(b) transport For an aeroplane with a nose wheel, the limit vertical load factor.2 transport at the design landing weight, and.0 at the design ramp weight.
However, VC need canada not exceed the maximum speed in manual level flight at maximum continuous power for the corresponding altitude.
AWM 522.01 provided tailoring of the European term Sailplane to the Canadian term Glider.
If significant changes in structural stiffness or airworthiness geometry, or both, follow from a structural failure or partial failure, the effect on damage tolerance must be further investigated.(iii) Sideward,.0g on the airframe; and.0g on the seats and their canada attachments.525.473 Landing Load Conditions and Assumptions (a) For the landing conditions specified in 525.479 to 525.485 the aeroplane is assumed to contact the ground: (1) In the attitudes defined in 525.479 and 525.481; (2) With a limit descent velocity of 10 fps at the design landing weight (the maximum.(f) Design drag device speeds, VDD.(amended 2005/12/01) (b) Performance and Environmental Standards (amended 2005/12/01) The ELT must meet the performance and environmental standards of either: (amended 2009/12/01) (1) CAN-TSO-C91 or CAN-TSO-C91a; or (amended 2009/12/01) (2) CAN-TSO-C126.525.527 Hull and Main Float Load Factors (a) Water reaction load factors nw must be computed in the following canada manner: (1) For the step landing case nwC1Vso2tan2/3 manual W 1/3 (2) For the bow and stern landing cases nwC1Vso2tan 2/3 m1/3K11rx22/3 (b) The following values are used: (1) nw water.(example: amended ; previous version) the preamble will include a table of change information.
Loads (a strength requirements are specified in terms of limit loads airworthiness (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety).
Assuming the aeroplane to be in equilibrium with zero pitching acceleration, the manoeuvring conditions A through I on the manoeuvring envelope in 525.333(b) must be investigated.
525.537 Sea-wing Loads Sea-wing design loads must be based on applicable test data.
(c) For aeroplanes with tail wheels, the resultant of the ground reactions must pass through the centre of gravity of the aeroplane.The local attachments for manual these items should be designed to withstand.33 times the specified loads if these items are subject to severe wear and tear through frequent removal (e.g.The area over which these pressures are applied must simulate pressures occurring during high localised impacts on the hull or float, but need not extend over an area that would induce critical stresses in the frames or in the overall structure.The distribution of the limit loads among the wheels of the landing gear must be established for each landing, taxiing, and ground handling condition, taking into account the effects of the following factors: (1) The airworthiness number of wheels and their physical arrangements.(effective 2017/06/19) (b) The control system and surface loads due to ground gust may be assumed to be static loads, and the hinge moments H must be computed from the formula: (effective 2017/06/19) H K 1/2 oV2 c S Where K hinge moment factor for ground gusts derived.(c) Equipment These design standards in the following documents apply: Standard Criteria for Acceptance for Installation As contained in Chapter 537: (effective 2019/05/29) CAN TSO C124 or later (effective 2019/05/29) Acceptable for new and existing FDR installations (effective 2019/05/29) CAN-TSO-C121a or later (effective 2019/05/29) Acceptable.(amended 2009/12/01) (D) The antenna must be mounted as far aft as possible.The angle of dead rise to be used in determining the float bottom pressures is set forth in paragraph (b) of this section.(d) Unsymmetrical loading on the empennage arising from buffet conditions of 525.305(e) must be taken into account.