178.-188. RESERVED107
CHAPTER 4. POWERPLANT108
189. SECTION 23.901 INSTALLATION. (RESERVED)108
190. SECTION 23.903 ENGINES108
191. SECTION 23.905 PROPELLERS111
192. SECTION 23.909 TURBO SUPERCHARGERS111
192.a. SECTION 23.925 PROPELLER CLEARANCE111
193. SECTION 23.929 ENGINE INSTALLATION ICE PROTECTION111
194. SECTION 23.933 REVERSING SYSTEMS111
195. SECTION 23.939 POWERPLANT OPERATING CHARACTERISTICS112
196. SECTION 23.943 NEGATIVE ACCELERATION112
197.-206. RESERVED113
207. SECTION 23.959 UNUSABLE FUEL SUPPLY113
208. SECTION 23.961 FUEL SYSTEM HOT WEATHER OPERATION113
209.-220. RESERVED113
221. SECTION 23.1001 FUEL JETTISONING SYSTEM113
222.-237. RESERVED114
238. SECTION 23.1027 PROPELLER FEATHERING SYSTEM114
239.-244. RESERVED115
245. SECTION 23.1041 GENERAL115
246. SECTION 23.1043 COOLING TESTS115
247. SECTION 23.1045 COOLING TEST PROCEDURES FOR TURBINE
ENGINE-POWERED AIRPLANES116
248. SECTION 23.1047 COOLING TEST PROCEDURES FOR
RECIPROCATING ENGINE-POWERED AIRPLANES119
249.-254. RESERVED122
255. SECTION 23.1091 AIR INDUCTION122
256. SECTION 23.1093 INDUCTION SYSTEM ICING PROTECTION122
257.-265. RESERVED127
266. SECTION 23.1141 POWERPLANT CONTROLS: GENERAL127
267. SECTION 23.1145 IGNITION SWITCHES. (RESERVED)127
268. SECTION 23.1153 PROPELLER FEATHERING CONTROLS127
269.-278. RESERVED127
279. SECTION 23.1189 SHUTOFF MEANS127
280.-285. RESERVED127
CHAPTER 5. EQUIPMENT128
286. (RESERVED)128
287. SECTION 23.1301 FUNCTION AND INSTALLATION128
288. (RESERVED)137
289. SECTION 23.1303 FLIGHT AND NAVIGATION INSTRUMENTS137
290. SECTION 23.1305 POWERPLANT INSTRUMENTS138
291. SECTION 23.1307 MISCELLANEOUS EQUIPMENT. (RESERVED)138
292. SECTION 23.1309 EQUIPMENT, SYSTEMS, AND INSTALLATIONS.
(RESERVED)138
293.-299. RESERVED138
300. SECTION 23.1311 ELECTRONIC DISPLAY INSTRUMENT SYSTEMS138
301. SECTION 23.1321 ARRANGEMENT AND VISIBILITY. (RESERVED)138
302. SECTION 23.1322 WARNING, CAUTION, AND ADVISORY LIGHTS.
(RESERVED)138
303. SECTION 23.1323 AIRSPEED INDICATING SYSTEM138
vii
304. SECTION 23.1325 STATIC PRESSURE SYSTEM140
305. SECTION 23.1326 PITOT HEAT INDICATION SYSTEMS. (RESERVED) ... 142
306. SECTION 23.1327 MAGNETIC DIRECTION INDICATOR. (RESERVED)... 142
307. SECTION 23.1329 AUTOMATIC PILOT SYSTEM142
308. SECTION 23.1331 INSTRUMENTS USING A POWER SUPPLY.
(RESERVED)142
309. SECTION 23.1335 FLIGHT DIRECTOR SYSTEMS. (RESERVED)142
310. SECTION 23.1337 POWERPLANT INSTRUMENTS142
311.-318. RESERVED143
319. SECTION 23.1351 GENERAL. (RESERVED)143
320. SECTION 23.1353 STORAGE BATTERY DESIGN AND INSTALLATION. .. 143
321. SECTION 23.1357 CIRCUIT PROTECTIVE DEVICES. (RESERVED)144
322. SECTION 23.1361 MASTER SWITCH ARRANGEMENT144
323. SECTION 23.1367 SWITCHES. (RESERVED)144
324.-328. RESERVED144
329. SECTION 23.1381 INSTRUMENT LIGHTS. (RESERVED)144
330. SECTION 23.1383 LANDING LIGHTS. (RESERVED)144
331.-335. RESERVED144
336. SECTION 23.1411 GENERAL. (RESERVED)144
337. SECTION 23.1415 DITCHING EQUIPMENT. (RESERVED)144
338. SECTION 23.1416 PNEUMATIC DEICER BOOT SYSTEM.
See AC 23.1419-2.144
339. SECTION 23.1419 ICE PROTECTION. See AC 23.1419-2144
340.-349. RESERVED144
350. SECTION 23.1431 ELECTRONIC EQUIPMENT144
351. SECTION 23.1435 HYDRAULIC SYSTEMS. (RESERVED)145
352. SECTION 23.1441 OXYGEN EQUIPMENT AND SUPPLY. (RESERVED)145
353. SECTION 23.1447 EQUIPMENT STANDARDS FOR OXYGEN
DISPENSING UNITS. (RESERVED)145
354. SECTION 23.1449 MEANS FOR DETERMINING USE OF OXYGEN.
(RESERVED)145
355. SECTION 23.1457 COCKPIT VOICE RECORDERS. (RESERVED)145
356. SECTION 23.1459 FLIGHT RECORDERS. (RESERVED)145
357.-364. RESERVED145
CHAPTER 6. OPERATING LIMITATIONS AND INFORMATION146
365. SECTION 23.1501 GENERAL146
366. SECTION 23.1505 AIRSPEED LIMITATIONS146
367. SECTION 23.1507 MANEUVERING SPEED146
368. SECTION 23.1511 FLAP EXTENDED SPEED146
369. SECTION 23.1513 MINIMUM CONTROL SPEED146
370. SECTION 23.1519 WEIGHT AND CENTER OF GRAVITY146
371. SECTION 23.1521 POWERPLANT LIMITATIONS. (RESERVED)146
372. SECTION 23.1523 MINIMUM FLIGHT CREW. (RESERVED)147
373. SECTION 23.1523 MINIMUM FLIGHT CREW147
374. SECTION 23.1524 MAXIMUM PASSENGER SEATING
CONFIGURATION151
375. SECTION 23.1525 KINDS OF OPERATION151
376. SECTION 23.1527 MAXIMUM OPERATING ALTITUDE151
377.-386. RESERVED152
387. SECTION 23.1541 GENERAL152
viii
388. SECTION 23.1543 INSTRUMENT MARKINGS: GENERAL152
389. SECTION 23.1545 AIRSPEED INDICATOR152
390. SECTION 23.1547 MAGNETIC DIRECTION INDICATOR152
391. SECTION 23.1549 POWERPLANT INSTRUMENTS153
392. SECTION 23.1551 OIL QUANTITY INDICATOR. (RESERVED)153
393. SECTION 23.1553 FUEL QUANTITY INDICATOR. (RESERVED)153
394. SECTION 23.1555 CONTROL MARKINGS153
395. SECTION 23.1557 MISCELLANEOUS MARKINGS AND PLACARDS.
(RESERVED)153
396. SECTION 23.1559 OPERATING LIMITATIONS PLACARD.
(RESERVED)153
397. SECTION 23.1561 SAFETY EQUIPMENT153
398. SECTION 23.1563 AIRSPEED PLACARDS153
399. SECTION 23.1567 FLIGHT MANEUVER PLACARD153
400.-409. RESERVED153
410. SECTION 23.1581 GENERAL153
411. SECTION 23.1583 OPERATING LIMITATIONS156
412. SECTION 23.1585 OPERATING PROCEDURES157
413. SECTION 23.1587 PERFORMANCE INFORMATION158
414. SECTION 23.1589 LOADING INFORMATION.
See GAMA Specification 1159
415.-424. RESERVED159
ix
APPENDICES
Appendix Number Figure Number Title Page Number
APPENDIX 1 Power Available A1-1
Figure A1-1 Brake Horsepower Versus Pressure Altitude A1-5 Figure A1-2 Turbocharged Brake Horsepower Versus Altitude A1-7
APPENDIX 2 Climb Data Reduction A2-1
Figure A2-1 Coefficient of Drag Versus Coefficient of Lift A2-3
APPENDIX 3 Minimum Control Speed Extrapolation to Sea Level A3-1
Table A3-1 Flight Test Data A3-3 Table A3-2 Tabulated Thrust Horsepower Available A3-5 Figure A3-1 Thrust Horsepower at Sea Level A3-5
APPENDIX 4 FAR 23 Manuals, Markings and Placards Checklist A4-1
APPENDIX 5 Guide for Preparing Airplane Flight Manual and Pilot’s Operating Handbook Supplements A5-1
APPENDIX 6 Sample Kinds of Operating Equipment List A6-1
APPENDIX 7 Useful Information A7-11
Figure A7-1 U.S. Standard Atmosphere A7-3 Figure A7-2 Temperature Conversion Chart A7-7 Figure A7-3 Determination of Air Temperature in A7-9 Relation to International Standard Atmosphere Figure A7-4 Density/Pressure Altitude Conversion A7-11 Figure A7-5 Compressibility Correction to CAS A7-13 Figure A7-6 Altimeter Error vs. CAS A7-15 Figure A7-7 Temperature Ram Rise A7-17 Figure A7-8 Stall Speed at Bank Angle A7-19 Figure A7-9 Vertical Acceleration Versus Angle of Bank A7-21 Figure A7-10 Flight Path Velocity - Knots (TAS) A7-23
x
Appendix Number Figure Number Title Page Number
Figure A7-11 Takeoff and Landing Crosswind Component
- Knots A7-27
APPENDIX 8 Conversion Factors Table A8-1
APPENDIX 9 Airspeed Calibrations A9-1
Figure A9-1 Error Analysis of Ground Course Method A9-3
Figure A9-2 Ground Airspeed Calibration A9-4 Table A9-1 Sample Speed Course Data and Data Reduction A9-11 Figure A9-3 Sketches of Trailing Static Bomb & the Trailing Static Cone A9-5 Figure A9-4 Typical Position Error Correction Data for an Aircraft A9-6 Figure A9-5 Typical Position Error Corrections Data for an Aircraft A9-7 Figure A9-6 Tower Fly-By Method A9-16 Figure A9-7 Trapped Static Source Schematic A9-21 Table A9-2 Trapped Static Data Reduction A9-23 Figure A9-8 Ground Airspeed Calibration A9-27 Table A9-3 Sample Ground Airspeed Calibration Using a Distance Measuring Unit A9-31
APPENDIX 10 Guide for Determining Climb A10-1 Performance after STC Modifications
xi
ILLUSTRATIONS
The first block of digits in the figure number denotes the associated paragraph number. The second block of digits denotes the figure number within the paragraph.
Figure Number Title Page Number
17-1 Stall Speed 16 17-2 Propeller Coefficients 18 17-3 Zero Thrust 18 21-1 Accelerate-Stop Time Delays 32 23-1 Takeoff Distance - Critical Engine Failure Recognized at V1 40 23-2 Takeoff Distance All Engines Operating 40 23-3 Takeoff Run - Critical Engine Failure Recognized at V1 41 23-4 Takeoff Run - All Engines Operating 41 23-5 Clearway Profiles 42 24-1 Takeoff Segments and Nomenclature 43 24-2 Net Takeoff Flight Path 44 25-1 Observed Data 46 25-2 Rate of Climb vs. Airspeed 47 26-1 Rate of Climb and Speeds 48 27-1 Landing Time Delays 55 51-1 Stick Force Per G 70 70-1 Static Longitudinal Stability Data 73 70-2 Low Speed Instabilities; Normal, Utility, and Acrobatic Airplanes 74 70-3 Low Speed Instabilities; Commuter Airplanes 74 71-1 Static Longitudinal Stability Data over Complete Speed Range 75 72-1 Static Longitudinal Stability Plot (Cruise Condition) 77 100-1 Spin Evaluation Configuration Matrix 93 256-1 Carburetor Air Heat Rise Calculations 125 256-2 Carburetor Air Heat Rise Plots 126
TABLES
The first block of digits in the table number denotes the associated paragraph number. The second block of digits denotes the table number within the paragraph.
Table Number Title Page Number
6-1 Tolerances 3 6-2 Corrections to Standard Value Parameter 3 6-3 Sample Portion of Airspeed Indicator Calibration 5 27-1 WAT Chart 49 51-1 Procedures 69 166-1 Sample of CO-concentration Matrix 107 287-1 Light Duration 131
xii
ADVISORY CIRCULARS Advisory Circular Paragraph Number Title Number
23-7 Substantiation for an Increase in Maximum Weight, Maximum Landing Weight, or Zero Fuel Weight 8a(2) 91-23A Pilot’s Weight and Balance Handbook 9b
23.629-1A Means of Compliance with Section
23.629, “Flutter” 132 23-17 Systems and Equipment Guide for Certification of Part 23 Airplanes
20.118A Emergency Evacuation Demonstration 164 23-16 Powerplant Guide for Certification of Part 23 Airplanes 20-124 Water Ingestion Testing for Turbine Powered Airplanes 255 20-67B Airborne VHF Communications Equipment Installations 287B(1) 25-4 Inertial Navigation systems (INS) 287b(12)(i) 121-13 Self-Contained Navigation Systems 287b(12)(i) (Long Range) 287b(13)(i) 90-79 Recommended Practices and Procedures for the Use of Electronic Long-Range Navigation Equipment 287b(16) 20-121 Airworthiness Approval of Airborne Loran-C Systems for Use in the U.S.
National Airspace System 287b(17) Fuel-Injection, Reciprocating Engines 290c xiii
Advisory Circular Paragraph Number Title Number
23.1419-1 Certification of Small 48b(5) Airplanes for Flight in 337 Icing Conditions 339
20-88A Guidelines on Marking of Aircraft 387c Powerplant Instruments (Displays) 388 20-129 Airworthiness Approval of Vertical Navigation (VNAV) Systems for Use in the U.S. National Airspace System (NAS) and Alaska 20-130A Airworthiness Approval of Navigation or Flight Management Systems Integrating Multiple Navigation Sensors 20-138 Airworthiness Approval of Global Positioning System Navigation Equipment For Use as a VFR and IFR Supplemental Navigation System
23.1309-1C Equipment, Systems, and Installations in 21c(1) Part 23 Airplanes
23.1311-1A Installation of Electronic Displays in Part 23 Airplanes 90-96 Approval of U.S. Operators and Aircraft 287b(11)(i) to Operate Under Instrument Flight Rules (IFR) in European Airspace Designated for Basic Area Navigation (BRNAV/RNP-5) 91-49 General Aviation Procedures for Flight in North Atlantic Minimum Navigation Performance Specifications Airspace xiv
CHAPTER 1. GENERAL
1. SECTION 23.1 APPLICABILITY.
a. Explanation.
(1) Airplane Categories. Section 23.1(a) is introductory and prescribes the airplane categories eligible for certification under 14 CFR Part 23 . Applicants should refer to 14 CFR Part 21 for certification procedures.
(2) Design Data. Section 23.1(b) requires an applicant to demonstrate compliance by some acceptable means even though the FAA has previously certificated an identical alteration for someone else and has the supporting data on file. Design data submitted with an application for certification is not releasable to the public or any other applicant without the consent of the data holder.
b. Procedures. None.
2. SECTION 23.3 AIRPLANE CATEGORIES.
a. Explanation. For Normal/Utility Category as well as for Commuter Category airplanes, stalls (except whip stalls) are approved maneuvers. In this context, approved stalls are to be understood to be stalls as defined in §§ 23.49, 23.201, and 23.203.
b. Procedures. None.
3.-5 RESERVED.
CHAPTER 2. FLIGHT Section 1. GENERAL
6. SECTION 23.21 PROOF OF COMPLIANCE.
a. Explanation.
(1) Determining Compliance. This section provides a degree of latitude for the FAA test team in selecting the combination of tests or inspections required to demonstrate compliance with the regulations. Engineering tests are designed to investigate the overall capabilities and characteristics of the airplane throughout its operating envelope and should include sufficient combinations of weight, center of gravity, altitude, temperature, airspeed, and so forth, necessary to define the envelope and show compliance within. Testing should be sufficiently rigorous to define the limits of the entire operating envelope and establish compliance with the regulations at these points. If compliance cannot be established between these points, additional testing should be conducted to determine compliance. Testing should confirm normal and emergency procedures, performance information, and operating limitations that are to be included in the Airplane Flight Manual (AFM).
(2) Flight Tests. Section 21.35 requires, in part, that the applicant make flight tests and report the results of the flight tests prior to official FAA Type Inspection Authorization testing. After the applicant has submitted sufficient data to the FAA showing that compliance can be met, the FAA will conduct any inspections, flight, or ground tests required to verify the applicant's test results. Compliance may be based on the applicant's engineering data and a spot check or validation through FAA flight tests. The FAA testing should obtain validation at critical combinations of proposed flight variables if compliance cannot be established using engineering judgment from the combinations investigated.
(3) Use of Ballast. Ballast may be carried during the flight tests whenever it is necessary to achieve a specific weight and center of gravity (c.g.) location. Consideration should be given to the vertical as well as horizontal location of the ballast in cases where it may have an appreciable effect on the flying qualities of the airplane. The strength of the supporting structures should be considered to preclude their failure as a result of the anticipated loads that may be imposed during the particular tests.
(4) Flight Test Tolerances. The purpose of the tolerances specified in § 23.21(b) is to allow for variations in flight test values from which data are acceptable for reduction to the value desired. They are not intended for routine test scheduling at the lower weights, or to allow for compliance to be shown at less than the critical condition; nor are they to be considered as allowable inaccuracy of measurement (such as in an airspeed calibration). Where variation in the parameter on which a tolerance is allowed will have an effect on the results of the test, the result should be corrected to the most critical value of that parameter within the operating envelope being approved. If such a correction is impossible or impractical, the average test conditions should assure that the measured characteristics represent the actual critical value.
(5) Following are additional tolerances that are acceptable:
Item Tolerance Airspeed 3 knots or ±3%, whichever is greater Power ±5% Wind (takeoff and, landing tests) As low as possible, but not to exceed approximately 12% VS1 or 10 knots, whichever is lower, along the runway measured at a height of 6 feet above the runway surface. At higher wind velocities, the data may be unreliable due to wind variations and unsmooth flight conditions.
TABLE 6-1 - Tolerances
(6) The following list indicates cases in which corrections to a standard value of the parameter are normally allowed:
Test Weight Density Power Airspeed Other Takeoff Performance X X X X Wind, runway gradient Landing Performance X X — X Wind, runway gradient Stall Speed X — — — Climb Performance X X X X Acceleration VMC — X X —
TABLE 6-2 - Corrections to Standard Value Parameter
(7) Function and Reliability Test. Section 21.35(b)(2) specifies the requirements of Function and Reliability Tests, which are required for aircraft with a maximum certificated weight over 6,000 pounds (lbs) (2730 kilograms (kg)).
b. Procedures.
(1) Test Plan. Efforts should begin early in the certification program to provide assistance to the applicant to ensure coverage of all certification requirements. The applicant should develop a test plan that includes the required instrumentation.
(2) Instrument Calibration. Test instrumentation (transducers, indicators, and so forth) should be calibrated (removed from the airplane and bench checked by an approved method in an approved facility) within 6 months of the tests. When electronic recording devices are used, such as oscillographs, data loggers, and other electronic data acquisition devices, preflight and post-flight parameter recalibrations should be run for each test flight to ensure that none of the parameters have shifted from their initial zero settings. Critical transducers 3
and indicators for critical tests (for example, airspeed indicators and pressure transducers for flight tests to VD) should be calibrated within 60 days of the test in addition to the other requirements mentioned above. The instrument hysteresis should be known; therefore, readings at suitable increments should be taken in both increasing and decreasing directions.
Calibration records, like the one shown below, should be signed by the agent of the repair or overhaul facility doing the work and be available to the test pilot prior to beginning test flying. It should be emphasized that these calibrations must be accomplished at an approved facility. For example, using a leak checker to "calibrate" an airspeed indicator, whether in or out of the airplane, is not acceptable.
SAMPLE PORTION OF AIRSPEED INDICATOR CALIBRATION XYZ INSTRUMENT SERVICE, INC.
ABC CITY AIRPORT APPROVED REPAIR STATION - NO. 1234 8/12/80 P/N 1701DX8-04 S/N AF55-17044
A/S Indicator KNOTS
Master Test
Ascent Indicator Reads
Descent Indicator Reads 40 38.0 39.0 50 49.0 50.5 60 59.5 61.0 70 70.0 71.0 80 80.0 81.0
TABLE 6-3 - Sample Portion of Airspeed Indicator Calibration
(3) Use of Ballast.
(i) Loading. Ballast loading of the airplane can be accomplished several ways to achieve a specific weight and c.g. location as long as the loading remains within the physical confines of the airplane. In flight test work, loading problems will occasionally be encountered, making it difficult to obtain the desired c.g. location. Those cases may require loading in engine compartments or other places not designed for load carrying.
When this condition is encountered, care should be taken to ensure that local structural 4