0832250-2 – Textron Aviation OEM Spar Support Assembly
Available now through the AirParts Aero marketplace.
Overview Section
The Textron Aviation 0832250-2 is a critical structural airframe component engineered for the Cessna single-engine piston fleet. This assembly serves as a primary load-bearing interface between the wing spar and the fuselage carry-through structure.
Manufactured to the precise engineering tolerances of the original equipment manufacturer (OEM), the 0832250-2 is responsible for transferring the bending and torsional loads from the wing into the fuselage cabin frame. Because it is located in a high-stress area subject to constant aerodynamic loading and vibration, this assembly is constructed from high-strength aerospace aluminum alloy and features reinforced attachment points for the main wing bolts.
Key Features Section
OEM Structural Integrity: Specifically engineered by Textron Aviation to meet the original Type Certificate (TC) requirements for the aircraft’s structural load paths.
Precision Machined Forging/Cast: Constructed from high-strength aluminum alloy, often treated with an alodine or epoxy-primer finish to prevent intergranular corrosion.
Pre-Drilled Alignment: Features factory-precision pilot holes or final-size bores for the main wing attach bolts, ensuring perfect dihedral and sweep alignment during installation.
Fatigue Resistance: The geometry is optimized to eliminate "stress risers," distributing the flight loads evenly across the fuselage bulkhead.
Direct Replacement: Designed as a drop-in replacement for damaged or corroded support assemblies, eliminating the need for field-engineered structural repairs.
Certified Traceability: Comes with full OEM documentation, ensuring compliance with Part 21 and Part 145 maintenance requirements.
Technical Specifications Section
| Specification | Detail |
| Part Number | 0832250-2 |
| Manufacturer | Textron Aviation (Cessna) |
| Component Type | Spar Support / Wing Attach Assembly |
| Material | High-Strength Aluminum Alloy |
| Finish | Zinc Chromate or Epoxy Primer (Lot dependent) |
| Placement | Wing-to-Fuselage Interface (Left or Right - Check IPC) |
Aircraft Compatibility Section
The 0832250-2 is a primary structural component found in the following Cessna models:
Cessna 172 Series (172R, 172S Skyhawk): Used in the upper cabin/wing-root interface.
Cessna 182 Series (182S, 182T Skylane): A critical support for the high-lift wing structure.
Cessna 206 Series (Stationair): Integral to the heavy-duty utility wing mounting system.
Technical Applications & Safety
The spar support assembly is the "hinge point" of the aircraft's structural integrity. During high-G maneuvers or turbulence, this component experiences massive tension and compression cycles.
Safety Warning: This is a life-limited or "condition-monitored" structural part. During 100-hour or Annual inspections, this area must be checked for "smoking rivets" (black oxidation streaks) or hairline cracks around the bolt holes. Any sign of elongated holes or "fretting" between the support and the fuselage skin requires immediate replacement. Never attempt to weld or "patch" a cracked 0832250-2; structural failure in this area can lead to catastrophic wing separation.
Technical Engineering Insight
The engineering value of the 0832250-2 lies in its Load Path Continuity. In high-wing Cessna aircraft, the spar supports are the primary conduit for "Lift" forces. The assembly is designed with a specific "grain flow" in the metal to ensure that cracks cannot easily propagate across the bolt-hole web. Textron engineers this part to act as a fail-safe; even under extreme stress, the material is designed to deform slightly (yielding) before it fractures, giving the pilot or mechanic visual cues (distorted skin or loose rivets) that the airframe has exceeded its limits.
Installation & Maintenance Addendum
Corrosion Protection: When installing the 0832250-2, it is standard practice to apply a layer of wet-install sealant (such as AeroSeal or BMS 5-95) between the assembly and the fuselage to prevent "crevice corrosion" caused by trapped moisture.
Bolt Torque: The main wing bolts passing through this support must be torqued precisely to the Cessna Maintenance Manual (AMM) values. Under-torque leads to vibration and hole elongation; over-torque can cause "stress corrosion cracking" (SCC).
Bushing Inspection: Check that any internal bushings are not "spinning" within the assembly. A loose bushing indicates the aluminum housing has expanded and the assembly is no longer airworthy.