Which structural parts are subject to the loading conditions specified in CS 29.479(b)(3)?

The loading conditions of CS 29.479(b)(3) are applied to the landing gear and its attaching structure only.

For the spin-up load condition in CS 29.479, what is the minimum ground speed that must be used?

The ground speed for determination of the spin-up loads must be at least 75% of the optimum forward flight speed for minimum rate of descent in autorotation.

What are the two level landing attitudes that must be considered for a rotorcraft under CS 29.479?

The two level landing attitudes are: (1) an attitude in which each wheel contacts the ground simultaneously, and (2) an attitude in which the aft wheels contact the ground with the forward wheels just clear of the ground.

Under CS 29.479, what is the minimum drag load that must be combined with the vertical load at each wheel?

The drag load at each wheel must be not less than 25% of the vertical load at that wheel.

If a rotorcraft has two forward wheels, how must the loads from CS 29.479(b)(1) and (b)(2) be distributed between those wheels?

The loads must be distributed in a ratio of 40:60 between the two forward wheels.

In the level landing attitude where all wheels contact the ground simultaneously, how are pitching moments assumed to be resisted?

Pitching moments are assumed to be resisted by the forward landing gear.

In the level landing attitude where the aft wheels contact the ground and the forward wheels are just clear, what resists the pitching moments?

Pitching moments are assumed to be resisted by the angular inertia forces.

CS 29.479 Level landing conditions

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CS 29.479 Level landing conditions

ED Decision 2003/16/RM

(a) Attitudes. Under each of the loading conditions prescribed in sub-paragraph (b), the rotorcraft is assumed to be in each of the following level landing attitudes:

(1) An attitude in which each wheel contacts the ground simultaneously.

(2) An attitude in which the aft wheels contact the ground with the forward wheels just clear of the ground.

(b) Loading conditions. The rotorcraft must be designed for the following landing loading conditions:

(1) Vertical loads applied under CS 29.471.

(2) The loads resulting from a combination of the loads applied under sub-paragraph (b)(1) with drag loads at each wheel of not less than 25% of the vertical load at that wheel.

(3) The vertical load at the instant of peak drag load combined with a drag component simulating the forces required to accelerate the wheel rolling assembly up to the specified ground speed, with:

(i) The ground speed for determination of the spin-up loads being at least 75% of the optimum forward flight speed for minimum rate of descent in autorotation; and

(ii) The loading conditions of sub-paragraph (b) applied to the landing gear and its attaching structure only.

(4) If there are two wheels forward, a distribution of the loads applied to those wheels under sub-paragraphs (b)(1) and (2) in a ratio of 40:60.

(1) In the case of the attitude in sub-paragraph (a)(1), the forward landing gear; and

(2) In the case of the attitude in sub-paragraph (a)(2), the angular inertia forces.

Details

Source-Title: CS 29.479 Level landing conditions View latest amendments

Erulesid: ERULES-1963177438-5426 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