ASTM F3173/F3173M-15

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Designation:F3173/F3173M −15
Standard Specification for
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Handling Characteristics of Aeroplanes
ThisstandardisissuedunderthefixeddesignationF3173/F3173M;thenumberimmediatelyfollowingthedesignationindicatestheyear
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.
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1. Scope 2.2 Federal Standard:
14 CFR Part 23 (Amendment 62) Airworthiness Standards:
1.1 This specification establishes the airworthiness design
Normal, Utility, Aerobatic, and Commuter Category Air-
standards associated with general airplane-handling character-
craft
istics in flight and on ground and water.
1.2 This specification is applicable to aeroplanes.
3. Terminology
1.3 The applicant for a design approval shall seek the
3.1 Refer to Terminology F3060 referenced in Section 2.
individual guidance of their respective civil aviation authority
(CAA) body concerning the use of this specification as part of 4. General Requirements
a certification plan. For information on which CAAregulatory
4.1 General—Unless otherwise specified in a specific
bodies have accepted this specification (in whole or in part) as
requirement, the airplane shall meet the requirements of 4.2 –
a means of compliance to their small aircraft airworthiness
4.9, Sections 5–8, 9.1, and 9.2 at all practical loading
regulations (hereinafter referred to as “the Rules”), refer to the
conditions and operating altitudes for which certification has
ASTM Committee F44 webpage (www.ASTM.org/
been requested, not exceeding the maximum operating altitude
COMITTEE/F44.htm) which includes CAA website links.
established in Specification F3174/F3174M, subsection 4.11,
1.4 Units—The values stated in either SI units or inch- and without requiring exceptional piloting skill, alertness, or
pound units are to be regarded separately as standard. The strength.
values stated in each system may not be exact equivalents;
4.2 Control Forces (General):
therefore,eachsystemshallbeusedindependentlyoftheother.
4.2.1 The airplane shall be safely controllable and maneu-
Combining values from the two systems may result in noncon-
verable during all flight phases including:
formance with the standard.
4.2.1.1 Takeoff,
1.5 This standard does not purport to address all of the 4.2.1.2 Climb,
safety concerns, if any, associated with its use. It is the 4.2.1.3 Level flight,
responsibility of the user of this standard to establish appro- 4.2.1.4 Descent,
priate safety and health practices and determine the applica- 4.2.1.5 Go-around, and
bility of regulatory requirements prior to use. 4.2.1.6 Landing (power on and power off) with the wing
flaps extended and retracted.
4.2.2 It shall be possible to make a smooth transition from
2. Referenced Documents
one flight condition to another (including turns and slips)
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2.1 ASTM Standards:
without danger of exceeding the limit load factor under any
F3060 Terminology for Aircraft
probable operating condition (including, for multiengine
F3061/F3061M Specification for Systems and Equipment in
airplanes, those conditions normally encountered in the sudden
Small Aircraft
failure of any engine).
F3174/F3174M Specification for Establishing Operating
4.2.3 If marginal conditions exist with regard to required
Limitations and Information for Aeroplanes
pilot strength, the control forces necessary shall be determined
by quantitative tests. In no case may the control forces under
the conditions specified in 4.2.1 and 4.2.2 exceed those
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ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
prescribed in Table 1.
AviationAircraft and is the direct responsibility of Subcommittee F44.20 on Flight.
4.3 Longitudinal Control:
Current edition approved Dec. 1, 2015. Published February 2016. DOI: 10.1520/
F3173_F3173M-15.
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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
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F3173/F3173M−15
TABLE 1 Control Forces
whichever is lower without requiring the application of two-
Control Longitudinal Lateral Directional handed control forces exceeding those specified in Table 1.
(a) For temporary application:
4.3.2.6 With maximum takeoff power, landing gear
Stick 267 N [60 lbf] 133 N [30 lbf]
retracted, flaps in the takeoff position, and the airplane as
Wheel (two hands on rim)
...