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EN2367-18010 – Airbus Helicopters OEM Split Pin
The Airbus Helicopters EN2367-18010 is a flight-critical, OEM positive mechanical locking element engineered to guarantee the absolute safety of critical threaded connections across a wide range of rotary-wing platforms. In the high-vibration environment of modern helicopters, structural components and flight control mechanisms are continuously subjected to severe multi-axial harmonic oscillations, high aerodynamic loads, and rapid cyclical thermal expansion. Threaded fasteners, particularly those found within the main rotor head, tail rotor drive lines, and flight control linkages, are inherently prone to transverse micro-slip. This micro-slip can rapidly degrade nominal bolt preloads, causing spontaneous counter-rotational backing-off and catastrophic joint separation. The EN2367-18010 split pin serves as an unyielding fail-safe mechanism, isolating the critical fastener assembly from rotational loosening by directly pinning castellated nuts to their mating drilled bolts or studs.
Manufactured in strict accordance with European aerospace standards (ASD-STAN), this precision-formed split pin is cold-drawn from premium, titanium-stabilized austenitic stainless steel wire. Its tight dimensional tolerances ensure a close-tolerance interference fit through standard aerospace fastener cotter holes, eliminating localized axial or radial play within the locking slot. When installed, the pin's prongs are cold-bent around the flats of the castellated nut, creating a permanent, highly secure geometric barrier that blocks thread disengagement under the most grueling operating profiles.
For helicopter fleet operators, directors of maintenance (DOM), and structures engineers, the integration of authentic OEM components like the EN2367-18010 is an absolute requirement for ensuring continuous fleet airworthiness and type certificate conformity. Sourcing certified aerospace-grade hardware through Airparts.aero completely eliminates the risks of premature mechanical fatigue or stress corrosion cracking associated with commercial-grade fasteners, safeguarding safety-critical control loops and rotor systems from sudden structural detachment.
Key Features
Premium EN 2573 Superalloy Base: Cold-formed from high-purity, air-melted X6CrNiTi18-10 (1.4541) austenitic stainless steel wire, ensuring exceptional ductility combined with high ultimate tensile strength safety margins.
Titanium-Stabilized Microstructure: Infused with a specialized titanium stabilization matrix that preferentially binds carbon, halting chromium carbide precipitation at grain boundaries and providing total immunity to intergranular corrosion (IGA) at temperatures up to 600°C.
Precision Cold-Formed Loop Eye: Engineered with a highly uniform circular head profile that eliminates microstructural surface defects, distributing installation forces evenly to prevent localized stress propagation.
Passivated Surface Finish: Undergoes a rigorous chemical passivation treatment to optimize the protective chromium-oxide boundary layer, ensuring long-term resistance to hydraulic fluids (Skydrol), aviation fuels, atmospheric moisture, and salt-spray exposure.
Calibrated Grain Alignment: Carefully controlled metallurgical wire drawing aligns structural grains along the longitudinal axis, allowing the prongs to sustain severe plastic deformation during installation wrapping without developing micro-cracks or shear lines.
Technical Specifications
Part Number: EN2367-18010
Component Type: Split Pin / Cotter Pin (Goupille Fendue)
OEM Manufacturer: Airbus Helicopters / ASD-STAN Standard Hardware
Governing Specification: ASD-STAN EN 2367 (Specification for split pins in steel EN 2573)
Material Composition: Steel FE-PA3601 / X6CrNiTi18-10 (Material Number 1.4541) Titanium-Stabilized Austenitic Stainless Steel
Finish: Passivated per applicable European aerospace processing standards
Nominal Diameter: 1.8 mm
Nominal Length: 10 mm
Maximum Continuous Temperature: 600°C (1,112°F)
Tensile Strength Class ($R_m$): $\le$ 780 MPa (Softened wire temper)
Export Control Classification Number (ECCN): EAR99
Certification Status: EASA Form 1 / FAA Form 8130-3 Dual Release or OEM Certificate of Conformance (CoC) required for flight log validation
Aircraft Compatibility
Airbus Helicopters H125 / AS350 Écureuil Series (Including AS350 B2, AS350 B3, and H125 variants)
Airbus Helicopters H130 / EC130 Series
Airbus Helicopters H135 / EC135 Series (P2, P3, T2, T3 variants)
Airbus Helicopters H145 / EC145 Series (BK117 C2, D2, and D3 variants)
Airbus Helicopters AS365 Dauphin & H155 Series
Airbus Helicopters H215 & H225 Super Puma Series
Note: The individual aircraft Illustrated Parts Catalog (IPC) or engine maintenance publication remains the final, absolute authority for part number verification, configuration control, and serial-number effectivity.
Applications
Flight Control Linkage Safety Retention: Secures primary castellated nuts on pitch change rods, bellcranks, swashplate mixer units, and servo actuator attachments.
Tail Rotor Drive Line Configuration: Applied across intermediate gearbox attachments, tail rotor shaft flexible couplings, and directional push-pull control tubes.
Engine Deck & Hot-Section Bracketry Fastening: Provides robust, oxidation-resistant positive mechanical locking near turbine casing insulation blankets and exhaust plenums where thermal output destroys standard alloys.
Main Rotor Head (MRH) Mechanical Links: Acts as a vital secondary safety containment for multi-blade rotor sleeves, damper pins, and rotor monitoring instrumentation mounts.
Why Choose EN2367-18010?
In the severe vibrational environment of a rotary-wing aircraft, using standard commercial-grade cotter pins or uncertified hardware introduces a dangerous and unpredictable point of failure. Commercial fasteners are typical products of basic carbon steel processing, making them highly vulnerable to hydrogen embrittlement, galvanic corrosion, and rapid material relaxation under persistent cyclical loads. Furthermore, non-certified hardware lacks the precise grain structure alignment and strict titanium stabilization required to resist mechanical fatigue.
Under continuous low-frequency and high-frequency helicopter harmonics (such as 1P main rotor frequencies and high-order blade passage oscillations), an uncertified pin can undergo rapid sub-critical cracking and complete shear failure. If the pin breaks, the corresponding castellated nut can effortlessly back off the threads, culminating in immediate loss of flight control linkage connectivity or structural joint separation. Sourcing the genuine OEM EN2367-18010 through Airparts.aero guarantees total metallurgical traceability, ensures absolute compliance with EASA and FAA regulatory directives, and locks critical flight systems safely in place.
The operational physics of the EN2367-18010 split pin focus on optimizing structural shear limits and maximizing isotropic plastic energy absorption within a face-centered cubic (FCC) austenitic metal matrix under severe harmonic excitation. Fabricated per standard EN 2573, this component features a specialized alloy composition (FE-PA3601) that undergoes high-precision cold-working to ensure a uniform distribution of dislocation densities. When a helicopter joint faces heavy transverse vibrational loads, microscopic slip (micro-slip) occurs at the thread contact zones, tending to convert the axial clamp load of a bolt into an unwinding rotational force. The EN2367-18010 counteracts this dynamic breakdown through a pure mechanical double-shear constraint system. Because rotary-wing aircraft generate continuous structural oscillations across narrow frequency spectrums, standard steels can undergo stress-induced grain boundary degradation or exhibit a dangerous ductile-to-brittle transition. The inclusion of an explicit titanium stabilizer prevents this sensitization by preferentially forming titanium carbides ($TiC$) instead of chromium carbides ($Cr_{23}C_6$) at the grain interfaces. This completely eliminates localized chromium depletion zones and keeps the hardware fully immune to intergranular corrosion and subsequent micro-fissure propagation under persistent mechanical cycles up to 600°C.
Note: The EN2367-18010 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.
