection. (F2245,
quired equipment, installed optional or special equipment,
F2564)
fixed ballast, unusable fuel, and full operating fluids, includ-
design maneuvering speed, V , n—speed below which you
A
ing oil, hydraulic fluid, and other fluids required for normal
can move a single flight control, one time, to its full
operation of aircraft systems, except potable water, lavatory
deflection, for one axis of airplane rotation only (pitch, roll
precharge water, and water intended for injection in the
or yaw), in smooth air, without risk of damage to the
engines. (F3082/F3082M, F3116/F3116M, F3117/F3117M)
airplane. (F2245, F2564, F2317/F2317M, F44)
equivalent airspeed, EAS, n—calibrated airspeed of an air-
design maximum aircraft weight, W , n—aircraft design
MAX
craft corrected for adiabatic compressible flow for the
maximum weight for LSA aircraft shall be the maximum
particular altitude. (14 CFR Part 1, EASA CS1)
weight for which the aircraft is designed. (F2317/F2317M)
DISCUSSION—Equivalent airspeed is equal to calibrated airspeed in
DISCUSSION—This is acceptable for LSA aircraft but is inadequate
standard atmosphere at sea level.
definitionformanyoftoday’sPart23aircraftthathaveamaximumtaxi
European Aviation Safety Agency, EASA, n—agency of the
weight, maximum takeoff weight, maximum landing weight, and
maximum zero fuel weight that are all different. European Union that serves as the CAA for contracting
states. (EASA)
design maximum trike carriage weight, W , n—highest
susp
trike carriage weight at which compliance with each appli-
European Organization for Civil Aviation Equipment,
cable structural loading condition and each applicable flight
EUROCAE, n—(1) nonprofit organization that was formed
requirement is shown. (F2317/F2317M)
at Lucerne, Switzerland in 1963 to provide a European
forum for resolving technical problems with electronic
design speed for maximum gust intensity, V , n—the speed
B
equipment for air transport; (2) deals exclusively with
at which particular gust intensities apply in the determina-
aviation standardization (airborne and ground systems and
tion of structural loads. (F44)
equipment) and related documents as required to use in the
design stall speed, V , n—stalling speed or the minimum regulation of aviation equipment and systems; and (3)
S
steady flight speed at which the airplane is controllable. association composed of members who are all specialized in
(F2245, F2564, F44) one or several technical fields of aeronautics and many of
them are considered to be among world’s leaders in their
design useful load, n—load (other than structure, engine,
domain. (F44)
enclosure, and systems) that an aircraft can carry while
achieving the design defining performance requirements. exhaust gas temperature, EGT, n—temperature of the ex-
(F2355, F44) haust gas exiting an engine. (F44)
F3060 − 20
factor of safety, FOS, n—design factor (multiplier) used to information, and/or instructions about a particular aircraft
provide for the possibility of loads greater than those and the operation of that aircraft. (F44)
assumed and uncertainties in design and fabrication. DISCUSSION—For airplanes, this is identified as an airplane flight
manual (AFM).
(ICAO, F2352)
DISCUSSION—Refer to ultimate load definition for relationship be-
flight manual supplement, FMS, n—document that provides
tween factor of safety and ultimate load.
supplemental information, usually for equipment such as
options or STCs that are not part of the basic aircraft and
final takeoff speed,V , n—speed of the airplane that exists
FTO
included in the main flight manual. (F44)
at the end of the takeoff path in the en-route configuration
with one engine inoperative. (14 CFR Part 1, EASA CS1)
flight training supplement, FTS, n—document providing
guidance for training for LSA aircraft. (F2457, F2745)
fireproof, adj—(1) With respect to materials and parts used to
confine fire in a designated fire zone, means the capacity to
full authority digital engine control, FADEC, n—system
withstand at least as well as steel in dimensions appropriate
consisting of digital computer, called an electronic engine
for the purpose for which they are used, the heat produced
controller (EEC) or engine control unit (ECU), and its
when there is a severe fire of extended duration in that zone;
related accessories that control all aspects of aircraft engine
and (2) with respect to other materials and parts, means the
performance. (F44)
capacity to withstand the heat associated with fire at least as
well as steel in dimensions appropriate for the purpose for
General Aviation Manufacturers Association, GAMA,
which they are used. (F2352, 14 CFR Part 1)
n—internationaltradeassociationrepresentingover80ofthe
DISCUSSION—For materials, this is considered to be equivalent to the world’s leading manufacturers of general aviation airplanes
capability of withstanding a fire at least as well as steel or titanium in
and rotorcraft, engines, avionics, components and related
dimensions appropriate for the purposes for which they are used.
services. (F44)
DISCUSSION—GAMA’s members also operate repair stations, fixed-
fire resistant, adj—(1) With respect to sheet or structural
based operations, pilot and maintenance training facilities, and they
members, means the capacity to withstand the heat associ-
manage fleets of aircraft.
ated with fire at least as well as aluminum alloy in dimen-
sions appropriate for the purpose for which they are used; ground adjustable propeller, n—propellerwhosepitchsetting
and (2) with respect to fluid-carrying lines, fluid system is adjustable only when the aircraft is on the ground and the
parts, wiring, air ducts, fittings, and powerplant controls, propeller is not rotating. (F2506)
means the capacity to perform the intended functions under
heavy maintenance, n—any maintenance, inspection, repair,
the heat and other conditions likely to occur when there is a
or alteration a manufacturer has designated that requires
fire at the place concerned. (14 CFR Part 1)
specialized training, equipment, or facilities. (F2483,
DISCUSSION—For materials, this may be considered to be equivalent
F2584)
to the capability of withstanding a fire at least as well as aluminum
alloy in dimensions appropriate for the purposes for which they are
high-intensity radiated field, HIRF, n—radio frequency en-
used.
ergy of a strength sufficient to adversely affect either a living
fixed pitch propeller, n—propeller, the pitch of which cannot organism or the performance of a device subjected to it.
(F44)
be changed, except by processes constituting a workshop
operation. (EASA CS1, F2506, F44)
illustrated parts breakdown, IPB, n—technical publications
identifying the parts making up assemblies and products and
flame resistant, adj—not susceptible to combustion to the
relation to each other through the use of illustrations. Also
point of propagating a flame, beyond safe limits, after the
referred to as an illustrated parts catalog (IPC). (F44)
ignition source is removed. (14 CFR, Part 1, EASA CS1)
instrument flight rules, IFR, n—rules and regulations gov-
flaps, n—trailing or leading edge devices to increase lift and
erning flight by relying on instrument readings instead of
drag. (F2245, F2564, F44)
visual reference to the ground. (14 CFR Part 1)
DISCUSSION—Althoughmostflapsareonthetrailingedge,someflaps
such as Krueger flaps are on the leading edge.
indicated airspeed, IAS, n—speed of an aircraft as shown on
flight data recorder, FDR, n—device used to record specific itspitotstaticairspeedindicatorcalibratedtoreflectstandard
atmosphere adiabatic compressible flow at sea level uncor-
aircraft parameters. (F44)
rected for airspeed system errors. (14 CFR Part 1)
flight management system, FMS, n—specialized computer
Institute of Electrical and Electronics Engineers, IEEE,
system that automates a wide variety of in-flight tasks,
n—leading authority on areas ranging from aerospace
reducing the workload on the flight crew. (F44)
systems, computers, and telecommunications to biomedical
DISCUSSION—Aprimaryfunctionisin-flightmanagementoftheflight
plan. engineering,electricpower,andconsumerelectronics. (F44)
flight manual, FM, n—manual describing the operation of the instructions for continued airworthiness, ICA, n—provide
aircraft and includes any limitations; normal, abnormal, and documentation of recommended methods, inspections,
emergency procedures; and provides specific facts, processes, and procedures to keep products airworthy. The
F3060 − 20
ICA must contain information on each item or part, as perform the annual condition inspection on experimental
appropriate, installed on the product. (F2799) light-sport aircraft or an equivalent rating issued by other
civil aviation authorities. (F2483)
instrument meteorological conditions, IMC, n—weather
DISCUSSION—Experimental LSA do not require the individual per-
conditions below the minimum for flight under visual flight
forming maintenance to hold any FAAairman certificate in the United
rules, also referred to as IFR conditions. (14 CFR Part 1,
States.
EASA CS1, CS2)
LSA repairman maintenance, LSRM, n—U.S. FAA-
International Civil Aviation Organization, ICAO,
certificated repairman (light-sport aircraft) with a mainte-
n—agency of the that codifies the principles and techniques
nance rating as defined by 14 CFR Part 65 authorized to
of international air navigation and fosters the planning and
perform line maintenance on aircraft certificated as special
development of international air transport to ensure safe and
LSAaircraft and authorized to perform the annual condition/
orderly growth. (F44)
100-hinspectiononanLSAoranequivalentratingissuedby
other civil aviation authorities. (F37, F2483)
International Electrotechnical Commission, IEC,
n—international standards and conformity assessment body
maintenance manual(s), MM(s), n—manual provided by a
for all fields of electrotechnology. (F44)
manufacturer or supplier that specifies all maintenance,
repairs, scheduled checks, and alterations authorized by the
Joint Electron Device Engineering Council, JEDEC,
manufacturer to maintain the aircraft in an airworthy
n—independent semiconductor engineering trade organiza-
condition. (F2483, F2930)
tion and standardization body associated with the Electronic
IndustriesAlliance (EIA), a trade association that represents
major alteration, n—alteration not listed in the aircraft,
all areas of the electronics industry in the United States.
aircraft engine, or propeller specifications: (1) that might
(F44)
appreciably affect weight, balance, structural strength,
performance, powerplant operation, flight characteristics, or
kit assembly instructions, KAI, n—instructions for assem-
other qualities affecting airworthiness or (2) that is not done
bling an LSA aircraft kit. (F2563, F2745)
according to accepted practices or cannot be done by
elementary operations. (F2483, 14 CFR Part 43)
life-limited part, n—part that, as a condition of the type
certificate, may not exceed a specified time, or number of DISCUSSION—For LSA, a major alteration is any alteration for which
instructions to complete the task are excluded from the maintenance
operating cycles, in service. (TCCA)
manual(s) supplied to the consumer. For certified aircraft refer to the
light-sport aircraft, LSA, n—an aircraft designed and built to applicable CAA guidance for additional definition and examples.
comply with light sport aircraft consensus standards.
major repair, n—repair: (1) that, if improperly done, might
DISCUSSION—National airworthiness authorities may have additional
appreciably affect weight, balance, structural strength,
certification requirements that supplement the ASTM consensus stan-
performance, powerplant operation, flight characteristics, or
dards for LSA’s certified by them.
other qualities affecting airworthiness or (2) that is not done
light-sport aircraft kit, LSA kit, n—aircraft designed in
according to applicable CAAguidance or cannot be done by
accordance with Specifications F2245 or F2564 that is
elementary operations. (F2483, 14 CFR Part 43)
manufactured and delivered as a kit. (F3035)
DISCUSSION—For LSA, a major repair is any repair for which
instructions to complete the task are excluded from the maintenance
lighter-than-air aircraft, n—aircraft that can rise and remain
manual(s) supplied to the consumer. For certified aircraft it is taken to
suspended by using contained gas weighting less than the air
mean changes to the empty weight or empty balance which increase in
that is displaced by the gas. (F2354, F2355, F2356, F2427)
the maximum certificated weight or center of gravity limits of the
DISCUSSION—Airships may include dynamic lift that derives as much
aircraft. See applicable CAA guidance for more specific examples of
as 30 % lift from other than buoyancy.
major repair.
limit load, n—maximum loads assumed to occur in the
manufacturer, n—any entity engaged in the production of an
anticipated operating conditions. (ICAO, F2352) aircraft or component used on an aircraft. (F44, F2295,
DISCUSSION—Refer to ultimate load for relationship of limit load to
F2415, F2483)
ultimate load.
DISCUSSION—For LSA, the manufacturer is also responsible for
completing all compliance related paperwork and assertions of com-
line maintenance, n—any repair, maintenance, scheduled
pliance.
checks, servicing, inspections, or alterations not considered
heavy maintenance that is specified in the manufacturer’s master compliance checklist, MCCL, n—listing of all the
maintenance manual. (F2483) regulations applicable to a specific product.
line replaceable unit, LRU, n—modular component of an material bond, n—adhesion of one surface to another with or
aircraft designed to be replaced quickly at an operating without the use of an adhesive as a bonding agent for the
location. (F2799, F44) purpose of making the parts act as one part. (F2639)
light-sport repairman inspection, LSRI, n—U.S. FAA- maximum continuous power or thrust or both, n—power or
certificated repairman (light-sport aircraft) with an inspec- thrust or both identified in the performance data for use
tion rating as defined by 14 CFR Part 65 authorized to during periods of unrestricted duration. (EASA CS1)
F3060 − 20
maximum continuous power or thrust or both rating, maximum permissible propeller speed, n—maximumpropel-
n—minimum test bed acceptance power or thrust or both, as ler rotational speed permitted in normal or likely emergency
stated in the engine-type certificate data sheet, of series and operation for fixed, adjustable, or variable (non-governing)
newly overhauled engines when running at the specified propellers. (EASA CS1)
conditionsandwithintheappropriateacceptancelimitations.
maximum propeller overspeed, n—maximum propeller rota-
(EASA CS1)
tional speed, the inadvertent occurrence and duration of
maximum empty weight,W , n—largest empty weight of the
which has been established not to require rejection of the
E
aircraft, including all operational equipment that is installed propeller from service or maintenance action. (EASA CS1)
in the aircraft: weight of the airframe, powerplant, required
maximum ramp weight, n—the maximum allowable weight
equipment, installed optional and specific equipment, fixed
of the aircraft while stationary or in motion on the ground
ballast, full engine coolant and oil, hydraulic fluid, and the
under its own power prior to beginning the takeoff roll.
unusable fuel. (F2564, F2245)
(F3082/F3082M, F3116/F3116M, F3117/F3117M)
DISCUSSION—Hence, the maximum empty weight equals maximum
DISCUSSION—For normal operations this may be: (a) equal to the
takeoff weight minus minimum useful load: W = W – W .
E U
MaximumTakeoffWeight,or(b)theMaximumTakeoffWeightplusan
maximum engine overspeed, n—maximum rotational speed
estimated fuel use from engine start up to takeoff. It is also frequently
referred to as Taxi Weight.
of a mechanically independent main rotating system of an
engine, inadvertent occurrence of which for periods agreed
maximum spoiler/speed brake extended speed, V ,
SP
to between CAA and engine manufacturer, has been agreed
n—maximum speed at which aircraft can be flown with
not to require rejection of the engine from service or
spoilers or speed brakes extended. (F2245)
maintenance action (other than to correct the cause).
(EASA CS1)
maximum stability characteristics speed, V /M ,
FC FC
n—maximum speed/Mach number for stability
maximum engine overtorque, n—for turbo-propeller and
characteristics. (14 CFR Part 1)
turbo-shaft engines incorporating free power turbines only:
the maximum torque of the free power turbine, the inadver-
maximum sustainable straight and level airspeed, V ,
H
tent occurrence and duration of which has been established
n—maximum speed in level flight with maximum continu-
not to require rejection of the engine from service or
ous power. (14 CFR Part 1)
maintenance action. (EASA CS1)
maximum takeoff weight, MTOW, n—the maximum allow-
maximum exhaust gas over temperature, n—for turbine
able weight when starting the takeoff roll. (F2244, F2245,
engines, the maximum engine exhaust gas temperature, the
F2355, F2564, F3082/F3082M, F3116/F3116M,
inadvertent occurrence, and duration has been established
F3117/F3117M)
not to require rejection of the engine from service or
DISCUSSION—This is the weight used to determine maximum flight
maintenance action. (EASA CS1)
loads and flight requirements and it may also be the weight used to
DISCUSSION—This is not to be confused with maximum temperatures
determine the maximum ground loads when it is the same as the Ramp
established for use during starting operations.
Weight, LandingWeight, orTowingWeight.This is sometimes referred
toasMaximumCertifiedTakeoffWeight(MCTOW)whenappliedonly
maximum flap extended speed, V , n—highest speed per-
FE
to the approved weight and not the design weight. It may also be
missible with wing flaps in a prescribed extended position.
referred to as the gross weight by some.
(14 CFR Part 1)
maximum towing weight, n—the maximum allowable weight
maximum governed propeller speed, n—maximumrotational
of the aircraft when being towed on the ground.
speed for variable pitch governing propellers as determined
(F3116/F3116M, F3082/F3082M, F3093/F3093M)
by the setting of the propeller governor or control
maximum zero wing fuel weight, n—the maximum weight of
mechanism. (EASA CS1)
the aircraft without any usable fuel in the wing fuel tanks.
maximum landing gear extended speed, V , n—maximum
LE
(F3082/F3082M, F3116/F3116M, F3117/F3117M)
speed at which an aircraft can be safely flown with the
DISCUSSION—Any weight added above this weight must be in the
landing gear extended. (14 CFR Part 1)
form of fuel added to the wing tank(s) to provide relieving inertia loads
forthewingstructure.Thistermisalsofrequentlyreferredtoasjustthe
maximum landing gear operating speed,V , n—maximum
LO
“maximumzerofuelweight”withtheunderstandingthatitappliesonly
speed at which the landing gear can be safely extended or
to fuel in the wing tanks.
retracted. (14 CFR 1.2, EASA CS1)
mean aerodynamic chord, MAC, n—wing area divided by
maximum landing weight, n—the maximum allowable
the span.
weight of the aircraft when it touches down for landing.
(F3116/F3116M, F3082/F3082M, F3093/F3093M, F3117/ mean time between failure, MTBF, n—average time between
failure of a part.
F3117M)
maximum operating speed, V , n—given as a limitation in minimum controllable level flight airspeed, V ,
O MIN
the AFM and it cannot exceed V √n. (14 CFR 23.1507) n—minimumcontrollablelevelflightairspeed,IAS. (F2352)
S
F3060 − 20
minimum useful load,W , n—minimum flying weight (W)– tional information not required by regulation. (F2245,
U
empty weight (W ). (F2245, F2564) F2512, F2745, F2746, F2972, F2352, F3035)
E
DISCUSSION—Refer to GAMA Specification 1—Pilot’s Operating
minor alteration, n—any alteration other than a major
Handbook for guidance on POH content.
alteration, or which are identified
...

This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Because
it may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
of the standard as published by ASTM is to be considered the official document.
Designation: F3060 − 16a F3060 − 20
Standard Terminology for
Aircraft
This standard is issued under the fixed designation F3060; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope
1.1 This terminology contains a listing of terms, abbreviations, acronyms, and symbols related to aircraft covered by ASTM
Committees F37 and F44 airworthiness design standards. It is intended to ensure the consistent use of terminology throughout all
ASTM light aircraft standards.
1.2 Units—The definitions of units will be as defined in NIST SP 330 and will not be duplicated in this document. NIST SP
330 is available on the internet. The values stated in either SI units or inch-pound units are to be regarded separately as standard.
The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other.
Combining values from the two systems may result in nonconformance with the standard.
1.3 Source References—The listed document(s) was/were the original source for the definition. However, the definition may
have been edited for use in this document and the F37 and F44 standards, and may not completely match the original in every
respect.
1.4 A definition adapted from a particular standard within the ASTM aircraft collection of standards is not limited to use within
only those standards.
1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility
of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of
regulatory limitations prior to use.
1.6 This international standard was developed in accordance with internationally recognized principles on standardization
established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued
by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
2. Referenced Documents
NOTE 1—All terms will reference the source of the definition. Any terms not referencing their source will be considered for deletion.
2.1 ASTM Standards:
F2241 Specification for Continued Airworthiness System for Powered Parachute Aircraft
F2242 Specification for Production Acceptance Testing System for Powered Parachute Aircraft
F2243 Specification for Required Product Information to be Provided with Powered Parachute Aircraft
F2244 Specification for Design and Performance Requirements for Powered Parachute Aircraft
F2245 Specification for Design and Performance of a Light Sport Airplane
F2249 Specification for In-Service Test Methods for Temporary Grounding Jumper Assemblies Used on De-Energized Electric
Power Lines and Equipment
F2279 Practice for Quality Assurance in the Manufacture of Fixed Wing Light Sport Aircraft (Withdrawn 2014)
F2295 Practice for Continued Operational Safety Monitoring of a Light Sport Aircraft (Withdrawn 2019)
F2317/F2317M Specification for Design of Weight-Shift-Control Aircraft
F2352 Specification for Design and Performance of Light Sport Gyroplane Aircraft
F2354 Specification for Continued Airworthiness System for Lighter-Than-Air Light Sport Aircraft
F2355 Specification for Design and Performance Requirements for Lighter-Than-Air Light Sport Aircraft
F2356 Specification for Production Acceptance Testing System for Lighter-Than-Air Light Sport Aircraft
This terminology is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.91 on Terminology.
Current edition approved Nov. 1, 2016Jan. 1, 2020. Published November 2016February 2020. Originally approved in 2014. Last previous edition approved in 2016 as
F3060 – 16.F3060–16a. DOI: 10.1520/F3060-16A.10.1520/F3060–20.
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM Standards
volume information, refer to the standard’sstandard’s Document Summary page on the ASTM website.
The last approved version of this historical standard is referenced on www.astm.org.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
F3060 − 20
F2411 Specification for Design and Performance of an Airborne Sense-and-Avoid System (Withdrawn 2014)
F2415 Practice for Continued Airworthiness System for Light Sport Gyroplane Aircraft
F2425 Specification for Continued Airworthiness System for Weight-Shift-Control Aircraft
F2426 Guide on Wing Interface Documentation for Powered Parachute Aircraft
F2427 Specification for Required Product Information to be Provided with Lighter-Than-Air Light Sport Aircraft
F2449 Specification for Manufacturer Quality Assurance Program for Light Sport Gyroplane Aircraft (Withdrawn 2014)
F2457 Specification for Required Product Information to be Provided withWeight-Shift-Control Aircraft
F2483 Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
F2490 Guide for Aircraft Electrical Load and Power Source Capacity Analysis
F2506 Specification for Design and Testing of Light Sport Aircraft Propellers
F2507 Specification for Recreational Airpark Design
F2512 Practice for Quality Assurance in the Manufacture of Light Unmanned Aircraft System (Withdrawn 2016)
F2563 Practice for Kit Assembly Instructions of Aircraft Intended Primarily for Recreation
F2564 Specification for Design and Performance of a Light Sport Glider
F2584 Practice for Maintenance and Development of Maintenance Manuals for Light Unmanned Aircraft System (UAS)
(Withdrawn 2015)
F2626 Terminology for Light Sport Aircraft (Withdrawn 2018)
F2639 Practice for Design, Alteration, and Certification of Aircraft Electrical Wiring Systems
F2745 Specification for Required Product Information to be Provided with an Airplane
F2746 Specification for Pilot’s Operating Handbook (POH) for Light Sport Airplane
F2799 Practice for Maintenance of Aircraft Electrical Wiring Systems
F2930 Guide for Compliance with Light Sport Aircraft Standards
F2972 Specification for Light Sport Aircraft Manufacturer’s Quality Assurance System
F3035 Practice for Production Acceptance in the Manufacture of a Fixed Wing Light Sport Aircraft
F3061F3061/F3061M Specification for Systems and Equipment in Small Aircraft
F3062F3062/F3062M Specification for Aircraft Powerplant Installation
F3082F3082/F3082M Specification for Weights and Centers of Gravity of Aircraft
F3093F3093/F3093M Specification for Aeroelasticity Requirements
F3116F3116/F3116M Specification for Design Loads and Conditions
F3117F3117/F3117M Specification for Crew Interface in Aircraft
F3341 Terminology for Unmanned Aircraft Systems
2.2 Other Standards:
ARP 4107 Aerospace Glossary for Human Factors Engineers
CFR, Title 14 Aeronautics and Space
DO-304 Guidance Material and Considerations for Unmanned Aircraft Systems
European Aviation Safety Agency (EASA) “Definitions and abbreviations used in Certification Specifications for products, parts
and appliances; CS-Definitions,” Annex to ED Decision 2007/016/R, Amendment 2, December 23, 2010
GAMA Specification No. 1 Specification for Pilot’s Operating Handbook
International Civil Aviation Organization (ICAO) International Standards and Recommended Practices, Annex 8 to the
Convention on International Civil Aviation, “Airworthiness of Aircraft: Part 1, Definitions,” eleventh edition, July 2010
J3016 Surface Vehicle Recommended Practice—Taxonomy and Definitions for Terms Related to Driving Automation Systems
for On-Road Motor Vehicles (2009)
NIST SP 330 The International System of Units
TCCA Canadian Aviation Regulations (CARs) 2012-1, Subpart 1, “Interpretation,” revised December 1, 2011
3. Terminology
3.1 Terms and Definitions:
100-hour inspection, n—inspection used when the aircraft is carrying any person for hire including flight instruction. (F2483)
Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale, PA 15096, http://www.sae.org.
Available from the U.S. Government Printing Office, Superintendent of Documents, Publishing Office, 732 N. Capital St. NW, Washington, DC 20402-0001.20401,
https://www.gpo.gov.
Available from RTCA, 1150 18th NW, Suite 910, Washington, DC 20036, https://www.rtca.org.
Available from the European Aviation Safety Agency, Ottoplatz, 1, D-50679 Cologne, Germany.Konrad-Adenauer-Ufer 3, D-50668 Cologne, Germany, https://
www.easa.europa.eu/.
Available from the General Aviation Manufacturers Association, Association (GAMA), 1400 K St. NW, Suite 801, Washington, DC 20005-2485.20005-2485,
https://gama.aero/.
Available from the International Civil Aviation Organization, http://www.intlaviationstandards.org/Documents/AircraftMakeModelSeriesBusinessRules1.pdf
Available from National Institute of Standards and Technology (NIST), 100 Bureau Dr., Stop 1070, Gaithersburg, MD 20899-1070, http://www.nist.gov.
Available from Transport Canada, 330 Sparks St., Ottawa, ON Canada K1A 0N5.K1A 0N5, Canada, https://www.tc.gc.ca/.
F3060 − 20
DISCUSSION—
Same as an annual condition inspection, except the interval of inspection is 100 hours of operation instead of twelve calendar months. “Annual
condition inspection” is a term used for U.S. experimental aircraft. The term “annual airworthiness inspection” is used when considering certified
aircraft. While similar, the two inspections differ by who is authorized to do the inspections and make log book entries.
abnormal electrical power operation, n—occurs when a malfunction or failure in the electric system has taken place and the
protective devices of the system are operating to remove the malfunction or failure from the remainder of the system before the
limits of abnormal electrical power operation are exceeded. (F2490)
accelerate-go distance, n—horizontal distance from the start of the takeoff to the point where the airplane reaches the prescribed
screen height above the takeoff surface with the critical engine having failed at the designated speed.
(AC 120-62)
accelerate-stop distance, n—horizontal distance from takeoff to the point where the airplane is stopped in the runway or runway
and stopway, when the stop is initiated at VI, and completed using the approved procedures and specified conditions. (AC
120-62)
acceptable means of compliance, AMC, n—method determined to be acceptable by a Civil Aviation Authority (CAA) as a means
to establish compliance with a regulation. (F44)
DISCUSSION—
The acceptable means is usually defined in CAA guidance or industry standards or both. There may be multiple means to determine compliance with
any regulation accepted by the CAA.
aerobatic maneuver, n—intentional maneuver involving an abrupt change in an aircraft’s attitude, an abnormal attitude, or
abnormal acceleration, not necessary for normal flight. (14 CFR Part 91.303)
Aeronautical Radio, Incorporated, ARINC, n—aeronautical standards body made up of Airlines Electronic Engineering
Committee, (AEEC), Avionics Maintenance Conference (AMC), and Flight Simulation, Engineering, and Maintenance
Committee, (FSEMC) and organized by ARINC to establish cooperatively consensus-based, voluntary aviation technical
standards that no one organization could develop independently.
Agência Nacional de Aviação Civil, ANAC, n—national civil aviation authority of Brazil. (ANAC)
aircraft make, n—name assigned to the aircraft by the aircraft manufacturer when each aircraft was produced (F2930, CICTT)
DISCUSSION—
In most cases, aircraft make is the name of the aircraft manufacturer, such as Cub Crafters, Quest, Piper, and so forth.
aircraft manufacturer, n—organization that has been recognized by its certifying authority as having manufactured the aircraft,
at the time of completion. (CICTT)
aircraft master model, n—grouping of similar aircraft models for analytical purposes and to identify aircraft models that share
airworthiness properties; the master model is the first model in a series of that aircraft make. (CICTT)
aircraft mechanic, n—person who performs maintenance on aircraft, engines, propellers, appliances, and other aircraft
components within the scope of their authorization by the applicable authority or regulation.
DISCUSSION—
An aircraft mechanic may go by different titles under different authorities. The common name for an aircraft mechanic in some countries is Licensed
Aircraft Maintenance Engineer and in others it may be Airframe and Powerplant (A&P) mechanic. For some authorizations a mechanic’s license or
certificate issued by an authority is required while for LSA aircraft authorization by the manufacturer may be required.
aircraft model, n—aircraft manufacturer’s designation for an aircraft. (F2930, CICTT)
DISCUSSION—
The aircraft model is: (1) listed in the aircraft type certificate, (2) the designation used by the aircraft manufacturer to legally distinguish a particular
aircraft, or (3) the designation used by a national military or armed force to distinguish a particular aircraft. It is usually a model number that may
be part of a series of similar models. If an aircraft manufacturer is amateur construction, in most cases, the aircraft model would be the name designated
by the organization responsible for design.
F3060 − 20
aircraft operating instructions, AOI, n—provide methods and procedures to operate the aircraft safely (F2243, F2427, F2457,
F2564, F2746)
DISCUSSION—
For LSA, the AOI specify those parameters (for example, weight, stall speed, and maximum speed) that show the aircraft make and model meets the
LSA definition. The AOI may also be referred to as a POH.
aircraft popular name, n—name used by the aircraft manufacturer to market or otherwise distinguish a particular aircraft model
or series or both or the name used by a national military or armed force to distinguish a particular aircraft model or series or
both. (CICTT)
DISCUSSION—
An aircraft model or series or both may have more than one popular name. It is normally not the legal identification of the aircraft and, when found
on the type certificate or type certificate data sheet, it is supplementary information. Examples would be the Cessna Skyhawk or Sovereign, which are
popular names but not the legal identification. Popular names can be changed without affecting the type data of the aircraft.
airplane configuration, n—particular combination of the fixed components including wing(s), fuselage, empennage, propulsion
system, and landing gear along with the positions of the moveable elements, such as wing flaps, cowl flaps, landing gear, and
equipment, software configuration, and so forth that affects the aerodynamic or operational characteristics of the airplane. (F44)
airplane positive gust limit load factor, n , n—airplane positive gust limit load factor at V . (14 CFR 23, App A, Par. A23.3)
3 C
airship, n—power-driven lighter-than-air aircraft that can be steered. (F2354, F2355, F2356, F2427)
airworthiness design standards, ADS, n—standards that identify acceptable means of compliance to the regulatory requirements
for aircraft design for certified aircraft or the consensus standards such as ASTM F37, F38, or F39 for non-certified aircraft.
airworthiness directive, AD, n—regulation issued by the CAA that applies to aircraft, aircraft engines, propellers, or appliances
when an unsafe condition exists and that condition is likely to exist or develop in other products of the same design. (F2639)
DISCUSSION—
Airworthiness Directives (ADs) are legally enforceable regulations issued by the CAA to correct an unsafe condition in a product. Each CAA will have
its own guidance on ADs. For FAA-issued Ads, this follows the guidance in 14 CFR 39.
airworthiness limitation, n—limitation applicable to an aircraft or article installed on an aircraft in the form of a life limit or a
maintenance task that is mandatory to maintain the aircraft in airworthy condition. (F44)
alteration, n—modification of a product to establish a new airworthy configuration. (F44)
American Institute of Aeronautics and Astronautics, AIAA, n—world’s largest technical society dedicated to the global
aerospace profession. (F44)
American Society ASTM International, ASTM, n—globally recognized leader in the development and delivery of international
voluntary consensus standards. (F44)
annual condition inspection, n—detailed inspection accomplished once a year on an aircraft in accordance with the applicable
instructions for continued airworthiness.
(F2483, F44)
DISCUSSION—
The purpose of the inspection is to look for any wear, corrosion, or damage that would cause an aircraft to not be in a condition for safe operation.
appliance, n—any instrument, mechanism, equipment, part, apparatus, appurtenance, or accessory, including communications
equipment, that is used or intended to be used in operating or controlling an aircraft in flight; is installed in or permanently
attached to the aircraft; and is not part of an airframe, engine, or propeller. (F2639, 14 CFR Part 1)
arc fault circuit breaker, n—circuit breaker specifically designed to open when arcing faults are detected. (F2639)
aspect ratio, AR, n—wing span (b) squared divided by the wing area (S), b /S. (F2245, F2564)
auxiliary power unit, APU, n—any power unit delivering rotating shaft power, compressed air, or both, that is not intended for
direct propulsion of an aircraft. (F44)
F3060 − 20
average design surface load, w, n—load divided by area. (F2564)
balanced field length, BFL, n—for airplanes with more than one engine, it is the minimum allowable runway length for a given
airplane weight, configuration and atmospheric conditions as per field limitations. (FAA AC 120-62)
DISCUSSION—
It corresponds to the point where the accelerate-go performance required is equal to (“balances”) the accelerate-stop performance required.
balloon, n—lighter-than-air aircraft that is not engine-driven and sustains flight through the use of either gas buoyancy or an
airborne heater or both. (F2354, F2355, F2356, F2427)
best angle of climb, n—climb angle which produces the most altitude gain with least distance traveled horizontally (F44)
best angle of climb speed, V , n—the speed at which the aircraft will obtain the highest altitude in a given horizontal distance.
x
(F2317/F2317M)
DISCUSSION—
This best angle-of-climb speed normally increases slightly with altitude.
best rate of climb, n—climb rate that produces the most altitude gain in the least amount of time. (F44)
best rate of climb speed, V , n—speed at which the aircraft will obtain the maximum increase in altitude per unit of time.
y
(F2317/F2317M)
DISCUSSION—
This best rate-of-climb speed normally decreases slightly with altitude.
calibrated airspeed, CAS, n—indicated airspeed of an aircraft corrected for position and instrument error. (FAA Part1, Part 1,
EASA CS1)
DISCUSSION—
Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level.
center of gravity, CG, n—point at which the entire weight of a body may be considered as concentrated so that if supported at
this point the body would remain in equilibrium in any position. (TCCA, F2245, F2352, F2564)
certificate of airworthiness, CofA, n—a CAA document which grants authorization to operate an aircraft in flight. (F44)
chord, c,n—straight line distance joining the leading and trailing edges of an airfoil. (F2245)
civil aviation authority, CAA, n—governmental agency responsible for regulation of civil-aviation-related activities in a country
or jurisdiction, such as Agência Nacional de Aviação Civil (ANAC) of Brazil, or Transport Canada Civil Aviation (TCCA).
(F2425, F2563, F2507)
DISCUSSION—
In some countries, only certain parts of the aviation activities are the responsibility of the CAA. For the purposes of this terminology, the activities
are those related to aircraft, engine, and propeller certification and continued operational safety.
commercial part, n—part that is listed on an approved commercial parts list included in a design approval holder’s instructions
for continued airworthiness and for which:
(1) The failure of the commercial part, as installed in the product, would not degrade the level of safety of the product; and
(2) The part is produced only under the commercial part manufacturer’s specification and marked only with the commercial
part manufacturer’s markings. (14 CFR 21.1(b)(3), 21.50(c)(2))
compliance package, n—set of documents that provides objective, verifiable evidence for compliance to CAA regulations using
CAA accepted means of compliance which may be industry consensus standards or applicant developed means of compliance.
(F44)
F3060 − 20
compliance program, n—set of activities planned for, executed, and for which results are reviewed against CAA accepted industry
consensus standards or applicant developed means of compliance for the purpose of declaring compliance to a particular
standard. (F2930, F44)
consensus standard, n—for the purpose of certificating aircraft, an industry developed standard that applies to aircraft design,
production, and airworthiness.
(14 CFR Part 1.1)
DISCUSSION—
It includes, but is not limited to, standards for aircraft design and performance, required equipment, manufacturer quality assurance systems, production
acceptance test procedures, operating instructions, maintenance and inspection procedures, identification and recording of major repairs and major
alterations, and continued airworthiness.
continuing airworthiness, n—set of processes by which an aircraft, engine, propeller, or part complies with the applicable
airworthiness requirements and remains in a condition for safe operation throughout its operating life. (ICAO)
conventional fixed pitch propeller, n—one-piece fixed pitch propeller that is constructed of material such as wood or metal that
has no abrupt changes in material properties as the blades transition through the hub area. (F2506)
creepage, n—conduction of electrical current along a surface between two points at different potentials. (F2639)
critical engine failure takeoff speed, V , n—speed at which the critical engine is assumed to fail during takeoff.
EF
cruise, n—condition during which the aircraft is in level flight or making altitude changes between the take-off and climb phase
and the descent to landing phase. (F2490)
demonstrated flight dive speed, V /M , n—maximum speed at which it has been demonstrated there is an absence of excessive
DF DF
buffet, vibration, or controllability problems (V ≤ V ). (14 CFR Part 1, F2317/F2317M, F2245, F2564)
DF D
design and performance specification, n—used herein to refer to Specifications F2245 and F2564. (F3035)
design cruising speed, V , n—maximum speed for which the aircraft has been designed for cruise flight. (14 CFR Part 1, F2245,
C
F2564)
design dive speed, V /M , n—maximum speed for which the structure has been designed. (FAA Part 1, F2245, F2564)
D D
design flap speed, V , n—maximum speed at which the aircraft can be flown at the selected flap deflection. (F2245, F2564)
F
design maneuvering speed, V , n—speed below which you can move a single flight control, one time, to its full deflection, for
A
one axis of airplane rotation only (pitch, roll or yaw), in smooth air, without risk of damage to the airplane. (F2245, F2564,
F2317/F2317M, F44)
design maximum aircraft weight, W , n—aircraft design maximum weight for LSA aircraft shall be the maximum weight for
MAX
which the aircraft is designed. (F2317/F2317M)
DISCUSSION—
This is acceptable for LSA aircraft but is inadequate definition for many of today’s Part 23 aircraft that have a maximum taxi weight, maximum takeoff
weight, maximum landing weight, and maximum zero fuel weight that are all different.
design maximum trike carriage weight, W , n—highest trike carriage weight at which compliance with each applicable
susp
structural loading condition and each applicable flight requirement is shown. (F2317/F2317M)
design speed for maximum gust intensity, V , n—the speed at which particular gust intensities apply in the determination of
B
structural loads. (F44)
design stall speed, V , n—stalling speed or the minimum steady flight speed at which the airplane is controllable. (F2245, F2564,
S
F44)
design useful load, n—load (other than structure, engine, enclosure, and systems) that an aircraft can carry while achieving the
design defining performance requirements. (F2355, F44)
drag coefficient, C , n—nondimensional number whose value represents a relative magnitude of the resistance force of a body
D
against a moving fluid environment, for example, to the free stream air flow in the case of an aircraft. (F2245, F2564, F44)
dynamic pressure, Q or q,n—pressure that would be exerted by a moving air flow against a body if it were brought to rest. (F2245,
F2564, F44)
F3060 − 20
electrical wiring interconnection system, EWIS, n—any wire, wiring device, or combination of these, including termination
devices, installed in any area of the aircraft for the purpose of transmitting electrical energy between two or more intended
termination points. (F2799)
electronic engine control system, EECS, n—engine control system in which the primary functions are provided using electronics.
(EASA CS1)
DISCUSSION—
It includes all the components (for example, digital, electrical, electronic, hydro-mechanical, and pneumatic) necessary for the control of the engine
and may incorporate other control functions where desired.
emergency electrical power operation, n—condition that occurs following a loss of all normal electrical generating power
sources or another malfunction that results in operation on an alternate electrical power source only or both. (F2490)
empty weight, n—the empty weight of the aircraft includes the combined weight of the airframe, propulsion system, required
equipment, installed optional or special equipment, fixed ballast, unusable fuel, and full operating fluids, including oil, hydraulic
fluid, and other fluids required for normal operation of aircraft systems, except potable water, lavatory precharge water, and
water intended for injection in the engines. (F3082F3082/F3082M, F3116F3116/F3116M, F3117F3117/F3117M)
equivalent airspeed, EAS, n—calibrated airspeed of an aircraft corrected for adiabatic compressible flow for the particular
altitude. (14 CFR Part 1, EASA CS1)
DISCUSSION—
Equivalent airspeed is equal to calibrated airspeed in standard atmosphere at sea level.
European Aviation Safety Agency, EASA, n—agency of the European Union that serves as the CAA for contracting states.
(EASA)
European Organization for Civil Aviation Equipment, EUROCAE, n—(1) nonprofit organization that was formed at Lucerne,
Switzerland in 1963 to provide a European forum for resolving technical problems with electronic equipment for air transport;
(2) deals exclusively with aviation standardization (airborne and ground systems and equipment) and related documents as
required to use in the regulation of aviation equipment and systems; and (3) association composed of members who are all
specialized in one or several technical fields of aeronautics and many of them are considered to be among world’s leaders in
their domain. (F44)
exhaust gas temperature, EGT, n—temperature of the exhaust gas exiting an engine. (F44)
factor of safety, FOS, n—design factor (multiplier) used to provide for the possibility of loads greater than those assumed and
uncertainties in design and fabrication.
(ICAO, F2352)
DISCUSSION—
Refer to ultimate load definition for relationship between factor of safety and ultimate load.
final takeoff speed, V , n—speed of the airplane that exists at the end of the takeoff path in the en-route configuration with one
FTO
engine inoperative. (14 CFR Part 1, EASA CS1)
fireproof, adj—(1) With respect to materials and parts used to confine fire in a designated fire zone, means the capacity to withstand
at least as well as steel in dimensions appropriate for the purpose for which they are used, the heat produced when there is a
severe fire of extended duration in that zone; and (2) with respect to other materials and parts, means the capacity to withstand
the heat associated with fire at least as well as steel in dimensions appropriate for the purpose for which they are used. (F2352,
14 CFR Part 1)
DISCUSSION—
For materials, this is considered to be equivalent to the capability of withstanding a fire at least as well as steel or titanium in dimensions appropriate
for the purposes for which they are used.
F3060 − 20
fire resistant, adj—(1) With respect to sheet or structural members, means the capacity to withstand the heat associated with fire
at least as well as aluminum alloy in dimensions appropriate for the purpose for which they are used; and (2) with respect to
fluid-carrying lines, fluid system parts, wiring, air ducts, fittings, and powerplant controls, means the capacity to perform the
intended functions under the heat and other conditions likely to occur when there is a fire at the place concerned. (14 CFR Part
1)
DISCUSSION—
For materials, this may be considered to be equivalent to the capability of withstanding a fire at least as well as aluminum alloy in dimensions
appropriate for the purposes for which they are used.
fixed pitch propeller, n—propeller, the pitch of which cannot be changed, except by processes constituting a workshop operation.
(EASA CS1, F2506, F44)
flame resistant, adj—not susceptible to combustion to the point of propagating a flame, beyond safe limits, after the ignition source
is removed. (14 CFR, Part 1, EASA CS1)
flaps, n—trailing or leading edge devices to increase lift and drag. (F2245, F2564, F44)
DISCUSSION—
Although most flaps are on the trailing edge, some flaps such as Krueger flaps are on the leading edge.
flight data recorder, FDR, n—device used to record specific aircraft parameters. (F44)
flight management system, FMS, n—specialized computer system that automates a wide variety of in-flight tasks, reducing the
workload on the flight crew. (F44)
DISCUSSION—
A primary function is in-flight management of the flight plan.
flight manual, FM, n—manual describing the operation of the aircraft and includes any limitations; normal, abnormal, and
emergency procedures; and provides specific facts, information, and/or instructions about a particular aircraft and the operation
of that aircraft. (F44)
DISCUSSION—
For airplanes, this is identified as an airplane flight manual (AFM).
flight manual supplement, FMS, n—document that provides supplemental information, usually for equipment such as options or
STCs that are not part of the basic aircraft and included in the main flight manual. (F44)
flight training supplement, FTS, n—document providing guidance for training for LSA aircraft. (F2457, F2745)
full authority digital engine control, FADEC, n—system consisting of digital computer, called an electronic engine controller
(EEC) or engine control unit (ECU), and its related accessories that control all aspects of aircraft engine performance. (F44)
General Aviation Manufacturers Association, GAMA, n—international trade association representing over 80 of the world’s
leading manufacturers of general aviation airplanes and rotorcraft, engines, avionics, components and related services. (F44)
DISCUSSION—
GAMA’s members also operate repair stations, fixed-based operations, pilot and maintenance training facilities, and they manage fleets of aircraft.
ground adjustable propeller, n—propeller whose pitch setting is adjustable only when the aircraft is on the ground and the
propeller is not rotating. (F2506)
heavy maintenance, n—any maintenance, inspection, repair, or alteration a manufacturer has designated that requires specialized
training, equipment, or facilities. (F2483, F2584)
high-intensity radiated field, HIRF, n—radio frequency energy of a strength sufficient to adversely affect either a living organism
or the performance of a device subjected to it. (F44)
F3060 − 20
illustrated parts breakdown, IPB, n—technical publications identifying the parts making up assemblies and products and relation
to each other through the use of illustrations. Also referred to as an illustrated parts catalog (IPC). (F44)
instrument flight rules, IFR, n—rules and regulations governing flight by relying on instrument readings instead of visual
reference to the ground. (14 CFR Part 1)
indicated airspeed, IAS, n—speed of an aircraft as shown on its pitot static airspeed indicator calibrated to reflect standard
atmosphere adiabatic compressible flow at sea level uncorrected for airspeed system errors. (14 CFR Part 1)
Institute of Electrical and Electronics Engineers, IEEE, n—leading authority on areas ranging from aerospace systems,
computers, and telecommunications to biomedical engineering, electric power, and consumer electronics. (F44)
instructions for continued airworthiness, ICA, n—provide documentation of recommended methods, inspections, processes, and
procedures to keep products airworthy. The ICA must contain information on each item or part, as appropriate, installed on the
product. (F2799)
instrument meteorological conditions, IMC, n—weather conditions below the minimum for flight under visual flight rules, also
referred to as IFR conditions. (14 CFR Part 1, EASA CS1, CS2)
International Civil Aviation Organization, ICAO, n—agency of the that codifies the principles and techniques of international
air navigation and fosters the planning and development of international air transport to ensure safe and orderly growth. (F44)
International Electrotechnical Commission, IEC, n—international standards and conformity assessment body for all fields of
electrotechnology. (F44)
Joint Electron Device Engineering Council, JEDEC, n—independent semiconductor engineering trade organization and
standardization body associated with the Electronic Industries Alliance (EIA), a trade association that represents all areas of the
electronics industry in the United States. (F44)
kit assembly instructions, KAI, n—instructions for assembling an LSA aircraft kit. (F2563, F2745)
life-limited part, n—part that, as a condition of the type certificate, may not exceed a specified time, or number of operating cycles,
in service. (TCCA)
light-sport aircraft, LSA, n—an aircraft designed and built to comply with light sport aircraft consensus standards.
DISCUSSION—
National airworthiness authorities may have additional certification requirements that supplement the ASTM consensus standards for LSA’s certified
by them.
light-sport aircraft kit, LSA kit, n—aircraft designed in accordance with Specifications F2245 or F2564 that is manufactured and
delivered as a kit. (F3035)
lighter-than-air aircraft, n—aircraft that can rise and remain suspended by using contained gas weighting less than the air that
is displaced by the gas. (F2354, F2355, F2356, F2427)
DISCUSSION—
Airships may include dynamic lift that derives as much as 30 % lift from other than buoyancy.
limit load, n—maximum loads assumed to occur in the anticipated operating conditions. (ICAO, F2352)
DISCUSSION—
Refer to ultimate load for relationship of limit load to ultimate load.
line maintenance, n—any repair, maintenance, scheduled checks, servicing, inspections, or alterations not considered heavy
maintenance that is specified in the manufacturer’s maintenance manual. (F2483)
line replaceable unit, LRU, n—modular component of an aircraft designed to be replaced quickly at an operating location.
(F2799, F44)
light-sport repairman inspection, LSRI, n—U.S. FAA-certificated repairman (light-sport aircraft) with an inspection rating as
defined by 14 CFR Part 65 authorized to perform the annual condition inspection on experimental light-sport aircraft or an
equivalent rating issued by other civil aviation authorities. (F2483)
F3060 − 20
DISCUSSION—
Experimental LSA do not require the individual performing maintenance to hold any FAA airman certificate in the United States.
LSA repairman maintenance, LSRM, n—U.S. FAA-certificated repairman (light-sport aircraft) with a maintenance rating as
defined by 14 CFR Part 65 authorized to perform line maintenance on aircraft certificated as special LSA aircraft and authorized
to perform the annual condition/100-h inspection on an LSA or an equivalent rating issued by other civil aviation authorities.
(F37, F2483)
maintenance manual(s), MM(s), n—manual provided by a manufacturer or supplier that specifies all maintenance, repairs,
scheduled checks, and alterations authorized by the manufacturer to maintain the aircraft in an airworthy condition. (F2483,
F2930)
major alteration, n—alteration not listed in the aircraft, aircraft engine, or propeller specifications: (1) that might appreciably
affect weight, balance, structural strength, performance, powerplant operation, flight characteristics, or other qualities affecting
airworthiness or (2) that is not done according to accepted practices or cannot be done by elementary operations. (F2483, 14
CFR Part 43)
DISCUSSION—
For LSA, a major alteration is any alteration for which instructions to complete the task are excluded from the maintenance manual(s) supplied to the
consumer. For certified aircraft refer to the applicable CAA guidance for additional definition and examples.
major repair, n—repair: (1) that, if improperly done, might appreciably affect weight, balance, structural strength, performance,
powerplant operation, flight characteristics, or other qualities affecting airworthiness or (2) that is not done according to
applicable CAA guidance or cannot be done by elementary operations. (F2483, 14 CFR Part 43)
DISCUSSION—
For LSA, a major repair is any repair for which instructions to complete the task are excluded from the maintenance manual(s) supplied to the
consumer. For certified aircraft it is taken to mean changes to the empty weight or empty balance which increase in the maximum certificated weight
or center of gravity limits of the aircraft. See applicable CAA guidance for more specific examples of major repair.
manufacturer, n—any entity engaged in the production of an aircraft or component used on an aircraft. (F44, F2295, F2415,
F2483)
DISCUSSION—
For LSA, the manufacturer is also responsible for completing all compliance related paperwork and assertions of compliance.
master compliance checklist, MCCL, n—listing of all the regulations applicable to a specific product.
material bond, n—adhesion of one surface to another with or without the use of an adhesive as a bonding agent for the purpose
of making the parts act as one part. (F2639)
maximum continuous power or thrust or both, n—power or thrust or both identified in the performance data for use during
periods of unrestricted duration. (EASA CS1)
maximum continuous power or thrust or both rating, n—minimum test bed acceptance power or thrust or both, as stated in the
engine-type certificate data sheet, of series and newly overhauled engines when running at the specified conditions and within
the appropriate acceptance limitations. (EASA CS1)
maximum empty weight, W , n—largest empty weight of the aircraft, including all operational equipment that is installed in the
E
aircraft: weight of the airframe, powerplant, required equipment, installed optional and specific equipment, fixed ballast, full
engine coolant and oil, hydraulic fluid, and the unusable fuel. (F2564, F2245)
DISCUSSION—
Hence, the maximum empty weight equals maximum takeoff weight minus minimum useful load: W = W – W .
E U
maximum engine overspeed, n—maximum rotational speed of a mechanically independent main rotating system of an engine,
inadvertent occurrence of which for periods agreed to between CAA and engine manufacturer, has been agreed not to require
rejection of the engine from service or maintenance action (other than to correct the cause).
(EASA CS1)
F3060 − 20
maximum engine overtorque, n—for turbo-propeller and turbo-shaft engines incorporating free power turbines only: the
maximum torque of the free power turbine, the inadvertent occurrence and duration of which has been established not to require
rejection of the engine from service or maintenance action. (EASA CS1)
maximum exhaust gas over temperature, n—for turbine engines, the maximum engine exhaust gas temperature, the inadvertent
occurrence, and duration has been established not to require rejection of the engine from service or maintenance action. (EASA
CS1)
DISCUSSION—
This is not to be confused with maximum temperatures established for use during starting operations.
maximum flap extended speed, V , n—highest speed permissible with wing flaps in a prescribed extended position. (14 CFR
FE
Part 1)
maximum governed propeller speed, n—maximum rotational speed for variable pitch governing propellers as determined by the
setting of the propeller governor or control mechanism. (EASA CS1)
maximum landing gear extended speed, V , n—maximum speed at which an aircraft can be safely flown with the landing gear
LE
extended. (14 CFR Part 1)
maximum landing gear operating speed, V , n—maximum speed at which the landing gear can be safely extended or retracted.
LO
(14 CFR 1.2, EASA CS1)
maximum landing weight, n—the maximum allowable weight of the aircraft when it touches down for landing.
(F3116F3116/F3116M, F3082F3082/F3082M, F3093F3093/F3093M, F3117F3117/F3117M)
maximum operating speed, V , n—given as a limitation in the AFM and it cannot exceed V √n. (14 CFR 23.1507)
O S
maximum permissible propeller speed, n—maximum propeller rotational speed permitted in normal or likely emergency
operation for fixed, adjustable, or variable (non-governing) propellers. (EASA CS1)
maximum propeller overspeed, n—maximum propeller rotational speed, the inadvertent occurrence and duration of which has
been established not to require rejection of the propeller from service or maintenance action. (EASA CS1)
maximum ramp weight, n—the maximum allowable weight of the aircraft while stationary or in motion on the ground under its
own power prior to beginning the takeoff roll. (F3082F3082/F3082M, F3116F3116/F3116M, F3117F3117/F3117M)
DISCUSSION—
For normal operations this may be: (a) equal to the Maximum Takeoff Weight, or (b) the Maximum Takeoff Weight plus an estimated fuel use from
engine start up to takeoff. It is also frequently referred to as Taxi Weight.
maximum spoiler/speed brake extended speed, V , n—maximum speed at which aircraft can be flown with spoilers or speed
SP
brakes extended. (F2245)
maximum stability characteristics speed, V /M , n—maximum speed/Mach number for stability characteristics. (14 CFR
FC FC
Part 1)
maximum sustainable straight and level airspeed, V , n—maximum speed in level flight with maximum continuous power. (14
H
CFR Part 1)
maximum takeoff weight, MTOW, n—the maximum allowable weight when starting the takeoff roll. (F2244, F2245, F2355,
F2564, F3082F3082/F3082M, F3116F3116/F3116M,
F3117F3117/F3117M)
DISCUSSION—
This is the weight used to determine maximum flight loads and flight requirements and it may also be the weight used to determine the maximum
ground loads when it is the same as the Ramp Weight, Landing Weight, or Towing Weight. This is sometimes referred to as Maximum Certified Takeoff
Weight (MCTOW) when applied only to the approved weight and not the design weight. It may also be referred to as the gross weight by some.
maximum towing weight, n—the maximum allowable weight of the aircraft when being towed on the ground.
(F3116F3116/F3116M, F3082F3082/F3082M, F3093F3093/F3093M)
F3060 − 20
maximum zero wing fuel weight, n—the maximum weight of the aircraft without any usable fuel in the wing fuel tanks.
(F3082F3082/F3082M, F3116F3116/F3116M, F3117F3117/F3117M)
DISCUSSION—
Any weight added above this weight must be in the form of fuel added
...