* 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 gystem failure and/or malfunction (1.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 1s 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.
This paragraph would include all information relative to hover performance (1.e., hover ceiling IGE and OGE for single and/or multiengine operation). Any relative wind effects would algo be included.
c. Takeoff and Landing and Climb Performance.
This paragraph would include information relative to the takeoff and landing profiles (1.e., HV curves, normal climbs, autorotation speeds, takeoff and landing distance over 50-foot obstacles, and any other data applicable to the particular helicopter).
d. Airspeed Calibration.
particular helicopter. This paragraph would include the airspeed calibrations required for the Chap 2 Par 762 1209
AC 29-2, CHG 1 11/19/84 * 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 helicopter.
PART II, Manufacturer's Data (Not FAA 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 helicopter would appear in this section.
Section 7 - Systems Description:
This section would include all information relative to the various helicopter systems that the manufacturer believes would apply to the particular helicopter Section 8 - Handling, Servicing, and Maintenance:
servicing, and maintenance that the manufacturer would care to present. This section would include all information relative to the handlins This section would also include dimensions (1.e., baggage areas, doors, and any internal, external information appropriate to the helicopter).
Section 9 - Supplemental Performance Information:
This section would include any supplemental performance information the manufaoturer would wish to provide. This section would also contain the cruise-range information associated with IFR operation.
Chap 2 1210 Par 762
* 763. § 29.1583 (through Amendment 29-19) OPERATING LIMITATIONS.
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: ‚Operation in compliance with the limitations presented in this section 18 required by the Federal Aviation Regulations.' 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 limitation section to the appropriate graph or page.
(5) Center of gravity limits are determined in accordance wth § 29.27 and may be presented in the same manner as prescribed for the weight limitations
(1.e., a statement under "oenter of gravity limits" in the limitations section which references graphs or page numbers in the performance section). If landing gear position can measurably effect allowable c.g., this information should be presented together with the moment change due to gear retraction.
(6) The minimum flightcrew is determined under § 29.1523 and 18 dependent upon the kinds of operation authorized. The established number and identity, by crew position of the minimum flightorew, must be listed.
(7) Kinds of operations are established under § 29.1525. This section Transport Category (A and/or B) and is eligible for the following kinds of • operation when the appropriate instruments and equipment required by the should contain the following preamble: This rotorcraft is certified in the Chap 2 Par 763 1211
AC 29-2, CHG 1 11/19/84 * 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 VER.
(11) Approved to operate in known icing conditions.
(111) IFR.
(1v) Category A vertical operations from ground level or elevated heliports.
(v) Extended overwater operations (ditching).
(vi) External load operations.
(8) Limiting heights and speeds are determined under § 29.1517 and are presented in the form of a height versus velocity diagram in the limitations section for Category A rotorcraft and in the performance section for Category B rotorcraft.
(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, his fuel gage will read "zero." A statement should appear in the limitations section to warn the pilot that the quantity of fuel remaining in the tanks when the gage reads zero 18 not usable in flight.
(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:
(1) Altitude limits.
(11) Ambient temperature limits.
(111) Conditions for use of rotor brake.
(1v) Prohibitions against prolonged hover in cross or tail winds to prevent accumulation of noxious fumes in cookpit or cabin.
(v) Prohibitions against acrobatic maneuvers.
(V1) Required placards including text and looation.
(Vi1) Special airworthiness equipment installations such as engine • out or low rotor r.p.m. warning systems.
Chap 2 1212 Par 763
* 764. § 29.1585 (through Amendment 29-19) 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 oategory 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.
(1) "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 ITT to 750° C on the operating engine).
(i11) "Warning" should be used with respect to safety matters of a primary order or imminent (e.g., Warning: Do not allow rotor r.p.m. 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 for guidance in identifying acceptable procedures for safe operation. Observance of these procedures is not mandatory, 22252 and FAA approval of such procedures is not intended to prohibit or discourage development and use of improved or equivalent alternate procedures based on 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 rotororaft design and operating features encountered in connection with routine operations, including malfunction cases not considered in the other procedures section (1.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.
Chap 2 Par 764 1213
AC 29-2, CHG 1 11/19/84
(2) Abnormal Procedures (Optional). Abnormal procedures are concerned vith foreseeable situations, usually entailing a failure condition, in which the ise of special systems, and/or the alternate use of regular systens, may be expeoted to maintain an acceptable level of airworthiness. Typical examples of events considered to entail abnormal procedures are minor engine malfunctions and associated conditions for gafe flight, stopping and restarting engines in flight, extending landing gear or flaps by alternate means, approach with inoperative engine (s), etc.
(3) Emergency Procedures.
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.
(4) Ditching Procedures. Amendment 29-12 added ditohing 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 helicopter type design. Many helicopter designs require emergency float bags that deploy either before water contaot or shortly after water contact to provide the flotation and stability necessary to comply with the requirements.
(1) Autorotation altitudes and airspeeds and water contact information, if appropriate, derived from or used during the ditching model tests, should be confirmed during FAA 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.
(11) Instructions for deploying liferafts may be needed for certain designs. For example, if liferafts are stowed outside the cabin, special instructions may be necessary.
(5) Evacuation Procedures for Helicopter 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.
Chap 2 1214 Par 764
* 765. § 29.1587 (through Amendment 29-19) PERFORMANCE INFORMATION.
Explanation•
(1) This section would contain the performance information necessary for operation in compliance with applicable performance requirements of FAR Part 29 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.
(1) 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 rotororaft 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 (1.e., IAS, CAS, ISA, configuration, CDP, VTOSS, Category A, Category B, LDP, etc.) plus calibration data for airspeed, ambient air temperature, and other information of a general nature.
Performance Procedures. The procedures, techniques, and other conditions associated with obtainment of the flight manual performance should be included, the procedures may be presented as a performance subsection or in connection with a particular performance graph. In the latter case, a comprehensive listing of the conditions associated with the particular performance may serve the objective of "procedures" if sufficiently complete.
Performance figures are based on the installed minimum specification engine unless normally depreciated engine performance is approved.
(111) Wind Accountability. Wind accountability may be utilized for conventional takeoff field lengths. This accountability shall not be more than 50 percent of the nominal wind component along the takeoff path opposite to the direction of takeoff. In some rotorcraft, it may be necessary to discount the beneficial aid to takeoff performance for winds from 0 to 10 knots. This should be done if it is evident that the winds from 0 to 10 knots have resulted in a significant degradation to the takeoff performance due to the washout of the ground effect cushion.
The following list is illustrative of the information that may be provided for a transport Category "A" and "B" helicopter.
(A) Density altitude chart for converting from pressure to density altitude.
(B) Temperature conversion chart (°C to °F to °C). • Chap 2 Par 765 1215
AC 29-2, CHG 1 11/19/84 * (C) Airspeed calibration (calibrated vs. indicated airspeed) for both pilot and copilot systems for level flight, climb, autorotation, and recommended approach rate of descent.
(D) Altimeter correction for pilot and copilot instruments showing the correction factor vs. indicated airspeed at sea level and altitude.
(E) Hover performance charts both in and out-of-ground effect with instructions for their use. The out-of-ground effect hover performance chart is not required but may be useful.
(F) A series of climb performance charts for various weights showing rate of olimb vs. pressure altitude for a range of temperatures and showing the variation of best rate of climb speed with pressure altitude. The conditions should appear on each chart (1.e., power, weight, single, or multiengine, etc.).
(G) A chart showing the takeoff flight path for Category A presented in height vs. distance from the hover wheel height to the point at whita vo the chat shot 1 35 fry the reached, dad then pointed a se (H) A chart or series of charts to allow calculation of any additional distance which may be required to accelerate to best rate of climb speed from Vross• (I) Landing distance chart for Category A showing the landing distance from a 50-foot height (25-foot for VTOL operations from an elevated heliport) to a stop with one engine inoperative vs, pressure altitude over the range of temperatures being certified. This chart should identify the balked landing decision point (LDP) so the pilot will know how to achieve this performance.
(J) For Category B, a chart or series of charts at various weights showing takeoff distance from hover to 50 feet vs. pressure altitude over the range of temperatures being certified.
(K) For Category B, a landing distance chart similiar to the one for Category A from a 50-foot height to stop with one engine inoperative.
(L) For turbine powered helicopters in all categories, a power assurance check chart.
(M) A statement of the maximum crosswind and downwind components that have been demonstrated as safe for operation near the ground.
(v) Miscellaneous Performance Data. Any performance information or data not covered in items (A) through (L) above, but considered necessary or for use with the operating procedures contained in the rotorcraft flight manual, should be included.
Chap 2 1216 Par 765