---
kind: "range"
citation: "14 C.F.R. §§ 29.479–29.485"
title: "14"
from: "29.479"
to: "29.485"
count: 4
url: "https://uscodex.org/cfr/14/29.479..29.485"
---

# §29.479. Level landing conditions.

- (a) **Attitudes.** Under each of the loading conditions prescribed in [paragraph (b)](#b) of this section, 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 [§ 29.471](/cfr/14/29.471.md).
  - (2) The loads resulting from a combination of the loads applied under [paragraph (b)(1)](#b-1) of this section with drag loads at each wheel of not less than 25 percent 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 percent of the optimum forward flight speed for minimum rate of descent in autorotation; and
    - (ii) **The loading conditions of 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 paragraphs [(b)(1)](#b-1) and [(2)](#b-2) of this section in a ratio of 40:60.
- (c) **Pitching moments.** Pitching moments are assumed to be resisted by—
  - (1) In the case of the attitude in [paragraph (a)(1)](#a-1) of this section, the forward landing gear; and
  - (2) **In the case of the attitude in paragraph (a)(2) of this section, the angular inertia forces.**

# §29.481. Tail-down landing conditions.

- (a) The rotorcraft is assumed to be in the maximum nose-up attitude allowing ground clearance by each part of the rotorcraft.
- (b) **In this attitude, ground loads are assumed to act perpendicular to the ground.**

# §29.483. One-wheel landing conditions.


For the one-wheel landing condition, the rotorcraft is assumed to be in the level attitude and to contact the ground on one aft wheel. In this attitude—

- (a) The vertical load must be the same as that obtained on that side under [§ 29.479(b)(1)](/cfr/14/29.479.md?p=b-1); and
- (b) The unbalanced external loads must be reacted by rotorcraft inertia.

# §29.485. Lateral drift landing conditions.

- (a) **The rotorcraft is assumed to be in the level landing attitude, with—**
  - (1) Side loads combined with one-half of the maximum ground reactions obtained in the level landing conditions of [§ 29.479(b)(1)](/cfr/14/29.479.md?p=b-1); and
  - (2) **The loads obtained under paragraph (a)(1) of this section applied—**
    - (i) At the ground contact point; or
    - (ii) **For full-swiveling gear, at the center of the axle.**
- (b) The rotorcraft must be designed to withstand, at ground contact—
  - (1) When only the aft wheels contact the ground, side loads of 0.8 times the vertical reaction acting inward on one side and 0.6 times the vertical reaction acting outward on the other side, all combined with the vertical loads specified in [paragraph (a)](#a) of this section; and
  - (2) **When the wheels contact the ground simultaneously—**
    - (i) For the aft wheels, the side loads specified in [paragraph (b)(1)](#b-1) of this section; and
    - (ii) For the forward wheels, a side load of 0.8 times the vertical reaction combined with the vertical load specified in [paragraph (a)](#a) of this section.