CASA 546/04 Direction under subregulation 235(2) Beech Model B200T Aircraft VH-LAB (Cth)

INSTRUMENT NUMBER:  CASA 546/04

CIVIL AVIATION REGULATIONS 1988

DIRECTION UNDER SUBREGULATION 235 (2)

BEECH MODEL B200T AIRCRAFT VH-LAB

I, ARTHUR JOHN WHITE, Acting Executive Manager, Aviation Safety Compliance, a delegate of CASA, under subregulation 235 (2) of the Civil Aviation Regulations 1988 (CAR 1988):

1. revoke instrument CASA 740/02; and

1. direct that the gross weight of the Beech Model B200T aircraft VH-LAB must not, at take-off or landing, exceed a maximum weight that will enable it, in accordance with its flight manual, to comply with the performance requirements set out in:

(a)section 20.7.4 of the Civil Aviation Orders, when the aircraft is at a gross weight that is not more than 12,500 lb;  or

(b)Schedule 1, when the aircraft is at a gross weight that is more than 12,500 lb but not more than 14,000 lb.

This instrument comes into effect on gazettal and stops having effect at the end of November 2006.

SCHEDULE 1

1. The gross weight of the aircraft at take-off must not exceed the take-off weight to achieve positive, one engine inoperative rate of climb at lift-off, as determined from page 5-26 or 5-27 in the flight manual, in the stated conditions.  This gross weight must be reduced, in accordance with pages 5-26 or 5-27 in the flight manual, to account for increase in the outside air temperature and pressure altitude at the place of take-off.

1. For the purposes of clause 1, the stated conditions are:

(a)with autofeather serviceable and armed at take-off;  and

(b)with one engine inoperative and propeller feathered;  and

(c)with operative engine at take-off power;  and

(d)with flaps up or flaps approach;  and

(e)with landing gear down.

1. The gross weight at take-off with all engines operating must be such that the total distance required, in accordance with the flight manual, to clear 50 feet, is, when multiplied by 1.15, equal to or less than the take-off distance available.

1. The gross weight at take-off with all engines operating must be such that the total accelerate-stop distance required, in accordance with the flight manual, is equal to or less than the accelerate-stop distance available.

1. The gross weight at take-off with an engine out operating must be such that the total accelerate-go distance required, in accordance with the flight manual, to clear 35 feet, is equal to or less than the take-off distance available.

1. For the purposes of clause 3, the total distance required in the ambient conditions to clear 50 feet must be calculated in accordance with page 5-36 or 5-40 in the flight manual, taking into account the outside air temperature and pressure altitude at the place of take-off.

1. For the purposes of clause 4, the total accelerate-stop distance required in the ambient conditions must be calculated in accordance with page 5-37 or 5-41 in the flight manual, taking into account the outside air temperature and pressure altitude at the place of take-off.

1. For the purposes of clause 5, the total accelerate-go distance required in the ambient conditions to clear 35 feet must be calculated in accordance with page 5-38 or 5-42 in the flight manual, taking into account the outside air temperature and pressure altitude at the place of take-off.

1. For the purposes of clause 3, credit may be taken for a head wind, or additional required take-off distance must be allowed for when taking off with a tail wind, in accordance with page 5-36 or 5-40 in the flight manual.

1. For the purposes of clause 4, credit may be taken for a head wind, or additional required take-off distance must be allowed for when taking off with a tail wind, in accordance with page 5-37 or 5-41 in the flight manual.

1. For the purposes of clause 5, credit may be taken for a head wind, or additional required take-off distance must be allowed for when taking off with a tail wind, in accordance with page 5-38 or 5-42 in the flight manual.

1. The gross weight of the aircraft at take-off must not exceed the weight at which the aircraft, after having first reached lowest safe altitude or minimum sector altitude, and allowing for fuel consumption, is able, at that altitude and in the event of an engine failure, to maintain a rate of climb of 50 feet per minute.

1. For the purposes of clause 12, the gross weight at take-off must be calculated from page 5-28 in the flight manual, entering page 5-28 for that purpose with the applicable outside air temperature and pressure altitude.

1. With a gross weight at take-off of not more than 12,500 lb, the aircraft may take off from any hard surface runway.

1. Subject to clauses 3, 4 and 5, with a gross weight at take‑off of more than 12,500 lb, the aircraft may only take off from a hard surface runway, if:

(a)there is no significant populated or built-up area beyond the end of the runway that cannot be avoided by manoeuvring the aircraft at an angle of bank of not more than 15^o;  and

(b)gross weight at take-off is limited in accordance with pages 5-34 and 5-39, or 5-34 and 5-43, of the flight manual so that the aircraft will clear significant obstacles in the chosen take-off flight path.

1. The gross weight of the aircraft at landing must be such that the rate of climb determined from page 5-131 in the flight manual is not less than 500 feet per minute.  This gross weight must be reduced, in accordance with page 5-131 in the flight manual, to account for increase in the outside air temperature and pressure altitude at the place of landing.

1. The gross weight of the aircraft at landing must be such that the total distance required to clear a 50 foot high obstacle and land, as shown in page 5-132 or 5-134 in the flight manual, when multiplied by 1.67, is equal to or less than the landing distance available, taking account of the outside air temperature and pressure altitude.

1. For the purposes of clause 17, credit may be taken when landing with a head wind, or additional required landing distance must be allowed for when landing with a tail wind, in accordance with page 5-132 or 5-134 in the flight manual.

1. For landing at an alternate aerodrome, the gross weight permitted at landing must be calculated in accordance with clause 17, except that the total distance required to clear a 50 foot high obstacle and land, must be multiplied by 1.43.

1. Clauses 16 to 19 (inclusive) do not apply if an emergency exists.

[Signed Arthur J. White]

Arthur White

Acting Executive Manager

Aviation Safety Compliance

11 November 2004