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ASTM F2317/F2317M-05

(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:ScopeReferenced DocumentsTerminologyFlight RequirementsStructural RequirementsDesign and Construction RequirementsPowerplant RequirementsEquipment RequirementsOperating LimitationsKeywordsAnnexAppendix
1.5 The values stated in SI units are to be regarded as the standard. The values given in parentheses are for information only.
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

Status
Historical
Publication Date
31-Oct-2005
ICS
49.020 - Aircraft and space vehicles in general
Technical Committee
F37 - Light Sport Aircraft
Drafting Committee
F37.40 - Weight Shift
Current Stage
Ref Project

Relations

Replaced By
ASTM F2317/F2317M-05(2007) - Standard Specification for Design of Weight-Shift-Control Aircraft
Effective Date
01-Dec-2007
Referred By
ASTM F3060-20 - Standard Terminology for Aircraft
Effective Date
01-Nov-2005
Referred By
ASTM F2507-15 - Standard Specification for Recreational Airpark Design
Effective Date
01-Nov-2005
Referred By
ASTM F3199-16a - Standard Guide for Wing Interface Documentation for Weight Shift Control Aircraft
Effective Date
01-Nov-2005

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ASTM F2317/F2317M-05 - Standard Specification for Design of Weight-Shift-Control Aircraft
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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: F 2317/F 2317M – 05
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 2. Referenced Documents
2
1.1 This specification covers the minimum airworthiness 2.1 ASTM Standards:
standards a manufacturer shall meet in the designing, testing, F2339 Practice for Design and Manufacture of Reciprocat-
and labeling of weight-shift-control aircraft. ing Spark Ignition Engines for Light Sport Aircraft
3
1.2 This specification covers only weight-shift-control air- 2.2 Federal Aviation Regulations:
craftinwhichflightcontrolsystemsdonotusehingedsurfaces FAR-33 Airworthiness Standards: Aircraft Engines
controlled by the pilot. FAR-35 Airworthiness Standards: Propellers
4
2.3 Joint Aviation Requirements:
NOTE 1—This section is intended to preclude hinged surfaces such as
JAR-E Engines
typically found on conventional airplanes such as rudders and elevators.
JAR-P Propellers
Flexible sail surfaces typically found on weight-shift aircraft are not
considered hinged surfaces for the purposes of this specification. JAR-22 Sailplanes and Powered Sailplanes
1.3 Weight-shift-control aircraft means a powered aircraft
3. Terminology
with a framed pivoting wing and a fuselage (trike carriage)
3.1 Definitions—Aircraft Weight:
controllable only in pitch and roll by the pilot’s ability to
3.1.1 design maximum aircraft weight, n—aircraft design
change the aircraft’s center of gravity with respect to the wing.
maximum weight W shall be the sum of W + W .
MAX WING SUSP
Flight control of the aircraft depends on the wing’s ability to
3.1.2 design maximum trike carriage weight, n—design
flexibly deform rather than the use of control surfaces.
maximum trike carriage weight, W , shall be established so
susp
1.4 This specification is organized and numbered in accor-
that it is: (1) highest trike carriage weight at which compliance
dance with the bylaws established for Committee F37. The
with each applicable structural loading condition and each
main sections are:
applicableflightrequirementisshown,and(2)notlessthanthe
Scope 1
empty trike carriage weight, W , plus a weight of occu-
Referenced Documents 2 tkmt
Terminology 3 pant(s)of86.0kg(189.6lb)forasingle-seataircraftor150kg
Flight Requirements 4
(330.8 lb) for a two-seat aircraft, plus the lesser of full usable
Structural Requirements 5
fuel or fuel weight equal to 1-h burn at economical cruise at
Design and Construction Requirements 6
Powerplant Requirements 7 maximum gross weight.
Equipment Requirements 8
3.1.3 trike carriage empty weight, W , n—all parts, com-
tkmt
Operating Limitations 9
ponents, and assemblies that comprise the trike carriage
Keywords 10
Annex Annex A1
assembly or that are attached to the suspended trike in flight,
Appendix Appendix X1
including any wing attachment bolts, shall be included in the
1.5 trike carriage assembly empty weight, W . These must
tkmt
include the required minimum equipment, unusable fuel,
1.6 This standard does not purport to address all of the
safety concerns, if any, associated with its use. It is the maximum oil, and where appropriate, engine coolant and
responsibility of the user of this standard to establish appro-
priate safety and health practices and determine the applica-
bility of regulatory requirements prior to use.
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.
1 3
This specification is under the jurisdiction of ASTM Committee F37 on Light Available from Federal Aviation Administration, 800 Independence Ave., SW,
Sport Aircraft and is the direct responsibility of Subcommittee F37.40 on Weight Washington, DC 20591.
4
Shift. Available from Global Engineering Documents, 15 Inverness Way, East
Current edition approved Nov. 1, 2005. Published November 2005. Englewood, CO 80112-5704
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1

---------------------- Page: 1 ----------------------
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
F 2317/F 2317M – 05
hydraulic fluid. Trike carriage empty weight, W , shall be 4.1.4 Climb performance requirements shall be met at
tkmt
recorded in the Aircraft Operating Instructions (AOI)
...

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1.2 The values stated in SI units are to be regarded as standard. There may be values given in parentheses that are mathematical conversions to inch-pound units. Values in parentheses are provided for information only and are not considered standard.  
1.2.1 Note that within the aviation community mixed units are appropriate in accordance with International Civil Aviation Organization (ICAO) agreements. While the values stated in SI units are regarded as standard, certain values such as airspeeds in knots and altitude in feet are also accepted as standard.  
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