MV-04-1

Operating function and signal path

Engine vibration loads the piezoelectric element, generating charge proportional to vibration acceleration for the compatible electronic processing block. 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. Mounting-face condition, orientation, fastening torque, shielded cable and the matching vibration-monitoring channel affect measurement accuracy. 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

MV-04-1 is documented with IV-50P-family vibration equipment on aircraft gas-turbine engines; the exact engine and sensor position follow the installation 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 MV-25G 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 maintenance checks

Before installation, technicians should compare the nameplate, suffix, connector, mounting faces and available acceptance record with the approved requirement. The housing, pressure ports or mechanical input, electrical contacts and sealing features should be inspected without altering calibration. Wiring continuity, insulation and output checks must follow the passport limits for this execution. Do not apply a supply voltage, pressure, acceleration, rotation or test signal taken from a neighbouring model. Storage condition and preservation date should also be reviewed when the unit has remained in stock for an extended period.

After installation, functional testing must be performed as part of the complete aircraft circuit, using approved test equipment and the limits defined by the maintenance manual. A correct bench response alone does not prove that the installation wiring, pneumatic lines, mechanical linkage or receiving unit is serviceable. Any discrepancy should be traced without adjusting sealed elements unless the repair documentation expressly authorises that procedure. The maintenance record should identify the fitted designation and serial number so that later troubleshooting does not confuse adjacent family executions.

Ordering MV-04-1

An enquiry should state MV-04-1, 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.