Civil Aviation Order 100.5 (General requirements in respect of maintenance of Australian aircraft) 2011
Part 1Compliance requirements
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Note 2 The aeroplane must comply with each of the following requirements and be approved by CASA. (See subsection 10 above.) Aircraft systems and equipment mentioned within these requirements must be approved under regulation 21.305 of CASR.
1 Aeroplane
The aeroplane type must have been originally certificated as a turbine-powered aeroplane under the certification requirements set under Part 23 of CASR that are equivalent to FAR 23 amendment 28 or a subsequent amendment.
Note Thus, a turbine conversion of an originally certificated piston-powered aeroplane cannot comply.
2 Engine
2.1The aeroplane engine type (the engine type) must have documented evidence of an acceptable world fleet reliability rate (WFRR) in accordance with this clause.
2.2The WFRR must be calculated as a 6 month rolling average, and consist of:
(a) an in-flight shutdown (IFSD) rate of not more than 0.01 per 1 000 hours based on a minimum experience history of 100 000 hours’ time-in-service; or
(b) an IFSD rate for individual engine components gained in the same engine types, or in equivalent engine types as determined by CASA, that collectively meet the standard of paragraph (a).
2.3For paragraphs 2.2 (a) and (b), where the accumulated history is less than the requirement, the history of individual components which have demonstrated time in service in similar engine types, may be taken into account.
3 Engine control system
3.1 The engine control system must meet the requirements of FAR 23.1141 Amendment 29 or a later amendment.
3.2 If use of an emergency/secondary power lever is available, the necessary procedures for its use must be documented in the Aircraft Flight Manual (AFM) or approved equivalent.
4 Engine ignition system
The aeroplane type must be equipped with 1 of the following engine ignition systems:
(a) an automatic ignition system which activates in the event of a loss of an engine parameter, for example, engine speed, turbine temperature or engine torque;
(b) an ignition system which can be selected “ON” and has a duty cycle greater than 1 hour.
5 Engine fire warning system
The aeroplane type must be equipped with an engine compartment fire detection and in-flight warning system.
6 Engine monitoring system
6.1 The aeroplane type must be equipped with an automatically activated electronic engine trend monitoring recording system, approved by or under Part 21 of CASR, which records the following:
Part Part 1 - Civil Aviation Order 100.5 (General requirements in respect of maintenance of Australian aircraft) 2011 - Compliance requirements | Zoe
(a) engine parameters referenced in the engine manufacturer’s published engine trend monitoring procedures; and
(b) any other engine performance parameters, mentioned in the approval, that are critical to the engine’s safe continuing airworthiness.
6.2 The engine oil consumption must be monitored in accordance with the engine manufacturer’s recommendations.
6.3 Any anomalies detected by the monitoring mentioned in subclause 6.1 or 6.2 must be checked against the manufacturer’s data to determine appropriate and timely corrective action.
7 Engine oil metal contamination detection system
The aeroplane must be equipped with an approved electronic engine oil metal contamination detection system which provides the pilot with an in-flight, visual, caution/warning indication of possible contamination of the engine oil, including as applicable the following:
(a) engine reduction gearbox oil system;
(b) engine accessory gearbox oil system.
8 Electrical power sources
The aeroplane must be equipped with the following:
(a) a primary electrical generator and 1 or more primary electrical storage batteries;
(b) an alternative source of electrical power, capable of supplying sufficient continuous power to each of the following:
(i) flight instruments;
(ii) navigation systems;
(iii) lighting systems;
(iv) icing protection systems;
(c) any other aeroplane system required under CAO 20.18 for the endurance of the aeroplane for flight at night under the I.F.R.
9 Battery capacity
9.1There must be an electrical load analysis (ELA) for the aeroplane.
Note The ELA is provided to CASA at the time of an application for PSEA inclusion on the TC, STC or TAC.
9.2The ELA is to certify that the electrical storage capacity of the aeroplane’s prime battery is capable of providing the following:
(a) full operation of essential flight and navigation instruments, lighting and associated icing protection systems during an engine failed glide from the maximum operating altitude, or an elected limiting altitude, to sea level at best range glide speed;
(b) sufficient capacity remaining during a glide mentioned in paragraph (a) to conduct 2 engine start attempts, and lower the flaps and undercarriage.
9.3The requirement for sufficient battery capacity for the 2 engine starts mentioned in paragraph 9.2 (b) may be reduced to capacity for 1 engine start, provided:
(a) the aeroplane’s engine fuel feed system from the aeroplane’s fuel tank to the engine fuel control unit is automatic; and
(b) the engine compressor air intake incorporates continuous anti-icing while the engine is operating; and
(c) the aeroplane incorporates an automatic engine ignition system which activates in the event of a loss of an engine parameter such as engine speed, turbine temperature or engine torque.
9.4 Where the aircraft avionics and electrical configuration:
(a) differs from the approved configuration; or
(b) is altered after approval of the configuration;
a revised ELA must be provided to CASA for approval.
10 Electrical load shedding
10.1Subject to subclause 10.2, the AFM or approved equivalent must provide the pilot with a procedure for shedding non-essential electrical systems during a maximum range glide descent following an engine failure in flight.
10.2In the case of an automatic shedding procedure that will commence to operate following an engine failure in flight, the AFM or an approved equivalent is not required to include a procedure in accordance with subclause 10.1 but must state, for the information of the pilot, how the automatic shedding procedure will operate.
11 Flight instrument systems
11.1The aeroplane must be equipped with flight and navigation instruments and instrument power sources complying with the regulatory requirements for air transport I.F.R. operations.
11.2Aeroplanes incorporating an electronic display flight instrument system must incorporate secondary attitude and gyroscopic heading instruments located on the pilot’s flight instrument panel and powered independently of the primary flight display.
11.3In aeroplanes approved for flight in icing conditions, the AFM or approved equivalent must provide the pilot with a procedure for ensuring essential flight instruments are protected from icing during a maximum range glide descent through icing conditions following an engine failure in flight.
12 Autopilot system
For single pilot operations, the aeroplane must be equipped with an automatic pilot providing a capability to:
(a) operate the flight controls to maintain flight and manoeuvre the aeroplane about the roll and pitch axis; and
(b) fly to an automatic heading; and
(c) provide altitude hold.
Radar altimeter
The aeroplane must be equipped with a radar altimeter.
Weather radar
The aeroplane must be equipped with a weather radar system.
Passenger seats
16.1The aeroplane must be equipped with passenger seats identified by:
(a) the part number or model number meeting the requirements of FAR 23.562 and 23.785 to amendment 36 or later amendment; or
(b) for Cessna 208 and 208B aircraft — the following part numbers:
(i) 2614028-();
(ii) 2614029-();
(iii) 2614076-();
(iv) 2614077-();
(v) 2619019-();
(vi) 2619020-().
Note For Cessna 208 and 208B, 2 or 3 place Rear Bench Seats (2614045-() or 2619017-(), IPC Ref 25-21-01), Stowable Seats (2614041-(), ATFS1-01, IPC Ref. 25-21-02) and non-factory seats not meeting FAR 23.562 (AMDT. 23-36), TSO-C127 or TSO-C127a, are not approved for ASETPA operations.
16.2Each passenger seat must be equipped with a shoulder harness.