Unit of Competency Mapping – Information for Teachers/Assessors – Information for Learners

AVIY0032 Mapping and Delivery Guide
Apply RPAS payload and configuration management principles

Version 1.0
Issue Date: May 2024


Qualification -
Unit of Competency AVIY0032 - Apply RPAS payload and configuration management principles
Description
Employability Skills
Learning Outcomes and Application This unit involves the skills and knowledge required to manage unmanned aerial vehicle (UAV) performance and load in compliance with relevant regulatory requirements of the Civil Aviation Safety Authority (CASA) and national operating standards.It includes applying mass and balance control to flight planning, identifying constraints affecting load planning and planning an aircraft load. It also includes applying principles of aircraft balance and longitudinal stability to load planning, identifying aircraft structural limitations, and identifying aircraft mass and performance planning safety factors. It also includes determining aircraft mass and speed limitations, calculating launch requirements, calculating climb performance, calculating landing requirements, and determining aircraft buffet boundaries and speeds.This unit addresses aviation technical skill requirements (physical, mental and task-management abilities) related to route planning and navigation duties of flight dispatch personnel and contributes to safe and effective performance in complex aviation operational environments.Operations are conducted as part of commercial or military aircraft activities across a variety of operational contexts within the Australian aviation industry.Work is performed independently or under limited supervision as a single operator or within a team environment.Licensing, legislative, regulatory or certification requirements are applicable to this unit.
Duration and Setting X weeks, nominally xx hours, delivered in a classroom/online/blended learning setting.
Prerequisites/co-requisites
Competency Field H – Route Planning and Navigation
Development and validation strategy and guide for assessors and learners Student Learning Resources Handouts
Activities 		Slides
PPT 		Assessment 1 Assessment 2 Assessment 3 Assessment 4
Elements of Competency Performance Criteria              
Element: Plan an aircraft load
  • Aircraft design and mass, launch, landing and zero-fuel weights (ZFW) are reviewed and applied to load planning activities
  • Operational load planning factors affecting a restriction on mass, operational (phase of flight), environmental, equipment, airspace and area of operations are considered and applied as required to aircraft load planning
  • Aircraft operating mass and passengers mass limits are summarised within load planning documentation
  • 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
  • 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
  • Manual load sheet, including payload location and last-minute changes, is prepared
  • Load sheet, including payload location and last-minute changes, is interpreted and automated
       
Element: Apply mass and balance control to flight planning
  • Components of mass, balance and control are considered and applied in flight planning activities
       
Element: Mass and control limitations are included in flight planning calculations
       
Element: Required fuel and payload quantities, including minimum fuel reserves, maximum allowable payloads and fuel quantity limitations, are considered when calculating mass and balance
       
Element: Calculated aircraft mass centre of gravity (CG) is within aircraft limits and is established for take-off, cruise and fuel economy calculation purposes
       
Element: Ground handling of baggage and cargo is minimised through load distribution and loading sequence planning
       
Element: Mass and CG is derived and calculated using basic data methods and is applied to flight planning calculations
       
Element: Comprehensive load sheet is compiled that includes all required flight performance and load planning data
       
Element: Identify constraints affecting load planning
  • Configuration of payload, mass and control limitations are considered
       
Element: Aircraft, route, fuel required, and performance limitation planning factors are assessed for potential constraints to load planning activities
       
Element: Hazards are identified, risks assessed, and hazard management implemented
       
Element: Operator advance index tables and potential impact of mass and fuel minima during seasonal change are identified and considered
       
Element: Unusual conditions when advanced allotment tables may be exceeded, the operational impacts and associated contingency planning factors are considered
       
Element: Load planning constraints and limitations are prioritised based on operational and regulatory requirements
  • Aircraft design and mass, launch, landing and zero-fuel weights (ZFW) are reviewed and applied to load planning activities
       
Element: Operational load planning factors affecting a restriction on mass, operational (phase of flight), environmental, equipment, airspace and area of operations are considered and applied as required to aircraft load planning
       
Element: Aircraft operating mass and passengers mass limits are summarised within load planning documentation
       
Element: 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
       
Element: 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
       
Element: Manual load sheet, including payload location and last-minute changes, is prepared
       
Element: Load sheet, including payload location and last-minute changes, is interpreted and automated
       
Element: Apply principles of aircraft balance and longitudinal stability to load planning
  • Load planning factors, including balance, CG (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
       
Element: Aircraft point of balance is calculated using aircraft data and aircraft balance principles, and is applied to load planning calculations
       
Element: Identify aircraft structural limitations
  • Satisfactory aircraft balance calculations are achieved ensuring aircraft is safely loaded, structural integrity has not been exceeded and load is capable of being satisfactorily restrained
       
Element: 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
       
Element: Maximum allowable package sizes are determined using aircraft tables
       
Element: Methods of restraint and the effect on passengers and crew, damage and CG, including principles of inertia and forces applied to load, are considered and applied to load planning activities
       
Element: Advantages and limitations of certified and non-certified cargo loads and containers, and methods of load security are considered when calculating aircraft load limitations
       
Element: Identify aircraft mass and performance planning safety factors
  • Aircraft certification considerations, including structural strength, loads, speed limitations, operating environment, performance capability, landing area lengths and terrain, are considered and applied to aircraft mass and performance calculations
       
Element: Aircraft certification standards, including categories, state/territory-based variations, operating mass or CG never exceeding limits, and aircraft flight manual restrictions are considered and applied to aircraft mass and performance calculations
       
Element: 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
       
Element: Determine aircraft mass and speed limitations
  • 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
       
Element: 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
       
Element: Calculate take-off requirements
  • Take-off requirements are determined considering clearways and stop-ways requirements and alternatives to balanced field length methods
       
Element: Critical engine failure speeds, flap positions and reduced thrust take-off stopping distance at critical engine failure speeds is calculated
       
Element: Calculate climb performance
  • Take-off flight path; climb segments, including terrain and obstacle avoidance; and the effects of mass, altitude and temperature; are determined
       
Element: 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
       
Element: 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
       
Element: Calculate landing area requirements
  • Landing distance requirements are determined, including effect of aircraft configuration, available stopping distance, and effects of marginal conditions
       
Element: Landing distance based on varying environmental conditions, effect of obstacles and braking systems is calculated
       
Element: Determine aircraft buffet boundary and speeds
  • Aircraft buffet characteristics, and the effect of variations of a given mass and speed are identified and applied to aircraft performance calculations
       
Element: Permissible buffet for a range of aircraft speeds for combinations of mass and altitude, including safe operating margins, is calculated
       

Submission Requirements

List each assessment task's title, type (eg project, observation/demonstration, essay, assignment, checklist) and due date here

Assessment task 1: [title]      Due date:

(add new lines for each of the assessment tasks)

Assessment Tasks

Copy and paste from the following data to produce each assessment task. Write these in plain English and spell out how, when and where the task is to be carried out, under what conditions, and what resources are needed. Include guidelines about how well the candidate has to perform a task for it to be judged satisfactory.

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

Copy and paste from the following performance criteria to create an observation checklist for each task. When you have finished writing your assessment tool every one of these must have been addressed, preferably several times in a variety of contexts. To ensure this occurs download the assessment matrix for the unit; enter each assessment task as a column header and place check marks against each performance criteria that task addresses.

Observation Checklist

Tasks to be observed according to workplace/college/TAFE policy and procedures, relevant legislation and Codes of Practice Yes No Comments/feedback
Aircraft design and mass, launch, landing and zero-fuel weights (ZFW) are reviewed and applied to load planning activities 
Operational load planning factors affecting a restriction on mass, operational (phase of flight), environmental, equipment, airspace and area of operations are considered and applied as required to aircraft load planning 
Aircraft operating mass and passengers mass limits are summarised within load planning documentation 
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 
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 
Manual load sheet, including payload location and last-minute changes, is prepared 
Load sheet, including payload location and last-minute changes, is interpreted and automated 
Components of mass, balance and control are considered and applied in flight planning activities 
 
 
 
 
 
 
Configuration of payload, mass and control limitations are considered 
 
 
 
 
Aircraft design and mass, launch, landing and zero-fuel weights (ZFW) are reviewed and applied to load planning activities 
 
 
 
 
 
 
Load planning factors, including balance, CG (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 
 
Satisfactory aircraft balance calculations are achieved ensuring aircraft is safely loaded, structural integrity has not been exceeded and load is capable of being satisfactorily restrained 
 
 
 
 
Aircraft certification considerations, including structural strength, loads, speed limitations, operating environment, performance capability, landing area lengths and terrain, are considered and applied to aircraft mass and performance calculations 
 
 
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 
 
Take-off requirements are determined considering clearways and stop-ways requirements and alternatives to balanced field length methods 
 
Take-off flight path; climb segments, including terrain and obstacle avoidance; and the effects of mass, altitude and temperature; are determined 
 
 
Landing distance requirements are determined, including effect of aircraft configuration, available stopping distance, and effects of marginal conditions 
 
Aircraft buffet characteristics, and the effect of variations of a given mass and speed are identified and applied to aircraft performance calculations 
 

Forms

Assessment Cover Sheet

AVIY0032 - Apply RPAS payload and configuration management principles
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Assessment Record Sheet

AVIY0032 - Apply RPAS payload and configuration management principles

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