206 

14 CFR Ch. I (1–1–14 Edition) 

§ 23.221 

(e) During the stall tests required by 

§ 23.203(a)(2), the stall warning must 
begin sufficiently in advance of the 
stall for the stall to be averted by pilot 
action taken after the stall warning 
first occurs. 

(f) For acrobatic category airplanes, 

an artificial stall warning may be mu-
table, provided that it is armed auto-
matically during takeoff and rearmed 
automatically in the approach configu-
ration. 

[Amdt. 23–7, 34 FR 13087, Aug. 13, 1969, as 
amended by Amdt. 23–45, 58 FR 42159, Aug. 6, 
1993; Amdt. 23–50, 61 FR 5191, Feb. 9, 1996] 

S

PINNING

 

§ 23.221

Spinning. 

(a) 

Normal category airplanes. A sin-

gle-engine, normal category airplane 
must be able to recover from a one- 
turn spin or a three-second spin, which-
ever takes longer, in not more than one 
additional turn after initiation of the 
first control action for recovery, or 
demonstrate compliance with the op-
tional spin resistant requirements of 
this section. 

(1) The following apply to one turn or 

three second spins: 

(i) For both the flaps-retracted and 

flaps-extended conditions, the applica-
ble airspeed limit and positive limit 
maneuvering load factor must not be 
exceeded; 

(ii) No control forces or char-

acteristic encountered during the spin 
or recovery may adversely affect 
prompt recovery; 

(iii) It must be impossible to obtain 

unrecoverable spins with any use of the 
flight or engine power controls either 
at the entry into or during the spin; 
and 

(iv) For the flaps-extended condition, 

the flaps may be retracted during the 
recovery but not before rotation has 
ceased. 

(2) At the applicant’s option, the air-

plane may be demonstrated to be spin 
resistant by the following: 

(i) During the stall maneuver con-

tained in § 23.201, the pitch control 
must be pulled back and held against 
the stop. Then, using ailerons and rud-
ders in the proper direction, it must be 
possible to maintain wings-level flight 
within 15 degrees of bank and to roll 

the airplane from a 30 degree bank in 
one direction to a 30 degree bank in the 
other direction; 

(ii) Reduce the airplane speed using 

pitch control at a rate of approxi-
mately one knot per second until the 
pitch control reaches the stop; then, 
with the pitch control pulled back and 
held against the stop, apply full rudder 
control in a manner to promote spin 
entry for a period of seven seconds or 
through a 360 degree heading change, 
whichever occurs first. If the 360 degree 
heading change is reached first, it must 
have taken no fewer than four seconds. 
This maneuver must be performed first 
with the ailerons in the neutral posi-
tion, and then with the ailerons de-
flected opposite the direction of turn in 
the most adverse manner. Power and 
airplane configuration must be set in 
accordance with § 23.201(e) without 
change during the maneuver. At the 
end of seven seconds or a 360 degree 
heading change, the airplane must re-
spond immediately and normally to 
primary flight controls applied to re-
gain coordinated, unstalled flight with-
out reversal of control effect and with-
out exceeding the temporary control 
forces specified by § 23.143(c); and 

(iii) Compliance with §§ 23.201 and 

23.203 must be demonstrated with the 
airplane in uncoordinated flight, cor-
responding to one ball width displace-
ment on a slip-skid indicator, unless 
one ball width displacement cannot be 
obtained with full rudder, in which 
case the demonstration must be with 
full rudder applied. 

(b) 

Utility category airplanes. A utility 

category airplane must meet the re-
quirements of paragraph (a) of this sec-
tion. In addition, the requirements of 
paragraph (c) of this section and 
§ 23.807(b)(7) must be met if approval for 
spinning is requested. 

(c) 

Acrobatic category airplanes. An ac-

robatic category airplane must meet 
the spin requirements of paragraph (a) 
of this section and § 23.807(b)(6). In addi-
tion, the following requirements must 
be met in each configuration for which 
approval for spinning is requested: 

(1) The airplane must recover from 

any point in a spin up to and including 
six turns, or any greater number of 
turns for which certification is re-
quested, in not more than one and one- 

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