Part V - Airworthiness Manual Chapter 529 - Transport Category Rotorcraft

Canadian Aviation Regulations (CARs) 2017-2

Content last revised: 2009/06/30

Preamble

SUBCHAPTERS 

  • A (529.1-529.20), 
  • B (529.21-529.300), 
  • C (529.301-529.600), 
  • D (529.601-529.900), 
  • E (529.901-529.1300), 
  • F (529.1301-529.1500), 
  • G (529.1501-529.1589)

APPENDICES 

ABCDE

SUBCHAPTER G OPERATING LIMITATIONS AND INFORMATION

529.1501 General

  1. (a) Each operating limitation specified in sections 529.1503 through 529.1525 and other limitations and information necessary for safe operation shall be established.
  2. (b) The operating limitations and other information necessary for safe operation shall be made available to the crew members as prescribed in sections 529.1541 through 529.1589.

529.1502 Reserved

Operating Limitations

529.1503 Airspeed Limitations: General

  1. (a) An operating speed range shall be established.
  2. (b) When airspeed limitations are a function of weight, weight distribution, altitude, rotor speed, power or other factors, airspeed limitations corresponding with the critical combinations of these factors shall be established.

529.1504 Reserved

529.1505 Never-exceed Speed

  1. (a) The never-exceed speed, VNE, shall be established so that it is:
    1. (1) not less than 40 knots (CAS); and
    2. (2) not more than the lesser of:
      1. (i) 0.9 times the maximum forward speeds established under section 529.309,
      2. (ii) 0.9 times the maximum speed demonstrated under sections 529.251 and 529.629, or
      3. (iii) 0.9 times the maximum speed substantiated for advancing blade tip mach number effects under critical altitude conditions.
  2. (b) VNE may vary with altitude, r.p.m., temperature and weight, if:
    1. (1) no more than two of these variables (or no more than two instruments integrating more than one of these variables) are used at one time; and
    2. (2) the ranges of these variables (or of the indications on instruments integrating more than one of these variables) are large enough to allow an operationally practical and safe variation of VNE.
  3. (c) For helicopters, a stabilized power-off VNE denoted as VNE (power-off) may be established at a speed less than VNE established pursuant to (a) of this section, if the following conditions are met:
    1. (1) VNE (power-off) is not less than a speed midway between the power-on VNE and the speed used in meeting the requirements of:
      1. (i) section 529.67 (a)(3) for Category A helicopters,
      2. (ii) section 529.65 (a) for Category B helicopters, except multi-engine helicopters meeting the requirements of section 529.67 (b), and
      3. (iii) section 529.67 (b) for multi-engine Category B helicopters meeting the requirements of section 529.67 (b);
    2. (2) VNE (power-off) is:
      1. (i) a constant airspeed,
      2. (ii) a constant amount less than power-on VNE, or
      3. (iii) a constant airspeed for a portion of the altitude range for which certification is requested, and a constant amount less than power-on VNE for the remainder of the altitude range.

529.1506 to 529.1508 Reserved

529.1509 Rotor Speed

  1. (a) Maximum power-off (autorotation). The maximum power-off rotor speed shall be established so that it does not exceed 95 percent of the lesser of:
    1. (1) the maximum design r.p.m. determined under section 529.309 (b); and
    2. (2) the maximum r.p.m. demonstrated during the type tests.
  2. (b) Minimum power-off. The minimum power-off rotor speed shall be established so that it is not less than 105 percent of the greater of:
    1. (1) the minimum demonstrated during the type tests; and
    2. (2) the minimum determined by design substantiation.
  3. (c) Minimum power-on. The minimum power-on rotor speed shall be established so that it is:
    1. (1) not less than the greater of:
      1. (i) the minimum demonstrated during the type tests, and
      2. (ii) the minimum determined by design substantiation; and
    2. (2) not more than a value determined under section 529.33 (a)(1) and (c)(1).

529.1510 to 529.1516 Reserved

529.1517 Limiting Height-Speed Envelope

For Category A rotorcraft, if a range of heights exists at any speed, including zero, within which it is not possible to make a safe landing following power failure, the range of heights and its variation with forward speed shall be established, together with any other pertinent information, such as the kind of landing surface.

529.1518 Reserved

529.1519 Weight and Centre of Gravity

The weight and centre of gravity limitations, determined under sections 529.25 and 529.27 respectively, shall be established as operating limitations.

529.1520 Reserved

529.1521 Powerplant Limitations

  1. (a) General. The powerplant limitations prescribed in this section shall be established so that they do not exceed the corresponding limits for which the engines are type certificated.
  2. (b) Take-off operation. The powerplant take-off operation shall be limited by:
    1. (1) the maximum rotational speed which shall not be greater than:
      1. (i) the maximum value determined by the rotor design, or
      2. (ii) the maximum value demonstrated during the type tests;
    2. (2) the maximum allowable manifold pressure (for reciprocating engines);
    3. (3) the maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines);
    4. (4) the maximum allowable power or torque for each engine, considering the power input limitations of the transmission with all engines operating;
    5. (5) the maximum allowable power or torque for each engine considering the power input limitations of the transmission with one engine inoperative;
    6. (6) the time limit for the use of the power corresponding to the limitations established in (b)(1) through (5) of this section; and
    7. (7) if the time limit established in (b)(6) of this section exceeds 2 minutes:
      1. (i) the maximum allowable cylinder head or coolant outlet temperature (for reciprocating engines), and
      2. (ii) the maximum allowable engine and transmission oil temperatures.
  3. (c) Continuous operation. The continuous operation shall be limited by:
    1. (1) the maximum rotational speed, which shall not be greater than:
      1. (i) the maximum value determined by the rotor design, or
      2. (ii) the maximum value demonstrated during the type tests;
    2. (2) the minimum rotational speed demonstrated under the rotor speed requirements in section 529.1509 (c);
    3. (3) the maximum allowable manifold pressure (for reciprocating engines);
    4. (4) the maximum allowable turbine inlet or turbine outlet gas temperature (for turbine engines);
    5. (5) the maximum allowable power or torque for each engine, considering the power input limitations of the transmission with all engines operating;
    6. (6) the maximum allowable power or torque for each engine, considering the power input limitations of the transmission with one engine inoperative; and
    7. (7) the maximum allowable temperatures for:
      1. (i) the cylinder head or coolant outlet (for reciprocating engines),
      2. (ii) the engine oil, and
      3. (iii) the transmission oil.
  4. (d) Fuel grade or designation. The minimum fuel grade (for reciprocating engines) or fuel designation (for turbine engines) shall be established so that it is not less than that required for the operation of the engines within the limitations prescribed in (b) and (c) of this section.
  5. (e) Ambient temperature. Ambient temperature limitations (including limitations for winterization installations if applicable) shall be established as the maximum ambient atmospheric temperature at which compliance with the cooling provisions of sections 529.1041 through 529.1049 is demonstrated.
  6. (f) 2 minute 30 second-OEI power operation. Unless otherwise authorized, the use of 2 minute 30 second-OEI power shall be limited to engine failure operation of multi-engine, turbine-powered rotorcraft for not longer than 2 minutes 30 seconds for any period in which that power is used. The use of 2 minute 30 second-OEI power shall also be limited by:
    1. (1) the maximum rotational speed, which shall not be greater than:
      1. (i) the maximum value determined by the rotor design, or
      2. (ii) the maximum value demonstrated during the type tests;
    2. (2) the maximum allowable gas temperature;
    3. (3) the maximum allowable torque; and
    4. (4) the maximum allowable oil temperature.
  7. (g) 30 minute-OEI power operation. Unless otherwise authorized, the use of 30 minute-OEI power shall be limited to multi-engine, turbine-powered rotorcraft for not longer than 30 minutes after failure of an engine. The use of 30 minute-OEI power shall also be limited by:
    1. (1) the maximum rotational speed which shall not be greater than:
      1. (i) the maximum value determined by the rotor design, or
      2. (ii) the maximum value demonstrated during the type tests;
    2. (2) the maximum allowable gas temperature;
    3. (3) the maximum allowable torque; and
    4. (4) the maximum allowable oil temperature.
  8. (h) Continuous OEI power operation. Unless otherwise authorized, the use of continuous OEI power shall be limited to multi-engine, turbine-powered rotorcraft for continued flight after failure of an engine. The use of continuous OEI power shall also be limited by:
    1. (1) the maximum rotational speed, which shall not be greater than:
      1. (i) the maximum value determined by the rotor design, or
      2. (ii) the maximum value demonstrated during the type tests;
    2. (2) the maximum allowable gas temperature;
    3. (3) the maximum allowable torque; and
    4. (4) the maximum allowable oil temperature.
  9. (i) Rated 30 second-OEI power operation. Rated 30 second-OEI power is permitted only on multi-engine, turbine-powered rotorcraft, also certificated for the use of rated 2 minute-OEI power, and can only be used for continued operation of the remaining engine(s) after a failure or precautionary shutdown of an engine. It shall be demonstrated that following application of 30 second-OEI power, any damage will be readily detectable by the applicable inspections and other related procedures furnished in accordance with section A529.4 of Appendix A of this chapter and section A533.4 of Appendix A of Chapter 533. The use of 30 second-OEI power shall be limited to not more than 30 seconds for any period in which that power is used, and by:
    1. (1) the maximum rotational speed which shall not be greater than:
      1. (i) the maximum value determined by the rotor design, or
      2. (ii) the maximum value demonstrated during the type tests;
    2. (2) the maximum allowable gas temperature; and
    3. (3) the maximum allowable torque.
  10. (j) Rated 2 minute-OEI power operation. Rated 2 minute-OEI power is permitted only on multi-engine, turbine-powered rotorcraft, also certificated for the use of rated 30 second-OEI power, and can only be used for continued operation of the remaining engine(s) after a failure or precautionary shutdown of an engine. It shall be demonstrated that following application of 2 minute-OEI power, any damage will be readily detectable by the applicable inspections and other related procedures furnished in accordance with section A529.4 of Appendix A of this chapter and section A533.4 of Appendix A of Chapter 533. The use of 2 minute-OEI power shall be limited to not more than 2 minutes for any period in which that power is used, and by:
    1. (1) the maximum rotational speed, which shall not be greater than:
      1. (i) the maximum value determined by the rotor design, or
      2. (ii) the maximum value demonstrated during the type tests;
    2. (2) the maximum allowable gas temperature; and
    3. (3) the maximum allowable torque.

529.1522 Auxiliary Power Unit Limitations

If an auxiliary power unit that meets the requirements of TSO-C77 is installed in the rotorcraft, the limitations established for that auxiliary power unit under the TSO including the categories of operation shall be specified as operating limitations for the rotorcraft.

529.1523 Minimum Flight Crew

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

  1. (a) the workload on individual crew members;
  2. (b) the accessibility and ease of operation of necessary controls by the appropriate crew member; and
  3. (c) the kinds of operation authorized under section 529.1525.

529.1524 Reserved

529.1525 Kinds of Operation

The kinds of operations (such as VFR, IFR, day, night, or icing) for which the rotorcraft is approved are established by demonstrated compliance with the applicable certification requirements and by the installed equipment.

529.1526 Reserved

529.1527 Maximum Operating Altitude

The maximum altitude up to which operation is allowed, as limited by flight, structural, powerplant, functional, or equipment characteristics, shall be established.

529.1528 Reserved

529.1529 Instructions for Continued Airworthiness

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

529.1530 to 529.1540 Reserved

Markings and Placards

529.1541 General

  1. (a) The rotorcraft shall contain:
    1. (1) the markings and placards specified in sections 529.1545 through 529.1565; and
    2. (2) any additional information, instrument markings, and placards required for the safe operation of the rotorcraft if it has unusual design, operating or handling characteristics.
  2. (b) Each marking and placard prescribed in (a) of this section:
    1. (1) shall be displayed in a conspicuous place; and
    2. (2) shall not be easily erased, disfigured, or obscured.

529.1542 Reserved

529.1543 Instrument Markings: General

For each instrument:

  1. (a) when markings are on the cover glass of the instrument there shall be means to maintain the correct alignment of the glass cover with the face of the dial; and
  2. (b) each arc and line shall be wide enough and located to be clearly visible to the pilot.

529.1544 Reserved

529.1545 Airspeed Indicator

  1. (a) Each airspeed indicator shall be marked as specified in (b) of this section, with the marks located at the corresponding indicated airspeeds.
  2. (b) The following markings shall be made:
    1. (1) a red radial line:
      1. (i) for rotorcraft other than helicopters, at VNE, and
      2. (ii) for helicopters, at VNE (power-on);
    2. (2) a red, cross-hatched radial line at VNE (power-off) for helicopters, if VNE (power-off) is less than VNE (power-on);
    3. (3) for the caution range, a yellow arc;
    4. (4) for the safe operating range, a green arc.

529.1546 Reserved

529.1547 Magnetic Direction Indicator

  1. (a) A placard meeting the requirements of this section shall be installed on or near the magnetic direction indicator.
  2. (b) The placard shall demonstrate the calibration of the instrument in level flight with the engines operating.
  3. (c) The placard shall state whether the calibration was made with radio receiver on or off.
  4. (d) Each calibration reading shall be in terms of magnetic heading in not more than 45° increments.

529.1548 Reserved

529.1549 Powerplant Instruments

For each required powerplant instrument, as appropriate to the type of instruments:

  1. (a) each maximum and, if applicable, minimum safe operating limit shall be marked with a red radial or a red line;
  2. (b) each normal operating range shall be marked with a green arc or green line, not extending beyond the maximum and minimum safe limits;
  3. (c) each takeoff and precautionary range shall be marked with a yellow arc or yellow line;
  4. (d) each engine or propeller range that is restricted because of excessive vibration stresses shall be marked with red arcs or red lines; and
  5. (e) each OEI limit or approved operating range shall be marked to be clearly differentiated from the markings of (a) through (d) of this section except that no marking is normally required for the 30-second OEI limit.
    (amended 1995/03/25)

529.1550 Reserved

529.1551 Oil Quantity Indicator

Each oil quantity indicator shall be marked with enough increments to indicate readily and accurately the quantity of oil.

529.1552 Reserved

529.1553 Fuel Quantity Indicator

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

529.1554 Reserved

529.1555 Control markings

  1. (a) Each cockpit control, other than primary flight controls or control whose function is obvious, shall be plainly marked as to its function and method of operation.
  2. (b) For powerplant fuel controls:
    1. (1) each fuel tank selector valve control shall 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 shall be marked on, or adjacent to, the selector for those tanks; and
    3. (3) each valve control for any engine of a multi-engine rotorcraft shall be marked to indicate the position corresponding to each engine controlled.
  3. (c) Useable fuel capacity shall be marked as follows:
    1. (1) for fuel systems having no selector controls, the useable fuel capacity of the system shall be indicated at the fuel quantity indicator;
    2. (2) for fuel systems having selector controls, the useable fuel capacity available at each selector control position shall be indicated near the selector control.
  4. (d) For accessory, auxiliary, and emergency controls:
    1. (1) each essential visual position indicator, such as those demonstrating rotor pitch or landing gear position, shall be marked so that each crew member can determine at any time the position of the unit to which it relates; and
    2. (2) each emergency control shall be red and shall be marked as to method of operation.
  5. (e) For rotorcraft incorporating retractable landing gear, the maximum landing gear operating speed shall be displayed in clear view of the pilot.

529.1556 Reserved

529.1557 Miscellaneous Markings and Placards

  1. (a) Baggage and cargo compartments, and ballast location. Each baggage and cargo compartment, and each ballast location shall 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 shall be permanently attached to the seat structure.
  3. (c) Fuel and oil filler openings. The following apply:
    1. (1) fuel filler openings shall be marked at or near the filler cover with:
      1. (i) the word "fuel",
      2. (ii) for reciprocating engine powered rotorcraft, the minimum fuel grade,
      3. (iii) for turbine-engine-powered rotorcraft, the permissible fuel designations. If impractical, this information may be included in the Rotorcraft Flight Manual, and the fuel filler may be marked with an appropriate reference to the flight manual, and
      4. (iv) for pressure fuelling systems, the maximum permissible fuelling supply pressure and the maximum permissible defuelling pressure;
    2. (2) oil filler openings shall be marked at or near the filler cover with the word "oil";
    3. (3) if placards and markings at the fuel or oil opening include tank capacity, the capacity shall be specified in litres. Imperial or U.S. gallons may be included.

      Information Note:

      No equivalent text is in the FAR.

  4. (d) Emergency exit placards. Each placard and operating control for each emergency exit shall differ in colour from the surrounding fuselage surface as prescribed in section 529.811 (h)(2). A placard shall be near each emergency exit control and shall clearly indicate the location of that exit and its method of operation.

529.1558 Reserved

529.1559 Limitations Placard

There shall be a placard in a clear view of the pilot that specifies the kinds of operations (VFR, IFR, day, night, or icing) for which the rotorcraft is approved.

529.1560 Reserved

529.1561 Safety Equipment

  1. (a) Each safety equipment control to be operated by the crew in emergency, such as controls for automatic life raft releases, shall be plainly marked as to its method of operation.
  2. (b) Each location, such as a locker or compartment, that carries any fire extinguishing, signalling or other life saving equipment, shall be so marked.
  3. (c) Stowage provisions for required emergency equipment shall be conspicuously marked to identify the contents and facilitate removal of the equipment.
  4. (d) Each life raft shall have obviously marked operating instructions.
  5. (e) Approved survival equipment shall be marked for identification and method of operation.

529.1562 to 529.1564 Reserved

529.1565 Tail Rotor

Each tail rotor shall be marked so that its disc is conspicuous under normal daylight ground conditions.

529.1566 to 529.1580 Reserved

Rotorcraft Flight Manual

529.1581 General

  1. (a) Furnishing information. A Rotorcraft Flight Manual shall be furnished with each rotorcraft, and it shall contain the following:
    1. (1) information required by sections 529.1583 through 529.1589; and
    2. (2) other information that is necessary for safe operation because of design, operating, or handling characteristics
  2. (b) Approved information. Each part of the manual listed in sections 529.1583 through 529.1589 that is appropriate to the rotorcraft, shall be furnished, verified and approved, and shall be segregated, identified and clearly distinguished from each unapproved part of that manual.
  3. (c) (Reserved.)
  4. (d) Table of contents. Each Rotorcraft Flight Manual shall include a table of contents if the complexity of the manual indicates a need for it.
  5. (e) Removed.
    (amended 2003/12/01)
  6. (f) Removed.
    (amended 2003/12/01)

529.1582 Reserved

529.1583 Operating Limitations

  1. (a) Airspeed and rotor limitations. Information necessary for the marking of airspeed and rotor limitations on or near their respective indicators shall be furnished. The significance of each limitation and of the colour coding shall be explained.
  2. (b) Powerplant limitations. The following information shall be furnished:
    1. (1) limitations required by section 529.1521;
    2. (2) explanation of the limitations, when appropriate;
    3. (3) information necessary for marking the instruments required by sections 529.1549 through 529.1553.
  3. (c) Weight and loading distribution. The weight and centre of gravity limits required by sections 529.25 and 529.27, respectively, shall be furnished. If the variety of possible loading conditions warrants, instructions shall be included to allow ready observance of the limitations.
  4. (d) Flight crews. When a flight crew of more than one is required, the number and functions of the minimum flight crew determined under section 529.1523 shall be furnished.
  5. (e) Kinds of operation. Each kind of operation for which the rotorcraft and its equipment installations are approved shall be listed.
  6. (f) Limiting heights. Enough information shall be furnished to allow compliance with section 529.1517.
  7. (g) Maximum allowable wind. For Category A rotorcraft, the maximum allowable wind for safe operation near the ground shall be furnished.
  8. (h) Altitude. The altitude established under section 529.1527 and an explanation of the limiting factors shall be furnished.
  9. (i) Ambient temperature. Maximum and minimum ambient temperature limitations shall be furnished.

529.1584 Reserved

529.1585 Operating Procedures

  1. (a) The parts of the manual containing operating procedures shall have information concerning any normal and emergency procedures, and other information necessary for safe operation, including the applicable procedures, such as those involving minimum speeds, to be followed if an engine fails.
  2. (b) For multi-engine rotorcraft, information identifying each operating condition in which the fuel system independence prescribed in section 529.953 is necessary for safety shall be furnished, together with instructions for placing the fuel system in a configuration used to demonstrate compliance with that section.
  3. (c) For helicopters for which a VNE (power-off) is established under section 529.1505(c), information shall be furnished to explain the VNENE (power-off) and the procedures for reducing airspeed to not more than the VNE (power-off) following failure of all engines.
  4. (d) For each rotorcraft demonstrating compliance with section 529.1353 (c)(6)(ii) or (c)(6)(iii), the operating procedures for disconnecting the battery from its charging source shall be furnished.
  5. (e) If the unuseable fuel supply in any tank exceeds 5 percent of the tank capacity, or 1 gallon, whichever is greater, information shall be furnished which indicates that when the fuel quantity indicator reads "zero" in level flight, any fuel remaining in the fuel tank cannot be used safely in flight.
  6. (f) Information on the total quantity of useable fuel for each fuel tank shall be furnished.
  7. (g) For Category B rotorcraft, the airspeeds and corresponding rotor speeds for minimum rate of descent and best glide angle as prescribed in section 529.71 shall be provided.

529.1586 Reserved

529.1587 Performance Information

Flight manual performance information which exceeds any operating limitation shall be demonstrated only to the extent necessary for presentation clarity or to determine the effects of approved optional equipment or procedures. When data beyond operating limits are demonstrated, the limits shall be clearly indicated. The following shall be provided:

  1. (a) Category A. For each category A rotorcraft, the Rotorcraft Flight Manual must contain a summary of the performance data, including data necessary for the application of any applicable operating rule of the CARs together with descriptions of the conditions, such as airspeeds, under which this data was determined, and must contain:
    (amended 2009/05/11)
    1. (1) the indicated airspeeds corresponding with those determined for take-off, and the procedures to be followed if the critical engine fails during take-off;
    2. (2) the airspeed calibrations;
    3. (3) the techniques, associated airspeeds, and rates of descent for autorotative landings;
    4. (4) the rejected take-off distance determined under section 529.62 and the take-off distance determined under section 529.61 or;
    5. (5) the landing data determined under sections 529.81 or 529.85; and
    6. (6) the steady gradient of climb for each weight, altitude and temperature for which take-off data are to be scheduled, along the take-off path determined in the flight conditions required in section 529.67 (a)(1) and (a)(2):
      1. (i) in the flight conditions required in section 529.67 (a)(1) between the end of the take-off distance and the point at which the rotorcraft is 200 feet above the take-off surface (or 200 feet above the lowest point of the take-off profile for elevated heliports), or
      2. (ii) in the flight conditions required in section 529.67 (a)(2) between the points at which the rotorcraft is 200 and 1000 feet above the take-off surface (or 200 and 1,000 feet above the lowest point of the take-off profile for elevated heliports); and
    7. (7) out-of-ground effect hover performance determined under section 529.49 and the maximum weight for each altitude and temperature condition at which the rotorcraft can safety hover out-of-ground effect in winds of not less than 17 knots from all azimuths. These data must be clearly referenced to the appropriate hover charts;
      (amended 2009/05/11)
  2. (b) Category B. For each category B rotorcraft, the Rotorcraft Flight Manual must contain:
    (amended 2009/05/11)
    1. (1) the take-off distance and the climb out speed together with the pertinent information defining the flight path with respect to autorotative landing if an engine fails, including the calculated effects of altitude and temperature;
    2. (2) the steady rates of climb and in-ground-effect hovering ceiling, together with the corresponding airspeeds and other pertinent information, including the calculated effects of altitude and temperature;
      (amended 2009/05/11>)
    3. (3) the landing distance, appropriate airspeed, and type of landing surface, together with all pertinent information that might affect this distance, including the effects of weight, altitude and temperature;
    4. (4) the maximum safe wind for operation near the ground;
    5. (5) the airspeed calibrations;
    6. (6) the height-speed envelope except for rotorcraft incorporating this as an operating limitation;
    7. (7) glide distance as a function of altitude when autorotating at the speeds and conditions for minimum rate of descent and best glide angle, as determined in section 529.71;
    8. (8) out-of-ground effect hover performance determined under section 529.49 and the maximum safe wind demonstrated under the ambient conditions for data presented. In addition, the maximum weight for each altitude and temperature condition at which the rotorcraft can safely hover out-of-ground-effect in winds of not less than 17 knots from all azimuths. These data must be clearly referenced to the appropriate hover charts; and
      (amended 2009/05/11)
    9. (9) any additional performance data necessary for the application of any operating rule of the CARs.

529.1588 Reserved

529.1589 Loading Information

There shall be loading instructions for each possible loading condition between the maximum and minimum weights determined under section 529.25 that can result in a centre of gravity beyond any extreme prescribed in section 529.27, assuming any probable occupant weights.

Date modified: