Rules and Regulations. Final special conditions; correction

Agency: Federal Aviation Administration (FAA), DOT
Action: Final special conditions; correction
Citation: FR Doc. 2011-7144 · Docket No. NM438 Special Conditions No. 25-423-SC · 14 CFR 25

Summary

This document corrects an error that appeared in Docket No. NM438, Special Conditions No. 25-423-SC, which were published in the Federal Register on March 28, 2011. The error resulted in the omission of two paragraphs of text in The Special Conditions section.

Dates

Effective May 31, 2012.

Supplementary Information

The document designated as “Docket No. NM438, Special Conditions No. 25-423-SC” was published in the Federal Register on March 28, 2011 (76 FR 17022). The document issued special conditions pertaining to a high incidence protection system that replaces the stall warning system during normal operating conditions, prohibits the airplane from stalling, limits the angle of attack at which the airplane can be flown during normal low speed operations, and cannot be overridden by the flight crew. These special conditions were, and continue to be applicable to, Gulfstream Model GVI airplanes. As published, the document contained an error because paragraphs 3(e)(6) and 3(e)(7) were omitted. Due to its complexity the entire text of paragraph 3(e) is included below, including paragraphs 3(e)(6) and 3(e)(7). 3. Minimum Steady Flight Speed and Reference Stall Speed —In lieu of the requirements of § 25.103, the following special condition is issued: (e) V ^SR must be determined with the following conditions: (1) Engines idling, or, if that resultant thrust causes an appreciable decrease in stall speed, not more than zero thrust at the stall speed. (2) The airplane in other respects (such as flaps and landing gear) in the condition existing in the test or performance standard in which V ^SR is being used. (3) The weight used when V ^SR is being used as a factor to determine compliance with a required performance standard. (4) The center of gravity position that results in the highest value of reference stall speed. (5) The airplane trimmed for straight flight at a speed selected by the applicant, but not less than 1.13 V ^SR and not greater than 1.3 V ^SR . (6) The high incidence protection function disabled, or adjusted to a high enough incidence to allow full development of the maneuver to the angle of attack corresponding to V ^SR . (7) From the stabilized trim condition, apply the longitudinal control to decelerate the airplane so that the speed reduction does not exceed one knot per second. Since no other part of the regulatory information has been changed, the special conditions are not being republished. Correction In Final special conditions document [FR Doc. 2011-7144 Filed 3-25-11; 8:45 a.m.]