CIVIL AVIATION ORDERS PART 20 SECTION 20.7.1B Issue 5 AEROPLANE WEIGHT AND PERFORMANCE LIMITATIONS — SPECIFIED AEROPLANES ABOVE 5 700 KG — ALL OPERATIONS (TURBINE AND PISTON-ENGINED) SUBSECTIONS
2 3 4 5 6 7 8 9 2 Application Definitions Take-off weight limitations Landing weight limitations Accelerate-stop and take-off distance required Take-off climb performance En-route climb performance Approach climb performance APPLICATION 10 11 12 Landing climb performance Landing distance required Obstacle clearance requirements 12A Alternative take-off area requirements 14 Aeroplane configuration and procedures Transitional and savings
2.1
Subject to paragraph 2.2, this section applies to: (a) all turbine powered aeroplanes having a maximum take-off weight in excess of 5 700 kg; and (b) all new types of piston engine aeroplanes having a maximum take-off weight in excess of 5 700 kg placed on the Register after 1 June 1963. For paragraph 2.1: (a) a certificate of airworthiness for the aircraft must be in force; and (b) the certificate must include a statement to the effect that the certificate is issued in the transport, commuter or normal category.
Note 1 The only normal category aeroplanes with maximum take-off weights exceeding 5 700 kg are SFAR 41 aeroplanes. See paragraph 7.6. Note 2 Aeroplanes of maximum take-off weight exceeding 5 700 kg and not subject to sections 20.7.1 or 20.7.1B of the Civil Aviation Orders remain subject to subregulation 235 (2) of the Regulations.
2.2
3
DEFINITIONS
3.1
In this section: accelerate-stop distance available means the sum of: (a) the length of the take-off run available; and (b) if stopway is provided — the length of the stopway.
Issue 5: 11 June 2005 Amendment No. 227
飞行翻译公司 www.aviation.cn 本文链接地址：200701b.pdf
2 3 4 5 6 7 8 9 2 Application Definitions Take-off weight limitations Landing weight limitations Accelerate-stop and take-off distance required Take-off climb performance En-route climb performance Approach climb performance APPLICATION 10 11 12 Landing climb performance Landing distance required Obstacle clearance requirements 12A Alternative take-off area requirements 14 Aeroplane configuration and procedures Transitional and savings
2.1
Subject to paragraph 2.2, this section applies to: (a) all turbine powered aeroplanes having a maximum take-off weight in excess of 5 700 kg; and (b) all new types of piston engine aeroplanes having a maximum take-off weight in excess of 5 700 kg placed on the Register after 1 June 1963. For paragraph 2.1: (a) a certificate of airworthiness for the aircraft must be in force; and (b) the certificate must include a statement to the effect that the certificate is issued in the transport, commuter or normal category.
Note 1 The only normal category aeroplanes with maximum take-off weights exceeding 5 700 kg are SFAR 41 aeroplanes. See paragraph 7.6. Note 2 Aeroplanes of maximum take-off weight exceeding 5 700 kg and not subject to sections 20.7.1 or 20.7.1B of the Civil Aviation Orders remain subject to subregulation 235 (2) of the Regulations.
2.2
3
DEFINITIONS
3.1
In this section: accelerate-stop distance available means the sum of: (a) the length of the take-off run available; and (b) if stopway is provided — the length of the stopway.
Issue 5: 11 June 2005 Amendment No. 227
飞行翻译公司 www.aviation.cn 本文链接地址：200701b.pdf
自定义标签： 
