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Evidence Guide: AVIH0003 - Manage aircraft performance and load

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!

From the Wiki University

 

AVIH0003 - Manage aircraft performance and load

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

Apply mass and balance control to flight planning

  1. Components of mass, balance and control are considered and applied in flight planning activities
  2. Mass and control limitations are included in flight planning calculations
  3. Required fuel and payload quantities, including minimum fuel reserves, maximum allowable payloads and fuel quantity limitations are considered when calculating mass and balance
  4. Calculated aircraft mass centre of gravity is within aircraft limits and is established for take-off, cruise and fuel economy calculation purposes
  5. Ground handling of baggage and cargo is minimised through load distribution and loading sequence planning
  6. Mass and centre of gravity is derived and calculated using basic data methods and is applied to flight planning calculations
  7. Comprehensive loadsheet is compiled that includes all required flight performance and load planning data
Components of mass, balance and control are considered and applied in flight planning activities

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Mass and control limitations are included in flight planning calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Required fuel and payload quantities, including minimum fuel reserves, maximum allowable payloads and fuel quantity limitations are considered when calculating mass and balance

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Calculated aircraft mass centre of gravity is within aircraft limits and is established for take-off, cruise and fuel economy calculation purposes

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Ground handling of baggage and cargo is minimised through load distribution and loading sequence planning

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Mass and centre of gravity is derived and calculated using basic data methods and is applied to flight planning calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Comprehensive loadsheet is compiled that includes all required flight performance and load planning data

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Identify constraints affecting load planning

  1. Implications of advanced sales on payload, mass and control limitations are considered
  2. Aircraft, route, fuel required and performance limitation planning factors are assessed for potential constraints to load planning activities
  3. Hazards are identified, risks are assessed and hazard management is implemented
  4. Operator advance index tables and potential impact of mass and fuel minima during seasonal change are identified and considered
  5. Unusual conditions when advanced allotment tables may be exceeded, the operational impacts, and associated contingency planning factors are considered
  6. Load planning constraints and limitations are prioritised based on operational and regulatory requirements
Implications of advanced sales on payload, mass and control limitations are considered

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Aircraft, route, fuel required and performance limitation planning factors are assessed for potential constraints to load planning activities

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Hazards are identified, risks are assessed and hazard management is implemented

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Operator advance index tables and potential impact of mass and fuel minima during seasonal change are identified and considered

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Unusual conditions when advanced allotment tables may be exceeded, the operational impacts, and associated contingency planning factors are considered

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Load planning constraints and limitations are prioritised based on operational and regulatory requirements

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Plan an aircraft load

  1. Aircraft design and mass, taxi, take-off, landing and zero-fuel weights (ZFW) are reviewed and applied to load planning activities
  2. Operational load planning factors affecting a restriction on mass, operational (phase of flight), environmental, equipment, airspace and airport/aerodrome are considered and applied as required to aircraft load planning
  3. Aircraft operating mass and passengers mass limits are summarised within load planning documentation
  4. Mass of minimum fuel based on ZFW, quantity, fuel type and specific gravity (including fuel quantity conversions) are reviewed and applied to load planning calculations
  5. Available payload based on specific conditions affecting a flight including maximum take-off weight (MTOW), regulated take-off weight (RTOW), minimum fuel and taxi fuel requirements are determined
  6. Manual loadsheet including payload location and last minute changes is prepared
  7. Loadsheet including payload location and last minute changes is interpreted and automated
Aircraft design and mass, taxi, take-off, landing and zero-fuel weights (ZFW) are reviewed and applied to load planning activities

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Operational load planning factors affecting a restriction on mass, operational (phase of flight), environmental, equipment, airspace and airport/aerodrome are considered and applied as required to aircraft load planning

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Aircraft operating mass and passengers mass limits are summarised within load planning documentation

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Mass of minimum fuel based on ZFW, quantity, fuel type and specific gravity (including fuel quantity conversions) are reviewed and applied to load planning calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Available payload based on specific conditions affecting a flight including maximum take-off weight (MTOW), regulated take-off weight (RTOW), minimum fuel and taxi fuel requirements are determined

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Manual loadsheet including payload location and last minute changes is prepared

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Loadsheet including payload location and last minute changes is interpreted and automated

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Apply principles of aircraft balance and longitudinal stability to load planning

  1. Load planning factors including balance, centre of gravity (variations), balance on the ground, principles of lift and centre of pressure, mean aerodynamic chord (MAC) and functions of stabilisers are identified and considered when calculating aircraft performance and load
  2. Aircraft point of balance is calculated using aircraft data and aircraft balance principles, and is applied to load planning calculations
Load planning factors including balance, centre of gravity (variations), balance on the ground, principles of lift and centre of pressure, mean aerodynamic chord (MAC) and functions of stabilisers are identified and considered when calculating aircraft performance and load

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Aircraft point of balance is calculated using aircraft data and aircraft balance principles, and is applied to load planning calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Identify aircraft structural limitations

  1. Satisfactory aircraft balance calculations are achieved ensuring aircraft is safely loaded, floor strengths have not been exceeded and load/cargo is capable of being satisfactorily restrained
  2. Fuselage structural limits over, forward and aft of the wing, and mass limitations for associated loading zones are considered and applied to load planning activities
  3. Maximum allowable package sizes are determined using aircraft tables
  4. Methods of restraint and the effect on passengers and crew, damage and centre of gravity (CG), including principles of inertia, and forces applied to load are considered and applied to load planning activities
  5. Advantages and limitations of certified and non-certified cargo pallets and containers, and methods of load security are considered when calculating aircraft load limitations
Satisfactory aircraft balance calculations are achieved ensuring aircraft is safely loaded, floor strengths have not been exceeded and load/cargo is capable of being satisfactorily restrained

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Fuselage structural limits over, forward and aft of the wing, and mass limitations for associated loading zones are considered and applied to load planning activities

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Maximum allowable package sizes are determined using aircraft tables

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Methods of restraint and the effect on passengers and crew, damage and centre of gravity (CG), including principles of inertia, and forces applied to load are considered and applied to load planning activities

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Advantages and limitations of certified and non-certified cargo pallets and containers, and methods of load security are considered when calculating aircraft load limitations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Identify aircraft mass and performance planning safety factors

  1. Aircraft certification considerations including structural strength, loads, speed limitations, operating environment, performance capability, runway lengths and terrain are considered and applied to aircraft mass and performance calculations
  2. Aircraft certification standards (including categories, statebased variations, operating mass or CG never exceeding limits), and aircraft flight manual restrictions are considered and applied to aircraft mass and performance calculations
  3. Environmental considerations (including certified aircraft operating envelope, pressurisation capabilities, system limitations and aircraft flight manual envelope charts) are considered and applied to aircraft performance calculations
Aircraft certification considerations including structural strength, loads, speed limitations, operating environment, performance capability, runway lengths and terrain are considered and applied to aircraft mass and performance calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Aircraft certification standards (including categories, statebased variations, operating mass or CG never exceeding limits), and aircraft flight manual restrictions are considered and applied to aircraft mass and performance calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Environmental considerations (including certified aircraft operating envelope, pressurisation capabilities, system limitations and aircraft flight manual envelope charts) are considered and applied to aircraft performance calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Determine aircraft mass and speed limitations

  1. Positive and negative load factor limitations including normal and ultimate (structural), speed limitations and differing express terms of speed are considered and applied to aircraft performance calculations
  2. Boundaries of aircraft operating envelope for a specific mass are determined using flight strength diagrams, illustrating effect of wind gusts, margins of speed limits, and turbulence penetration considerations
Positive and negative load factor limitations including normal and ultimate (structural), speed limitations and differing express terms of speed are considered and applied to aircraft performance calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Boundaries of aircraft operating envelope for a specific mass are determined using flight strength diagrams, illustrating effect of wind gusts, margins of speed limits, and turbulence penetration considerations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Calculate take-off runway requirements

  1. Turbo-jet aircraft take-off requirements are determined considering clearways and stop-ways, runway requirements and alternatives to balanced field length methods
  2. Critical engine failure speeds, flap positons and reduced thrust take-off stopping distance at critical engine failure speeds is calculated
Turbo-jet aircraft take-off requirements are determined considering clearways and stop-ways, runway requirements and alternatives to balanced field length methods

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Critical engine failure speeds, flap positons and reduced thrust take-off stopping distance at critical engine failure speeds is calculated

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Calculate climb performance

  1. Take-off flight path, climb segments including terrain and obstacle avoidance, and the effects of mass, altitude and temperature are determined
  2. En route considerations affecting climb performance such as take-off mass, en route alternate selection and terrain are considered and applied to aircraft performance calculations
  3. Approach and landing requirement planning factors including terrain and obstacle avoidance, and effects of mass, altitude and temperature are considered and applied to aircraft performance calculations
Take-off flight path, climb segments including terrain and obstacle avoidance, and the effects of mass, altitude and temperature are determined

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

En route considerations affecting climb performance such as take-off mass, en route alternate selection and terrain are considered and applied to aircraft performance calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Approach and landing requirement planning factors including terrain and obstacle avoidance, and effects of mass, altitude and temperature are considered and applied to aircraft performance calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Calculate landing runway requirements

  1. Runway landing distance requirements are determined, including effect of aircraft configuration, available stopping distance, and effects of marginal conditions
  2. Landing distance based on varying environmental conditions, effect of obstacles and braking systems is calculated
Runway landing distance requirements are determined, including effect of aircraft configuration, available stopping distance, and effects of marginal conditions

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Landing distance based on varying environmental conditions, effect of obstacles and braking systems is calculated

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Determine aircraft buffet boundary and speeds

  1. Aircraft buffet characteristics, and the effect of variations of a given mass and speed are identified and applied to aircraft performance calculations
  2. Permissible buffet for a range of aircraft speeds for combinations of mass and altitude, including safe operating margins is calculated
Aircraft buffet characteristics, and the effect of variations of a given mass and speed are identified and applied to aircraft performance calculations

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Permissible buffet for a range of aircraft speeds for combinations of mass and altitude, including safe operating margins is calculated

Completed
Date:

Teacher:		 Evidence:

 

 

 

 

 

 

 

Assessed

Teacher: ___________________________________ Date: _________

Signature: ________________________________________________

Comments:

 

 

 

 

 

 

 

 

Instructions to Assessors

Evidence Guide

ELEMENTS

PERFORMANCE CRITERIA

Elements describe the essential outcomes.

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

1

Apply mass and balance control to flight planning

1.1

Components of mass, balance and control are considered and applied in flight planning activities

1.2

Mass and control limitations are included in flight planning calculations

1.3

Required fuel and payload quantities, including minimum fuel reserves, maximum allowable payloads and fuel quantity limitations are considered when calculating mass and balance

1.4

Calculated aircraft mass centre of gravity is within aircraft limits and is established for take-off, cruise and fuel economy calculation purposes

1.5

Ground handling of baggage and cargo is minimised through load distribution and loading sequence planning

1.6

Mass and centre of gravity is derived and calculated using basic data methods and is applied to flight planning calculations

1.7

Comprehensive loadsheet is compiled that includes all required flight performance and load planning data

2

Identify constraints affecting load planning

2.1

Implications of advanced sales on payload, mass and control limitations are considered

2.2

Aircraft, route, fuel required and performance limitation planning factors are assessed for potential constraints to load planning activities

2.3

Hazards are identified, risks are assessed and hazard management is implemented

2.4

Operator advance index tables and potential impact of mass and fuel minima during seasonal change are identified and considered

2.5

Unusual conditions when advanced allotment tables may be exceeded, the operational impacts, and associated contingency planning factors are considered

2.6

Load planning constraints and limitations are prioritised based on operational and regulatory requirements

3

Plan an aircraft load

3.1

Aircraft design and mass, taxi, take-off, landing and zero-fuel weights (ZFW) are reviewed and applied to load planning activities

3.2

Operational load planning factors affecting a restriction on mass, operational (phase of flight), environmental, equipment, airspace and airport/aerodrome are considered and applied as required to aircraft load planning

3.3

Aircraft operating mass and passengers mass limits are summarised within load planning documentation

3.4

Mass of minimum fuel based on ZFW, quantity, fuel type and specific gravity (including fuel quantity conversions) are reviewed and applied to load planning calculations

3.5

Available payload based on specific conditions affecting a flight including maximum take-off weight (MTOW), regulated take-off weight (RTOW), minimum fuel and taxi fuel requirements are determined

3.6

Manual loadsheet including payload location and last minute changes is prepared

3.7

Loadsheet including payload location and last minute changes is interpreted and automated

4

Apply principles of aircraft balance and longitudinal stability to load planning

4.1

Load planning factors including balance, centre of gravity (variations), balance on the ground, principles of lift and centre of pressure, mean aerodynamic chord (MAC) and functions of stabilisers are identified and considered when calculating aircraft performance and load

4.2

Aircraft point of balance is calculated using aircraft data and aircraft balance principles, and is applied to load planning calculations

5

Identify aircraft structural limitations

5.1

Satisfactory aircraft balance calculations are achieved ensuring aircraft is safely loaded, floor strengths have not been exceeded and load/cargo is capable of being satisfactorily restrained

5.2

Fuselage structural limits over, forward and aft of the wing, and mass limitations for associated loading zones are considered and applied to load planning activities

5.3

Maximum allowable package sizes are determined using aircraft tables

5.4

Methods of restraint and the effect on passengers and crew, damage and centre of gravity (CG), including principles of inertia, and forces applied to load are considered and applied to load planning activities

5.5

Advantages and limitations of certified and non-certified cargo pallets and containers, and methods of load security are considered when calculating aircraft load limitations

6

Identify aircraft mass and performance planning safety factors

6.1

Aircraft certification considerations including structural strength, loads, speed limitations, operating environment, performance capability, runway lengths and terrain are considered and applied to aircraft mass and performance calculations

6.2

Aircraft certification standards (including categories, statebased variations, operating mass or CG never exceeding limits), and aircraft flight manual restrictions are considered and applied to aircraft mass and performance calculations

6.3

Environmental considerations (including certified aircraft operating envelope, pressurisation capabilities, system limitations and aircraft flight manual envelope charts) are considered and applied to aircraft performance calculations

7

Determine aircraft mass and speed limitations

7.1

Positive and negative load factor limitations including normal and ultimate (structural), speed limitations and differing express terms of speed are considered and applied to aircraft performance calculations

7.2

Boundaries of aircraft operating envelope for a specific mass are determined using flight strength diagrams, illustrating effect of wind gusts, margins of speed limits, and turbulence penetration considerations

8

Calculate take-off runway requirements

8.1

Turbo-jet aircraft take-off requirements are determined considering clearways and stop-ways, runway requirements and alternatives to balanced field length methods

8.2

Critical engine failure speeds, flap positons and reduced thrust take-off stopping distance at critical engine failure speeds is calculated

9

Calculate climb performance

9.1

Take-off flight path, climb segments including terrain and obstacle avoidance, and the effects of mass, altitude and temperature are determined

9.2

En route considerations affecting climb performance such as take-off mass, en route alternate selection and terrain are considered and applied to aircraft performance calculations

9.3

Approach and landing requirement planning factors including terrain and obstacle avoidance, and effects of mass, altitude and temperature are considered and applied to aircraft performance calculations

10

Calculate landing runway requirements

10.1

Runway landing distance requirements are determined, including effect of aircraft configuration, available stopping distance, and effects of marginal conditions

10.2

Landing distance based on varying environmental conditions, effect of obstacles and braking systems is calculated

11

Determine aircraft buffet boundary and speeds

11.1

Aircraft buffet characteristics, and the effect of variations of a given mass and speed are identified and applied to aircraft performance calculations

11.2

Permissible buffet for a range of aircraft speeds for combinations of mass and altitude, including safe operating margins is calculated

Required Skills and Knowledge

ELEMENTS

PERFORMANCE CRITERIA

Elements describe the essential outcomes.

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

1

Apply mass and balance control to flight planning

1.1

Components of mass, balance and control are considered and applied in flight planning activities

1.2

Mass and control limitations are included in flight planning calculations

1.3

Required fuel and payload quantities, including minimum fuel reserves, maximum allowable payloads and fuel quantity limitations are considered when calculating mass and balance

1.4

Calculated aircraft mass centre of gravity is within aircraft limits and is established for take-off, cruise and fuel economy calculation purposes

1.5

Ground handling of baggage and cargo is minimised through load distribution and loading sequence planning

1.6

Mass and centre of gravity is derived and calculated using basic data methods and is applied to flight planning calculations

1.7

Comprehensive loadsheet is compiled that includes all required flight performance and load planning data

2

Identify constraints affecting load planning

2.1

Implications of advanced sales on payload, mass and control limitations are considered

2.2

Aircraft, route, fuel required and performance limitation planning factors are assessed for potential constraints to load planning activities

2.3

Hazards are identified, risks are assessed and hazard management is implemented

2.4

Operator advance index tables and potential impact of mass and fuel minima during seasonal change are identified and considered

2.5

Unusual conditions when advanced allotment tables may be exceeded, the operational impacts, and associated contingency planning factors are considered

2.6

Load planning constraints and limitations are prioritised based on operational and regulatory requirements

3

Plan an aircraft load

3.1

Aircraft design and mass, taxi, take-off, landing and zero-fuel weights (ZFW) are reviewed and applied to load planning activities

3.2

Operational load planning factors affecting a restriction on mass, operational (phase of flight), environmental, equipment, airspace and airport/aerodrome are considered and applied as required to aircraft load planning

3.3

Aircraft operating mass and passengers mass limits are summarised within load planning documentation

3.4

Mass of minimum fuel based on ZFW, quantity, fuel type and specific gravity (including fuel quantity conversions) are reviewed and applied to load planning calculations

3.5

Available payload based on specific conditions affecting a flight including maximum take-off weight (MTOW), regulated take-off weight (RTOW), minimum fuel and taxi fuel requirements are determined

3.6

Manual loadsheet including payload location and last minute changes is prepared

3.7

Loadsheet including payload location and last minute changes is interpreted and automated

4

Apply principles of aircraft balance and longitudinal stability to load planning

4.1

Load planning factors including balance, centre of gravity (variations), balance on the ground, principles of lift and centre of pressure, mean aerodynamic chord (MAC) and functions of stabilisers are identified and considered when calculating aircraft performance and load

4.2

Aircraft point of balance is calculated using aircraft data and aircraft balance principles, and is applied to load planning calculations

5

Identify aircraft structural limitations

5.1

Satisfactory aircraft balance calculations are achieved ensuring aircraft is safely loaded, floor strengths have not been exceeded and load/cargo is capable of being satisfactorily restrained

5.2

Fuselage structural limits over, forward and aft of the wing, and mass limitations for associated loading zones are considered and applied to load planning activities

5.3

Maximum allowable package sizes are determined using aircraft tables

5.4

Methods of restraint and the effect on passengers and crew, damage and centre of gravity (CG), including principles of inertia, and forces applied to load are considered and applied to load planning activities

5.5

Advantages and limitations of certified and non-certified cargo pallets and containers, and methods of load security are considered when calculating aircraft load limitations

6

Identify aircraft mass and performance planning safety factors

6.1

Aircraft certification considerations including structural strength, loads, speed limitations, operating environment, performance capability, runway lengths and terrain are considered and applied to aircraft mass and performance calculations

6.2

Aircraft certification standards (including categories, statebased variations, operating mass or CG never exceeding limits), and aircraft flight manual restrictions are considered and applied to aircraft mass and performance calculations

6.3

Environmental considerations (including certified aircraft operating envelope, pressurisation capabilities, system limitations and aircraft flight manual envelope charts) are considered and applied to aircraft performance calculations

7

Determine aircraft mass and speed limitations

7.1

Positive and negative load factor limitations including normal and ultimate (structural), speed limitations and differing express terms of speed are considered and applied to aircraft performance calculations

7.2

Boundaries of aircraft operating envelope for a specific mass are determined using flight strength diagrams, illustrating effect of wind gusts, margins of speed limits, and turbulence penetration considerations

8

Calculate take-off runway requirements

8.1

Turbo-jet aircraft take-off requirements are determined considering clearways and stop-ways, runway requirements and alternatives to balanced field length methods

8.2

Critical engine failure speeds, flap positons and reduced thrust take-off stopping distance at critical engine failure speeds is calculated

9

Calculate climb performance

9.1

Take-off flight path, climb segments including terrain and obstacle avoidance, and the effects of mass, altitude and temperature are determined

9.2

En route considerations affecting climb performance such as take-off mass, en route alternate selection and terrain are considered and applied to aircraft performance calculations

9.3

Approach and landing requirement planning factors including terrain and obstacle avoidance, and effects of mass, altitude and temperature are considered and applied to aircraft performance calculations

10

Calculate landing runway requirements

10.1

Runway landing distance requirements are determined, including effect of aircraft configuration, available stopping distance, and effects of marginal conditions

10.2

Landing distance based on varying environmental conditions, effect of obstacles and braking systems is calculated

11

Determine aircraft buffet boundary and speeds

11.1

Aircraft buffet characteristics, and the effect of variations of a given mass and speed are identified and applied to aircraft performance calculations

11.2

Permissible buffet for a range of aircraft speeds for combinations of mass and altitude, including safe operating margins is calculated

Evidence required to demonstrate competence in this unit must be relevant to and satisfy all of the requirements of the elements and performance criteria on at least one occasion and include:

adapting to differences in equipment and operating environment in accordance with standard operating procedures

applying basic principles of mass and performance limitations

applying fuel, payload and load considerations while respecting regulatory and company approved requirements

applying knowledge of low and high speed aircraft buffet characteristics and determining speeds at which aircraft buffet is encountered

applying precautions and required action to minimise, control or eliminate identified hazards

applying relevant aeronautical knowledge

calculating aircraft centre of gravity (CG) arithmetically and graphically using practical methods of and within acceptable ranges

calculating balance mass required given unequal lengths of arm of beam balance and mass of one pan

calculating CG of fully loaded aircraft with variable passenger and cargo configurations

calculating moments about aircraft in flight

calculating point of suspension given unequal mass in the pans of a beam balance and total length of beam

communicating effectively with others

completing relevant documentation

determining maximum permissible take-off and landing mass under variable operating conditions

determining permissible mass, altitude and temperature limit data using aircraft operating flight manual in varying conditions

determining take-off and landing runway length and speeds using aircraft operations and flight manual in varying configurations and conditions

developing an International Air Transport Association (IATA) loadsheet based on mass, balance and control components

establishing and applying aircraft climb performance limitations

identifying aircraft mass and performance planning safety factors

identifying and correctly using equipment required to manage aircraft performance and load

implementing contingency plans

implementing work health and safety (WHS)/occupational health and safety (OHS) procedures and relevant regulations

modifying activities depending on workplace contingencies, situations and environments

monitoring and anticipating operational problems and hazards and taking appropriate action

monitoring work activities in terms of planned schedule

operating electronic communications equipment to required protocol

preparing and planning manual and automated loadsheets based on all known operational constraints and considerations

reading, interpreting and following relevant regulations, instructions, procedures, information and signs

reporting and/or rectifying problems, faults and malfunctions promptly, in accordance with workplace procedures

selecting and using required personal protective equipment conforming to industry and WHS/OHS standards

using aircraft flight manual charts and graphs to determine buffet boundaries and safe operating conditions

using aircraft operating environment envelope chart effectively

using operator advanced allotment tables to determine typical values for various routes, aircraft and operational needs

working collaboratively with others

working systematically with required attention to detail without injury to self or others, or damage to goods or equipment.

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

aircraft design mass:

maximum taxi mass

maximum take-off mass

maximum landing mass

maximum zero-fuel mass

aircraft mass, balance and control definitions:

basic operating mass (BOW)

dry operating mass (DOW)

zero-fuel mass (ZFW)

critical engine failure speed V1 characteristics:

mass

runway slope

runway braking coefficient

pressure altitude

temperature

wind component

flap position

definition of aircraft moment

derivation of aircraft data and calculation techniques related to aircraft performance, and load planning factors and considerations

express terms of speed:

indicated airspeed (IAS)

mach number

designed dive speed

maximum operating speed

normal operating speed

IATA loadsheet information requirements and compilation:

flight number

aircraft registration

dry operating mass and dry operating CG

zero fuel mass

zero fuel CG

take off mass CG (MAC %)

landing mass

landing mass CG (MAC %)

passenger distribution

deadload distribution – baggage, cargo, mail

details of dangerous goods (NOTOC)

details of live and perishable cargo

IATA numbering scheme for cargo holds

mass and balance calculations:

graphical

arithmetical

mass x arm = moment

total moments = arm of CG

use of automated systems

maximum payload limitations:

volumetric, floor and loading limitations

ramp unload, reload limitations

CG

dangerous goods

differences between DOW and MZFW

passenger capacity

meaning and calculation of take-off safety speed (V2)

operating mass definitions and application to load planning:

basic operating mass (BOW)

BOW + crew, crew bags, catering, and spares = dry operating mass (DOW)

DOW + payload/passenger load = zero-fuel mass (ZFW)

DOW + take-off fuel = operating mass (OW)

ZFW + payload/passenger load = take-off mass (TOW)

TOW + taxi fuel = taxi mass

TOW – fuel consumed en route = landing mass (LDW)

TOW – take-off fuel = zero-fuel mass (ZFW)

other terminology relevant to aircraft performance calculations not otherwise defined

principles of balance control

principles of mass control

ramp mass or taxi mass:

take-off mass (TOW)

landing mass (LDW).

Range Statement

Range is restricted to essential operating conditions and any other variables essential to the work environment.