EN2367-18012 - Airbus Helicopter Split Pin

EN2367-18012 – Airbus Helicopters OEM Split Pin

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The Airbus Helicopters EN2367-18012 is a flight-critical, OEM positive mechanical locking element engineered to guarantee the absolute security of high-stress threaded connections under severe vibrational and thermal loading profiles. In rotary-wing aircraft, primary structures and flight control installations—such as main rotor head links, tail rotor drives, and hydraulic servo actuator linkages—are continuously subjected to intense, complex multi-axial harmonic frequencies. These persistent cyclic forces naturally induce micro-slip between fastener thread faces, rapidly degrading the engineered bolt preloads and threatening the integrity of the joint. The EN2367-18012 split pin acts as a definitive mechanical safety fail-safe, isolating the fastener assembly from rotational loosening by directly pinning castellated nuts to their mating drilled bolts or studs.

Manufactured in strict compliance with European aerospace standards (ASD-STAN) for commercial and military airworthiness, this split pin is cold-drawn from premium, air-melted EN 2573 titanium-stabilized austenitic stainless steel wire. Its precise geometric profile features a uniform loop head and calibrated dual prongs configured to achieve a close-tolerance interference fit within standard aerospace safety holes. When installed, the prongs are bent around the flats of the castellated nut, undergoing uniform plastic deformation to create a permanent, vibration-proof mechanical barrier that blocks thread disengagement under the most grueling flight maneuvers.

As a senior A&P/IA mechanic with over 30 years of hands-on experience troubleshooting rotary-wing powerplants and flight controls, I cannot overstate the criticality of using certified OEM hardware like the EN2367-18012. In helicopter operations, uncertified commercial-grade pins are a direct path to a catastrophic hardware failure. Sourcing genuine, fully traceable EN2367-18012 split pins through Airparts.aero ensures total metallurgical conformity with EASA and FAA type certificate data sheets, prevents premature mechanical fatigue fracturing, and guarantees that your critical control loops remain safely locked in place.

Key Features

• Titanium-Stabilized Austenitic Alloy: Manufactured from premium EN 2573 (X6CrNiTi18-10) stainless steel, explicitly stabilized with titanium to completely eliminate the risk of intergranular corrosion (IGA) at temperatures up to 600°C.

• Vibration-Proof Positive Lock: Provides a rigid mechanical interference barrier within castellated nut slots, absorbing high-frequency rotor harmonics and blocking spontaneous fastener unwinding.

• Optimized Plastic Ductility: Softened wire temper processing ($R_m \le 780 \text{ MPa}$) provides excellent plastic deformation properties, permitting flawless wrapping without localized work-hardening cracks.

• High Shear Fatigue Life: Controlled longitudinal grain alignment developed during precision wire-drawing resists sub-critical micro-fissuring along the tight bend radii of the prongs.

• Full Aerospace Chemical Passivation: Chemically treated to reinforce the passive chromium-oxide surface film, conferring absolute immunity to degradation from Skydrol hydraulic fluid, aviation fuel, and marine salt-fog environments.

Technical Specifications

• Part Number: EN2367-18012

• Component Type: Split Pin / Cotter Pin (Goupille Fendue)

• OEM Manufacturer: Airbus Helicopters / ASD-STAN Standard Hardware

• Material Standard: EN 2573 (ASD-STAN Material Designation: FE-PA3601)

• Chemical Composition: Steel X6CrNiTi18-10 (Material Number 1.4541 / AISI 321 Equivalent)

• Finish: Passivated per aerospace standard specifications

• Nominal Diameter: 1.8 mm

• Nominal Length: 12 mm

• Ultimate Tensile Strength ($R_m$): $\le 780 \text{ MPa}$ (Softened wire temper configuration)

• Maximum Continuous Service Temperature: 600°C (1,112°F)

• Export Control Classification Number (ECCN): EAR99

• Certification Status: EASA Form 1 / FAA Form 8130-3 Dual Release or OEM Certificate of Conformance (CoC)

Aircraft Compatibility

• Airbus Helicopters H125 / AS350 Écureuil Series (AS350 B2, AS350 B3, H125 variants)

• Airbus Helicopters H130 / EC130 Series (EC130 B4, H130 T2 variants)

• Airbus Helicopters H135 / EC135 Series (EC135 P2/T2, H135 P3/T3 variants)

• Airbus Helicopters H145 / EC145 Series (BK117 C2, D2, and D3 configurations)

• Airbus Helicopters AS365 Dauphin & H155 Series

• Airbus Helicopters H215 & H225 Super Puma Series

• Note: The individual aircraft model Illustrated Parts Catalog (IPC) for the applicable airframe serial number remains the final, absolute authority for part number verification, exact quantity requirements, and component effectivity.

Applications

• Primary Flight Control System Retention: Locks primary castellated attachment nuts on main pitch-change rods, mixing units, swashplate links, and directional push-pull tubes.

• Tail Rotor Drive System Safetying: Applied to flexible coupling bolts, intermediate gearbox flanges, and tail rotor pitch-control crosshead mechanisms.

• Engine Bay and Hot-Section Securement: Safeties structural fasteners on engine mounts, fire seals, bleed air ducts, and exhaust cowl brackets exposed to extreme thermal radiant fields.

• Rotor Head Mechanical Assemblies: Secures instrumentation brackets, blade damper link pins, and auxiliary retention components within the rotating main and tail rotor heads.

Why Choose EN2367-18012?

Choosing the genuine OEM Airbus Helicopters EN2367-18012 split pin safeguards critical flight systems against the unpredictable failure modes of generic commercial-grade hardware. Commercial cotter pins are typically manufactured from basic carbon steels or low-tier stainless alloys without stringent microstructural control. When subjected to the persistent low-frequency 1P and high-order blade passage frequencies characteristic of rotary-wing aircraft, these inferior hardware choices experience rapid fatigue propagation, hydrogen embrittlement, or sub-critical stress corrosion cracking.

Furthermore, without the precise titanium stabilization found in the EN2367-18012, exposures to thermal cycles around the engine deck provoke chromium depletion at grain boundaries, leading to sudden intergranular failure. If a split pin breaks under load, the castellated nut is free to back off, which can culminate in an immediate and catastrophic loss of flight control connectivity or component separation. Procurement of authentic EN2367-18012 pins through Airparts.aero guarantees total metallurgical traceability, enforces regulatory conformity with EASA/FAA mandates, and ensures absolute field safety.

The operational mechanics of the EN2367-18012 split pin are rooted in optimizing structural shear thresholds and managing microstructural dislocations within a face-centered cubic (FCC) austenitic crystal lattice under severe harmonic excitation. Fabricated from air-melted EN 2573 steel (ASD-STAN designation FE-PA3601), the component is processed to a softened wire temper with a maximum tensile limit ($R_m \le 780 \text{ MPa}$) to maintain high plastic energy absorption parameters. When a flight-control joint is subject to multi-axial transverse vibrational loads, microscopic interfacial slippage occurs between the bolt and nut threads, generating an unwinding torque vector.

The EN2367-18012 counteracts this dynamic breakdown through a pure mechanical double-shear constraint loop. To prevent the phenomenon of sensitization—where exposure to temperatures up to 600°C causes chromium carbides ($Cr_{23}C_6$) to precipitate along grain boundaries—the alloy's chemistry features localized titanium stabilization. The titanium atoms preferentially react with interstitial carbon to form highly stable titanium carbides ($TiC$), completely eliminating localized chromium depletion zones. This preserves the material's structural homogeneity, preventing intergranular micro-fissuring propagation and ensuring the pin maintains its full ultimate shear strength safety margin under persistent cyclic loading profiles.

Note: The EN2367-18012 split pin is a flight-critical, single-use mechanical safety element. Upon initial installation and cold-forming of the prongs, the alloy undergoes definitive plastic deformation and intentional strain-hardening (work hardening) to anchor the fastener assembly. Attempting to straighten, re-bend, or reuse a previously deployed split pin introduces structural macro-fissures, severe fatigue sensitivity, and localized brittleness, predisposing the pin to rapid shear fracturing under operational vibration loads. Installation, final wrapping profiles, and inspection verification must be executed exclusively by a certified A&P mechanic, authorized structures technician, or approved MRO facility in strict compliance with the relevant Airbus Helicopters Aircraft Maintenance Manual (AMM) or structural rigging directives.

Documentation

No public-facing OEM or regulatory documentation was located for this part. Please cross-reference this part number within the official Airbus Helicopters technical publication portal or consult the current aircraft-specific Illustrated Parts Catalog (IPC) or Aircraft Maintenance Manual (AMM) for official maintenance procedures and rigging tolerances.