(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 the 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 29 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.
(i) 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, for 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.
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(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.
Under this heading, crew requirements, VFR and/or IFR flight authorizations, and any operational restrictions would be presented.
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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 (i.e., HV limitations for Part 29 Category A 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, WAT limitations for Part 29 rotorcraft, etc.).
d. Powerplant Limitations.
This section would include the temperature and pressure limits associated with powerplant operation; i.e., torque, RPM, turbine outlet temperature (TOT), etc. This section would also include approved fuels and oils and their temperature and pressure limits. Any accessories attached to the powerplant (i.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 system(s).
f. Drive System Limitations.
This section would include all limitations associated with the drive system (i.e., main transmission, any adapter gear boxes, 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.
i. Placards.
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The exact wording and general location of all placards pertaining to flightcrew function or cargo loading 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(s).
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 duration of the rotorcraft operation.
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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.
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.
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Section 4 - Performance Data:
a. Power Assurance.
This section would include all information relative to the power assurance checks.
b. Hover Information.
This paragraph would include all information relative to hover performance (i.e., hover ceiling in ground effect (IGE) and out of ground effect (OGE) for single and/or multiengine operation). Any relative wind effects would also be included.
c. Takeoff and Landing and Climb Performance.
This paragraph would include information relative to the takeoff and landing profiles (i.e., height-velocity (HV) curves, normal climbs, autorotation speeds, takeoff and landing distance over 50-foot obstacles, and any other data applicable to the particular rotorcraft).
d. Airspeed Calibration.
This paragraph would include the airspeed calibrations required 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.
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AC 29-2C, Chg 4 5/1/2014 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 (i.e., baggage areas, doors, and any internal, external information appropriate to the rotorcraft).
Section 9 - Supplemental Performance Information:
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.
AC 29.1583. § 29.1583 (Amendment 29-24) 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 without explanations other than those explanations prescribed in part 29. 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: “Compliance with the limitations in this section is required by the applicable operating rules.”
Section 29.1583 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 29.1545 gives the markings required for the airspeed indicator.
(2) Rotor limits are established during compliance with § 29.33. The markings are specified in § 29.1549.
(3) Powerplant limits are discussed under §§ 29.1549 through 29.1553.
(4) Weight limitations are specified in § 29.25. In the operating limitations section, there should be a statement of the maximum and minimum certificated takeoff and landing weights. For those weight limitations that vary with altitude, temperature, or other variables, the variation in weights may be given in the form of graphs in the performance section of the manual and included as a limitation by specific reference in the limitations section to the appropriate graph or page.
(5) Center of gravity (CG) limits are determined in accordance with § 29.27 and may be presented in the same manner as prescribed for the weight limitations (i.e., a statement under “center of gravity limits” in the limitations section which references Page G - 42
graphs 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 § 29.1523 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 § 29.1525. This section should contain the following preamble: “This rotorcraft is certified in the Transport 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. An example would be for rotorcraft certificated both as category A and category B, and with a maximum weight greater than 20,000 pounds (9072 kg), the flight manual limitations should agree with § 29.1(d) by not implying that category B is certificated for more than 9 passengers.
(8) Limiting heights and speeds are determined in accordance with § 29.79 and established as operating limitations in accordance with § 29.1517.
(i) For transport category A rotorcraft, § 29.1583(f) requires that enough information be furnished in the limitations section of the rotorcraft flight manual ( RFM) to allow compliance with the requirements of § 29.1517. One method of complying with this requirement is to provide charts or graphs similar to those shown in Figures AC 29.79-1 and AC 29.79-2, as required to encompass the approved takeoff and landing envelope of the rotorcraft. However, many category A approvals have not required an actual HV diagram to be included in the RFM for category A operations. The category A takeoff and landing profiles are developed so that a continued takeoff, go- around, or safe landing can be accomplished following failure of the critical engine at any point in the profile.
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AC 29-2C, Chg 4 5/1/2014 Development of the category A profiles is very similar to HV testing. The resulting takeoff and landing profiles coupled with precisely defined procedures and the weight, altitude, and temperature (WAT) limitations for which the profiles have been shown to be valid constitute an operating envelope for which compliance with § 29.1517 has been demonstrated. During the category A flight test evaluation, abuse testing is done to verify that variations reasonably expected to occur in service will not result in a hazardous condition from which a safe landing cannot be accomplished. Therefore, if the category A takeoff and landing profiles, procedures, and WAT limitations are adequately and clearly defined in the RFM, this information is considered sufficient for compliance with the requirements of § 29.1583(f) without the inclusion of an actual HV diagram. The category A procedures and profile definitions may be presented in the normal procedures or performance sections of the RFM but should be referenced as being mandatory requirements in the limitations section unless an HV diagram valid for category A operations is presented.
(ii) For transport category B rotorcraft, the height-speed information developed in accordance with § 29.79 should be included in the performance section of the RFM in accordance with § 29.1587(b)(6). HV diagrams similar to those shown in Figures AC 29.79-1 and AC 29.79-2 have been satisfactory for previous certifications.
(iii) For transport category B rotorcraft with part 29 and CAR part 7 certification bases prior to Amendment 29-21, the HV information should be included in the limitations section of the RFM unless the following procedure has been accomplished for rotorcraft, which satisfy the following conditions:
(A) Certificated for a maximum gross weight of 20,000 pounds or less;
and (B) Configured with nine passenger seats or less. RFM s for rotorcraft falling in this group may be revised to remove the HV data from the limitations section and place it in the performance section. Such actions should be processed and approved by a STC. Conditions b. (8)(iii)(A) and (B) above should be shown as limitations on the STC, and the certification basis should include Amendment 29- 21. If a TC holder desires to revise the type design to take advantage of Amendment 29-21, the certification basis on the TC data sheet should be revised to show §§ 29.1, 29.79,
29.1517, and 29.1587 of Amendment 29-21 for the HV data in the RFM.
(9) Unusable fuel tests are required by § 29.959. When the amount of unusable fuel has been determined, the manufacturer calibrates his fuel quantity system so that when the fuel quantity in the tank is down to the unusable quantity, the fuel gauge will read “zero.” Additional information may also be provided in the RFM to advise the pilot(s) of different unusable fuel quantities for various flight conditions.
(10) 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:
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(i) Altitude limits.
(ii) Ambient temperature limits.
(iii) 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.
AC 29.1583A. § 29.1583 (Amendment 29-24) OPERATING LIMITATIONS.
a. Explanation. Amendment 29- 24 to the regulation establishes additional operating limitations for maximum allowable wind for operation near the ground and ambient temperature limits.
b. Procedures. All of the previous advisory material remains applicable except that the minimum and maximum ambient temperature limitations are required in the limitations section. (These limitations were optional before Amendment 29-24.)
Additionally, the wind envelope for safe operation near the ground, which is established under § 29.143(c), must be included in the Limitations section. Such operations may include: IGE hover, takeoff, landing, rolling takeoff, rolling landing, and taxi. Advisory material for § 29.143(c) is given in paragraph AC 29.143(a)(2)(ii).
AC 29.1585. § 29.1585 (Amendment 29-24) 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 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.
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AC 29-2C, Chg 2 4/25/06
(2) Notes, cautions, and warnings may be used to emphasize specific instructions or information in general accord with the following.
(i) “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).
(ii) “Caution” should be used with respect to safety matters of a secondary order not immediately imminent (e.g., Caution: On engine restart reduce inter-turbine temperature (ITT) to 750° C on the operating engine).
(iii) “Warning” should be used with respect to safety matters of a primary order or 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
(i.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 § 29.1585(b)), missed approaches, etc.
(2) Malfunction or Abnormal Procedures (Optional). Malfunction or abnormal procedures are included in many flight manuals to provide corrective crew actions that are not as urgent as those in the Emergency Procedures sections. These procedures are concerned with foreseeable situations, usually entailing a failure condition, in which the use of special systems, or the alternate use of regular systems, may be expected to maintain an acceptable level of safety. Typical examples of events considered to entail abnormal procedures are engine failure and or conditions that require an engine shutdown (under flight conditions where the failure is not critical), stopping and restarting engines in flight, extending landing gear or flaps by alternate means, approach in multiengine aircraft with inoperative engine(s), etc.
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(3) Emergency Procedures. Emerge ncy 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 or control, etc. It is expected that, in the case of tail rotor failure, the emergency procedures will have been validated by analysis, simulation, or any relevant service experience. The analysis or simulation of the tail rotor control failure procedures may be validated where practical by limited flight test.
(4) Ditching Procedures. Amendment 29 -12 added ditching standards to Part 29. 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.
(i) 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 heights to length ratios, investigated and found satisfactory, may be included in the manual if nonsevere sea states are likely to be exceeded.
(ii) Instructions for deploying life rafts may be needed for certain designs.
For example, if life rafts are stowed outside the cabin, special instructions may be necessary.
(5) 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.
(6) The use of illustrations to show controls, instruments, explain systems, etc., is encouraged.
AC 29.1587. § 29.1587 (Amendment 29-24) PERFORMANCE INFORMATION.
a. Explanation.
(1) This section should contain the performance information necessary for operation in compliance with applicable performance requirements of Part 29 and applicable special conditions, together with additional information and data essential for implementing pertinent operational requirements.
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