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1.2 Apply the pressure altitude to the pressure altitude in feet co-ordinate on the
chart. Move vertically to intersect the temperature line representing the
forecast temperature.
1.3 From this point move horizontally to intersect the corrected effective
operational length to the corrected effective operational length available for
landing.
1.4 Move vertically downwards and read take-off weight. Record the weight thus
obtained.
1.5 Ascertain the elevation of the aerodrome.
1.6 Apply this elevation to the aerodrome elevation co-ordinate. Move vertically to
intersect the landing climb limitation line.
1.7 From this point move horizontally and read the landing weight. Record the
weight thus obtained.
1.8 The maximum permissible landing weight is the lesser of the 2 weights as
determined in paragraphs 1.4 and 1.7 above.
1.9 The landing weight as obtained by the foregoing method shall apply only when
the aeroplane is to be flown in the configuration specified in the relevant
Landing Chart. The use of any other configuration is prohibited except where
an application to use some other condition has been made to CASA and it has
approved such condition.
1.10 When it is necessary to specify an alternate aerodrome, the above procedure
shall be repeated for that aerodrome.
2 Under Declared Conditions:
2.1 Use the appropriate seasonal Declared Density Altitude Chart, and add the
elevation of the destination aerodrome to the value(s) read from the chart and
thus obtain the declared seasonal density altitude.
2.2 Apply the declared seasonal density altitude to the density altitude co-ordinate
of the landing weight chart. Move horizontally to intersect the corrected
effective operational length line corresponding to the corrected effective
operational length available for landing.
2.3 Move vertically downwards and obtain the landing weight. Record the weight
thus obtained.
Issue 4: 8 December 2004
Amdt No. 209
-7- SECTION 20.7.1
Issue 4
2.4 Ascertain the elevation of the destination aerodrome.
2.5 Apply this elevation to the aerodrome elevation co-ordinate. Move vertically to
intersect the landing climb limitation line.
2.6 From this point move horizontally and read the landing weight. Record the
weight thus obtained.
2.7 The maximum permissible landing weight shall be the lesser of the 2 weights
as determined in paragraphs 2.3 and 2.6 above.
2.8 The landing weight as obtained by the foregoing method shall apply only
where the aeroplane is to be flown in the configuration specified in the relevant
Landing Chart. The use of any other configuration is prohibited except where
an application to use some other condition has been made to CASA and it has
approved such condition.
Issue 4: 8 December 2004
Amdt No. 209
SECTION 20.7.1 -8-
Issue 4
THIS PAGE INTENTIONALLY LEFT BLANK
Issue 4: 8 December 2004
Amdt No. 209
Issue 5: 11 June 2005
Amendment No. 227
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 Application
3 Definitions
4 Take-off weight limitations
5 Landing weight limitations
6 Accelerate-stop and take-off
distance required
7 Take-off climb performance
8 En-route climb performance
9 Approach climb performance
10 Landing climb performance
11 Landing distance required
12 Obstacle clearance
requirements
12A Alternative take-off area
requirements
14 Aeroplane configuration and
procedures
Transitional and savings
2 APPLICATION
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.
2.2 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.
3 DEFINITIONS
3.1 In this section:
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