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0513369-1 – Textron Aviation OEM Left-Hand (LH) Tunnel Reinforcement Angle
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The 0513369-1 is a primary structural stiffener engineered for the central floor architecture of Cessna single-engine aircraft. As a "Reinforcement Angle," this component is vital to the integrity of the cabin tunnel—the longitudinal structural corridor that houses the aircraft's primary flight control cables, fuel lines, and electrical harnesses.
The -1 variant is the Left-Hand (LH) counterpart to the 0513369-2. Manufactured from aerospace-grade 2024-T3 aluminum alloy, it is designed to provide torsional rigidity to the fuselage, ensuring the airframe maintains its geometric alignment under the various aerodynamic and landing loads encountered during the aircraft's service life.
Key Features
Structural Stabilization: Specifically designed to reinforce the lower fuselage skins and tunnel sidewalls, preventing "oil-canning" or buckling under stress.
Corrosion Resistance: Typically supplied with an OEM-spec zinc-chromate or epoxy-polyamide primer to combat the moisture and debris that commonly settle in the lower belly of the aircraft.
Precision-Bent Geometry: Pre-formed to the exact internal radii required for a flush fit against Cessna's specific bulkhead and skin profiles, ensuring a high-strength mechanical bond.
Fatigue Resistance: Constructed from high-strength aluminum with specific grain orientation to resist the development of stress cracks in high-vibration areas.
Direct OEM Replacement: Manufactured to the original Textron Aviation engineering drawings, ensuring that the repair returns the aircraft to its original Type Certificate strength.
Technical Specifications
Part Number: 0513369-1
Manufacturer: Textron Aviation (Cessna OEM)
Component Type: Tunnel Reinforcement Angle / Structural Member
Position: Left-Hand (LH)
Material: 2024-T3 Aluminum Alloy
Finish: Factory Primed (typically Green or Gray)
Weight: 0.45 lbs (0.20 kg)
Certification: FAA-PMA / Part 23 Structural Component
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: This part is highly specific to the aircraft's central tunnel configuration. Always cross-reference the 0513369-1 with your Illustrated Parts Catalog (IPC) Section 53-10 to ensure compatibility with your specific serial number.
Applications
The 0513369-1 is utilized for Fuselage Structural Maintenance. Its primary roles include:
Corrosion Remediation: Replacing internal angles that have been compromised by standing water, battery acid, or environmental salt exposure in the aircraft belly.
Structural Repair: Substituting damaged original components following a hard landing or gear-up incident where the lower fuselage structure has been deformed.
Maintenance Restoration: Resolving "smoking rivets" (evidence of structural movement) by installing a fresh, properly seated reinforcement angle.
Why Choose 0513369-1?
Choosing the genuine Textron 0513369-1 is essential for maintaining the Calculated Load Path of the airframe. The floor tunnel acts as a "backbone" for the cabin area. Using non-spec materials or "shop-made" angles can lead to localized "hard spots" that cause the surrounding thin-gauge skins to crack prematurely. The 0513369-1 is engineered with the correct Fracture Toughness to flex slightly with the airframe while providing the necessary support to keep the flight control systems properly aligned within the tunnel.
The 0513369-1 operates on the principle of Increased Section Modulus. By adding an angled flange to a flat skin surface, the component significantly increases the Area Moment of Inertia ($I$) of the fuselage floor. This prevents the tunnel from twisting during high-torque maneuvers or heavy landings. The use of 2024-T3 Aluminum is a deliberate engineering choice; it provides the high yield strength required for structural loads while maintaining excellent fatigue life under the constant harmonic vibrations generated by the engine and propeller.
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 edge distance for rivets and correct "bucking" techniques are mandatory to maintain the airworthiness of the fuselage. Refer to the Cessna Structural Repair Manual (SRM) for specific rivet patterns and sealing requirements before final assembly.
