Subject: STALL AND SPIN AWARENESS 

TRAINING

Date: 9/25/00

Initiated By: AFS-840

AC No: 61-67C

Change: 

1. PURPOSE. This advisory circular (AC) explains the stall and spin awareness training required 

under Title 14 of the Code of Federal Regulations (14 CFR) part 61 and offers guidance to flight 

instructors who provide that training. In addition, this AC informs pilots of the airworthiness 

standards for the type certification of normal, utility, and acrobatic category airplanes prescribed in 

14 CFR part 23, section 23.221, concerning spin maneuvers, and it emphasizes the importance of 

observing restrictions that prohibit the intentional spinning of certain airplanes. 

2. CANCELLATION. AC 61-67B, Stall and Spin Awareness Training, dated May 17, 1991, is 

canceled. 

3. RELATED READING MATERIAL.

a. Report No. FAA-RD-77-26, General Aviation Pilot Stall Awareness Training Study. This 

document may be purchased from the National Technical Information Service (NTIS), U.S. 

Department of Commerce, 5285 Port Royal Road, Springfield, Virginia 22161. Telephone orders: 

(800) 553-6847. NTIS identification number is ADA041310. 

b. The current version of AC 61-65, Certification: Pilots and Flight and Ground Instructors, 

may be obtained at no cost from: Department of Transportation, Subsequent Distribution Office, 

Ardmore East Business Center, 3341 Q 75th Ave., Landover, MD 20785. 

c. The current version of the following documents may be purchased from the Superintendent 

of Documents, U.S. Government Printing Office, Washington, DC 20402: 

(1) FAA-H-8083-1, Aircraft Weight and Balance Handbook. 

(2) FAA-H-8083-3, Airplane Flying Handbook. 

(3) FAA-H-8083-9, Aviation Instructor’s Handbook. 

(4) FAA-S-8081-3, Recreational Pilot - Practical Test Standards for Airplane and Rotorcraft. 

(5) FAA-S-8081-6, Flight Instructor - Practical Test Standards for Airplane (Single-Engine/ 

Multiengine). 

(6) FAA-S-8081-8, Flight Instructor - Practical Test Standards for Glider. 
AC 61-67C 9/25/00 

(7) FAA-S-8081-12, Commercial Pilot - Practical Test Standards for Airplane. 

(8) FAA-S-8081-14, Private Pilot - Practical Test Standards for Airplane. 

(9) FAA-S-8081-22 Private Pilot - Practical Test Standards for Glider. 

(10) FAA-S-8081-23 Commercial Pilot - Practical Test Standards for Glider. 

4. BACKGROUND.

a. In January 1980, the Federal Aviation Administration (FAA) announced its policy of 

incorporating the use of certain distractions during the performance of flight test maneuvers. This 

policy came about as a result of Report No. FAA-RD-77-26 which revealed that stall/spin related 

accidents accounted for approximately one-quarter of all fatal general aviation accidents. National 

Transportation Safety Board statistics indicate that most stall/spin accidents result when a pilot is 

distracted momentarily from the primary task of flying the aircraft. 

b. Changes to part 61, completed in 1991, included increased stall and spin awareness training

for recreational, private, and commercial pilot certificate applicants. The training is intended to 

emphasize recognition of situations that could lead to an inadvertent stall and/or spin by using

realistic distractions such as those suggested in Report No. FAA-RD-77-26 and incorporated into 

the performance of flight test maneuvers. Although the training is intended to emphasize stall and 

spin awareness and recovery techniques for all pilots, only flight instructor-airplane and flight 

instructor-glider candidates are required to demonstrate instructional proficiency in spin entry, spins, 

and spin recovery techniques as a requirement for certification. Since 1991, part 61 was extensively

updated in 1997. Additionally, since 1991, some sections of part 23 (Airworthiness Standards: 

Normal, Utility, Acrobatic, and Commuter Category Airplanes) that apply to spin requirements and 

placards have changed. This AC incorporates those changes. 

5. COMMENTS INVITED. Comments regarding this publication should be directed to: 

Federal Aviation Administration 

General Aviation and Commercial Division, AFS-800 

800 Independence Ave., SW. 

Washington, DC 20591 

Every comment will not necessarily generate a direct acknowledgment to the commenter. 

Comments received will be considered in the development of upcoming AC revisions or other 

related technical material. 

6. INTERNET. AC 61-67C can be accessed on the Internet at Uniform Resource Locator address 

http://www.faa.gov/avr/afs/acs/ac-idx.htm. 

/s/ 

L. Nicholas Lacey

Director, Flight Standards Service 

Page Par 3 ii
9/25/00 AC 61-67C 

CONTENTS 

CHAPTER 1. GROUND TRAINING: STALL AND SPIN AWARENESS

Paragraph Page

100. Stall/Spin Effects and Definitions.............................................................................. 1 

101. Distractions................................................................................................................. 3 

102. Wing Contamination Effects on Stall Warning, Stall Speed, and 

Poststall Recovery..................................................................................................... 3 

103. Stall Recognition ........................................................................................................ 4 

104. Types of Stalls............................................................................................................ 4 

105. Stall Recovery ............................................................................................................ 5

106. Secondary Stalls......................................................................................................... 5 

107. Spins........................................................................................................................... 5 

108. Weight and Balance.................................................................................................... 5 

109. Primary Cause ............................................................................................................ 6 

110. Types of Spins............................................................................................................ 6

111. Spin Recovery ............................................................................................................ 6 

112. Spiral Mode Recovery................................................................................................ 7 

113. thru 199. Reserved...................................................................................................... 7

CHAPTER 2. FLIGHT TRAINING: STALLS

200. Stall Training.............................................................................................................. 9 

201. thru 299. Reserved.................................................................................................... 12 

CHAPTER 3. FLIGHT TRAINING: SPINS

300. Spin Training............................................................................................................ 13 

301. Spin Training and Parachutes................................................................................... 14 

302. thru 399. Reserved.................................................................................................... 14 

CHAPTER 4. AIRWORTHINESS STANDARDS

400. Operating Limitations............................................................................................... 15 

401. Placards .................................................................................................................... 16 

402. Pilot Awareness........................................................................................................ 16

403. thru 499. Reserved.................................................................................................... 16 

Page iii (and iv)

9/25/00 AC 61-67C 

CHAPTER 1. GROUND TRAINING: STALL AND SPIN AWARENESS

100. STALL/SPIN EFFECTS AND DEFINITIONS. A stall is a loss of lift and increase in drag

that occurs when an aircraft is flown at an angle of attack (AOA) greater than the angle for 

maximum lift. If recovery from a stall is not effected in a timely and appropriate manner by

reducing the AOA, a secondary stall and/or a spin may result. All spins are preceded by a stall on at 

least part of the wing. The angle of the relative wind is determined primarily by the aircraft's

airspeed and attitude. Other factors are considered, such as aircraft weight, center of gravity, 

configuration, and the amount of acceleration used in a turn. The speed at which the critical angle 

of the relative wind is exceeded is the stall speed. Stall speeds are listed in the Airplane Flight

Manual (AFM) or the Pilot Operating Handbook (POH) and pertain to certain conditions or aircraft 

configurations, e.g., landing configuration. Other specific operational speeds are calculated based 

upon the aircraft's stall speed in the landing configuration. Airspeed values specified in the AFM or 

POH may vary under different circumstances. Factors such as weight, center of gravity, altitude, 

temperature, turbulence, and the presence of snow, ice, or frost on the wings will affect an aircraft's

stall speed. To thoroughly understand the stall/spin phenomenon, some basic factors affecting

aircraft aerodynamics and flight should be reviewed with particular emphasis on their relation to 

stall speeds. (This AC is principally concerned with and discusses airplanes. However, much of the 

information is also applicable to gliders.) The following terms are defined as they relate to 

stalls/spins. 

a. Angle of Attack. AOA is the angle at which the chord line of the wing meets the relative 

wind. The chord line is a straight line drawn through the profile of the wing connecting the 

extremities of the leading edge and trailing edge. The AOA must be small enough to allow attached 

airflow over and under the airfoil to produce lift. A change in AOA will affect the amount of lift 

that is produced. Consequently, AOA is an element of lift. An excessive AOA will disrupt the flow 

of air over the airfoil. If the AOA is not reduced, a section of the airfoil will reach its critical AOA, 

lose lift, and stall. Exceeding the critical AOA for a particular airfoil section will always result in a 

stall of that section. 

b. Airspeed. Airspeed is controlled primarily by the elevator or longitudinal control position 

for a given configuration and power. Conversely, airspeed is controlled by power at a given 

configuration and AOA. If an airplane's speed is too slow, the AOA required for level flight will be 

so large that the air can no longer follow the upper curvature of the wing. The result is a separation 

of airflow from the wing, loss of lift, a large increase in drag, and eventually a stall if the AOA is 

not reduced. The stall is the result of excessive AOA - not insufficient airspeed. For example, at a 

60° banked turn in level coordinated flight, the load factor is 2 G's and the stall speed increases 

40 percent over the straight and level stall speed. A STALL CAN OCCUR AT ANY AIRSPEED, 

IN ANY ATTITUDE, AT ANY POWER SETTING. 

c. Configuration. Flaps, landing gear, and other configuring devices can affect an airplane's

stall speed. Extension of flaps and/or landing gear in flight will increase drag. Flap extension will 

generally increase the lifting ability of the wings, thus reducing the airplane's stall speed. The effect

of flaps on an airplane's stall speed can be seen by markings on the airplane's airspeed indicator, 

where the lower airspeed limit of the white arc (power-off stall speed with gear and flaps in the

landing configuration) is less than the lower airspeed limit of the green arc (power-off stall speed in 

the clean configuration).

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d. VSO. VSO means the stall speed or the minimum steady flight speed in the landing

configuration. 

e. VS1. VS1 means the stall speed or the minimum steady flight speed obtained in a specified 

configuration. 

f. VA. VA is the design maneuvering speed. Do not use full or abrupt control movements at or 

above this speed. It is possible to exceed the airplane structural limits at or above VA. 

g. Load Factor. Load factor is the ratio of the lifting force produced by the wings to the actual 

weight of the airplane and its contents. Load factors are usually expressed in terms of "G." The 

aircraft's stall speed increases in proportion to the square root of the load factor. For example, an 

airplane that has a normal unaccelerated stall speed of 45 knots can be stalled at 90 knots when 

subjected to a load factor of 4 G's. The possibility of inadvertently stalling the airplane by

increasing the load factor (i.e., by putting the airplane in a steep turn or spiral) is much greater than

in normal cruise flight. A stall entered from straight and level flight or from an unaccelerated 

straight climb will not produce additional load factors. In a constant rate turn, increased load factors 

will cause an airplane's stall speed to increase as the angle of bank increases. Excessively steep 

banks should be avoided because the airplane will stall at a much higher speed. If the aircraft 

exceeds maneuvering speed, structural damage to the aircraft may result before it stalls. If the nose 

falls during a steep turn, the pilot might attempt to raise it to the level flight attitude without 

shallowing the bank. This situation tightens the turn and can lead to a diving spiral. A feeling of 

weightlessness will result if a stall recovery is performed by abruptly pushing the elevator control 

forward, which will reduce the up load on the wings. Recoveries from stalls and spins involve a 

tradeoff between loss of altitude (and an increase in airspeed) and an increase in load factor in the

pullup. However, recovery from the dive following spin recovery generally causes higher airspeeds 

and consequently higher load factors than stall recoveries due to the much lower position of the

nose. Significant load factor increases are sometimes induced during pullup after recovery from a 

stall or spin. It should be noted that structural damage can result from the high load factors that 

could be imposed on the aircraft by intentional stalls practiced above the airplane's design

maneuvering speed. 

h. Center of Gravity (CG). The CG location has a direct effect on the effective lift and AOA 

of the wing, the amount and direction of force on the tail, and the degree of stabilizer deflection 

needed to supply the proper tail force for equilibrium. The CG position, therefore, has a significant 

effect on stability and stall/spin recovery. As the CG is moved aft, the amount of elevator deflection 

needed to stall the airplane at a given load factor will be reduced. An increased AOA will be 

achieved with less elevator control force. This could make the entry into inadvertent stalls easier,

and during the subsequent recovery, it would be easier to generate higher load factors due to the 

reduced elevator control forces. In an airplane with an extremely aft CG, very light back elevator 

control forces may lead to inadvertent stall entries and if a spin is entered, the balance of forces on 

the airplane may result in a flat spin. Recovery from a flat spin is often impossible. A forward CG 

location will often cause the stalling AOA to be reached at a higher airspeed. Increased back 

elevator control force is generally required with a forward CG location. 

i. Weight. Although the distribution of weight has the most direct effect on stability, increased 

gross weight can also have an effect on an aircraft's flight characteristics, regardless of the CG 

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9/25/00 AC 61-67C 

position. As the weight of the airplane is increased, the stall speed increases. The increased weight 

requires a higher AOA to produce additional lift to support the weight. 

j. Altitude and Temperature. Altitude has little or no effect on an airplane's indicated stall 

speed. Thinner air at higher altitudes will result in decreased aircraft performance and a higher true

airspeed for a given indicated airspeed. Higher than standard temperatures will also contribute to 

increased true airspeed for a given indicated airspeed. However, the higher true airspeed has no 

effect on indicated approach or stall speeds. The manufacturer's recommended indicated airspeeds 

should therefore be maintained during the landing approach, regardless of the elevation or the 

density altitude at the airport of landing. 

k. Snow, Ice, or Frost on the Wings. Even a small accumulation of snow, ice, or frost on an 

aircraft's surface can cause an increase in that aircraft's stall speed. Such accumulation changes the 

shape of the wing, disrupting the smooth flow of air over the surface and, consequently, increasing

drag and decreasing lift. Flight should not be attempted when snow, ice, or frost have accumulated 

on the aircraft surfaces. 

l. Turbulence. Turbulence can cause an aircraft to stall at a significantly higher airspeed than 

in stable conditions. A vertical gust or windshear can cause a sudden change in the relative wind, 

and result in an abrupt increase in AOA. Although a gust may not be maintained long enough for a 

stall to develop, the aircraft may stall while the pilot is attempting to control the flightpath, 

particularly during an approach in gusty conditions. When flying in moderate to severe turbulence 

or strong crosswinds, a higher than normal approach speed should be maintained. In cruise flight in 

moderate or severe turbulence, an airspeed well above the indicated stall speed and below 

maneuvering speed should be used. It should be noted that maneuvering speed is lower at a lower 

weight. 

101. DISTRACTIONS. Stalls resulting from improper airspeed management are most likely to 

occur when the pilot is distracted by one or more other tasks, such as locating a checklist or 

attempting a restart after an engine failure; flying a traffic pattern on a windy day; reading a chart or

making fuel and/or distance calculations; or attempting to retrieve items from the floor, back seat, or

glove compartment. Pilots at all skill levels should be aware of the increased risk of entering into an 

inadvertent stall or spin while performing tasks that are secondary to controlling the aircraft. 

102. WING CONTAMINATION EFFECTS ON STALL WARNING, STALL SPEED, AND 

POSTSTALL RECOVERY. Stall speeds and stall characteristics are usually determined with 

uncontaminated airfoils. For airplanes that are certified for flight in icing conditions, ice shapes

may have also been considered for their effects on aircraft. However, not all possible icing

conditions and configurations can be tested. Further, any contamination or alteration of the leading

edge caused by factors such as mud, insect residue, or ice can significantly alter the aerodynamic 

characteristics of the wing, but it is icing that is of primary concern. 

a. In some icing conditions there are adverse changes to the stall speed, stall characteristics, 

performance, and handling characteristics of the airplane. These adverse changes are potentially

hazardous for several reasons. First, aerodynamic stall may occur with little or none of the usual 

cues in advance of the stall or at the occurrence of stall. These cues include airframe or control

surface buffet, reduced control effectiveness, and activation of the stall warning horn, stick shaker, 

and stick pusher. Next, because of high drag on unprotected surfaces and residual ice on protected 

Par 100 Page 3
AC 61-67C 9/25/00 

surfaces, there may be insufficient power or thrust to increase speed while holding constant altitude 

to reduce the AOA. Finally, poststall recovery of a contaminated airplane may be complicated by

gross changes in control effectiveness, airplane response characteristics, and abnormal control 

forces. As a result of these factors, large losses in altitude can occur during recovery. 

b. Accordingly, in these conditions, a prompt control input to decrease pitch attitude to recover 

lateral control, with aggressive power application ensures the most rapid recovery with minimum 

altitude loss. The AOA must be reduced immediately as the wing, or part of the wing is already

stalled and no margin remains to allow holding altitude/ attitude as power is applied. The pilot 

should note the AOA (or airspeed) at upset and not approach that AOA (airspeed) during the 

recovery or another upset may occur. This AOA may be well below the normal stall AOA (below 

shaker AOA) and the airspeed may be well above normal stall airspeed. Stall speed increases as 

high as 50 knots have been observed in post upset data review. 

c. Further complications involve use of the autopilot. The autopilot may apply control inputs 

that will mask detection of some of these tactile cues by the pilot or attempt to control the airplane

in the stall. Sudden autopilot self-disconnect with control surfaces trimmed into extreme positions 

or with controls trimmed into uncoordinated flight will complicate poststall recovery and may lead

to a spin or spiral. 

103. STALL RECOGNITION. There are several ways to recognize that a stall is impending

before it actually occurs. When one or more of these indicators is noted, initiation of a recovery

should be instinctive (unless a full stall is being practiced intentionally from an altitude that allows 

recovery at least 1,500 feet above ground level (AGL) for single-engine airplanes and 3,000 feet 

AGL for multiengine airplanes). One indication of a stall is a mushy feeling in the flight controls 

and less control effect as the aircraft's speed is reduced. This reduction in control effectiveness is 

attributed in part to reduced airflow over the flight control surfaces. In fixed pitch propeller 

airplanes, a loss of revolutions per minute (RPM) may be evident when approaching a stall in

power-on conditions. For both airplanes and gliders, a reduction in the sound of air flowing along

the fuselage is usually evident. Just before the stall occurs, buffeting, uncontrollable pitching, or 

vibrations may begin. Many aircraft are equipped with stall warning devices that will alert the pilot 

4 to 8 knots prior to the onset of a stall. Finally, kinesthesia (the sensing of changes in direction or 

speed of motion), when properly learned and developed, will warn the pilot of a decrease in speed or

the beginning of a mushing of the aircraft. These preliminary indications serve as a warning to the

pilot to increase airspeed by adding power, lowering the nose, and/or decreasing the angle of bank. 

104. TYPES OF STALLS. Stalls can be practiced both with and without power. Stalls should be 

practiced to familiarize the student with the aircraft's particular stall characteristics without putting

the aircraft into a potentially dangerous condition. In multiengine airplanes, single-engine stalls 

must be avoided. Descriptions of some different types of stalls follows: 

a. Power-off stalls (also known as approach-to-landing stalls) are practiced to simulate normal 

approach-to-landing conditions and configuration. Many stall/spin accidents have occurred in these 

power-off situations, such as crossed control turns from base leg to final approach (resulting in a

skidding or slipping turn); attempting to recover from a high sink rate on final approach by using

only an increased pitch attitude; and improper airspeed control on final approach or in other

segments of the traffic pattern. 

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9/25/00 AC 61-67C 

b. Power-on stalls (also known as departure stalls) are practiced to simulate takeoff and 

climbout conditions and configuration. Many stall/spin accidents have occurred during these phases 

of flight, particularly during go-arounds. A causal factor in such accidents has been the pilot's 

failure to maintain positive control due to a nose-high trim setting or premature flap retraction. 

Failure to maintain positive control during short field takeoffs has also been a causal accident factor. 

c. Accelerated stalls can occur at higher-than-normal airspeeds due to abrupt and/or excessive 

control applications. These stalls may occur in steep turns, pullups, or other abrupt changes in 

flightpath. Accelerated stalls usually are more severe than unaccelerated stalls and are often 

unexpected because they occur at higher-than-normal airspeeds. 

105. STALL RECOVERY. The key factor in recovering from a stall is regaining positive control 

of the aircraft by reducing the AOA. At the first indication of a stall, the aircraft AOA must be 

decreased to allow the wings to regain lift. Every aircraft in upright flight may require a different 

amount of forward pressure or relaxation of elevator back pressure to regain lift. It should be noted 

that too much forward pressure can hinder recovery by imposing a negative load on the wing. The 

next step in recovering from a stall is to smoothly apply maximum allowable power (if applicable)

to increase the airspeed and to minimize the loss of altitude. Certain high performance airplanes 

may require only an increase in thrust and relaxation of the back pressure on the yoke to effect 

recovery. As airspeed increases and the recovery is completed, power should be adjusted to return 

the airplane to the desired flight condition. Straight and level flight should be established with full 

coordinated use of the controls. The airspeed indicator or tachometer, if installed, should never be 

allowed to reach their high speed red lines at anytime during a practice stall. 

106. SECONDARY STALLS. If recovery from a stall is not made properly, a secondary stall or a 

spin may result. A secondary stall is caused by attempting to hasten the completion of a stall 

recovery before the aircraft has regained sufficient flying speed. When this stall occurs, appropriate 

forward pressure or the relaxation of back elevator pressure should again be performed just as in a 

normal stall recovery. When sufficient airspeed has been regained, the aircraft can then be returned 

to straight and level flight. 

107. SPINS. A spin in a small airplane or glider is a controlled (recoverable) or uncontrolled 

(possibly unrecoverable) maneuver in which the airplane or glider descends in a helical path while 

flying at an AOA greater than the critical AOA. Spins result from aggravated stalls in either a slip 

or a skid. If a stall does not occur, a spin cannot occur. In a stall, one wing will often drop before 

the other and the nose will yaw in the direction of the low wing.

108. WEIGHT AND BALANCE. Minor weight or balance changes can affect an aircraft's spin

characteristics. For example, the addition of a suitcase in the aft baggage compartment will affect

the weight and balance of the aircraft. An aircraft that may be difficult to spin intentionally in the

utility category (restricted aft CG and reduced weight) could have less resistance to spin entry in the

normal category (less restricted aft CG and increased weight) due to its ability to generate a higher

AOA and increased load factor. Furthermore, an aircraft that is approved for spins in the utility

category, but loaded in the normal category, may not be recoverable from a spin that is allowed to 

progress beyond one turn or 3-second spin, whichever is longer (refer to section 23.221(a)). 

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109. PRIMARY CAUSE. The primary cause of an inadvertent spin is exceeding the critical AOA 

while applying excessive or insufficient rudder and, to a lesser extent, aileron. Insufficient or 

excessive control inputs to correct for Power Factor (PF), or asymmetric propeller loading, could 

aggravate the precipitation of a spin. At a high AOA the downward moving blade, which is 

normally on the right side of the propeller arc, has a higher AOA and therefore higher thrust than the 

upward moving blade on the left. This results in a tendency for the airplane to yaw around the 

vertical axis to the left. If insufficient or excessive rudder correction is applied to counteract PF, 

uncoordinated flight may result. A classic situation where PF could play an important role in a 

stall/spin accident is during a go-around or short field takeoff where the airplane is at a high pitch 

attitude, high power setting, and low airspeed. In an uncoordinated maneuver, the pitot/static

instruments, especially the altimeter and airspeed indicator, are unreliable due to the uneven 

distribution of air pressure over the fuselage. The pilot may not be aware that a critical AOA is 

approaching until the stall warning device activates. If a stall recovery is not promptly initiated, the

airplane is more likely to enter an inadvertent spin. For example, stall/spin accidents have occurred 

during a turn from base to final because the pilot attempted to rudder the airplane around (skid) so 

as not to overshoot the runway nor use excessive bank angle in the traffic pattern. The spin that 

occurs from cross controlling an aircraft usually results in rotation in the direction of the rudder 

being applied, regardless of which wingtip is raised. In a skidding turn, where both aileron and 

rudder are applied in the same direction, rotation will be in the direction the controls are applied. 

However, in a slipping turn, where opposite aileron is held against the rudder, the resultant spin will 

usually occur in the direction opposite the aileron that is being applied. 

110. TYPES OF SPINS.

a. An incipient spin is that portion of a spin from the time the airplane stalls and rotation starts, 

until the spin becomes fully developed. Incipient spins that are not allowed to develop into a steady

state spin are commonly used as an introduction to spin training and recovery techniques. 

b. A fully developed, steady state spin occurs when the aircraft angular rotation rate, airspeed, 

and vertical speed are stabilized from turn-to-turn in a flightpath that is close to vertical. 

c. A flat spin is characterized by a near level pitch and roll attitude with the spin axis near the

CG of the airplane. Recovery from a flat spin may be extremely difficult and, in some cases, 

impossible. 

111. SPIN RECOVERY. Before flying any aircraft, in which spins are to be conducted, the pilot 

should be familiar with the operating characteristics and standard operating procedures, including

spin recovery techniques, specified in the approved AFM or POH. The first step in recovering from 

an upright spin is to close the throttle completely to eliminate power and minimize the loss of

altitude. If the particular aircraft spin recovery techniques are not known, the next step is to 

neutralize the ailerons, determine the direction of the turn, and apply full opposite rudder. When the 

rotation slows, briskly move the elevator control forward to approximately the neutral position. 

Some aircraft require merely a relaxation of back pressure; others require full forward elevator 

control pressure. Forward movement of the elevator control will decrease the AOA. Once the stall 

is broken, the spinning will stop. Neutralize the rudder when the spinning stops to avoid entering a 

spin in the opposite direction. When the rudder is neutralized, gradually apply enough aft elevator 

pressure to return to level flight. Too much or abrupt aft elevator pressure and/or application of 

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rudder and ailerons during the recovery can result in a secondary stall and possibly another spin. If

the spin is being performed in an airplane, the engine will sometimes stop developing power due to 

centrifugal force acting on the fuel in the airplane's tanks causing fuel interruption. It is, therefore, 

recommended to assume that power is not available when practicing spin recovery. As a rough 

estimate, an altitude loss of approximately 500 feet per each 3-second turn can be expected in most 

small aircraft in which spins are authorized. Greater losses can be expected at higher density

altitudes. 

112. SPIRAL MODE RECOVERY. The spiral mode is an autorotation mode similar to a spin. 

The center of rotation is close to the centerline of the airplane but the airplane is not stalled. Many

airplanes and gliders will not spin at forward CG locations but will spiral. Many airplanes will enter

a spin but the spin will become more vertical and degenerate into a spiral. It is important to note

that when the spin transitions into the spiral the airspeed will increase as the nose goes down to near

vertical. The side forces on the airplane build very rapidly and recovery must be effected 

immediately before exceeding the structural limits of the airplane. Release the back pressure on the 

stick (yoke), neutralize the rudder and recover from the steep dive. As in the spin recovery, avoid 

abrupt or excessive elevator inputs that could lead to a secondary stall. 

113. - 199. RESERVED. 

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CHAPTER 2. FLIGHT TRAINING: STALLS

200. STALL TRAINING. Flight instructor-airplane and flight instructor-glider applicants must be

able to give stall training. The flight instructor should emphasize that techniques and procedures for 

each aircraft may differ and that pilots should be aware of the flight characteristics of each aircraft 

flown. Because of the possible catastrophic consequences, single-engine stalls should not be 

demonstrated or practiced in multiengine airplanes. Airplanes with normally aspirated engines will 

lose power as altitude increases because of the reduced density of the air entering the induction 

system of the engines. This loss of power will result in a VMC lower than the stall speed at higher 

altitudes. (VMC is the minimum control speed with the critical engine inoperative.) Also, some 

airplanes have such an effective rudder that even at sea level VMC is lower than stall speed. For

these airplanes, demonstration of loss of directional control may be safely conducted by limiting

rudder travel to simulate maximum rudder available rudder. Limiting rudder travel should be 

accomplished well above the power-off stall speed (approximately 20 knots). This will avoid the 

hazards of stalling one wing with the maximum allowable power applied to the engine on the other

wing. The flight training required by part 61 does not entail the actual practicing of spins for other

than flight instructor-airplane and flight instructor-glider applicants, but emphasizes stall and spin 

avoidance. The most effective training method contained in Report No. FAA-RD-77-26 is the 

simulation of scenarios that can lead to inadvertent stalls by creating distractions while the student is 

practicing certain maneuvers. Stall demonstrations and practice, including maneuvering during

slow flight and other maneuvers with distractions that can lead to inadvertent stalls, should be 

conducted at a sufficient altitude to enable recovery above 1,500 feet AGL in single-engine 

airplanes and 3,000 feet AGL in multiengine airplanes. The following training elements are based 

on Report No. FAA-RD-77-26: 

a. Stall Avoidance Practice at Slow Airspeeds.

(1) Assign a heading and an altitude. Have the student reduce power and slow to an

airspeed just above the stall speed, using trim as necessary. 

(2) Have the student maintain heading and altitude with the stall warning device activated. 

(3) Demonstrate the effect of elevator trim (use neutral and full noseup settings) and rudder 

trim, if available.

(4) Note the left turning tendency and rudder effectiveness for lateral/directional control. 

(5) Emphasize how right rudder pressure is necessary to center the ball indicator and 

maintain heading.

(6) Release the rudder and advise the student to observe the left yaw. 

(7) Adverse yaw demonstration. While at a low airspeed, have the student enter left and 

right turns without using rudder pedals. 

(8) Have the student practice turns, climbs, and descents at low airspeeds. 

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(9) Demonstrate the proper flap extension and retraction procedures while in level flight to 

avoid a stall at low airspeeds. Note the change in stall speeds with flaps extended and retracted. 

(10) Realistic distractions at low airspeeds. Give the student a task to perform while flying

at a low airspeed. Instruct the student to divide his/her attention between the task and flying the 

aircraft to maintain control and avoid a stall. The following distractions can be used: 

(a) Drop a pencil. Ask the student to pick it up. 

(b) Ask the student to determine a heading to an airport using a chart.

(c) Ask the student to reset the clock to Universal Coordinated Time. 

(d) Ask the student to get something from the back seat. 

(e) Ask the student to read the outside air temperature. 

(f) Ask the student to call the Flight Service Station (FSS) for weather information. 

(g) Ask the student to compute true airspeed with a flight computer. 

(h) Ask the student to identify terrain or objects on the ground. 

(i) Ask the student to identify a field suitable for a forced landing. 

(j) Have the student climb 200 feet and maintain altitude, then descend 200 feet and 

maintain altitude. 

(k) Have the student reverse course after a series of S-turns. 

(11) Flight at low airspeeds with the airspeed indicator covered. Use various flap settings

and distractions. 

b. Power-On (Departure) Stall.

(1) At a safe altitude, have the student attempt coordinated power-on (departure) stalls 

straight ahead and in turns. Emphasize how these stalls could occur during takeoff. 

(2) Ask the student to demonstrate a power-on (departure) stall and distract him/her just 

before the stall occurs. Explain any effects the distraction may have had on the stall or recovery. 

c. Engine Failure in a Climb Followed by a Gliding Turn. This demonstration will show the

student how much altitude the airplane loses following a power failure after takeoff and during a

turn back to the runway and why returning to the airport after losing an engine is not a 

recommended procedure. This can be performed using either a medium or steep bank in the turn, 

but emphasis should be given to stall avoidance. 

(1) Set up best rate of climb (VY). Directly below you there should be a straight line 

landmark (i.e., road or power line) parallel to your flightpath. 

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(2) Reduce power smoothly to idle as the airplane passes through a cardinal altitude. 

(3) Lower the nose to maintain the best glide speed and make a 260° turn at the best glide 

speed. It should be emphasized that this turn should be into the wind (if there is a crosswind). 

(4) Re-intercept the final your outbound course (over the landmark you chose) inbound with 

an 80° turn in the opposite direction. 

(5) Point out the altitude loss and emphasize how rapidly airspeed decreases following a

power failure in a climb attitude. 

NOTE: Depending on winds, length of runway, and altitude the 260/80° turns may 

need to be modified (250/70° or 270/90°) to meet the existing situation. 

d. Cross Controlled Stalls in Gliding Turns. Perform stalls in gliding turns to simulate turns 

from base to final. Perform the stalls from a properly coordinated turn, a slipping turn, and a 

skidding turn. Explain the difference between slipping and skidding turns. Explain the ball 

indicator position in each turn and the aircraft behavior in each of the stalls. 

e. Power-Off (Approach-To-Landing) Stalls.

(1) Have the student perform a full-flap, gear extended, power-off stall with the correct 

recovery and cleanup procedures. Note the loss of altitude. 

(2) Have the student repeat this procedure and distract the student during the stall and 

recovery and note the effect of the distraction. Show how errors in flap retraction procedure can 

cause a secondary stall. 

f. Stalls During Go-Arounds. 

(1) Have the student perform a full-flap, gear extended, power-off stall, then recover and 

attempt to climb with flaps extended. If a higher than normal climb pitch attitude is held, a

secondary stall will occur. (In some airplanes, a stall will occur if a normal climb pitch attitude is 

held.) 

(2) Have the student perform a full-flap, gear extended, power-off stall, then recover and 

retract the flaps rapidly as a higher than normal climb pitch attitude is held. A secondary stall or 

settling with a loss of altitude may result. 

g. Elevator Trim Stall.

(1) Have the student place the airplane in a landing approach configuration, in a trimmed 

descent.

(2) After the descent is established, initiate a go-around by adding full power, holding only

light elevator and right rudder pressure. 

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(3) Allow the nose to pitch up and torque to swerve the airplane left. At the first indication 

of a stall, recover to a normal climbing pitch attitude. 

(4) Emphasize the importance of correct attitude control, application of control pressures, 

and proper trim during go-arounds. 

201. - 299. RESERVED. 

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CHAPTER 3. FLIGHT TRAINING: SPINS

300. SPIN TRAINING. Spin training is required for flight instructor-airplane and flight 

instructor-glider applicants only. Upon completion of the training, the applicant's log book or 

training record should be endorsed by the flight instructor who provided the training. A sample 

endorsement of spin training for flight instructor applicants is available in the current edition of 

AC 61-65. 

a. Spin training must be accomplished in an aircraft that is approved for spins. Before 

practicing intentional spins, the AFM or POH should be consulted for the proper entry and recovery

techniques. 

b. The training should begin by practicing both power-on and power-off stalls to familiarize the 

applicant with the aircraft's stall characteristics. Spin avoidance, incipient spins, actual spin entry,

spin, and spin recovery techniques should be practiced from an altitude above 3,500 feet AGL. 

c. Spin avoidance training should consist of stalls and maneuvering during slow flight using

realistic distractions such as those listed in chapter 2. Performance is considered unsatisfactory if it 

becomes necessary for the instructor to take control of the aircraft to avoid a fully developed spin. 

d. Incipient spins should be practiced to train the instructor applicant to recover from a student's

poorly performed stall or unusual attitude that could lead to a spin. Configure the aircraft for a 

power-on or power-off stall, and continue to apply back elevator pressure. As the stall occurs, apply

right or left rudder and allow the nose to yaw toward the stalled wing. Release the spin inducing

controls and recover as the spin begins by applying opposite rudder and forward elevator pressure. 

The instructor should discuss control application in the recovery. 

e. Spin entry, spin, and spin recovery should be demonstrated by the instructor and repeated in 

both directions by the applicant. 

(1) Apply the entry procedure for a power-off stall. As the airplane approaches a stall,

smoothly apply full rudder in the direction of desired spin rotation and continue to apply back 

elevator to the limit of travel. The ailerons should be neutral. 

(2) Allow the spin to develop, and be fully recovered no later than one full turn. Observe the 

airspeed indicator during the spin and subsequent recovery to ensure that it does not reach the red 

line (VNE). 

(3) Follow the recovery procedures recommended by the manufacturer in the AFM or POH. 

In most aircraft, spin recovery techniques consist of retarding power (if in a powered aircraft), 

applying opposite rudder to slow the rotation, neutralizing the ailerons, applying positive forward 

elevator movement to break the stall, neutralizing the rudder as the spinning stops, and returning to 

level flight. 

f. During spin training if a spin is not fully developed, the aircraft may instead go into a spiral. 

A spiral may be recognized by a rapidly increasing airspeed after the attempted spin entry. (In an 

actual spin, the airspeed normally stabilizes below stall speed.) The pilot must recognize a spiral

and initiate immediate recovery to prevent exceeding structural limits of the airplane.

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301. SPIN TRAINING AND PARACHUTES. Part 91, section 91.307(c), prohibits the pilot of a 

civil aircraft from executing any intentional maneuver that exceeds 60° of bank relative to the 

horizon, or exceeds 30° noseup or nosedown attitude relative to the horizon, unless an approved 

parachute is worn by each occupant (other than a crewmember). Section 91.307(d) states, in 

pertinent part, that section 91.307(c) does not apply to flight tests for a pilot certificate or rating; or 

spins and other flight maneuvers required by the regulations for any certificate or rating when given 

by a certified flight instructor (CFI) or an airline transport pilot (ATP) instructing in accordance 

with section 61.167. 

a. Section 61.183(i) requires an applicant for a flight instructor certificate or rating to receive 

flight training in stall awareness, spin entry, spins, and spin recovery procedures. The applicant 

must also possess and demonstrate instructional proficiency in these areas to receive the certificate 

or rating.

b. Because spin entry, spins, and spin recovery are required for a flight instructor certificate or 

rating, a person receiving instruction from a CFI (or an ATP instructing in accordance with

section 61.167) need not wear an approved parachute while instruction is being provided in these 

maneuvers. This provision applies regardless of the certificate or rating for which the person is 

receiving training and also if the person is receiving instruction that is not being provided for the 

purpose of obtaining any additional certificate or rating. The instructor providing the training is also 

not required to wear an approved parachute while providing this flight training. 

c. Additionally, it should be noted that any pilot or required crewmember may perform a 

maneuver that exceeds the limits prescribed in section 91.307(c) without wearing an approved 

parachute, provided there are no other occupants in the aircraft or the other occupants are wearing

approved parachutes. 

302. - 399. RESERVED. 

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CHAPTER 4. AIRWORTHINESS STANDARDS

400. OPERATING LIMITATIONS. Operating limitations are imposed for the safety of pilots 

and their passengers. Operations contrary to these restrictions are a serious compromise of safety. 

It is, therefore, most important that all pilots and flight and ground instructors, and pilot examiners 

apply the following information on spinning to pilot training and flight operations. 

a. Normal Category. Normal category airplanes are not approved for the performance of 

acrobatic maneuvers, including spins, and are placarded against intentional spins. However, to 

provide a margin of safety when recovery from a stall is delayed, normal category airplanes are 

tested during certification and must be able to recover from a one turn spin or a 3-second spin, 

whichever takes longer, in not more than one additional turn with the controls used in the manner 

normally used for recovery or demonstrate the airplane’s resistance to spins. In addition for 

airplanes demonstrating compliance with one turn or 3-second requirements: 

(1) For both the flaps retracted and flaps extended conditions, the applicable airspeed limit 

and positive limit maneuvering load factor must not be exceeded; 

(2) No control forces or characteristic encountered during the spin of the recovery may

adversely affect prompt recovery; 

(3) It must be impossible to obtain uncontrollable spins with any use of the flight or engine 

power controls either at the entry or during the spin; and 

(4) For the flaps extended condition, the flaps may be retracted during recovery but not 

before the rotation has ceased. 

NOTE: Since airplanes certificated in the normal category have not been tested

for more than a one turn or 3-second spin, their performance characteristics 

beyond these limits are unknown. This is the reason they are placarded against 

intentional spins.

b. Acrobatic Category. An acrobatic category airplane must meet the spin requirements for 

normal category aircraft and the following additional requirements: 

(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 requested, in not more than one and one-half 

additional turns after initiation of the first control action for recovery. However, beyond three turns, 

the spin may be discontinued if spiral characteristics appear. 

(2) The applicable airspeed limits and limit maneuvering load factor must not be exceeded. 

For the flaps extended configuration for which approval is requested, the flaps must not be retracted 

during recovery. 

(3) It must be impossible to obtain uncontrollable spins with any use of the flight or engine 

power controls either at the entry or during the spin. 

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Page 16 Par 400 

(4) There must be no characteristics during the spin (such as excessive rates of rotation or 

extreme oscillatory motion) that might prevent a successful recovery due to disorientation or 

incapacitation of the pilot. 

NOTE: Unless a greater number of turns are requested for certification 

acrobatic category airplanes have not been tested for more than six turns. The 

recovery characteristics for additional turns are unknown.

c. Utility Category. A utility category airplane must meet the spinning requirements for both 

normal and acrobatic category airplanes and the applicable emergency exit requirements of 

section 23.807 if the aircraft is approved for spins. 

401. PLACARDS. Under section 23.1567, all airplanes type certificated under part 23 must have a 

flight maneuver placard containing the following information: 

a. For normal category airplanes, there must be a placard in front of and in clear view of the 

pilot stating: "No acrobatic maneuvers, including spins, approved." 

b. For utility category airplanes that meet the spin requirements, there must be a placard in front 

of and in clear view of the pilot stating: "Acrobatic maneuvers are limited to the following (list 

approved maneuvers and the recommended entry speed for each). 

c. For utility category airplanes that do not meet the spin requirements for acrobatic category 

airplanes, there must be an additional placard in clear view of the pilot stating: "Spins Prohibited." 

d. For acrobatic category airplanes, there must be a placard in clear view of the pilot listing the 

approved acrobatic maneuvers and the recommended entry airspeed for each. If inverted flight 

maneuvers are not approved, the placard must include a notation to this effect. 

e. For acrobatic category airplanes and utility category airplanes approved for spinning, there 

must be a placard in clear view of the pilot listing the control actions for the recovery from spinning 

maneuvers; and stating that recovery must be initiated when spiral characteristics appear, or after 

not more than six turns or not more than any greater number of turns for which the airplane has been 

certificated. 

402. PILOT AWARENESS. The pilot of an airplane placarded against intentional spins should 

assume that the airplane may become uncontrollable in a spin. In addition, stall warning devices 

should not be deactivated for pilot certification flight tests in airplanes for which they are required 

equipment. 

403. - 499. RESERVED.