DT-211

Operating function and signal path

The probe senses inlet-air total temperature and provides the corresponding resistive temperature signal to compatible engine or air-data equipment. The unit is a sensing element within a larger aircraft circuit; it is not a complete indicator, controller or protective system by itself. Its output is interpreted by compatible receiving equipment, so supply characteristics, polarity or phase, connector pinout, load and calibration must match the documented configuration. The two platinum elements change resistance with temperature and are positioned in the engine inlet flow according to the installation drawing. A general explanation of the underlying measurement class is available in this technical reference. That general reference explains the principle only and does not replace product-specific documentation.

Aircraft and equipment application

DT-211 is installed in aircraft-engine air intakes near the low-pressure-compressor inlet; exact engine and mounting position require the applicable engine manual. Where an aircraft or engine family is named, the statement identifies a documented installation context rather than universal applicability to every modification. The exact equipment set, production series and installed connector must be checked before ordering. Related products in the aviation sensors category are provided for catalogue navigation. The DTA-10 card is another same-category reference, but the link does not state that the two units are interchangeable or perform the same function.

Installation and passport checks

The supplied DT-211 passport gives specific mounting requirements. The arrow on the sensor housing must point in the direction of airflow. The plane of the front face must be positioned against the flow and remain perpendicular to it within ±2°. The flexible sleeve must not be twisted, its bend radius must be at least 30 mm, and axial force applied to the sleeve during installation must not exceed 1 kgf. After mounting, the sleeve must be securely fixed to the aircraft or host assembly.

Electrical verification should use the passport values for the exact unit. The resistance of each sensing element at 0 °C is 46 ±0.1 Ω, while permissible instability of the actual resistance at 0 °C during operation is limited to ±0.1 Ω. At an airflow mass velocity of 60 kg/(m²·s), the time constant must not exceed 2.0 s. Individual release values for sensing elements A and B belong in the product passport, so the document accompanying the offered serial-numbered unit should be checked before acceptance and installation.

Ordering DT-211

An enquiry should state DT-211, the required condition, quantity, aircraft or equipment context and the documentation needed with delivery. If the installed marking is incomplete, provide a clear photograph of the label, connector and mounting arrangement together with the relevant catalogue reference. Aviamisto can compare these identifiers before supply, but final installation approval remains with the operator or maintenance organisation. Technical Details below separates confirmed data from values that still require passport verification. Same-category cross-sells are navigation aids only; they must never be interpreted as approved replacements.

For a traceable quotation, also state whether a new-production unit, preserved stock item or another documented condition is acceptable. Requested acceptance documents, test records and packing requirements should be agreed before order placement.