(c) Weight. The following information shall be included:

(1) Maximum weight for which the airplane has been certificated,

(2) Airplane empty weight and center of gravity location,

(3) Useful load,

(4) The composition of the useful load, including the total weight of fuel and oil with tanks full.

(d) Load distribution. (1) All authorized center of gravity limits shall be stated. If the available space for loading the airplane is adequately placarded or so arranged that any reasonable distribution of the useful load listed in weight above will not result in a center of gravity location outside of the stated limits, this section need not include any other information than the statement of center of gravity limits.

(2) In all other cases this section shall also include adequate information to indicate satisfactory loading combinations which will assure maintaining the center of gravity position within approved limits.

(e) Maneuvers. All authorized maneuvers and the appropriate air-speed limitations as well as all unauthorized maneuvers shall be included in accordance with the following:

(1) Normal category. All acrobatic maneuvers, including spins, are unauthorized. If the airplane has been demonstrated to be characteristically incapable of spinning in accordance with §3.124 (d), a statement to this effect shall be entered here.

(2) Utility category. All authorized maneuvers demonstrated in the type flight tests shall be listed, together with recommended entry speeds. All other maneuvers are not approved. If the airplane has been demonstrated to be characteristically incapable of spinning in accordance with § 3.124 (d), a statement to this effect shall be entered here.

(3) Acrobatic category. All approved flight maneuvers demonstrated in the type flight tests shall be included, together with recommended entry speeds.

(f) Flight load factor. The positive limit load factors made good by the airplane's structure shall be described here in terms of accelerations.

(g) Flight crew. When a flight crew of more than one is required to operate the airplane safely, the number and

functions of the minimum flight crew shall be included.

§ 3.779 Operating procedures.

This section shall contain information concerning normal and emergency procedures and other pertinent information peculiar to the airplane's operating characteristics which are necessary to safe operation.

§ 3.780 Performance information.

(a) For airplanes with a maximum certificated take-off weight of more than 6,000 lbs., information relative to the items of performance set forth in subparagraphs (1) through (5) of this paragraph shall be included:

(1) The stalling speed, Vso, at maximum weight,

(2) The stalling speed, V11, at maximum weight and with landing gear and wing flaps retracted,

(3) The take-off distance determined in accordance with § 3.84, including the air speed at the 50-foot height, and the airplane configuration, if pertinent,

(4) The landing distance determined in accordance with § 3.86, including the airplane configuration, if pertinent,

(5) The steady rate of climb determined in accordance with § 3.85 (a), (c), and, as appropriate, (b), including the air speed, power, and airplane configuration, if pertinent.

(b) The effect of variation in paragraph (a) (2) of this section with angle of bank up to 60 degrees shall be included.

(c) The calculated approximate effect of variations in paragraph (a) (3), (4) and (5) of this section with altitude and temperature shall be included.

(d) The best climb/minimum descent speed with one engine inoperative for multiengine airplanes shall be included. [21 F.R. 3339, May 22, 1956, as amended by Amdt. 3-5, 24 F.R. 7067, Sept. 1, 1959] § 3.780-1 Calculated effects of temperature and altitude variations (FAA policies which apply to § 3.780). Section 3.780 requires that the calculated effects of variations in temperature and altitude on the take-off distance (§ 3.84(a) (2)), the landing distance (§ 3.86), and the steady rate of climb (§ 3.85 (a), (b), and (c)), shall be included in the Airplane Flight Manual. The following ranges of these variables

will be considered acceptable by the Administrator:

(a) The altitudes and temperatures for which performance in take-off distance, landing distance, take-off climb and balked landing climb shall be calculated are sea level to 7,000 feet and 0° F. to 100° F. respectively, except that take-off and landing distances for a seaplane need not show temperatures below 30° F. at altitudes above 1,000 feet.

(b) For multiengined aircraft, the climb with the critical engine inoperative shall be calculated for an altitude range of sea level to absolute ceiling and a temperature range from 60° F. below the standard temperature to 40° F. above the standard temperature at the altitude involved.

[Supp. 1, 12 F. R. 3438, May 28, 1947, as amended by Amdt. 1, 14 F. R. 36, Jan. 5, 1949] § 3.780-2 Performance data for altered

airplanes of this part (FAA policies which apply to § 3.780).

Performance data for altered airplanes of this part must be changed in the Airplane Flight Manual if the alteration decreases the performance below that given in the existing manual. If performance can be shown to equal or exceed original values then a statement in the manual to this effect is sufficient. [Supp. 10, 16 F. R. 3295, Apr. 14, 1951]

§ 3.780-3 Performance data and flight tests for ski installations on airplanes of this part (FAA policies which apply to § 3.780).

(a) Take-off and landing distances. It will not be necessary, in complying with § 3.780 (a) (3) and (4), to make take-off and landing distance tests on skiplane installations where landplane distances are given in the Airplane Flight Manual. The following, or similar, statements should be given in the performance information section of the Airplane Flight Manual.

(1) Take-off. Under the most favorable conditions of smooth packed snow at temperatures approximating 32° F. the skiplane take-off distance is approximately 10 percent greater than that shown for the landplane.

NOTE: In estimating take-off distances for other conditions caution should be exercised in that lower temperatures or other snow conditions will usually increase these dis

tances.

(2) Landing. Under the most favorable conditions of smooth packed snow

at temperatures approximating 32° F. the skiplane landing distance is approximately 20 percent greater than that shown for the landplane.

NOTE: In estimating landing distances for other conditions caution should be exercised in that other temperatures or other snow conditions may either decrease or increase these distances.

(b) Climb performance.

In cases

where the landing gear is fixed (both landplane and skiplane), where the climb requirements are not critical, and the climb reduction is small (30 to 50 feet per minute), the FAA will accept a statement of the approximate reduction in climb performance placed in the Airplane Flight Manual performance information section. For larger variations in climb performance, or where the minimum requirements are critical, or where the landing gear of the landplane was data retractable, appropriate climb should be obtained to determine the changes, and new curves, tables, or a note should be incorporated in the Airplane Flight Manual.

(c) Flight and handling tests. At least a general flight check should be made prior to approval. This should include more than one landing to determine the ground handling characteristics as well as take-off and landing characteristics. Note should be taken of ski angle at landing contact during tail high and tail low landings to avoid having the ski dig in or fail from localized stress. Ground control should be sufficient to satisfactorily complete a landing run with a turn off at slow speed in cases where brakes are not provided. In flight the ski should ride steady with no unusual drag and produce no unsatisfactory flight characteristics. Spin checks should be made on all aircraft in which spins are an approved maneuver. When spins are approved under § 3.124 (a), investigation with ski installations need not be made unless the spin characteristics of the type are known to be marginal.

[Supp. 10, 16 F. R. 3295, Apr. 14, 1951] Subpart H-Identification Data

§ 3.791 Identification plate.

A fireproof identification plate shall be securely attached to the structure in an accessible location where it will not likely be defaced during normal service.