Part V - Airworthiness Manual Chapter 523 - Normal, Utility, Aerobatic And Commuter Category Aeroplanes

Canadian Aviation Regulations (CARs) 2017-2

Content last revised: 2002/01/29

Preamble

SUBCHAPTERS

  • A (523.1-523.3),
  • B (523.21-523.253),
  • C (523.301-523.575),
  • D (523.601-523.871),
  • E (523.901-523.1203),
  • F (523.1301-523.1461),
  • G (523.1501-523.1589)

APPENDICES

A, B, C, D, E, F, G, H, I, J

(2001/06/01)

SUBCHAPTER G OPERATING LIMITATIONS AND INFORMATION

523.1501 General

  1. (a) Each operating limitation specified in 523.1505 through 523.1527 and other limitations and information necessary for safe operation must be established.

  2. (b) The operating limitations and other information necessary for safe operation must be made available to the crew members as prescribed in 523.1541 through 523.1589.

523.1505 Airspeed Limitations

  1. (a) The never-exceed speed VNE must be established so that it is:

    1. (1) Not less than 0.9 times the minimum value of VD allowed under 523.335; and

    2. (2) Not more than the lesser of:

      1. (i) 0.9 VD established under 523.335; or

      2. (ii) 0.9 times the maximum speed shown under 523.251.

  2. (b) The maximum structural cruising speed VNO must be established so that it is:

    1. (1) Not less than the minimum value of VC allowed under 523.335; and

    2. (2) Not more than the lesser of:

      1. (i) VC established under 523.335; or

      2. (ii) 0.89 VNE established under paragraph (a) of this section.

  3. (c)

    1. (1) Paragraphs (a) and (b) of this section do not apply to turbine aeroplanes or to aeroplanes for which a design diving speed VD/MD is established under 523.335 (b)(4). For those aeroplanes, a maximum operating limit speed (VMO/ MMO airspeed or Mach number, whichever is critical at a particular altitude) must be established as a speed that may not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training operations.

    2. (2) VMO/MMO must be established so that it is not greater than the design cruising speed VC/MC and so that it is sufficiently below VD/MD, or VDF/MDF for jets, and the maximum speed shown under section 523.251 to make it highly improbable that the latter speeds will be inadvertently exceeded in operations.
      (effective 2016/08/04)

    3. (3) The speed margin between VMO/MMO and VD/MD, or VDF/MDF for jets, may not be less than that determined under 523.335 (b), or the speed margin found necessary in the flight tests conducted under section 523.253.
      (effective 2016/08/04)

523.1507 Operating Manoeuvring Speed

The maximum operating manoeuvring speed, VO, must be established as an operating limitation.  VO is a selected speed that is not greater than VSiestablished in 523.335(c).

(Change 523-4 (96-09-01))

523.1511 Flap Extended Speed

  1. (a) The flap extended speed VFE must be established so that it is:

    1. (1) Not less than the minimum value of VF allowed in 523.345(b); and

    2. (2) Not more than VF established under 523.345(a), (c), and (d).

  2. (b) Additional combinations of flap setting, airspeed, and engine power may be established if the structure has been proven for the corresponding design conditions.

(Change 523-5)

523.1513 Minimum Control Speed

The minimum control speed VMC, determined under 523.149, must be established as an operating limitation.

523.1519 Weight and Centre of Gravity

The weight and centre of gravity limitations determined under 523.23 must be established as operating limitations.

523.1521 Powerplant Limitations

  1. (a) General.  The powerplant limitations prescribed in this section must be established so that they do not exceed the corresponding limits for which the engines or propellers are type approved.  In addition, other powerplant limitations used in determining compliance with this chapter must be established.

  2. (b) Take-off operation. The powerplant take -off operation must be limited by:

    1. (1) The maximum rotational speed (rpm);

    2. (2) The maximum allowable manifold pressure (for reciprocating engines);

    3. (3) The maximum allowable gas temperature (for turbine engines);

    4. (4) The time limit for the use of the power or thrust corresponding to the limitations established in subparagraphs (1) through (3) of this paragraph; and

    5. (5) The maximum allowable cylinder head (as applicable), liquid coolant and oil temperatures.

  3. (c) Continuous operation.  The continuous operation must be limited by:

    1. (1) The maximum rotational speed;

    2. (2) The maximum allowable manifold pressure (for reciprocating engines);

    3. (3) The maximum allowable gas temperature (for turbine engines); and

    4. (4) The maximum allowable cylinder head, oil, and liquid coolant temperatures.

  4. (d) Fuel grade or designation.  The minimum fuel grade (for reciprocating engines), or fuel designation (for turbine engines), must be established so that it is not less than that required for the operation of the engines within the limitations in paragraphs (b) and (c) of this section.

  5. (e) Ambient temperature.  For all aeroplanes except reciprocating engine-powered aeroplanes of 6,000 pounds or less maximum weight, ambient temperature limitations (including limitations for winterization installations if applicable) must be established as the maximum ambient atmospheric temperature at which compliance with the cooling provisions of 523.1041 through 523.1047 is shown.

(Change 523-4 (96-09-01))
(Change 523-5)

523.1522 Auxiliary Power Unit Limitations

If an auxiliary power unit is installed, the limitations established for the auxiliary power unit must be specified in the operating limitations for the aeroplane.

(Change 523-4 (96-09-01))

523.1523 Minimum Flight Crew

The minimum flight crew must be established so that it is sufficient for safe operation considering:

  1. (a) The workload on individual crew members and, in addition for commuter category aeroplanes, each crewmember workload determination must consider the following:

    1. (1) Flight path control,

    2. (2) Collision avoidance,

    3. (3) Navigation,

    4. (4) Communications,

    5. (5) Operation and monitoring of all essential aeroplane systems,

    6. (6) Command decisions, and

    7. (7) The accessibility and ease of operation of necessary controls by the appropriate crewmember during all normal and emergency operations when at the crewmember flight station.

  2. (b) The accessibility and ease of operation of necessary controls by the appropriate crew member; and

  3. (c) The kinds of operation authorizsed under 523.1525.

(Change 523-1 (88-01-01))

523.1524 Maximum Passenger Seating Configuration

The maximum passenger seating configuration must be established.

523.1525 Kinds of Operation

The kinds of operation authorised (e.g. VFR, IFR, day or night) and the meteorological conditions (e.g. icing) to which the operation of the aeroplane is limited or from which it is prohibited, must be established appropriate to the installed equipment.

(Change 523-4 (96-09-01))

523.1527 Maximum Operating Altitude

  1. (a) The maximum altitude up to which operation is allowed, as limited by flight, structural, powerplant, functional or equipment characteristics, must be established.

  2. (b) A maximum operating altitude limitation of not more than 25,000 feet must be established for pressurizsed aeroplanes unless compliance with 523.775(e) is shown.

(Change 523-4 (96-09-01))

523.1529 Instructions for Continued Airworthiness

The applicant must prepare Instructions for Continued Airworthiness in accordance with Appendix G to this Chapter that are acceptable to the Minister.  The instructions may be incomplete at type certificate if a program exists to ensure their completion prior to delivery of the first aeroplane or issuance of a standard certificate of airworthiness, whichever occurs later.

Markings and Placards

523.1541 General

  1. (a) The aeroplane must contain:

    1. (1) The markings and placards specified in 523.1545 through 523.1567; and

    2. (2) Any additional information, instrument markings, and placards required for the safe operation if it has unusual design, operating, or handling characteristics.

  2. (b) Each marking and placard prescribed in paragraph (a) of this section:

    1. (1) Must be displayed in a conspicuous place; and

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

  3. (c) For aeroplanes which are to be certificated in more than one category:

    1. (1) The applicant must select one category upon which the placards and markings are to be based; and

    2. (2) The placards and markings information for all categories in which the aeroplane is to be certificated must be furnished in the Aeroplane Flight Manual.

523.1543 Instrument Markings: General

For each instrument:

  1. (a) When markings are on the cover glass of the instrument, there must be means to maintain the correct alignment of the glass cover with the face of the dial; and

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

  3. (c) All related instruments must be calibrated in compatible units.

(Change 523-5)

523.1545 Airspeed Indicator

  1. (a) Each airspeed indicator must be marked as specified in paragraph (b) of this section, with the marks located at the corresponding indicated airspeeds.

  2. (b) The following markings must be made:

    1. (1) For the never-exceed speed VNE, a radial red line.

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

    3. (3) For the normal operating range, a green arc with the lower limit at VS1 with maximum weight and with landing gear and wing flaps retracted, and the upper limit at the maximum structural cruising speed VNO established under 523.1505(b).

    4. (4) For the flap operating range, a white arc with the lower limit at VSO at the maximum weight and the upper limit at the flaps extended speed VFE established under 523.1511.

    5. (5) For reciprocating multi-engine-powered aeroplanes of 6,000 pounds or less maximum weight, for the speed at which compliance has been shown with 523.69(b) relating to rate of climb at maximum weight and at sea level, a blue radial line.

    6. (6) For reciprocating multi-engine-powered aeroplanes of 6,000 pounds or less maximum weight, for the maximum value of minimum control speed, VMC, (one-engine-inoperative) determined under 523.149(b), a red radial line.

  3. (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. 

  4. (d) Subparagraphs (b)(1) through (b)(4) and paragraph (c) of this section do not apply to aeroplanes for which a maximum operating speed VMO/MMO is established under 523.1505(c). For those aeroplanes there must either be a maximum allowable airspeed indication showing the variation of VMO/MMO with altitude or compressibility limitations (as appropriate), or a radial red line marking for VMO/MMO must be made at lowest value of VMO/MMO established for any altitude up to the maximum operating altitude for the aeroplane.
    (effective 2016/08/04)

(Change 523-5)

523.1547 Magnetic Direction Indicator

  1. (a) A placard meeting the requirements of this section must be installed on or near the magnetic direction indicator.

  2. (b) The placard must show the calibration of the instrument in level flight with the engines operating.

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

  4. (d) Each calibration reading must be in terms of magnetic headings in not more than 30° increments.

  5. (e) If a magnetic non-stabilised direction indicator can have a deviation of more than 10 degrees caused by the operation of electrical equipment, the placard must state which electrical loads, or combination of loads, would cause a deviation of more than 10 degrees when turned on.

523.1549 Powerplant and Auxiliary Power Unit Instruments

For each required powerplant and auxiliary power unit instrument, as appropriate to the type of instruments:

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

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

  3. (c) Each take -off and precautionary range must be marked with a yellow arc or a yellow line; and

  4. (d) Each engine, auxiliary power unit, or propeller range that is restricted because of excessive vibration stresses must be marked with red arcs or red lines.

(Change 523-4 (96-09-01))

523.1551 Oil Quantity Indicator

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

523.1553 Fuel Quantity Indicator

A red radial line must be marked on each indicator at the calibrated zero reading, as specified in 523.1337(b)(1).

(Change 523-5)

523.1555 Control Markings

  1. (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.

  2. (b) Each secondary control must be suitably marked.

  3. (c) For powerplant fuel controls:

    1. (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. (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;

    3. (3) The conditions under which the full amount of usable fuel in any restricted usage fuel tank can safely be used must be stated on a placard adjacent to the selector valve for that tank; and

    4. (4) Each valve control for any engine of a multi-engine aeroplane must be marked to indicate the position corresponding to each engine controlled.

  4. (d) Usable fuel capacity must be marked as follows:

    1. (1) For fuel systems having no selector controls, the usable fuel capacity of the system must be indicated at the fuel quantity indicator.

    2. (2) For fuel systems having selector controls, the usable fuel capacity available at each selector control position must be indicated near the selector control.

    3. (3) For fuel systems having a calibrated fuel quantity indication system complying with 523.1337(b)(1) and accurately displaying the actual quantity of usable fuel in each selectable tank, no fuel capacity placards outside of the fuel quantity indicator are required.
      (effective 2016/08/04)

  5. (e) For accessory, auxiliary, and emergency controls:

    1. (1) If retractable landing gear is used, the indicator required by 523.729 must be marked so that the pilot can, at any time, ascertain that the wheels are secured in the extreme positions; and

    2. (2) Each emergency control must be red and must be marked as to method of operation.  No control other than an emergency control, or a control that serves an emergency function in addition to its other functions, shall be this colour.

(Change 523-5)

523.1557 Miscellaneous Markings and Placards

  1. (a) Baggage and cargo compartments, and ballast location.  Each baggage and cargo compartment, and each ballast location, must have a placard stating any limitations on contents, including weight, that are necessary under the loading requirements.

  2. (b) Seats.  If the maximum allowable weight to be carried in a seat is less than 170 pounds, a placard stating the lesser weight must be permanently attached to the seat structure.

  3. (c) Fuel, oil, and coolant filler openings.  The following apply:

    1. (1) Fuel filler openings must be marked at or near the filler cover with:

      1. (i) For reciprocating engine powered aeroplanes:

        1. (A) The word "Avgas"; and

        2. (B) The minimum fuel grade.

      2. (ii) For turbine engine-powered aeroplanes:

        1. (A) The words "Jet Fuel"; and

        2. (B) The permissible fuel designations, or references to the Aeroplane Flight Manual (AFM) for permissible fuel designations.

      3. (iii) For pressure fuelling systems, the maximum permissible fuelling supply pressure and the maximum permissible defuelling pressure.

    2. (2) Oil filler openings must be marked at or near the filler cover with the word "Oil" and the permissible oil designations, or references to the Aeroplane Flight Manual (AFM) for permissible oil designations.

    3. (3) Coolant filler openings must be marked at or near the filler cover with the word "Coolant".

    4. (4) If placards and markings at the fuel or oil opening include tank capacity, the capacity must be specified in litres.  Imperial or U.S. gallons may also be included.

    5. FAR - No corresponding text.

  4. (d) Emergency exit placards.  Each placard and operating control for each emergency exit must be red.  A placard must be near each emergency exit control and must clearly indicate the location of that exit and its method of operation.

  5. (e) The system voltage of each direct current installation must be clearly marked adjacent to its external power connection.

  6. (f) (Removed)

(Change 523-4 (96-09-01))

523.1559 Operating Limitations Placard

  1. (a) There must be a placard in clear view of the pilot stating:

    1. (1) That the aeroplane must be operated in accordance with the Aeroplane Flight Manual; and

    2. (2) The certification category of the aeroplane to which the placards apply.

  2. (b) For aeroplanes certificated in more than one category, there must be a placard in clear view of the pilot stating that other limitations are contained in the Aeroplane Flight Manual.

  3. (c) There must be a placard in clear view of the pilot that specifies the kind of operations to which the operation of the aeroplane is limited or from which it is prohibited under 523.1525.

  4. (d) The placard(s) required by this section need not be lighted.
    (effective 2016/08/04)

(Change 523-5)

523.1561 Safety Equipment

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

  2. (b) Stowage provisions for required safety equipment must be marked for the benefit of occupants.

523.1563 Airspeed Placards

There must be an airspeed placard in clear view of the pilot and as close as practicable to the airspeed indicator.  This placard must list:

  1. (a) The operating manoeuvring speed, VO; and

  2. (b) The maximum landing gear operating speed VLO.

  3. (c) For reciprocating multi-engine-powered aeroplanes of more than 6,000 pounds maximum weight, and turbine engine-powered aeroplanes, the maximum value of the minimum control speed, VMC (one-engine-inoperative) determined under 523.149(b).

  4. (d) The airspeed placard(s) required by this section need not be lighted if the landing gear operating speed is indicated on the airspeed indicator or other lighted area such as the landing gear control and the airspeed indicator has features such as low speed awareness that provide ample warning prior to VMC.
    (effective 2016/08/04)

(Change 523-4 (96-09-01))
(Change 523-5)

523.1567 Flight Manoeuvre Placard

  1. (a) For normal category aeroplanes, there must be a placard in front of and in clear view of the pilot stating:  "No aerobatic manoeuvres, including spins, approved".

  2. (b) For utility category aeroplanes, there must be:

    1. (1) A placard in clear view of the pilot stating:  "Aerobatic manoeuvres are limited to the following ......" (list approved manoeuvres and the recommended entry speed for each); and

    2. (2) For those aeroplanes that do not meet the spin requirements for aerobatic category aeroplanes, an additional placard in clear view of the pilot stating:  "Spins Prohibited".

  3. (c) For aerobatic category aeroplanes, there must be a placard in clear view of the pilot listing the approved aerobatic manoeuvres and the recommended entry airspeed for each.  If inverted flight manoeuvres are not approved, the placard must bear a notation to this effect.

  4. (d) For aerobatic category aeroplanes and utility category aeroplanes approved for spinning, there must be a placard in clear view of the pilot:

    1. (1) Listing the control actions for recovery from spinning manoeuvres; and

    2. (2) Stating that recovery must be initiated when spiral characteristics appear, or after not more than six turns or not more than any greater number of turns for which the aeroplane has been certificated.

  5. (e) The placard(s) required by this section need not be lighted.
    (effective 2016/08/04)

(Change 523-5)

Aeroplane Flight Manual and Approved Manual Material

523.1581 General

  1. (a) Furnishing information.  An Aeroplane Flight Manual must be furnished with each aeroplane, and it must contain the following:

    1. (1) Information required by 523.1583 through 523.1589.

    2. (2) Other information that is necessary for safe operation because of design, operating, or handling characteristics.

    3. (3) Further information necessary to comply with the relevant operating rules.

  2. (b) Approved information.

    1. (1) Except as provided in paragraph (b)(2) of this section, each part of the Aeroplane Flight Manual containing information prescribed in 523.1583 through 523.1589 must be approved, segregated, identified and clearly distinguished from each unapproved part of that Aeroplane Flight Manual.

    2. (2) The requirements of paragraph (b)(1) of this section do not apply to reciprocating engine-powered aeroplanes of 6,000 pounds or less maximum weight, if the following is met:

      1. (i) Each part of the Aeroplane Flight Manual containing information prescribed in 523.1583 must be limited to such information, and must be approved, identified, and clearly distinguished from each other part of the Aeroplane Flight Manual.

      2. (ii) The information prescribed in 523.1585 through 523.1589 must be determined in accordance with the applicable requirements of this Chapter and presented in its entirety in a manner acceptable to the Minister.

    3. (3) Each page of the Aeroplane Flight Manual containing information prescribed in this section must be of a type that is not easily erased, disfigured, or misplaced, and is capable of being inserted in a manual provided by the applicant, or in a folder, or in any other permanent binder.

  3. (c) The units used in the Aeroplane Flight Manual must be the same as those marked on the appropriate instruments and placards.

  4. (d) All Aeroplane Flight Manual operational airspeeds, unless otherwise specified, must be presented as indicated airspeeds.

  5. (e) Provision must be made for stowing the Aeroplane Flight Manual in a suitable fixed container which is readily accessible to the pilot.

  6. (f) Revisions and Amendments.  Each Aeroplane Flight Manual (AFM) must contain a means for recording the incorporation of revisions and amendments.

(Change 523-1 (88-01-01))
(Change 523-4 (96-09-01))
(Change 523-5)

523.1583 Operating Limitations

The Aeroplane Flight Manual must contain operating limitations determined under this Chapter 523, including the following -:

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

    1. (1) Information necessary for the marking of the airspeed limits on the indicator as required in 523.1545, and the significance of each of those limits and of the colour coding used on the indicator.

    2. (2) The speeds VMC, VO, VLE, and VLO, if established, and their significance.

    3. (3) In addition, for turbine powered commuter category aeroplanes:

      1. (i) The maximum operating limit speed, VMO/MMO and a statement that this speed must not be deliberately exceeded in any regime of flight (climb, cruise or descent) unless a higher speed is authorized for flight test or pilot training;

      2. (ii) If an airspeed limitation is based upon compressibility effects, a statement to this effect and information as to any symptoms, the probable behaviour of the aeroplane, and the recommended recovery procedures; and

      3. (iii) The airspeed limits must be shown in terms of VMO/MMO instead of VNO and VNE.

  2. (b) Powerplant limitations.  The following information must be furnished:

    1. (1) Limitations required by 523.1521.

    2. (2) Explanation of the limitations, when appropriate.

    3. (3) Information necessary for marking the instruments required by 523.1549 through 523.1553.

  3. (c) Weight.  The Aeroplane Flight Manual must include:

    1. (1) The maximum weight; and

    2. (2) The maximum landing weight, if the design landing weight selected by the applicant is less than the maximum weight.

    3. (3) For reciprocating engine-powered aeroplanes of more than 2720 kg (6,000 lbs) maximum weight, single-engine turbines and multi-engine jets 2720 kg (6,000 lbs) or less maximum weight in the normal, utility, and aerobatic category, performance operating limitations as follows:
      (effective 2016/08/04)

      1. (i) The maximum take -off weight for each airport altitude and ambient temperature within the range selected by the applicant at which the aeroplane complies with the climb requirements of 523.63(c)(1).

      2. (ii) The maximum landing weight for each airport altitude and ambient temperature within the range selected by the applicant at which the aeroplane complies with the climb requirements of 523.63(c)(2).

    4. (4) For normal, utility and aerobatic category multi-engine jets over 2720 kg (6,000 lbs) and commuter category aeroplanes, the maximum take-off weight for each airport altitude and ambient temperature within the range selected by the applicant at which:
      (effective 2016/08/04)

      1. (i) the aeroplane complies with the climb requirements of 523.63(d)(1); and

      2. (ii) the accelerate-stop distance determined under section 523.55 is equal to the available runway length plus the length of any stopway, if utilized; and either:

        1. (A) the take-off distance determined under 523.59(a) is equal to the available runway length; or

        2. (B) at the option of the applicant, the take-off distance determined under 523.59(a) is equal to the available runway length plus the length of any clearway and the take-off run determined under 523.59(b) is equal to the available runway length.

    5. (5) For normal, utility and aerobatic category multi-engine jets over 2720 kg (6,000 lbs) and commuter category aeroplanes, the maximum landing weight for each airport altitude within the range selected by the applicant at which:
      (effective 2016/08/04)

      1. (i) The aeroplane complies with the climb requirements of 523.63(d)(2) for ambient temperatures within the range selected by the applicant; and

      2. (ii) The landing distance determined under 523.75 for standard temperatures is equal to the available runway length.

    6. (6) The maximum zero wing fuel weight, where relevant, as established in accordance with 523.343.

  4. (d) Centre of gravity.  The established centre of gravity limits.

  5. (e) Manoeuvres.  The following authorized manoeuvres, appropriate airspeed limitations, and unauthorized manoeuvres, as prescribed in this section.

    1. (1) Normal category aeroplanes.  No aerobatic manoeuvres, including spins, are authorized.

    2. (2) Utility category aeroplanes.  A list of authorized manoeuvres demonstrated in the type flight tests, together with recommended entry speeds and any other associated limitations.  No other manoeuvre is authorized.

    3. (3) Aerobatic category aeroplanes.  A list of approved flight manoeuvres demonstrated in the type flight tests, together with recommended entry speeds and any other associated limitations.

    4. (4) Aerobatic category aeroplanes and utility category aeroplanes approved for spinning.  Spin recovery procedure established to show compliance with 523.221(c).

    5. (5) Commuter category aeroplanes.  Manoeuvres are limited to any manoeuvre incident to normal flying, stalls, (except whip stalls) and steep turns in which the angle of bank is not more than 60 degrees.

  6. (f) Manoeuvre load factor.  The positive limit load factors in g's, and, in addition, the negative limit load factor for aerobatic category aeroplanes.

  7. (g) Minimum flight crew.  The number and functions of the minimum flight crew determined under 523.1523.

  8. (h) Kinds of operation.  A list of the kinds of operation to which the aeroplane is limited or from which it is prohibited under 523.1525, and also a list of installed equipment that affects any operating limitation and identification as to the equipment's required operational status for the kinds of operation for which approval has been given.

  9. (i) Maximum operating altitude.  The maximum altitude established under 523.1527.

  10. (j) Maximum passenger seating configuration.  The maximum passenger seating configuration.

  11. (k) Allowable lateral fuel loading.  The maximum allowable lateral fuel loading differential, if less than the maximum possible.

  12. (l) Baggage and cargo loading.  The following information for each baggage and cargo compartment or zone:

    1. (1) The maximum allowable load; and

    2. (2) The maximum intensity of loading.

  13. (m) Systems.  Any limitations on the use of aeroplane systems and equipment.

  14. (n) Ambient temperatures.  Where appropriate, maximum and minimum ambient air temperatures for operation.

  15. (o) Smoking.  Any restrictions on smoking in the aeroplane.

  16. (p) Types of surface.  A statement of the types of surface on which operations may be conducted.  (See 523.45(g) and 523.1587(a)(4), (c)(2), and (d)(4)).

(Change 523-1 (88-01-01))
(Change 523-4 (96-09-01))
(Change 523-5)

523.1585 Operating Procedures

  1. (a) For all aeroplanes, information concerning normal, abnormal (if applicable), and emergency procedures and other pertinent information necessary for safe operation and the achievement of the scheduled performance must be furnished, including (:

    1. (1) An explanation of significant or unusual flight or ground handling characteristics;

    2. (2) The maximum demonstrated values of crosswind for take -off and landing, and procedures and information pertinent to operations in crosswinds;

    3. (3) A recommended speed for flight in rough air.  This speed must be chosen to protect against the occurrence, as a result of gusts, of structural damage to the aeroplane and loss of control (for example, stalling);

    4. (4) Procedures for restarting any turbine engine in flight, including the effects of altitude; and

    5. (5) Procedures, speeds, and configuration(s) for making a normal approach and landing, in accordance with 523.73 and 523.75, and a transition to the balked landing condition.

    6. (6) For seaplanes and amphibians, water handling procedures and the demonstrated wave height.

  2. (b) In addition to paragraph (a) of this section, for all single-engine aeroplanes, the procedures, speeds, and configuration(s) for a glide following engine failure, in accordance with 523.71 and the subsequent forced landing, must be furnished.

  3. (c) In addition to paragraph (a) of this section, for all multi-engine aeroplanes, the following information must be furnished:

    1. (1) Procedures, speeds, and configuration(s) for making an approach and landing with one engine inoperative;

    2. (2) Procedures, speeds, and configuration(s) for making a balked landing with one engine inoperative and the conditions under which a balked landing can be performed safely, or a warning against attempting a balked landing;

    3. (3) The VSSE determined in 523.149.

    4. (4) Procedures for restarting any engine in flight including the effects of altitude.

  4. (d) In addition to paragraphs (a) and either (b) or (c) of this section, as appropriate, for all normal, utility, and aerobatic category aeroplanes, the following information must be furnished:

    1. (1) Procedures, speeds, and configuration(s) for making a normal take -off, in accordance with 523.51(a) and (b), and 523.53(a) and (b), and the subsequent climb, in accordance with 523.65 and 523.69(a).

    2. (2) Procedures for abandoning a take -off due to engine failure or other cause.

  5. (e) In addition to paragraphs (a), (c), and (d) of this section, for all normal, utility, and aerobatic category multi-engine aeroplanes, the information must include the following:

    1. (1) Procedures and speeds for continuing a take -off following engine failure and the conditions under which take-off can safely be continued, or a warning against attempting to continue the take-off.

    2. (2) Procedures, speeds, and configurations for continuing a climb following engine failure, after take -off, in accordance with 523.67, or enroute, in accordance with 523.69(b).

  6. (f) In addition to paragraphs (a) and (c) of this section, for normal, utility and aerobatic category multi-engine jets weighing over 2720 kg (6,000 lbs), and commuter category aeroplanes, the information must include the following:
    (effective 2016/08/04)

    1. (1) Procedures, speeds, and configuration(s) for making a normal take -off.

    2. (2) Procedures and speeds for carrying out an accelerate-stop in accordance with 523.55.

    3. (3) Procedures and speeds for continuing a take -off following engine failure in accordance with 523.59(a)(1) and for following the flight path determined under 523.57 and 523.61(a).

  7. (g) For multi-engine aeroplanes, information identifying each operating condition in which the fuel system independence prescribed in 523.953 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.

  8. (h) For each aeroplane showing compliance with 523.1353(g)(2) or (g)(3), the operating procedures for disconnecting the battery from its charging source must be furnished.

  9. (i) Information on the total quantity of useable fuel for each fuel tank, and the effect on the useable fuel quantity, as a result of a failure of any pump, must be furnished.

  10. (j) Procedures for the safe operation of the aeroplane's systems and equipment, both in normal use and in the event of malfunction, must be furnished.

(Change 523-1 (88-01-01))
(Change 523-4 (96-09-01))
(Change 523-5)

523.1587 Performance Information

Unless otherwise prescribed, performance information must be provided over the altitude and temperature ranges required by 523.45(b).

  1. (a) For all aeroplanes, the following information must be furnished:

    1. (1) The stalling speeds VSO and VS1 with the landing gear and wing flaps retracted, determined at maximum weight under 523.49, and the effect on these stalling speeds of angles of bank up to 60 degrees;

    2. (2) The steady rate and gradient of climb with all engines operating, determined under 523.69(a);

    3. (3) The landing distance, determined under 523.75 for each airport altitude and standard temperature, and the type of surface for which it is valid;

    4. (4) The effect on landing distances of operation on other than smooth hard surfaces, when dry, determined under 523.45(g); and

    5. (5) The effect on landing distances of runway slope and 50 percent of the headwind component and 150 percent of the tailwind component.

  2. (b) In addition to paragraph (a) of this section, for all normal, utility, and aerobatic category reciprocating engine-powered aeroplanes of 6,000 pounds or less maximum weight, the steady angle of climb/descent, determined under 523.77(a), must be furnished.

  3. (c) In addition to paragraphs (a) and (b) of this section, if appropriate, for normal, utility, and aerobatic category aeroplanes, the following information must be furnished:

    1. (1) The take -off distance, determined under 523.53 and the type of surface for which it is valid.

    2. (2) The effect on take -off distance of operation on other than smooth hard surfaces, when dry, determined under 523.45(g);

    3. (3) The effect on take -off distance of runway slope and 50 percent of the headwind component and 150 percent of the tailwind component;

    4. (4) For multi-engine reciprocating engine-powered aeroplanes of more than 6,000 pounds maximum weight and multi-engine turbine powered aeroplanes, the one-engine-inoperative take-off climb/descent gradient, determined under 523.66;

    5. (5) For multi-engine aeroplanes, the enroute rate and gradient of climb/descent with one engine inoperative, determined under 523.69(b); and

    6. (6) For single-engine aeroplanes, the glide performance determined under 523.71.

  4. (d) In addition to paragraph (a) of this section, for normal, utility and aerobatic category multi-engine jets weighing over 2720 kg (6,000 lbs), and commuter category aeroplanes, the following information must be furnished:
    (effective 2016/08/04)

    1. (1) The accelerate-stop distance determined under 523.55;

    2. (2) The take -off distance determined under 523.59(a);

    3. (3) At the option of the applicant, the take -off run determined under 523.59(b);

    4. (4) The effect on accelerate-stop distance, take -off distance and, if determined, take -off run, of operation on other than smooth hard surfaces, when dry, determined under 523.45(g);

    5. (5) The effect on accelerate-stop distance, take -off distance, and if determined, take -off run, of runway slope and 50 percent of the headwind component and 150 percent of the tailwind component;

    6. (6) The net take -off flight path determined under 523.61(b);

    7. (7) The enroute gradient of climb/descent with one engine inoperative, determined under 523.69(b);

    8. (8) The effect, on the net take -off flight path and on the enroute gradient of climb/descent with one engine inoperative, of 50 percent of the headwind component and 150 percent of the tailwind component;

    9. (9) Overweight landing performance information (determined by extrapolation and computed for the range of weights between the maximum landing and maximum take -off weights) as follows:

      1. (i) The maximum weight for each airport altitude and ambient temperature at which the aeroplane complies with the climb requirements of 523.63(d)(2); and

      2. (ii) The landing distance determined under 523.75 for each airport altitude and standard temperature.

    10. (10) The relationship between IAS and CAS determined in accordance with 523.1323(b) and (c).

    11. (11) The altimeter system calibration required by 523.1325(e).

(Change 523-1 (88-01-01))
(Change 523-3 (92-01-02))
(Change 523-4 (96-09-01))
(Change 523-5)

523.1589 Loading Information

The following loading information must be furnished:

  1. (a) The weight and location of each item of equipment that can be easily removed, relocated, or replaced and that is installed when the aeroplane was weighed under the requirement of 523.25.

  2. (b) Appropriate loading instructions for each possible loading condition between the maximum and minimum weights established under 523.25, to facilitate the centre of gravity remaining within the limits established under 523.23.
    (Change 523-4 (96-09-01))

(Change 523-5)

Date modified: