(subregulation 2 (1), definition of CASA maintenance schedule)

1.1 An inspection (in this Part called a daily inspection) must be carried out on the aircraft before the aircraft’s first flight on each day on which the aircraft is flown.

1.2 A daily inspection must consist of the making of such of the checks set out in the table at the end of this Part as are applicable to the aircraft.

Table of checks included in a daily inspection

Section 1 General

(1) Check that the ignition switches are off, the mixture control is lean or cut off, the throttle is closed and the fuel selector is on.

(2) Check that the propeller blades are free from cracks, bends and detrimental nicks, that the propeller spinner is secure and free from cracks, that there is no evidence of oil or grease leakage from the propeller hub or actuating cylinder and that the propeller hub, where visible, has no evidence of any defect which would prevent safe operation.

(3) Check that the induction system and all cooling air inlets are free from obstruction.

(4) Check that the engine, where visible, has no fuel or oil leaks and that the exhaust system is secure and free from cracks.

(5) Check that the oil quantity is within the limits specified by the manufacturer for safe operation and that the oil filler cap, dipstick and inspection panels are secure.

(6) Check that the engine cowlings and cowl flaps are secure.

(7) Check that the landing gear tyres are free from cuts or other damage, have no plies exposed and, by visual inspection, are adequately inflated.

(8) Check that the landing gear oleo extensions are within normal static limits and that the landing gear doors are secure.

(9) Check that the wing and fuselage surfaces are free from damage and that the inspection panels, flight control surfaces and flight control devices are secure.

(10) Check that the interplane and centre section struts are free from damage and that the bracing wires are of the correct tension.

(11) Check that the pitot heads and static ports are free from obstruction and that the pitot cover is removed or is free to operate.

(12) Check that the fuel tank filler caps, chains, vents and associated access panels are secure and free from damage.

(13) Check that the empennage surfaces are free from damage and that the control surfaces control cables and control rods, where visible, are secure.

(14) Check that the canard surfaces are free from damage and that the control surfaces, control cables and control rods, where visible, are secure.

(15) Check that the flight controls, the trim systems and the high lift devices operable from the ground have full and free movement in the correct sense.

(16) Check that the radios and antennae are secure and that where visible, radio units and interwiring are secure.

(17) Check that the drain holes are free from obstruction.

(18) Check that there is no snow, frost or ice on the wings, tail surfaces, canards, propeller or windscreen.

(19) Check that each tank sump and fuel filter is free from water and foreign matter by draining a suitable quantity of fuel into a clean transparent container.

(20) Check that the windscreen is clean and free from damage.

(21) Check that the instruments are free from damage, legible and secure.

(22) Check that the seat belts, buckles and inertia reels are free from damage, secure and functioning correctly.

Section 2 Additional items for agricultural aeroplanes

(1) Check that the agricultural equipment is secure.

(2) Check that the dump and fan brake mechanisms are free from obstructions and operate correctly.

Section 3 Additional items for seaplanes

(1) Check that the hull and floats are free from damage, corrosion and water accumulation.

(2) Check that the float attachment struts, bracing wires and attachment fittings are secure and free from damage and corrosion.

(3) Check that the water rudder and its attachments are secure and free from damage and corrosion and that the water rudder has full, free and correct travel.

Part 2 Periodic inspection

2.1 Subject to paragraph 2.2, an inspection (in this Part called a periodic inspection) must consist of the taking of the actions set out in the table at the end of this Part as applicable to the aircraft.

2.2 The holder of a certificate of registration for a class B aircraft may elect to have a section or sections of the periodic inspection carried out on the aircraft at a different time from the other sections.

2.3 A periodic inspection must be carried out on a private aircraft within the period of 1 year from:

(a) the day on which the aircraft’s current certificate of airworthiness was issued; or

(b) the day on which the most recent general maintenance inspection on the aircraft was completed;

whichever is the later.

2.4 Subject to paragraph 2.5, a periodic inspection must be carried out on a class B aircraft that is not a private aircraft within whichever of the following periods expires first:

(a) one year from:

(i) the day on which the aircraft’s current certificate of airworthiness was issued; or

(ii) the day on which the most recent general maintenance inspection on the aircraft was completed;

whichever is the later;

(b) the aircraft has been in service for 100 hours since:

(i) the aircraft’s current certificate of airworthiness was issued; or

(ii) the most recent general maintenance inspection on the aircraft was completed;

whichever occurred later.

2.5 In spite of paragraph 2.4, if the holder of the certificate of registration for a class B aircraft that is not a private aircraft has elected under paragraph 2.2 to have the sections of the periodic inspection carried out on the aircraft at different times, the following provisions have effect:

(a) the first carrying out of each section of the periodic inspection on the aircraft after the election is made must be carried out within whichever of the following periods expires first:

(i) 18 months from:

(A) the day on which the aircraft’s current certificate of airworthiness was issued; or

(B) the day on which the most recent general maintenance inspection on the aircraft was completed;

whichever is the later;

(ii) the aircraft has been in service for 150 hours since:

(A) the aircraft’s current certificate of airworthiness was issued; or

(B) the most recent general maintenance inspection on the aircraft was completed;

whichever occurred later;

(b) each subsequent carrying out of each section of the periodic inspection must be carried out within whichever of the following periods expires first:

(i) the aircraft has been in service for 100 hours since the section concerned was most recently carried out on the aircraft;

(ii) 1 year from the day on which the section concerned was most recently carried out on the aircraft.

2.6 In this Part:

general maintenance inspection means a regular inspection and check of a class B aircraft, its systems and components that:

(a) is required by the aircraft’s maintenance schedule to be carried out at regular intervals; and

(b) is not required to be carried out before the aircraft’s first flight on each day on which the aircraft is flown.

private aircraft means an aircraft:

(a) that is a class B aircraft; and

(b) that has a maximum take off weight of 5700 kg or less; and

(i) the owner of the aircraft; or

(ii) a person to whom the owner has provided the aircraft without receiving any remuneration from the person.

2.7 Unless otherwise indicated in the table, where the table requires a thing to be inspected, the inspection is to be a thorough check made to determine whether the thing will continue to be airworthy until the next periodic inspection.

Table of actions included in a periodic inspection

Section 1 The airframe

(1) Check the external and internal required placards.

Note Reference should be made to the aircraft flight manual and airworthiness directives for the required placards.

(2) Take the following action in relation to the mainplane and empennage (including canards) of the aircraft:

(a) inspect the skins for evidence of wrinkles, buckles, sheared or loose rivets, corrosion, disbonds and general damage;

(b) if the skin is fabric, check the strength of the fabric;

(d) inspect the lift struts, interplane struts, jury struts, spreaders, chafing discs and bracing wires;

(e) inspect the flight control surfaces, slats, spoilers, tabs, flaps, mass balance weight attachments, hinge brackets, tracks and rollers;

(f) inspect the flight control system bellcranks, push pull rods, torque tubes, cables, fairleads, turnbarrells and pulleys;

(g) inspect the wing and empennage to fuselage attachments and surrounding structure;

(h) lubricate as necessary.

(3) Take the following action in relation to the fuselage:

(a) inspect the fuselage skin for evidence of wrinkles, buckles, sheared or loose rivets, corrosion, disbonds and general damage;

(b) inspect the areas around cut‑outs (such as windows and inspection apertures) for cracks and inspect the sealing and fit of all doors and emergency exits;

(d) inspect the strength of the fabric covering on surfaces;

(e) inspect the internal structure;

(f) inspect the locks, latches and hinges of doors, canopy, windows which may be opened and direct vision windows;

(g) check that the windshields and windows are clean and free from crazing, cracking, discoloration, delamination and scratches;

(h) inspect the seats, seat attachments, seat adjustment mechanisms, seat stops, seat belts, safety harnesses and inertia reels;

(j) inspect the control wheels, control columns, rudder pedals, control levers, control system bellcranks, push pull rods, torque tubes and cables;

(k) operate all trim controls through the complete range of travel and check them for correct trim position indication;

(l) inspect the brake master cylinders, brake lines, reservoirs, parking brake linkage and mechanical brake system operating mechanisms;

(m) check the cabin fire extinguisher for correct charge, legibility of operating instructions and condition of locking pin or seal and ensure that the extinguisher has not reached its expiry date;

(n) inspect the heating and fresh air system ducting and outlets and the airflow control valves;

(p) inspect the emergency and flotation equipment and ensure that the equipment has not reached its expiry date;

(q) lubricate as necessary.

(4) Jack the aircraft so that the landing gear is clear of the ground and take the following action:

(a) inspect the undercarriage attachment to the airframe;

(b) inspect the structural members, drag and side braces, compression members, oleo struts, bracing struts and torque links;

(d) inspect the flexible hoses;

(e) inspect the main wheels and tyres and the nose or tail wheels and tyres;

(f) clean the wheel bearings, check that they are free from scoring and brinelling, re‑lubricate them, re‑install them and adjust the bearing pre‑load;

(g) inspect the brake linings or pads and the brake drums or discs;

(h) inspect the brake lines and flexible hoses;

(j) inspect the nosewheel or tailwheel steering mechanism and the shimmy dampener;

(k) inspect the landing gear retraction mechanism, the door and the door operating linkage;

(l) carry out an operational check of the landing gear and doors and ensure that the adjustment of downlocks, overcentre links, uplocks and spring tensions are within the manufacturer’s specified limits;

(m) lubricate as necessary.

(5) Take the following action in relation to the fuel system:

(a) inspect the fuel tanks (where visible), lines, drains, vents, signs, filler caps, filler cap securing chains or cables, filler cap seals and scupper drains;

(b) inspect the fuel selector valves;

(6) Take the following action in relation to the hydraulic system:

(a) remove, clean, and refit the hydraulic system filter element, or if it is unserviceable, install a new filter element;

(b) inspect the hydraulic system reservoirs, powerpack, accumulators, selector valves, hand pump, pipelines and flexible hoses.

(7) Inspect the anti‑icing and de‑icing systems.

(8) Inspect the air‑conditioning evaporator, condenser and compressor and the air‑conditioning ducting, pipelines and units.

(9) Inspect the pressurisation control system and indication system.

(10) Take the following additional action if the aircraft is used in agricultural operations:

(a) inspect the hopper, hopper lid and fasteners, baffles and internal braces;

(b) inspect the spreader, spreader gate and controls;

(d) inspect the emergency dump doors and dump controls.

(11) Take the following additional action if the aircraft is a seaplane:

(a) inspect the external covering and internal structure of the floats or hull;

(b) drain the bilge compartments, refit and re‑lock the drain plugs;

(d) inspect the water rudders, water rudder attachments and water rudder controls, operate and check them for full and free movement in the correct sense and for correct locking;

(e) inspect the protective treatment and finish.

Section 2 The engine

(1) Check the external and internal required placards.

Note Reference should be made to the aircraft flight manual and airworthiness directives for the required placards.

(2) Take the following action in relation to the cowls:

(a) remove, clean and inspect the cowls, cowl flaps and fastenings.

(3) Inspect, and record the compression of, each cylinder.

(4) Take the following action in relation to the engine oil system:

(a) drain the sump or tank and refit the plug and lockwire;

(b) drain the oil cooler and refit and secure the hose;

(i) remove, inspect, clean and refit the pressure filter and lockwire; or

(ii) remove, open and inspect the cartridge full flow filter and fit a new cartridge and lockwire;

(d) inspect the oil cooler, oil temperature control valves, oil tank and attachment fittings;

(e) inspect all oil lines, fittings, breather pipe and the oil cooler shutter;

(f) refill the sump or tank with the recommended grade and quantity of oil.

(5) Take the following action in relation to the ignition system:

(a) remove the spark plugs, clean and inspect them, check the spark plug electrode gap, test the spark plugs and renew them if required;

(b) inspect the spark plug high tension leads and ceramics;

(d) inspect the breaker compartment and cam follower;

(e) inspect the breaker points for serviceability and check the breaker points gap, magneto engine timing and synchronisation;

(f) inspect the switch and earth leads;

(g) refit and torque the spark plugs;

(h) refit the spark plug high tension leads.

(6) Take the following action in relation to the fuel system:

(a) place the fuel selector in the off position;

(b) remove, inspect, clean and refit the fuel strainers and screens and lockwire;

(d) inspect the carburettor or fuel injection components;

(e) inspect the throttle and mixture shafts;

(f) inspect all fuel lines and fittings;

(g) move the fuel selector from the off position;

(h) inspect the auxiliary fuel pump for operation;

(j) pressurise and purge the fuel system and inspect it for leaks.

(7) Take the following action in relation to the induction system:

(a) remove the air filters, clean them, inspect them and refit or renew them;

(b) inspect the hot and alternate air systems for the integrity of seals and for serviceability of valves, shafts, bearings, magnets and hinges;

(8) Take the following action in relation to the exhaust system:

(a) inspect the exhaust system;

(b) remove the muffler shroud, inspect the muffler and refit the shroud;

(d) inspect the cabin heat flexible hoses.

(9) Take the following action in relation to the engine cylinders and baffles:

(a) inspect the cylinder assemblies;

(b) inspect the cylinder base to the crankcase area;

(d) inspect the push rod housing seals.

(10) Take the following action in relation to the crankcase, accessory housing and firewall:

(a) inspect the engine for evidence of oil leakage;

(b) inspect the accessories and drive belts;

(d) inspect the engine mount frame;

(e) inspect the firewall, including seals and sealant.

(11) Inspect the following controls for full and free movement in the correct sense:

(a) throttle, mixture and propeller;

(b) alternate air and carburettor heat;

(d) oil cooler shutter and cowl flap;

(e) turbocharger.

(12) Take the following action in relation to the propeller:

(a) inspect the propeller for static track;

(b) inspect the propeller hub, spinner and backplate;

(d) inspect the blades;

(e) inspect the counterweights;

(f) lubricate the propeller hub;

(g) service the propeller hub with air.

(13) Take the following action in relation to the turbocharger:

(a) remove the heat shield and inspect the turbocharger housing for cracks and oil leaks from the inlet and outlet ports;

(b) inspect the compressor and turbine wheel;

(d) inspect the turbocharger mount;

(e) inspect the transition assembly, the induction and exhaust components and the clamps;

(f) inspect the upper deck pressure manifold and hoses;

(g) lubricate the waste gate linkages and the butterfly valve;

(h) inspect the flexible oil lines;

(j) inspect the controllers and actuators;

(k) inspect the compressor by‑pass door;

(m) refit the heat shield.

(14) Take the following action in relation to the refitting of the cowls:

(a) check that no tooling, rags or other foreign objects remain in the compartment;

(b) inspect the latches and fasteners for correct tension;

(d) inspect the landing and taxi light wiring;

(e) inspect the cowl flap linkage and engine drain lines.

(15) Chock the wheels and check the brake operation, then set the park brake, start the engine and take the following action to determine satisfactory performance in accordance with the manuracturer’s recommendations:

(a) stabilise the engine temperatures and pressures;

(b) check the idle speed, mixture and the magneto switch operation at low engine revolutions per minute;

(d) check the gyro or vacuum pressure indication;

(e) inspect the generator or alternator;

(f) check any unusual engine vibration or noises;

(g) check the engine response to throttle application;

(h) check each magneto and propeller governor for operation;

(j) check the static engine revolutions per minute, manifold pressure and fuel flow;

(k) check the idle cut‑off operation.

(16) After taking the action described above, remove the cowls, inspect the engine for oil, fuel or other fluid leaks, then replace the cowls.

Section 3 The electrical system

(1) Check the external and internal required placards.

Note Reference should be made to the aircraft flight manual and airworthiness directives for the required placards.

(2) Take the following action in relation to the air‑conditioning system:

(a) inspect the distribution system electrical components and interwiring;

(b) inspect the heating and temperature control system;

(d) inspect the air cycle system electrical components and interwiring.

(3) Take the following action in relation to the electrical power:

(a) inspect the AC generation system (including the generator, invertor, regulator, interwiring, control relays and switching);

(b) inspect the AC distribution system;

(c) inspect the DC generation system (including the generator, regulator, transformer or rectifier units, interwiring, control relays and switches);

(d) inspect the DC distribution system (including the busses, circuit breakers or fuses, relays, switches and interwiring);

(e) inspect the starter generator;

(f) inspect the indication systems;

(g) inspect the batteries;

(h) inspect the external power system.

(4) Take the following action in relation to electrical equipment and furnishing:

(a) inspect the flight compartment (including any spare bulbs and fuses);

(b) inspect the passenger compartment (including any spare bulbs and fuses);

(c) inspect the buffet or galley electrical systems, the lavatory compartment electrical systems and the cargo compartment electrical systems.

(5) Take the following action in relation to the following fire protection systems:

(a) inspect the engine fire detection system;

(b) inspect any other fire and smoke detection systems;

(d) inspect any other fire extinguishing systems.

(6) Inspect the electrical components and interwiring of the following flight control systems:

(a) the trim and flap system;

(b) the lift dump and spoiler system;

(7) Inspect the electrical components and interwiring of the fuel distribution and dump system.

(8) Inspect the electrical components and interwiring of the main and auxiliary hydraulic systems.

(9) Inspect the electrical components and interwiring of the following ice and rain protection systems:

(a) the anti/de‑ice systems;

(b) the ice detection and indication systems.

(10) Inspect the systems and components that give audible or visual warnings.

(11) Inspect the electrical components and interwiring of the following landing gear systems:

(a) the extension and retraction systems;

(b) the wheels, brakes and anti‑skid system;

(d) the position and warning system;

(e) the anti‑retract system.

(12) Inspect lights in or on the following areas:

(a) the flight compartment, the passenger compartment and the cargo and service compartment;

(b) the exterior and emergency systems.

(13) Inspect the electrical components and interwiring of pneumatic systems.

(14) Inspect the electrical or electronic control panels, equipment racks and junction boxes.

(15) Inspect the electrical components and interwiring of passenger, crew and cargo doors.

(16) Inspect the electrical components and interwiring of the propeller control and anti/de‑ice systems.

(17) Inspect the electrical harnesses, excluding the ignition harness.

(18) Inspect the electrical components and interwiring of the engine fuel and engine control systems.

(19) Take the following action in relation to the ignition:

(a) inspect the electrical power supplies;

(b) inspect the booster coils, vibrator systems and high energy ignition systems;

(20) Inspect the engine starting system.

Section 4 The instruments

(1) Check the external and internal required placards.

Note Reference should be made to the aircraft flight manual and airworthiness directives for the required placards.

(2) Take the following action in relation to the auto‑flight system:

(a) inspect the autopilot or the automatic flight control system, including the flight director and stability control augmentation;

(b) inspect the yaw damper system;

(3) Inspect the flight control surface indication systems.

(4) Inspect the fuel pressure and quantity indication systems.

(5) Inspect the hydraulic power indication system.

(6) Inspect the ice protection indication system.

(7) Take the following action in relation to indicating and recording systems:

(a) inspect the instrument and control panels;

(b) inspect the independent instrument systems, including the inclinometers, indicators and clocks;

(8) Take the following action in relation to navigation systems:

(a) inspect the flight environment data system, including:

(i) the central air data system; and

(ii) the pitot/static system, including instruments; and

(iii) the stall warning system;

(b) inspect the attitude and direction systems, including:

(i) the magnetic compass; and

(ii) the vertical attitude gyro system; and

(iii) the directional gyro system, including the magnetic referenced systems; and

(iv) the electronic flight instrument system and multi‑function displays;

(i) the inertial navigation and reference systems; and

(ii) the ground proximity warning systems;

(d) inspect the flight management system, including the flight management and performance management systems.

(9) Take the following action in relation to oxygen systems:

(a) inspect the crew, passenger and portable systems;

(b) inspect the indicating systems.

(10) Inspect the pneumatic indicating systems, including the pressure gauge and warning indicators.

(11) Take the following action in relation to the instrument pressure or vacuum system:

(a) inspect the distribution system, including the filters, manifolds, regulating valves, check valves and plumbing;

(b) inspect the indicating system, including the pressure gauge and warning system.

(12) Inspect the engine indicating systems, including fuel flow, temperature and pressure.

(13) Take the following action in relation to the engine indicating systems:

(a) inspect the power indicating system;

(b) inspect the temperature indication system;

(14) Inspect the oil indicating systems, including quantity, pressure and temperature.

(15) Inspect the water injection indicating system.

Section 5 The radio system

(1) Check the interior and exterior required placards including frequency charts.

Note Reference should be made to the aircraft flight manual and airworthiness directives for the required placards.

(2) Take the following action in relation to communication and navigation systems:

(a) inspect the accessible interwiring, plugs and sockets;

(b) inspect the microphones, headsets and cords;

(d) inspect the antennae and antenna insulators;

(e) inspect the Emergency Location Transmitter/Crash Location Beacon batteries for electrolyte leakage and check that the battery life has not expired;

(f) inspect the removable units, mounting racks, vibration isolators and bonding straps;

(g) inspect the switches and controllers;

(h) inspect the radio panel lamps for adequate illumination;

(j) inspect the radio indicators for legibility.

(3) Take the following additional action in relation to communication systems in aircraft equipped for I.F.R. flight:

(a) inspect the HF communication system, including for correct performance by communication with ground stations or by other means;

(b) inspect the VHF communication system, including for correct performance by communication with ground stations or by other means;

(c) inspect the audio system, including for correct operation of all distribution and amplifying systems in all modes of operation.

(4) Take the following action in relation to navigation systems in aircraft equipped for I.F.R. flight:

(a) check the ADF system for accuracy and correct performance in all modes of operation within the limits specified in section 108.34 of the Civil Aviation Orders;

(b) check the VOR system for correct performance within the limits specified in section 108.34 of the Civil Aviation Orders;

(c) check the localiser system for correct performance within the limits specified in section 108.34 of the Civil Aviation Orders;

(d) check the glideslope system for correct performance within the limits specified in section 108.34 of the Civil Aviation Orders;

(e) check the marker system for correct performance in all modes: an approved simulator may be used for these tests;

(f) inspect the DME system;

(g) inspect the Omega/VLF system;

(h) inspect the Doppler navigation system;

(j) inspect the weather radar system;

(k) check the ATC transponder system for correct performance in all modes using the self test facility: select code 0101 for this test;

(l) inspect the radio altimeter system;

(m) inspect the ground proximity warning system; and

(n) inspect the electronic flight instrument system.

Part 3 Post inspection check

3.1 On completion of each section of the inspection, check to ensure that all tools, maintenance equipment or rags have been removed from the aircraft and all panel, access doors, detachable fairings and fillets have been correctly secured.

Schedule 6 CASA system of certification of completion of maintenance

(subregulation 2 (1), definition of CASA system of certification of completion of maintenance)

Part 1 Interpretation

What is meant by the person who carries out the maintenance?

1.1 In this Schedule, a reference to the person who carries out the maintenance does not include a reference to a person who performs maintenance in the course of his or her employment with an employer.

What is meant by performs maintenance?

1.2 In this Schedule, a reference to the person who performs maintenance is a reference to the person who physically does the maintenance.

Supervisor to be responsible for work he or she supervises

1.3 In this Schedule, maintenance performed by a person who is permitted by paragraph 42ZC (3) (b) or 42ZC (4) (c) to carry out maintenance under the supervision of a person who holds an aircraft maintenance engineer licence is to be taken to have been performed by the person who supervised the maintenance and not by the first‑mentioned person.

Part 2 Certification of completion of stages of maintenance and inspections under subregulation 42G (2)

What is to be certified?

2.1 A certification must be made for:

(a) the completion of each stage of maintenance; and

(b) the completion of an inspection under subregulation 42G (2).

Who is to certify?

2.2 A certification for completion of a stage of maintenance or an inspection under subregulation 42G (2) is only to be made by the person who performed the stage of maintenance or the inspection.

Note Regulation 42ZC sets out who can perform maintenance.

Where must a certification be made?

2.3 A certification for completion of a stage of maintenance or an inspection under subregulation 42G (2) must be made:

(a) in the documents kept by the person carrying out the maintenance as a record of the carrying out of the maintenance; or

(b) in the aircraft log book or approved alternative maintenance record for the aircraft.

2.4 If completion of an inspection under subregulation 42G (2) is certified in the documents kept by the person carrying out the maintenance as a record of the carrying out of the maintenance, completion of the inspection must also be certified in the aircraft log book or approved alternative maintenance record for the aircraft.

What must be included in a certification?

2.5 A certification for completion of a stage of maintenance must:

(a) be signed by the person making the certification; and

(b) include the licence number, airworthiness authority number, aircraft welding authority number or certificate of approval number of the person making the certification; and

(e) if an exemption from or variation to a requirement is in force under regulation 42ZS in relation to the aircraft — set out details of the exemption or variation; and

(f) if, in the course of carrying out the maintenance, the weight or balance of the aircraft has been varied — include a record of the variation; and

(g) if a special inspection was carried out — set out what was found as a result of the inspection; and

(h) if, in the course of carrying out the maintenance, an inspection using a non‑destructive testing method was carried out — set out:

(i) the non‑destructive testing method used in carrying out the inspection; and

(ii) the procedure used in carrying out the inspection; and

(iii) what was found as a result of the inspection; and

(j) include a list of airworthiness directives complied with in the course of carrying out the maintenance and set out any defects found in complying with those directives; and

(k) if, in the course of carrying out the maintenance, an aircraft component:

(i) that has had maintenance carried out on it; and

(ii) that was supplied to the person carrying out the maintenance by another person;

was fitted — set out the number of the document that covered the supply of the component in accordance with subregulation 42W (4);

(l) if, in the course of carrying out the maintenance, a time‑lifed aircraft component was fitted or replaced:

(i) identify the component and specify (if applicable) the part number and serial number of the component; and

(ii) list the airworthiness directives that have been complied with in relation to the component; and

(iii) if the component was supplied to the person carrying out the maintenance by another person — set out the number of the document that covered the supply of the component in accordance with subregulation 42W (4); and

(iv) if the component has not been overhauled — set out the time in service of, or the number of cycles completed by, the component since new; and

(v) if the component has been overhauled — set out the time in service of, or number of cycles completed by, the component since its most recent overhaul; and

(vi) if the component is an engine — set out the test performance figures of the engine;

(m) if, in the course of carrying out the maintenance, an aircraft material:

(i) that has had maintenance carried out on it; and

(ii) that was supplied to the person by another person; and

(iii) that is not a fluid;

was used — set out the number of the document that covered the supply of the material in accordance with subregulation 42X (1); and

(n) if a certification is made in the aircraft log book or approved alternative maintenance record for the aircraft — set out:

(i) the time in service of the aircraft since new; and

(ii) if the person making the certification is an employee — the name of the person’s employer and the employer’s certificate of approval number, licence number, airworthiness authority number or aircraft welding authority number.

2.6 A certification for completion of an inspection under subregulation 42G (2) must:

(a) set out which system was inspected; and

(b) be signed by the person making the certification; and

(c) include the licence number or airworthiness authority number or certificate of approval number of the person making the certification; and

(d) include the date on which the certification was made.

Part 3 Certification of co‑ordination of maintenance

When is co‑ordination of maintenance required?

3.1 If more than one person performs stages of maintenance within a category of maintenance, the person carrying out the maintenance must ensure that one of the persons specified in paragraph 3.5 co‑ordinates the carrying out of that category of maintenance.

3.2 If:

(a) maintenance within more than one category of maintenance is carried out on an aircraft; and

(b) more than one person performs that maintenance;

the person carrying out the maintenance must ensure that one of the persons specified in paragraph 3.6 co‑ordinates the carrying out of those categories of maintenance.

What is the responsibility of a person who co‑ordinates maintenance?

3.3 A person who co‑ordinates the carrying out of maintenance within a category of maintenance must ensure:

(a) that each stage of maintenance is performed by a person who is permitted by regulation 42ZC to carry out the maintenance; and

(b) that a certification for the completion of each stage of maintenance is made by the person who performed the stage of maintenance; and

(d) that the carrying out of the category of maintenance is completed.

3.4 A person who co‑ordinates the carrying out of more than one category of maintenance must ensure:

(a) that each category of maintenance that is required to be co‑ordinated by paragraph 3.1 is co‑ordinated by a person specified in paragraph 3.5; and

(b) that a certification for the co‑ordination of each category of maintenance that is required to be co‑ordinated because of paragraph 3.1 is made by the person who co‑ordinated the category of maintenance; and

(d) that the carrying out of the maintenance is completed.

Who must co‑ordinate maintenance within a category of maintenance?

3.5 If the carrying out of maintenance within a category of maintenance is required to be co‑ordinated because of paragraph 3.1, the maintenance must be co‑ordinated by one of the persons who performed a stage of maintenance within that category.

Who must co‑ordinate maintenance across categories?

3.6 If the carrying out of different categories of maintenance is required to be co‑ordinated because of paragraph 3.2, the maintenance must be co‑ordinated by:

(a) if maintenance within a category of maintenance is performed by more than one person — the person co‑ordinating the carrying out of maintenance within that category; or

(b) if maintenance within a category of maintenance is performed by one person — that person; or

When and by whom does co‑ordination of maintenance have to be certified?

3.7 If maintenance is required to be co‑ordinated under this Part, the person who co‑ordinates that maintenance must certify that it was co‑ordinated.

What is the responsibility of a person who certifies for co‑ordination of maintenance?

3.8 The person who co‑ordinates the carrying out of maintenance within a category of maintenance must not certify for co‑ordination of the maintenance unless the person is satisfied:

(a) that each stage of maintenance was performed by a person who is permitted by regulation 42ZC to carry out the maintenance; and

(b) that a certification for completion of each stage of maintenance has been made by the person who performed the stage of maintenance; and

(c) if the person thinks that the carrying out of a stage of maintenance adversely affected another stage of maintenance:

(i) that the affected stage of maintenance is no longer adversely affected; and

(ii) if maintenance was performed — that certification has been made for completion of the maintenance; and

(d) that the carrying out of the category of maintenance has been completed.

3.9 The person who co‑ordinates the carrying out of more than one category of maintenance must not certify for co‑ordination of the maintenance unless the person is satisfied:

(a) that each category of maintenance that was required to be co‑ordinated by paragraph 3.1 was co‑ordinated by a person specified in paragraph 3.5; and

(b) that a certification for the co‑ordination of each category of maintenance that was required to be co‑ordinated by paragraph 3.1 was made by the person who co‑ordinated the maintenance; and

(c) if the person thinks that the carrying out of a category of maintenance adversely affected another category of maintenance:

(i) that the affected category of maintenance is no longer adversely affected; and

(ii) if maintenance was performed — that certification has been made for completion of the maintenance; and

(d) that the carrying out of the maintenance has been completed.

Where must a certification for co‑ordination of maintenance be made?

3.10 A certification for the co‑ordination of maintenance must be made:

(a) in the documents kept by the person carrying out the maintenance as a record of the carrying out of the maintenance; or

(b) in the aircraft log book or approved alternative maintenance record for the aircraft.

What must be included in a certification for co‑ordination of maintenance?

3.11 A certification for the co‑ordination of maintenance must:

(a) be signed by the person making the certification; and

(b) include the licence number, airworthiness authority number or certificate of approval number of the person making the certification; and

(c) if the person making the certification is an employee — state the name of the person’s employer and the employer’s certificate of approval number, licence number or airworthiness authority number; and

(d) if the certification is for the co‑ordination and completion of the carrying out of maintenance within a category of maintenance — set out the category of maintenance; and

(e) if the certification is for the co‑ordination of the carrying out of different categories of maintenance — include a statement to that effect; and

(f) include the date on which the certification was made.

Part 4 Final certification

When must a final certification be made?

4.1 A final certification for completion of maintenance on an aircraft must be made when:

(a) all of the maintenance required to be carried out on an aircraft at a particular time; and

(b) if the maintenance is required to be co‑ordinated by Part 3 — co‑ordination of the maintenance;

has been completed and certified.

Where must a final certification be made?

4.2 A final certification for the completion of maintenance on an aircraft must be made in the aircraft log book or approved alternative maintenance record for the aircraft.

Who must certify?

4.3 A final certification must be made by:

(a) if one person certified for the carrying out of the maintenance — that person; or

(b) if the carrying out of maintenance within one category of maintenance only was co‑ordinated — the person who co‑ordinated the category of maintenance; or

(c) if the carrying out of different categories of maintenance was co‑ordinated — the person who co‑ordinated the maintenance.

What must be included in a final certification?

4.4 If certifications for completion of stages of maintenance are made in the documents kept by the person carrying out the maintenance as a record of the carrying out of the maintenance, a final certification must:

(a) include a brief description of the type of maintenance carried out; and

(b) be signed by the person making the certification; and

(c) include the licence number, airworthiness authority number or certificate of approval number of the person making the certification; and

(d) set out the time in service of the aircraft since new; and

(e) if the person making the certification is an employee — state the name of the person’s employer and the employer’s certificate of approval number, licence number or airworthiness authority number; and

(f) set out details of the approved maintenance data used to carry out the maintenance; and

(g) if an exemption from or variation to a requirement is in force under regulation 42ZS in relation to the aircraft — set out details of the exemption or variation; and

(h) if, in the course of carrying out the maintenance, the weight or balance of the aircraft has been varied — include a record of the variation; and

(j) if a special inspection was carried out — set out what was found as a result of the inspection; and

(k) if, in the course of carrying out the maintenance, an inspection using a non‑destructive testing method was carried out — set out:

(i) the non‑destructive testing method used in carrying out the inspection; and

(ii) the procedure used in carrying out the inspection; and

(iii) what was found as a result of the inspection; and

(l) include a list of airworthiness directives complied with in the course of carrying out the maintenance and a statement setting out any defects found in complying with those directives; and

(m) if, in the course of carrying out the maintenance, an aircraft component:

(i) that has had maintenance carried out on it; and

(ii) that was supplied to the person carrying out the maintenance by another person;

was fitted — set out the number of the document that covered the supply of the component in accordance with subregulation 42W (4); and

(n) if, in the course of carrying out the maintenance, a time‑lifed aircraft component was fitted or replaced:

(i) identify the component and that includes (if applicable) the part number and serial number of the component; and

(ii) list the airworthiness directives that have been complied with in relation to the component; and

(iv) if the component has not been overhauled — set out the time in service of, or the number of cycles completed by, the component since new; and

(v) if the component has been overhauled — set out the time in service of, or number of cycles completed by, the component since its most recent overhaul; and

(vi) if the component is an engine — set out the test performance figures of the engine; and

(p) if, in the course of carrying out the maintenance, an aircraft material:

(i) that has had maintenance carried out on it; and

(ii) that was supplied to the person by another person; and

(iii) that is not a fluid;

was used — set out the number of the document that covered the supply of the material in accordance with subregulation 42X (1); and

(q) identify the documents kept by the person carrying out the maintenance as a record of the carrying out of the maintenance; and

(s) include the date on which the certification was made.

4.5 If certifications for completion of stages of maintenance are made in the aircraft log book or approved alternative document for the aircraft, a final certification must:

(b) be signed by the person making the certification; and

(c) include the licence number, airworthiness authority number or certificate of approval number of the person making the certification; and

(d) if the person making the certification is an employee — state the name of the person’s employer and the employer’s certificate of approval number, licence number or airworthiness authority number; and

(e) include the date on which the certification was made.

What is the responsibility of a person who makes a final certification?

4.6 A person must not make a final certification unless the person is satisfied that:

(a) all maintenance required to be carried out on the aircraft has been carried out; and

(b) if the maintenance was required to be co‑ordinated by paragraph 3.1 or 3.2 — the maintenance has been co‑ordinated; and

Schedule 7 Maintenance that must not be carried out on a Class B aircraft by a person referred to in paragraph 42ZC (4) (b)

(paragraph 42ZC (4) (b))

Part 1 General

1.1 The inspection of an aircraft for the purpose of the issue of a maintenance release.

1.2 Maintenance involving disturbing the individual parts of an aircraft component supplied as a bench tested component where the subsequent functioning of the component can only be proved by the use of test equipment additional to the equipment used for normal functional checks and trouble shooting checks.

1.3 Maintenance involving the use of non‑destructive testing methods, but not including the use of aerosol packed materials in conducting liquid penetrant inspections.

1.4 Maintenance involving the complete jacking of an aircraft.

1.5 Maintenance involving the use of jigs, but not including the use of control rigging devices.

Part 2 Maintenance of airframes

2.1 The repair or modification of:

(a) the primary structure of an aircraft; or

(b) the seat support structure of an aircraft.

2.2 Welding, brazing, heat treating or metalizing of or on the primary structure of an aircraft.

2.3 Riveting, gluing or bonding joints in the primary structure of an aircraft.

2.4 Bolting joints in the airframe of an aircraft, where the bolting requires the use of special techniques.

2.5 Replacing a complete fabric covering of a fuselage, aerofoil or flying surface.

2.6 Balancing flying control surfaces.

2.7 Balancing main or tail rotor assemblies.

2.8 Refurbishing the interior of an aircraft.

2.9 Repainting that might affect the balance of flying control surfaces.

Part 3 Maintenance of engines

3.1 Disassembly or assembly of a crankcase of a reciprocating engine.

3.2 Disassembly or assembly of a crankshaft of a reciprocating engine (including removal and replacement of a connecting rod).

3.3 Disassembly or assembly of a rotor housing of a rotary engine.

3.4 Disassembly or assembly of a rotor assembly of a rotary engine.

3.5 Disassembly or assembly of a main casing of a turbine engine.

3.6 Disassembly or assembly of a rotating assembly of a turbine engine.

3.7 Balancing of rotating assemblies of engines.

3.8 Welding, brazing, heat treating or metalizing, but not including minor repairs to exhaust pipes.

3.9 Machining, other than machining using standard hand tools or valve refacing equipment.

3.10 Removal or replacement of reduction gears or accessory drive gears that are not attached to an accessory.

3.11 Balancing of propellers.

3.12 Disassembly and assembly of propeller hubs.

3.13 Straightening of propeller blades.

Part 4 Maintenance on electrical, instrument and radio systems

4.1 Maintenance of operational software and automatic test equipment software;

4.2 Initial installation of an electrical, instrument or radio system.

Part 5 Specific maintenance on manned balloons and hot air airships

5.1 In relation to a manned balloon or a hot air airship:

(a) the replacement of one or more panels in the upper half of the envelope; or

(b) the replacement of 4 or more panels in the lower half of the envelope; or

(d) the repair of the suspension system; or

(e) the repair of the burner system, other than seal replacement or the cleaning of jets.

Note For maintenance of engines of hot air airships see Part 3.

Schedule 8 Maintenance that may be carried out on a Class B aircraft by a pilot entitled to do so under subregulation 42ZC (4)

(subregulation 42ZC (4))

1. Removal or installation of landing gear tyres, but only if the removal or installation does not involve the complete jacking of the aircraft.

2. Repair of pneumatic tubes of landing gear tyres.

3. Servicing of landing gear wheel bearings.

4. Replacement of defective safety wiring or split pins, but not including wiring or pins in control systems.

5. Removal or refitting of a door, but only if:

(a) no disassembly of the primary structure or operating system of the aircraft is involved; and

(b) if the aircraft is to be operated with the door removed — the aircraft has a flight manual and the manual indicates that the aircraft may be operated with the door removed.

6. Replacement of side windows in an unpressurised aircraft.

7. Replacement of seats, but only if the replacement does not involve disassembly of any part of the primary structure of the aircraft.

8. Repairs to the upholstery or decorative furnishings of the interior of the cabin or cockpit.

9. Replacement of seat belts or harnesses.

10. Replacement or repair of signs and markings.

11. Replacement of bulbs, reflectors, glasses, lenses or lights.

12. Replacement, cleaning, or setting gaps of, spark plugs.

13. Replacement of batteries.

14. Changing oil filters or air filters.

15. Changing or replenishing engine oil or fuel.

16. Lubrication not requiring disassembly or requiring only the removal of non‑structural parts, or of cover plates, cowlings and fairings.

17. Replenishment of hydraulic fluid.

18. Application of preservative or protective materials, but only if no disassembly of the primary structure or operating system of the aircraft is involved.

19. Removal or replacement of equipment used for agricultural purposes.

20. Removal or replacement of glider tow hooks.

21. Carrying out of an inspection under regulation 42G of a flight control system that has been assembled, adjusted, repaired, modified or replaced.

22. Carrying out of a daily inspection of an aircraft.

Schedule 9 Maintenance control manual and maintenance controller

(regulation 42ZV)

Part 1 Requirements for person who is a maintenance controller

1.1 To be the maintenance controller a person must:

(a) know and understand the operator’s maintenance control manual; and

(b) know and understand the requirements of the regulations in relation to the maintenance of aircraft; and

(c) demonstrate the required knowledge and understanding for the purposes of being approved as the maintenance controller.

Part 2 Functions of maintenance controller

2.1 A maintenance controller must perform the following functions:

(a) the control of all maintenance carried out on the aircraft, either scheduled or unscheduled;

(b) the development, organisation and supervision of all activities and procedures specified in the maintenance control manual;

(d) the investigation of all defects in the aircraft that come to the attention of the aircraft’s maintenance organisation.