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(1) Must be displayed in a conspicu$ place; and

(2) May not be easily erased, disfiged, or obscured.

(c) If the airplane is to be certificated more than one category

(1) The applicant must select one tegory on which the placards and arkings are to be based;

(2) The placard and marking infortion for the other categories in which e airplane is to be certificated must be Corded in the Airplane Flight Manual; d

(3) A reference to this information 1st be on a placard that also indicates e category on which the placards and arkings are based.

13.1543 Instrument markings: general.

For each instrument

(a) When markings are on the cover iss of the instrument, there must be ans to maintain the correct alignent of the glass cover with the face of e dial; and

(b) Each arc and line must be wide Lough and located to be clearly visible the pilot.

23.1545 Airspeed indicator.

(a) Each airspeed indicator must be arked to show calibrated airspeed. (b) The following markings must be ade:

(1) For the never-exceed speed VNE adial red line.

(2) For the caution range, a yellow extending from the red line specified subparagraph (1) of this paragraph the upper limit of the green arc specid in subparagraph (3) of this paraaph.

(3) For the normal operating range, green arc with the lower limit at Vs1 th maximum weight and with landing ar and wing flaps retracted, and the per limit at the maximum structural ruising speed VNo established under 23.1505(b).

(4) For the flap operating range, a hite arc with the lower limit at V 80 the maximum weight, and the upper

limit at the flaps-extended speed VF established under § 23.1511.

(5) For the one-engine-inoperative best rate-of-climb speed, Vr, a blue radial line and for the minimum control speed (one engine inoperative), Vмc, a red radial line.

(c) If VNE or VNo vary with altitude, there must be means to indicate to the pilot the appropriate limitations throughout the operating altitude range.

(d) Subparagraphs (1) through (3) of paragraph (b) and paragraph (c) of this section do not apply to aircraft for which a maximum operating speed VмO/Mмo is established under § 23.1505(c). For those aircraft there must either be a maximum allowable airspeed indication showing the variation of VмO/MмO with altitude or compressibility limitations (as appropriate), or a radial red line marking for VMO/Mмo must be made at lowest value of VмO/Mмо established for any altitude up to the maximum operating altitude for the airplane.

[Doc. No. 4080, 29 F.R. 17955, Dec. 18, 1964, as amended by Amdt. 23-3, 30 F.R. 14240, Nov. 13, 1965; Amdt. No. 23-7, 34 F.R. 13097, Aug. 13, 1969]

§ 23.1547 Magnetic direction indicator.

(a) A placard meeting the requirements of this section must be installed on or near the magnetic direction indicator. (b) The placard must show the calibration of the instrument in level flight with the engines operating.

(c) The placard must state whether the calibration was made with radio receivers on or off.

(d) Each calibration reading must be in terms of magnetic headings in not more than 30 degree increments. § 23.1549 Powerplant instruments.

For each required powerplant instrument

(a) Each maximum and, if applicable, minimum safe operating limit must be marked with a red radial line;

(b) Each normal operating range must be marked with a green arc not extending beyond the maximum and minimum continuous safe operating limits;

(c) Each takeoff and precautionary range must be marked with a yellow arc; and

(d) Each engine speed range that is restricted because of excessive vibration must be marked with a red arc.

§ 23.1551

Oil quantity indicator.

Each oil quantity indicator must be marked in sufficient increments to indicate readily and accurately the quantity of oil.

§ 23.1553 Fuel quantity indicator.

If the unusable fuel supply for any tank exceeds one gallon, or five percent of the tank capacity, whichever is greater, a red arc must be marked on its indicator extending from the calibrated zero reading to the lowest reading obtainable in level flight.

§ 23.1555 Control markings.

(a) Each cockpit control, other than primary flight controls and simple push button type starter switches, must be plainly marked as to its function and method of operation.

(b) Each secondary control must be suitably marked.

(c) For powerplant fuel controls

(1) Each fuel tank selector control must be marked to indicate the position corresponding to each tank and to each existing cross feed position;

(2) If safe operation requires the use of any tanks in a specific sequence, that sequence must be marked on or near the selector for those tanks; and

(3) Each valve control for any engine of a multiengine airplane must be marked to indicate the position corresponding to each engine controlled.

(d) The usable capacity of each tank must be marked on or near each selector controlling that tank.

(e) For accessory, emergency controls

auxiliary,

and

(1) If retractable landing gear is used, the indicator required by § 23.729 must be marked so that the pilot can, at any time, ascertain that the wheels are secured in the extreme positions; and

(2) Each emergency control must be red and must be marked as to method of operation.

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170 pounds, a placard stating the les weight must be permanently attached the seat structure.

(c) Fuel and oil filler openings. following must be marked on or n each appropriate filler cover:

(1) The word "fuel" and the minim fuel grade or designation for the engi (2) The word "oil" and the oil ta capacity.

(d) Emergency exit placards. E placard and operating control for e emergency exit must be red. A plac must be near each emergency exit c trol and must clearly indicate the lo tion of that exit and its method operation.

[Docket No. 4080, 29 F.R. 17955, Dec. 18, as amended by Amdt. No. 23-7, 34 F.R. 13 Aug. 13, 1969]

§ 23.1559 Operating limitations ard.

(a) There must be a placard in c view of the pilot stating: "This airp must be operated as a

or --

category airplane in compliance with operating limitations stated in the f of placards, markings, and manuals" sert correct categories).

(b) There must be a placard in o view of the pilot that specifies the of operations (such as VFR, IFR, day night) and the meteorological condit (such as icing conditions) to which operation of the airplane is limited from which it is prohibited, by the equ ment installed.

§ 23.1561 Safety equipment.

(a) Safety equipment must be pla marked as to method of operation.

(b) Stowage provisions for requ safety equipment must be marked for benefit of occupants.

§ 23.1563 Airspeed placards.

There must be an airspeed placa clear view of the pilot and as clos practicable to the airspeed indic This placard must list

(a) The design maneuvering VA; and

(b) The maximum landing gear ating speed VLO.

[Amdt. No. 23–7, 34 F.R. 13097, Aug. 13, § 23.1567 Flight maneuver placard

(a) For normal category airpla there must be a placard in front of in clear view of the pilot stating: acrobatic maneuvers, including s approved."

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(a) Furnishing information. The applicable information in §§ 23.1583 through 23.1589 must be furnished

(1) For each airplane of more than 3,000 pounds maximum weight, in an Airplane Flight Manual; and

(2) For each airplane of 6,000 pounds or less maximum weight, in an Airplane Flight Manual or in any combination of manuals, markings, and placards.

(b) Approval and segregation of information. Each part of the Airplane Flight Manual containing information prescribed in §§ 23.1583 through 23.1589 must be approved, segregated, identified, and clearly distinguished from each unapproved part of that manual.

(c) Additional information. Any information not specified in §§ 23.1583 through 23.1589 that is required for safe operation because of unusual design, operating, or handling characteristics,

must be furnished.

$23.1583 Operating limitations.

(a) Airspeed limitations. The following information must be furnished:

(1) Information necessary for the marking of the airspeed limits on the Indicator as required in § 23.1545, and the significance of each of those limits and of the color coding used on the indicator.

(2) The speeds VA, VLE, and VLO and their significance.

(b) Powerplant limitations. Information must be furnished to explain the powerplant limitations and to allow marking the instruments under $23.1549.

(c) Weight. The airplane flight manual must include

(1) The maximum weight; and

(2) The maximum landing weight, if

the design landing weight selected by the applicant is less than the maximum weight.

(d) Center of gravity. The established center of gravity limits must be furnished.

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(e) Maneuvers. The following thorized maneuvers, appropriate airspeed limitations, and unauthorized maneuvers must be furnished as prescribed in this section.

(1) Normal category airplanes. For normal category airplanes, acrobatic maneuvers, including spins, are unauthorized. If the airplane has been shown to be "characteristically incapable of spinning" under § 23.221(d), a statement to this effect must be entered. Other normal category airplanes must be placarded against spins.

(2) Utility category airplanes. For utility category airplanes, authorized maneuvers shown in the type flight tests must be furnished, together with recommended entry speeds. No other maneuver is authorized. If the airplane has been shown to be "characteristically incapable of spinning" under § 23.221(d), a statement to this effect must be entered.

(3) Acrobatic category airplanes. For acrobatic category airplanes, the approved flight maneuvers shown in the type flight tests must be included, together with recommended entry speeds. A placard listing the use of the controls required to recover from spinning maneuvers must be in the cockpit.

(f) Flight load factor. The positive limit load factors, in g's, must be furnished.

(g) Flight crew. If a flight crew of more than one is required for safety, the number and functions of the minimum flight crew must be furnished.

(h) Kinds of operation. The kinds of operation (such as VFR, IFR, day, or night) in which the airplane may or may not be used, and the meteorological conditions under which it may or may not be used, must be furnished. Any installed equipment that affects any operating limitation must be listed and identified as to operational function.

(i) If the unusable fuel supply in any tank exceeds five percent of the tank capacity, or one gallon, whichever is greater, information, showing that the fuel remaining in the tank when the quantity indicator reads "zero" cannot be safely used in flight, must be furnished. This information must be in the

Airplane Flight Manual (if provided) and on a placard.

(j) Climb conditions. For turbine engines, the temperatures and corresponding altitudes used in the climb test prescribed in § 23.1043 (b) (2) must be furnished.

(k) Maximum operating altitude. The maximum altitude established under § 23.1527 must be furnished.

[Docket No. 4080, 29 F.R. 17955, Dec. 18, 1964, as amended by Amdt. No. 23-7, 34 F.R. 13097, Aug. 13, 1969]

§ 23.1585 Operating procedures.

(a) For each airplane, information concerning normal and emergency procedures and other pertinent information necessary to safe operation must be furnished, including the demonstrated crosswind velocity and procedures and information pertinent to operation of the airplane in crosswinds.

(b) For airplanes of more than 6,000 pounds maximum weight, the airspeeds, procedures, and information pertinent to the use of the following airspeeds must be furnished:

(1) The recommended climb speed;
(2) Vx; and

(3) The approach speeds, including speeds for transition to the balked landing condition.

(c) For multiengine airplanes, the information must include:

(1) Procedures for maintaining or recovering control of the airplane with one engine inoperative at speeds above and below VMC.

(2) Procedures for making a landing with one engine inoperative and procedures for making a go-around with one engine inoperative, if this latter maneuver can be performed safely; otherwise, a warning against attempting the

maneuver.

(3) Procedures for obtaining the best performance with one engine inoperative, including the effects of the airplane configuration.

(d) For multiengine airplanes, information identifying each operating condition in which the fuel system independence prescribed in § 23.953 is necessary for safety must be furnished, together with instructions for placing the fuel system in a configuration used to show compliance with that section.

[Doc. No. 4080, 29 F.R. 17955, Dec. 18, 1964, as amended by Amdt. 23-3, 30 F.R. 14240, Nov. 13, 1965; Amdt. 23-5, 32 F.R. 6912, May 5, 1967; Amdt. No. 23-7, 34 F.R. 13097, Aug. 13, 1967]

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(2) The stalling speed, V at max mum weight and with landing gear an wing flaps retracted, and the effect up this stalling speed of angles of bank to 60 degrees.

(3) The takeoff distance determin under 23.51(a), the airspeed at th 50-foot height, the airplane configur tion (if pertinent), the kind of surfa used in the tests, and the pertinent i formation with respect to cowl flap p sition, use of flight-path control device and use of the landing gear retractio system.

(4) The landing distance determine under § 23.75 (a), the airplane configura tion (if pertinent), the kind of surfa used in the tests, and the pertinent i formation with respect to flap positi and the use of flight-path control d vices.

(5) The steady rate of climb, dete mined under §§ 23.65 (a), 23.67(a) (if a propriate) and 23.77(a), the airspee power, and, if pertinent, the airpla configuration.

(6) The calculated approximate effe on takeoff distance (subparagraph ( of this paragraph), landing distan (subparagraph (4) of this paragraph and steady rate of climb (subparagrap (5) of this paragraph), of variations in (i) Altitude from sea level to 8,00 feet; and

(ii) Temperature at these altitud from minus 60 degrees F. below standa to plus 40 degrees F. above standard.

For skiplanes, a statement in the Ai plane Flight Manual of the approxima

reduction in climb performance may be ased instead of complete new data for the skiplane configuration if

(1) The landing gear is fixed in both landplane and skiplane configurations; (2) The climb requirements are not critical; and

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(3) The climb reduction in the skiplane configurations is small (30 to 50 feet per minute).

(c) Multiengine airplanes. For multiengine airplanes, the following information must be furnished:

(1) The loss of altitude during the one engine inoperative stall shown under 23.205 (as measured from the altitude at which the airplane starts to pitch uncontrollably to the altitude at which level flight is regained) and the pitch angle during that maneuver. This information must be furnished—

(i) In the Airplane Flight Manual, for airplanes of more than 6,000 pounds maximum weight; and

(ii) On a placard, for airplanes of 6,000 pounds or less maximum weight. (2) The best climb speed, or the minimum descent speed, with one engine inoperative.

(3) The calculated approximate effect, on the steady rate of climb determined under § 23.67(b), of variations in—

(i) Altitude at sea level and at 8,000 feet in a standard atmosphere and cruise configuration; and

(ii) Temperature, at those altitudes, from 60° F. below standard to 40° F. above standard.

[Docket No. 4080, 29 F.R. 17955, Dec. 18, 1964, as amended by Amdt. No. 23–7, 34 F.R. 13097, Aug. 13, 1969]

§ 23.1589 Loading information.

The following loading information must be furnished:

(a) The weight and location of each item of equipment installed when the airplane was weighed under § 23.25.

(b) Appropriate loading instructions for each possible loading condition between the maximum and minimum weights determined under § 23.25 that can result in a center of gravity beyond— (1) The extremes selected by the applicant;

(2) The extremes within which the structure is proven; or

(3) The extremes within which compliance with each functional requirement is shown.

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The criteria in this Appendix may be used for certification in the normal, utility, and acrobatic categories, or in any combination of these categories. If certification in more than one category is desired, the design category weights must be selected to make the term "niW" constant for all categories or greater for one desired category than for others. The wings and control surfaces (including wing flaps and tabs) need only be investigated for the maximum value of "n1W", or for the category corresponding to the maximum design weight, where “n1W” is constant. If the acrobatic category is selected, a special unsymmetrical flight load investigation in accordance with subparagraphs A23.9 (c) (2) and A23.11 (c) (2) of this Appendix must be completed. The wing, wing carrythrough, and the horizontal tail structures must be checked for this condition. The basic fuselage structure need only be investigated for the highest load factor design category selected. The local supporting structure for dead weight items need only be designed for the highest load factor imposed when the particular items are installed in the airplane. The engine mount, however, must be designed for a higher side

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