ED Decision 2003/16/RM
(a) Furnishing information. A Rotorcraft Flight Manual must be furnished with each rotorcraft, and it must contain the following:
(1) Information required by CS 29.1583 to 29.1589.
(2) Other information that is necessary for safe operation because of design, operating, or handling characteristics.
(b) Approved information. Each part of the manual listed in CS 29.1583 to 29.1589 that is appropriate to the rotorcraft, must be furnished, verified, and approved, and must be segregated, identified, and clearly distinguished from each unapproved part of that manual.
(c) Reserved.
(d) Table of contents. Each Rotorcraft Flight Manual must include a table of contents if the complexity of the manual indicates a need for it.
CS 29.1583 Operating limitations
ED Decision 2003/16/RM
(a) Airspeed and rotor limitations. Information necessary for the marking of airspeed and rotor limitations on or near their respective indicators must be furnished. The significance of each limitation and of the colour coding must be explained.
(b) Powerplant limitations. The following information must be furnished:
(1) Limitations required by CS 29.1521.
(2) Explanation of the limitations, when appropriate.
(3) Information necessary for marking the instruments required by CS 29.1549 to 29.1553.
(c) Weight and loading distribution. The weight and centre of gravity limits required by CS 29.25 and CS 29.27, respectively, must be furnished. If the variety of possible loading conditions warrants, instructions must be included to allow ready observance of the limitations.
(d) Flight crew. When a flight crew of more than one is required, the number and functions of the minimum flight crew determined under CS 29.1523 must be furnished.
(e) Kinds of operation. Each kind of operation for which the rotorcraft and its equipment installations are approved must be listed.
(f) Limiting heights. Enough information must be furnished to allow compliance with CS 29.1517.
(g) Maximum allowable wind. For Category A rotorcraft, the maximum allowable wind for safe operation near the ground must be furnished.
(h) Altitude. The altitude established under CS 29.1527 and an explanation of the limiting factors must be furnished.
(i) Ambient temperature. Maximum and minimum ambient temperature limitations must be furnished.
AMC 29.1583 Operating limitations
ED Decision 2016/025/R
This AMC provides further guidance and acceptable means of compliance to supplement FAA AC 29-2C Change 4 (AC 29.1583 § 29.1583 (Amendment 29-24) OPERATING LIMITATIONS), to meet the Agency's interpretation of CS 29.1583. As such it should be used in conjunction with the FAA AC but take precedence over it, where stipulated, in the showing of compliance.
Specifically, this AMC addresses an area where the FAA AC has been deemed by the Agency as being at variance to the Agency’s interpretation. This being as follows:
b. Procedures.
(7) Kinds of operations are established under CS 29.1525. This section should contain the following preamble: ‘This rotorcraft is certified in the Large Category (category B or category A and category B) and is eligible for the following kinds of operations when the appropriate instruments and equipment required by the airworthiness and operating rules are installed and approved and are in an operable condition.’ The following, and any other kinds of operations that are applicable, should be listed.
(i) Day and night VFR.
(ii) Approved to operate in known icing conditions.
(iii) IFR.
(iv) Category A vertical operations from ground level or elevated heliports.
(v) Extended overwater operations (ditching).
(vi) External load operation.
Each operating limitation must be clear, unambiguous, and consistent with any other applicable limitation or regulatory requirement.
[Amdt 29/4]
CS 29.1585 Operating procedures
ED Decision 2018/007/R
(a) The parts of the manual containing operating procedures must 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.
(b) For multi-engine rotorcraft, information identifying each operating condition in which the fuel system independence prescribed in CS 29.953 is necessary for safety must be furnished, together with instructions for placing the fuel system in a configuration used to show compliance with that paragraph.
(c) For helicopters for which a VNE (power-off) is established under CS 29.1505(c), information must be furnished to explain the VNE (power-off) and the procedures for reducing airspeed to not more than the VNE (power-off) following failure of all engines.
(d) For each rotorcraft showing compliance with CS 29.1353(c)(6)(ii) or (c)(6)(iii), the operating procedures for disconnecting the battery from its charging source must be furnished.
(e) If the unusable fuel supply in any tank exceeds 5% of the tank capacity, or 3.8 litres (0.8 Imperial gallon/1 US gallon), whichever is greater, information must 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.
(f) Information on the total quantity of usable fuel for each fuel tank must be furnished.
(g) For Category B rotorcraft, the airspeeds and corresponding rotor speeds for minimum rate of descent and best glide angle as prescribed in CS 29.71 must be provided.
(h) The maximum duration of operation after a failure resulting in a loss of lubrication of a rotor drive system gearbox and an associated oil pressure warning must be furnished and must not exceed the maximum period substantiated in accordance with CS 29.927(c).
[Amdt No: 29/5]
AMC 29.1585 Operating Procedures
ED Decision 2018/007/R
CS 29.927(c) provides guidance for the completion of testing to simulate a loss of lubrication and on how to demonstrate confidence in the margin of safety associated with the maximum period of operation following loss of lubrication. This margin of safety is intended to substantiate a period of operation that has been evaluated as likely to be safer than making a forced landing over hostile terrain. Accordingly, the need to ‘Land as Soon as Possible’, which may include ditching where circumstances permit, should be reflected in the associated RFM emergency procedures. This can be supplemented with ’Land Immediately’ in the event of additional conditions to that of low oil pressure being present.
Emergency procedures should identify the need to minimise the power that is used for yaw and accessories following a loss of oil pressure warning.
[Amdt No: 29/5]
CS 29.1587 Performance information
ED Decision 2018/007/R
Flight manual performance information which exceeds any operating limitation may be shown 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 shown, the limits must be clearly indicated. The following must be provided:
(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, together with descriptions of the conditions, such as airspeeds, under which this data was determined, and must contain –
(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) The airspeed calibrations;
(3) The techniques, associated airspeeds, and rates of descent for autorotative landings;
(4) The rejected take-off distance determined under CS 29.62 and the take-off distance determined under CS 29.61;
(5) The landing data determined under CS 29.81 and 29.85;
(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 CS 29.67(a)(1) and (a)(2):
(i) In the flight conditions required in CS 29.67(a)(1) between the end of the take-off distance and the point at which the rotorcraft is 61 m (200 ft) above the take-off surface (or 61 m (200 ft) above the lowest point of the take-off profile for elevated heliports).
(ii) In the flight conditions required in CS 29.67(a)(2) between the points at which the rotorcraft is 61 m (200 ft) and 305 m (1000 ft) above the take-off surface (or 61 m (200 ft) and 305 m (1000 ft) above the lowest point of the take-off profile for elevated heliports).
(7) Hover performance determined under CS 29.49 and the maximum weight for each altitude and temperature condition at which the rotorcraft can safely hover in-ground effect and out-of-ground effect in winds of not less than 31 km/h (17 knots) from all azimuths. This data must be clearly referenced to the appropriate hover charts.
(b) Category B. For each Category B rotorcraft, the Rotorcraft Flight Manual must contain:
(1) The take-off distance and the climbout 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) The steady rates of climb and hovering ceiling, together with the corresponding airspeeds and other pertinent information, including the calculated effects of altitude and temperature;
(3) The landing distance, appropriate airspeed and type of landing surface, together with any pertinent information that might affect this distance, including the effects of weight, altitude and temperature;
(4) The maximum safe wind for operation near the ground;
(5) The airspeed calibrations;
(6) The height-speed envelope except for rotorcraft incorporating this as an operating limitation;
(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 CS 29.71;
(8) Hover performance determined under CS 29.49 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 in-ground effect and out-of-ground effect in winds of not less than 31 km/h (17 knots) from all azimuths. This data must be clearly referenced to the appropriate hover charts; and
(9) Any additional performance data necessary for the application of any applicable operating rule.
(c) The RFM must contain the substantiated sea conditions and any associated information relating to the certification obtained with ditching or emergency flotation provisions.
[Amdt No: 29/1]
[Amdt No: 29/2]
[Amdt No: 29/5]
AMC 29.1587(c) Performance Information
ED Decision 2018/007/R
This AMC supplements FAA AC 29.1587, AC 29.1587A and AC 29.1587B.
a. Explanation
The rotorcraft flight manual (RFM) is an important element in the certification process of the rotorcraft for approval with ditching or emergency flotation provisions. The material may be presented in the form of a supplement or a revision to the basic manual. This material should include:
(1) A statement in the ‘Limitations’ section stating that the rotorcraft is approved for ditching or emergency flotation, as appropriate.
If certification with ditching provisions is obtained in a segmented fashion (i.e. one applicant performing the safety equipment installation and operations portion and another designing and substantiating the safety equipment’s performance and deployment facilities), the RFM limitations should state that the ditching provisions are not approved until all the segments are completed. The outstanding ditching provisions for a complete certification should be identified in the ‘Limitations’ section.
(2) Procedures and limitations for the inflation of a flotation device.
(3) A statement in the performance information section of the RFM, identifying the substantiated sea conditions and any other pertinent information. If substantiation was performed using the default North Sea wave climate (JONSWAP), the maximum substantiated significant wave height (Hs) should be stated. If extended testing was performed in accordance with the AMC to 29.801(e) and 29.802(c) to demonstrate that the target level of capsize probability can be reached without any operational limitations, this should also be stated. If substantiation was performed for other sea conditions, the maximum substantiated significant wave height (Hs) and the limits of the geographical area represented should be stated.
(4) Recommended rotorcraft water entry attitude and speed.
(5) Procedures for the use of safety equipment.
(6) Egress and life raft entry procedures.
[Amdt No: 29/5]
CS 29.1589 Loading information
ED Decision 2003/16/RM
There must be loading instructions for each possible loading condition between the maximum and minimum weights determined under CS 29.25 that can result in a centre of gravity beyond any extreme prescribed in CS 29.27, assuming any probable occupant weights.
CS 29.1593 Exposure to volcanic cloud hazards
ED Decision 2016/025/R
If required by an operating rule, the susceptibility of rotorcraft features to the effects of volcanic cloud hazards must be established.
[Amdt 29/4]
AMC 29.1593 Exposure to volcanic cloud hazards
ED Decision 2016/025/R
The aim of CS 29.1593 is to support commercial and non-commercial operators operating complex motor-powered rotorcraft by identifying and assessing airworthiness hazards associated with operations in contaminated airspace. Providing such data to operators will enable those hazards to be properly managed as part of an established management system.
Acceptable means of establishing the susceptibility of rotorcraft features to the effects of volcanic clouds should include a combination of experience, studies, analysis, and/or testing of parts or sub-assemblies.
Information necessary for safe operation should be contained in the unapproved part of the flight manual or other appropriate manual, and should be readily usable by operators in preparing a safety risk assessment as part of their overall management system.
A volcanic cloud comprises volcanic ash together with gases and other chemicals. Although the primary hazard is volcanic ash itself, other elements of the volcanic cloud may also be undesirable to operate through, thus their effect on airworthiness should be assessed.
In determining the susceptibility of rotorcraft features to the effects of volcanic clouds as well as the necessary information to be provided to operators, the following points should be considered:
(a) Identify the features of the rotorcraft that are susceptible to airworthiness effects of volcanic clouds. These may include but are not limited to the following:
(1) malfunction or failure of one or more engines, leading not only to reduction or complete loss of thrust but also to failures of electrical, pneumatic and hydraulic systems;
(2) blockage of pitot and static sensors, resulting in unreliable airspeed indications and erroneous warnings;
(3) windscreen abrasion, resulting in windscreens rendered partially or completely opaque;
(4) fuel contamination;
(5) volcanic ash and/or toxic chemical contamination of cabin air-conditioning packs, possibly leading to loss of cabin pressurisation or noxious fumes in the cockpit and/or cabin;
(6) erosion, blockage or malfunction of external and internal rotorcraft components;
(7) volcanic cloud static discharge, leading to prolonged loss of communications; and
(8) reduced cooling efficiency of electronic components, leading to a wide range of rotorcraft system failures.
(b) The nature and severity of effects.
(c) Details of any device or system installed on the rotorcraft that can detect the presence of volcanic cloud hazards (e.g. volcanic ash (particulate) sensors or volcanic gas sensors)
(d) The effect of volcanic ash on operations arriving to or departing from contaminated aerodromes.
(e) The related pre-flight, in-flight and post-flight precautions to be taken by the operator including any necessary amendments to Aircraft Operating Manuals, Aircraft Maintenance Manuals, Master Minimum Equipment List/Dispatch Deviation or equivalents, required to support the operator. Pre-flight precautions should include clearly defined procedures for the removal of any volcanic ash detected on parked rotorcraft.
(f) The recommended continuing-airworthiness inspections associated with operations in airspace contaminated by volcanic cloud(s) and arriving to or departing from aerodromes contaminated by volcanic ash; this may take the form of Instructions for Continued Airworthiness (ICA) or other advice.
[Amdt 29/4]