Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 18365

Authority of CDCs To Perform years of substantive, decision-making DEPARTMENT OF TRANSPORTATION Liquidation and Debt Collection experience in administering the Litigation liquidation and workout of defaulted or Federal Aviation Administration I 28. Add § 120.975 to read as follows: problem loans secured in a manner substantially similar to loans funded 14 CFR Part 25 § 120.975 CDC Liquidation of loans and with 504 loan program debentures, and [Docket No. NM370; Special Conditions No. debt collection litigation. who have completed a training program 25–349–SC] (a) PCLP CDCs. If a CDC is designated on loan liquidation developed by the as a PCLP CDC under § 120.845, the Agency in conjunction with qualified Special Conditions: CDC must liquidate and handle debt CDCs that meet the requirements of this Model Falcon 7X Airplane; Side Stick collection litigation with respect to all section; or Controllers, Electronic Flight Control PCLP Loans in its portfolio on behalf of System: Lateral-Directional and SBA as required by § 120.848(f), in (ii) The CDC has entered into a Longitudinal Stability, Low Energy accordance with subpart E of this part. contract with a qualified third party for Awareness, Flight Control Surface With respect to all other 504 loans that the performance of its liquidation Position Awareness, and Flight a PCLP CDC makes, the PCLP CDC is an responsibilities and obtains the Characteristics Compliance Via the Authorized CDC Liquidator and must approval of SBA with respect to the Handling Qualities Rating Method; exercise its delegated authority to qualifications of the contractor and the Flight Envelope Protection: General liquidate and handle debt-collection terms and conditions of the contract. Limiting Requirements, High Incidence litigation in accordance with subpart E (c) CDC counsel. To perform debt Protection Function, Normal Load of this part for such loans, if the PCLP collection litigation under paragraphs Factor (g) Limiting, and Pitch, Roll, and CDC is notified by SBA that it meets (a) or (b) of this section, a CDC must also High Speed Limiting Functions either of the following requirements to have either in-house counsel with be an Authorized CDC Liquidator, as AGENCY: Federal Aviation adequate experience as approved by determined by SBA: Administration (FAA), DOT. SBA or entered into a contract for the (1) The PCLP CDC has one or more ACTION: Final special conditions. employees who have not less than two performance of debt collection litigation years of substantive, decision-making with an experienced attorney or law SUMMARY: These special conditions are experience in administering the firm as approved by SBA. issued for the Dassault Aviation Model liquidation and workout of defaulted or (d) Application for authority to Falcon 7X airplane. This airplane will problem loans secured in a manner liquidate and litigate. To seek authority have novel or unusual design features substantially similar to loans funded to perform liquidation and debt when compared to the state of with 504 loan program debentures, and collection litigation under paragraphs technology envisioned in the who have completed a training program (b) and (c) of this section, a CDC other airworthiness standards for transport on loan liquidation developed by the than a PCLP CDC must submit a written category airplanes. These design features include side stick controllers, Agency in conjunction with qualified application to SBA and include electronic flight control systems, and CDCs that meet the requirements of this documentation demonstrating that the section; or flight envelope protections. These CDC meets the requirements of (2) The PCLP CDC has entered into a special conditions pertain to control and contract with a qualified third party for paragraph (b) and (c) of this section. If handling qualities of the airplane and the performance of its liquidation a CDC intends to use a contractor to protection limits within the normal responsibilities and obtains the perform liquidation, it must obtain flight envelope. The applicable approval of SBA with respect to the approval from SBA of both the airworthiness regulations do not contain qualifications of the contractor and the qualifications of the contractor and the adequate or appropriate safety standards terms and conditions of the contract. terms and conditions in the contract for these design features. These special (b) All other CDCs. A CDC that is not covering the CDC’s retention of the conditions contain the additional safety authorized under paragraph (a) of this contractor. SBA will notify a CDC in standards that the Administrator section may apply to become an writing when the CDC can begin to considers necessary to establish a level Authorized CDC Liquidator with perform liquidation and/or debt of safety equivalent to that established authority to liquidate and handle debt collection litigation under this section. by the existing airworthiness standards. collection litigation with respect to 504 Dated: April 9, 2007. EFFECTIVE DATE: April 4, 2007. loans on behalf of SBA, in accordance FOR FURTHER INFORMATION CONTACT: Joe with subpart E of this part, if the CDC Steven C. Preston, Jacobsen, FAA, Airplane and Flight meets the following requirements: Administrator. Crew Interface Branch, ANM–111, (1) The CDC meets either of the [FR Doc. E7–6946 Filed 4–11–07; 8:45 am] Transport Airplane Directorate, Aircraft following criteria: BILLING CODE 8025–01–P (i) The CDC participated in the loan Certification Service, 1601 Lind Avenue liquidation pilot program established by SW., Renton, Washington 98057–3356; the Small Business Programs telephone (425) 227–2011; facsimile Improvement Act of 1996 prior to (425) 227–1149. October 1, 2006; or SUPPLEMENTARY INFORMATION: (ii) During the three fiscal years Background immediately prior to seeking such authority, the CDC made an average of On June 4, 2002, Dassault Aviation, 9 not less than ten 504 loans per year; and rond Point des Champs Elysees, 75008, (2) The CDC meets either of the Paris, , applied for FAA type following requirements: certificate for its new Model Falcon 7X (i) The CDC has one or more airplane. The Dassault Model Falcon 7X employees who have not less than two airplane is a 19 passenger transport

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category airplane powered by three aft • Electronic flight control system: and simulator tests to have suitable mounted Pratt & Whitney PW307A high flight control surface position handling and control characteristics. engines. awareness, Special Condition No. 2. Electronic Maximum takeoff weight will be 63,700 • Electronic flight control system: Flight Control System: Lateral- pounds, and maximum certified altitude flight characteristics compliance via the Directional Stability, Longitudinal will be 51,000 feet with a range of 5,700 handling qualities rating method Stability, and Low Energy Awareness nautical miles. The airplane is operated (HQRM); using a fly-by-wire (FBW) primary flight • Flight envelope protection: general In lieu of compliance with the control system. This will be the first limiting requirements, regulations pertaining to lateral- application of a FBW primary flight • Flight envelope protection: high directional and longitudinal stability, control system in an airplane primarily incidence protection function, these special conditions ensure that the intended for private/corporate use. • Flight envelope protection: normal Model Falcon 7X will have suitable The Dassault Aviation Model Falcon load factor (g) limiting, airplane handling qualities throughout 7X design incorporates equipment that • Flight envelope protection: pitch, the normal flight envelope. was not envisioned when part 25 was roll, and high speed limiting functions. The unique features of the Model created. This equipment includes side Because of these rapid improvements in Falcon 7X flight control system and side stick controllers, and an electronic flight airplane technology, the applicable stick controllers, when compared with control system that provides flight airworthiness regulations do not contain conventional airplanes with wheel and envelope protection. Therefore, special adequate or appropriate safety standards column controllers, do not provide conditions are required that provide the for these design features. These special conventional awareness to the level of safety equivalent to that conditions address equipment which flightcrew of a change in speed or a established by the regulations. may affect the airplane’s structural change in the direction of flight. These special conditions require that adequate Type Certification Basis performance, either directly or as a result of failure or malfunction. These awareness be provided to the pilot of a Under the provisions of 14 CFR 21.17, special conditions are identical or low energy state (low speed, low thrust, Dassault Aviation must show that the nearly identical to those previously and low altitude) below normal Model Falcon 7X airplane meets the required for type certification of other operating speeds. applicable provisions of 14 CFR part 25, airplane models. a. Lateral-Directional Static Stability: as amended by Amendments 25–1 The electronic flight control system through 25–108. Discussion (EFCS) on the Falcon 7X contains fly- If the Administrator finds that the Because of these rapid improvements by-wire control laws that result in applicable airworthiness regulations do in airplane technology, the applicable neutral lateral-directional static not contain adequate or appropriate airworthiness regulations do not contain stability. Therefore, the conventional safety standards for the Model Falcon adequate or appropriate safety standards requirements of the regulations are not 7X airplane because of novel or unusual for these design features. Therefore, in met. design features, special conditions are addition to the requirements of part 25, The Model Falcon 7X airplane has a prescribed under the provisions of subparts C and D, the following special flight control design feature within the § 21.16. conditions apply. normal operational envelope in which In addition to the applicable side stick deflection in the roll axis airworthiness regulations and special Special Condition No. 1. Side Stick commands roll rate. As a result, the conditions, the Dassault Model Falcon Controllers stick force in the roll axis will be zero 7X airplane must comply with the fuel The Falcon 7X will use side stick (neutral stability) during the straight, vent and exhaust emission requirements controllers for pitch and roll control. steady sideslip flight maneuver of of 14 CFR part 34 and the noise Regulatory requirements for § 25.177(c) and will not be certification requirements of 14 CFR conventional wheel and column ‘‘substantially proportional to the angle part 36. controllers, such as requirements of sideslip,’’ as required by the The FAA issues special conditions, as pertaining to pilot strength and regulation. defined in § 11.19, under § 11.38, and controllability, are not directly With conventional control system they become part of the type applicable to side stick controllers. requirements, positive static directional certification basis under § 21.17(a)(2). Certain ergonomic considerations such stability is defined as the tendency to Special conditions are initially as armrest support, freedom of arm recover from a skid with the rudder free. applicable to the model for which they movement, controller displacement, Positive static lateral stability is defined are issued. Should the type certificate handgrip size and accommodations for as the tendency to raise the low wing in for that model be amended later to a range of pilot sizes are not addressed a sideslip with the aileron controls free. include any other model that in the regulations. In addition, pilot These special conditions are intended to incorporates the same novel or unusual control authority may be uncertain, accomplish the following: design features, these special conditions because the side sticks are not • Provide additional cues of would also apply to the other model mechanically interconnected as with inadvertent sideslips and skids through under § 21.101. conventional wheel and column control force changes. controls. Pitch and roll control force and • Ensure that short periods of Novel or Unusual Design Features displacement sensitivity must be unattended operation do not result in The 7X airplane will compatible, so that normal inputs on any significant changes in yaw or bank incorporate the following novel or one control axis will not cause angle. unusual design features: significant unintentional inputs on the • Provide predictable roll and yaw • Side stick controllers; other. response. • Electronic flight control system: These special conditions require that • Provide acceptable level of pilot lateral-directional and longitudinal the unique features of the side stick attention (i.e., workload) to attain and stability, low energy awareness, must be demonstrated through flight maintain a coordinated turn.

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b. Longitudinal Static Stability: The energy state (low speed and thrust at between needed crew awareness and longitudinal flight control laws for the low altitude). Past experience on nuisance warnings. Falcon 7X provide neutral static airplanes fitted with a flight control Special Condition No. 4. Electronic stability within the normal operational system which provides neutral Flight Control System: Flight envelope. Therefore, it is inappropriate longitudinal stability shows there are Characteristics Compliance Via the to require the airplane design to comply insufficient feedback cues to the pilot of Handling Qualities Rating Method with the static longitudinal stability excursion below normal operational (HQRM) requirements of §§ 25.171, 25.173, and speeds. The maximum angle of attack 25.175. protection system limits the airplane The Model Falcon 7X airplane will Static longitudinal stability on angle of attack and prevents stall during have an electronic flight control system conventional airplanes with mechanical normal operating speeds, but this (EFCS). This system provides an links to the pitch control surface means system is not sufficient to prevent stall electronic interface between the pilot’s that a pull force on the controller will at low speed excursions below normal flight controls and the flight control result in a reduction in speed relative to operational speeds. Until intervention, surfaces (for both normal and failure the trim speed, and a push force will there are no stability cues because the states). The system also generates the result in higher than trim speed. airplane remains trimmed. Additionally, actual surface commands that provide Longitudinal stability is required by the feedback from the pitching moment due for stability augmentation and control regulations for the following reasons: to thrust variation is reduced by the about all three airplane axes. Because • Speed change cues are provided to flight control laws. Recovery from a low EFCS technology has outpaced existing the pilot through increased and speed excursion may become hazardous regulations-written essentially for decreased forces on the controller. when the low speed is associated with unaugmented airplanes with provision • Short periods of unattended control low altitude and the engines are for limited ON/OFF augmentation- of the airplane do not result in operating at low thrust or with other suitable special conditions and a significant changes in attitude, airspeed, performance limiting conditions. method of compliance are required to or load factor. Because § 25.173 requires that the aid in the certification of flight • A predictable pitch response is pilot receive speed change cues through characteristics. provided to the pilot. increased or decreased forces on the These special conditions and the • An acceptable level of pilot controller, it would be inappropriate to method of compliance presented in attention (i.e., workload) to attain and apply those requirements for feedback Appendix 7, FAA Handling Qualities maintain trim speed and altitude is cues to the Falcon Model 7X systems. Rating Method, of AC 25–7A, Flight provided to the pilot. These special conditions require that Test Guide Certification of Transport • Longitudinal stability provides gust the airplane provide adequate Category Airplanes, provide a means to stability. awareness of a low energy state to the evaluate flight characteristics—for The pitch control movement of the pilot. example, ‘‘satisfactory,’’ ‘‘adequate,’’ or side stick is a normal load factor or ‘‘g’’ ‘‘controllable’’—to determine Special Condition No. 3. Electronic command which results in an initial compliance with the regulations. The Flight Control System: Flight Control movement of the elevator surface to HQRM in Appendix 7 was developed Surface Position Awareness attain the commanded load factor. That for airplanes with control systems movement is followed by integrated With a response-command type of having similar functions and is movement of the stabilizer and elevator flight control system and no direct employed to aid in the evaluation of the to automatically trim the airplane to a mechanical coupling from cockpit following: neutral (1g) stick-free stability. The controller to control surface, the • All EFCS/airplane failure states not flight path commanded by the initial controller does not provide the Falcon shown to be extremely improbable and side stick input will remain stick-free 7X pilot with an awareness of the actual where the envelope (task) and until the pilot gives another command. surface deflection position during flight atmospheric disturbance probabilities This control function is applied during maneuvers. Some unusual flight are each 1. ‘‘normal’’ control law within the speed conditions, arising from atmospheric • All combinations of failures, range from the speed at the angle of conditions or airplane or engine failures atmospheric disturbance level, and attack protection limit to initiation of or both, may result in full or nearly full flight envelope not shown to be the angle of attack protection limit. surface deflection. Unless the flightcrew extremely improbable. Once outside this speed range, the is made aware of excessive deflection or • Any other flight condition or control laws introduce the conventional impending control surface deflection characteristic where 14 CFR part 25 longitudinal static stability as described limiting, the pilot or auto-flight system proves to be inadequate for proper above. may encounter situations where loss of assessment of unique Falcon Model 7X As a result of neutral static stability, control or other unsafe handling or flight characteristics. the Falcon 7X does not meet the part 25 performance characteristics occur. The Handling Qualities Rating requirements for static longitudinal These special conditions require that Method provides a systematic approach stability. It would not be appropriate to suitable annunciation be provided to the to the assessment of handling qualities. apply the conventional part 25 flightcrew when a flight condition exists It is not intended to dictate program size requirements for static longitudinal in which nearly full control surface or need for a fixed number of pilots to stability to the unconventional control deflection occurs. Suitability of such a achieve multiple opinions. The airplane systems of the Falcon 7X. These special display must take into account that design itself and success in defining conditions require that the airplane be some pilot-demanded maneuvers (e.g., critical failure combinations from the shown to have suitable static rapid roll) are necessarily associated many reviewed in Systems Safety longitudinal stability in any condition with intended full or nearly full control Assessments dictate the scope of any normally encountered in service. surface deflection. Therefore, simple HQRM application. c. Low Energy Awareness: Static alerting systems which function in both Handling qualities terms, principles, longitudinal stability provides an intended or unexpected control-limiting and relationships familiar to the awareness to the flightcrew of a low situations must be properly balanced aviation community have been used to

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formulate the HQRM. For example, we These special conditions define a minimum load factor requirements to have established that the well-known minimum steady flight speed, VMIN, to ensure adequate maneuver capability COOPER–HARPER rating scale and the be demonstrated during flight test, at during normal flight. Other limiting FAA three-part rating system are which the airplane can develop lift features of the normal load factor similar. This approach on the flying normal to the flight path and equal to limiting function, as discussed above, qualities of highly augmented/ relaxed its weight at the angle of attack limit of that affect the upper load limits are not static stability airplanes in relation to the protection function. It further addressed in these special conditions. regulatory and flight test guide defines procedures for establishing the The phrase ‘‘in the absence of other requirements is reported in DOT/FAA/ reference stall speed, VSR, to be used for limiting factors’’ has been added relative CT–82/130, Flying Qualities of Relaxed defining reference speeds during takeoff to past similar special conditions to Static Stability Aircraft, Volumes I and and landing. clarify that while the main focus is on II. In the absence of specific regulations the lower load factor limits, there are in 14 CFR part 25, these special other limiting factors that must be Special Condition No. 5. Flight conditions present High Incidence considered in the load limiting function. Envelope Protection: General Limiting Protection Function requirements for Requirements the capability and reliability of the Special Condition No. 8. Flight These special conditions and the function, stall warning with a failure Envelope Protection: Pitch, Roll, and following ones-pertaining to flight condition, handling qualities and High Speed Limiting Functions envelope protection-present general characteristics at high incidence or The Model Falcon 7X will incorporate limiting requirements for all the unique angle of attack flight maneuvers, and pitch attitude and high speed limiting flight envelope protection features of the specific applications of the newly functions via the Electronic Flight basic Model Falcon 7X Electronic Flight defined VMIN in lieu of current Control System (EFCS) normal operating Control System (EFCS) design. Current regulations. mode. In addition, positive spiral regulations do not address these types of stability and partial pitch compensation Special Condition No. 7. Flight protection features. The general limiting will be introduced in the lateral and Envelope Protection: Normal Load requirements are necessary to ensure a pitch axes through the control laws for Factor (G) Limiting smooth transition from normal flight to bank angles greater than 35 degrees. the protection mode and adequate The Falcon 7X flight control system The purpose of the pitch attitude maneuver capability. The general design incorporates a normal load factor limiting function, in conjunction with limiting requirements also ensure that limiting function on a full time basis the high incidence protection function, the structural limits of the airplane are that will prevent the pilot from is to prevent airplane stall during low not exceeded. Furthermore, failure of inadvertently or intentionally exceeding speed, high angle of attack excursions. the protection feature must not create the positive or negative airplane limit The high speed limiting protection hazardous flight conditions. Envelope load factor. This limiting feature is function prevents the pilot from protection parameters include angle of active in the normal flight control mode inadvertently or intentionally exceeding attack, normal load factor, pitch angle, and cannot be overridden by the pilot. the airplane maximum design speeds, and speed. To accomplish these There is no requirement in the VD/MD. Part 25 does not address such a envelope protections, one or more regulations for this limiting feature. function that would limit or modify significant changes occur in the EFCS This normal load factor limit is flying qualities in the high speed region. control laws as the normal flight unique in that traditional airplanes with There are no specific hard limits on envelope limit is approached or conventional flight control systems the Falcon 7X for bank angle. At bank exceeded. (mechanical linkages) are limited in the angles up to 35 degrees, side movement Each specific type of envelope pitch axis only by the elevator surface of the controller commands roll rate protection is addressed individually in area and deflection limit. The elevator depending on the amount of deflection. the special conditions that follow. control power is normally derived for Bank angle is immediately adequate controllability and Special Condition No. 6. Flight accomplished by the control law maneuverability at the most critical Envelope Protection-High Incidence function and deflection of the control longitudinal pitching moment. The Protection Function surfaces. With the stick released to its result is that traditional airplanes have neutral point, the airplane will maintain The Falcon 7X is equipped with a a significant portion of the flight the commanded bank angle (neutral high incidence protection function that envelope in which maneuverability in spiral stability). Positive spiral stability limits the angle of attack at which the excess of limit structural design values is introduced at and above 35 degrees airplane can be flown during normal is possible. band angle such that a stick force is low speed operation and that cannot be Part 25 does not require a required to maintain bank angle, and overridden by the flightcrew. This demonstration of maneuver control or releasing the stick will return the function prevents the airplane from handling qualities beyond the design airplane to 35 degrees. stalling and therefore, the stall warning limit structural loads. Nevertheless, In addition to the requirements of system is not needed during normal some pilots have become accustomed to § 25.143, this special condition flight conditions. If there is a failure of the availability of this excess maneuver establishes requirements to ensure that the high incidence protection function capacity in case of extreme emergency, pitch and high speed limiting functions that is not shown to be extremely such as upset recoveries or collision do not impede normal maneuvering and improbable, the flight characteristics at avoidance. that pitch and roll limiting functions do the angle of attack for CLMAX must be Because Dassault has chosen to not restrict or prevent attaining bank suitable in the traditional sense, and include this optional design feature on angles necessary for emergency stall warning must be provided in a the Falcon 7X, for which part 25 does maneuvering. conventional manner. These special not contain adequate or appropriate conditions address these and other safety standards, special conditions Discussion of Comments unique features of this function on the pertaining to this feature are included. Notice of proposed special conditions Model Falcon 7X. These special conditions establish No. 25–07–06–SC for the Dassault

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Aviation Model Falcon 7X airplanes b. Pilot control authority: The rudder control movements and forces was published in the Federal Register electronic side stick controller coupling must be substantially proportional to on February 26, 2007 (72 FR 8296). No design must provide for corrective and/ the angle of sideslip, and the factor of comments were received, and the or overriding control inputs by either proportionality must be between limits special conditions are adopted as pilot with no unsafe characteristics. found necessary for safe operation proposed. Annunciation of the controller status throughout the range of sideslip angles must be provided, and must not be appropriate to the operation of the Applicability confusing to the flightcrew. airplane. At greater angles—up to the As discussed above, these special c. Pilot control: It must be shown by angle at which full rudder control is conditions are applicable to the Dassault flight tests that the use of side stick used or a rudder pedal force of 180 Aviation Model Falcon 7X airplanes. controllers does not produce unsuitable pounds (81.72 kg) is obtained—the Should Dassault Aviation apply at a pilot-in-the-loop control characteristics rudder pedal forces may not reverse, later date for a change to the type when considering precision path and increased rudder deflection must certificate to include another model on control/tasks and turbulence. In produce increased angles of sideslip. the same type certificate incorporating addition, pitch and roll control force Unless the airplane has a suitable the same novel or unusual design and displacement sensitivity must be sideslip indication, there must be features, these special conditions would compatible, so that normal inputs on enough bank and lateral control apply to that model as well. one control axis will not cause deflection and force accompanying significant unintentional inputs on the sideslipping to clearly indicate any For Final Special Conditions Effective other. departure from steady, unyawed flight. Upon Issuance d. quick-release control 3. Electronic Flight Control System: Under standard practice, the effective location: In lieu of compliance with § 25.1329(d), autopilot quick release Flight Control Surface Position date of final special conditions would Awareness be 30 days after the date of publication (emergency) controls must be on both in the Federal Register; however, as the side stick controllers. The quick release In addition to the requirements of certification date for the Dassault means must be located so that it can §§ 25.143, 25.671 and 25.672, the Aviation Model Falcon 7X airplanes is readily and easily be used by the following special conditions apply: imminent, the FAA finds that good flightcrew. a. A suitable flight control position annunciation must be provided to the cause exists to make these special 2. Electronic Flight Control System: conditions effective upon issuance. crew in the following situation: Lateral-Directional and Longitudinal A flight condition exists in which— Conclusion Stability, and Low Energy Awareness without being commanded by the This action affects only certain novel In lieu of the requirements of crew—control surfaces are coming so or unusual design features on model §§ 25.171, 25.173, 25.175, and 25.177(c), close to their limits that return to Falcon 7X airplanes. It is not a rule of the following special conditions apply: normal flight and (or) continuation of general applicability. a. The airplane must be shown to safe flight requires a specific crew have suitable static lateral, directional, action. List of Subjects in 14 CFR Part 25 and longitudinal stability in any b. In lieu of control position Aircraft, Aviation safety, Reporting condition normally encountered in annunciation, existing indications to the and recordkeeping requirements. service, including the effects of crew may be used to prompt crew atmospheric disturbance. The showing action, if they are found to be adequate. The authority citation for these of suitable static lateral, directional and Note: The term ‘‘suitable’’ also indicates an special conditions is as follows: longitudinal stability must be based on appropriate balance between nuisance and Authority: 49 U.S.C. 106(g), 40113, 44701, the airplane handling qualities, necessary operation. 44702, 44704. including pilot workload and pilot 4. Electronic Flight Control System: The Special Conditions compensation, for specific test procedures during the flight test Flight Characteristics Compliance Via Accordingly, pursuant to the evaluations. the Handling Quantities Rating Method authority delegated to me by the b. The airplane must provide (HQRM) Administrator, the following special adequate awareness to the pilot of a low a. Flight characteristics compliance conditions are issued as part of the type energy (low speed/low thrust/low determination for electronic flight certification basis for Dassault Aviation height) state when fitted with flight control system (EFCS) Failure Cases: Model Falcon 7X airplanes. control laws presenting neutral In lieu of compliance with § 25.672(c), 1. Side Stick Controllers longitudinal stability significantly the HQRM contained in Appendix 7, below the normal operating speeds. FAA Handling Qualities Rating Method, In the absence of specific ‘‘Adequate awareness’’ means warning of the Flight Test Guide for Certification requirements for side stick controllers, information must be provided to alert of Transport Category Airplanes, AC 25– the following special conditions apply: the crew of unsafe operating conditions 7A (or an equivalent method of a. Pilot strength: In lieu of the and to enable them to take appropriate compliance found acceptable to the ‘‘strength of pilots’’ limits shown in corrective action. FAA), must be used for evaluation of § 25.143(c) for pitch and roll, and in lieu c. The static directional stability—as EFCS configurations resulting from of the specific pitch force requirements shown by the tendency to recover from single and multiple failures not shown of §§ 25.145(b) and 25.175(d), it must be a skid with the rudder free—must be to be extremely improbable. shown that the temporary and positive for any and flap The handling qualities ratings are: maximum prolonged force levels for the position and symmetrical power (1) Satisfactory: Full performance side stick controllers are suitable for all condition, at speeds from 1.13 VSR1 up criteria can be met with routine pilot expected operating conditions and to VFE, VLE, or VFC/MFC (as appropriate). effort and attention. configurations, whether normal or non- d. In straight, steady sideslips (2) Adequate: Adequate for continued normal. (unaccelerated forward slips), the safe flight and landing; full or specified

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reduced performance can be met, but (3) The airplane must be responsive to environmental conditions such as with heightened pilot effort and intentional dynamic maneuvering to windshears and gusts at low speeds, as attention. within a suitable range of the parameter required by paragraph g, Atmospheric (3) Controllable: Inadequate for limit. Dynamic characteristics, such as Disturbances, below. continued safe flight and landing, but damping and overshoot, must also be (3) The ability of the high incidence controllable for return to a safe flight appropriate for the flight maneuver and protection function to accommodate any condition, safe flight envelope and/or limit parameter in question. reduction in stalling incidence resulting reconfiguration, so that the handling (4) When simultaneous envelope from residual ice must be verified. qualities are at least Adequate. limiting is engaged, adverse coupling or (4) The reliability of the function and b. Handling qualities will be allowed adverse priority must not result. the effects of failures must be to progressively degrade with failure b. Failure States: EFCS failures, acceptable, in accordance with state, atmospheric disturbance level, including sensor failures, must not § 25.1309 and Advisory Circular and flight envelope, as shown in Figure result in a condition where a parameter 25.1309–1A, System Design and 12, ‘‘Minimum HQ Requirements,’’ of is limited to such a reduced value that Analysis. Appendix 7. Specifically, for probable safe and controllable maneuvering is no (5) The high incidence protection failure conditions within the normal longer available. The crew must be function must not impede normal flight envelope, the pilot-rated handling alerted by suitable means, if any change maneuvering for pitch angles up to the qualities must be satisfactory in light in envelope limiting or maneuverability maximum required for normal atmospheric disturbance and adequate is produced by single or multiple maneuvering, including a normal all- in moderate atmospheric disturbance. failures of the EFCS not shown to be engines operating takeoff plus a suitable The handling qualities rating must not extremely improbable. margin to allow for satisfactory speed be less than adequate in light 6. Flight Envelope Protection: High control. atmospheric disturbance for improbable Incidence Protection Function c. Minimum Steady Flight Speed and failures. Reference Stall Speed. In lieu of the a. Definitions. For the purpose of this Note: AC 25–7A, Appendix 7 presents a requirements of § 25.103, the following method of compliance and provides guidance special condition, the following special conditions apply: for the following: definitions apply: (1) VMIN: The minimum steady flight • Minimum handling qualities rating Electronic Flight Control System speed, for the airplane configuration requirements in conjunction with (EFCS): The electronic and software under consideration and with the high atmospheric disturbance levels, flight command and control elements of the incidence protection function operating, envelopes, and failure conditions (Figure 12), flight control system. is the final stabilized calibrated airspeed • Flight Envelope definition (Figures 5A, 6 High Incidence Protection Function: and 7), obtained when the airplane is • An airplane level function that decelerated at an entry rate not Atmospheric Disturbance Levels (Figure automatically limits the maximum angle 5B), exceeding 1 knot per second until the • Flight Control System Failure State of attack that can be attained to a value longitudinal pilot control is on its stop. (Figure 5C), below that at which an aerodynamic (2) The minimum steady flight speed, • stall would occur. Combination Guidelines (Figures 5D, 9 VMIN, must be determined with: and 10), and Alpha Limit: The maximum angle of (a) The high incidence protection • General flight task list, from which attack at which the airplane stabilizes function operating normally. appropriate specific tasks can be selected or with the high incidence protection (b) Idle thrust. developed (Figure 11). function operating and the longitudinal (c) All combinations of flap settings control held on its aft stop. and landing gear positions. 5. Flight Envelope Protection: General VMIN: The minimum steady flight (d) The weight used when V is Limiting Requirements speed is the stabilized, calibrated SR being used as a factor to determine airspeed obtained when the airplane is a. General Requirements. compliance with a required decelerated at an entry rate not (1) Onset characteristics of each performance standard. exceeding 1 knot per second, until the envelope protection function must be (e) The most unfavorable center of longitudinal pilot control is on its stop smooth, appropriate to the phase of gravity allowable, and with the high incidence protection flight and type of maneuver, and not in (f) The airplane trimmed for straight function operating. conflict with the ability of the pilot to flight at a speed achievable by the VMIN1g: V corrected to 1g satisfactorily change the airplane flight MIN automatic trim system. conditions. It is the minimum calibrated path, speed, or attitude, as needed. (3) V is V corrected to 1g (2) Limit values of protected flight airspeed at which the airplane can MIN1g MIN conditions. V is the minimum parameters (and if applicable, associated develop a lift force normal to the flight MIN1g calibrated airspeed at which the warning thresholds) must be compatible path and equal to its weight when at an airplane can develop a lift force normal with the following: angle of attack not greater than that to the flight path and equal to its weight (a) Airplane structural limits, determined for VMIN. (b) Required safe and controllable b. Capability and Reliability of the when at an angle of attack not greater maneuvering of the airplane, and High Incidence Protection Function than that determined for VMIN. VMIN1g is (c) Margins to critical conditions. (1) It must not be possible to defined as follows: Dynamic maneuvering, airframe and encounter a stall during pilot induced V system tolerances (both manufacturing maneuvers, and handling characteristics V = MIN and in-service), and non-steady must be acceptable, as required by MIN1 g nzw atmospheric conditions—in any paragraphs e and f below, titled High appropriate combination and phase of Incidence Handling Demonstrations and Where— flight—must not result in a limited High Incidence Handling Characteristics nzw = load factor normal to the flight path at flight parameter beyond the nominal respectively. VMIN design limit value that would cause (2) The airplane must be protected (4) The Reference Stall Speed, VSR, is unsafe flight characteristics. against stalling due to the effects of a calibrated airspeed selected by the

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applicant. VSR may not be less than the VMIN1g, an equivalent safety finding to (6) The airplane trimmed for straight 1g stall speed. VSR is expressed as: the intent of § 25.103 may be considered flight at a speed achievable by the to have been met. The applicant may automatic trim system. V choose VSR to be less than VMIN1g but f. High Incidence Handling ≥=CLMAX VVSR S1 g not less than VS1g if compensating Characteristics. In lieu of the nzw factors are provided to ensure safe requirements of § 25.203, the following Where— characteristics. special conditions apply: d. Stall Warning. VCLMAX = Calibrated airspeed obtained when (1) In demonstrating the handling the load factor-corrected lift coefficient (1) Normal Operation. If the characteristics specified in paragraphs conditions of paragraph b, Capability (2), (3), (4), and (5) below, the following  nW and Reliability of the High Incidence procedures must be used:  zw  Protection Function, of this special (a) Starting at a speed sufficiently  qS  conditions are satisfied, a level of safety above the minimum steady flight speed is first a maximum during the maneuver equivalent to that intended by § 25.207, to ensure that a steady rate of speed prescribed in paragraph (5)(h) of this Stall Warning, must be considered to reduction can be established, apply the special condition. have been met without provision of an longitudinal control so that the speed nzw = Load factor normal to the flight path additional, unique warning device. reduction does not exceed one knot per at VCLMAX (2) Failure Cases. Following failures second until the control reaches the W = Airplane gross weight of the high incidence protection stop. S = Aerodynamic reference wing area, and function not shown to be extremely q = Dynamic pressure. (b) The longitudinal control must be improbable, if the function no longer maintained at the stop until the airplane (5) VCLMAX must be determined with satisfies paragraph b, Capability and has reached a stabilized flight condition the following conditions: Reliability of the High Incidence and must then be recovered by normal (a) Engines idling or—if that resultant Protection Function, paragraphs b(1), recovery techniques. thrust causes an appreciable decrease in (2), and (3) of this special condition, (c) The requirements for turning flight stall speed—not more than zero thrust at stall warning must be provided in maneuver demonstrations must also be the stall speed accordance with § 25.207. The stall met with accelerated rates of entry to (b) The airplane in other respects, warning should prevent inadvertent the incidence limit, up to the maximum such as flaps and landing gear, in the stall under the following conditions: rate achievable. condition existing in the test or (a) Power off straight stall approaches (2) Throughout maneuvers with a rate performance standard in which VSR is to a speed 5 percent below the warning of deceleration of not more than 1 knot being used. onset. per second, both in straight flight and in (c) The weight used when V is being SR (b) Turning flight stall approaches 30 degree banked turns, the airplane’s used as a factor to determine with at least 1.5g load factor normal to characteristics must be as follows: compliance with a required the flight path at entry rate of at least 2 (a) There must not be any abnormal performance standard. knots per second when recovery is airplane nose-up pitching. (d) The center of gravity position that initiated not less than one second after (b) There must not be any results in the highest value of reference warning onset. uncommanded nose-down pitching that stall speed. e. High Incidence Handling would be indicative of stall. However, (e) The airplane trimmed for straight Demonstrations. In lieu of the reasonable attitude changes associated flight at a speed achievable by the requirements of § 25.201, the following with stabilizing the incidence at alpha automatic trim system, but not less than special conditions apply: limit as the longitudinal control reaches 1.13 VSR and not greater than 1.3 VSR. Maneuvers to the limit of the (f) [Reserved] longitudinal control in the nose up the stop would be acceptable. Any (g) The high incidence protection direction must be demonstrated in reduction of pitch attitude associated function adjusted to a high enough straight flight and in 30 degree banked with stabilizing the incidence at the incidence to allow full development of turns under the following conditions: alpha limit should be achieved the 1g stall. (1) The high incidence protection smoothly and at a low pitch rate, such (h) Starting from the stabilized trim function operating normally. that it is not likely to be mistaken for condition, apply the longitudinal (2) Initial power condition of: natural stall identification. control to decelerate the airplane so that (a) Power off. (c) There must not be any the speed reduction does not exceed one (b) The power necessary to maintain uncommanded lateral or directional knot per second. level flight at 1.5 VSR1, where VSR1 is the motion, and the pilot must retain good (6) The flight characteristics at the reference stall speed with the flaps in lateral and directional control by angle of attack for CLMAX must be the approach position, the landing gear conventional use of the cockpit suitable in the traditional sense at FWD retracted, and the maximum landing controllers throughout the maneuver. and AFT center of gravity in straight weight. The flap position to be used to (d) The airplane must not exhibit and turning flight at IDLE power. determine this power setting is that buffeting of a magnitude and severity Although for a normal production EFCS position in which the stall speed, VSR1, that would act as a deterrent to and steady full aft stick this angle of does not exceed 110% of the stall speed, completing the maneuver. attack for CLMAX cannot be achieved, the VSR0, with the flaps in the most (3) In maneuvers with increased rates angle of attack can be obtained extended landing position. of deceleration, some degradation of momentarily under dynamic (3) [Reserved] characteristics is acceptable, associated circumstances and deliberately in a (4) Flaps, landing gear and with a transient excursion beyond the steady state sense with some EFCS deceleration devices in any likely stabilized alpha-limit. However, the failure conditions. combination of positions. airplane must not exhibit dangerous (7) The reference stall speed, VSR, is (5) Representative weights within the characteristics or characteristics that a calibrated airspeed defined by the range for which certification is would deter the pilot from holding the applicant. If VSR is chosen equal to requested, and longitudinal controller on the stop for a

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period of time appropriate to the a. The positive limiting load factor DEPARTMENT OF TRANSPORTATION maneuvers. must not be less than: (4) It must always be possible to (1) 2.5g for the Electronic Flight Federal Aviation Administration reduce incidence by conventional use of Control System (EFCS) normal state. the controller. (2) 2.0g for the EFCS normal state 14 CFR Part 25 (5) The rate at which the airplane can with the high lift devices extended. be maneuvered from trim speeds [Docket No. NM371; Special Conditions No. b. The negative limiting load factor 25–350–SC] associated with scheduled operating must be equal to or more negative than: speeds, such as V and V , up to 2 REF (1) Minus 1.0g for the EFCS normal Special Conditions: Dassault Aviation alpha-limit must not be unduly damped state. Model Falcon 7X Airplane; Sudden or significantly slower than can be Engine Stoppage, Operation Without achieved on conventionally controlled (2) 0.0g for the EFCS normal state with high lift devices extended. Normal Electrical Power, and Dive transport airplanes. Speed Definition With Speed g. Atmospheric Disturbances. Note: This special condition does not Protection System Operation of the high incidence impose an upper bound for the normal load protection function must not adversely factor limit, nor does it require that the limit AGENCY: Federal Aviation affect aircraft control during expected exist. If the limit is set at a value beyond the Administration (FAA), DOT. levels of atmospheric disturbances or structural design limit maneuvering load factor ‘‘n,’’ indicated in §§ 25.333(b) and ACTION: Final special conditions. impede the application of recovery 25.337(b) and (c), there should be a very SUMMARY: These special conditions are procedures in case of windshear. positive tactile feel built into the controller Simulator tests and analysis may be and obvious to the pilot that serves as a issued for the Dassault Aviation Model used to evaluate such conditions but deterrent to inadvertently exceeding the Falcon 7X Airplane; Sudden Engine must be validated by limited flight structural limit. Stoppage, Operation Without Normal testing to confirm handling qualities at Electrical Power, and Dive Speed critical loading conditions. 8. Flight Envelope Protection: Pitch, Definition with Speed Protection h. [Reserved] Roll, and High Speed Limiting System. This airplane will have novel or i. Proof of Compliance. In addition to Functions unusual design features that include the requirements of § 25.21, the engine size and torque load, which In addition to § 25.143, the following following special conditions apply: affect sudden engine stoppage; electrical The flying qualities must be evaluated special conditions apply: and electronic systems which perform at the most unfavorable center of gravity a. Operation of the high speed limiter critical functions, which affect position. during all routine and descent operation without normal electrical j. Longitudinal Control: procedure flight must not impede power; and dive speed definition with (1) In lieu of the requirements of normal attainment of speeds up to the speed protection system. These special § 25.145(a) and (a)(1), the following overspeed warning. conditions pertain to their effects on the special conditions apply: b. The pitch limiting function must structural performance of the airplane. It must be possible—at any point not impede airplane maneuvering, The applicable airworthiness between the trim speed for straight including an all-engines operating regulations do not contain adequate or flight and Vmin—to pitch the nose takeoff, for pitch angles up to the appropriate safety standards for these downward, so that the acceleration to maximum required for normal design features. These special this selected trim speed is prompt, with: operations plus a suitable margin in the conditions contain the additional safety The airplane trimmed for straight pitch axis to allow for satisfactory speed standards that the Administrator flight at the speed achievable by the control. considers necessary to establish a level automatic trim system and at the most c. The high speed limiting function of safety equivalent to that established unfavorable center of gravity; must not impede normal attainment of by the existing airworthiness standards. (2) In lieu of the requirements of speeds up to VMO/MMO during all EFFECTIVE DATE: April 4, 2007. § 25.145(b)(6), the following special routine and descent procedure flight FOR FURTHER INFORMATION CONTACT: Tom conditions apply: conditions. With power off, flaps extended and Rodriguez, FAA, International Branch, d. The pitch and roll limiting ANM–116, Transport Airplane the airplane trimmed at 1.3 VSR1, obtain functions must not restrict nor prevent Directorate, Aircraft Certification and maintain airspeeds between Vmin attaining bank angles up to 65 degrees Service, 1601 Lind Avenue, SW., and either 1.6 VSR1 or VFE, whichever is and pitch attitudes necessary for Renton, Washington 98057–3356; lower. emergency maneuvering. Positive spiral k. Airspeed Indicating System. (1) In telephone (425) 227–1503; facsimile stability, which is introduced above 35 (425) 227–1320. lieu of the requirements of degrees bank angle, must not require § 25.1323(c)(1), the following special excessive pilot strength on the side stick SUPPLEMENTARY INFORMATION: conditions apply: VMO to Vmin with the controller to achieve bank angles up to Background flaps retracted. 65 degrees. Stick force at bank angles On June 4, 2002, Dassault Aviation, 9 (2) In lieu of the requirements of greater than 35 degrees must not be so rond Point des Champs Elysees, 75008, § 25.1323(c)(2), the following special light that over-control would lead to Paris, France, applied for an FAA type conditions apply: Vmin to VFE with flaps pilot-induced oscillations. in the landing position. certificate for its new Model Falcon 7X Issued in Renton, Washington, on April 4, airplane. The Dassault Model Falcon 7X 7. Flight Envelope Protection: Normal 2007. airplane is a 19 passenger transport Load Factor (g) Limiting Stephen P. Boyd, category airplane powered by three aft In addition to the requirements of Acting Manager, Transport Airplane mounted Pratt & Whitney PW307A high § 25.143(a)—and in the absence of other Directorate, Aircraft Certification Service. bypass ratio turbofan engines. limiting factors—the following special [FR Doc. E7–6888 Filed 4–11–07; 8:45 am] Maximum takeoff weight will be 63,700 conditions apply: BILLING CODE 4910–13–P pounds, and maximum certified altitude

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