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Evidence Guide: MEA277 - Maintain twin engine aircraft electrical systems and components

Student: __________________________________________________

Signature: _________________________________________________

Tips for gathering evidence to demonstrate your skills

The important thing to remember when gathering evidence is that the more evidence the better - that is, the more evidence you gather to demonstrate your skills, the more confident an assessor can be that you have learned the skills not just at one point in time, but are continuing to apply and develop those skills (as opposed to just learning for the test!). Furthermore, one piece of evidence that you collect will not usualy demonstrate all the required criteria for a unit of competency, whereas multiple overlapping pieces of evidence will usually do the trick!

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MEA277 - Maintain twin engine aircraft electrical systems and components

What evidence can you provide to prove your understanding of each of the following citeria?

Inspect twin engine aircraft electrical systems and components

  1. Relevant maintenance documentation and modification status, including system defect reports, where relevant, are used to identify specific inspection requirements
  2. Isolation tags are checked and aircraft configured for safe system inspection and operation in accordance with the applicable maintenance manual while observing all relevant work health and safety (WHS) requirements
  3. Direct current (DC) electrical system is visually or physically checked for external signs of defects in accordance with applicable maintenance manual
  4. Defects are correctly identified and reported
Relevant maintenance documentation and modification status, including system defect reports, where relevant, are used to identify specific inspection requirements

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Isolation tags are checked and aircraft configured for safe system inspection and operation in accordance with the applicable maintenance manual while observing all relevant work health and safety (WHS) requirements

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Direct current (DC) electrical system is visually or physically checked for external signs of defects in accordance with applicable maintenance manual

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Defects are correctly identified and reported

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Test/adjust twin engine aircraft electrical systems

  1. Aircraft and system are prepared in accordance with applicable maintenance manual for the application of power/system operation
  2. Electrical system is functionally tested in accordance with maintenance manual for evidence of serviceability or malfunction
  3. System calibration or adjustments are performed in accordance with maintenance manual, as appropriate
Aircraft and system are prepared in accordance with applicable maintenance manual for the application of power/system operation

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Electrical system is functionally tested in accordance with maintenance manual for evidence of serviceability or malfunction

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

System calibration or adjustments are performed in accordance with maintenance manual, as appropriate

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Troubleshoot twin engine aircraft electrical systems

  1. Available information from maintenance documentation and inspection and test results is used, where necessary, to assist in fault determination
  2. Maintenance manual fault diagnosis guides and logic processes are used to ensure efficient and accurate troubleshooting to line replacement level
  3. Specialist advice is obtained, where required, to assist with the troubleshooting process
  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
  5. Rectification requirements are determined
Available information from maintenance documentation and inspection and test results is used, where necessary, to assist in fault determination

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Maintenance manual fault diagnosis guides and logic processes are used to ensure efficient and accurate troubleshooting to line replacement level

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Specialist advice is obtained, where required, to assist with the troubleshooting process

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

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

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Rectification requirements are determined

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Remove and install twin engine aircraft electrical system components

  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
  2. Electrical component removal is carried out in accordance with the applicable maintenance manual while observing all relevant WHS requirements
  3. Required maintenance documentation is completed and processed in accordance with standard enterprise procedures
  4. Removed components are tagged and packaged in accordance with specified procedures
  5. Electrical components to be installed are checked to confirm correct part numbers, modification status, serviceability and shelf life
  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
  7. System is reinstated to correct operational condition in preparation for testing, as necessary
System is rendered safe and prepared in accordance with the applicable maintenance manual and isolation tags are fitted, where necessary, to ensure personnel safety

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Electrical component removal is carried out in accordance with the applicable maintenance manual while observing all relevant WHS requirements

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Required maintenance documentation is completed and processed in accordance with standard enterprise procedures

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Removed components are tagged and packaged in accordance with specified procedures

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Electrical components to be installed are checked to confirm correct part numbers, modification status, serviceability and shelf life

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Physical installation of electrical components is performed in accordance with the applicable maintenance manual, ensuring appropriate adjustment/alignment with mechanical interface is carried out

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

System is reinstated to correct operational condition in preparation for testing, as necessary

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Required maintenance documentation is completed and processed in accordance with standard enterprise procedures

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Assessed

Teacher: ___________________________________ Date: _________

Signature: ________________________________________________

Comments:

 

 

 

 

 

 

 

 

Instructions to Assessors

Evidence Guide

Elements describe the essential outcomes.

Performance criteria describe the performance needed to demonstrate achievement of the element.

1.

Inspect twin engine 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 while observing all relevant work health and safety (WHS) requirements

1.3

Direct current (DC) electrical system is visually or physically checked for external signs of defects in accordance with applicable maintenance manual

1.4

Defects are correctly identified and reported

2.

Test/adjust twin engine 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 twin engine 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 twin engine 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

Required Skills and Knowledge

Elements describe the essential outcomes.

Performance criteria describe the performance needed to demonstrate achievement of the element.

1.

Inspect twin engine 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 while observing all relevant work health and safety (WHS) requirements

1.3

Direct current (DC) electrical system is visually or physically checked for external signs of defects in accordance with applicable maintenance manual

1.4

Defects are correctly identified and reported

2.

Test/adjust twin engine 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 twin engine 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 twin engine 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

using approved maintenance documentation and aircraft publications relating to twin engine aircraft electrical systems

identifying/locating:

DC multi-generator power generation, regulation, distribution and control systems and components, i.e. regulators and bus bars

electrical propeller control systems and components, such as feathering and synchronising systems

batteries in dual battery installations and associated mounting equipment, including related anti-vibration aids

fire warning and extinguishing systems and components

identification of halogen (e.g. BCF) fire extinguishers

combustion heating systems

equipment cooling and ventilation

fuel storage and distribution system electrical components

master and central warning systems

correctly connecting DC generators and alternator/rectifier generators in multi-generator systems and paralleling generator output

recognising system and component defects/external damage, correct installation, connection of plugs, terminations, attaching hardware (including cabling/harnesses) and security in the above systems and system components

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:

system testing procedures and paralleling of generator output

the basic layout (block diagram level), function and operation of:

DC multi-generator and alternator/rectifier generator regulation and distribution systems and components

electrical propeller control systems, such as feathering and synchronising systems and system components

dual battery systems and associated mounting equipment, including related anti-vibration aids

fire warning and extinguishing systems and system components, including regulatory requirements relating to halogen (e.g. BCF) fire extinguishers

combustion heating systems and system components

equipment cooling and ventilation systems and system components

fuel storage and distribution systems and system components

master and central warning systems and system components

maintenance requirements and troubleshooting procedures for the above electrical systems

relevant WHS practices

relevant maintenance manuals

relevant regulatory requirements and standard 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.

DC electrical systems include:

DC multi-generator and alternator/rectifier generator regulation and distribution systems and components

Electrical propeller control systems, such as feathering systems (where applicable to the enterprise)

Batteries in dual battery installations and associated mounting equipment, including related anti-vibration aids

Fire warning and extinguishing systems, including handling of halogen fire extinguishers (where applicable to the enterprise)

Combustion heating systems (where applicable to the enterprise)

Equipment cooling and ventilation

Fuel storage and distribution systems

Master and central warning systems (where applicable to the enterprise)

Electrical components include:

Components of multi-generator regulation and distribution systems

Electrical propeller control system components (where applicable to the enterprise)

Batteries in dual battery installations and associated mounting equipment, including related anti-vibration aids

Fire warning and extinguishing system components (where applicable to the enterprise)

Combustion heaters and associated components (where applicable to the enterprise)

Equipment cooling and ventilation components

Fuel storage and distribution system electrical components

Master and central warning system components (where applicable to the enterprise)

Procedures and requirements include:

Industry standard procedures specified by manufacturers, regulatory authorities or the enterprise