ED Decision 2003/15/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 27.1583 to 27.1589.
(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 27.1583 to 27.1589, 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 27.1583 Operating limitations
ED Decision 2003/15/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 27.1521.
(2) Explanation of the limitations, when appropriate.
(3) Information necessary for marking the instruments required by CS 27.1549 to 27.1553.
(c) Weight and loading distribution. The weight and centre of gravity limits required by CS 27.25 and 27.27, 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 27.1523 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) (Reserved)
(g) Altitude. The altitude established under CS 27.1527 and an explanation of the limiting factors must be furnished.
CS 27.1585 Operating procedures
ED Decision 2003/15/RM
(a) Parts of the manual containing operating procedures must have information concerning any normal and emergency procedures and other information necessary for safe operation, including take-off and landing procedures and associated airspeeds. The manual must contain any pertinent information including:
(1) The kind of take-off surface used in the tests and each appropriate climb out speed; and
(2) The kind of landing surface used in the tests and appropriate approach and glide airspeeds.
(b) For multi-engine rotorcraft, information identifying each operating condition in which the fuel system independence prescribed in CS 27.953 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 27.1505(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 27.1353(g)(2) or (g)(3), 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) The airspeeds and rotor speeds for minimum rate of descent and best glide angle as prescribed in CS 27.71 must be provided.
CS 27.1587 Performance information
ED Decision 2018/007/R
(a) The rotorcraft flight manual (RFM) must contain the following information, determined in accordance with CS 27.49 through CS 27.79 and CS 27.143(c) and (d):
(1) Enough information to determine the limiting height-speed envelope.
(2) Information relative to:
(i) The steady rates of climb and descent, in-ground effect and out-of-ground effect hovering ceilings, together with the corresponding airspeeds and other pertinent information including the calculated effects of altitude and temperatures;
(ii) 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. In addition, if there are other combinations of weight, altitude, and temperature for which performance information is provided and at which the rotorcraft cannot land and take-off safely with the maximum wind value, those portions of the operating envelope and the appropriate safe wind conditions must be stated in the Rotorcraft Flight Manual;
(iii) For reciprocating engine-powered rotorcraft, the maximum atmospheric temperature at which compliance with the cooling provisions of CS 27.1041 to 27.1045 is shown; and
(iv) Glide distance as a function of altitude when autorotating at the speeds and conditions for minimum rate of descent and best glide as determined in CS 27.71.
(b) The RFM must contain:
(1) In its performance information section any pertinent information concerning the take-off weights and altitudes used in compliance with CS 27.51;
(2) The horizontal take-off distance determined in accordance with CS 27.65(a)(2)(i), and
(3) The substantiated sea conditions and any associated information relating to the certification obtained with ditching or emergency flotation provisions.
[Amdt No: 27/1]
[Amdt No: 27/5]
AMC 27.1587(b)(3) Performance Information
ED Decision 2018/007/R
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 27.801(e) and 27.802(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: 27/5]
CS 27.1589 Loading information
ED Decision 2003/15/RM
There must be loading instructions for each possible loading condition between the maximum and minimum weights determined under CS 27.25 that can result in a centre of gravity beyond any extreme prescribed in CS 27.27, assuming any probable occupant weights.
CS 27.1593 Exposure to volcanic cloud hazards
ED Decision 2016/024/R
If required by an operating rule, the susceptibility of rotorcraft features to the effects of volcanic cloud hazards must be established.
[Amdt 27/4]
AMC 27.1593 Exposure to volcanic cloud hazards
ED Decision 2016/024/R
The aim of CS 27.1593 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 (a) 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 27/4]