1970-1976 Cessna Model 210 & T210 Centurion Aircraft Service Manual
Repair guide for all 210 and T210 Centurion aircraft configurations, covering hydraulic systems, landing gear, and airframe components.
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Models Covered & Key Technical Specifications
OEM-Grade Instructional Assembly Manual: Aircraft Cessna 210 & T210 Centurion Aircraft - Factory Service & Repair Reference (1970-1976) Parts-Reference Model-Portfolio: Cessna 210 / T210 (1970-1976) // Engineering-Base: Aircraft / Hydraulic System Logic // Model-Portfolio: 60.17 MB
- Design Power Draw: 3800 lb establishes the maximum operational weight Architecture.
- Advanced Ambient Limits: For optimal operation, 40°F defines the environmental limit Framework.
- Technical Feed Speed: 90 gal -- signifies the active fuel capacity Threshold.
- Standard DPI Rating: The main gear requires 11 qt for standard operation Logic.
- Prescribed Volume Data: 10 qt establishes the wing flap travel limit.
- Engineered Circuit Specs: 50 psi signifies the nose wheel tire pressure Parameters.
Manual Description & Preview
OEM-Grade Instructional Assembly Manual: Aircraft Cessna 210 & T210 Centurion Aircraft - Factory Service & Repair Reference (1970-1976) Parts-Reference
Model-Portfolio: Cessna 210 / T210 (1970-1976) // Engineering-Base: Aircraft / Hydraulic System Logic // Model-Portfolio: 60.17 MB
| Specification | Parameters | Architecture |
|---|---|---|
| Aircraft Type | Single-Engine, Semimonocoque Construction | Standard |
| Engine | Continental IO-520 Series | Military Specification |
| Fuel Capacity | 90 gal (Usable) | Standard |
| Landing Gear | Retractable | Hydraulically-Actuated |
OEM specifications cover the following key areas:
- General Description & Specifications
- Hydraulic System Diagrams
- Landing Gear Components & Maintenance
- Airframe Structures & Repair
- Fuel System Servicing
This manual details the structure, systems, and maintenance procedures for the Cessna 210 and T210 Centurion aircraft from 1970-1976. It includes in-depth information on the hydraulic system, landing gear, and airframe components, essential for proper upkeep and repair.
Testing requirements are specified for hydraulic system components to ensure proper function.
Clearance measurements are addressed for landing gear actuators and linkages.
Special procedures are addressed for servicing the hydraulic power pack and related systems.
Verification procedures are included for the nose gear and main gear assemblies.
Repair information is provided for airframe structures and control surfaces.
This manual documents torque specifications for various components to ensure proper assembly and pressure slip prevention.
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