What are the specific test procedures for climb cooling tests for Category A rotorcraft and multi-engine Category B rotorcraft certified under Category A powerplant installation requirements?

Climb cooling tests must be conducted at the steady rate of climb or descent established under CS 29.67(b) for Category A rotorcraft and multi-engine Category B rotorcraft for which certification is requested under the Category A powerplant installation requirements and under the requirements of CS 29.861(a).

CS 29.1045 Climb cooling test procedures

Q: Which engine must be inoperative during climb or descent cooling tests?

The engine inoperative that produces the most adverse cooling conditions for the remaining engines and powerplant components.

Q: What power setting must be used for each operating engine during climb cooling tests for helicopters requesting 30-minute OEI power?

Each operating engine must be at 30-minute OEI power for 30 minutes, and then at maximum continuous power (or at full throttle, when above the critical altitude).

Q: For helicopters requesting continuous OEI power, what power setting is required for each operating engine during climb cooling tests?

Each operating engine must be at continuous OEI power (or at full throttle when above the critical altitude).

Q: What power setting is required for each operating engine during climb cooling tests for rotorcraft other than those with OEI power requests?

Each operating engine must be at maximum continuous power (or at full throttle when above the critical altitude).

Q: At what altitude must the climb cooling test begin after temperatures have stabilised in flight?

The climb must be begun from an altitude not greater than the lower of: (i) 305 m (1000 ft) below the engine critical altitude; and (ii) 305 m (1000 ft) below the maximum altitude at which the rate of climb is 0.76 m/s (150 fpm).

Q: How long must the climb cooling test be continued after the highest temperature is recorded?

The climb must be continued for at least 5 minutes after the occurrence of the highest temperature recorded, or until the rotorcraft reaches the maximum altitude for which certification is requested.

Q: For Category B rotorcraft without a positive rate of climb, where must the descent cooling test begin and end?

The descent must begin at the all-engine-critical altitude and end at the higher of: (1) the maximum altitude at which level flight can be maintained with one engine operative; and (2) sea-level.

Q: Can the climb cooling test be conducted in conjunction with the take-off cooling test?

Yes, the climb cooling test may be conducted in conjunction with the take-off cooling test of CS 29.1047.

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CS 29.1045 Climb cooling test procedures

ED Decision 2003/16/RM

(a) Climb cooling tests must be conducted under this paragraph for:

(1) Category A rotorcraft; and

(2) Multi-engine Category B rotorcraft for which certification is requested under the Category A powerplant installation requirements, and under the requirements of CS 29.861(a) at the steady rate of climb or descent established under CS 29.67(b).

(b) The climb or descent cooling tests must be conducted with the engine inoperative that produces the most adverse cooling conditions for the remaining engines and powerplant components.

(1) For helicopters for which the use of 30-minute OEI power is requested, be at 30-minute OEI power for 30 minutes, and then at maximum continuous power (or at full throttle, when above the critical altitude);

(2) For helicopters for which the use of continuous OEI power is requested, be at continuous OEI power (or at full throttle when above the critical altitude); and

(3) For other rotorcraft, be at maximum continuous power (or at full throttle when above the critical altitude).

(d) After temperatures have stabilised in flight, the climb must be:

(1) Begun from an altitude not greater than the lower of:

(i) 305 m (1000 ft) below the engine critical altitude; and

(ii) 305 m (1000 ft) below the maximum altitude at which the rate of climb is 0.76 m/s (150 fpm); and

(2) Continued for at least 5 minutes after the occurrence of the highest temperature recorded, or until the rotorcraft reaches the maximum altitude for which certification is requested.

(e) For Category B rotorcraft without a positive rate of climb, the descent must begin at the all-engine-critical altitude and end at the higher of:

(1) The maximum altitude at which level flight can be maintained with one engine operative; and

(2) Sea-level.

(f) The climb or descent must be conducted at an airspeed representing a normal operational practice for the configuration being tested. However, if the cooling provisions are sensitive to rotorcraft speed, the most critical airspeed must be used, but need not exceed the speeds established under CS 29.67(a)(2) or 29.67(b). The climb cooling test may be conducted in conjunction with the take-off cooling test of CS 29.1047.

Details

Source-Title: CS 29.1045 Climb cooling test procedures View latest amendments

Erulesid: ERULES-1963177438-5483 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