List the assessment methods to be used and the context and resources required for assessment. Copy and paste the relevant sections from the evidence guide below and then re-write these in plain English.
Elements describe the essential outcomes. | Performance criteria describe the performance needed to demonstrate achievement of the element. |
1. | Inspect basic aircraft electrical systems and components | 1.1 | Relevant maintenance documentation and modification status, including system defect reports where relevant, are used to identify specific inspection requirements |
| | 1.2 | Isolation tags are checked and aircraft configured for safe system inspection and operation in accordance with the applicable maintenance manual |
| | 1.3 | Direct current (DC) electrical system is visually or physically checked for external signs of defects in accordance with applicable maintenance manual while observing all relevant work health and safety (WHS) requirements |
| | 1.4 | Defects are correctly identified and reported |
2. | Test/adjust basic aircraft electrical systems | 2.1 | Aircraft and system are prepared in accordance with applicable maintenance manual for the application of power/system operation |
| | 2.2 | Electrical system is functionally tested in accordance with maintenance manual for evidence of serviceability or malfunction |
| | 2.3 | System calibration or adjustments are performed in accordance with maintenance manual, as appropriate |
3. | Troubleshoot basic aircraft electrical systems | 3.1 | Available information from maintenance documentation and inspection and test results is used, where necessary, to assist in fault determination |
| | 3.2 | Maintenance manual fault diagnosis guides and logic processes are used to ensure efficient and accurate troubleshooting to line replacement level |
| | 3.3 | Specialist advice is obtained, where required, to assist with the troubleshooting process |
| | 3.4 | System faults are located and the causes of the faults are clearly identified and correctly recorded in maintenance documentation, where required, and in accordance with standard enterprise procedures |
| | 3.5 | Rectification requirements are determined |
4. | Remove and install basic aircraft electrical system components | 4.1 | System is rendered safe and prepared in accordance with the applicable maintenance manual and isolation tags are fitted, where necessary, to ensure personnel safety |
| | 4.2 | Electrical component removal is carried out in accordance with the applicable maintenance manual while observing all relevant WHS requirements |
| | 4.3 | Required maintenance documentation is completed and processed in accordance with standard enterprise procedures |
| | 4.4 | Removed components are tagged and packaged in accordance with specified procedures |
| | 4.5 | Electrical components to be installed are checked to confirm correct part numbers, modification status, serviceability and shelf life |
| | 4.6 | Physical installation of electrical components is performed in accordance with the applicable maintenance manual, ensuring appropriate adjustment/alignment with mechanical interface is carried out |
| | 4.7 | System is reinstated to correct operational condition in preparation for testing, as necessary |
| | 4.8 | Required maintenance documentation is completed and processed in accordance with standard enterprise procedures |
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:
applying relevant WHS practices, including those relating to gas turbine engine high energy ignition units
using approved maintenance documentation and aircraft publications relating to DC electrical systems
identifying/locating:
DC power generation, regulation, distribution and control systems and components:
generators and starter/generators
regulators
bus bars
circuit breakers and fuses
wiring
piston engine ignition and starting systems and components
magnetos or coils
starter motors
ignition switches/start switches
ignition harnesses
low tension wiring
spark plugs
auxiliary starting devices
gas turbine engine ignition and starting systems (where applicable to the enterprise):
starter motors and starter/generators
high energy ignition units
control units
switches
batteries and associated mounting equipment, including related anti-vibration aids
motors and actuators in basic DC electrical systems
correctly connecting DC generators, alternator/rectifier generators and starter/generators
recognising system and component defects/external damage, correct installation, connection of plugs, terminations, attaching hardware (including cabling/harnesses) and security in:
DC power generation systems including regulation, distribution and control
battery installations
piston engine ignition and starting systems
gas turbine engine ignition and starting systems (where applicable to the enterprise)
internal/external lighting systems, including controls
motors and actuators in basic DC electrical systems
applying logic processes, taking and interpreting electrical measurements, using test equipment and appropriate wiring diagrams and manuals to isolate malfunctions in the above systems
performing system functional tests and checks to isolate system faults and assess post-maintenance serviceability.
It is essential that system testing procedures, cleanliness requirements and safety precautions applicable to the electrical system being maintained are fully observed, understood and complied with. Ability to interpret inspection procedures and specifications (allowable limits) and apply them in practice across a range of inspection, testing and troubleshooting applications (including the timely involvement of supervisors or other trades) is critical.
Evidence of transferability of skills and knowledge related to inspection, testing and troubleshooting and component removal and installation is essential. This is to be demonstrated through application across a range of aircraft electrical systems and components listed in the Assessment Conditions.
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
DC electrical principles:
properties of permanent magnets
precautions for the care and storage of permanent magnets
properties of electromagnets
primary and secondary cells
aircraft battery types, construction, care and safety
resistor characteristics
fuses and circuit breakers
fundamental DC circuits
inductive circuits
capacitive circuits
basic fault-finding principles
general construction, operating characteristics and applications for aircraft:
DC generators
alternator/rectifier generators
DC motors including starter motors
starter/generators
DC actuators (linear and rotary)
gas turbine high energy ignition system components and related safety precautions
lighting systems
the basic layout (block diagram level), function and operation of the systems listed in the Range of Conditions
electrical system maintenance requirements and troubleshooting procedures
relevant WHS practices, including those relating to gas turbine engine high energy ignition units
relevant maintenance manuals
relevant regulatory requirements and standard procedures.
Competency should be assessed in the work environment or simulated work environment using tools and equipment specified in maintenance documentation. It is also expected that general-purpose tools and test equipment found in most routine situations would be used where appropriate.
The application of testing procedures should clearly indicate knowledge of system operation, the relationship of individual components and the links with other systems (if applicable) within the limits of the aircraft/system fault-finding guide before undertaking any action. The work plan should take account of applicable safety and quality requirements in accordance with the industry and regulatory standards.
The following conditions of assessment represent the requirements of the Regulators (ADF and CASA) and maintenance stakeholders and must be rigorously observed.
A person cannot be assessed as competent until it can be demonstrated to the satisfaction of the workplace assessor that the relevant elements and performance criteria of the unit of competency are being achieved under routine supervision on electrical looms, cables and connection hardware, and on each of the following systems and on at least one (1) major component/line replaceable unit (LRU) in each case:
DC power generation, regulation and distribution systems
piston engine and gas turbine engine ignition and starting systems (gas turbine may be omitted where not applicable to the enterprise)
DC electrical systems, such as flaps, including related motors and actuators
aircraft lighting
aircraft main battery (competency may be demonstrated through the performance of a battery check).
Component removal and installation competencies are to be demonstrated on at least one (1) component from each of:
DC generators, and alternator/rectifier generators, and components of related single generator regulation and distribution systems
motors
actuators
piston engine and gas turbine engine ignition and starting system components (gas turbine may be omitted where not applicable to the enterprise)
aircraft batteries
aircraft lighting components such as bulbs, lenses, switches and rheostats .
This shall be established via the records in the Log of Industrial Experience and Achievement or, where appropriate, an equivalent Industry Evidence Guide (for details refer to the Companion Volume Assessment Guidelines).
Assessors must satisfy the requirements of the National Vocational Education and Training Regulator (Australian Skills Quality Authority, or its successors).
Where the unit is to be used for CASA licensing purposes the Assessor must also meet the criteria specified in the CASR Part 147 Manual of Standards.