# TCDS A00014WI: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 7 - Revised: July 29, 2015 - Product: Aircraft, Small Airplane - Certification basis: Part 1, Part 14, Part 21, Part 23, Part 34, Part 36, Part 183 - Registered aircraft: 270, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/94/28/9428e46fa027c805f8cf6817234b1eda612b47a0d21751a8d78f8bfbf307da2e - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C5CAD653EA73D70486257EA400535022.0001 - Page: https://openairdocs.org/tcds/A00014WI ## Models (1) As the data sheet lists them. - 510 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 Rev. No. 7 6 3 4 7 DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION A00014WI Revision 7 Textron Aviation Inc. 510 July 29, 2015 TYPE CERTIFICATE DATA SHEET A000014WI This data sheet which is part of Type Certificate No. A00014WI prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of Title 14 of the Code of Federal Regulations. Type Certificate Holder Textron Aviation Inc. One Cessna Boulevard P.O. Box 7704 Wichita, Kansas 67277 Type Certificate Holder Record: Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 I. Model 510, (Normal Category), Approved September 8, 2006 Engines: Two Pratt & Whitney Canada PW615F-A turbofans Engine TC #E00073EN Certified September 8, 2006 Fuel: Jet A, Jet A-1, JP-8, or PRC National Standard No. 3 Jet fuel Engine Limits Static thrust standard day, sea level: Takeoff 1,460 lb. Max. permissible engine rotor operating speeds (Takeoff and Maximum Continuous): N1(fan) 100% (100% = 21,830 rpm) N2 (Gas Gen.) 100% (100% = 44,040 rpm) Max. permissible interturbine gas temperatures: Takeoff 830 Degrees C Max. continuous 830 Degrees C Transient (starting 5 sec.) 862 Degrees C Transient (operation 20 sec) 862 Degrees C Airspeed limitations: VMO (maximum operating) Sea level to 27,120 ft. 250 KIAS MMO above 27,120 ft. 0.63 Mach VFE (maximum flap extended) 15 degrees (takeoff & approach) 185 KIAS 30 degrees (landing) 150 KIAS VMCA (minimum control airspeed) Air 0 degrees (takeoff) 92 KIAS 15 degrees (takeoff & approach) 81 KIAS A00014WI Page 2 of 5 Rev. 7 I. Model 510 (cont’d) Airspeed limitations: (cont’d) VMCG (minimum control speed) Ground 73 KIAS VLO (landing gear operating) Extend 250 KIAS Retract 185 KIAS VLE (landing gear extended) 250 KIAS VSB (speedbrake extended) Any speed with or without flaps Maximum autopilot operating speed 250 KIAS or 0.63 Mach Maximum tire ground speed 160 knots C.G. Range Design C.G. Limits: Forward Limits: Linear variation from 287.04 in. aft of datum (21.32% MAC) at 8730 lb. to 285.59 in. aft of datum (19.00 % MAC) at 6927 lb.; 285.59 in. aft of datum (19.00 % MAC) from 6927 lb. to 5550 lb. Aft Limits: 292.46 in. aft of datum (30% MAC) from 8730 lb. to 5314 lb. Landing Gear retracting moment (-1964.84) in-lb. MAC: 62.51 in. (L.E. of MAC at +273.71 in. aft of datum) Maximum Weight: Takeoff 8,645 lb. Landing 8,000 lb. Zero Fuel 6,750 lb. Ramp 8,730 lb. Minimum Crew for all Flights (See note 5 for cockpit equipment/arrangement restrictions): One pilot (in the left pilot seat) plus additional equipment as specified in the Kinds of Operations Equipment List (KOEL) contained in the Limitations Section of the FAA Approved Airplane Flight Manual OR One pilot and one copilot No. of Seats: Maximum of six occupants Maximum Baggage: Nose compartment 320 lb. (+120.10 in. aft of datum) Tailcone total 300 lb. (+356.33 in. aft of datum) Fuel Capacity (usable): Total usable fuel 2,580 lbs. Two wing tanks with 1,290 lbs. usable each; (see NOTE 1 for unusable) +291.97 in. aft of datum Oil Capacity (total): Tank mounted on each engine: 5.12 quarts (4.85 liters) total each engine; +363.11 in. aft of datum; (see NOTE 1) Maximum Operating Altitude: 41,000 ft. A00014WI Page 3 of 5 Rev. 7 I. Model 510 (cont’d) Control Surface Movements: Elevator Up 25 +0/-1 degrees Down 15 +1/-1 degrees Elevator Trim Tab Up 4.5 +1/-1 degrees Down 20 +1/-1 degrees Rudder Right 35 +1/-1 degrees Left 35 +1/-1 degrees Rudder Trim Tab Right 20 +2/-1 degrees Left 20 +2/-1 degrees Aileron Neutral Pos (TE up) 2 +0.5/-0.5 degrees Up (from neutral) 23 +1/-1 degrees Down (from neutral) 18.5 +1/-1 degrees Aileron Trim Tab Up 21 +2/-1 degrees Down 21 +2/-1 degrees Wing Flap Up 0 degrees (Utilizing the Flap Streamline Fixture per AMM) TO/APP 15 +1/-1 degrees Land 30 +1/-1 degrees Speedbrakes Upper 0 to 59.5 +1/-1 degrees Lower 0 to 62.5 +1/-1 degrees See Airplane Maintenance Manual (AMM) for rigging instructions. Serial Numbers Eligible: 510-0001 and On Datum: 143.7 in. forward of the jig point (nose jack pad location). Leveling Means: Longitudinal – In board crew seat rails at FS 196.00. Lateral - In board crew seat rails at FS 196.00. Certification Basis - Model 510: (1) Part 23 of Title 14 of the Code of Federal Regulations effective February 1, 1965, as amended by Amendments 23-1 through 23-54; (2) Part 36 of Title 14 of the Code of Federal Regulations effective December 1, 1969, as amended by Amendments 36-1 through 36-26 (3) Part 34 of Title 14 of the Code of Federal Regulations effective September 10, 1990, as amended by Amendments 34-1 through 34-3; (4) Compliance with the Noise Control Act of 1972; (5) Special Conditions as follows: (a) 23-193-SC, Turbofan Engines and Engine Location (b) 23-158-SC, Protection of Systems for High Intensity Radiated Fields (HIRF) (c) 23-181-SC, Flight Performance, Flight Characteristics, and Operating Limitations; items 1 through 24 (d) 23-192-SC, Full Authority Digital Engine Control (FADEC) System A00014WI Page 4 of 5 Rev. 7 I. Model 510 (cont’d) Certification Basis - Model 510: (cont’d) (6) Equivalent level of safety as follows: (a) ACE-05-8: 14 CFR § 23.1305(c)(5) and (c)(2), and § 23.1549, digital indication of N2 and FF. (b) ACE-05-9: 14 CFR § 23.1555(d)(1), usable fuel quantity marking on the Cessna Model 510. (c) ACE-05-10: 14 CFR § 23.807(e), Emergency Exit Water Barrier on the Cessna 510 Mustang (d) ACE-05-11: 14 CFR § 23.841(b)(6), Cabin Pressurization for High Altitude takeoff and Landing Operations (e) ACE-05-12: 14 CFR § 23.1435(a)(2), Hydraulic Pressure Indication (f) ACE-05-23: 14 CFR § 23.1447(e), Passenger Oxygen Dispensing Units for Cessna Model 510 (g) ACE-05-28: 14 CFR § 23.841(a), Cabin Pressurization (h) ACE-06-03: 14 CFR § 23.1545(b)(4), Airspeed indicator (i) ACE-07-03: 14 CFR § 23.841(a) & § 23.1301(d), Cabin Pressure Control System (j) ACE-09-04: 14 CFR § 23.1326, Pitot Heat Indication (7) Compliance with ice protection has been demonstrated in accordance with 14 CFR § 23.1416 and 23.1419. (8) Compliance with 14 CFR 23.1141(e) is in accordance with ACE-05-24, Guidance on compliance with 14 CFR 23.1141(e) for the Cessna Model 510 aircraft (Project # TC3801WI-A). Changes affecting 14 CFR 23.1141(e), should be coordinated with the Wichita Aircraft Certification Office. Application for type certificate dated December 31, 2003. Type Certificate A00014WI issued September 8, 2006, obtained by the manufacturer using Delegation Option Authorization Procedures of Part 21 of Title 14 of the Code of Federal Regulations. The Model 510 is defined by Cessna Airplane Assembly Drawing Number 7000000-1. Production Basis – Model 510: Production Certificate No. 4 issued November 22, 2006, and Delegation Option Authorization No. DOA- 230594-CE authorized to issued Airworthiness Certificates under Delegation Option Authorization Procedures of Part 21 of Title 14 of the Code of Federal Regulations through January 4, 2009. Effective January 5, 2009: Organization Designation Authorization No. ODA-100129-CE authorized to issue Airworthiness Certificates under Organization Designation Authorization Procedures of Part 183 of Title 14 of the Code of Federal Regulations. The Basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. NOTE 1. Current weight and balance information, including list of equipment included in certificated empty weight, and loading instructions are provided for each airplane in the FAA Approved Airplane Flight Manual (AFM) at the time of original certification. The certificated empty weight and corresponding center of gravity location must include: Unusable fuel 31.40 lbs. at +291.16 in Full oil 20.2 lbs. at +363.11 in. Hydraulic Fluid 10.23 lbs. at +192.45 in. NOTE 2. Airplanes must be operated according to the FAA Approved Airplane Flight Manual (AFM), part number 510FM-00 (or later approved revisions). Required placards and markings are listed in Chapter Eleven (11) of Maintenance Manual, part number 510MM00. NOTE 3. See Maintenance Manual, Chapter Four (4), "Airworthiness Limitations" for inspections, mandatory retirement life information, and other requirements for continued airworthiness. A00014WI Page 5 of 5 Rev. 7 I. Model 510 (cont’d) NOTE 4. All replacement seats (crew and passenger), although they may comply with TSO C127, must also be demonstrated to comply with installation requirements into the aircraft listed in 14 CFR §§23.2, 23.561, 23.562, and 23.785. The foam cushion buildup of all seats (crew and passenger) may not be altered. Any deviations in the foam construction or stiffness must be demonstrated by test to comply with the 14 CFR 23.562 paragraph. NOTE 5. Approval for operation with a minimum crew of one pilot is based upon the cockpit equipment installation and arrangement evaluated during FAA certification testing. No significant changes may be made to the installed cockpit equipment or arrangement (EFIS, autopilot, avionics, etc.), except as permitted by the approved MMEL, without prior approval from the responsible Aircraft Certification Office. NOTE 6. S/N 510-001 and On: All airplanes are equipped with Garmin G1000 dual RVSM capable Air Data Computers and pilot’s and copilot’s Primary Flight Displays as standard equipment. Each operator must obtain RVSM operating approval directly from the FAA. NOTE 7. The Model 510 is approved for One Engine Inoperative 10 minutes thrust capability with the Pratt & Whitney Canada PW615F-A turbofan engine, per FAA Policy Memo “Project Specific Policy on Approval for 10-Minute Rated Takeoff Thrust during Takeoff with One-Engine Inoperative (OEI) under 14 CFR Part 23 and 14 CFR Part 33 for Cessna Model 510 Airplane with PW615F-A Engines”, dated August 15, 2006, from Standards Office, Small Airplane Directorate and Standards Office, Engine and Propeller Directorate. NOTE 8. The System Safety Assessment process has identified mandatory maintenance actions, which must be performed at specific intervals to compensate for latent failures. A list of those actions is contained in report RL-510-176, and cannot be changed without participation from the certificating ACO. This document has influenced certain maintenance actions documented in Airworthiness Limitations section (Chapter 4) of the maintenance manual. Those particular items cannot be changed without participation from the certificating ACO. NOTE 9. The following serials are manufactured under the name Cessna Aircraft Company: 510-0001 thru 510- 0460. NOTE 10. Company name change effective 7/19/15. The following serials are manufactured under the name Textron Aviation Inc.: 510-0461 and On. --- END --- ``` ## ADs (2, in force first) - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2018-07-13](https://openairdocs.org/ad/2018-07-13): Landing Gear · Textron 510, 680 and 680A. Effective May 15, 2018 ## Registered aircraft by registry model (OpenAirDocs) - [Cessna 510](https://openairdocs.org/model/cessna-510): 264 aircraft (registry codes 2076617, 2076621) - [Textron 510](https://openairdocs.org/model/textron-510): 6 aircraft (registry code 2076627) ## STCs approved under this data sheet (24) - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA12345IB](https://openairdocs.org/stc/SA12345IB): Replacement of the Halon Type 1211 portable fire extinguisher with the Halotron BrX portable fire extinguisher. Cessna Duesseldorf Citation Service Center GmbH - [STC SA02017WI](https://openairdocs.org/stc/SA02017WI): The Installation of the Parker-Meggitt iPRESS™ System. 3S Certification LLC - [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc. - [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica Cellular Module (avCM. Aircraft Systems and Manufacturing Inc. - [STC SA04747NY](https://openairdocs.org/stc/SA04747NY): Installation of Mustang Skystep Assembly. SkyWay Group Inc. - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics - [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH - [STC SA02272SE](https://openairdocs.org/stc/SA02272SE): Installation of a Crane Aerospace & Electronics Tire Sensor Assembly. ELDEC Corporation - [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King) - [STC SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC - [STC SA01896WI](https://openairdocs.org/stc/SA01896WI): Garmin G1000 Integrated Avionics System hardware and software updates including optional Flight Stream 510 Data Required.... Garmin International Inc - [STC SA02075SE](https://openairdocs.org/stc/SA02075SE): Installation of a Mid-Continent MD835( ) Lithium Ion Battery. Mid-Continent Instrument Co. Inc. - [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS - [STC SA02678LA](https://openairdocs.org/stc/SA02678LA): Modification to upgrade the existing Mode S Transponder system by installing the ACSS NXT-600 Transponder with ADS-B Out and optionally install the ACSS NXG-900 GPS as the position source for ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC - [STC SA02897CH](https://openairdocs.org/stc/SA02897CH): Install air ambulance conversion in accordance with Spectrum Aeromed Master Drawing List 6053DL, No Revision, dated April 21, 2010, or later FAA approved revisions.. Spectrum Aeromed LLC dba Spectrum Aeromed - [STC SA02653LA](https://openairdocs.org/stc/SA02653LA): Replacement of original equipment main battery with Concorde RG-390E/30 Valve Regulated Lead-Acid battery. Concorde Battery Corporation - [STC SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics - [STC SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc - [STC SA01695WI](https://openairdocs.org/stc/SA01695WI): Installation of Airfield Technology AT-950 Flight Inspection System (FIS). Duncan Aviation Inc - [STC SA00730DE](https://openairdocs.org/stc/SA00730DE): Installation of a monorail sunvisor system in accordance with Drawing List 1970000-DL, Revision D, dated April 8, 2011, FAA approved May 24, 2011, or later FAA approved revision.. Rosen Sunvisor Systems LLC - [STC SA00712DE](https://openairdocs.org/stc/SA00712DE): Modification of the aircraft interior to allow for two configurations, 1.) Observer configuration and 2.) back to the Type Certificated standard Executive configuration in accordance with Straight Flight Master Drawing List Document No. 4979-MDL-01, Revision B, dated June 15, 2010, or later FAA approved revision.. Straight Flight Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.