AC 29-2C, Chg 2 4/25/06
CHAPTER 3 - MISCELLANEOUS GUIDANCE (MG), NORMAL CATEGORY ROTORCRAFT
AC 29 MG 1 Certification Procedure for Rotorcraft Avionics Equipment................................MG 1-1 AC 29 MG 2 Standardized Test Procedure for Rotorcraft DC................................................MG 2-1 Electrical System Tests AC 29 MG 3 Rotorcraft and Systems Certification for Category II Operations.......................MG 3-1 AC 29 MG 4 Full Authority Digital Electronic Controls (FADEC) ............................................MG 4-1 AC 29 MG 5 Agricultural Dispensing Equipment Installation .................................................MG 5-1 AC 29 MG 6 Emergency Medical Service (EMS) Systems, Installations, ..............................MG 6-1 Interior Arrangements, and Equipment AC 29 MG 7 Structural Condition Indicators ..........................................................................MG 7-1 AC 29 MG 8 Substantiation of Composite Rotorcraft Structure .............................................MG 8-1 AC 29 MG 9 Rotorcraft One-Engine-Inoperative (OEI) Power Assurance .............................MG 9-1 AC 29 MG 10 Advisory Material for Substantiation of Emergency.........................................MG 10-1 Flotation System AC 29 MG 11 Fatigue Tolerance Evaluation of Transport Category Rotorcraft .....................MG 11-1 Metallic Structure (Including Flaw Tolerance) AC 29 MG 12 External Loads.................................................................................................MG 1 2-1 AC 29 MG 13 Systems Certification Considerations .............................................................MG 13-1 AC 29 MG 14 Certification Procedure for Installation of Vapor Cycle ...................................MG 14-1 Air Conditioning Systems AC 29 MG 15 Airworthiness Approval of Rotorcraft Health Usage Monitoring ......................MG 15-1 Systems (HUMS) AC 29 MG 16 Certification Procedure for Rotorcraft Night Vision Imaging ...........................MG 16-1 Systems (NVIS) Equipment AC 29 MG 17 (reserved) ........................................................................................................MG 17-1 AC 29 MG 18 Helicopter Terrain Awareness and Warning System (HTAWS).......................MG 18-1
AC 29 Appendix A – Instructions for Continued Airworthiness................................................Apdx A-1 AC 29 Appendix B - Airworthiness Guidance for Rotorcraft Instrument Flight ........................Apdx B-1 AC 29 Appendix C - (reserved) (Icing Certification)…….…………………………………...… ..Apdx C-1 AC 29 Appendix D - (reserved) (Criteria for Demonstration of Emergency ………………….. Apdx D-1 Evacuation Procedures Under § 29.803)
FIGURES
The first digits in the figure number are the same as the related paragraph number. The digits after the hyphen are the number within the paragraph. Most figures are located at the end of the related paragraph.
Figure No. Title Page
AC 29.45-1 H-V Requirements B-21
AC 29.45-2 IGE Controllability Requirements B-22
AC 29.45-3 Shaft Horsepower vs. Turbine Outlet B-23 Temperature - Sea Level Standard Day
AC 29.45-4 Uninstalled Takeoff Power Available B-24
AC 29.45-5 Installed Takeoff Power Available, Anti-Ice Off, B-25 400 RPM
AC 29.45-6 Power Assurance Check Chart B-26
AC 29.53-1 Takeoff Performance Category A B-33
AC 29.53A-1 Takeoff Performance Category A B-35
AC 29.59-1 Category A Vertical Takeoff Profile Ground B-44 Level Heliport
AC 29.59-2 Category A Vertical Takeoff Profile Pinnacle B-45
AC 29.59A-1 Category A Vertical Takeoff Profile Ground B-55 Level Heliport
AC 29.59A-2 Category A Vertical Takeoff Profile Elevated B-56 Heliport
AC 29.63-1 Conventional Tak eoff Profile Category B B-59
AC 29.71-1 Autorotational Characteristics - Typical B-68
AC 29.75-1 Category A Conv entional Landing - Clear B-78 Heliport
AC 29-2C, Chg 2 4/25/06 Figure No. Title Page
AC 29.75-2 Category A Vertical Landing B-79
AC 29.75A-1 Category A Conventional Landing - Clear B-89 Heliport
AC 29.75A-2 Category A Vertical Landing B-90
AC 29.79-1 Height-Velocity Diagram B-98
AC 29.79-2 Altitude/Wei ght Accountability B-99
AC 29.175-1 Static Longi tudinal Stability B-115
AC 29.251-1 Demonstration Points B-127
AC 29.337-1 Load Factor Gross Weight Curve C-7
AC 29.351-1 Sample Yaw/Forward Speed Diagram C-12
AC 29.351A-1 Sample Yaw/Forward Speed Diagram C-14
AC 29.351B-1 Yaw/Forward Speed Diagram C-1 7
AC 29.351B-2 Safety Factors for Probability of Failure C-18
AC 29.427-1 (View Looking Forward) C-31
AC 29.427-2 (View Looking Forward) C-32
AC 29.562-1 Seat Restraint System Dynamic Tests C-58
AC 29.562-2 Schematic Floor De formation Fixture; Seat C-65 Legs Attached at Floor Level
AC 29.562-3 Schematic Test Fixt ure; Side Wall Mounted Seat C-69
AC 29.562-4 Installation of Pelv ic Lumbar Spine Load Cell in C-73 Part 572B Anthropomorphic Dummy
AC 29.562-5 Measurement to be Tak en Over Full Width of Seat C-85 Bottom Cushion
AC 29.562-6 Post Test Condition C-85
Figure No. Title Page
AC 29.562-7 Impulse Shape C-91
AC 29.562-8 Change in Velocity C-91
AC 29.571-1 Comparison Percent of Time in Level Flight C-96
AC 29.621-1 Example of Cast ing Load Sheet Retract D-24 Actuator Support-Landing Gear
AC 29.621-2 Castings to be Static Tested for Model XYZ D-26
AC 29.773-1 Cockpit Visibility D-73
AC 29.801-1 Sea State Code - World Meteorological D-96 Organization
AC 29.863-1 Flammable Fluids Fire Protection Flow Chart D-128
AC 29.865-1 Summary of Part 133 Rotorcraft Load D-136 Combinations Certifiable Under § 29.865
AC 29.865B-1 U.S. Operational (Part 133) Rotorcraft-Load D-146 Combination vs. Applicable Cargo Type Data And Definition Summary
AC 29.877-1 Continuous Icing-Te mperature vs. Altitude D-181 Limits
AC 29.877-2 Intermittent Icing- Temperature vs. Altitude D-182 Limits
AC 29.877-3 Mean Effective Drop Diameter-Microns D-183
AC 29.877-4 Intermittent Icing- Liquid Water Content vs. D-184 Drop Diameter
AC 29.877-5 Supercooled Clouds D-185
AC 29.903C-1 Estimated Path of Fragments E-23
AC 29.903C -2 Single One- Third Disc Fragment E-24
AC 29.903C -3 Intermediate and Small Pieces of Debris E-25
AC 29-2C, Chg 1 2/12/03 Figure No. Title Page
AC 29.903C -4 Blade Fragment Definition E-26
AC 29.903C -5 Distribution of Translational and Rotational E-27 Kinetic Energy of Rotor-Component Fragments as a Function of Fragment Size
AC 29.903C -6 Cross Section through Aircraft at Plane of E-28 Rotation of the Engine Disk Fragment
AC 29.923A-1 Rotor Drive System Endurance E-48
AC 29.923A-2 Takeoff Run Portion of Rotor Drive System E-49 Endurance Test If 2 ½ Minute OEI Rating is Requested.
AC 29.923A-3 Takeoff Run Portion of Rotor Drive System E-50 Endurance Test If 30 Second/2 Minute OEI Rating is Requested.
AC 29.931-1 Cantilevered Shaft, First Critical Speed E-62
AC 29.931-2 Shaft Between Support Bearings, First Critical E-62 Speed
AC 29.952-1 Static Tensi on and Shear Loading Modes E-87
AC 29.952-2 Hose Assembly Tests E-88
AC 29.952-3 Minimum Average and Individual Loads for E-89 Hose and Hose-End Fitting Combinations
AC 29.952-4 Typical Method of Breakaway Fuel Fitting Load E-90 Calculations
AC 29.952-5 Typical Methods of Frangible or Deformable E-91 Attachment Load Calculations (Frangible Bolts)
AC 29.952-6 Typical Methods of Frangible or Deformable E-92 Attachment Load Calculations (Frangible Baffle)
AC 29.955A-1 Fuel Flow E-102
AC 29.1041-1 Additional Cooling Test Point E-139
Figure No. Title Page
AC 29.1045-1 All-Engine-Critical Altitude Additional Cooling E-146 Test Point
AC 29.1191-1 Table of Materials and Gages Acceptable E-190 for Fireproof Protective Devices with Flat Surface Geometries
AC 29.1309-1 Relationship Between Probability and Severity F-17 of Failure Condition Effects
AC 29.1309-2 Failure Condition Categories and Probability F-18 Definitions
AC 29.1309-3 Failure Condition Conversion F-19
AC 29.1309-4 Safety Assessment Process Overview F-24
AC 29.1309-5 Depth of Analysis Flowchart F-25
AC 29.1329-1 Deviation Profile F-57
AC 29.1329-2 Operational Limitation F-59
AC 29.1419-1 Continuous Icing-Te mperature vs. Altitude F-110 Limits
AC 29.1419-2 Intermittent Icing- Temperature vs. Altitude F-111 Limits
AC 29.1419-3 Continuous Icing-Liquid Water Content vs F-112 Drop Diameter
AC 29.1419-4 Intermittent Icing- Liquid Water Content vs. F-113 Drop Diameter
AC 29.MG 3-1 Category II A pproach Evaluation MG 3-5
AC 29.MG 3-2 Category II Approac h Evaluation (cont.) MG 3-6
AC 29.MG 5-1 Acceptable Ultim ate Load Factor for MG 5-2 Agricultural Dispensing Equipment Design
AC 29.MG 5-2 Sketch of Tank Pressure Test MG 5-6
AC 29-2C, Chg 2 4/25/06 Figure No. Title Page
AC 29.MG 6-1 Typical Liquid Oxygen System MG 6-18
AC 29.MG 6-2 Typical Liquid Oxygen System - Using MG 6-19 Combination Valve
AC 29 MG 8-1 Schematic Diagram of Building Block Tests MG 8-16
AC 29 MG 8-2 Characterization of Impact Damage MG 8-20
AC 29 MG 8-3 Residual St rength vs. Tiime MG 8-23
AC 29 MG 8-4 Residual Strength and Damage Size MG 8-24 Relationships for Fail-Safe Substantiation
AC 29 MG 9-1 Installed Engine Fuel Flow Capacity Check MG 9-8
AC 29 MG 11-1 Crack Growth for Single Element Structure MG 11-14
AC 29 MG 11-2 Crack Growth for Remaining Elements of MG 11-16 Multiple Element Structure
AC 29 MG 11-3 No Crack Growth Scenario MG 11-18
AC 29 MG 11-4 Slow Crack Growth Scenario MG 11-18
AC 29 MG 11-5 Detectable Crack Growth Scenario MG 11-19
AC 29 MG 14-1 Refrigeration Cycle MG 14-7
AC 29 MG 15-1 Flow Chart for Use of Mitigating Actions MG 15-8 Applied for Reduction of Software Level
AC 29 MG 15-2 Flow Chart for App lication of HUMS Specific MG 15-11 Software with a Ground Base that uses COTS Software for Operational Software
AC 29 MG 18-1 Recommended Alert Prioritization between MG 18-16 HTAWS and TCAS TA
AC 29 MG 18-2 Flight Test Matrix MG 18-19
AC 29 MG 18-2.1 TAWS Required Terrain Clearance (RTC) MG 18-25 by Phase of Flight
Figure No. Title Page
AC 29.APX B-1 Rotorcraft Dynamic Stability Requirements Apdx B-20 for IFR
AC 29-2C, Chg 1 2/12/03 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 Btu British thermal unit 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 EGPWS enhanced ground proximity warning system 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 FLIRS Forward Looking Infrared System 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 HSI horizontal situation indicator 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 LCD liquid crystal display 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 NVG night vision goggles OAT outside air temperature OEI one engine inoperative Page xxiv
OGE out of ground effect PBA pitch bias actuator 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 S/N stress vs. number of cycles SRM structural repair manual SSA system safety assessment 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 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 Page xxv
CHAPTER 1. PART 21
FAR 21 - GENERAL
CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS (Amendment 21-50)
AC 21.16. § 21.16 SPECIAL CONDITIONS.
a. The Process. Chapter 2, Section 1, Paragraph 8 of the Type Certificate Handbook, Order 8110.4A, 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.
Page FAR 21 - 1
AC 21.31 § 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.
AC 21.33 § 21.33 INSPECTION AND TESTS.
a. Applicant Responsibility. Section 21.33 requires the applicant to:
(1) Assure the test rotorcraft confo rms 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 shoul d 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.
AC 21.35 § 21.35 (Amendment 21-59) FLIGHT TESTS.
a. Explanation.
(1) This section outlines the require ments of the applicant for aircraft type certification and should be used in conjunction with FAA Order 8110.4A, Section 5.
Section 21.35 requires, in part, that the applicant conduct sufficient flight tests to show compliance with the flight requirements throughout the proposed flight envelope. The results of the applicant’s flight test should be submitted to the FAA/AUTHORITY in report form for evaluation to determine what verification flight tests the FAA/AUTHORITY may elect to conduct. The report should conclude that in the applicant’s opinion the test aircraft complies with the applicable certification requirements. The FAA/AUTHORITY verification flight test should include, but not be limited to, the critical or marginal results contained in the applicant’s flight test report.
The FAA/AUTHORITY’s role in the certification effort is not envisioned to be one of conducting day-to-day routine flight tests with the applicant, but only to verify his results through limited sampling. In certain tests, such as high altitude testing at a remote mountain site, there is an advantage in conducting flight tests concurrently with the applicant. Additionally, the FAA/AUTHORITY can provide technical flight test assistance to the applicant in certain cases. This can be done after a cursory review and a letter of authorization is issued to the flight test crew.
Page FAR 21 - 2