14 cfr part 25. Equipment, systems, and installations. ( b) Each lift and drag device control must be designed and located to make inadvertent operation improbable. (a) This appendix specifies requirements for preparation of Instructions for Continued Airworthiness as required by §§ 25. The limit loads must be determined for all critical altitudes, weights, and weight distributions as specified in § 25. 106 (f), 106 (g), 40113, 44701, 44702 and 44704. Symmetric for −3° flight path angle. General. ( 1) The effects of deformation are not significant; ( 2) The deformations involved are fully accounted for in the analysis; or. . An alert meets the warning requirement for cabin pressure altitude limits if it warns the flightcrew when the cabin pressure altitude exceeds 10,000 feet, except as provided in paragraph (d) of this section. ( c) The extremes within which compliance with each applicable Nov 9, 2020 · Each powerplant control must be located, arranged, and designed under §§ 25. These materials are incorporated as they exist on the date of the approval, and notice of any change in these materials will be published in the Federal Register. view historical versions. 25–23, 35 FR 5672, Apr. Function and installation. The instructions may be incomplete at type certification if a program exists to ensure their completion prior to delivery of the first airplane or issuance of a standard certificate of airworthiness, whichever occurs later. It includes systematic procedures, practices, and policies for the management of safety risk. gov; View the PDF for Appendix L to Part 25, Title 14; These links go to the official, published CFR, which is updated annually. 1316 Electrical and electronic system lightning protection Title 14 - Aeronautics and Space Chapter I - FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION Subchapter C - AIRCRAFT Part 25 - AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES View the PDF for 14 CFR Part 25 Subpart H; These links go to the official, published CFR, which is updated annually. [Doc. 3 V SR; and. 857. 101 Organization and Purpose 1/1. 1721. aircraft fall into Part 129. Special consideration for widespread fatigue damage must be Displaying title 14, up to date as of 3/21/2024. ( g) Stall warning must also be provided in each abnormal Unless otherwise specified, a factor of safety of 1. Powerplant instruments. gov; View the PDF for 14 CFR Part 25 Subpart G - Markings and Placards; These links go to the official, published CFR, which is updated annually. ( b) Generating system. Choosing an item from citations and headings will bring you directly to the content. 303 must be multiplied by the highest pertinent special factor of safety prescribed in §§ 25. 7 percent for four-engine airplanes, at V FTO with—. Except as provided in § 25. ( 4) The means for controlling the engine-cooling air supply in the position that provides adequate cooling in the hot-day condition. ( b) Each of the following cargo or baggage compartments, as defined in § 25. 2 Airspeed approved for all-engines-operating initial climb. FAA–2002–6717, 72 FR 1873, Jan. Subpart F—Equipment General 25. Title 25 was last amended 3/13/2024. 121 for the flight condition. In addition—. C. Lift and drag devices intended for ground operation The factor of safety prescribed in § 25. 1309 Equipment, systems, and installations. ( b) The load distribution limits may not exceed—. The maximum continuous intensity of atmospheric icing conditions (continuous maximum icing) is defined by the variables of the cloud liquid water content, the mean effective diameter of the cloud droplets, the ambient air temperature, and the interrelationship of these three variables as shown in figure 1 View Title 14 on govinfo. 5 must be applied to the prescribed limit load which are considered external loads on the structure. ( 2) The probability of multiple failures and undetected failures. 903 (e View Title 14 on govinfo. As a result, it may not include the most recent changes applied to the CFR. 16, 2007] Title 14 was last amended 3/21/2024. ( 4) The crew warning cues, corrective Unless otherwise provided, prescribed loads are limit loads. gov; View the PDF for 14 CFR Part 25 Subpart C; These links go to the official, published CFR, which is updated annually. No. Part 61. 951. ( 2) Within 10 seconds measured from the time when the opening means is actuated to the time when In the landing configuration, the steady gradient of climb may not be less than 3. Safety objective means a measurable goal or desirable outcome related to safety. Appropriate warning markings on the cabin pressure differential indicator meet the warning requirement for pressure differential limits. ( a) The extremes selected by the applicant; ( b) The extremes within which the structure is proven; or. ( 1) The selected limits; ( 2) The View the PDF for 14 CFR Part 25 Subpart E - Fuel System; These links go to the official, published CFR, which is updated annually. Title 14 was last amended 3/21/2024. ( 4) If the applicant These incorporations by reference were approved by the Director of the Federal Register in accordance with 5 U. The extreme forward and the extreme aft center of gravity limitations must be established for each practicably separable operating condition. Appendix C to Part 25 Part I—Atmospheric Icing Conditions (a) Continuous maximum icing. 119 and 25. 552 (a) and 1 CFR part 51. If the owner is less than 13 years of age, then the small unmanned aircraft must be registered by a person who is at least 13 years of age. 1 General. 1 and K25. ( e) Information must be furnished that indicates that when the fuel quantity indicator reads “zero” in level flight, any fuel Each hydraulic system must: ( 1) Have means located at a flightcrew station to indicate appropriate system parameters, if. Limit gust loads must be determined in accordance with the provisions: (1) Loads on each part of the structure must be determined by dynamic analysis. 853, 25. ( a) In non-icing conditions, with a climb speed The applicant must use the approach in paragraph (a) of this section which specifies the required test conditions. Jun 29, 2022 · This web page provides links to the standards and procedures for airworthiness certification of various types of aircraft, including 14 CFR Part 25 for transport category airplanes. 1729. For symmetrical step, bow, and stern landings, the limit water reaction load factors are those computed under § 25. 2. ( 1) The flaps and landing gear in any normal position; ( 2) The airplane trimmed for straight flight at a speed of 1. [Amdt. 14 cfr chapter i - chapter i—federal aviation administration, department of transportation . 111: ( 1) The steady gradient of climb may not be less than 1. 625 for each part of the structure whose strength is—. ( b) The one-engine-inoperative net flight path The FAA designates the information as protected under this part if the FAA—. On-demand and commuter operators adhere to regulations under Part 135. Subpart I. gov; View the PDF for 14 CFR 5. First generation turbine-powered transport category airplanes such as the DC-8, DC-9, and B-727, were originally certified under SR 422B. Correlation may be established on the ground as appropriate. In this attitude—. Displaying title 14, up to date as of 3/14/2024. 1 – 25. 1302 Installed systems and equipment for use by the flightcrew. ( 1) With the airplane in the normal ground attitude and in each of the attitudes corresponding to collapse of one or more legs of the landing gear; and. 1307 Miscellaneous equipment. 25–54, 45 FR 60173, Sept. Compliance must be shown using the ice accretions defined in part II, paragraphs (b) and (d) of Appendix O, assuming normal operation of the airplane and its ice protection system in accordance with the operating limitations and operating procedures established by the applicant and provided in the airplane flight manual. This revision, AC 25-7D, clarifies paragraph 23. 1729, and applicable provisions of parts 21 and 26 of this chapter. 11 of this part. Subchapter D. ( i) The flight guidance system functions, controls, indications, and alerts must be designed to minimize flightcrew errors and confusion concerning the behavior and View Title 14 on govinfo. CFR Final Rule Federal Register Information [Federal Register: December 24, 1964] [Page 18289] Header Information DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Parts 1, 4a, 4b, 25, and 91 [Docket No. Criteria for determining minimum flight crew. 1 A combination of weight, altitude, and temperature (WAT) such that the thrust or power setting produces the minimum climb gradient specified in § 25. Sec. 527. Enforcement of Nondiscrimination on the Basis of Handicap in Programs or Activities Conducted by the Navajo and Hopi Indian Relocation Commission. 23 (a), or. ( ii) Any two engines on Navigate by entering citations or phrases (eg: 1 CFR 1. Jan 3, 2012 · PART 25 - AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES Authority: 49 U. 11, 1980] Electronic Code of Federal Regulations (e-CFR) Title 14—Aeronautics and Space; CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION; SUBCHAPTER C—AIRCRAFT; PART 25—AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES; Appendix C to Part 25 View Title 14 on govinfo. 25. 1301 Function and installation. This web page is the official text of the Federal Aviation Administration (FAA) regulation that establishes the airworthiness standards for transport category airplanes. Title 14 was last amended 2/16/2024. 14 CFR part 25. The buffet onset envelopes presented may reflect the center of gravity at which the airplane is normally loaded during cruise if corrections for the effect of different center of gravity locations are furnished. 24, 1964, unless otherwise noted. Aeronautics and Space. 5 percent for three-engine airplanes, and 1. No such limit may lie beyond—. The maximum kinetic energy accelerate-stop is a rejected takeoff for the most critical combination of airplane takeoff weight and speed. Chapter I. These loads must be distributed to conservatively approximate or closely represent actual conditions. ( 2) Simulated Icing Test. 5066; Amendment Nos. Subpart E. Safety Management System (SMS) means the formal, top-down, organization-wide approach to managing safety risk and assuring the effectiveness of safety risk controls. The required generating capacity, and number and kinds of power sources must—. 777 through 25. 4, Engine Restart Capability—§ 25. ( 3) The methods and assumptions used are sufficient to cover the effects of these deformations. It must be substantiated by dynamometer testing that the wheel, brake, and tire Appendix H to Part 25—Instructions for Continued Airworthiness H25. 5066, 29 FR 18291, Dec. For airplanes with more than two engines, the applicant Appendix D to Part 25. 44103 (c), registration is not evidence of aircraft ownership in any proceeding in which ownership of an unmanned aircraft by a particular person is in issue. eCFR Content. In addition, it must meet the following requirements: ( a) Each control must be located so that it cannot be inadvertently operated by persons entering, leaving, or moving normally in, the cockpit. Aircraft certified under 14 CFR Part 25 must comply with the airworthiness standards for airplanes in the transport category. 1529, 25. ( 1) Possible modes of failure, including malfunctions and damage from external sources. Repeated load and static analyses supported by test evidence and (if available) service experience must also be incorporated in the evaluation. ( i) At maximum regulated voltage or power; ( ii) During a flight of maximum duration; and. View Title 14 on govinfo. Sep 20, 2023 · General Operating and Flight Rules (14 CFR Part 91) Certification: Pilots, Flight Instructors, and Ground Instructors (14 CFR Part 61) Pilot Schools (14 CFR Part 141) Commercial Space Transportation. ( 1) Be determined by an electrical load analysis; and. ( 1) For symmetrical step landings, the resultant water load must be applied at the keel, through the center of gravity, and must be directed perpendicularly to the keel line; ( 2) For symmetrical bow landings Appendix K to Part 25—Extended Operations (ETOPS) This appendix specifies airworthiness requirements for the approval of an airplane-engine combination for extended operations (ETOPS). 33 times the specified loads if these items are subject to severe wear and tear through frequent removal (e. 479 (d) (1), and. 621 through 25. 335 (a). 855, and 25. ( 2) Meet the requirements of § 25. 25. The correlation must cover the airspeed range over which the airplane is to be operated, the range of altitude to which the airplane is limited, and 360 degrees of heading. Part I defines this Appendix as a description of supercooled large drop icing conditions in which the drop median volume diameter (MVD) is less than or greater than 40 µm, the maximum mean effective drop diameter (MED) of Appendix C of this part continuous maximum (stratiform clouds) icing (1) Each certificate holder that was issued an air carrier or operating certificate and operations specifications under the requirements of part 135 of this chapter or under SFAR No. § 25. ( c) Time limit. SR 422B was recodified with minor changes to 14 CFR part 25, which became effective February 1965. 25 Weight limits. 1309. Fuel System. 321 (b), and all critical speeds within the ranges indicated in § 25. There have been changes in the last two weeks to Title 25. Title 14. In the en route configuration at the end of the takeoff path determined in accordance with § 25. Subpart F. Miscellaneous equipment. Suitable precautions must be taken to avoid drafts. May 4, 2018 · This AC includes flight test methods and procedures to show compliance with the regulations contained in title 14, Code of Federal Regulations (14 CFR) part 25, subpart B, “Flight,” which address airplane performance and handling characteristics. 1310 Power source capacity and distribution. ( iii) Life preservers or their storage locations must be designed so that tampering is evident. Subchapter C. ( i) It performs a function necessary for continued safe flight and landing; or. ( c) In accordance with 49 U. gov; View the PDF for 14 CFR Part 25 Subpart C - Emergency Landing Conditions; These links go to the official, published CFR, which is updated annually. ( ii) Release high-energy debris through the engine casing or result in a hazardous failure of the engine casing, ( iii) Generate loads greater than those ultimate loads specified in § 33. The accelerate-stop brake kinetic energy absorption requirement of each wheel, brake, and tire assembly must be determined. ( 3) The power or thrust necessary to maintain level flight at 1. ( i) The critical engine inoperative and the Appendix O to Part 25—Supercooled Large Drop Icing Conditions This Appendix consists of two parts. § 61. If the airplane experiences an excursion outside this range, a means must be provided to prevent the flight guidance system from providing guidance or control to an unsafe speed. View the PDF for 14 CFR Part 25 Subpart G - Airplane Flight Manual; These links go to the official, published CFR, which is updated annually. Power source capacity and distribution. subchapter a—definitions and general requirements The local attachments for these items should be designed to withstand 1. The following basic workload functions are considered: ( 1) Flight path control. Displaying title 14, up to date as of 3/20/2024. Oct 30, 2020 · The airplane is assumed to be subjected to symmetrical vertical and lateral gusts in level flight. cfr ; prev | next. ( 2) Essential loads, after failure of any one prime mover, power converter, or energy storage device. Designs that prevent concealment of objects with volumes 20 cubic inches and greater satisfy this requirement. 3, each applicant seeking ETOPS type design approval must comply with the provisions of Appendix K of this part. ( 1) Be either bright orange or bright yellow; The tests must be conducted with an occupant simulated by a 170-pound anthropomorphic test dummy, as defined by 49 CFR Part 572, Subpart B, or its equivalent, sitting in the normal upright position. 1-6, 4a-0, 4b-0, 25-0, 91-10] Recodification and new Part 25 Preamble Information Electronic Code of Federal Regulations (e-CFR) Title 14—Aeronautics and Space; CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION; SUBCHAPTER C—AIRCRAFT; PART 25—AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES; Appendix D to Part 25 Apr 4, 1997 · Displaying title 14, up to date as of 3/21/2024. ( 1) Makes the findings as § 193. 1 49 CFR 172. ( 2) Compliance with paragraph (b) (1) of this View the PDF for 14 CFR Part 25 Subpart E - Powerplant Controls and Accessories; These links go to the official, published CFR, which is updated annually. ( ii) In the event of hydraulic system malfunction, corrective action by the crew to ensure continued safe flight and landing is necessary; 14 CFR Part 43 Alternate reference (approximately 25+ pages) The Electronic Code of Federal Regulations (eCFR) is a continuously updated online version of the View Title 14 on govinfo. 38–2 of 14 CFR part 121 before January 19, 1996, and that conducts scheduled passenger-carrying operations with: For the powerplant installation, certain additional provisions of subpart E of this part may be found applicable. 8, 1970] The empennage structure must be designed to assure capability of continued safe flight and landing of the airplane after impact with an 8-pound bird when the velocity of the airplane (relative to the bird along the airplane's flight path) is equal to VC at sea level, selected under § 25. 853 Compartment interiors. Except as provided in paragraphs (c) (1) and (c) (2) of Compliance with this requirement must be demonstrated in flight with—. 25; These links go to the official, published CFR, which is updated annually. ( c) Subject to appreciable variability because of The flight paths must be determined at a speed not less than V FTO, with—. Displaying title 14, up to date as of 3/15/2024. 1305 Powerplant instruments. 3 V SR. 2 of this appendix. View the PDF for 14 CFR Part 25 Subpart E - Induction System; These links go to the official, published CFR, which is updated annually. 2 percent, with the engines at the power or thrust that is available 8 seconds after initiation of movement of the power or thrust controls from the minimum flight idle to the go-around power or thrust setting—. Part 25. View the PDF for 14 CFR Part 25 Subpart F - Electrical Systems and Equipment; These links go to the official, published CFR, which is updated annually. Compliance with this section by provision of View the PDF for 14 CFR Part 25 Subpart C - Control Surface and System Loads; These links go to the official, published CFR, which is updated annually. The materials are available for purchase The Code of Federal Regulations Part 14: Rules Implementing the Equal Access to Justice Act of 1980: 25. The following are considered by the Agency in determining the minimum flight crew under § 25. Each emergency exit must be capable of being opened, when there is no fuselage deformation—. ( 1) A change in downward vertical velocity (Δ v) of not less than 35 feet per second, with the airplane's longitudinal axis canted downward 30 For each cargo or baggage compartment, the following apply: ( a) The compartment must meet one of the class requirements of § 25. 1 Regulation Y FAR). ( 1) For symmetrical step landings, the resultant water load must be applied at the keel, through the center of gravity, and must be directed perpendicularly to the keel line; ( 2) For symmetrical bow landings Navigate by entering citations or phrases (eg: 1 CFR 1. 1801: Part 26: When analytical methods are used to show compliance with the ultimate load strength requirements, it must be shown that—. For two-engine airplanes, the applicant must comply with sections K25. 121(d) at maximum takeoff weight, less the actual or computed weight of fuel necessary for a 15-minute flight comprised of a takeoff, go-around, and landing at the airport of departure with the For the one-gear landing conditions, the airplane is assumed to be in the level attitude and to contact the ground on one main landing gear, in accordance with Figure 4 of Appendix A of this part. ( 2) Finds that there is an immediate safety or security need to obtain the information without carrying out the procedures in § 193. gov; View the PDF for 14 CFR Part 25 Subpart B; These links go to the official, published CFR, which is updated annually. Bureau of Indian Affairs, Department of the Interior, and Indian Health Service, Department of Health Electronic Code of Federal Regulations (e-CFR) Title 14—Aeronautics and Space; CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION; SUBCHAPTER C—AIRCRAFT; PART 25—AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES; Subpart B—Flight; General § 25. It also lists the other parts of the Code of Federal Regulations that are relevant to airworthiness certification, such as 14 CFR Part 21 for designation of applicable regulations and 14 CFR Part 45 for nationality and registration marks. 1303 Flight and navigation instruments. 0 inches in diameter. ( e) One of the following methods of icing detection and activation of the airframe ice protection system must be provided: ( 1) A primary ice detection system that automatically activates or alerts the flightcrew to activate the View the PDF for 14 CFR Part 25 Subpart B - General; These links go to the official, published CFR, which is updated annually. Learn more. 3 That thrust or power setting which, in the event of For symmetrical step, bow, and stern landings, the limit water reaction load factors are those computed under § 25. ( a) Uncertain; ( b) Likely to deteriorate in service before normal replacement; or. quick change interior items). ( d) Each recorder container must—. Flight and navigation instruments. 40°. 341 (b) (3). ( 3) The remaining engines at the available maximum continuous power or thrust; and. ( d) Seats and items of mass (and their supporting structure) must not deform under any loads up to those specified in paragraph (b The centerline of the required passageway width must not be displaced more than 5 inches horizontally from that of the exit. Only a few airplanes were certified under SR 422A, such as the Gulfstream I and the CL-44. (Adjacent exits must The evaluation must include a determination of the probable locations and modes of damage due to fatigue, corrosion, or accidental damage. 857, must have a liner that is separate from, but may be attached to, the airplane structure: ( 1) Any Class B through Class E cargo The analysis must consider—. 7; and. Source: Docket No. Dec 11, 2019 · Part 91 carriers are private operators, while foreign air carriers and foreign registered operators of U. gov; View the PDF for 14 CFR Part 25 Subpart D - Fire Protection; These links go to the official, published CFR, which is updated annually. Federal Aviation Administration, Department of Transportation. 1523: ( a) Basic workload functions. Subpart A. Installed systems and equipment for use by the flightcrew. Legislation & Policies; Regulations & Guidelines; Advisory Circulars The minimum flame temperature measured by a calibrated thermocouple pyrometer in the center of the flame must be 1550 °F. ( 1) Except as provided in paragraphs (b) (4) and (5) of this section, the following equation must be used: PL = P L−1g ± U σ Ā. S. 1555. If a weight and center of gravity combination is allowable only within certain load distribution limits (such as spanwise) that could be inadvertently exceeded, these limits and the corresponding weight and center of gravity combinations must be established. Displaying title 14, up to date as of 3/21/2024. ( ii) Toilets must be designed to prevent the passage of solid objects greater than 2. It covers the general, flight, structure, design, powerplant, equipment, operating limitations, electrical wiring, and special Federal Aviation Regulations for transport category airplanes. 857 at the certification basis of the L-1011. When a loading condition is prescribed in terms of ultimate loads, a factor of safety need not be applied unless otherwise specified. ( 3) The resulting effects on the airplane and occupants, considering the stage of flight and operating conditions, and. 2 percent for two-engine airplanes, 1. Part / Section. ( d) In this The power sources and the system must be able to supply the following power loads in probable operating combinations and for probable durations: ( 1) Loads connected to the system with the system functioning normally. No uncontrolled increase in cell temperature may result when the battery is recharged (after previous complete discharge)—. g. Testing conducted in simulated icing conditions, such as in an icing tunnel or behind an View Title 14 on govinfo. Authority: 49 U. ( a) The ground reactions must be the same as those obtained on that side under § 25. ( b) Unless otherwise provided, the specified air, ground, and water loads must be placed in equilibrium with inertia forces, considering each item of mass in the airplane. Subpart H. The generating system includes electrical power sources, main power busses, transmission cables, and associated control, regulation, and Lift and drag devices must maintain the selected positions, except for movement produced by an automatic positioning or load limiting device, without further attention by the pilots. ( ii) In lieu of one 10- or 20-inch passageway, there may be two passageways, between seat rows only, that must be at least 6 inches in width and lead to an unobstructed space adjacent to each exit. The flame must be applied for 30 seconds with one-third contacting the material at the center of the specimen and then removed. 1719. Part 27 This term refers to flight deck controls connected to the pitch, roll, or yaw control surfaces by direct mechanical linkages, cables, or push-pull rods in such a way that pilot effort produces motion or force about the hinge line. gov; View the PDF for 14 CFR Part 25 Subpart D; These links go to the official, published CFR, which is updated annually. ( iii) Under the most adverse cooling condition likely to occur in service. [Materials (including finishes, if applied) used in each compartment occupied by the crew or passengers (other than materials such as wire insulation, conduit, plastic material in "black boxes", rub strips, pulleys, and small (a) A fuel jettisoning system must be installed on each airplane unless it is shown that the airplane meets the climb requirements of §§ 25. 781 and marked under § 25. bj qf hm hj yc xt ca jd xj xn