Page No.
CHAPTER 3 - MISCELLANEOUS GUIDANCE (MG),
TRANSPORT CATEGORY ROTORCRAFT AC 29 MG 1 Certification Procedure for Rotorcraft Avionics Equipment............. MG 1-1 System Tests Interior Arrangements, and Equipment Flotation System Rotorcraft Metallic Structure (Including Flaw Tolerance) Air Conditioning Systems Systems (HUMS) Systems (NVIS) Equipment System AC 29 MG 18 Helicopter Terrain Awareness and Warning System (HTAWS) ...... MG 18-1 Installations Assessment (FHA) Installation in Part 29 Rotorcraft AC 29 MG 2 Standardized Test Procedure for Rotorcraft DC Electrical ............. MG 2-1 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 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 AC 29 MG 11 Fatigue Tolerance Evaluation of Transport Category ..................... MG 11-1 AC 29 MG 12 External Loads ............................................................................... MG 12-1 AC 29 MG 13 Systems Certification Considerations ............................................ MG 13-1 AC 29 MG 14 Certification Procedure for Installation of Vapor Cycle .................. MG 14-1 AC 29 MG 15 Airworthiness Approval of Rotorcraft Health Usage Monitoring ..... MG 15-1 AC 29 MG 16 Certification Procedure for Rotorcraft Night Vision Imaging .......... MG 16-1 AC 29 MG 17 Guidance on Analyzing an Advanced Flight Controls (AdFC) ........ MG 17-1 AC 29 MG 19 Guidance on Electronic Display Systems (EDS) for Rotor craft ...... MG 19-1 AC 29 MG 20 Human Factors (HF) ....................................................................... MG 20-1 AC 29 MG 21 Guidance on Creating a System Level Functional Hazard ............. MG 21-1 AC 29 MG 22 Rotorcraft One Engine Inoperative (OEI) Training Mode................ MG 22-1 AC 29 MG 23 Automatic Flight Guidance and Control Systems (AFGCS) ............ MG 23-1 Page xvii
AC 29-2C, Chg 9 6/23/23
APPENDICES 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 Page xviii
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 No.
AC 29.45-1 H-V Requirements. B-22 AC 29.45-2 IGE Controllability Requirements. B-23 AC 29.45-3 Shaft Horsepower vs. Turbine Outlet Temperature - B- 24 Sea Level Standard Day.
AC 29.45-4 Uninstalled Takeoff Power Available. B-25 AC 29.45-5 Installed Takeoff Power Available, Anti-Ice Off, 400 RPM. B-26 AC 29.45-6 Power Assurance Check Chart. B-26.1 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 Level Heliport. B-44 AC 29.59-2 Category A Vertical Takeoff Profile Pinnacle. B-45 AC 29.59A-1 Category A Vertical Takeoff Profile Ground Level Heliport. B-55 AC 29.59A-2 Category A Vertical Takeoff Profile Elevated Heliport. B-56 AC 29.63-1 Conventional Takeoff Profile Category B. B-59 AC 29.71-1 Autorotational Characteristics – Typical. B-68 AC 29.75-1 Category A Conventional Landing - Clear Heliport. B-78 AC 29.75-2 Category A Vertical Landing. B-79 AC 29.75A-1 Category A Conventional Landing - Clear Heliport. B-89 AC 29.75A-2 Category A Vertical Landing. B-90 AC 29.79-1 Height-Velocity (HV) Diagram. B-98 AC 29.79-2 Altitude/Weight Accountability. B-99 AC 29.175-1 Static Longitudinal Stability. B-115 AC 29.175A-1 Static Longitudinal Stability. B-116.3 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 Page xix
AC 29-2C, Chg 7 2/4/2016 Figure No. Title Page No.
AC 29.351A-1 Sample Yaw/Forward Speed Diagram. C-14 AC 29.351B-1 Yaw/Forward Speed Diagram. C-17 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 at Floor Level.
Anthropomorphic Dummy.
Bottom Cushion.
in this guidance.
AC 29.562-1 Seat Restraint System Dynamic Tests. C-58 AC 29.562-2 Schematic Floor Deformation Fixture; Seat Legs Attached C-65 AC 29.562-3 Schematic Test Fixture; Side Wall Mounted Seat. C-69 AC 29.562-4 Installation of Pelvic Lumbar Spine Load Cell in Part 572B C-73 AC 29.562-5 Measurement to be Taken Over Full Width of Seat C-85 AC 29.562-6 Post Test Condition. C-85 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 29.571B-1 Seven Fatigue Evaluation Methods discussed C-103 AC 29.571B-2 No Growth. C-118 AC 29.571B-3 Slow Growth of Undetectable Crack. C-118 AC 29.571B-4 Slow Growth of Detectable Crack. C-119 AC 29.571B-5 Decreasing Residual Life in Secondary Load Path C-122 for Multiple Element Crack Growth with Inspections.
AC 29.571B-6 Multiple Load Path Structure Analytical Evaluation To C-123 Support Inspection for a Failed Load Path.
AC 29.571B-7 Multiple Load Path Structure Evaluation by Test to C-125 Support Inspection for a Failed Load Path.
AC 29.571B-8 Multiple Load Path Structure Analytical Evaluation to C-126 Support Inspection for Less than a Failed Load Path.
Page xx
AC 29-2C, Chg 7 2/4/2016 Figure No. Title Page No.
AC 29.573-1 Schematic Diagram of Building Block Tests. C-144 AC 29.573-2 Characterization of Impact Damage. C-150 AC 29.573-3 Residual Strength vs. Time. C-154 AC 29.573-4 Illustration of Residual Strength and Damage Size. C-155 Relationships for Fail-Safe Substantiation.
AC 29.621-1 Example of Casting Load Sheet Retract Actuator D-24 Support-Landing Gear.
Certifiable Under § 29.865.
Combination vs. Applicable Cargo Type Data And Definition Summary.
AC 29.903C -4 Blade Fragment Definition.
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 Organization. D-96 AC 29.863-1 Flammable Fluids Fire Protection Flow Chart. D-128 AC 29.865-1 Summary of Part 133 Rotorcraft Load Combinations D-136 AC 29.865B-1 U.S. Operational (Part 133) Rotorcraft-Load D-146 AC 29.877-1 Continuous Icing-Temperature vs. Altitude Limits. D-181 AC 29.877-2 Intermittent Icing-Temperature vs. Altitude Limits. D-182 AC 29.877-3 Mean Effective Drop Diameter-Microns. D-183 AC 29.877-4 Intermittent Icing-Liquid Water Content vs. Drop Diameter. D-184 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 E-26 AC 29.903C -5 Distribution of Translational and Rotational Kinetic. E-27 Energy of Rotor-Component Fragments as a Function of Fragment Size.
AC 29.903C -6 Cross Section through Aircraft at Plane of Rotation of E-28 the Engine Disk Fragment.
AC 29.923A-1 Rotor Drive System Endurance. E-48 Page xxi
AC 29-2C, Chg 7 2/4/2016 Figure No. Title Page No.
AC 29.923A-2 Takeoff Run Portion of Rotor Drive System EnduranceE-49
Test If 2 ½ Minute OEI Rating is Requested.
AC 29.923A-3 Takeoff Run Portion of Rotor Drive System EnduranceE-50
Test If 30 Second/2 Minute OEI Rating is Requested.
AC 29.931-1 Cantilevered Shaft, First Critical SpeedE-62
AC 29.931-2 Shaft Between Support Bearings, First Critical SpeedE-62
AC 29.952-1 Static Tension and Shear Loading ModesE-87
AC 29.952-2 Hose Assembly TestsE-88
AC 29.952-3 Minimum Average and Individual Loads for Hose andE-89
Hose-End Fitting Combinations.
AC 29.952-4 Typical Method of Breakaway Fuel Fitting Load Calculations. E-90
AC 29.952-5 Typical Methods of Frangible or Deformable AttachmentE-91
Load Calculations (Frangible Bolts).
AC 29.952-6 Typical Methods of Frangible or Deformable AttachmentE-92
Load Calculations (Frangible Baffle).
AC 29.955A-1 Fuel Flow. E-102
AC 29.1041-1 Additional Cooling Test PointE-139
AC 29.1045-1 All-Engine-Critical Altitude Additional Cooling Test PointE-146
AC 29.1191-1 Table of Materials and Gages Acceptable for FireproofE-190
Protective Devices with Flat Surface Geometries.
AC 29.1309-1 Relationship Between Probability and Severity of Failure.......F-1 7 / F-40.5 Condition Effects.
AC 29.1309-2 Failure Condition Categories and Probability Definitions. .......F-18 / F-40.6
AC 29.1309-3 Failure Condition ConversionF-19
AC 29.1309-4 Safety Assessment Process Overview....................................F-24 / F-40.10 AC 29.1309-5 Depth of Analysis Flowchart....................................................F-2 5 / F-40.11
AC 29.1321-1 Primary Fields of ViewF-43
AC 29.1321-1 Secondary Fields of ViewF-44
AC 29.1329-1 Height Loss MethodF-54
AC 29.1329-2 Deviation ProfileF-58
AC 29.1329-3 Deviation ProfileF-60
AC 29.1419-1 Continuous Icing-Temperature vs. Altitude LimitsF-110
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AC 29-2C, Chg 7 2/4/2016 Figure No. Title Page No.
AC 29.1419-2 Intermittent Icing-Temperature vs. Altitude LimitsF-111
Dispensing Equipment Design.
Fail-Safe Substantiation.
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 Multiple..................MG 11-16 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 Reduction of Software Level.
with a Ground Base that uses COTS Software for Operational Software
AC 29.1419-3 Continuous Icing-Liquid Water Content vs Drop DiameterF-112
AC 29.1419-4 Intermittent Icing-Liquid Water Content vs Drop DiameterF-113
AC 29.MG 3-1 Category II Approach Evaluation.............................................MG 3-5 AC 29.MG 3-2 Category II Approach Evaluation. (cont.) ................................MG 3-6 AC 29.MG 5-1 Acceptable Ultimate Load Factor for Agricultural ....................MG 5-3 AC 29.MG 5-2 Sketch of Tank Pressure Test.................................................MG 5-7 AC 29.MG 6-1 Typical Liquid Oxygen System................................................MG 6-22 AC 29.MG 6-2 Typical Liquid Oxygen System - Using Combination Valve.....MG 6-23 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 Strength vs. Time. ....................................................MG 8-23 AC 29 MG 8-4 Residual Strength and Damage Size Relationships for...........MG 8-24 AC 29 MG 9-1 Installed Engine Fuel Flow Capacity Check ............................MG 9-8 AC 29 MG 14-1 Refrigeration Cycle..................................................................MG 14-7 AC 29 MG 15-1 Flow Chart for Use of Mitigating Actions Applied for ...............MG 15-8 AC 29 MG 15-2 Flow Chart for Application of HUMS Specific Software...........MG 15-11 AC 29 MG 17-1 Verification Methodology.........................................................MG 17-4 AC 29 MG 19-1 Primary Field of View ..............................................................MG 19-15 AC 29 MG 19-2 Secondary Field of View .........................................................MG 29-16 AC 29 MG 20-1 Primary and Secondary Horizontal Fields of View ..................MG 20-18 Page xxiii
AC 29-2C, Chg 7 2/4/2016 AC 29 MG 20-2 Primary and Secondary Vertical Field of View ........................MG 20-19 AC 29 MG 20-3 Sample HF Compliance Matrix................................................MG 20-27 AC 29 MG 21-1 Generic Examples by ATA ......................................................MG 21-5 AC 29.APX B-1 Rotorcraft Dynamic Stability Requirements for IFR............... Apdx B-27 Page xxiv
Acronyms AC advisory circular ACO aircraft certification office ADF automatic direction finding ADI attitude direction indicator AEH airborne electronic hardware AEO all engines operating AdFC advanced flight control AFCS automatic flight control systems AFGCS automatic flight guidance and 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 CFR Code of Federal Regulations CG center of gravity COTS commercial off-the-shelf CPS cycles per second CRFS crash resistant fuel system CRI certification review item CRT cathode ray tube CVR cockpit voice recorder DER designated engineering representative DME distance measuring equipment EASA European Aviation Safety Agency ECAS engine caution advisory systems ECU environmental control unit EDS electronic data system EFIS electronic flight instrument System[Replaced by EDS.] EFP engine failure point EHE exhaust heat exchanger ELOS equivalent level of safety ELT emergency locator transmitter EMC electromagnetic compatibility EMI electromagnetic interference EMS emergency medical service EOL end of life EUROCAE European Organization for EVS FAA FADEC FAR FEM FHA FMEA FPM FPS FTA GPS GW HEC HF HIRF HRD HUMS HV IAS ICA ICAO ICS IFR Civil Aviation Equipment enhanced vision system Federal Aviation Administration full authority digital engine control Federal Aviation Regulations [OBSOLETE term.] finite element modeling functional hazard assessment failure mode and effects analysis feet per minute feet per second fault tree analysis global positioning system gross weight human external cargo high frequency high intensity radiated fields high rate of discharge health and usage monitoring systems height-velocity indicated airspeed instructions for continued airworthiness International Civil Aviation Organization inter-communication system instrument flight rules Page xxv
AC 29-2C, Chg 7 2/4/2016 PCDS personnel carrying device IGE in ground effect Systems IIDS integrated instrument display system ILS instrument landing system IMC instrument meteorological conditions PCF PIO PSA PSIG post crash fire pilot induced oscillation preliminary safety assessment pounds per square inch INS inertial navigation system gauge ISA international standard QPL qualified parts list atmosphere RFM rotorcraft flight manual ISIS integral spar inspection system ITT inter-turbine temperature RFMS rotorcraft flight manual supplement KCAS knots calibrated airspeed RGL Regulatory and Guidance KIAS knots indicated air speed Library KTAS knots true airspeed LDP landing decision point RPM RTCA revolutions per minute Radio Technical Commission LPV localizer performance with Of Aeronautics vertical guidance LRU line replaceable unit LWC liquid water content MC maximum continuous MCP maximum continuous power MEL minimum equipment list MG miscellaneous guidance MGB main gearbox MGT measured gas temperature MGW maximum gross weight MMEL master minimum equipment list MSL mean sea level MVD median volume diameter NASA National Aeronautics and Space Administration NDI non-destructive inspection NM nautical mile NPRM notice of proposed rulemaking NTSB National Transportation Safety Board NVG night vision goggles NVIS night vision imaging systems OAT outside air temperature OEI one engine inoperative OGE out of ground effect RVR SAE SAR SAS SCAS SHP S/N SRM SSA STC STOL TBO TC TCDS TDP TIA TIR TOP TOT TSO TVP VBIM VFR VMC runway visual range Society of Automotive Engineers search and rescue stability augmentation system stability and control augmentation systems shaft horsepower stress vs. number of cycles structural repair manual system safety assessment supplemental type certificate short takeoff and landing time between overhaul type certificate type certificate data sheet takeoff decision point type inspection authorization type inspection report takeoff power turbine outlet temperature technical standard order true vapor pressure visual blade inspection method visual flight rules visual meteorological PBA pitch bias actuator conditions Page xxvi
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 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.
AC 21.35 § 21.35 (Amendment 21-59) FLIGHT TESTS.
a. Explanation.
(1) This section outlines the requirements 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 Page FAR 21 - 2