Document ID: chunk:federal_register_of_legislation:F2021C01280:reg:1049:p3
Version: federal_register_of_legislation:F2021C01280
Segment Type: reg
Provision Reference: reg 1049 (pt 3/12)
Character Range: 82510–85614

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