1、634 14 CFR Ch. I (1111 Edition) Pt. 27 PART 27AIRWORTHINESS STAND-ARDS: NORMAL CATEGORY ROTORCRAFT Subpart AGeneral Sec. 27.1 Applicability. 27.2 Special retroactive requirements. Subpart BFlight GENERAL 27.21 Proof of compliance. 27.25 Weight limits. 27.27 Center of gravity limits. 27.29 Empty weig
2、ht and corresponding cen-ter of gravity. 27.31 Removable ballast. 27.33 Main rotor speed and pitch limits. PERFORMANCE 27.45 General. 27.49 Performance at minimum operating speed. 27.51 Takeoff. 27.65 Climb: all engines operating. 27.67 Climb: one engine inoperative. 27.71 Autorotation performance.
3、27.75 Landing. 27.87 Height-speed envelope. FLIGHT CHARACTERISTICS 27.141 General. 27.143 Controllability and maneuverability. 27.151 Flight controls. 27.161 Trim control. 27.171 Stability: general. 27.173 Static longitudinal stability. 27.175 Demonstration of static longitudinal stability. 27.177 S
4、tatic directional stability. GROUND AND WATER HANDLING CHARACTERISTICS 27.231 General. 27.235 Taxiing condition. 27.239 Spray characteristics. 27.241 Ground resonance. MISCELLANEOUS FLIGHT REQUIREMENTS 27.251 Vibration. Subpart CStrength Requirements GENERAL 27.301 Loads. 27.303 Factor of safety. 27
5、.305 Strength and deformation. 27.307 Proof of structure. 27.309 Design limitations. FLIGHT LOADS 27.321 General. 27.337 Limit maneuvering load factor. 27.339 Resultant limit maneuvering loads. 27.341 Gust loads. 27.351 Yawing conditions. 27.361 Engine torque. CONTROL SURFACE AND SYSTEM LOADS 27.391
6、 General. 27.395 Control system. 27.397 Limit pilot forces and torques. 27.399 Dual control system. 27.411 Ground clearance: tail rotor guard. 27.427 Unsymmetrical loads. GROUND LOADS 27.471 General. 27.473 Ground loading conditions and as-sumptions. 27.475 Tires and shock absorbers. 27.477 Landing
7、gear arrangement. 27.479 Level landing conditions. 27.481 Tail-down landing conditions. 27.483 One-wheel landing conditions. 27.485 Lateral drift landing conditions. 27.493 Braked roll conditions. 27.497 Ground loading conditions: landing gear with tail wheels. 27.501 Ground loading conditions: land
8、ing gear with skids. 27.505 Ski landing conditions. WATER LOADS 27.521 Float landing conditions. MAIN COMPONENT REQUIREMENTS 27.547 Main rotor structure. 27.549 Fuselage, landing gear, and rotor pylon structures. EMERGENCY LANDING CONDITIONS 27.561 General. 27.562 Emergency landing dynamic condi-tio
9、ns. 27.563 Structural ditching provisions. FATIGUE EVALUATION 27.571 Fatigue evaluation of flight struc-ture. Subpart DDesign and Construction GENERAL 27.601 Design. 27.602 Critical parts. 27.603 Materials. 27.605 Fabrication methods. 27.607 Fasteners. 27.609 Protection of structure. 27.610 Lightnin
10、g and static electricity pro-tection. 27.611 Inspection provisions. 27.613 Material strength properties and de-sign values. 27.619 Special factors. 27.621 Casting factors. VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00644 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1
11、PROD with CFRProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-635 Federal Aviation Administration, DOT Pt. 27 27.623 Bearing factors. 27.625 Fitting factors. 27.629 Flutter. ROTORS 27.653 Pressure venting and drainage of rotor blades. 27.659 Mass bala
12、nce. 27.661 Rotor blade clearance. 27.663 Ground resonance prevention means. CONTROL SYSTEMS 27.671 General. 27.672 Stability augmentation, automatic, and power-operated systems. 27.673 Primary flight control. 27.674 Interconnected controls. 27.675 Stops. 27.679 Control system locks. 27.681 Limit lo
13、ad static tests. 27.683 Operation tests. 27.685 Control system details. 27.687 Spring devices. 27.691 Autorotation control mechanism. 27.695 Power boost and power-operated con-trol system. LANDING GEAR 27.723 Shock absorption tests. 27.725 Limit drop test. 27.727 Reserve energy absorption drop test.
14、 27.729 Retracting mechanism. 27.731 Wheels. 27.733 Tires. 27.735 Brakes. 27.737 Skis. FLOATS AND HULLS 27.751 Main float buoyancy. 27.753 Main float design. 27.755 Hulls. PERSONNEL AND CARGO ACCOMMODATIONS 27.771 Pilot compartment. 27.773 Pilot compartment view. 27.775 Windshields and windows. 27.7
15、77 Cockpit controls. 27.779 Motion and effect of cockpit controls. 27.783 Doors. 27.785 Seats, berths, litters, safety belts, and harnesses. 27.787 Cargo and baggage compartments. 27.801 Ditching. 27.805 Flight crew emergency exits. 27.807 Emergency exits. 27.831 Ventilation. 27.833 Heaters. FIRE PR
16、OTECTION 27.853 Compartment interiors. 27.855 Cargo and baggage compartments. 27.859 Heating systems. 27.861 Fire protection of structure, controls, and other parts. 27.863 Flammable fluid fire protection. EXTERNAL LOADS 27.865 External loads. MISCELLANEOUS 27.871 Leveling marks. 27.873 Ballast prov
17、isions. Subpart EPowerplant GENERAL 27.901 Installation. 27.903 Engines. 27.907 Engine vibration. ROTOR DRIVE SYSTEM 27.917 Design. 27.921 Rotor brake. 27.923 Rotor drive system and control mech-anism tests. 27.927 Additional tests. 27.931 Shafting critical speed. 27.935 Shafting joints. 27.939 Turb
18、ine engine operating characteris-tics. FUEL SYSTEM 27.951 General. 27.952 Fuel system crash resistance. 27.953 Fuel system independence. 27.954 Fuel system lightning protection. 27.955 Fuel flow. 27.959 Unusable fuel supply. 27.961 Fuel system hot weather operation. 27.963 Fuel tanks: general. 27.96
19、5 Fuel tank tests. 27.967 Fuel tank installation. 27.969 Fuel tank expansion space. 27.971 Fuel tank sump. 27.973 Fuel tank filler connection. 27.975 Fuel tank vents. 27.977 Fuel tank outlet. FUEL SYSTEM COMPONENTS 27.991 Fuel pumps. 27.993 Fuel system lines and fittings. 27.995 Fuel valves. 27.997
20、Fuel strainer or filter. 27.999 Fuel system drains. OIL SYSTEM 27.1011 Engines: General. 27.1013 Oil tanks. 27.1015 Oil tank tests. 27.1017 Oil lines and fittings. 27.1019 Oil strainer or filter. 27.1021 Oil system drains. 27.1027 Transmissions and gearboxes: Gen-eral. COOLING 27.1041 General. 27.10
21、43 Cooling tests. 27.1045 Cooling test procedures. VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00645 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-636 14 CFR
22、 Ch. I (1111 Edition) Pt. 27 INDUCTION SYSTEM 27.1091 Air induction. 27.1093 Induction system icing protection. EXHAUST SYSTEM 27.1121 General. 27.1123 Exhaust piping. POWERPLANT CONTROLS AND ACCESSORIES 27.1141 Powerplant controls: general. 27.1143 Engine controls. 27.1145 Ignition switches. 27.114
23、7 Mixture controls. 27.1151 Rotor brake controls. 27.1163 Powerplant accessories. POWERPLANT FIRE PROTECTION 27.1183 Lines, fittings, and components. 27.1185 Flammable fluids. 27.1187 Ventilation and drainage. 27.1189 Shutoff means. 27.1191 Firewalls. 27.1193 Cowling and engine compartment covering.
24、 27.1194 Other surfaces. 27.1195 Fire detector systems. Subpart FEquipment GENERAL 27.1301 Function and installation. 27.1303 Flight and navigation instruments. 27.1305 Powerplant instruments. 27.1307 Miscellaneous equipment. 27.1309 Equipment, systems, and installa-tions. 27.1317 High-intensity Rad
25、iated Fields (HIRF) Protection. INSTRUMENTS: INSTALLATION 27.1321 Arrangement and visibility. 27.1322 Warning, caution, and advisory lights. 27.1323 Airspeed indicating system. 27.1325 Static pressure systems. 27.1327 Magnetic direction indicator. 27.1329 Automatic pilot system. 27.1335 Flight direc
26、tor systems. 27.1337 Powerplant instruments. ELECTRICAL SYSTEMS AND EQUIPMENT 27.1351 General. 27.1353 Storage battery design and installa-tion. 27.1357 Circuit protective devices. 27.1361 Master switch. 27.1365 Electric cables. 27.1367 Switches. LIGHTS 27.1381 Instrument lights. 27.1383 Landing lig
27、hts. 27.1385 Position light system installation. 27.1387 Position light system dihedral an-gles. 27.1389 Position light distribution and in-tensities. 27.1391 Minimum intensities in the hori-zontal plane of forward and rear position lights. 27.1393 Minimum intensities in any vertical plane of forwar
28、d and rear position lights. 27.1395 Maximum intensities in overlapping beams of forward and rear position lights. 27.1397 Color specifications. 27.1399 Riding light. 27.1401 Anticollision light system. SAFETY EQUIPMENT 27.1411 General. 27.1413 Safety belts. 27.1415 Ditching equipment. 27.1419 Ice pr
29、otection. 27.1435 Hydraulic systems. 27.1457 Cockpit voice recorders. 27.1459 Flight data recorders. 27.1461 Equipment containing high energy rotors. Subpart GOperating Limitations and Information 27.1501 General. OPERATING LIMITATIONS 27.1503 Airspeed limitations: general. 27.1505 Never-exceed spee
30、d. 27.1509 Rotor speed. 27.1519 Weight and center of gravity. 27.1521 Powerplant limitations. 27.1523 Minimum flight crew. 27.1525 Kinds of operations. 27.1527 Maximum operating altitude. 27.1529 Instructions for Continued Air-worthiness. MARKINGS AND PLACARDS 27.1541 General. 27.1543 Instrument mar
31、kings: general. 27.1545 Airspeed indicator. 27.1547 Magnetic direction indicator. 27.1549 Powerplant instruments. 27.1551 Oil quantity indicator. 27.1553 Fuel quantity indicator. 27.1555 Control markings. 27.1557 Miscellaneous markings and plac-ards. 27.1559 Limitations placard. 27.1561 Safety equip
32、ment. 27.1565 Tail rotor. ROTORCRAFT FLIGHT MANUAL AND APPROVED MANUAL MATERIAL 27.1581 General. 27.1583 Operating limitations. 27.1585 Operating procedures. 27.1587 Performance information. 27.1589 Loading information. APPENDIX A TO PART 27INSTRUCTIONS FOR CONTINUED AIRWORTHINESS VerDate Mar2010 14
33、:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00646 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-637 Federal Aviation Administration, DOT 27.21 APPENDIX B TO PART 27AIRWORTHINE
34、SS CRI-TERIA FOR HELICOPTER INSTRUMENT FLIGHT APPENDIX C TO PART 27CRITERIA FOR CAT-EGORY A APPENDIX D TO PART 27HIRF ENVIRON-MENTS AND EQUIPMENT HIRF TEST LEV-ELS AUTHORITY: 49 U.S.C. 106(g), 40113, 44701 44702, 44704. SOURCE: Docket No. 5074, 29 FR 15695, Nov. 24, 1964, unless otherwise noted. Sub
35、part AGeneral 27.1 Applicability. (a) This part prescribes airworthiness standards for the issue of type certifi-cates, and changes to those certifi-cates, for normal category rotorcraft with maximum weights of 7,000 pounds or less and nine or less passenger seats. (b) Each person who applies under
36、Part 21 for such a certificate or change must show compliance with the appli-cable requirements of this part. (c) Multiengine rotorcraft may be type certified as Category A provided the requirements referenced in appen-dix C of this part are met. Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as amended
37、 by Amdt. 2733, 61 FR 21906, May 10, 1996; Amdt. 2737, 64 FR 45094, Aug. 18, 1999 27.2 Special retroactive require-ments. (a) For each rotorcraft manufactured after September 16, 1992, each applicant must show that each occupants seat is equipped with a safety belt and shoul-der harness that meets t
38、he require-ments of paragraphs (a), (b), and (c) of this section. (1) Each occupants seat must have a combined safety belt and shoulder har-ness with a single-point release. Each pilots combined safety belt and shoul-der harness must allow each pilot, when seated with safety belt and shoul-der harne
39、ss fastened, to perform all functions necessary for flight oper-ations. There must be a means to se-cure belts and harnesses, when not in use, to prevent interference with the operation of the rotorcraft and with rapid egress in an emergency. (2) Each occupant must be protected from serious head inj
40、ury by a safety belt plus a shoulder harness that will prevent the head from contacting any injurious object. (3) The safety belt and shoulder har-ness must meet the static and dynamic strength requirements, if applicable, specified by the rotorcraft type certifi-cation basis. (4) For purposes of th
41、is section, the date of manufacture is either (i) The date the inspection accept-ance records, or equivalent, reflect that the rotorcraft is complete and meets the FAA-Approved Type Design Data; or (ii) The date the foreign civil air-worthiness authority certifies that the rotorcraft is complete and
42、 issues an original standard airworthiness certifi-cate, or equivalent, in that country. (b) For rotorcraft with a certification basis established prior to October 18, 1999 (1) The maximum passenger seat ca-pacity may be increased to eight or nine provided the applicant shows com-pliance with all th
43、e airworthiness re-quirements of this part in effect on Oc-tober 18, 1999. (2) The maximum weight may be in-creased to greater than 6,000 pounds provided (i) The number of passenger seats is not increased above the maximum number certificated on October 18, 1999, or (ii) The applicant shows complian
44、ce with all of the airworthiness require-ments of this part in effect on October 18, 1999. Doc. No. 26078, 56 FR 41051, Aug. 16, 1991, as amended by Amdt. 2737, 64 FR 45094, Aug. 18, 1999 Subpart BFlight GENERAL 27.21 Proof of compliance. Each requirement of this subpart must be met at each appropri
45、ate com-bination of weight and center of grav-ity within the range of loading condi-tions for which certification is re-quested. This must be shown (a) By tests upon a rotorcraft of the type for which certification is re-quested, or by calculations based on, and equal in accuracy to, the results of
46、testing; and VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00647 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-638 14 CFR Ch. I (1111 Edition) 27.25 (b) By sys
47、tematic investigation of each required combination of weight and center of gravity if compliance cannot be reasonably inferred from combinations investigated. Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as amended by Amdt. 2721, 49 FR 44432, Nov. 6, 1984 27.25 Weight limits. (a) Maximum weight. The m
48、aximum weight (the highest weight at which compliance with each applicable re-quirement of this part is shown) must be established so that it is (1) Not more than (i) The highest weight selected by the applicant; (ii) The design maximum weight (the highest weight at which compliance with each applic
49、able structural loading condition of this part is shown); (iii) The highest weight at which compliance with each applicable flight requirement of this part is shown; or (iv) The highest weight in which the provisions of 27.87 or 27.143(c)(1), or combinations thereof, are dem-onstrated if the weights and operating conditions (altitude and temperature) prescribed by those requirements can-not be met; and (2) Not less tha
