(1)
Proper use is made of seats, belts, and other safety design provisions;

(2)
The wheels are retracted(where applicable); and

′
Elodie Roux. Septembre 2003
Subpart C : Strength Requirements
(3) Each occupant and each item of mass inside the cabin that could injure an occupant is restrained when subjected to the following ultimate inertial load factors relative to the surrounding structure :
(i)
Upward–4g.

(ii)
Forward–16g.

(iii) Sideward–8g.
(iv)
Downward–20g, after the intended displacement of the seat device.

(v)
[Rearward–1.5g.]

(c)
The supporting structure must be designed to restrain, under any ultimate inertial load up to those speci.ed in thisparagraph, anyitem of mass above and/orbehind the crew andpassenger compartment that couldinjure an occupantifit cameloose in an emergencylanding.Items ofmasstobe consideredinclude,but are notlimited to, rotors, transmissions, and engines.Theitems of mass mustbe restrainedfor the following ultimate inertial load factors :

(1)
Upward–1.5g.

(2)
Forward–[12g.]

(3)
Sideward–[6g.]

(4)
Downward–[12g.

(5)
Rearward–1.5g.]

(d)
Any fuselage structure in the area of internal fuel tanks below the passenger .oor level must be designed to resist the following ultimate inertial factors and loads and to protect the fuel tanks from rupture when those loads are applied to that area :

(i)
Upward–1.5g.

(ii)
Forward–4.0g.

(iii) Sideward–2.0g.

(iv)
Downward-4.0g. Amdt. 27-32, E.. 6/11/96

FAR27.562 :[Emergencylandingdynamic conditions.]

(a)
[The rotorcraft, although it may be damaged in an emergencycrash landing, must bedesigned to reasonablyprotect each occupant when–

(1)
The occupant properly uses the seats, safety belts, and shoulder harnesses provided in the design; and

(2)
The occupantis exposed totheloads resulting fromthe conditionsprescribed in this section.

(b)
Each seat type design or other seating device approved for crew or passenger occu-pancy during takeo. and landing must successfully complete dynamic tests or be demonstrated by rational analysis based on dynamic tests of a similar type seat in accordance with the following criteria. The tests must be conducted with an occu-pant, simulatedby a170-pound anthropomorphictestdummy(ATD), asde.ned by49CFR572,SubpartB, orits equivalent, sittingin the normaluprightposition.

(1)
A change in downward velocity of not less than 30 feet per second when the seat or other seating deviceis orientedinits nominalposition with respectto the rotorcraft’s reference system, the rotorcraft’s longitudinal axis is canted upward 60'with respect to the impact velocity vector, and the rotorcraft’s lateral axisisperpendicularto a verticalplanecontaining theimpact velocity vector and the rotorcraft’s longitudinal axis. Peak .oor deceleration must occurin not more than0.031 seconds afterimpact and must reach a minimum of 30g’s.

(2)
A change in forward velocity of not less than 42 feet per second when the seat or other seating device is oriented in its nominal position with respect to the rotorcraft’s reference system, the rotorcraft’s longitudinal axis is ya-wed 10'either right or left of the impact velocity vector (whichever would cause the greatest load on the shoulder harness), the rotorcraft’s lateral axis is contained in a horizontal plane containing the impact velocity vector, and the rotorcraft’svertical axisisperpendicularto ahorizontalplane containing the impact velocity vector. Peak .oor deceleration must occur in not more than 0.071 seconds after impact and must reach a minimum of 18.4g’s.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(82)