AC 27.1B, Chg 9 AC 27.1351 AC 27.1353 AC 27.1353A AC 27.1357 AC 27.1361 AC 27.1365 AC 27.1367 AC 27.1381 AC 27.1383 AC 27.1385 AC 27.1387 AC 27.1389 AC 27.1391 AC 27.1393 AC 27.1395 AC 27.1397 AC 27.1399 AC 27.1401 AC 27.1411 AC 27.1413 AC 27.1415 AC 27.1419 AC 27.1435 AC 27.1457 AC 27.1459 AC 27.1461 AC 27.1501 Page No.
SUBPART F – EQUIPMENT (continued)
ELECTRICAL SYSTEMS AND EQUIPMENT
Electrical Systems and Equipment - GeneralF-55
Storage Battery Design and InstallationF-58
Energy Storage Systems ................................................................... F-62.1 Circuit Protectiv e Devices ................................................................. F-62.13
Master SwitchF-64
Electric CablesF-65
SwitchesF-66
LIGHTS
Instrument LightsF-67
Rear Position Lights Rear Position Lights Rear Position Lights
Landing LightsF-67
Position Light System InstallationF-68
Position Light System Dihedral AnglesF-68
Position Light Distribution and IntensitiesF-68
Minimum Intensities in the Horizontal Plane of Forward andF-68
Minimum Intensities in Any Vertical Plane of Forward andF-68
Maximum Intensities In Overlapping Beams of Forward andF-68
Color SpecificationsF-68
Riding LightF-68
Anti-collision Light SystemF-70
SAFETY EQUIPMENT
GeneralF-71
Safety BeltsF-73
Ditching EquipmentF-74
Ice ProtectionF-75
Hydraulic SystemsF-97
Cockpit Voice RecorderF-99
Flight RecordersF-101
Equipment Containing High Energy RotorsF-103
SUBPART G - OPERATING LIMITATIONS AND INFORMATION
GeneralG-1
Page xiii
AC 27.1B, Chg 9 AC 27.1503 AC 27.1505 AC 27.1509 AC 27.1519 AC 27.1521 AC 27.1521A AC 27.1521B AC 27.1523 AC 27.1525 AC 27.1527 AC 27.1529 AC 27.1529A AC 27.1541 AC 27.1543 AC 27.1543A AC 27.1545 AC 27.1545A AC 27.1547 AC 27.1549 AC 27.1549A AC 27.1549B AC 27.1549C AC 27.1551 AC 27.1553 AC 27.1555 AC 27.1555A AC 27.1557 AC 27.1559 AC 27.1561 AC 27.1565 Page No.
SUBPART G - OPERATING LIMITATIONS AND INFORMATION (continued)
OPERATING LIMITATIONS
Airspeed Limitations: GeneralG-1
Never-Exceed SpeedG-4
Rotor SpeedG-6
Weight and Center of GravityG-8
Powerplant LimitationsG-9
Powerplant LimitationsG-10
Powerplant LimitationsG-10
Minimum FlightcrewG-11
Kinds of OperationsG-15
Maximum Operating AltitudeG-16
Instructions for Continued Airworthiness (Maintenance Manual)G-16
Instructions for Continued Airworthiness (Maintenance Manual)G-20
MARKINGS AND PLACARDS
Marking and Placards - GeneralG-21
Instrument Markings: GeneralG-21
Instrument Markings: General......................................................... G-25.1 Airspeed Indicator ............................................................................. G-25.6 Airspeed Indicator ............................................................................. G-25.7 Magnetic Direction Indicator.............................................................. G-25.9 Powerplant Markings......................................................................... G-25.10 Powerplant Instruments .................................................................... G-25.10 Powerplant Instruments .................................................................... G-25.10
Powerplant InstrumentsG-26
Oil Quantity Indicators....................................................................... G-2 6.1 Fuel Quantity Indicator ...................................................................... G-26.2
Control MarkingsG-27
Control Markings ............................................................................... G-28.1 Miscellaneous Markings and Placards .............................................. G-28.2
Limitations PlacardG-30
Safety EquipmentG-31
Tail RotorG-32
AC 27.1583 AC 27.1585 AC 27.1585A AC 27.1587 AC 27.1587A AC 27.1587B AC 27.1589
ROTORCRAFT FLIGHT MANUAL AND APPROVED MANUAL MATERIAL
AC 27.1581 Rotorcraft Flight Manual - GeneralG-33
Performance InformationG-48
Loading Information ......................................................................... G-48.1 Operati
ng LimitationsG-40
Operating ProceduresG-42
Operating ProceduresG-45
Performance InformationG-45
Performance InformationG-47
Page xiv
Page No.
CHAPTER 3 - MISCELLANEOUS GUIDANCE (MG),
NORMAL CATEGORY ROTORCRAFT AC 27 MG 1 Certification Procedure for Rotorcraft Avionics Equipment............. MG 1-1 System Tests §§ 27.79(b)(2), 27.141(b)(1), and 27.143(d)(1) Including: Interior Arrangements, Equipment, Helicopter Terrain Awareness and Warning System (HTAWS), Radio Altimeter, and Flight Data Monitoring System.
System Air Conditioning Systems Systems (HUMS) Systems (NVIS) Equipment System Installations Assessment (FHA) Installation in Part 27 Rotorcraft AC 27 MG 2 Standardized Test Procedure for Rotorcraft DC Electrical ............. MG 2-1 AC 27 MG 3 Definition of Engine Isolation Features as Applied to .................... MG 3-1 AC 27 MG 4 Full Authority Digital Electronic Controls (FADEC) ......................... MG 4-1 AC 27 MG 5 Agricultural Dispensing Equipment Installation............................... MG 5-1 AC 27 MG 6 Emergency Medical Service (EMS) Systems, Installations, .......... MG 6-1 AC 27 MG 7 Hour Meters or Time-in-Service Recording Devices in Rotorcraft .. MG 7-1 AC 27 MG 8 Substantiation of Composite Rotorcraft Structure .......................... MG 8-1 AC 27 MG 9 Rotorcraft One-Engine-Inoperative (OEI) Power Assurance .......... MG 9-1 AC 27 MG 10 Advisory Material for Substantiation of Emergency Flotation ......... MG 10-1 AC 27 MG 11 Fatigue Evaluation of Rotorcraft Structure...................................... MG 11-1 AC 27 MG 12 External Loads (see AC 27.865B) .................................................. MG 12-1 AC 27 MG 13 Systems Certification Considerations............................................. MG 13-1 AC 27 MG 14 Certification Procedure for Installation of Vapor Cycle .................. MG 14-1 AC 27 MG 15 Airworthiness Approval of Rotorcraft Health Usage Monitoring ..... MG 15-1 AC 27 MG 16 Certification Procedure for Rotorcraft Night Vision Imaging .......... MG 16-1 AC 27 MG 17 Guidance on Analyzing an Advanced Flight Controls (AdFC) ........ MG 17-1 AC 27 MG 18 Helicopter Terrain Awareness and Warning System (HTAWS)...... MG 18-1 AC 27 MG 19 Guidance on Electronic Display Systems (EDS) for Rotorcraft ...... MG 19-1 AC 27 MG 20 Human Factors (HF)....................................................................... MG 20-1 AC 27 MG 21 Guidance on Creating a System Level Functional Hazard ............ MG 21-1 AC 27 MG 22 Rotorcraft One Engine Inoperative (OEI) Training Mode................ MG 22-1 AC 27 MG 23 Automatic Flight Guidance and Control systems (AFGCS ) ........... MG 23-1 Page xv
AC 27-1B, Chg 9
APPENDICES AC 27 Appendix A - Instructions for Continued Airworthiness................................... Apdx A-1 AC 27 Appendix B - Airworthiness Guidance for Rotorcraft Instrument Flight........... Apdx B-1 AC 27 Appendix C - (reserved) (Criteria for Category A) ........................................ Apdx C-1 Page xvi
FIGURES The first digits in the figure number are the same as the related section number.
Figure No. Title Page
AC 27.45-1 H-V RequirementsB-20
Temperature - Sea Level Standard Day 400 RPM Attached at Floor Level Part 572B Anthropomorphic Dummy Seat Bottom Cushion AC 27.562-6 Post Test Condition
AC 27.45-2 IGE Controllability RequirementsB-21
AC 27.45-3 Shaft Horsepower vs. Turbine OutletB-22
AC 27.45-4 Uninstalled Takeoff Power AvailableB-23
AC 27.45-5 Installed Takeoff Power Available, Anti-Ice Off,B-24
AC 27.45-6 Power Assurance Check Chart .................................................... B-24.1
AC 27.71-1 Autorotational Characteristics - TypicalB-31
AC 27.79-1 Height-Velocity DiagramB-43
AC 27.79-2 Altitude/Weight AccountabilityB-44
AC 27.175-1 Static Longitudinal Stability .......................................................... B-60.1 AC 27.175A-1 Static Longitudinal Stability .......................................................... B-60.5
AC 27.251-1 Demonstration PointsB-70
AC 27.337-1 Load Factor Gross Weight CurveC-7
AC 27.351-1 Sample Yaw/Forward Speed DiagramC-12
AC 27.351-2 Safety Factors for Probability of FailureC-13
AC 27.427-1 View Looking ForwardC-26
AC 27.427-2 View Looking ForwardC-27
AC 27.562-1 Seat Restraint System Dynamic TestsC-47
AC 27.562-2 Schematic Floor Deformation Fixture; Seat LegsC-54
AC 27.562-3 Schematic Test Fixture; Side Wall Mounted SeatC-58
AC 27.562-4 Installation of Pelvic-Lumbar Spine Load Cell inC-62
AC 27.562-5 Measurement to be Taken Over Full Width ofC-74
C-74 Page xvii
AC 27.1B, Chg 4 5/1/2014 FIGURES (continued) Figure No. Title Page
AC 27.562-7 Impulse ShapeC-80
Size Relationships for Fail-Safe SubstantiationC113
Actuator Support-Landing Gear Model XYZ Organization..............................................................................
Versus Applicable Cargo Type Data and Definition Summary Hose-End Fitting Combinations Calculations Load Calculations, Frangible Bolts Load Calculations, Frangible Baffle
AC 27.562-8 Change in VelocityC-80
AC 27.571-1 Comparison Percent of Time in Level FlightC-85
AC 27.573-1. Schematic diagram of building block testsC102
AC 27.573-2. Characterization of Impact DamageC-107
AC 27.573-3. Residual Strength vs. TimeC-112
AC 27.573-4. Illustration of Residual Strength and Damage
AC 27.621-1 Example of Casting Load Sheet RetractD-24
AC 27.621-2 Example of Castings to be Static Tested forD-26
AC 27.773-1 Cockpit VisibilityD-67
AC 27.801-1 Sea State Code - World MeteorologicalD-90
AC 27.865B-1 U.S. Operational (Part 133) Rotorcraft-Load CombinationD-116
AC 27.931-1 Cantilevered Shaft, First Critical SpeedE-25
AC 27.931-2 Shaft Between Support Bearings, First Critical SpeedE-25
AC 27.952-1 Static Tension and Shear Loading ModesE-50
AC 27.952-2 Hose Assembly TestsE-51
AC 27.952-3 Minimum Average and Individual Loads for Hose andE-52
AC 27.952-4 Typical Method of Breakaway Fuel Fitting LoadE-53
AC 27.952-5 Typical Methods of Frangible or Deformable AttachmentE-54
AC 27.952-6 Typical Methods of Frangible or Deformable AttachmentE-55
AC 27.955-1 Fuel Flow E-61E-61
Page xviii
FIGURES (continued) Figure No. Title Page
AC 27.1041-1 Additional Cooling Test PointE-93
AC 27.1191-1 Table of Materials and Gauges Acceptable forE-131
Fireproof Protective Devices with Flat Surface Geometries Failure Condition Effec ts AC 27.1309-1 Relationship between Probability and Severity of .........................F-30.5 AC 27.1309-2 Failure Condition Categories and Probably Definitions ...............F-30.6 Diameter Diamet er Dispensing Equipment Design Valve for Fail-Safe Substantiation for Three Rotorcraft Types AC 27.1309-4 Safety Assessment Process Overview .........
...............................F-30.10 AC 27.1309-5 Depth of Analysis Flowchart ........................................................F-30.11 AC 27.1321-1 Primary Fields of View ................................................................. F - 34 AC 27,1321-2 Secondary Fields of View............................................................. F – 34.1
AC 27.1329-1 Height Loss MethodF-45
AC 27.1329-2 Deviation ProfileF-49
AC 27.1329-3 Deviation ProfileF-50
AC 27.1419-1 Continuous Icing-Temperature vs. Altitude LimitsF-93
AC 27.1419-2 Intermittent Icing-Temperature vs. Altitude LimitsF-94
AC 27.1419-3 Continuous Icing-Liquid Water Content vs DropF-95
AC 27.141 9-4 Interm
ittent Icing-Liquid Water Content vs. DropF-96
AC 27 M G 3-1 Part 29 Engine Isolation Rules..................................................... MG 3-5 AC 27 MG 5-1 Acceptable Ultimate Load Factor for Agricultural ......................... MG 5-3 AC 27 MG 5-2 Sketch of Tank Pressure Test...................................................... MG 5-7 AC 27 MG 6-1 Typical Liquid Oxygen System..................................................... MG 6-21 AC 27 MG 6-2 Typical Liquid Oxygen System - Using Combination....................MG 6-22 AC 27 MG 8-1 Schematic Diagram of Building Block Tests................................. MG 8-16 AC 27 MG 8-2 Characterization of Impact Damage............................................. MG 8-20 AC 27 MG 8-3 Residual Strength vs. Time .......................................................... MG 8-23 AC 27- MG 8-4 Residual Strength and Damage Size Relationships.....................MG 8-24 AC 27 MG 9-1 Installed Engine Fuel Flow Capacity Check ................................. MG 9-8 AC 27 MG 11-1 Example of Variation in Time Spent in Level Flight......................MG 11-7 AC 27 MG 11-2 Flight Regime to be Investigated Power-On Operation................MG 11-17 Page xix
AC 27.1B, Chg 7 xx/xx/2014 FIGURES (continued) Figure No. Title Page AC 27 MG 11-3 Flight Regime to be Investigated for Power-Off ...........................MG 11-17 Operation Investigated Reduction of Software Level Software with a Ground Base that uses COTS Software for Operational Software AC 27 MG 11-4 Simplified Analytical Method for Safe Life Evaluation ..................MG 11-18 AC 27 MG 11-5 Typical S/N Curve for Safe Life Evaluation .................................. MG 11-18 AC 27 MG 11-6 Elements of Safe Life Determination............................................ MG 11-19 AC 27 MG 11-7 Flight Load Measurement Program Conditions to be...................MG 11-20 AC 27 MG 11-8 Lifting Helicopter Load Measurement........................................... MG 11-23 AC 27 MG 11-9 Example of Twin Turbine Usage Spectrum.................................. MG 11-24 AC 27 MG 14-1 Refrigeration Cycle....................................................................... MG 14-7 AC 27 MG 15-1 Flow Chart for Use of Mitigating Actions Applied for ....................MG 15-8 AC 27 MG 15-2 Flow Chart for Application of HUMS Specific ............................... MG 15-11 AC 27 MG 17-1 Verification Methodology.............................................................. MG 17-4 AC 27 MG 19-1 Primary Field of View ................................................................... MG 19-15 AC 27 MG 19-2 Secondary Field of View .............................................................. MG 19-16 AC 27 MG 20-1 Primary and Secondary Horizontal Fields of View .......................MG 20-18 AC 27 MG 20-2 Primary and Secondary Vertical Fields of View............................MG 20-19 AC 27 MG 20-3 Sample HF Compliance Matrix..................................................... MG 20-27 AC 27 MG 21-1 Generic Examples by ATA ........................................................... MG 21-5 AC 27 APX B-1 Rotorcraft Dynamic Stability Requirements for IFR......................Apdx B-27 Page xx
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 Civil Aviation Equipment EVS enhanced vision system FAA Federal Aviation Administration FADEC full authority digital engine control FAR Federal Aviation Regulations FEM FHA FMEA FPM FPS FTA GPS GW HEC HF HIRF HRD HUMS HV IAS ICA ICAO ICS IFR [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 xxi
AC 27.1B, Chg 4 5/1/2014 PCDS personnel carrying device IGE in ground effect Systems IIDS integrated instrument display syst em ILS instrument landing system IMC instrument meteorological conditions PCF P IO 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 k nots true airspeed LDP landing decision point RPM RTC A revolutions per minute Radi o Technical Commission LPV l ocalizer performance with Of Ae ronautics ver tical 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 S AE 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 xxii
2/4/2016 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 HD HP VD VH VMO VNE VTOSS VX VY MMO NF NG NP NR CD CL CP CT AC 27-1B, Chg 7 Altitudes density altitude pressure altitude V speeds diving speed speed in level flight with maximum continuous power maximum operating limit speed never-exceed speed takeoff safety speed for Category A rotorcraft speed for best angle of climb speed for best rate of climb maximum operating mach number N speeds free turbine speed gas generator speed power turbine speed rotor speed Coefficients coefficient of drag coefficient of lift coefficient of power coefficient of thrust Page xxiii
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 ensure coordination with the affected agency and industry elements including the Assistant Chief Counsel. All comments will be considered and the disposition document ed by the Rotorcraft Directorate. ASW-100 will issue the special conditions.
b. Basis for Development.
(1) Special conditions are justified on the basis of the existing Part 27 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 ensure they are inadequate or inappropriate in light of a new and novel design feature.
Page FAR 21 - 1