The physical limit of an aircraft's fuselage length establishes a non-negotiable boundary during low-altitude maneuvers. When a stretched-fuselage aircraft transitions rapidly from touchdown to a rejected landing, the margin for error narrows to fractions of a degree. This mechanical vulnerability materialized on October 18, 2024, when a Turkish Airlines Airbus A321neo (registration TC-LTL) experienced a severe tail strike during a go-around on Runway 28L at Dublin Airport.
The Air Accident Investigation Unit (AAIU) Synoptic Report isolates a combination of micro-climatic volatility, geometric constraints, and high-rate manual control inputs as the mechanics behind the structural failure. Understanding this event requires breaking down the flight profile into distinct aerodynamic, mechanical, and cognitive phases.
The Geometric Constraint Engine
The structural architecture of the Airbus A321neo significantly reduces the rear fuselage clearance compared to its shorter predecessor, the A320. This physical reality underpins the entire incident profile. While the A320 provides a generous margin, the A321neo features an elongated fuselage that shortens the distance between the main landing gear pivot point and the aft under-fuselage skin.
During a standard landing flare or a rotated take-off, the maximum permissible pitch angle before fuselage contact—the tail strike limit—depends directly on landing gear strut compression. With fully extended landing gear struts, the geometric tail strike limit sits at approximately 11 degrees of pitch. When the landing gear struts are compressed by the weight of the aircraft upon touchdown, this critical threshold drops to roughly 9.5 degrees.
The AAIU data indicates that the aircraft was operating at 13 tonnes below its maximum landing weight. This reduced mass altered the kinetic energy absorption requirement during the flare, rendering the airframe highly reactive to vertical aerodynamics and control surface deflections.
Chronology of Dynamic Destabilization
The approach remained stabilized until the final descent phase below 100 feet, where a sequence of environmental and operational variables disrupted the flight path.
[Stable Final Approach]
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[Micro-Climatic Shift] ──► (Sudden crosswind drop + Tailwind spike)
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[Asymmetric Touchdown] ──► (Left main gear contact + Leftward drift)
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[Energy Rebound (Bounce)] ──► (Captain calls Go-Around)
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[Full Back Sidestick Input] ──► (Rapid pitch rate acceleration)
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[Structural Strike] ──► (Tail hits runway at compressed gear limit)
1. The Micro-Climatic Shift
As the aircraft entered the flare window, the local wind profile underwent a rapid vector change. The left crosswind dropped abruptly, paired with an instantaneous increase in tailwind component. This environmental shift stripped away a portion of the aircraft’s indicated airspeed, causing a localized loss of lift over the wings. The immediate consequence was a lateral drift to the left of the runway centerline and an accelerated sink rate.
2. Asymmetric Touchdown and Kinetic Rebound
The aircraft made initial contact with Runway 28L via its left main landing gear only. Due to the high descent rate and uneven lift distribution, the airframe suffered a brief, minor bounce before settling down again on both main landing gear units. This sequence destabilized the lateral and vertical axes of the aircraft simultaneously, introducing unexpected rolling and pitching moments.
3. The Pitch Acceleration Phase
Immediately following the second touchdown, the captain initiated a rejected landing, calling for a go-around. The first officer, acting as the pilot flying, advanced the thrust levers to the Take-Off/Go-Around (TOGA) detent and pulled the sidestick fully back to its rear limit.
This full aft control input triggered a rapid pitch rate. In an aircraft with an elongated fuselage, applying maximum nose-up elevator command while the landing gear is still in contact with—or inches above—the runway surface causes the aircraft to pivot sharply around its main wheels. The pitch angle accelerated past the safety margins, overriding the automated defenses before the wings could generate sufficient lift to climb away. This resulted in a 16-meter scrape mark on the runway, located 9 meters left of the centerline.
The Human-Machine Feedback Loop
The core breakdown in this event lies within the interaction between fly-by-wire flight control logic and human performance under high stress. The AAIU explicitly cited "startle and surprise" as a primary contributory factor.
When the aircraft drifted and bounced, the sudden deviation from a routine landing profile created a high cognitive load for the flight crew. The captain’s sudden call for a go-around forced an immediate transition from a landing mindset to an emergency escape mindset. This sudden shift explains the first officer's aggressive control input.
A full aft sidestick command represents a raw survival reflex rather than a measured technical maneuver. In a standard go-around from a clean approach, the fly-by-wire system manages pitch rates smoothly. However, close to the ground with the landing gear compressed or bouncing, the normal flight protection laws operate differently. The system interpreted the full aft stick command as a mandate for maximum achievable pitch change, accelerating the tail into the tarmac before the "PITCH PITCH" aural warning could prompt corrective action.
Structural Consequences and Risk Profile
The physical inspection at Dublin Airport revealed substantial structural damage to the aft section of TC-LTL. The impact generated a 3.4-meter-long tear in the lower fuselage skin, alongside structural cracking within the internal frames and stringers. Crucially, some of this cracking extended into the pressurized envelope of the fuselage.
The flight crew detected the physical impact and suspected structural damage immediately. However, they failed to execute the mandated "TAILSTRIKE" emergency checklist. While they monitored the cabin pressurization system and noted it was operating normally, skipping the dedicated checklist represents a significant procedural omission. The aircraft climbed, circled back, and landed safely 13 minutes later.
The structural damage created a specific operational vulnerability during the recovery phase:
- Pressurized Flight Risk: The integrity of the aft pressure bulkhead was compromised by proximity to the structural cracking. A standard pressurized flight would put intense cyclical stress on the torn skin, risking a rapid decompression event.
- Logistical Limitation: The aircraft could not return to its primary maintenance hub under normal operating conditions. It required temporary structural stabilization at Dublin Airport before executing a ferry flight to a heavy maintenance facility. This flight had to be conducted entirely unpressurised and at low altitude to mitigate the risk of structural failure.
The systemic nature of this risk profile is underscored by a striking historical parallel. On July 1, 2025, a second, nearly identical tail strike incident occurred at Dublin Airport involving the exact same aircraft type and operator. This recurring pattern indicates that the combination of Dublin’s local wind shear profiles, the geometry of the A321neo, and fleet-wide pilot training protocols creates a highly repeatable error pathway.
Operational Action Plan for Fleet Operators
To prevent the repetition of high-rate over-rotation events during rejected landings, flight operations departments must implement explicit, non-punitive intervention protocols.
Implement Pitch-Rate Awareness Training
Simulator training modules must move away from standard, generic go-arounds to focus exclusively on rejected landings after touchdown. Pilots must be trained to recognize that a go-around initiated after wheels-down is not a standard take-off rotation. The initial pitch input must be deliberate and limited to a maximum of 7.5 to 8 degrees until the aircraft is verified as airborne, completely independent of thrust application.
Mandate Strict Sidestick Discipline
Fleet-wide directives must reinforce that full-aft, high-rate sidestick inputs on stretched aircraft variants are unacceptable outside of windshear recovery profiles. Flight data monitoring programs should actively track rotation rates during go-arounds, flagging any pitch-rate acceleration that exceeds 2 degrees per second during low-altitude transitions.
Standardize the TAILSTRIKE Checklist Execution
Training must enforce the immediate, unconditional execution of the "TAILSTRIKE" checklist whenever an abnormal contact is suspected. Relying solely on real-time pressurization readings is an unreliable diagnostic method. Internal structural cracking can remain stable at low differentials but fail catastrophically under normal operational pressure cycles.
