[FAR Part § 25.331: [Flight Maneuver and Gust Conditions] - Symmetric maneuvering conditions -- FAA FARS, 14 CFR] -- Flightsim Aviation Zone - Number 1 Flight Simulation and Aviation Resource! Information, Tools, Downloads, Databases, FAQ, Aviation Humour, Glossaries, Directory, FS2006, Multimedia, Screenshots, Free Flight Planner, Weather Reports | Aviation Databases - aircraft, airports, airlines, countries, timezones | Flight Simulator X
 
» Support this site -> Shop Online at Amazon!
Friday 31 October 2014 14:49 GMT
 
 

FAA Federal Aviation Regulations (FARS, 14 CFR)

FARs   >   Part 25   >   Section 331 - Symmetric maneuvering conditions

PREVIOUS section 25.321  |  section 25.333 NEXT

FONT
serif sans
TEXT SIZE
T T T T

(a) Procedure. For the analysis of the maneuvering flight conditions specified in paragraphs (b) and (c) of this section, the following provisions apply:

(1) Where sudden displacement of a control is specified, the assumed rate of control surface displacement may not be less than the rate that could be applied by the pilot through the control system.

(2) In determining elevator angles and chordwise load distribution in the maneuvering conditions of paragraphs (b) and (c) of this section, the effect of corresponding pitching velocities must be taken into account. The in-trim and out-of-trim flight conditions specified in §25.255 must be considered.

(b) Maneuvering balanced conditions. Assuming the airplane to be in equilibrium with zero pitching acceleration, the maneuvering conditions A through I on the maneuvering envelope in §25.333(b) must be investigated.

(c) Pitch maneuver conditions. The conditions specified in paragraphs (c)(1) and (2) of this section must be investigated. The movement of the pitch control surfaces may be adjusted to take into account limitations imposed by the maximum pilot effort specified by §25.397(b), control system stops and any indirect effect imposed by limitations in the output side of the control system (for example, stalling torque or maximum rate obtainable by a power control system.)

Top of Page

(1) Maximum pitch control displacement at VA. The airplane is assumed to be flying in steady level flight (point A1, §25.333(b)) and the cockpit pitch control is suddenly moved to obtain extreme nose up pitching acceleration. In defining the tail load, the response of the airplane must be taken into account. Airplane loads that occur subsequent to the time when normal acceleration at the c.g. exceeds the positive limit maneuvering load factor (at point A2 in §25.333(b)), or the resulting tailplane normal load reaches its maximum, whichever occurs first, need not be considered.

(2) Specified control displacement. A checked maneuver, based on a rational pitching control motion vs. time profile, must be established in which the design limit load factor specified in §25.337 will not be exceeded. Unless lesser values cannot be exceeded, the airplane response must result in pitching accelerations not less than the following:

Top of Page

(i) A positive pitching acceleration (nose up) is assumed to be reached concurrently with the airplane load factor of 1.0 (Points A1 to D1, §25.333(b)). The positive acceleration must be equal to at least

where --

n is the positive load factor at the speed under consideration, and V is the airplane equivalent speed in knots.
 

(ii) A negative pitching acceleration (nose down) is assumed to be reached concurrently with the positive maneuvering load factor (points A2 to D2, §25.333(b)). This negative pitching acceleration must be equal to at least

where --

n is the positive load factor at the speed under consideration; and V is the airplane equivalent speed in knots.
 

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-23, 35 FR 5672, Apr. 8, 1970; Amdt. 25-46, 43 FR 50594, Oct. 30, 1978; 43 FR 52495, Nov. 13, 1978; 43 FR 54082, Nov. 20, 1978; Amdt. 25-72, 55 FR 29775, July 20, 1990; 55 FR 37607, Sept. 12, 1990; Amdt. 25-86, 61 FR 5220, Feb. 9, 1996; Amdt. 25-91, 62 FR 40704, July 29, 1997]

PRINTABLE VERSION of this PageE-MAIL THIS PAGE to Somebody!SAVE TO FAVORITES / Bookmark this PageLINK TO THIS PAGE! (view simple HTML code)

Current page:   FARs   >   Part 25   >   Section 331 - Symmetric maneuvering conditions

PREVIOUS section 25.321  |  section 25.333 NEXT

page stats: viewed 6495 unique times - last change 08-Jan-2005

SEARCH the FARS :

Top of Page

» DOWNLOADING (PARTS OF) THIS WEBSITE AUTOMATICALLY IS NOT ALLOWED! «

THIS IS NO OFFICIAL SOURCE -- [DISCLAIMER] [FAA WEBSITE]

See also: AIM | ATC | FSS | NOTAMS | PCG |

 
Top of page
add to favorites @ E-mail this! Link to this!
Top of page
© 2002-2014 - Legal | Contact | Advertise | Sitemap
Visit our $pons0rs:
8mm Film to DVD
hosted by 123XS || also visit: Flightsim Search & Aviation Search || Link to us!