Task VII.D
Spin Awareness
To determine the applicant exhibits satisfactory knowledge of the causes and procedures for recovery from unintentional spins and understands the risk associated with unintentional spins.
References: AC 61-67; FAA-H-8083-2, FAA-H-8083-3, FAA-H-8083-25; POH/AFM
Quick Review
An aggravated stall with autorotation: both wings are stalled, but one is more deeply stalled than the other. The asymmetric lift and drag roll and yaw the airplane around a helical path, descending nose-low while rotating.
Stall + yaw. No stall, no spin. No yaw, no spin — a coordinated stall breaks straight ahead. That's why coordination during slow flight and stalls is the primary spin prevention.
The low (dropping) wing. As it drops, its relative wind comes from further below, increasing its angle of attack — deeper stall, less lift, more drag. The rising wing's AoA decreases, so it's less stalled and keeps flying. The lift/drag imbalance sustains the rotation without any further control input.
- Entry — the stall breaks with yaw present; a wing drops.
- Incipient — roughly the first two turns (about 4–6 seconds in most light airplanes) while the rotation accelerates. Recovery here is quick.
- Developed — rotation rate, airspeed, and descent rate stabilize; the flightpath is nearly vertical. Recovery takes longer and loses more altitude.
- Recovery — anti-spin inputs stop the rotation, AoA drops below critical, and the airplane is flying again — in a dive.
Overshoot final, and the temptation is to hold the bank shallow and cheat the nose around with inside (bottom) rudder — a skid — while slow and pulling. The yaw slows the inside wing; if the stall breaks, the inside wing drops and the airplane snaps toward the low wing, nose slicing down. At pattern altitude there isn't enough sky to recover. Fix: go around and re-enter — never rudder the nose around a turn.
The stall horn and buffet are calibrated around 1G coordinated flight. Pull hard and stall speed rises with the square root of load factor (an accelerated stall); add a skid and the break can be abrupt and toward the low wing, with the warning margin compressed to almost nothing. A stall can occur at any airspeed, attitude, and power setting.
Thrust tends to raise the nose and flatten the spin, and propeller gyroscopic effects can aggravate it — both delay recovery. Idle power also means less airspeed to fight in the dive that follows.
Aileron toward the "up" side to lift the low wing increases the down wing's AoA — deepening its stall and accelerating the rotation. Neutral takes ailerons out of the fight; rudder and elevator do the recovery.
Neutralize the rudder (holding it invites a spin the other way), then ease out of the ensuing nose-low dive smoothly. Yank back and you risk a secondary accelerated stall or overstressing the airframe; dawdle and airspeed builds toward Vne.
Aft CG flattens the spin — less nose-down pitching moment and less elevator authority to break the AoA — and a flat spin may be unrecoverable. Forward CG makes the airplane harder to spin and steepens the spin, aiding recovery. Higher weight adds rotational inertia: slower to spin up, but slower to stop, too. This is a big reason aft-of-limit loading is dangerous.
For most normal-category airplanes — the Warrior included — intentional spins are prohibited; check the placards and POH limitations. Private pilot training requires spin awareness only, not spin demonstrations. If a spin happens unintentionally, recover per the POH — for the PA-28 the published flow matches PARE.
Even a prompt recovery from an incipient spin can take several hundred to over 1,000 feet including the dive pullout; a developed spin loses far more. That's why a spin entered in the traffic pattern is usually not survivable — prevention (coordination + AoA awareness) is the real recovery.
Tolerances per FAA-S-ACS-6C (ASEL).
Technique Notes
How a spin actually works
A spin is not a "worse stall" — it's a stall with a rotation engine attached. At the stall break, any yaw means one wing is moving slower through the air than the other. The slower wing stalls deeper and drops; as it drops, its relative wind shifts upward from below, driving its AoA even higher. The rising wing's AoA falls, so it keeps producing lift. More lift on one side, more drag on the other: the airplane rolls and yaws into the low wing and keeps going — autorotation. Once established, the spin sustains itself; I'm a passenger until I put in anti-spin controls.
Contrast with a spiral dive, which looks similar from the seat but is the opposite problem: in a spiral the wings are flying (not stalled), airspeed is increasing rapidly, and G is building. Spin: stalled, airspeed low and steady, rotation steady. Spiral: not stalled, airspeed winding up. The recovery for one is wrong for the other — pulling back in a spiral tightens it and loads the airframe; check the airspeed indicator if there's any doubt.
Phase by phase
- Entry. Stall plus yaw. In training entries this is deliberate; in the real world it's a skidded turn, a botched go-around with full power and heavy right-rudder demand, or a distraction during slow flight.
- Incipient — first ~two turns. The aerodynamic and inertial forces haven't balanced yet; rotation is still accelerating. Recovery inputs here work fast, which is why immediate recognition matters more than perfect technique.
- Developed. Forces are in balance: rotation rate, airspeed, and vertical speed all stabilize, descending nearly vertically at a couple of thousand feet per minute or more. The airspeed indicator sits low and steady — one more cue distinguishing it from a spiral.
- Recovery. Opposite rudder breaks the yaw, forward elevator breaks the AoA, rotation stops — and I'm in a steep nose-low dive at idle. The maneuver isn't over until I've smoothly returned to level flight without a secondary stall.
PARE, and why each step is in that order
- Power idle — thrust flattens the spin attitude and gyroscopic precession from the prop can resist recovery; idle removes both, and keeps the dive tamer.
- Ailerons neutral — instinct screams to pick up the low wing with aileron. That aileron deflects the down wing's trailing edge down, raising its AoA at exactly the wrong moment — deepening the stall and speeding rotation. Hands do less, feet do more.
- Rudder full opposite the rotation — the rudder is the one control still working cleanly in the disturbed airflow, and it attacks the yaw that powers the autorotation.
- Elevator briskly forward — after opposite rudder, positively reduce the AoA below critical. "Briskly forward" feels wrong pointed at the ground; it's still the answer, because the wing is stalled and only AoA reduction un-stalls it.
- Then: rudder neutral as rotation stops (held rudder can snap it into a spin the opposite direction), flaps up if they were out, and ease out of the dive — smooth pull, respecting load factor, before airspeed runs toward Vne.
The POH/AFM procedure is the authority — PARE is the memory scaffold, and for the PA-28 the published procedure follows the same flow. Know the actual POH wording for the checkride.
Configuration, weight, and CG
- Aft CG shortens the arm of the stabilizing nose-down pitching moment and the elevator's authority. Spins go flatter, and a truly flat spin — nose near the horizon, rotation fast, airflow over the tail garbage — may be unrecoverable in a normal-category airplane. This is the visceral reason W&B limits aren't paperwork.
- Forward CG resists spinning and steepens any spin that does develop — steeper means more airflow over the tail and easier recovery.
- Weight adds rotational inertia, slowing both spin-up and recovery; heavier airplanes lose more altitude getting out.
- Flaps should come up during recovery per the POH — the dive after rotation stops can blow through Vfe quickly, and flaps degrade spin recovery characteristics.
- Power and configuration at entry matter too: a power-on, flaps-out entry (think botched go-around) breaks harder and more wing-drop-prone than a power-off clean stall.
Environmental and human factors
- Turbulence and gusts can shove AoA past critical with no change in what I did — margin matters on gusty days, especially slow and low.
- High density altitude means higher TAS (and groundspeed) at the same IAS: more real-world altitude consumed by any stall/spin event, and sluggish climb performance tempting a tighter, slower pattern.
- Distraction is the common thread in stall/spin accidents: heads-down in the pattern, stretching a glide, dodging traffic. The defense is discipline — coordinated feet as habit, AoA awareness over airspeed fixation, and a hard "go around" trigger when a turn to final starts needing rudder to make the runway.
Official ACS elementsreference
Knowledge3 elements
The applicant demonstrates understanding of:
PA.VII.D.K1Aerodynamics associated with spins in various airplane configurations, including the relationship between angle of attack, airspeed, load factor, power setting, airplane weight and center of gravity, airplane attitude, and yaw effects.PA.VII.D.K2What causes a spin and how to identify the entry, incipient, and developed phases of a spin.PA.VII.D.K3Spin recovery procedure.
Risk Management6 elements
The applicant is able to identify, assess, and mitigate risk associated with:
PA.VII.D.R1Factors and situations that could lead to inadvertent spin and loss of control.PA.VII.D.R2Range and limitations of stall warning indicators (e.g., aircraft buffet, stall horn, etc.).PA.VII.D.R3Spin recovery procedure.PA.VII.D.R4Effect of environmental elements on airplane performance related to spins (e.g., turbulence, microbursts, and high-density altitude).PA.VII.D.R5Collision hazards.PA.VII.D.R6Distractions, task prioritization, loss of situational awareness, or disorientation.