(A) Systems Affected by Icing. Gross inaccuracies in altitude and airspeed indicators resulting from icing could be disastrous in IFR flight. For rotorcraft not equipped with approved alternate static sources, static ports should be carefully evaluated and should either be heated or an analysis verified by flight test data submitted to substantiate leaving them unheated. Static line routing should be carefully evaluated for low spots. In addition, if static ports are on the side of the rotorcraft, the lines should be initially routed upward just behind the static ports, then down to a drain.
If the lines are initially routed upward, the lines will not fill with water when the rotorcraft is flown through rain or is washed.
(B) Overvoltage Protection. If the rotorcraft is certificated under part 29, Category A, it is required to have overvoltage protection. Other rotorcraft may have this protection, but many do not. Since overvoltage protection is specifically required for IFR operation, the rotorcraft’s basic electrical system should be very carefully reviewed for this capability.
(C) Power Adequacy Indication. Most flight instruments th at use a power supply have a visual means integral with the instrument to indicate the adequacy of the power being supplied. For those required flight instruments that are not provided with a visual means, the following must be accounted for:
(1) The visual means provided must be at least adjacent to the instrument.
(2) The visual means must be adequately placarded.
(3) The power must be measured at or near the point where it enters the instrument.
(4) For electrical instruments, the power is considered adequate when the voltage is within approved limits. The source of power for the visual means of indication must be independent of the source of power for the instrument itself.
Independent in this case means a separate circuit protective device and a separate distribution system bus.
(D) Multiple System Separation. Multiple systems performing the same function are required in certain instances because it is probable that a single system will fail. Separation of such systems would preclude a single fault from causing a multiple system failure. The following should be considered:
(1) When possible, cable routing should be accomplished to assure the maximum separation; for example, one system routed on one side of the rotorcraft and the other system on the opposite side. In some areas, physical separation may be minimal, as pedestals, junction boxes, and equipment racks bring systems close together.
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AC 29-2C, Chg 7 2/4/2016
(2) Systems that are required to be duplicated should not be routed through one electrical disconnect plug.
(3) System grounds should be evaluated to assure wiring for two required systems are not grounded to the same terminal. If a terminal strip contains grounds for multiple systems, it should be grounded to the rotorcraft’s airframe in two places from two separate terminals.
(E) Circuit Protective Devices. All systems that are “required” for IFR operation are considered necessary for safe IFR operation, and the circuit protective devices for those systems should generally be accessible to the crew in the cockpit so they can be readily reset or replaced in flight. For example, where a capability is provided that is above the minimum certification requirements, accessibility may not be an issue. A tradeoff here, however, is that additional equipment may be required for dispatch in IFR operation. The location of the generator field protective devices has been a problem in some rotorcraft. The protective devices that can result in the loss of a required power system source should be capable of being reset or replaced in the cockpit while in flight. This position is further supported by the occurrence of nuisance opening of circuit protective devices in rotorcraft. Further discussion on this issue is included in section 29.1357 of this AC.
(F) Intercommunication System. All audio for the entire rotorcraft comes together at this system. An evaluation should be made to assure that no single failure would result in the loss of all audio for the rotorcraft. Check for common grounds, common connectors, etc. Power inputs should also be disabled.
(15) RFM Material.
(i) In addition to other required information, the limitations section of the RFM or RFM Supplement (RFMS) must include the approved IFR flight envelope, minimum IFR crew requirements, the minimum required equipment for dispatch into IFR conditions that is not covered by the operating regulations, and the maximum approach gradient that has been approved. If a significant loss of altitude is experienced in any flight regime or maneuver during certification analysis or testing, the emergency operating procedures should include a statement of this altitude loss along with any other appropriate information.
(ii) The limitations section of the RFM should not include restrictions prohibiting external cargo operations. These operations are covered by parts 91 and 133, and all external load operations conducted under these parts must be approved by the controlling operations inspector. It is the responsibility of the operator to demonstrate and the operations inspector to confirm that any external load operation, including en route IFR, can be safely conducted.
(16) Rotorcraft Flight Below Instrument Flight Minimum Speed.
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(i) The advent of localizer performance with vertical guidance (LPV) precision GPS approach procedures may necessitate flying at airspeeds below the previously published instrument flight minimum speed (VMINI) established for most rotorcraft under Appendix B to part 29, paragraph II.(c).
(ii) Additionally, some modern automatic flight control systems (AFCS) have been certificated to fly fully-coupled below previously published VMINI in order to improve operational safety while conducting certain operations, such as Search and Rescue, steep-angle approaches, and special rig approaches.
(iii) Certification for flight below previously published VMINI will require the applicant to either re-establish VMINI at a lower airspeed per Appendix B to part 29 or be granted special conditions that specifies the AFCS reliability and functionality requirements that allow for coupled flight below the previously established VMINI.
(A) If VMINI is to be re-established, the certification requirements in Appendix B to part 29 for VMINI must be followed. Among the part 29 requirements, below are two items that are often overlooked.
(1) Static and dynamic stability requirements of Appendix B to part 29 must be complied with at all approved descent angles.
(2) Pilot workload needs to be evaluated at the proposed lower VMINI.
Legacy AFCS may not be able to cope with higher angles of descent, thus increasing pilot workload beyond an acceptable level.
(B) The FAA has previously approved special conditions that permit rotorcraft to fly below airspeeds at which the stability requirements of Appendix B to part 29 cannot be demonstrated. The bas es of these special conditions are that the AFCS has specific modes that permit coupled flight from VMINI to a minimum airspeed (or groundspeed specified by the applicant), stabilized flight at the minimum airspeed (or groundspeed), and flight from the minimum airspeed back to VMINI. The following items should be considered if the applicant chooses to utilize a robust AFCS to permit coupled flight below the previously established VMINI. These topics are not all -inclusive, but are general considerations. The actual requirements specified within an individual project’s special conditions will depend on the specific functionalities provided by the design.
(1) The rotorcraft must be certificated for IFR flight and meet the part 29 requirements for category A engine isolation.
(2) For system safety calculations for functional failure modes with operations less than VMINI, an exposure time of no less than the entire flight duration should be used.
(3) The AFCS should provide coupled flight modes that permit safe and controlled flight in the three axes at all airspeeds (lateral position and speed, Page Apdx B - 23
AC 29-2C, Chg 7 2/4/2016 longitudinal position and speed, and height and vertical speed)) from the previous VMINI to a hover (within the maximum demonstrated wind envelope). The AFCS should also provide automatic transition to the helicopter instrument flight (Appendix B to part 29) envelope as part of normal sequencing. Additional considerations include:
(i) A pilot-selectable “Go-Around” mode to safely interrupt any other coupled mode and automatically transition to the helicopter instrument flight (part 29, Appendix B) envelope.
(ii) A means to prevent unintended flight below a safe minimum height.
(4) The AFCS sub-mode system architecture should support the following functionalities:
(i) A system for limiting the engine power demanded by the AFCS when any of the automatic piloting modes are engaged, so that FADEC power limitations, such as torque and temperature, are not exceeded.
(ii) If applicable, a system providing the aircraft height above the surface and final pilot-selected height at a location on the instrument panel in a position acceptable to the FAA that will make it plainly visible to and usable by any pilot at their station.
(iii) A system providing the aircraft heading and the pilot-selected heading at a location on the instrument panel in a position acceptable to the FAA that will make it plainly visible to and usable by any pilot at their station.
(iv) If applicable, a system providing the aircraft longitudinal and lateral ground speeds and the pilot-selected longitudinal and lateral ground speeds when used by the AFCS in the flight envelope where airspeed indications become unreliable. This information must be presented at a location on the instrument panel in a position acceptable to the FAA that is plainly visible to and usable by any pilot at their station.
(v) A system providing wind speed and wind direction when automatic piloting modes are engaged or transitioning from one mode to another.
(vi) A system that monitors for flight guidance deviations and failures with an appropriate alerting function that enables the flight crew to take appropriate corrective action.
(vii) An alerting system that provides visual or aural alerts, or both, to the flight crew when (if applicable) the stored or pilot-selected safe minimum height is reached, when an AFCS malfunction occurs, and when the AFCS changes modes automatically from one AFCS mode to another.
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Note: For normal transitions from one AFCS mode to another, a single visual or aural alert may suffice. For an AFCS mode malfunction or a mode having a timecritical component, the flight crew alerting system must activate early enough to allow the flight crew to take timely and appropriate action. The alerting system means must be designed to alert the flight crew in order to minimize crew errors that could create an additional hazard.
(5) The reliability of the AFCS must be related to the effects of its failure. The occurrence of any failure condition that would prevent continued safe flight and landing must be extremely improbable. For any failure condition of the AFCS , which is not shown to be extremely improbable, the helicopter must be safely controllable and capable of continued safe flight without exceptional piloting skill, alertness, or strength. Additional unrelated probable failures affecting the control system must be evaluated. Additionally, the AFCS must be designed so that it cannot create a hazardous deviation in the flight path or produce hazardous loads on the helicopter during normal operation or in the event of a malfunction or failure, assuming corrective action begins within an appropriate period of time. Where multiple systems are installed, subsequent malfunction conditions must be evaluated in sequence unless their occurrence is shown to be improbable. A functional hazard assessment and a system safety assessment must be provided in accordance with section 29.1309 of this AC to address the failure conditions associated with the AFCS modes. The assessments must consider all systems required for AFCS mode operation, including the AFCS, all associated AFCS sensors (for example, radio altimeter), and primary flight displays. Electrical and electronic systems with catastrophic failure conditions (for example, AFCS) must comply with the § 29.1317(a)(4) High Intensity Radiated Field requirements.
(6) The AFCS modes must be demonstrated in the requested flight envelope.
(7) For any single failure or any combination of failures of the AFCS that is not shown to be extremely improbable, the recovery must not result in a loss of height greater than half of the minimum use height.
(8) For coupled flight below the previous VMINI, at the maximum demonstrated winds, the helicopter must be able to maintain any required flight condition and make a smooth transition from any flight condition to any other flight condition without requiring exceptional piloting skill, alertness, or strength, and without exceeding the limit load factor.
(9) For coupled flight below the previous VMINI, the following requirements of Appendix B to part 29 must be met and will be used as an extension to the IFR certification envelope of the basic aircraft:
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AC 29-2C, Chg 7 2/4/2016
(i) Static Longitudinal Stability: The requirements of Appendix B to part 27, paragraph IV are not applicable.
(ii) Static Lateral-Directional Stability: The requirements of Appendix B to part 27, paragraph V are not applicable.
(iii) Dynamic Stability: In lieu of the requirements of Appendix B to part 29, paragraph VI, the following apply:
(A) Any oscillation must be damped and any aperiodic response must not double in amplitude in less than 10 seconds. This requirement must also be met with degraded upper mode(s) of the AFCS.
(B) After any upset, such as a wind gust, the AFCS must return the aircraft to the last commanded position within 10 seconds or less.
(10) With any of the upper mode(s) of the AFCS engaged, the pilot must be able to manually recover the aircraft and transition to the normal (Appendix B to part 29) IFR flight profile envelope without exceptional skill, alertness, or strength.
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15 I L 10 I
UNACCEPTABLE 5 -0.3 -0.2 -0.1 I' ' 0
DAMPING RATIO
ACCEPTABLE
0.05 0.1 0.15 2/4/2016 AC 29-2C, Chg 7 FIGURE AC 29 APX B-1 ROTORCRAFT DYNAMIC STABILITY
REQUIREMENTS FOR IFR Page Apdx B - 27
AC 29 APPENDIX B (AMENDMENT 29-59) AIRWORTHINESS GUIDANCE FOR ROTORCRAFT INSTRUMENT FLIGHT.
a. Explanation.
(3) Amendment 29-59 revised section VIII (b)(5)(i), which requires isolating the pilot instrument system from any other operating systems, to only apply to pneumatic systems. This change allows other types of pilot instrument systems to be connected to other systems on the rotorcraft and allows the use of modern technology to monitor and display highly integrated information. This guidance remains unchanged except paragraphs (b)(9)(v) and (b)(9)(vi) of this AC section do not apply to non-pneumatic systems.
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