MS20392-2C11 - Straight Headed Alloy Steel Clevis Pin 0.186 In Diameter 0.516 In Length

MS20392-2C11 – Aeronautical Standards Group Straight Headed Alloy Steel Clevis Pin

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The MS20392-2C11 is a flight-critical, high-strength alloy steel straight headed clevis pin manufactured in strict accordance with the Aerospace Industries Association's NASM20392 standard (formerly the MS20392 military standard sheet). Featuring a nominal shank diameter of 3/16 inches ($0.188\text{ in}$) and an under-head length of 11/32 inches ($0.516\text{ in}$), this precision fastener is specifically engineered to serve as a pivotal load-bearing connector within primary and secondary aircraft control systems. Designed to carry high-frequency transverse shear loads, the MS20392-2C11 secures critical rotational mechanical hinges and linkage junctions, preventing joint separation while allowing smooth angular deflection across various flight envelopes.

Manufactured from premium, high-density carbon or low-alloy steel—such as AMS 6300, AISI 4130, or AISI 8630 structural steel matrix—the MS20392-2C11 undergoes controlled heat treatment to achieve an optimized hardness rating ranging between 26.5 and 32.0 HRC. The pin is finished with a protective electro-deposited cadmium plating (QQ-P-416 Type II, Class 2) topped with a gold chromate conversion strike. This plating serves as a sacrificial boundary layer, preventing intergranular oxidation and safeguarding the joint from galvanic corrosion when inserted into non-ferrous aluminum airframe fittings or magnesium clevis forks. Its precision-ground shank features a single drilled hole near the chamfered end, providing a clean physical path for a cotter pin to establish a positive mechanical lock against axial migration.

The MS20392-2C11 represents the foundational hardware benchmark for general aviation, commercial transport platforms, and defense airframe sustainment. Superceding legacy part numbers AN393-11 and 424-174, its structural profile is precision-machined to eliminate micro-voids and surface discontinuities, ensuring highly predictable fatigue limits under severe engine vibrations and aerodynamic buffering. For structural mechanics, quality control inspectors, and aerospace procurement specialists, sourcing fully traceable MS20392-2C11 pins ensures that flight deck control linkages match original factory type-certificate limits, maintaining absolute command path predictability.

Key Features

• High-Shear Alloy Steel Matrix: Heat-treated to standard aerospace specifications, yielding superior shear capacity to withstand high-load push-pull and rotational control demands.

• Sacrificial Cadmium over Chromate Plating: Plated per QQ-P-416 parameters to maximize defense against corrosion and atmospheric moisture in non-pressurized zones.

• Positive Locking Drilled Shank: Incorporates a clean 5/64-inch drilled cross-hole optimized for cotter pin retention, eliminating the risk of unfastening under cyclic vibrations.

• Strict Dimensional Parallelism: Precision-ground outer body minimizes slop and mechanical hysteresis within tight-tolerance clevis joints, maintaining sharp control responses.

• Pre-Chamfered Tip Geometry: Features an engineered chamfered or radiused shank end to facilitate rapid self-alignment during blind-mating field maintenance cycles.

Technical Specifications

• Part Number: MS20392-2C11 (Supersedes: AN393-11, 424-174)

• Component Type: Straight Headed Drilled Shank Clevis Pin

• Governing Specification: AIA/NAS NASM20392 / MS20392

• Nominal Shank Diameter: 3/16 Inch ($0.1875\text{ in}$ nominal / $0.186\text{ in}$ minimum baseline)

• Under-Head Length: 11/32 Inch ($0.516\text{ in}\ \pm 0.010\text{ in}$)

• Effective Grip Length: 0.344 Inches ($0.344\text{ in}$)

• Drilled Hole Diameter: 5/64 Inch ($0.076\text{ in}$ nominal)

• Head Style: Flat Pan Style (Pan No. 2 Configuration)

• Head Diameter: 0.312 Inches ($0.312\text{ in}$)

• Material Composition: Heat-Treated Low-Alloy Steel (AISI 4037 / 4130 / 8630 / 8740 per AMS 6300 or MIL-S-6758)

• Hardness Rating: 26.5 to 32.0 Rockwell C (HRC)

• Surface Treatment: Cadmium Plated (QQ-P-416, Type II, Class 2) with Chromate overall

• Certification Status: Certificate of Conformance (CoC) / Full Material Traceability Profile

• Alternate Part Number:   AN393-11, 424-174

Aircraft Compatibility

• Beechcraft King Air & Turboprop Fleet: King Air 90, C90, C90A, E90, B200, B200GT, 300, 350, 350i, 360, 360C Series; Beechcraft Baron B55, E55, 58, G58; Bonanza 36, F33A, F33C Series; Beechjet 400/400A; 1900, 1900C, and 1900D Airliners.

• Cessna Citation Jet Family: Citation M2, Mustang, CJ3, CJ4, Excel, XLS, XLS+, Citation III, VI, VII, Citation X, SkyCourier.

• Cessna Piston Series: Cessna 172 Skyhawk, 182 Skylane, 206 Stationair, 210 Centurion.

• Note: Fastener selection, hole-tolerances, and installation authority must be verified strictly by referencing the target aircraft's specific Illustrated Parts Catalog (IPC), Structural Repair Manual (SRM), or Wiring/Mechanical Control Maintenance logs.

Applications

• Flight Control Linkages: Acting as the primary shear pins in push-pull rod assemblies, control yoke pivots, bellcrank connectors, and rudder pedal arrays.

• Mechanical Actuator Tie-ins: Coupling secondary mechanical drive rods to trim tab actuators, environmental control valves, and engine power control quadrants.

• Structural Bracket Pivots: Retaining secondary structural attachment hinge loops, door latch arms, and cowl flap mechanical linkages.

Why Choose MS20392-2C11?

Selecting a trace-certified MS20392-2C11 structural clevis pin prevents localized hinge failures or flight control binding associated with generic or unverified industrial hardware. Commercial pins often suffer from inconsistent material density, structural grain distortion, or uneven zinc-plating thickness, which causes premature wear and thread backing. Under sustained aerodynamic loads, a non-aviation pin can shear unexpectedly or deform inside the clevis fork lugs. This distortion induces high friction, control slop, or mechanical binding that blocks cable tracking. Sourcing fully traceable NASM20392 standard parts ensures exact hardness depth and dimensional concentricity, maintaining tight joint limits and delivering a long operational fatigue life across grueling commercial cycles.

The mechanical structural envelope of the MS20392-2C11 clevis pin relies on the principles of pure transverse shear strain resolution and isotropic material grain optimization within tight-tolerance planar joints. Positioned at the juncture of a planar four-bar linkage or an actuator control fork, the pin is subjected to zero intentional tensile stresses. Instead, it must oppose the orthogonal cutting forces acting across the shear plane defined by the mating clevis lugs. By utilizing a high-toughness, low-alloy steel substrate processed to a homogeneous martensitic matrix, the shank resists localized fretting fatigue and deformation.

The cadmium coating functions as a sacrificial lubricated interface, lowering the sliding coefficient of friction against the inner walls of the linkage bushed bore. This configuration halts stick-slip friction anomalies that cause aerodynamic flight control hunting. Concurrently, the single end cross-drilled path is deburred precisely to eliminate macroscopic notch filters that accelerate fatigue crack propagation under high-frequency engine harmonics. This structural composition preserves absolute geometric trueness and structural safety margins across thousands of flight command hours.

Note: The MS20392-2C11 is a flight-critical, shear-dominant mechanical fastener. Reusing a distorted pin, utilizing an out-of-tolerance hole size, or failing to install the correct specification corrosion-resistant cotter pin can induce structural joint separation, catastrophic flight control failure, or complete loss of aircraft attitude command. Fastener inspection, measurement of clearance tolerances using a calibrated micrometer, and component replacement must be executed exclusively by a certified A&P/IA mechanic or authorized avionics repair station in strict accordance with the applicable aircraft Structural Repair Manual (SRM) or Standard Practices Manual. Always verify that a matching AN960/NAS1149 flat washer is installed under the cotter pin head loop to protect the clevis assembly from side-play scoring.

Documentation

• AIA/NAS NASM20392 Standard Sheet for Pins, Straight, Headed, Drilled Shank

• FAA Advisory Circular AC 43.13-1B: Acceptable Methods, Techniques, and Practices - Aircraft Inspection and Repair (Chapter 7: Aircraft Hardware)

• No direct standalone OEM manufacturing print PDF download is available for this generic military standard fastener line item sequence; precise dimensional limits should be validated using authorized standard military specification log views or a licensed Textron/AIA technical database sheet print.

Description:   Straight Headed Pin
Part Number:   MS20392-2C11
Alternate Part Number:   AN393-11, 424-174


Product Overview
length: 11/32", diameter: 1/8", straight drilled shank, cadmium plated steel alloy, MS20392 series pin


Features and Specification

Aircraft Eligibilities
• Bombardier Challenger 601
• 604
• 605
• Bombardier Learjet 40
• 45
• 55
• 60
• Embraer Legacy 600-650
• Embraer Phenom 300
• Piaggio Avanti II
• Avanti P180
• Beechcraft King Air 100
• 200
• 300
• 90
• Beechcraft Premier
• Cessna 500 Citation I-ISP
• 510 Citation Mustang
• 525 Citation Citationjet
• 550 Citation I-II-Bravo
• 560 Citation V-Ultra-Encore-Excel-XLS
• 650 Citation III-IV-VI-VII
• 750 Citation X
• Hawker 400-400XP



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