(13) Procedures for operation of integrated flight guidance and control systems. This should include proper pilot response to cockpit warnings, diagnosis of system failures, discussion of possible pilot-induced flight control system problems, and use of the system in a safe manner.
411. SECTION 23.1583 OPERATING LIMITATIONS.
a. Limitations Section. The purpose of the Limitations Section is to present the limitations applicable to the airplane model by serial number, if applicable, as established in the course of the type certification process in determining compliance with Parts 23 and 36. The limitations should be presented without explanation other than those explanations prescribed in Parts 23 and 36.
The operating limitations contained in the Limitations Section (including any noise limited weights) should be expressed in mandatory, not permissive, language. The terminology used in the AFM should be consistent with the relevant regulatory language.
b. GAMA Specification. GAMA Specification No. 1, Revision No. 1 dated September 1, 1984, section 2, provides guidance for the contents of the limitations section. Additional guidance is provided below for "Kinds of Operation," "Fuel Limitations," and "Commuter Category."
c. Kinds of Operation Equipment List (KOEL). The KOEL is to be placed in the limitations section of the AFM since the KOEL items form part of the limitations applicable to airplane operation. The sample KOEL given in Appendix 6 lists systems and equipment for a specific airplane in an acceptable format. Although the sample KOEL may contain items that are not applicable to all airplanes, it may be used as a guide.
Although there is no specific format required for the KOEL, we recommend, in the interest of standardization, that the KOEL be placed in columns and each item of equipment required for a specific type of operation for which the airplane is approved be noted in the appropriate column.
Regardless of the format used, the KOEL should provide for:
(1) The kinds of operation for which the airplane was type certificated (that is, day or night Visual Flight Rules (VFR), day or night Instrument Flight Rules (IFR), and icing conditions).
(2) The identity of the systems and equipment upon which type certification for each kind of operation was predicated and must be installed and operable for the particular kind of operation indicated. Systems and equipment necessary for certification includes those:
(i) required under the basic airworthiness requirements;
(ii) required by the operating rules;
(iii) required by special conditions;
(iv) required to substantiate equivalent safety findings;
(v) required by airworthiness directives (AD), and
(vi) either items of equipment or systems not specifically required under items (i) through (v) of this paragraph but used by the applicant in order to show compliance with the regulations.
The KOEL should not:
(1) Contain those obvious components required for the airplane to be airworthy, such as wings, empennage, engines, landing gear, brakes, and so forth.
(2) Contain an exceptions column.
d. Fuel Limitations. The fuel limitations discussion in GAMA Specification 1 may not be applicable, depending on the airplane certification basis.
e. Commuter Category Airplanes. For those performance weight limits that may vary with runway length, altitude, temperature, and other variables, the variation in weight limitation may be presented as graphs in the Performance Section of the manual and included as limitations by specific reference in the Limitations Section of the AFM.
412. SECTION 23.1585 OPERATING PROCEDURES.
a. Explanation. See GAMA Specification 1.
b. Electronic Checklist Displays.
(1) Background. Checklists, both hard copy and electronic displays, are a method used by manufacturers to provide (in part) the normal and emergency operating procedures required by § 23.1585. Section 23.1581 is also applicable for the manner and format of presentation.
(2) Display Content. For those airplanes with approved AFM's, the wide variety of configurations and corresponding flight manual supplements within a single model may establish a virtually unique set of checklist procedures for each individual airplane. The responsibility for electronic checklist display contents rests with the operator. A hard copy of the AFM should be available to the operator for reference.
(3) AFM Changes. Incorporation of STC’s could necessitate changes to the flight manual, flight manual supplements, or addition of new supplements. These supplements could require revision to the checklist for that particular airplane. Such changes should be made by the operator.
(4) Operator Revisions. Although it is not necessary for equipment manufacturers to store electronic checklist data in such a manner that it cannot be changed in the field, some equipment manufacturers have chosen to program checklist data in a manner that prevents field alternation. The operator would be responsible for ensuring the checklist data is revised as necessary upon installation of new/different equipment.
(5) Disclaimers. Electronic checklists are usually displayed on the same cathode-ray tube (CRT) as other electronic displays. Certain disclaimer statements may be appropriate.
Presentation of a disclaimer statement each time the equipment is turned on will provide adequate notification to the pilot. This disclaimer should include statements that clearly state:
(i) Contents of the checklists are the responsibility of the operator.
(i) The approved AFM takes precedence in case of conflicting checklist information.
(6) Automatic Display. Automatic display of appropriate checklists during conditions of engine failure, generator failure, and so forth, will require a review based upon the specific application involved. Approval of the checklist content, malfunction prioritization, and operation is required.
413. SECTION 23.1587 PERFORMANCE INFORMATION.
a. Performance Information. This section contains the airworthiness performance information necessary for operation in compliance with applicable performance requirements of Part 23, applicable special conditions, and data required by Part 36. Additional information and data essential for implementing special operational requirements may be included. Performance information and data should be presented for the range of weight, altitude, temperature, airplane configurations, thrust rating, and any other operational variables stated for the airplane. This information should include a discussion of icing operations, loss of performance possible, and any information to aid in recognition of icing conditions that may exceed the certificated capabilities of the aircraft ice protection systems.
b. Normal, Utility, and Acrobatic Category Airplanes. See GAMA Specification 1.
c. Commuter Category Airplanes.
(1) General. Include all descriptive information necessary to identify the precise configuration and conditions for which the performance data are applicable. Such information should include the complete model designations of airplane and engines, the approved flap, sweep, or canard settings, definition of installed airplane features and equipment that affect performance, together with the operative status thereof (for example, antiskid devices, automatic spoilers, and so forth). This section should also include definitions of terms used in the Performance Section (that is, IAS, CAS, ISA, configuration, net takeoff flight path, icing conditions, and so forth), plus calibration data for airspeed (flight and ground), Mach number, altimeter, ambient air temperature, and other pertinent information.
(2) Performance Procedures. The procedures, techniques, and other conditions associated with attainment of the flight manual performance data should be included. Performance procedures may be presented as a performance subsection or in connection with a particular performance graph. In the latter case, a comprehensive listing of the conditions associated with the particular performance may serve the objective of "procedures" if sufficiently complete.
(3) Thrust or Power Setting. Thrust or power settings should be provided for at least takeoff and maximum continuous and the methods required to obtain the performance shown in the AFM. If appropriate, these data may be required to be shown for more than one thrust setting parameter.
(4) Takeoff Speeds. The operational takeoff speeds V1, VR, and V2 should be presented together with associated conditions. Section 23.1587(d)(10) requires the speeds be given in CAS. Since the flightcrew flies IAS, the airspeeds should also be presented in IAS. The V1 and VR speeds should be based upon "ground effect" calibration data; the V2 speeds should be based upon "free air" calibration data.
(5) Takeoff Distance. Takeoff distance should be shown in compliance with § 23.59.
(6) Climb Limited Takeoff Weight. The climb limited takeoff weight, that is the most limiting weight showing compliance with § 23.67, should be provided.
(7) Miscellaneous Takeoff Weight Limits. Takeoff weight limits, for any equipment or characteristic of the airplane configuration which imposes an additional takeoff weight restriction, should be shown (that is, tire speed limitations, brake energy limitations, and so forth).
(8) Takeoff Climb Performance. For the prescribed takeoff climb airplane configurations, the climb gradients should be presented together with associated conditions. The scheduled climb speed(s) should be included.
(9) Takeoff Flight Path Data. The takeoff flight paths of § 23.61 or performance information necessary to enable construction of such paths, together with associated conditions (that is, procedures, speed schedules), should be presented for the configurations and flight path segments existing between the end of the prescribed takeoff distance and the point of attaining the en route climb configuration airspeed or 1500 feet, whichever is higher.
(10) En Route Climb Data. The climb gradients prescribed in § 23.67 should be presented together with associated conditions, including the speed schedule used.
(11) Balked Landing Climb Limited Landing Weight. The climb limited landing weight that is the most limiting weight showing compliance with § 23.77.
(12) Approach Climb Limited Landing Weight. The climb gradient determined in § 23.67(e)(3) should be presented. The required climb gradient may limit the landing weight.
(13) Landing Approach Speeds. The scheduled speeds associated with the approved landing distances should be presented together with associated conditions.
(14) Landing Distance. The landing distance from a height of 50 feet should be presented together with associated ambient temperature, altitude, wind conditions, and weights up to the maximum landing weight. Operational landing distance data should be presented for smooth, dry, and hard-surfaced runways. At the option of the applicant, with concurrence by the FAA, additional data may be presented for wet or contaminated runways and for other than smooth, hard-surfaced runways.
414. SECTION 23.1589 LOADING INFORMATION. See GAMA SPECIFICATION 1.