TCDS A21NM

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A21NM Revision 17 Airbus Defense and Space S.A. Model CN-235 CN-235-100 CN-235-200 CN-235-300 C-295 February 19, 2025 TYPE CERTIFICATE DATA SHEET NO. A21NM This data sheet, which is part of Type Certificate No. A21NM, 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 Airbus Defense and Space S.A (formerly known as Construcciones Aeronauticas, S.A.) Avenida de Aragon 404 28022 Madrid, Spain I. Model CN-235 (Transport Category Airplane) approved 3 December, 1986: Engines Two (2) engines - General Electric Company, Model CT7-7A, free turbine turboprop.* Power turbine/propeller reduction gearing 15.9:1. Fuel (a) Fuels shall conform to the specifications listed or to subsequent revisions thereof: Designation Specification Jet A, A-1, B ASTM D1655 JP-4, JP-5 MIL-T-5624 JP-8 MIL-T-83133 (b) For approved fuel additives, see General Electric Company jet fuel specification D50TF2, current approved revision. Anti-icing additives to specification MIL-I-27686E may be used to a concentration not in excess of 0.15% by volume. *CT7-7A engines are to be equipped with redundant propeller speed sensors (NP) per General Electric Engineering Change Number 270598 (General Electric Service Bulletin 72-112 “Engine-General-Installation of PGC drive shaft speed sensor on CT7-7A Turboprop Engine”) or FAA engineering approved equivalent. Engine Limits The Maximum Continuous and Takeoff Static Sea Level rating at ISA: Condition Maximum Time Limit Maximum Torque (FT - LBS) Maximum ITT (°C) Maximum NH (RPM) Rated Shaft Horsepower (HP) Takeoff Max. Cont. Transient Starting 5 min. Cont. 12 sec. 413 413 475 930 917 960 950 45,000 44,720 47,000 1700 1700 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev. No. 17 6 6 14 10 6 6 10 14 10 6 6 10 14 6 6 10 14 Page No. 19 20 21 22 23 24 25 26 27 28 29 30 31 Rev. No. 10 13 13 13 14 17 13 17 13 13 13 15 16 2 of 31 A21NM Propeller and Propeller Limits Two (2) Propellers - Hamilton Standard, Model 14RF-21. Maximum Propeller Operating Speed: 1384 RPM (100% indicated NP Overspeed Limit: 103% (indicated NP) Blades: Four (4), model RFC11L1-0C Diameter: 132.24 in. maximum, 131,94 in. minimum NOTE: No further reduction permitted. Blade Angle measured at 42 in. - radius station: Ground Idle -3.7° ± 1.0° Maximum Reverse -12.4° ± 1.3° Feather 80.8° ± 0.5° Flight Idle 16.7° ± 0.8° Propeller Spinner: Hamilton Standard, P/N 784920-1 or 790185-1 Propeller Deicer: Included in blade P/N Airspeed Limits (IAS) Unless otherwise noted below, speeds are indicated airspeeds in knots: VNO (Maximum Operating) Sea Level 240 knots 20,000 ft. 210 knots 25,000 ft. 190 knots Straight line variation between points. VA (Design, Maneuvering) Sea Level to 25,000 ft. 160 knots VFE (Flaps Extended) 8° (Takeoff) 160 knots 10° (Approach) 160 knots 23° (Landing) 150 knots VLE (Landing Gear Extended) 150 knots For other airspeed limits, see the appropriate FAA approved Airplane Flight Manual listed herein. C.G. Range CG limits for both takeoff, landing and inflight are 16% to 30% Mean Aerodynamic Chord except as limited at gross weight below 20,723 lbs. (9,400 kg). See the appropriate FAA Approved Flight Manual Limitation Section, listed herein for further definition. Datum The fuselage datum, Sta. 0.0, is located 92.40 in. forward to the fuselage jig point (rivet), which is located on the underside fuselage skin, immediately forward of fuselage frame 1A. Mean Aerodynamic Chord (MAC) Length: 100.83 in. L.E. of MAC: 377.61 in. aft of fuselage datum Leveling Means Plumb-bob suspended from aft face of aft cockpit compartment bulkhead over reticule on floor. 3 of 31 A21NM Maximum Weights Maximum Ramp 31,862 lb (14,450 kg) Maximum Takeoff 31,752 lb (14,400 kg) Maximum Landing 31,311 lb (14,200 kg) Maximum Zero Fuel 29,988 lb (13,600 kg) Minimum Flight 19,183 lb ( 8,700 kg) Minimum Crew Two (2): pilot and co-pilot Maximum Passengers 39 Maximum Baggage 1,654 lb (750 kg) in rear cargo compartment. See the appropriate Weight and Balance Manual listed herein. Fuel Capacity Usable fuel (see Note 1 for unusable fuel): Location Volume (U.S. Gal.) Weight (lb) Moment Arm (in) Main Right Wing Aux 270 420 1809 2814 409.45 412.45 Main Left Wing Aux 270 420 1809 1814 409.45 412.45 TOTAL USABLE 1380 9246 411.26 Fuel weight is based upon fuel density of 6.7 lb/U.S. gallon. Pressure fueling: Maximum pressure for pressure fueling is 50 psi. Oil Capacity Volume (U.S. -quarts) Moment Arm (in) 7.3 U.S. qt./tank on each engine +350.47 3.8 U.S. qt/tank usable 5.0 U.S. qt/tank on each propeller gear box +315.97 1.5 U.S. qt/tank usable Maximum Operating Altitude 25,000 ft. (18,000 ft. for passenger transportation) Control Surface Movements Elevator: Up 30.0° ± 0.5° Down 15.0° ± 0.5° Up to A/C Serial Number C-005: Elevator Trim Tabs : Up 0.5° ± 0.5° Down 8.5° ± 0.5° From Serial Number C-006: Normal Trim Tab: Up -0.5° ± 0.5° Down 9.5° ± 0.5° Emergency Trim Tab: Up 2.0° ± 0.5° Down 7.0° ± 0.5° Elevator balance tab: Up (for +15° elevator) 1.75° ± 0.5° Down (for -30° elevator) 9.50° ± 0.5° Rudder: Right 17.0° ± 0.25° Left 12.0°± 0.25° Rudder trim tab: Right 5.0° ± 0.5° Left 3.0° ± 0.5° Rudder balance tab: Right (for +12° rudder) 2.5° ± 0.25° Left (for -17° rudder) 5.0° ± 0.25° 4 of 31 A21NM Control Surface Movements Ailerons: Up 20.0° ± 0.5° Down 20.0° ± 0.5° Aileron trim tab: Up 8.0° ± 0.5° Down 8.0° ± 0.5° Aileron balance tabs: Trailing edge up for aileron 0°: 5.0° ± 0.5° Trailing edge down for aileron 20° up: 8.0° ± 0.5° Trailing edge up for aileron 20° down: 18.0° ± 0.5° Flaps (inner and outer) Cruise 0.0° ± 0.5° Takeoff 8.0° ± 0.5° Approach 10.0° ± 0.5° Landing 23.0° ± 0.5° All measurements are taken at trailing edge from neutral position. Serial Nos. Eligible A Spanish DGAC Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” below must be submitted for each individual airplane for which application for United States certification is made. Import Requirements The FAA can issue a U.S. airworthiness certificate based on an Export Certificate of Airworthiness (Export C of A) signed by a representative of the Spanish DGAC on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to conform with the Type Design approved under U.S. Type Certificate No. A21NM and to be in a condition for safe operation.’ Only CN235 airplane manufactured in Spain and accompanied by a Spanish export certificate of airworthiness are eligible for a United States Airworthiness Certificate. Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Certification Basis 14 CFR Section 21.29 and 14 CFR Part 25, effective 1 February 1965, including Amendments 25-1 through 25-54. Federal Aviation Administration Exemption No. NM-103, from 14 CFR Section 25.571 (e) (2), issued on January 20, 1984. Special Federal Aviation Regulation No. 27, effective 1 February 1974, including Amendments 27-1 through 27-5 (Fuel Venting and Exhaust Emissions). 14 CFR Part 36, effective 1 December 1969, including Amendments 36-1 through 36-12. Equivalent safety findings exist with respect to the following regulation: 14 CFR Section 25.1305 (a) (2): Fuel Quantity Indicator. Construcciones Aeronauticas, S.A. elected to demonstrate compliance with: 14 CFR Section 25.1419: Ice Protection. Date of Application for Type Certificate: 3 December 1981. The Spanish DGAC originally type certificated this aircraft under its type certificate Number 01-86. The FAA validated this product under U.S. Type Certificate number A21NM. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the Spanish DGAC . 5 of 31 A21NM 14 CFR part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on 14 CFR § 21.29(a) for new import Type Certificates (TCs), (or 14 CFR § 21.101(g) for changes to TCs), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Required Equipment The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the airplane. Equipment approved for the Construcciones Aeronauticas, S.A. Model CN-235 is listed in CASA Document No. 86-3309, Master Equipment List, dated July 1986 or as revised and approved by the DGAC. Federal Aviation Administration (FAA) approve Airplane Flight Manual Construcciones Aeronauticas, S.A. Model CN-235, Document No. D.T. 85-3503, published in the English language (EASA approved on behalf of the FAA on 11 January 2008 or later EASA approved revision), is required. Service Information Each of the documents listed below must state that it is approved by EASA – or for approvals made before September 28, 2003 – by the Spanish DGAC. Any such documents are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Construcciones Aeronauticas, S.A.under the authority of EASA approved Design Organization EASA.21J.032 - or for approvals made before September 28, 2003 - under the authority of Spanish DGAC Design Organization Approval No. 1 are considered FAA approved. These approvals pertain to the type design only.  TC holder Service Bulletins, except as noted below,  Structural repair manuals  Vendor manuals referenced in TC holder Service Bulletins  Airplane flight manuals  Repair instructions. Note: Design changes that are contained in TC holder Service Bulletins and that are classified as Level 1 Major in accordance with either the US/Spain or US/EASA Bilateral Aviation Safety Agreement – Implementation Procedures for Airworthiness, must be approved by the FAA. Available Documents - Airplane Weight and Balance Control and Loading Data Document No. D.T. 85-3502. - Maintenance Review Board Report, Document No. MRB CN-235-PV.01. NOTES NOTE 1 Weight and Balance: (a) A current Weight and Balance Report must be in each aircraft at the time of original airworthiness certification and at all times thereafter except in the case of an operator having an FAA approved loading system for weight and balance control. (b) The airplane empty weight and corresponding center of gravity location must include: Total engine and gearbox oil: 47.6 lb at Sta 336.44 in. Total hydraulic fluid: 39.03 lb at Sta 461.22 in. Unusable fuel (77.05 lb) listed as follows: Unusable Fluid U.S. Gallons Pounds Moment Arm (in) Drainable: Left Wing 4.25 28.47 409.68 Right Wing 4.25 28.47 409.68 6 of 31 A21NM Trapped Fuel: Tanks and fuel lines 3.00 20.10 410.07 Total unusable fuel 11.50 77.05 409.76 (c) The airplane must be loaded in accordance with Section 2 of the approved Airplane Flight Manual and the C.G. must be within the specified limits at all times. NOTE 2 Airplane operation must be in accordance with the Airplane Flight Manual (AFM) listed above. NOTE 3 Required structural inspections, inspection times, and retirement times for structural parts and for components are listed in the Airworthiness Limitations as presented in Section 1.4 of Construcciones Aeronauticas, S.A. Document No. D.T. 86-3001. Material covered in this Section must not be changed without FAA approval. NOTE 4 Engine certification maintenance requirements (CMR) and systems certification maintenance requirements are included in Section 1.4.1 of Construcciones Aeronauticas, S.A. Document No. D.T. 86-3001. Material covered in this section must not be changed without FAA approval. NOTE: The CMR’s may also be included in any appendix to the Maintenance Review Board Document No. MRB CN-235-PV.01. II. Model CN-235-100 (Approved October 26, 1989) Engines 2 Engines - General Electric Company, Model CT7-9C, free turbine turboprop. Power turbine/propeller reduction gearing 15.9:1. Fuel (a) Fuels shall conform to the specifications listed or to subsequent revisions thereof: Designation Specification Jet A, A-1, B ASTM D1655 JP-4, JP-5 MIL-T-5624 JP-8 MIL-T-83133 (b) For approved fuel additives, see General Electric Company jet fuel specification D50TF2, current approved revision. Anti-icing additives to specification MIL-I-27686E may be used to a concentration not in excess of 0.15% by volume. Engine Limits The Maximum continuous and takeoff static level rating at ISA: Conditions Shaft Horse Power Jet Thrust (lb) Torque Meter Reading (ft - lb) ITT (°C) Engine RPM Takeoff (normal) 1750 168 425 921* 45,300 ** Takeoff (APR on) 1870 179 454 950 45,615 Max Continuous 1750 168 425 917 45,614 *When OAT is lower than 35°C, ITT limit is 921°C. When OAT is between 35°C and 41°C the ITT limit has a lineal variation with the OAT, from 921°C to 944°C at sea level. When OAT is higher than 41°C the ITT limit is 950°C at sea level. ** If OAT is higher than 41°C, the takeoff limit with APR on is applied. Propeller and Propeller Limits 2 Propellers - Hamilton Standard Model - 14 RF-21. Blades: 4, Model RFC11R1-0C. Diameter:132.24 in. max., 131.94 in. min. 7 of 31 A21NM Blade angle measured a 42 in. - radius - station: Ground Idle -3.7° ± 1.0° Max Reverse -12.4° ± 1.3° Feather 80.8° ± 0.5° Flight Idle 16.7° ± 0.8° Propeller Spinner: Hamilton Standard, P/N 790185-1 Propeller Deicer: Included in blade P/N Airspeed Limits (IAS) Unless otherwise noted below, speeds are - indicated airspeeds. VMO (Maximum Operating) (See NOTE 5) Sea Level 240 knots 20,000 ft 210 knots 25,000 ft 190 knots Straight line variation between points. VA (Maneuvering) Sea level to 25.000 ft 160 knots VFE (Flaps Extended) 10° (Takeoff) 160 knots 15° (Approach) 160 knots 23° (Landing) 150 knots VLE (Landing Gear Extended) 150 knots For other airspeed limits, see the appropriate FAA Approved Airplane Flight Manual listed below. C.G. Range See the appropriate FAA Approved Airplane Flight Manual listed below. Datum Sta 0.0 is located 92.40 in. forward of the fuselage jig point (rivet), which is located on the underside fuselage skin, immediately forward of fuselage frame 1A. Mean Aerodynamic Length: 100.83 in. Chord (MAC) L.E. of MAC: 377.61 in aft of datum Leveling Means Plumb-bob suspended from aft face of aft cockpit compartment bulkhead over reticule on floor. Maximum Weights Maximum Ramp 31.862 lb. (14,450 kg) (See NOTE 5) Maximum Takeoff 31,752 lb (14,400 kg) Maximum Landing 31,311 lb (14,200 kg) Maximum Zero Fuel 29,988 lb (13,600 kg) Minimum Crew Two (2): Pilot and co-pilot Maximum Passengers 44 Maximum Baggage 1654 lb (750 kg) in rear cargo compartment. See the appropriate Weight and Balance Manual listed below. Fuel Capacity Usable f+uel (see Note 1 for unusable fuel): Location Volume (U.S. Gal.) Weight (lb) Moment Arm (in) Main Right Wing Aux 270 420 1809 2814 409.45 412.45 8 of 31 A21NM Main Left Wing Aux 270 420 1809 1814 409.45 412.45 TOTAL USABLE 1380 9246 411.26 Fuel weight is based upon fuel density of 6.7 lb/U.S. gallon. Pressure fueling: Maximum pressure for pressure fueling is 50 psi. Oil Capacity Volume (U.S. -quarts) Moment Arm (in) 7.3 U.S. qt./tank on each engine +350.47 3.8 U.S. qt/tank usable 5.0 U.S. qt/tank on each propeller gear box +315.97 1.5 U.S. qt/tank usable Maximum Operating Altitude 25,000 ft. (18,000 ft. for passenger transportation) Control Surface Movements Elevator: Up 30.0° ± 0.5° Down 15.0° ± 0.5° Elevator tab (trim) Up -0.5° ± 0.5° Down 9.5° ± 0.5° Elevator tab (emergency trim) Up 2° ± 0.5° Down 7.0° ± 0.5° Elevator balance tab: Up (for +15° elevator) 1.75° ± 0.5° Down (for -30° elevator) 9.50° ± 0.5° Rudder: Right 17.0° ± 0.25° Left 12.0° ± 0.25° Rudder trim tab: Right 5.0° ± 0.5° Left 3.0° ± 0.5° Rudder balance tab: Right (for rudder 12° left) 2.5° ± 0.25° Left (for rudder 17° right) 5.0° ± 0.25° Ailerons: Up 20.0° ± 0.5° Down 20.0° ± 0.5° Aileron trim tabs: Up 8.0° ± 0.5° Down 8.0° ± 0.5° Aileron balance tabs: trailing edge up for aileron 0°: 5.0° ± 0.5° trailing edge down for aileron 20° up: 8.0° ± 0.5° trailing edge up for aileron 20° down: 18.0° ± 0.5° Flaps (inner and outer) Cruise 0.0° ± 0.5° Takeoff 10.0° ± 0.5° Approach 15.0° ± 0.5° Landing 23.0° ± 0.5° All measurements are taken at trailing edge from neutral position. Serial Nos. Eligible The Spanish DGAC Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” below must be submitted for each individual airplane for which application for certification is made. Import Requirements The FAA can issue a U.S. airworthiness certificate based on an Export Certificate of Airworthiness (Export C of A) signed by a representative of the Spanish DGAC on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to conform with the Type Design approved under U.S. Type Certificate No. A21NM and to be in a condition for safe operation.’ 9 of 31 A21NM “Only CN-235-100 airplanes manufactured in Spain and accompanied by a Spanish export certificate of airworthiness are eligible for a United States airworthiness certificate.” Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Certification Basis 14 CFR Section 21.29 and 14 CFR Part 25, effective 1 February 1965, including Amendments 25-1 through 25-59, 25-61 and 25-62. Federal Aviation Administration Exemption No. Nm-103, from 14 CFR Section 25.571 (e) (2), issued on January 20,1984. Special Federal Aviation Regulation No. 27, effective 1 February 1974, including Amendments 27-1 through 27-5 (Fuel Venting and Exhaust Emissions). 14 CFR Part 36, effective 1 December 1969, including Amendments 36-1 through 36-15. The CN-235-100 weight increase to 15,100 kg (33295 lbs) takeoff weight and 14,900 kg (32854 lbs) max landing weight, incorporating Service Bulletin 235-34-04 or CASA Document CDS) No 37-49 includes Amendment 36-17. Equivalent safety findings exist with respect to the following regulation: 14CFR Section 25.1305 (a) (2): Fuel Quantity Indicator. The Special Conditions No. 25-ANM-22 (Docket no. NM-35), dated December 13, 1988, “Lightning and Radio Frequency (RF) Energy Protection”. Construcciones Aeronauticas S.A. elected to demonstrate compliance with: 14 CFR Section 25.1419: Ice Protection. Date of Application for Amended Type Certificate: May 12, 1987. Date of Application for the CN-235-100 weight increase: April 3, 1991. The Spanish DGAC originally type certificated this aircraft under its type certificate Number 01-86. The FAA validated this product under U.S. Type Certificate number A21NM. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the Spanish DGAC . 14 CFR part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on 14 CFR § 21.29(a) for new import TCs, (or 14 CFR § 21.101(g) for changes to TCs), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Equipment The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the airplane. Equipment approved for the Construcciones Aeronauticas, S.A. CN-235-100 is listed in CASA Document No. 88-3003, Master Equipment List, dated July 1988 or as revised and approved by DGAC. Federal Aviation Administration (FAA) approved Airplane Flight Manual, Construcciones Aeronauticas, S.A. Model CN-235-100, Document No. D.T. 87- 3501, published in the English language (DGAC approved on behalf of the FAA on December 9, 1988 or later DGAC approved revision) is required. (See NOTE 5) 10 of 31 A21NM Service Information Each of the documents listed below must state that it is approved by EASA – or for approvals made before September 28, 2003 – by the Spanish DGAC. Any such documents are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Construcciones Aeronauticas, S.A.under the authority of EASA approved Design Organization EASA.21J.032 - or for approvals made before September 28, 2003 - under the authority of Spanish DGAC Design Organization Approval No. 1 are considered FAA approved. These approvals pertain to the type design only.  TC holder Service Bulletins, except as noted below,  Structural repair manuals  Vendor manuals referenced in TC holder Service Bulletins  Airplane flight manuals  Repair instructions. Note: Design changes that are contained in TC holder Service Bulletins and that are classified as Level 1 Major in accordance with either the US/Spain or US/EASA Bilateral Aviation Safety Agreement – Implementation Procedures for Airworthiness, must be approved by the FAA. Available Documents - Airplane Weight and Balance Control and Loading Data Document No. D.T. 85- 3502. (See NOTE 5). - Maintenance Review Board Report, Document No. MRB CN-235-PV.01. NOTES NOTE 1 Weight and Balances (a) A current Weight and Balance must be in each aircraft at the time of original airworthiness certification and at all times thereafter except in the case of an operator having an FAA approved loading system for weight and balance control. (b) The airplane empty weight and corresponding center of gravity location must include: Total engine and gearbox oil 47.6 lb at Sta 335.57 in. Type hydraulic fluid of 39.03 lb at Sta 460.35 in. Unusable fuel (77.05 lb) listed as follows: Unusable Fluid U.S. Gallons Pounds Moment Arm (in) Drainable: Left Wing 4.25 28.47 409.68 Right Wing 4.25 28.47 409.68 Trapped Fuel: Tanks and fuel lines 3.00 20.10 410.07 Total unusable fuel 11.50 77.05 409.76 (c) The airplane must be loaded in accordance with Section 2 of the approved Airplane Flight Manual and the C.G. must be within the specified limits at all times. NOTE 2 Airplane operation must be in accordance with the Airplane Flight Manual (AFM) listed above. All placards required in either the approved AFM, the application operating rules, or the certification basis must be installed in the airplane. NOTE 3 Required structural inspections, inspections times, and retirement times for structural parts and for