include other "unapproved" data in a separate and distinctively identified portion within the same document.
The RFM is considered necessary for safe operation of the rotorcraft and care should therefore be taken to produce a manual that is consistent with the need for completeness and clarity of the required information. Also, since the RFM is necessary for operation of the rotorcraft in accordance with the certificate limitations, it is considered to be public information.
(3) The page size for the RFM will be left to the discretion of the manufacturer.
In this regard, operational compliance with § 91.31 should be considered. A cover should be provided and should indicate the nature of the contents by means of the title, "Rotorcraft Flight Manual." Each page of the approved portion should bear the notation "FAA/AUTHORITY approved," an indication of the approval sequence of that particular page (e.g., a date of approval, a revision number suitably supported by an amendment log which contains the appropriate date, etc.) the rotorcraft model number as it appears on the type data sheet, and any appropriate document identification number. Pages of the unapproved portion of the flight manual would use the issue date in lieu of the FAA/AUTHORITY-approved date. The material should be bound in semipermanent fashion so that the pages will be protected and retained in proper sequence. In selecting the form of binding, consideration should be given to the necessity for amendment and the ease with which amendments can be accomplished.
(4) Amendments may take the form of revisions or supplements.
A revision is a change to the RFM or its supplement made by the holder of the type certificate (TC) or supplemental type certificate (STC) involved.
(ії) A supplement is an addition to the RFM. If the rotorcraft manufacturer (holder of the TC) adds optional equipment or specific operations (such as Category "A" vertical operation or IFR operations), then the rotorcraft manufacturer is responsible for preparing any necessary RFM supplement. If someone other than the rotorcraft manufacturer applies for an STC to install equipment or modify the rotorcraft such that an RFM supplement is necessary, then the person who applies for the STC is responsible for the preparation of the RFM supplement.
(5) "Revision" may be incorporated by inserting new pages which embody the amended text and, where applicable, by removing superseded pages. A vertical amendment bar or data processing symbol should be inserted in the outer margin, where practicable, to indicate those parts of the text that have been changed. Each amended page should be identified in the same manner as pages of the basic manual and, in addition, should carry the assigned revision number and the FAA/AUTHORITY-approved revision date.
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(6) Supplements are incorporated in the manual by inserting the applicable pages which contain the information associated with the particular change. Each supplemental page should also identify the rotorcraft type and model flight manual for which the supplement was issued, the name of the issuer, and the FAA/AUTHORITY approval date. The following statement is an example of a note which would be included on the title page of a flight manual supplement: "For rotorcraft approved to operate in accordance with the provisions of this rotorcraft flight manual supplement, the information contained herein supplements the information of the basic flight manual.
For limitations, procedures, and performance data not contained in this supplement, consult the basic flight manual."
(7) Supplements should contain as much of the flight manual contents outlined below as considered appropriate for the particular change in type design, including title page and index of contents. It is suggested that these be prepared with a view to insertion in the FAA/AUTHORITY-approved portion of the flight manual as a complete and self-contained unit.
(8) The RFM should contain as much of the information required in Part 27 as is applicable to the individual type and model. For the purpose of standardization, it is recommended that the sequence of sections and of items within sections follow the format presented at the end of this paragraph if practicable.
(9) The following information would normally be included in the introduction section of the flight manual.
Title Page. This page should include the manufacturer's name and address and the rotorcraft model number as it appears on the type certificate data sheet. If desired, include a trade name or trade model number in quotes, provisions for rotorcraft serial number and registration number, approval date of the basic document, and title and signature of the FAA/AUTHORITY approving official.
(ii) Table of Contents. An index should be located at the front of each section or at the front part of the manual.
(iii) Amendment Log. This log should be in the form of a table with provisions to record each amendment, an identifying number, title or description, the page numbers involved, the issue date, the identification of the FAA/AUTHORITY approving official, and the FAA/AUTHORITY approval date.
(iv) Separate amendment logs should be provided for each type of amendment issued; i.e., Log of Revisions, Log of Supplements, etc. Amendments issued by other than the holder of the basic type certificate should include a separate amendment log which, in addition to the issue date, should also identify the issuer and the STC number or other approval basis for the associated modification.
Par 762 1003
(v) List of Current Pages. This table should list, for each approved page of the manual, the issue date and any other appropriate identification necessary to establish that the manual is complete and current.
(10) The following flight manual format would be acceptable. The format recommends a sequence of sections and suggests items which would be included in those sections.
FLIGHT MANUAL FORMAT
INTRODUCTION
PART I, FAA/AUTHORITY APPROVED Section 1 Limitations Section 2 Normal Procedures Section 3 Emergency Malfunction Procedures Section 4 Performance Data Section 5 Optional Equipment Supplements
PART II, MANUFACTURER'S DATA Section 6 Weight and Balance Section 7 Systems Description Section 8 Handling, Servicing, and Maintenance Section 9 Supplemental Performance Information INTRODUCTION: This section would include any signature pages, list of approved pages, the log of revisions, and any additional introductory information desired. For each section, it is suggested that the following major titles be utilized and that the recommended information listed under each title be incorporated. Each section should include a table of contents and a list of figures applicable to that particular section.
Section 1 - Limitations:
a. Kinds of Operation.
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Under this heading, the certification basis, crew requirements, VFR and/or IFR flight authorizations, and any operational restrictions would be presented.
b. Flight Limitations.
This section would include limitations with respect to airspeed, altitude, ambient temperatures, wind, slope, prohibited maneuvers, and any other flight limitations associated with a particular rotorcraft.
c. Weight Limitations.
This section would contain all gross weight, center of gravity (both longitudinal and lateral) limitations, and any other weight limitations unique to the rotorcraft (i.e., crew, passenger and/or cargo loadings).
d. Powerplant Limitations.
This section would include the temperature and pressure limits associated with powerplant operation (i.e., torque, RPM, TOT, etc.). This section would also include approved fuels and oils and their temperature and pressure limits. Any accessories attached to the powerplant (l.e., starters, generators, etc.), to which limitations in starting or operation are applicable, would be included herein.
e. Rotor Limitations.
This would include the power-on and power-off RPM limits, the effect of altitude on these parameters, and any other limitations associated with the rotor systems).
f. Drive System Limitations.
This section would include all limitations associated with the drive system (i.e., main transmission, any adapter gearboxes, tail rotor gearbox, and any other drive system component applicable to a particular rotorcraft).
g. System Limitations.
This section would include any particular system limitations unique to the rotorcraft (i.e., battery limitations, hydraulic system limitations) and any limitations associated with the various types of stability augmentation and/or automatic flight control systems.
h. Instrument Markings.
All instrument markings would appear in this section. The significance of each limitation and of the color coding would be explained in this paragraph.
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i. Placards.
The exact wording and general location of all placards would appear in this section.
Section 2 - Normal Procedures:
a. Preflight Checks.
This paragraph would include any exterior, interior, and any system checks prior to starting the engine(s).
b. Engine Start.
This paragraph would include any procedures associated with the engine start.
c. System Checks.
This paragraph would include any system check procedures such as hydraulic, stability augmentation, electrical, flight control, etc., which should be accomplished prior to takeoff.
d. Takeoff.
This paragraph would include any procedures associated with the takeoff and any procedures unique or applicable to the takeoff profile.
e. Cruise and/or Level Flight.
This paragraph would include any procedures applicable to cruise and/or level flight operation.
f. Approach and Landing.
This paragraph would include any procedures required or recommended for the approach and landing operation of the rotorcraft.
g. Engine/Rotor Shutdown.
This paragraph would include any procedures applicable to the engine and/or rotor shutdown and any procedures applicable upon completion of the rotorcraft operation.
h. Miscellaneous Procedures.
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This section would include procedures for miscellaneous systems or conditions, such as bleed air heater, anti-ice systems, cold weather operations, etc.
Section 3 - Emergency and Malfunction Procedures:
a. Introduction.
This paragraph would include any introductory type information (i.e., definitions of terms used and any other information the manufacturer deemed appropriate).
b. Powerplant Failures.
This paragraph would include any information relative to engine, fuel control, or any other powerplant related emergency or malfunction.
c. Drive System Failures.
This paragraph would include recommendations and procedures relative to any drive system failure and/or malfunction.
d. System Failures.
This paragraph would include procedures and recommendations relative to any system failure and/or malfunction (i.e., electrical, hydraulic, and augmented flight control systems).
e. Fire.
This paragraph would include procedures to be followed in the event that engine, cabin, baggage compartment fire or smoke is detected.
f. Emergency Egress.
This paragraph would include emergency evacuation procedures for both the flightcrew and the passengers.
Section 4 - Performance Data:
a. Power Assurance.
This section would include all information relative to the power assurance checks.
b. Hover Information.
Par 762 1007
This paragraph would include all information relative to hover performance (i.e., hover ceiling IGE and OGE for single and/or multiengine operation). Any relative wind effects may also be included.
c. Height Velocity, Climbs, and Descents.
This paragraph would contain information relative to the HV curves, normal climbs, autorotation speeds, and any other data applicable to the particular rotorcraft.
d. Airspeed Calibration.
This paragraph would include the airspeed calibrations for the particular rotorcraft.
Section 5 - Optional Equipment Supplements:
This section would include all optional equipment supplements. These supplements may modify any of the limitations, procedures (both normal and emergency), and performance characteristics of the basic rotorcraft.
PART II, Manufacturer's Data (Not FAA/AUTHORITY Approved) Section 6 - Weight and Balance:
All supplemental weight and balance information such as crew tables, passenger tables, fuel and oil tables, cargo tables, and any other loading tables applicable to the particular rotorcraft would appear in this section.
Section 7 - Systems Description:
This section would include all information relative to the various rotorcraft systems that the manufacturer believes would apply to the particular rotorcraft.
Section 8 - Handling, Servicing, and Maintenance:
This section would include all information relative to the handling, servicing, and maintenance that the manufacturer would care to present. This section would also include dimensions (l.e., baggage areas, doors, and any internal, external information appropriate to the rotorcraft).
Section 9 - Supplemental Performance Information:
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This section would include any supplemental performance information the manufacturer would wish to provide. This section would also contain the cruise-range information associated with IFR operation.
763. §27.1583 (Amendment 27-16) OPERATING LIMITATIONS.
a. Explanation. The purpose of this section is to present the limitations applicable to the rotorcraft type and model as established in the course of the type certification process. The limitations should be presented with explanation when approved. To the maximum practicable extent, the limitations should be presented in "operations" language and format. Since operation of the rotorcraft in accordance with such limitations is required by the operating regulations, the following should be inserted as a note at the beginning of this section:Operation in compliance with the limitations presented in this section is required by the Federal Aviation Regulations.
Section 27.1583 merely states that certain information must be given. The specific information is found during the showing of compliance with other paragraphs in the regulation.
b. Procedures.
(1) Section 27.1545 gives the markings required for the airspeed indicator.
(2) Rotor limits are established during compliance with § 27.33. The method of marking is specified in § 27.1549.
(3) Powerplant limits are discussed under § 27.1549.
(4) Weight limitations are specified in § 27.25. In the operating limitations section, there should be a statement of the maximum and minimum certificated takeoff and landing weights.
(5) Center of gravity limits are determined in accordance with § 27.27. Detailed center of gravity limitations information may either be presented in the limitations section of the flight manual or presented as a statement in limitations section which references charts or page numbers in the performance section. If landing gear position can measurably affect allowable CG, this information should be presented together with the moment change due to gear retraction.
(6) The minimum flightcrew is determined under § 27.1523 and is dependent upon the kinds of operation authorized. The established number and identity, by crew position of the minimum flightcrew, must be listed.
(7) Kinds of operations are established under § 27.1525. This section should contain the following preamble:iThis rotorcraft is certified in the normal category (A and/or B) and is eligible for the following kinds of operation when the appropriate Par 762 1009
instruments and equipment required by the airworthiness and/or operating rules are installed and approved and are in operable condition. Those of the following, and any others that are applicable, should be listed.
(1) Day and night VFR.
(ii) Approved to operate in known icing conditions.
(iii) IFR.
(iv) Extended overwater operations (ditching).
(v) External load operation.
(8) Limiting heights and speeds are determined under § 27.79 and are presented in the form of a height versus velocity diagram in the performance information section.
(9) Often other limitations are included in the limitations section that are not specifically mentioned in the rules but which are necessary for safe operation.
Examples are:
• Altitude limits.
(il) Ambient temperature limits.
Conditions for use of rotor brake.
(iv) Prohibitions against prolonged hover in cross or tail winds to prevent accumulation of noxious fumes in cockpit or cabin.
(v) Prohibitions against acrobatic maneuvers.
(Vi) Required placards including text and location.
(vii) Special airworthiness equipment installations such as engine out or low rotor RPM warning systems.
764. § 27,1585 (Amendment 27-16) OPERATING PROCEDURES.
a. Explanation. The procedures sections of the manual should contain essential information peculiar to the particular type or model, the knowledge of which may be expected to enhance safety in the kinds of operations for which the type or model is approved. Information or procedures not directly related to airworthiness, or not under 1010 Par 763
control of the crew, should not be included, nor should any procedure which is accepted as basic airmanship.
(1) Procedures information should be presented with respect to normal and emergency procedures. Alternatively, information outside the category of normal procedures may be subdivided into categories described as "abnormal" procedures and "emergency" procedures, as described herein.
(2) Notes, cautions, and warnings may be used to emphasize specific instructions or information in general accord with the following.
"Note" should be used with respect to matters not directly related to safety but which are particularly important (e.g., Note: For normal twin-engine operation, maximum permissible torque needle split is 4 percent total).
(it) "Caution" should be used with respect to safety matters of a secondary order not immediately imminent (e.g., Caution: On engine restart reduce ITT to 750° C on the operating engine).
(iii) "Warning" should be used with respect to safety matters of a primary order or immediately imminent (e.g., Warning: Do not allow rotor RPM to drop below minimum limits).
(3) The operating procedures of this section have been developed with specific regard for the design features and operating characteristics of the rotorcraft and have been approved by FAA/AUTHORITY for guidance in identifying acceptable procedures for safe operation. Observance of these procedures is not mandatory, and FAA/AUTHORITY approval of such procedures is not intended to prohibit or discourage development and use of improved or equivalent alternate procedures based on operational experience with the rotorcraft. When alternate procedures are used, full responsibility for compliance with applicable airworthiness safety standards rests with the operator.
b. Procedures. Procedural information should be presented in substantial accord with the categories described below:
(1) Normal Procedures. Normal procedures are concerned with peculiarities of the rotorcraft design and operating features encountered in connection with routine operations, including malfunction cases not considered in the other procedures section
(l.e., not considered to degrade safety). Material conforming to the above should be presented for each phase of flight, following in sequence from preflight through engine shutdown, and should include, but not be limited to, systems operation (including fuel system information prescribed in § 27.1585(b)), missed approaches, balked landings, Par 764 1011
(2) Emergency Malfunction Procedures.
(i) Abnormal procedures are concerned with foreseeable situations, usually entailing a failure condition, in which the use of special systems, and/or the alternate use of regular systems, may be expected to maintain an acceptable level of airworthiness. Typical examples of events considered to entail abnormal procedures are engine failure and associated conditions for safe flight, stopping and restarting engines in flight, extending landing gear or flaps by alternate means, approach with inoperative engine(s), etc.
(ії) Emergency procedures are concerned with foreseeable but unusual situations in which immediate and precise action by the crew, as detailed in the recommended procedures, may be expected to reduce substantially the risk of disaster.
Typical examples of incidents considered to be emergencies are fire, ditching, loss of tail rotor thrust, etc.
(iii) Amendment 27-11 added ditching standards to Part 27. When ditching approval is requested, appropriate procedures and information will be included in the manual. Scale model tests are generally used to prove autorotation "ditching" characteristics and to prove stability in the water (capsize threshold) of the rotorcraft type design. Many rotorcraft designs require emergency float bags that deploy either before water contact or shortly after water contact to provide the flotation and stability necessary to comply with the requirements.
(A) Autorotation altitudes and airspeeds and water contact information, if appropriate, derived from or used during the ditching model tests, should be confirmed during FAA/AUTHORITY flight tests and should be included in the manual. Information concerning sea states or wave height to length ratios, investigated and found satisfactory, may be included in the manual if nonsevere sea states are likely to be exceeded.
(B) Instructions for deploying liferafts may be needed for certain designs. For example, if liferafts are stowed outside the cabin, special instructions may be necessary.
(iv) Evacuation Procedures for Rotorcraft Litter Configurations.
Appropriate procedures and minimum crew requirements should be considered and included in the manual or manual supplement, if necessary, to assure timely evacuation.
(3) The use of illustrations to show controls, instruments, explain systems, etc., is encouraged.
(4) If the unusable fuel supply in any tank exceeds 5 percent or 1 gallon, whichever is greater, a statement should appear in the normal procedures section to 1012 Par 764
warn the pilot that the quantity of fuel remaining in the tank when the gauge reads zero is not usable in flight.
764A. § 27.1585 (Amendment 27-21) OPERATING PROCEDURES.
a. Explanation. Amendment 21 to the regulation adds the requirement to present the airspeeds and type of landing surface used in takeoff and landing tests.
Additionally, the airspeeds and rotorspeeds for minimum rate of descent and best glide in autorotation at maximum gross weight should be presented in the Rotorcraft Flight Manual (RFM).
b. Procedures. All of the policy material pertaining to this section remains in effect with the following additions:
(1) Takeoff and landing procedures and speeds and the kind of surface used in takeoff and landing tests should be presented in the Normal Procedures section of the RFM.
(2) The airspeeds and rotor speeds corresponding to minimum rate of descent and maximum gliding distance in autorotation should be included in the Emergency Malfunction section of the RFM.
765. § 27.1587 (Amendment 27-21) PERFORMANCE INFORMATION.
a. Explanation.
(1) This section contains the performance information necessary for operation in compliance with applicable performance requirements of FAR Part 27 and applicable special conditions together with additional information and data essential for implementing pertinent operational requirements.
(2) Performance information and data may be presented for the range of weight, altitude, temperature, and other operational variables stated as operational performance limitations. It is recommended that performance information and data be presented substantially in accordance with the following paragraphs. Where applicable, reference to the appropriate requirement of the certification or operating regulation should be included.
General. Include all descriptive information necessary to identify the configuration and conditions for which the performance data are applicable. Such information may include the complete model designations of rotorcraft and engines, definition of installed rotorcraft features, and equipment that affects performance together with the operative status thereof. This section should also include definitions or terms used in the performance section (i.e., IAS, CAS, ISA, configuration, etc.) plus Par 764 1013