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0513369-2 – Textron Aviation OEM Right-Hand (RH) Tunnel Reinforcement Angle
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The 0513369-2 is a primary structural airframe component designed for the central fuselage architecture of Cessna single-engine aircraft. As a "Reinforcement Angle," this part serves as a critical stiffener for the cabin floor tunnel—the longitudinal structural housing that runs along the belly of the aircraft. This tunnel protects and routes essential flight control cables (aileron, elevator, and rudder), fuel lines, and electrical harnesses.
The -2 variant is specifically engineered for the Right-Hand (RH) side of the assembly. It is manufactured from high-strength, aerospace-grade aluminum alloy (typically 2024-T3) and is pre-formed to the exact contour of the tunnel interface. This component is vital for maintaining the torsional rigidity of the fuselage, ensuring that the airframe can withstand the aerodynamic loads and "G-forces" experienced during flight and landing.
Key Features
Structural Integrity: Provides localized reinforcement to prevent "oil-canning" (flexing) of the floor skins and tunnel sidewalls.
Corrosion Protection: Typically supplied with a factory zinc-chromate or epoxy-polyamide primer coating, protecting the alloy from the moisture and condensation that frequently accumulates in the aircraft's lower belly.
Precision Geometry: Features pre-defined bend radii and flange dimensions that ensure a "snap-fit" against the mating bulkheads and skins, reducing the need for extensive field trimming.
OEM Material Standards: Manufactured to strict Textron (Cessna) specifications for grain direction and tempered hardness, ensuring the part will not crack under vibrational stress.
Lightweight Architecture: Optimized for the highest strength-to-weight ratio, contributing to the aircraft's overall payload efficiency.
Technical Specifications
Part Number: 0513369-2
Manufacturer: Textron Aviation (Cessna OEM)
Component Type: Structural Angle / Tunnel Reinforcement
Position: Right-Hand (RH)
Material: 2024-T3 Aluminum Alloy (Standard)
Finish: Primed (Green or Gray)
Weight: Approx. 0.45 lbs (0.20 kg)
Certification: FAA-PMA / OEM Part 23 Certified
Aircraft Compatibility
Cessna 172 Series: 172N, 172P, 172Q, 172R, and 172S (Skyhawk).
Cessna 182 Series: 182Q, 182R, 182S, and 182T (Skylane).
Cessna 206 Series: U206G, TU206G, and 206H (Stationair).
Note: Structural reinforcement parts are highly sensitive to the aircraft's model year and serial number. Always verify the 0513369-2 against your Illustrated Parts Catalog (IPC) Section 53-10 (Fuselage Structure) before installation.
Applications
The 0513369-2 is utilized for Airframe Structural Maintenance and Repair. Its primary roles include:
Structural Repair: Replacing original angles that have suffered from "smoking rivets" (indication of structural movement) or localized stress cracks.
Corrosion Remediation: Providing a factory-new replacement for parts damaged by long-term moisture entrapment or battery acid leaks in the tunnel area.
Restoration: Used during major airframe overhauls to return the fuselage to its original Type Certificate strength.
Why Choose 0513369-2?
Choosing the genuine Textron 0513369-2 is essential for Load Path Continuity. In an aircraft fuselage, every rivet and angle is part of a calculated load-bearing path. Using a "shop-made" angle from hardware-store aluminum or even standard 6061-T6 can result in a part that is either too brittle or too soft. The 0513369-2 is designed with a specific Modulus of Elasticity that allows it to work in harmony with the surrounding 2024-T3 skins. This ensures that the reinforcement doesn't create "stress risers" that could lead to catastrophic failure of the surrounding primary structure.
The 0513369-2 functions as a Stiffening Member governed by the physics of Area Moment of Inertia ($I$). By providing an "L-shaped" cross-section, the part significantly increases the resistance of the tunnel sidewall to bending and buckling forces. The aluminum alloy is chosen for its Fracture Toughness, which is a measure of the material's ability to resist the growth of a crack under repetitive flight-load cycles. During installation, the rivet pattern must match the original engineering drawing exactly to ensure the Shear Flow ($q$) of the fuselage is maintained without overloading individual fasteners.
Note: This is a primary structural component. Installation must be performed by a certified A&P/AME or at an authorized structural repair station. Proper rivet spacing, edge distance, and "deburring" of holes are critical to prevent future stress cracks. If the mating tunnel skins show signs of heavy corrosion, they must be addressed in accordance with the Cessna Structural Repair Manual (SRM) before the new angle is installed.
