# TCDS T00015WI: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 9 - Revised: June 29, 2023 - Product: Aircraft, Large Airplane - Certification basis: Part 25 - Registered aircraft: 175, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/79/42/794257f7262a8ff039e0afada08ad34442423962fa52be5e2120781c4f667d98 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID135832854220230630133052.0001 - Page: https://openairdocs.org/tcds/T00015WI ## Models (1) As the data sheet lists them. - 700 ## 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 6 Rev. No. 9 6 4 9 7 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00015WI Revision 9 Textron Aviation Inc. 700 June 29, 2023 TYPE CERTIFICATE DATA SHEET NO. T00015WI This data sheet which is part of Type Certificate No. T00015WI prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 I. Model 700 (Transport Categor y) Approved September 21, 2019 Engines Two Honeywell AS907-2-1S turbofans Fuel FUEL TYPE SPECIFICATION Jet A ATSM D1655 Jet A-1 ATSM D1655 JP-5 MIL-DTL-5624 JP-8 MIL-DTL-83133 Russian TS-1 GOST 10227 Russian RT GOST 10227 Ukraine TS-1 GSTU 320-00149943.011 Ukraine RT GSTU 320-00149943.007 Chinese No. 3 GB 6537 Engine Limits Static thrust standard day, sea level: Takeoff 7,665 lb. Maximum Continuous 7,428 lb. Maximum permissible engine rotor operating speeds: N 1 (fan) 9,830 RPM (96.79%) Takeoff 9,800 RPM (96.49%) Continuous N 2 (Gas Gen.) 27,714 RPM (98.62%) Takeoff 27,599 RPM (98.22%) Continuous 28,075 RPM (99.9%) Transient (20 sec. max) Maximum permissible interturbine gas temperatures ºF (ºC): Takeoff 1,751 (955) Max. continuous 1,742 (950) T00015WI Page 2 of 6 Rev. 9 I. Model 700 (cont’d) Airspeed Limitations: Vmo (maximum operating speed) Sea Level (0 ft.) 290 KIAS (289 KCAS) 8,000 ft. 305 KIAS (304 KCAS) Airspeed to be linearly interpolated from 0 ft. – 8,000 ft. 8,000 ft. to 29,375 ft. 325 KIAS (324 KCAS) Mmo above 29,375 ft. 0.84 M I (0.838 MACH calibrated) Va (Maneuvering speed sea level) 39,500 lb. 222 KIAS (221 KCAS) See AFM for variations with weight and altitude. VRA (Rough air speed) 235 KIAS (234 KCAS)/ 0.75 M I (0.747 MACH calibrated) Flap extension speeds V FE (Up (0°) to 1 (7°) extension) 250 KIAS (249 KCAS) V FE (1 (7°) to 2 (15°) extension) 230 KIAS (229 KCAS) V FE (2 (15°) to Full (35°) extension) 180 KIAS (179 KCAS) V MCA (Minimum control speed) Air Flaps 1 100 KIAS (100 KCAS) V MCA (Minimum control speed) Air Flaps 2 96 KIAS (96 KCAS) V MCL (Minimum control speed) Landing Flaps 2 102 KIAS (102 KCAS) V MCL (Minimum control speed) Landing Flaps Full 91 KIAS (91 KCAS) V MCG (Minimum control speed) Ground Flaps 1 80 KIAS (80 KCAS) V MCG (Minimum control speed) Ground Flaps 2 80 KIAS (80 KCAS) V LO (Landing gear operating speed) 230 KIAS (229 KCAS) V LE (Landing gear extended speed) 230 KIAS (229 KCAS) V SB (Max speed brakes extension speed) No Limit Maximum tire ground speed 195 knots C.G. Range (Landing Gear Extended) Design C.G. Limits: Forward: Linear variation from 34.00% MA C at 22,400 lbs. to 30.57% MAC at 24,000 lbs. Linear variation from 30.57% MAC at 24,000 lbs. to 26.30% MAC at 28,000 lbs. Linear variation from 26.30% MAC at 28,000 lbs. to 24.00% MAC at 32,000 lbs. 24.00% MAC at 32,000 lbs. to 36,000lbs. Linear variation from 24.00% MAC at 36,000 lbs. to 25.50% MAC at 39,700 lbs. Takeoff Forward 25.42% MAC at 39,500 lbs. Aft: 40.63% MAC at 22,400 lbs. to 23,000 lbs. Linear variation from 40.63% MAC at 23,000 lbs. to 31.95% MAC at 30,000 lbs. 31.95% MAC at 30,000 lbs. to 37,500 lbs. Linear variation from 31.95% MAC at 37,500 lbs. to 30.99% MAC at 39,700 lbs. Takeoff Aft 31.07% MAC at 39,500 lbs. Landing Gear retracting moment -6,904 in-lbs. Empty Wt. C.G. None Range MAC 118.99 in. (L.E. of MAC at +402.02 in. aft of datum) Rev. 9 Page 3 of 6 T00015WI I. Model 700 (cont’d) Maximum Weight Takeoff 39,500 lbs. Landing 33,500 lbs. Zero Fuel 26,800 lbs. Ramp 39,700 lbs. Minimum Crew Two (2) Pilots for all flights Number of Seats Maximum Thirteen (two crew plus eleven passenger seats) Maximum Baggage Aft Cabin Bagga ge Compartment: 1,000 lbs. Fuel Capacity Total usable fuel 14,511 lbs. (2,166 gal). Two wing tanks with 7,255.5 lbs. (1,083 gal) usable each (usable) (See NOTE 1 for unusable); +422.39 in. aft of datum. Oil Capacity Tank mounted on each engine: 1.6 quarts us able RH engine, 1.7 quarts usable LH engine; (usable) +593.29 in. aft of datum (See NOTE 1) Maximum Operating 45,000 ft. Altitude Control Surface (Up/Down/Left/Right refers to mo tion of the trailing edge of each control surface) Movements Elevator Up 16.0 +1/-0 degrees Down 11.5 +/-0.5 degrees Elevator Tab Up 10.4 +/-0.5 degrees Down 14.4 +/-0.5 degrees Rudder Right 32.0 +1/-0 degrees Left 32.0 +1/-0 degrees Horizontal Stabilizer Up 7.5 +0.5/-0 degrees Down 2.5 +0.5/-0 degrees Aileron Left and Right Up 15.0 +/-0.5 degrees Down 15.2 +/-0.5 degrees Aileron Servo Tab Up 12.5 +/-0.5 degrees Down 11.6 +/-0.5 degrees Wing Flap Outboard Up 0.0 +/-0.25 degrees 1 7.0 +/-1.0 degrees 2 15.0 +/-1.0 degrees Full 35.0 +/-1.0 degrees Wing Flap Inboard Up 0.0 +/-0.25 degrees 1 7.8 +/-1.0 degrees 2 16.3 +/-1.0 degrees Full 36.2 +/-1.0 degrees Groundspoilers Panels 3, 4 60.0 +1/-2.0 degrees Panels 1, 2, 5, 6 60.0 +1.0/-4.0 degrees Roll Spoilers/Speedbrakes Full extend in air, flaps ≤ 15° 35.0 +/-1.0 degrees Full extend in air, flaps > 15° 17.5 +/-1.0 degrees See Airplane Maintenance Manual for rigging instructions. Serial Nos. Eligible 700-0001 and On Datum 135.52 in. forward of the nose jack point. Leveling Means Longitudinal: Place level directly on the inboa rd crew seatrail and ensure it is parallel with the seatrail. Lateral: Place the leveling bar across the inboard crew seatrails flush against the back of the rails at approximately FS 160.00 in. T00015WI Page 4 of 6 Rev. 9 I. Model 700 (cont’d) Certification Basis: 1. 14 CFR Part 25, effective February 1, 1965, as Amended by 25-1 through 25-139, 25-141, and 25-143. 2. Special Conditions. The following special conditions apply: SC No. Subject 25-648-SC Airplane Electronic-System Security Protection from Unauthorized External Access 25-649-SC Isolation of Airplane Electronic System S ecurity Protection from Unauthorized Internal Access 25-669-SC Design Roll Maneuver Condition 25-681-SC Non-Rechargeable Lithium Battery Installation 25-700-SC Use of Automatic Power Reserve (APR) for Go-Around Performance Credit 25-721-SC Side-Facing Seats – Inst allation of Airbag Systems 25-723-SC Interaction of Systems and Structures 25-724-SC Occupant Protection for Side-Facing Seats 25-728-SC Installed Rechargeable Lithium Batteries 25-738-SC Operation Without Normal Electrical Power 3. Equivalent Safety Findings. The F AA made the following equivalent level of safety (ELOS) findings for the subject regulations: ELOS MEMO NO REGULATION SUBJECT TXTAV-014180-A-04 25.807(i) Ditching Emergency Exits for Passengers TXTAV-014180-A-15 25.811(d)(1), 25.812(b)(1) Emergency Exit Marker & Locator Signs TXTAV-014180-P-05 25.1141(f)(2) Powerplant Valve Indication TXTAV-014180-P-10 14 CFR Part 25 subparts E, F, G applicable to APU installations Auxiliary Power Unit (APU) Certification Requirements TXTAV-014180-P-13 25.1549(a)(b)(c) Digital-Only Display of Engine Operating Parameters TXTAV-014180-P-15 25.1203(a) Turbine Tailpipe Fire Detection TXTAV-014180-P-17 25.933(a)(1) Flight Critical Thrust Reverser TXTAV-014180-P-37 25.904, I25.5(b)(3), I25.6(a) Lack of Functional Indication of ATTCS Operation TXTAV-014180-SE-03 25.1303(a)(3) Electronic St andby Direction Indicator (Compass) TXTAV-014180-SM-01 25.671(c)(2) Flight Control System Failure Criteria TXTAV-014180-SM-04 25.841(a)(b)(6) Cabin Pressurization – High Elevation Takeoff and Landing Operations (See NOTE 8 for additional information concerning high elevation operations) TXTAV-014180-SM-05 25.831(g) Acceptable High Temperature Physiological Environment During Failure Conditions TXTAV-014180-SM-10 25.783(d)(2) Cabin Entry D oor Latching and Locking Independence TXTAV-014180-SM-11 25.783(d)(2) Nose Access D oors Latching and Locking Independence TXTAV-014180-SM-12 25.841(b)(1), 25.843(b)(1) Cabin Outflow Valve 4. Exemptions. The following exem ptions from 14 CFR Part 25 apply: a. Exemption No. 16838, dated 15 June 2016, Partial Grant of Exemption to §25.809(a) for relief to the requirement for a means to permit viewing of the likely areas of evacuee ground contact prior to opening the overwing exit. b. Exemption No. 17119, dated 30 September 2016, Partial Grant of Exemption to §25.813(e), door between passenger compartments (for private operations only - not for hire, not for common carriage). c. Exemption No. 17119A, dated 15 October 2019, Grant of Exemption to §25.813(e), door between passenger compartments (for either private, not for hire operations, or on demand commercial operations). Rev. 9 Page 5 of 6 T00015WI I. Model 700 (cont’d) Certification Basis: (cont’d) d. Exemption No. 17610, dated 23 October 2017, Grant of Exemption to §25.981(a)(3) from lightning protection aspects of fuel tank structure and systems. e. Exemption No. 17623, dated 27 October 2017, Grant of Exemption to §25.815 Aisle Width. f. Exemption No. 17941, dated August 16, 2018, Partial Grant of Time-Limited Exemption to §25.981(b) Fuel Tank Fleet Average Flammability Exposure (effective for Provisional TC Only). g. Exemption No. 18263, dated June 26, 2019, Grant of Exemption from criteria of §§ M25.1 and M25.2(b) of appendix M as they related to the requirements of 14 CFR 25.981(b). 5. Additional Design Requirement s and Conditions. The following design details or information must be maintained to ensure that an unsafe design condition is not present: a. Inflight Engine Restart. Compliance shown by test. Any modifications to the associated Airplane Flight Manual (AFM) procedures require evaluation to ensure an unsafe condition is not introduced. Changes in the engine design affecting engine restart require aircraft-level evaluation. b. Engine Damage from Wing Ice Caused by Cold Soaked Fuel. The AFM must specifically address potential hazards associated with ice that may form on the wings due to cold soaked fuel including an AFM pre-flight inspection procedure (with inspection criteria based on fuel temperature and observed ambient weather conditions) must detect and address any ice accumulation on the upper wing surface after refueling. The FAA must evaluate any modification to this AFM procedure for a tactile check for wing ice to ensure an unsafe condition is not introduced. 6. Optional Design Regulations. The Model 700 complie s with the following optional design regulations: a. Ice protection in accordance with §25.1419 at Amendment 25-129. 7. 14 CFR Part 26, Amendments 26-0 through 26-6 are not applicable to the Model 700. 8. 14 CFR 25.801 ditching not complied with. 9. Additional requirements when a vision system with transparent display (HUD) is installed: §25.773(e) at Amendment 25-144. Environmental Standards: 1. Noise Standards: a. 14 CFR Part 36, as amended by Amendments 36-1 through 36-31. b. A finding of regulatory adequacy pursuant to the “Noise Control Act of 1972” (49 USC Section 44715). 2. Fuel Venting and Exhaust Emissions Standards: 14 CFR Part 34, as amended by Amendments 34-1 through 34-5A. Production Basis: Production Certificate No. 4 amended to add Model 700 effective October 11, 2019. See NOTE 12 for airplane serial effectivity of Production Certificate No. 4 on new airplane serials. Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. T00015WI Page 6 of 6 Rev. 9 Data Pertinent to all Models NOTE 1. Current weight and balance information, incl uding list of equipment included in certificated empty weight, and loading instructions are provided for each airplane at the time of original certification. The certificated empty weight and correspondi ng center of gravity location must include: Unusable Fuel 83.08 lb. at +417.07 in. Full Oil 23.25 lb. at +593.29 in. Hydraulic Fluid 77.53 lb. at +487.89 in. NOTE 2. Airplanes must be operated according to the F AA Approved AFM, part numbers 700FM-00 AFM Volume 1, 700NP-00 AFM Volume 2 Normal Procedures, and 700EAP-00 AFM Volume 3 Emergency/ Abnormal Procedures (or later FAA approved revisions). All placards required by either the FAA Approved AFM, the applicable operating rules, or the certification basis, must be installed as specified for this Type Certificate via Parts List 7400100, Airplane Assembly. A useful placarding reference is the Textron Aviation Illustrated Parts Catalogue (IPC). Any discrepancies identified between the IPC and an aircraft under inspection needs to be reconciled using the previously stated parts list. NOTE 3. See Maintenance Manual, Chapter 4, "Airworthine ss Limitations" for inspections, mandatory retirement life information, and other requirements for continued airworthiness. NOTE 4. Aircraft definition for Type Certifi cate is Parts List 7400100, Airplane Assembly. NOTE 5. Certification Maintenance Requi rements (CMR) are found in Maintenance Manual, Chapter 4. Engineering approval of the CMR’s is documented in the Textron Aviation System Safety Assessment reports. NOTE 6. DELETED NOTE 7. DELETED NOTE 8. Flight crew use of the alerti ng system during high elevation airport takeoff and landing operations may result in non-compliance with §91.211(a)(1), 121.329(b)(1)(2), and 135.89(b) requirements for flight crew use of supplemental oxygen. NOTE 9 The Model 700 has been approved for high altitude operations (altitudes above 41,000 ft) by compliance with certain Part 25 sections. To ensure the compliance is maintained, any modifications to the pressure vessel must be approved in accordance with the requirements as shown in the appropriate certification basis. To ensure pressurization compliance is not affected, this includes modifications which could result in a pressure vessel opening, either crack-growth or antenna loss, greater than 5.5 sq. in. NOTE 10 The Model 700 has been shown to meet the airworthiness requirements for operations in RVSM airspace. All serial numbers are eligible. Each operator must obtain RVSM operating approval directly from the FAA. NOTE 11. The Model 700 received a Provisional Type Cer tificate on December 4, 2018, that was subsequently cancelled when the Type Certificate was issued on September 21, 2019. NOTE 12. The following serials will be certificat ed TC only: 700-0001 through 700-0004, 700-0008, 700-0009, and 700-0011. Production Certificate No. 4 applies to Model 700 serial numbers: 700-0007, 700-0010, 700-0012 and On. NOTE 13. The Model 700 is configured with fuel tank vent system protection approved by the FAA administrator, meeting the requirements of §121.1119(b) and §129.119(b). NOTE 14. Required Equipment. The basic required equipment prescribed in the applicable airworthiness requirements (see certification basis) must be installed in the aircraft. Only hand fire extinguishers that use water and U.S. – UL 5B:C – Halotron BrX (2-BTP), C3H2BrF3, CAS Number 1514 82 5 OR U.S. – UL 2A:10B:C – Halotron (HCFC Blend-B), C2HCI2BrF3, CAS Number 306-83-2 are approved for use. No airplanes may have a combination of Halotron BrX AND Halotron I hand fire extinguishers installed. --- END --- ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Textron 700](https://openairdocs.org/model/textron-700): 175 aircraft (registry code 2076819) ## STCs approved under this data sheet (11) - [STC ST12145SE](https://openairdocs.org/stc/ST12145SE): Installation of Starlink Aviation System. AeroMech Incorporated - [STC ST04736NY](https://openairdocs.org/stc/ST04736NY): True Blue TS28 Emergency Battery Power Supply Replacement. Aerospace Design and Compliance LLC - [STC ST00415BO](https://openairdocs.org/stc/ST00415BO): Installation of an NVIS/NVG compatible lighting system and infrared capable exterior lighting. ATI Engineering Services LLC - [STC ST04575AT](https://openairdocs.org/stc/ST04575AT): Installation of the Rockwell Collins ALT-1000+/ -4000+ with 5G Filtering. Chippewa Aerospace Inc. - [STC ST02812LA](https://openairdocs.org/stc/ST02812LA): Installation of the Honeywell EDG-100 Connected Engine Data Access System. Honeywell International Inc. - [STC ST04572CH](https://openairdocs.org/stc/ST04572CH): Installation of an Airborne Terminal System and a Ka Radome. StandardAero Business Aviation Services LLC - [STC ST02746SE](https://openairdocs.org/stc/ST02746SE): Installation of external aerodynamic modifications, interior furnishings and equipment, including provisions for additional non-essential systems. Textron Aviation Inc. - [STC ST02694SE](https://openairdocs.org/stc/ST02694SE): Group Reduced Vertical Separation Minimum (RVSM) airworthiness approval. AeroMech Incorporated - [STC ST04211NY](https://openairdocs.org/stc/ST04211NY): Installation of of NSM UNIFIS 3000 G2 Flight Inspection System. Aerospace Design & Compliance LLC - [STC ST01971WI](https://openairdocs.org/stc/ST01971WI): Installation of the Garmin G5000 Software Changes & GH-3900 Standby Configuration Updates. Textron Aviation Inc. - [STC ST01027DE](https://openairdocs.org/stc/ST01027DE): Installation of MarathonNorco Aerospace Inc Nickel Cadmium battery in place of existing Nickel Cadmium main aircraft battery/batteries. MarathonNorco Aerospace 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.