I, William Bruce Byron, Director of Aviation Safety, on behalf of CASA, make this instrument under paragraph 28BA (1) (b) of the Civil Aviation Act 1988.
[Signed Bruce Byron]
Bruce Byron
Director of Aviation Safety and
Chief Executive Officer
8 April 2008
Civil Aviation Order 82.3 Amendment Order (No. 1) 2008
1 Name of instrument
This instrument is the Civil Aviation Order 82.3 Amendment Order (No. 1) 2008.
2 Commencement
This instrument commences on the day after it is registered.
3 Amendment of Civil Aviation Order 82.3
Schedule 1 amends Civil Aviation Order 82.3.
Schedule 1 Amendment
[1] Subparagraphs 6.1 (a) and (b)
substitute
(a) subject to subparagraphs (b) and (c) and paragraph 6.4, aeroplanes which have a maximum take-off weight (MTOW) exceeding 3 500 kg in the:
(i) transport category; or
(ii) commuter category; or
(iii) normal category, subject to the condition that the aeroplane meets the requirements of Appendix 5 of this Order;
(b) aeroplanes in respect of which a certificate of type approval or type acceptance certificate has been issued and which have an MTOW exceeding 3 500 kg and comply with the United States of America Special Federal Aviation Regulation No. 41 — normal category;
[2] After Appendix 4
insert
Appendix 5
1 Landing gear warning
1.1 Except as provided in subclauses 1.4 and 1.5 of this Appendix, aeroplanes equipped with retractable landing gear or retractable floats must be provided with an audible warning device to give unmistakable continuous warning if the landing or alighting gear is not fully extended and locked when:
(a) 1 or more throttles are retarded to or beyond the position for a normal landing approach; and
(b) the wing flaps are extended beyond the approach-climb configuration.
Note The flap warning may be initiated by a sensing unit installed at any suitable location in the flap system.
1.2 If provision is made for silencing audible warnings that are derived from the throttle positions, the design of the warning system must ensure that after a warning has been silenced, the subsequent retardation of any throttles to or beyond the position for a normal landing approach results in an audible warning.
1.3 Nothing must be done to silence warnings derived from the position of the wing flaps.
1.4 The requirement of paragraph 1.1 (a) of this Appendix does not apply to:
(a) amphibious aeroplanes; and
(b) aeroplanes having the throttle lever(s) mechanically interconnected with the landing gear selector lever in such a way that the throttle(s) cannot be closed until the landing gear is fully down and locked.
1.5 The requirement of paragraph 1.1 (b) of this Appendix does not apply to an aeroplane which is of the same type as another type of aeroplane for which an Australian certificate of airworthiness or import permit was issued before 30 June 1967.
2 Propeller feathering systems
Except where CASA is satisfied that adequate safety will be provided, automatic propeller feathering systems must be designed to ensure that a propeller will not feather automatically when any other propeller is already feathered or in the process of being feathered.
3 Powerplant fire protection
3.1 Engine compartment fire detection and extinguishing systems must be installed if the aeroplane is equipped with supercharged or turbo supercharged piston engines or gas turbine engines.
3.2 An engine compartment fire detection system required by subclause 3.1 of this Appendix must meet the requirements of section 1203 of Federal Aviation Regulation (FAR) Part 23 or European Aviation Safety Agency (EASA) CS-23.
3.3 The powerplant fire warnings must be indicated in the cockpit by individual red lights and also by an audible warning device that may be common to all fire detection circuits.
3.4 An audible warning device must be capable of being silenced.
3.5 Fire extinguishing systems required by subclause 3.1 of this Appendix must meet the requirements of sections 1195, 1197, 1199 and 1201 of FAR Part 23 or EASA CS-23.
