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Elements and Performance Criteria

1. Remove basic aircraft instrument system components
   • System is rendered safe and prepared in accordance with the applicable maintenance manual and isolation tags are fitted, where necessary, to ensure personnel safety
   • Instrument component removal is carried out in accordance with the applicable maintenance manual while observing all relevant work health and safety (WHS) requirements
   • Required maintenance documentation is completed and processed in accordance with standard enterprise procedures
   • Removed components are tagged and packaged in accordance with specified procedures
2. Install basic aircraft instrument system components
   • Instrument components to be installed are checked to confirm correct part numbers, modification status, serviceability and shelf life
   • Physical installation of instrument components is performed in accordance with the applicable maintenance manual and regulatory requirements, ensuring appropriate adjustment/alignment is carried out
   • System is reinstated to correct operational condition in preparation for testing, as necessary
   • Required maintenance documentation is completed and processed in accordance with standard enterprise procedures

Range Statement

This field allows for different work environments and conditions that may affect performance. Essential operating conditions that may be present (depending on the work situation, needs of the candidate, accessibility of the item, and local industry and regional contexts) are included.
Instrument components include:	Pitot/static system components, airspeed indicators (ASIs), vertical speed indicators (VSIs) and counter pointer altimeters Directional gyros (DGs) and artificial horizons (AHs), both air and electrically driven Turn and bank and slip/turn coordinators Direct reading compasses Remote reading gyro compasses (where applicable to the enterprise) Piston engine indication system components (direct reading measuring instruments and temperature indication) Gas turbine engine indication system components (where applicable to the enterprise) Outside air temperature gauges (OAT) Electrical systems indication (voltage, current, power and frequency) Basic fuel quantity indication system components Pneumatic/vacuum indication system components
Procedures and requirements include:	Industry standard procedures specified by manufacturers, regulatory authorities or the enterprise

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Performance Evidence

Evidence required to demonstrate competency in this unit must be relevant to and satisfy all of the requirements of the elements and performance criteria under the specified conditions of assessment, and must include:

locating and identifying flight instrument system components comprising:

piston engine system temperature, pressure, speed (including mechanical and electrical tachometers), manifold pressure/boost (including aneroid type, sylphon bellows and dual compartment type)

gas turbine engine indicating system temperature, pressure, speed, torque, fuel flow and vibration (may be omitted if not relevant to the enterprise)

auxiliary direct reading systems, including hydraulic pressure, pneumatic pressure and vacuum, and fuel storage quantities

flight systems, including attitude, altitude, air speed and OAT

locating and identifying direct reading compasses

locating and identifying remote reading gyro compass system components (may be omitted if not relevant to enterprise)

correct handling and observance of maintenance precautions relating to gyroscopes, gimbals, pitot/static systems (connections, heating and protrusions)

applying relevant WHS practices.

It is essential that cleanliness requirements and safety precautions applicable to the system being maintained are fully observed, understood and complied with, as well as work practices associated with electrostatic sensitive devices.

Evidence of transferability of skills and knowledge related to removal and installation is essential. This is to be demonstrated by application across a range of aircraft instrument system components as listed in the Assessment Conditions.

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Knowledge Evidence

Evidence required to demonstrate competency in this unit must be relevant to and satisfy all of the requirements of the elements and performance criteria and include knowledge of:

component attachment methods

connection of hardware and plugs

handling precautions relating to:

electrostatic sensitive devices

gyroscopes and gimbals

basic instrument system and component operating principles:

atmospherics and barometry

terminology and unit of measurement conversion

aircraft instrumentation requirements

instrument panel layout

pressure sensing elements

pitot static systems and testing requirements

gyroscopic principles

direct reading compasses

remote reading gyro compasses

temperature sensors

fluid quantity indication systems

general layout and components of the following systems:

flight systems, including:

altitude (direct reading altimeters)

attitude, including directional gyros and artificial horizons (both air and electrically driven), turn and slip and turn coordinator

airspeed

OAT

remote reading gyro compass system

piton engine indication systems, including:

direct reading temperature

direct reading pressure (e.g. oil pressure)

speed, including mechanical and electric tachometers

manifold pressure/boost, including aneroid, sylphon bellows and dual compartment types

gas turbine engine indication systems, including:

temperature and pressure

speed, including mechanical and electric tachometers

torque

fuel flow

vibration

auxiliary direct reading systems, including:

electrical

hydraulic pressure

pneumatic pressure and vacuum

basic fuel quantity indication

relevant WHS practices

relevant maintenance manuals

relevant regulatory requirements and standard procedures.

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