ASTM F2317/F2317M-16
(Specification)Standard Specification for Design of Weight-Shift-Control Aircraft
Standard Specification for Design of Weight-Shift-Control Aircraft
ABSTRACT
This specification covers the minimum requirement for designing, testing, and labeling of weight-shift-control aircraft. This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot. Flight requirements are specified for: (1) proof of compliance including hang point and trimming setting; (2) general performance such as (a) stall speed in the landing configuration, (b) stall speed free of control limits, (c) minimum climb performance, (d) flutter, buffeting, and vibration, (e) turning flight and stalls, and (f) maximum sustainable speed in straight and level flight; (3) controllability and maneuverability such as general, longitudinal, and lateral control; and (4) longitudinal stability and pitch testing. Structural requirements specified include: (1) strength requirements, (2) fulfillment of design requirements, (3) safety factors, (4) design airspeeds, (5) flight loads, (6) pilot control loads, (7) ground loads including landing gear shock absorption, and (8) emergency landing loads. Design and construction requirements are specified for: (1) materials, (2) fabrication methods, (3) self-locking nuts, (4) protection of structure, (5) accessibility, (6) setup and breakdown, (7) control system evaluated by operation test, (8) mast (pylon) safety device, (9) cockpit design, and (10) markings and placards. Powerplant requirements including installation, fuel system, oil system, induction system, and fire prevention, as well as equipment requirements such as powerplant instruments, miscellaneous equipment, and lap belts and harnesses, are detailed. Operating limitations such as load distribution limits are also specified.
SCOPE
1.1 This specification covers the minimum airworthiness standards a manufacturer shall meet in the designing, testing, and labeling of weight-shift-control aircraft.
1.2 This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot.
Note 1: This section is intended to preclude hinged surfaces such as typically found on conventional airplanes such as rudders and elevators. Flexible sail surfaces typically found on weight-shift aircraft are not considered hinged surfaces for the purposes of this specification.
1.3 Weight-shift-control aircraft means a powered aircraft with a framed pivoting wing and a fuselage (trike carriage) controllable only in pitch and roll by the pilot's ability to change the aircraft's center of gravity with respect to the wing. Flight control of the aircraft depends on the wing's ability to flexibly deform rather than the use of control surfaces.
1.4 This specification is organized and numbered in accordance with the bylaws established for Committee F37. The main sections are:
Scope
1
Referenced Documents
2
Terminology
3
Flight Requirements
4
Structural Requirements
5
Design and Construction Requirements
6
Powerplant Requirements
7
Equipment Requirements
8
Operating Limitations
9
Keywords
10
Annex
Annex A1
Appendix
Appendix X1
1.5 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 non-conformance with the standard.
1.6 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 and health practices and determine the applicability of regulatory requirements prior to use.
General Information
Relations
Buy Standard
Standards Content (Sample)
NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation:F2317/F2317M −16
Standard Specification for
1
Design of Weight-Shift-Control Aircraft
ThisstandardisissuedunderthefixeddesignationF2317/F2317M;thenumberimmediatelyfollowingthedesignationindicatestheyear
of original adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.
A superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 1.6 This standard does not purport to address all of the
safety concerns, if any, associated with its use. It is the
1.1 This specification covers the minimum airworthiness
responsibility of the user of this standard to establish appro-
standards a manufacturer shall meet in the designing, testing,
priate safety and health practices and determine the applica-
and labeling of weight-shift-control aircraft.
bility of regulatory requirements prior to use.
1.2 This specification covers only weight-shift-control air-
2. Referenced Documents
craftinwhichflightcontrolsystemsdonotusehingedsurfaces
2
controlled by the pilot.
2.1 ASTM Standards:
NOTE 1—This section is intended to preclude hinged surfaces such as
F2339Practice for Design and Manufacture of Reciprocat-
typically found on conventional airplanes such as rudders and elevators.
ing Spark Ignition Engines for Light Sport Aircraft
Flexible sail surfaces typically found on weight-shift aircraft are not
3
2.2 Federal Aviation Regulations:
considered hinged surfaces for the purposes of this specification.
FAR-33Airworthiness Standards: Aircraft Engines
1.3 Weight-shift-control aircraft means a powered aircraft
FAR-35Airworthiness Standards: Propellers
with a framed pivoting wing and a fuselage (trike carriage)
4
2.3 Joint Aviation Requirements:
controllable only in pitch and roll by the pilot’s ability to
JAR-EEngines
change the aircraft’s center of gravity with respect to the wing.
JAR-PPropellers
Flight control of the aircraft depends on the wing’s ability to
JAR-22Sailplanes and Powered Sailplanes
flexibly deform rather than the use of control surfaces.
3. Terminology
1.4 This specification is organized and numbered in accor-
dance with the bylaws established for Committee F37. The
3.1 Definitions—Aircraft Weight:
main sections are:
3.1.1 design maximum aircraft weight, n—aircraft design
Scope 1
maximum weight W shall be the sum of W + W .
MAX WING SUSP
Referenced Documents 2
3.1.2 design maximum trike carriage weight, n—design
Terminology 3
Flight Requirements 4
maximum trike carriage weight, W , shall be established so
susp
Structural Requirements 5
that it is: (1) highest trike carriage weight at which compliance
Design and Construction Requirements 6
with each applicable structural loading condition and each
Powerplant Requirements 7
Equipment Requirements 8
applicableflightrequirementisshown,and(2)notlessthanthe
Operating Limitations 9
empty trike carriage weight, W , plus a weight of occu-
tkmt
Keywords 10
pant(s)of86.0kg[189.6lb]forasingle-seataircraftor150kg
Annex Annex A1
Appendix Appendix X1
[330.8 lb] for a two-seat aircraft, plus the lesser of full usable
fuel or fuel weight equal to 1-h burn at economical cruise at
1.5 The values stated in either SI units or inch-pound units
maximum gross weight.
are to be regarded separately as standard. The values stated in
each system may not be exact equivalents; therefore, each
3.1.3 trike carriage empty weight, W ,n—all parts,
tkmt
system shall be used independently of the other. Combining
components, and assemblies that comprise the trike carriage
values from the two systems may result in non-conformance
assembly or that are attached to the suspended trike in flight,
with the standard.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
1
This specification is under the jurisdiction of ASTM Committee F37 on Light Standards volume information, refer to the standard’s Document Summary page on
Sport Aircraft and is the direct responsibility of Subcommittee F37.40 on Weight the ASTM website.
3
Shift. Available from Federal Aviation Administration, 800 Independence Ave., SW,
CurrenteditionapprovedJune1,2016.PublishedJuly2016.Originallyapproved Washington, DC 20591.
4
in 2005. Last previous edition approved in 2010 as F2317/F2317M–10. DOI: Available from Global Engineering Documents, 15 Inverness Way, East
10.1520/F2317_F2317M-16. Englewood, CO 80112-5704
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F2317/F2317M−16
including any wing attachment bolts, shall be included in the 4.1.1 It shall be possible to demonstrate that the aircraft
trike carriage assembly empty weight, W . These must meet
...
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: F2317/F2317M − 10 F2317/F2317M − 16
Standard Specification for
1
Design of Weight-Shift-Control Aircraft
This standard is issued under the fixed designation F2317/F2317M; 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 specification covers the minimum airworthiness standards a manufacturer shall meet in the designing, testing, and
labeling of weight-shift-control aircraft.
1.2 This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces
controlled by the pilot.
NOTE 1—This section is intended to preclude hinged surfaces such as typically found on conventional airplanes such as rudders and elevators. Flexible
sail surfaces typically found on weight-shift aircraft are not considered hinged surfaces for the purposes of this specification.
1.3 Weight-shift-control aircraft means a powered aircraft with a framed pivoting wing and a fuselage (trike carriage)
controllable only in pitch and roll by the pilot’s ability to change the aircraft’s center of gravity with respect to the wing. Flight
control of the aircraft depends on the wing’s ability to flexibly deform rather than the use of control surfaces.
1.4 This specification is organized and numbered in accordance with the bylaws established for Committee F37. The main
sections are:
Scope 1
Referenced Documents 2
Terminology 3
Flight Requirements 4
Structural Requirements 5
Design and Construction Requirements 6
Powerplant Requirements 7
Equipment Requirements 8
Operating Limitations 9
Keywords 10
Annex Annex A1
Appendix Appendix X1
1.5 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 non-conformance with the standard.
1.6 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 and health practices and determine the applicability of regulatory
requirements prior to use.
2. Referenced Documents
2
2.1 ASTM Standards:
F2339 Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft
3
2.2 Federal Aviation Regulations:
FAR-33 Airworthiness Standards: Aircraft Engines
FAR-35 Airworthiness Standards: Propellers
4
2.3 Joint Aviation Requirements:
JAR-E Engines
JAR-P Propellers
1
This specification is under the jurisdiction of ASTM Committee F37 on Light Sport Aircraft and is the direct responsibility of Subcommittee F37.40 on Weight Shift.
Current edition approved Jan. 1, 2010June 1, 2016. Published February 2010July 2016. Originally approved in 2005. Last previous edition approved in 20092010 as
F2317/F2317M – 05 (2009).F2317/F2317M – 10. DOI: 10.1520/F2317_F2317M-10.10.1520/F2317_F2317M-16.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
3
Available from Federal Aviation Administration, 800 Independence Ave., SW, Washington, DC 20591.
4
Available from Global Engineering Documents, 15 Inverness Way, East Englewood, CO 80112-5704
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F2317/F2317M − 16
JAR-22 Sailplanes and Powered Sailplanes
3. Terminology
3.1 Definitions—Aircraft Weight:
3.1.1 design maximum aircraft weight, n—aircraft design maximum weight W shall be the sum of W + W .
MAX WING SUSP
3.1.2 design maximum trike carriage weight, n—design maximum trike carriage weight, W , shall be established so that it is:
susp
(1) highest trike carriage weight at which compliance with each applicable structural loading condition and each applicable flight
requirement is shown, and (2) not less than the empty trike carriage weight, W , plus a weight of occupant(s) of 86.0 kg [189.6
tkmt
lb] for a single-seat aircraft or 150 kg [330.8 lb] for a two-seat aircraft, plus the lesser of full usable fuel o
...
Questions, Comments and Discussion
Ask us and Technical Secretary will try to provide an answer. You can facilitate discussion about the standard in here.