Figure/Table No. Title Page 450A-1 Fuel Flow 734 516-1 Additional Cooling Test Point 809 518-1 All-Engine-Critical Altitude Additional Cooling 816 Test Point 589-1 Table of Materials and Gages Acceptable 903 for Fireproof Protective Devices with Flat Surface Geometries 637-1 Deviation Profile 990 637-2 Operational Limitation 992 693-1 Continuous Icing-Temperature vs. Altitude 1064 Limits 693-2 Intermittent Icing-Temperature vs. Altitude 1065 Limits 693-3 Continuous Icing-Liquid Water Content vs 1066 Drop Diameter 693-4 Intermittent Icing-Liquid Water Content vs. 1067 Drop Diameter 775-1 Rotorcraft Dynamic Stability Requirements for 1191 IFR 782-1 Category II Approach Evaluation 1228 782-2 Category II Approach Evaluation (cont.) 1229 785-1 Acceptable Ultimate Load Factor for Agricultural 1237 Dispensing Equipment Design 785-2 Sketch of Tank Pressure Test 1241 786-1 Typical Liquid Oxygen System 1259 XXII
Figure/Table No. Title Page 786-2 Typical Liquid Oxygen System - Using 1260 Combination Valve APX1-1 S-N or P-N Curve Usage A1-15 APX1-2 Crack Growth for Single Element Structure A1-18 APX1-3 Crack Growth for Remaining Elements of A1-20 Multiple Element Structure APX2-1 Installed Engine Fuel Flow Capacity Check A2-9 APX3-1 Estimated Path of Fragments A3-10 APX3-2 Single One-Third Disc Fragment A3-11 APX3-3 Intermediate and Small Pieces of Debris A3-12 APX3-4 Blade Fragment Definition A3-13 APX3-5 Distribution of Translational and Rotational A3-14 Kinetic Energy of Rotor-Component Fragments as a Function of Fragment Size e APX3-6 Cross Section through Aircraft at Plane of A3-15 Rotation of the Engine Disk Fragment XXIII
Abbreviations and Definitions AC advisory circular ACO aircraft certification office ADF automatic direction finding ADI attitude direction indicator AEO all engines operating AFCS automatic flight control systems AGL above ground level AHRS attitude heading reference system Amdt. Amendment APU auxiliary power unit ATC air traffic control BIM blade inspection method CAM cockpit area microphone CAR Civil Air Regulations CAS calibrated air speed CBIM cockpit blade inspection method CDP critical decision point CG center of gravity CPS cycles per second CRFS crash resistant fuel system CRT cathode ray tube CVR cockpit voice recorder DER designated engineering representative DME distance measuring equipment ECAS engine caution advisory systems ECU environmental control unit EFIS electronic flight instrument system EFP engine failure point EHE exhaust heat exchanger ELT emergency locator transmitter EMI electromagnetic interference EMS emergency medical service EOL end of life FAA Federal Aviation Administration FADEC full authority digital engine control FAR Federal Aviation Regulations FMEA failure mode and effects analysis FPM feet per minute FPS feet per second GPS global positioning system HF high frequency HIRF high intensity radiated fields HRD high rate of discharge HUMS health and usage monitoring systems HV height-velocity IAS indicated airspeed ICAO International Civil Aviation Organization ICS inter-communication system IFR instrument flight rules IGE in ground effect IIDS integrated instrument display system ILS instrument landing system IMC instrument meteorological conditions INS inertial navigation system ISA international standard atmosphere ISIS integral spar inspection system ITT inter-turbine temperature KCAS knots calibrated airspeed KIAS knots indicated air speed KTAS knots true airspeed LDP landing decision point LWC liquid water content MCP maximum continuous power MGT measured gas temperature MSL mean sea level MVD median volume diameter NDI non-destructive inspection NM nautical mile NPRM notice of proposed rulemaking NTSB National Transportation Safety Board NG night vision goggles OAT outside air temperature OEl one engine inoperative OGE out of ground effect PBA pitch bias actuator XXIV
7/30/97 PCF post crash fire PIO pilot induced oscillation PSIG pounds per square inch gauge QPL qualified parts list RFM rotorcraft flight manual RFMS rotorcraft flight manual supplement RPM revolutions per minute RTCA Radio Technical Commission of Aeronautics RVR runway visual range SAE Society of Automotive Engineers SAS stability augmentation system SCAS stability and control augmentation systems SRM structural repair manual STC supplemental type certificate STOL short takeoff and landing TBO time between overhaul TC type certificate TCDS type certificate data sheet TDP takeoff decision point TIA type inspection authorization TIR type inspection report TOT turbine outlet temperature TSO: technical standard order TVP true vapor pressure VBIM visual blade inspection method VFR visual flight rules VMC visual meteorological conditions VOR very high frequency omnidirectional range radio VSI vertical speed indicator V/STOL vertical/short takeoff and landing VTOL vertical takeoff and landing WAT weight, altitude, temperature AC 29-2B Altitudes HD density altitude HP pressure altitude V speeds VD diving speed VH speed in level flight with maximum continuous power VMO maximum operating limit speed VNE never-exceed speed VTOSS takeoff safety speed for Category A rotorcraft VX speed for best angle of climb VY speed for best rate of climb MMO maximum operating mach number N speeds NF free turbine speed NG gas generator speed NP power turbine speed NR rotor speed Coefficients CD coefficient of drag CL coefficient of lift CP coefficient of power CT coefficient of thrust XXV
CHAPTER 1. PART 21
CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS (Amendment 21-50)
1.-2. RESERVED.
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3. RESERVED.
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4. § 21.16 SPECIAL CONDITIONS.
a. The Process. Chapter 2, Section 1, Paragraph 8 of the Type Certificate Handbook, Order 8110.4, provides detailed guidance on the special conditions process.
However, much of that material has been outdated with the implementation of the Aircraft Certification Directorate Program. Rotorcraft special conditions are processed through the Rotorcraft Standards Staff, ASW-110. That office will assure coordination with the affected agency and industry elements including the Assistant Chief Counsel.
All comments will be considered and the disposition will be documented by the Rotorcraft Standards Staff. ASW-100 will issue the special conditions.
b. Basis for Development.
(1) Special conditions are justified on the basis of the existing Part 29 being inadequate or inappropriate due to novel or unusual design features of the rotorcraft to be certificated.
(2) The phrase "novel or unusual" as used in § 21.16 is a very relative term. As used hereafter in applying § 21.16 to justify the issuance of special conditions, "novel or unusual" will be taken with respect to the state of technology envisaged by the applicable airworthiness standards of this subchapter. It must be recognized that in some areas which will vary from time to time, the state of the regulations may somewhat lag the state of the art in new design because of the rapidity in which the state of the art is advancing in civil aeronautical design and because of the time required to develop the experience base needed by the FAA/AUTHORITY to proceed with general rulemaking. Applicants for type certification of a new design have the opportunity to mitigate the impact of not knowing the precise airworthiness standards to be applied for "novel or unusual design features" by consulting with the FAA/AUTHORITY early in their certification planning when such features are suspected or known by the applicant to exist. It should also be recognized that, because of the intentional objective nature of the airworthiness standards of this subchapter, many new design features which might be thought of as "novel or unusual" may already be adequately covered by existing regulations, thus obviating the need to issue special conditions.
(3) Before proposing special conditions, the certification staff should very thoroughly analyze the existing regulations and assure they are inadequate or inappropriate in light of a new and novel design feature.
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5.-7. RESERVED.
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8. § 21,31 TYPE DESIGN. The regulatory basis for requiring data to define the design is contained in § 21.31. This section is self-explanatory and broad enough in scope to give the certification staff access to sufficient data to determine compliance with Part 29.
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9.-11. RESERVED.
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12. § 21.33 INSPECTION AND TESTS.
a. Applicant Responsibility. Section 21.33 requires the applicant to:
(1) Assure the test rotorcraft conforms to the type design. This must be accomplished prior to presentation to the FAA/AUTHORITY for testing.
(2) Conduct all inspections and tests necessary to determine compliance with the airworthiness and noise requirements.
b. FAA/AUTHORITY Responsibility.
(1) The design evaluation engineers should assure that the type design is adequate in their technical area and that the inspections and tests to be conducted are appropriate and sufficient to show compliance with Part 29.
(2) As changes to the rotorcraft are made during the test program, the flight test crew should assure that the appropriate design evaluation engineer concurs with the change and the conformity inspection of the change has been conducted.
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7/30/97 АС 29-2B
13.-15. RESERVED.
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