What conditions must be used to determine hovering performance for a Category A helicopter?

For each Category A helicopter, hovering performance must be determined over the ranges of weight, altitude and temperature for which take-off data are scheduled, with not more than take-off power, with the landing gear extended, and at a height consistent with the procedure used in establishing the take-off, climbout and rejected take-off paths.

For a Category B helicopter, what power setting and landing gear configuration are required when determining hovering performance in ground effect?

For a Category B helicopter, hovering performance must be determined with take-off power and with the landing gear extended.

At what height must hovering performance be evaluated for a Category B helicopter?

For a Category B helicopter, hovering performance must be evaluated with the helicopter in ground effect at a height consistent with normal take-off procedures.

Which performance parameter must be determined for rotorcraft other than helicopters at the minimum operating speed?

The steady rate of climb at the minimum operating speed must be determined for rotorcraft other than helicopters.

For Category A helicopters, what is the maximum power setting allowed when determining hovering performance?

For Category A helicopters, hovering performance must be determined with not more than take-off power.

What landing gear configuration is specified for determining hovering performance of Category A and Category B helicopters?

For both Category A and Category B helicopters, hovering performance must be determined with the landing gear extended.

What height is used for determining hovering performance of a Category A helicopter?

For a Category A helicopter, hovering performance must be determined at a height consistent with the procedure used in establishing the take-off, climbout and rejected take-off paths.

CS 29.49 Performance at minimum operating speed

Q: What are the required conditions for determining out-of-ground-effect hovering performance for any helicopter?

For each helicopter, out-of-ground-effect hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with take-off power.

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CS 29.49 Performance at minimum operating speed

ED Decision 2003/16/RM

(a) For each Category A helicopter, the hovering performance must be determined over the ranges of weight, altitude and temperature for which take-off data are scheduled:

(1) With not more than take-off power;

(2) With the landing gear extended; and

(3) At a height consistent with the procedure used in establishing the take-off, climbout and rejected take-off paths.

(b) For each Category B helicopter, the hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with:

(1) Take-off power;

(2) The landing gear extended; and

(3) The helicopter in ground effect at a height consistent with normal take-off procedures.

(c) For each helicopter, the out-of ground- effect hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with take-off power.

(d) For rotorcraft other than helicopters, the steady rate of climb at the minimum operating speed must be determined over the ranges of weight, altitude and temperature for which certification is requested, with:

(1) Take-off power; and

(2) The landing gear extended.

Details

Source-Title: CS 29.49 Performance at minimum operating speed View latest amendments

Erulesid: ERULES-1963177438-5446 Compare versions

Domain: Initial airworthiness

Amendedby: Initial issue

Applicabilitydate: 14 November, 2003

Entryintoforcedate: 14 November, 2003

Regulatorysource: ED Decision 2003/16/RM Navigate

Regulatorysubject: CS-29

Typeofcontent: CS (Certification specification)

Origin: EASA

Category: EAR