AMC 25.101(h)(3) General

• ED Decision 2003/2/RM found in: CS-25 Amdt 27 - Large Aeroplanes (Jan 2023)

AMC 25.101(h)(3) General ED Decision 2003/2/RM [CS 25.109(a) and (b)](#_DxCrossRefBm1709820677) require the accelerate-stop distance to include a distance equivalent to 2 seconds at V1 in addition to the demonstrated distance to accelerate to V1 and then bring the aeroplane to a full stop. This additional distance is not intended to allow extra time for making a decision to stop as the aeroplane passes through V1, but is to account for operational variability in the time it takes pilots to accomplish the actions necessary to bring the aeroplane to a stop. It allows for the typical requirement for up to three pilot actions (i.e. brakes – throttles – spoilers) without introducing additional time delays to those demonstrated. If the procedures require more than three pilot actions, an allowance for time delays must be made in the scheduled accelerate-stop distance. These delays, which are applied in addition to the demonstrated delays, are to be 1 second (or 2 seconds if a command to another crew member to take the action is required) for each action beyond the third action. This is illustrated in Figure 1.  <table cellpadding="0" cellspacing="0" width="100%"><tr><td><div></div></td></tr></table> <table cellpadding="0" cellspacing="0" width="100%"><tr><td><div><p>* 2 sec. where a command to another crew member is required. </p></div></td></tr></table> <table cellpadding="0" cellspacing="0" width="100%"><tr><td><div></div></td></tr></table> FIGURE 1. ACCELERATE-STOP TIME DELAYS where:– VEF is the calibrated airspeed selected by the applicant at which the critical engine is assumed to fail. The relationship between VEF and V1 is defined in [CS 25.107](#_DxCrossRefBm1709820678). ∆tact1 = the demonstrated time interval between engine failure and activation of the first deceleration device. This time interval is defined as beginning at the instant the critical engine is failed and ending when the pilot recognises and reacts to the engine failure, as indicated by the pilot’s application of the first retarding means during accelerate-stop tests. A sufficient number of demonstrations should be conducted using both applicant and Agency test pilots to assure that the time increment is representative and repeatable. The pilot’s feet should be on the rudder pedals, not the brakes, during the tests. For AFM data expansion purposes, in order to provide a recognition time increment that can be executed consistently in service, this time increment should be equal to the demonstrated time or 1 second, whichever is greater. If the aeroplane incorporates an engine failure warning light, the recognition time includes the time increment necessary for the engine to spool down to the point of warning light activation, plus the time increment from light ‘on’ to pilot action indicating recognition of the engine failure. ∆tact 2 = the demonstrated time interval between activation of the first and second deceleration devices. ∆tact3 = the demonstrated time interval between activation of the second and third deceleration devices. ∆tact4→n = the demonstrated time interval between activation of the third and fourth (and any subsequent) deceleration devices. For AFM expansion, a 1-second reaction time delay to account for in-service variations should be added to the demonstrated activation time interval between the third and fourth (and any subsequent) deceleration devices. If a command is required for another crew member to actuate a deceleration device, a 2-second delay, in lieu of the 1-second delay, should be applied for each action. For automatic deceleration devices that are approved for performance credit for AFM data expansion, established systems actuation times determined during certification testing may be used without the application of the additional time delays required by this paragraph.