# TCDS A21NM: Airbus Defense and Space S.A. - Type: Type certificate data sheet - Status: Current - Holder: Airbus Defense and Space S.A. - Revision: 17 - Revised: February 19, 2025 - Product: Aircraft, Large Airplane - Certification basis: Part 25, Part 21 - Registered aircraft: 16, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/7b/b6/7bb616b44ec0d6c290d053977c7e8ca916209231694920a625312fa4df0ec390 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID145195307020250219180838.0001 - Page: https://openairdocs.org/tcds/A21NM ## Models (5) As the data sheet lists them. - CN-235-100 - CN-235 - C-295 - CN-235-300 - CN-235-200 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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 components are listed in the Airworthiness Limitation 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 engineering approval. 11 of 31 A21NM NOTE 4 Engine certification maintenance requirements (CMR) and systems certification maintenance requirements are included in section 1.4.1 of covered in this section must not be changed without FAA engineering approval. NOTE: The CMR’s may also be included in any appendix to the Maintenance Review Board Document No. MRB CN-235-PV.01. NOTE 5 For aircraft Model CN-235-100 incorporating CASA Service Bulletin S.B. 235-34-04 or the modification defined by the CASA Document CDS 3749, the previously established limitations to the parameters mentioned below, are modified in the following way: Airspeed Limits (IAS) VMO (Maximum Operating) Sea Level 232 knots 20,000 ft 202 knots 25,000 ft 1 82 knots Straight line variation between points. Maximum Weights Maximum Ramp 33,405 lb (15,150 kg) Maximum Takeoff 33,295 lb (15,100 kg) Maximum Landing 32,854 lb (14,900 kg) Maximum Zero 31,090 lb (14,100 kg) Also applicable with the Airplane Flight Manual, Document D.T. 90-3504, is the Airplane Weight and Balance Control and Loading Data Document No. D.T. 90-3505, FAA approval of the CN-235-100 weight increase was given on February 21, 1999 III. Model CN-235-200 (Approved March 13, 1992) 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. 12 of 31 A21NM 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. 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) Sea level 232 knots 20,000 ft 202 knots 25,000 ft 182 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 knotsFor 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 34940 lb (15850 kg) Maximum Takeoff 34830 lb (15800 kg) Maximum Landing 34390 lb (15600 kg) Maximum Zero Fuel 31080 lb (14100 kg) Minimum Crew Two (2): Pilot and co-pilot Max. Passengers 44 Maximum Baggage 1985 lb (900 kg) in rear cargo compartment. See the appropriate Weight and Balance Manual listed below. Fuel Capacity Usable fuel (see Note 1 for unusable fuel): Location Volume (U.S. Gal.) Weight (lb) Moment Arm (in) Main Right Wing 270 1809 409.45 13 of 31 A21NM Aux 420 2814 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: Up30.0° ± 0.5° Down 15.0° ± 0.5° Elevator tab (trim) Up +0.5° ± 0.5° Down +11° ± 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 19.0° ± 0.5° Left 15.0° ± 0.5° Rudder trim tab: Right 5.0° ± 0.5° Left 3.0° ± 0.5° Rudder balance tab: Right (for rudder 15°left) 2.0° ± 0.5° Left (for rudder 19º right)5.25° ± 0.5° 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.’ “Only CN-235-200 airplanes manufactured in each Spain and accompanied by a Spanish export certificate of airworthiness are eligible for a United States Airworthiness Certificate.” 14 of 31 A21NM 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 14CFR 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 25.57 (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- 18. Equivalent safety findings exist with respect to the following regulation. 14 CFR Section 25.1305 (a) (2): Fuel Quantity Indicator. The Special Conditions No. 25-ANM-22 (Docket No. NM-35), dated December 13, 988, “Lightning and Radio Frequency (RF) Energy Protection”. Construcciones Aeronauticas S.A. elected to demonstrate compliance with: 14 CFR ection 25.1419: Ice Protection. Date of Application for Amended Type Certificate: January 12,1990. 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. 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. CN-235-200 is listed in CASA Document No. 90-3016, 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-235-200, Document No. D.T. 91-3501, published in the English language (DGAC approved on behalf of the FAA on September 27, 1991 or later DGAC 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 15 of 31 A21NM 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. 91-3502. - Maintenance Review Board Report, Document No. MRB CN-235-PV.01. NOTES NOTE 1 Weight and Balance: (a) A current Weight and Balance must be in each aircraft at the time of original airworthiness certification and at all time 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 Fuel 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 components are listed in the Airworthiness Limitation 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 engineering 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 engineering approval. NOTE: The CMR’s may also be included in any appendix to the Maintenance Review Board Document No. MRB CN-235-PV.01. NOTE 5 CN-235-100 airplanes are eligible for conversion to upgraded model CN-235-200 when CASA Service Bulletin SB235-11-06 has been incorporated and further modified as per DGAC approved Documents CDS 30040, 30049, 30178 and 30188. 16 of 31 A21NM IV. Model CN-235-300 (Approved December 30, 1998) Engines 2 Engines - General Electric Company, Model CT7-9C3, 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 ITT (ºC) Engine RPM (%) Torque Meter Reading (%) ESHP Takeoff (normal) 1750 (a) (b) 917 101.3 (c) 100 1816 Max Continuous 1750 944 102.0 100 1816 Takeoff (APR on) 1870 940 102.0 107 1942 (a) The shown temperature value is the absolute maximum. See the appropriate FAA Approved Airplane Flight Manual listed below for the maintained ITT limits in relation with the environmental conditions. (b) Up to 10ºC overtemperature are permitted over the maintained ITT values, for a maximum of two minutes. (c) The shown torque value is the absolute maximum. See the appropriate FAA Approved Airplane Flight Manual listed below for the maintained torque limits in relation with the environmental conditions. Propeller and Propeller Limits 2 Propellers - Hamilton Standard Model - 14 RF-37. Blades: 4, Model RFA12A1-POC. Diameter:144.84 in.. Prohibited % rpm interval: 47% to 71% Propeller Spinner: Hamilton Standard, P/N 790185-2 Propeller Deicer: Included in blade P/N Airspeed Limits (IAS) Unless otherwise noted below, speeds are - indicated airspeeds. VMO (Maximum Operating) Sea level 232 knots 20,000 ft 202 knots 25,000 ft 182 knots Straight line variation between points. VA (Maneuvering) Sea level to 25,000 ft 160 knots VFE (Flaps Extended) 17 of 31 A21NM 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 93.19 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 aft of datum Leveling Means Plumb-bob suspended from aft face of aft cockpit compartment bulkhead over reticule on floor. Maximum Weights Maximum Ramp 34940 lb (15850 kg) Maximum Takeoff 34830 lb (15800 kg) Maximum Landing 34390 lb (15600 kg) Maximum Zero Fuel 31080 lb (14100 kg) Minimum Crew Two (2): Pilot and co-pilot Max. Passengers 44 Maximum Baggage 1985 lb (900 kg) in rear cargo compartment. See the appropriate Weight and Balance Manual listed below. 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. Control Surface Movements Elevator: Up30.0° ± 0.5° Down 15.0° ± 0.5° Elevator tab (trim) Up +0.5° ± 0.5° Down +11° ± 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 19.0° ± 0.5° 18 of 31 A21NM Left 15.0° ± 0.5° Rudder trim tab: Right 5.0° ± 0.5° Left 3.0° ± 0.5° Rudder balance tab: Right (for rudder 15° left ) 2.0° ± 0.5° Left (for rudder +19°right)5.25° ± 0.5° Ailerons: Up 18.0° ± 0.5° Down 18.0° ± 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.’ “Only CN-235-300 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 and voluntary compliance with 14 CFR part 25.1419, Amendment 25-23 for parts not changed or not affected by the change. Compliance with 14 CFR part 25.1419 Amendment 25-72 for the airframe ice protection system, 14 CFR part 25.1316 at Amendment 25-80 for the Integrated Electronic Display System (IEDS), and 14 CFR part 25.905(d) at Amendment 25-72. Voluntary compliance with 14 CFR section 25.365(e) at Amendment 25-71 and 14 CFR part 25.571(e)(2) at Amendment 25-72. 14 CFR Part 34, including Amendments 14-1 through 14-2. 14 CFR Part 36, effective 1 December 1969, including Amendments 36-1 through 36-18. Equivalent safety findings exist with respect to the following regulation. 14 CFR Section 25.1305 (a) (2): Fuel Quantity Indicator. - Special Condition No. 25-ANM -22 (Docket No. NM -35), dated December 13, 1988, "Lightning and Radio Frequency (RF) Energy Protection" for parts not changed or not affected by the change. 19 of 31 A21NM - Radio Frequency (RF) Energy Protection requirements included in Special Condition No. 25-ANM-22 for parts changed or affected by the change. Date of Application for Amended Type Certificate: September 8, 1998. 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. 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. CN-235-300 is listed in CASA Document No. 98-3016, CN-235-300 Equipment List, dated Nov. 1998 or as revised and approved by DGAC. Federal Aviation Administration (FAA) approved Airplane Flight Manual, Construcciones Aeronauticas S.A. Model CN-235-300, Document No. D.T. 98-3002, published in the English language (DGAC approved on behalf of the FAA on December XX, 1998 or later DGAC 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. 98-3003. - Maintenance Review Board Report, Document No. MRB CN-235-PV.01. NOTES NOTE 1 Weight and Balance: (a) A current Weight and Balance must be in each aircraft at the time of original airworthiness certification and at all time 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: 20 of 31 A21NM 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 Fuel 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 components are listed in the Airworthiness Limitation 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 engineering 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 engineering approval. NOTE: The CMR’s may also be included in any appendix to the Maintenance Review Board Document No. MRB CN-235-PV.01. V. Model C-295 (Approved December 17, 1999 - SEE NOTE 5). Engines 2 Engines – Pratt & Whitney of Canada, Model P&W 127G, free turbine turboprop. Power turbine/propeller reduction gearing 16.6:1. Fuel (a) Fuels shall conform to the specifications listed or to subsequent revisions thereof: Designation Specification Jet A, A-1, B ASTM D1655 J-B ASTM D6615 JP-4, JP-5 MIL-T-5624 JP-8 MIL-T-83133 Approved Fuel Additives and Inhibitors are set forth in sections 2 of FAA Approved Airplane Flight Manual listed below Engine Limits The Maximum continuous and takeoff static level rating at ISA: Conditions Max. Torque % Max. ITT (ºC) Max. NH % Max. NP % Takeoff (normal) (5 min.) 101 765 [1] 102.3 101 Max Continuous 112 800 103.7 101 21 of 31 A21NM [3] Transient [2] (20 seconds) 125 840 104.3 120 Max.Takeoff (One engine inoperative) 112 800 103.7 101 [1]. The value shown is an absolute maximum. The steady state ITT limit for the existing ambient conditions to be observed in a normal take-off (two engine operation) [2]. The corresponding transient limit is further restricted to five seconds [3] Maximum continuous power; although authorized for non-limited periods, is for use in abnormal conditions (for instance Operations with one engine inoperative, important ice, accumulation over the structure, compliance with CTAATC requirements, or when the obstacles require a descent angle according to pilot decision). Propeller and Propeller Limits 2 Propellers - Hamilton Standard Model - HSD 568F-5 Blades: 6, Model R815505-4 Diameter: 3,932 mm. (12.9 ft.) Propeller Spinner: Hamilton Standard, P/N 790185-2 Propeller Deicer: Included in blade P/N Airspeed Limits (IAS) Unless otherwise noted below, speeds are - indicated airspeeds. VMO (Maximum Operating) Sea level 245 knots 7,000 ft 254 knots 14,000 ft 245 knots 25,000 ft 200 knots Straight line variation between points. VA (Maneuvering) Sea level to 25,000 ft 190 knots VFE (Flaps Extended) 10° (Takeoff) 185 knots 15° (Approach) 180 knots 23° (Landing) 175 knots VLE (Landing Gear Extended) 175 knots For other airspeed limits, see the appropriate Spanish DGAC Approved Airplane Flight Manual listed below. C-295FW “FW variant” VMO (Maximum Operating) Sea level 246.4 knots 15,300 ft 246.4 25,000 ft 203.4 knots Straight line variation between points VA (Manoeuvring) Sea Level to 25,000 ft. 185 knots VFE ( Maximum Flap Extended) 10° (Takeoff) 190 knots 15° (Approach) 185 knots 23° (Landing) 180 knots VLE (Landing Gear Extended) 180 knots 22 of 31 A21NM For other airspeed limits, see the appropriate FAA Approved Airplane Flight Manual listed below C.G. Range See the appropriate Spanish DGAC Approved Airplane Flight Manual listed below. Datum The reference datum is located 2 367 mm (93.19 in.) forward of jig point. The jig point is defined by a rivet located on the underside skin fuselage nose. Mean Aerodynamic Length: 100.83 in. Chord (MAC) L.E. of MAC: 11,115 mm (437.61 in.) aft from reference datum Leveling Means Plumb-bob suspended from aft face of aft cockpit compartment bulkhead over reticule on floor. Maximum Weights Maximum Ramp 46,410 lb (21.050 kg) Maximum Takeoff 46,300 lb (21.000 kg) Maximum Landing 45,630 lb (20.700 kg) Maximum Zero Fuel 40,780 lb (18.500 kg) Minimum Crew Two (2): Pilot and co-pilot C-295FW “FW variant” The total number of persons carried, including the minimum flight crew, shall not exceed three Max. Passengers Not applicable, freighter version. Fuel Capacity Usable fuel (see Note 1 for unusable fuel): Location Volume (U.S. Gal.) Moment Arm (in) Main Right Wing Aux 424 571 410.2 414.72 Main Left Wing Aux 424 571 410.2 414.72 TOTAL USABLE 1990 412..8 Fuel weight is based upon fuel density of 6.7 lb/U.S. gallon. Pressure fueling: Maximum pressure for pressure fueling is 50 psi. C-295FW “FW variant” Location Volume (U.S. Gal.) Moment Arm (in) Main Right Wing Aux 448 543 470.2 474.7 Main Left Wing Aux 448 543 470.2 474.7 TOTAL USABLE 1982 Oil Capacity The following data apply to each powerplant. Volume (U.S. -gal) Moment Arm (in) Usable Oil: 2.90 U.S. Gal. 407.91 Total Oil: 6.08 U.S. Gal. 411.22 23 of 31 A21NM Maximum Operating Altitude 25,000 ft. Control Surface Movements Elevator: Up: -25.0° ± 0.5° Down: +12.5 ° ± 0.5° Elevator tab (trim) Up: +0.0° ± 0.5° Down: +12.0° ± 0.5° Elevator tab (emergency trim) Up: +0.0 ± 0.5° Down: +12.0° ± 0.5° Elevator balance tab: Up (for +12.5º elevator) - 2.2 ± 0.5° Down (for -25° elevator) 7.7 ± 0.5° Rudder: Right:- 21.0° ± 0.5º (-25 in Expander mode) Left : +12.5º± 0.5º (+18.8º in Expander mode) Rudder trim tab: Right: - 5.0° ± 0.5° (-7º trim in standby) Left : +5.0° ± 0.5º ( +7º trim standby) Rudder balance tab: Left (for rudder - 25°) - 10.3° ± 0.5° Right (for rudder +18.8°) + 3.8° ± 0.5° Ailerons: Up 21.0° ± 0.5° Down 21.0° ± 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 21° up: -8.5 ° ± 0.5° trailing edge up for aileron -21° down: 18.5° ± 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° A ll 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.’ “Only C-295 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. C-295FW “FW variant” Definition (December 17, 2020) The C-295FW “FW variant” designation does not correspond to a model designation. This is only a commercial designation for a C-295 on which the Major modifications listed in the following paragraph (a), (b) & (c) have been embodied during production. (a) Winglets Major Significant modification DC10718A 24 of 31 A21NM (b) TS03.01 Avionic and Autopilot Upgrade Major Significant consist of the following modifications DC10278, DC10280, DC10281, DC10282, DC10283, DC10284, DC10285, DC10286 DC10288, DC10289, DC10290, DC10291, DC10310, DC10415, DC10416, DC10417, DC10418, DC10419, DC10420, DC10421, DC10422, DC10423, DC10424, DC10426, DC10428, DC10429, DC10451, DC10293 (c) Major Not Significant modifications: DC10735A, DC10736A, DC10737A, DC10738A, DC10739A, DC10740A, DC10741A, DC10877A, DC10892, DC10402, DC10287, DC10550, DC10656, DC10657, DC10967, DC10965A, DC10684-E, DC10702-E, DC10914-E, DC10998-E, DC10943-E, DC11090-E, DC11174-E, DC11000-E, DC11002-E, DC10890-E, DC10907-E, DC10910-E, DC10936-E, DC10955-E, DC10956-E, DC10993-E, DC11004-E, DC11030-E, DC11301-E, DC10915-E,DC10973-E, DC10974-E, DC11416S-E, S30301, S30333, S30307, S30338, S30305, S30306, S30331, S30337 Certification Basis The original certification basis is based on the CASA Model CN-235-200: 14 CFR part 21.29 and 14 CFR part 25, effective 1 February 1965, including Amendments 25- 1 through 25-59, 25-61, 25-62 for parts not changed or not affected by the change. For changed portions of the aircraft: 14CFR Section 21.29 and 14 CFR Part 25, as amended by Amendments 25-1 through 25-89, Amendment 25-91 for Section 25.351, Amendment 25-72 for Section 25.1419(Ice Protection), and excluding Amendment 25-64 for Section 25.562 (c)(5) for the pilot and copilot seats. The aircraft is not certified against ditching 14 CFR Part 34, including Amendments 34-1 through 34-3. 14 CFR Part 36 including Amendments 36-1 through 36-21. Equivalent Safety Finding exists with respect to the following regulation: - FAR 25.1149 "Propeller Speed and Pitch Control" (ref. FAA Issue Paper P-2) - FAR 25.103 & 25.201 “Use of 1-g Stall Speed Criteria Instead of Minimum Speed in the Stall as a Basis for Determining Compliance for Airplanes with Stall Identification Systems" (ref. FAA Issue Paper F-6, dated December 3, 1999). Exemptions: The following exemptions have been granted: - Exemption 6708 to FAR §25.571 (e)(1) for the "Bird Strike Speed" - Exemption 6929 to §C36.9(e)(1) of 14 CFR Part 36 for "Approach Speed Criteria", and to §C36.3(c) of 14 CFR Part 36 "Sideline Noise Criteria." - Partial Grant of Exemption 7088 to FAR §25.723 for “Shock Absorption Tests” (SEE NOTE 5). Special Conditions: - High Intensity Radiated Fields (HIRF) - Use Automatic Takeoff Thrust Control System (autofeather/APR) for Approach Climb and Go-Around - Special Condition No. 25-764-SC, Non-Rechargeable Lithium Batteries, (this SC is not applicable to design changes approved before the SC effective date of January 7, 2020.) Date of application: The reference date of application for the Amended Type Certificate is January 10, 1997. 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: 25 of 31 A21NM 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. Certification Basis (C-295FW) Certification basis for Airworthiness & Environmental Standards for components and areas not affected by the change remain unchanged from the basic C-295. (A) Certification basis revised for Major Significant Winglet modification DC10718A This modification has been determined to be a no acoustic change in accordance with 14 CFR 21.93(b). Airworthiness and Environmental Standards for components and areas affected by the change are as follows: 14 CFR part 25, effective February 1, 1965, including amendments 25-1 through 25-141. The following sections are applicable: SUBPART B – Flight 25.101, 25.109, 25.113, 25.115 25.21(a),(b),(c,),(d), (e),(f) at Amendment 25-72 plus FAA Additional design requirements and conditions (ADRC) Memo AT11023IB-T- ADRC-25.21. 25.103 at Amendment 25-0 modified by ESF F-02 25.105 at Amendment 25-92 plus ADRC Memo AT11023IB-T- ADRC-25.21; 25.111 at Amendment 25-72 modified by ESF IP F-02 plus ADRC Memo AT11023IB-T- ADRC-25.21. 25.107 at Amendment 25-92 modified by ESF IP F-02 25.119, 25.121, 25.125 at Amendment 25-84 modified by ESF IP F- 02 plus ADRC Memo AT11023IB-T- ADRC- 25.21; 25.123 at Amendment 25-0 plus FAA ADRC Memo AT11023IB-T- ADRC-25.21. 25.143, 25145, 25.149, 25.201 at Amendment 25-84 modified by ESF F-02 25.147, 25.177, 25.181 at Amendment 25-72 modified by ESF F-02 25.161 at Amendment 25-38 modified by ESF F-02 25.175 at Amendment 25-7 modified by ESF F-02 25.207, 25.233, 25.237 at Amendment 25-42 modified by ESF F-02 SUBPART C – STRUCTURE 25.307, 25.331, 25.335, 25.341, 25.345, 25.349, 25.361, 25.367, 25.391, 25.473, 25.479, 25.481, 25.561 25.571 at Amendment 25-86 SUBPART D – DESIGN AND CONSTRUCTION 25.735(f) SUBPART E - POWERPLANT 25.903(d1), 25.905(d) 25.981 at Amendment 25-11 (Note: FAA acceptance of this exception is for fuel tank structural changes only and is based on the following design features incorporated: increased thickness of upper skin, front spars and rear spars in the fuel tank. The fuel tank structural changes meet the criteria for the use of exceptions in FAA policy PS-ANM-25.981-02, “Policy on Issuance of Special Conditions and Exemptions Related to Lightning Protection of Fuel Tank Structure and Systems,” dated June 24, 2014.) SUBPART F - EQUIPMENT 26 of 31 A21NM 25.1301(a), (b), 25.1309(b),(d), 25.1419 SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1583(a), 25.1585(a), 25.1587 SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1703(a), (b), (d), (e),25.1705(a), 25.170(a), (b), (l), 7, 25.1709, 25.1711(a),(c),(d),(e), 25.1713(a),(c), 25.1715(b), 25.1717, 25.1719, 25.1729 Equivalent Safety Findings: The original Equivalent Safety Finding with respect to the regulations CFR 14 sections 25.103, 25.107, 25.111, 25.119, 25.121, 25.125, 25.143, 25.145, 25.147, 25.149, 25.161, 25.175, 25.177, 25.181, 25.201, 25.207, 25.233, 25.237 is applicable: “Use of 1-g Stall Speed Criteria Instead of Minimum Speed in the Stall as a Basis for Determining Compliance for Airplanes with Stall Identification Systems" (ref. FAA Issue Paper ESF F-6, dated December 3, 1999). Additional Design Requirements and Conditions (ADRC): Additional Design Requirements and Conditions exist with respect to the regulation 14 CFR sections 25.21, 25.105, 25.111, 25.119, 25.121, 25.123, and 25.125, documented in the ADRC Memo AT11023IB-T-ADRC-25.21 (B). Certification basis revised for Major Significant TS03.01 Avionic and Autopilot Upgrade modifications: DC10278, DC10280, DC10281, DC10282, DC10283, DC10284, DC10285, DC10286 DC10288, DC10289, DC10290, DC10291, DC10310, DC10415, DC10416, DC10417, DC10418, DC10419, DC10420, DC10421, DC10422, DC10423, DC10424, DC10426, DC10428, DC10429, DC10451, DC10293. Airworthiness and Environmental Standards for components and areas affected by the change are as follows: 14 CFR part 25, effective February 1, 1965, including Amendments 25-1 through 25-139. The following sections are applicable (Applicable regulations for each design change listed above is defend in the section 3.1 of the ADS Certification Plan document TAE-5-DT-150026 Issue S dated 9/29/2020): SUBPART B – Flight 25.207(a),(b) SUBPART C – STRUCTURE 25.307, 25.561 SUBPART D – DESIGN AND CONSTRUCTION 25.677 (b), 25.735 (h), 25.729 (e2-e7), 25.773 (a2), 25.858 (a), (c), 25.899 SUBPART E - POWERPLANT 25.903 (d1), 25.901 (c), 25.905 (d), 25.1141 (f2i), (f2ii), 25.1203 (b2), (b3), (d) SUBPART F - EQUIPMENT 25.1301, 25.1302, 25.1303 (a), (b), (c1), 25.1305 (a1), (a2), (a3), (a4), (a5), (a6), (a7), (c1), (c2), (c3), (c6), (c7), (e1), (e2), 25.1309 (a), (b1), (b2), (c), 25.1316, 25. 1317, 25.1322 (a1),(a2), (a3), (b1), (b2), (b3), (c1), (c2), (c3), (d1), (d2), (e1), (f), 25.1323 (a), (c), (f), (g), (h), 25.1325 (a), (c1), (c2), (d), (e), (f), 25.1329 (a), (b), (c), (d), (e ), (f), (g), (h), (i), (j), (l) , 25.1353(a), 25.1419(c), 25.1431 (a), (c), (d), 25.1435 (b1), 25.1457, 25.1459 SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1527, 25.1583, 25.1585, 25.1587 SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1701, 25.1703 (a), (b), (d), (e), 25.1705(a), (b), 25.1707, 25.1709 (a1), (a2), (b), 25.1711, 25.1713(a), (c), 25.1715, 25.1717, 25.1719, 25.1721, 25.1725 (b), 25.1729 Equivalent Safety Findings: Equivalent safety finding exists with respect to the regulation 14 CFR section 25.1549(a), (b) and (c) documented in the ELOS Memo AT11057IB-T-P-3 Turbine Engine Oil Pressure, Oil Temperature, Low Pressure Spool Speed and Fuel Flow Parameters and Lack of Green Arc or Green Line for Normal Operations. 27 of 31 A21NM Special Conditions: 25-764-SC, “Non-rechargeable Lithium Batteries” 25-765-SC, “Electronic System Security Protection from Unauthorized External Access” 25-766-SC, “Electronic System Security Protection from Unauthorized Internal Access” (C) Certification Basis Revised for Major Not Significant modification elect to comply by Airbus Defense & Space: C.1- For modification DC10998-E (New Control Wheel Installation) elect to comply with CFR 14 part 25 sections 25.1301, 25.1302, 25.1321, 25.1329, 25.1459, 25.1701, 25.1703, 25.1705, 25.1707, 25.1711, 25.1713, 25.1715, 25.1717, 25.1719, 25.1721, at Amendment 25-139. C.2 - For modification DC11090-E (High Life Control Unit (HLCU) Installation) elect to comply with, CFR 14 part 25 section 25.1317 at Amendment 25-139. C.3 - For modification DC11416S-E (New Emergency Locator Transmitter) elect to comply with the following CFR 14 part 25 sections at Amendment 25-139: SUBPART C – STRUCTURE 25.307, 25.561, 25.571 SUBPART D – DESIGN AND CONSTRUCTION 25.899 SUBPART F - EQUIPMENT 25.1301 (a1), (a2), (a3), (a4), 25.1302, 25.1309 (a1), (c), 25.1322 (a1), (a3), (b), (c), (d1), (e1), 25.1353 (a), 25.1431 (a), (c) SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1585 (a) SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1701, 25.1703 (a) (b), (d), (e), 25.1705 (a), 25.1707 (a), (b), (i), (j), (l), 25.1711 (a), (c), (d), (e), 25.1713 (a), (c), 25.1719, 25.1721 Special Conditions: 25-764-SC, “Non-rechargeable Lithium Batteries” C.4 – For modification DC10915-E (Electrical and Avionics Version Adjustment) elect to comply with the following CFR 14 part 25 sections at Amendment 25-139: SUBPART D – DESIGN AND CONSTRUCTION 25.773 (a2) SUBPART F - EQUIPMENT 25.1301 (a1), (a2), (a3), (a4), 25.1302 (a), (b), (c), (d), 25.1309 (a1), (b), (c), 25.1317, 25.1322 (a1), (a3), (b), (c), (d1), (e1), (f), 25.1323 (a), (c), (h), 25.1325 (a), (c1), (c2), (d), (e), 25.1423 (a1), (a2), (d), (e) , (f), 25.1431 (a), (b), (d), 25.1459 (e) SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1583, 25.1585 (a) SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1701, 25.1703 (a) (b), (d), (e), 25.1705 (a), 25.1707, 25.1711, 25.1713 (a), (c), 25.1715, 25.1717, 25.1719, 25.1721 Special Conditions: 25-764-SC, “Non-rechargeable Lithium Batteries” 25-765-SC, “Electronic System Security Protection from Unauthorized External Access” 25-766-SC, “Electronic System Security Protection from Unauthorized Internal Access” C.5 – For modification DC10736A (Fuel System Modification) elect to comply with CFR 14 part 25 section 25.1583 (a), (c) at Amendment 25-141 28 of 31 A21NM C.6 - For modification DC10287 (Variable Frequency Generator Change VFG 40 KVAs for TS-03 ) elect to comply with the following CFR 14 part 25 sections at Amendment 25-138: SUBPART C – STRUCTURE 25.307, 25.561 SUBPART D – DESIGN AND CONSTRUCTION 25.869 (a) SUBPART E - POWERPLANT 25.901 (b1) SUBPART F – EQUIPMENT 25.1301 (a1) (a2) (a3), 25.1309 (a), (b), (c), 25.1316, 25.1317, 25.1353 (a), (b), (c1), (c2), (c3), (c4), 25.1357 (All) except (f), 25.1360, 25.1362, 25.1431(a), (c) SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1585 SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1725 (b) C.7 - For modification DC10550 (Architecture Electrical system) elect to comply with the following CFR 14 part 25 sections at Amendment 25-138: SUBPART C – STRUCTURE 25.307, 25.561 SUBPART D – DESIGN AND CONSTRUCTION 25.869 (a) SUBPART E - POWERPLANT 25.903 (d1), 25.905 (d) SUBPART F – EQUIPMENT 25.1301 (a1) (a2) (a3), 25.1309 (a), (b), (c), 25.1310, 25.1316, 25.1317, 25.1353 (a), (b), (c1), (c2), (c3), (c4), 25.1357 (All) except (f), 25.1360 (a) (b), 25.1362, 25.1431(a), (c), SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1585 SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1725 (b) C.8 - For modification DC10967 (TS03 Emergency Lights new position) elect to comply with the CFR 14 part 25 sections 25.307, 25.561, 25.1353 (a), 25.1431 (c), 25.1725 (b) at Amendment 25-138. C.9 - For modification DC10402 (ECS conditioning) elect to comply with the following CFR 14 part 25 sections at Amendment 25-138: SUBPART E - POWERPLANT 25.903 (d1), 25.905 (d) SUBPART F - EQUIPMENT 25.1301 (a1), (a2), (a3),(a4), 25.1309 (a), (b1), (b2), (c), 25.1316, 25.1317, 25.1353 (a), 25.1431 (c), SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1583, 25.1585 SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 29 of 31 A21NM 25.1729 C.10 - For modification DC10656 (Smoke Detection installation) elect to comply with the following CFR 14 part 25 sections at Amendment 25-138: SUBPART D – DESIGN AND CONSTRUCTION 25.855 (h2), (i), 25.858 (a), (b), (d) SUBPART E - POWERPLANT 25.903 (d1), 25.905 (d) SUBPART F - EQUIPMENT 25.1301 (a1) (a2) (a3) (a4), 25.1309 (a), (b), (c), 25.1316, 25.1317, 25.1353 (a), 25.1431 (c) C.11 - For modification DC10943-E (Halon-Free Portable Fire Extinguishers) elect to comply with the following CFR 14 part 25 sections at Amendment 25-139: SUBPART C – STRUCTURE 25.561 (c1)(i) SUBPART D – DESIGN AND CONSTRUCTION 25.851 (a1), (a2), (a3), (a5), (a6), (a7), (a8), (c) SUBPART F - EQUIPMENT 25.1301 (a1),(a2), (a3) (a4) , 25.1309 (a1) C.12 - For modification DC11174-E (New External anti-collision LED Lights for landing and taxi), DC10890-E (Contactors Replacement) , DC11301-E (C295 FW FDCU Update) elect to comply with CFR 14 part 25 section 25.1317 at Amendment 25-139. C.13 - For modification DC10907-E (EPC Bonding Improvement) elect to comply with CFR 14 part 25 sections 25.899, 25.1317, 25.901 (b1), (b4) at Amendment 25-139. C.14 - For modification DC10973-E (AHRS Equipment Installation), elect to comply with the following CFR 14 part 25 sections at Amendment 25-139: SUBPART D – DESIGN AND CONSTRUCTION 25.773 (a2) SUBPART F - EQUIPMENT 25.1301 (a1), (a2), (a3), (a4), 25.1302 (a),(b),(c),(d), 25.1303 (b4), (b5), (b6), 25.1309, 25.1317, 25.1322 (a1), (a3), (b), (c), (d1), (e1), (f), 25.1329 (c), (d), (e), (g), 25.1431 (a), (d), 25.1459 (a1), (e) SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1583 (a), 25.1585 (a) SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1701, 25.1703 (a), (b), (d), (e), 25.1705, 25.1707, 25.1711, 25.1713 (a), (c), 25.1715, 25.1717, 25.1719, 25.1721 C.15 - For modification DC10974-E (Second Transponder Installation) elect to comply with the following CFR 14 part 25 sections at Amendment 25-139: SUBPART F - EQUIPMENT 25.1301 (a1), (a2), (a3), (a4), 25.1302 (a),(b),(c),(d), 25.1309 (a1), (b), (c) , 25.1317, 25.1322 (a1), (a3), (b), (c), (d1), (e1), (f), 25.1431 (a), (d), 25.1459 (a1), (e) SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1583 (a), 25.1585 (a) SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1701, 25.1703 (a), (b), (d), (e), 25.1705, 25.1707, 25.1711, 25.1713 (a), (c), 25.1715, 25.1717, 25.1719, 25.1721 30 of 31 A21NM C.16 - For modification DC11678-E (Avionics Version TS-03.02 AFD 3710 HW Update), elect to comply with the following CFR 14 part 25 sections25.1301 (a1), (a2), (a3), 25.1302,25.1309 (a1), (b) at Amendment 25-139. C.17 - For modification DC11680A-E (Avionics Version TS-03.02 - AFM update to include CTNF- 33270 (spurious CAS)) elect to comply with CFR 14 part 25 sections 25.1309 (b), 25.1322 (d1), 25.1585 (a2) at Amendment 25-139. C.18 - For modification DC10702-E (Civil Freighter Layout) , elect to comply with CFR 14 part 25 section 25.1583 (c) at Amendment 25- 139. C.19 - For modification DC11609S-E (TS03.04 HW & SW MODIFICATIONS) elect to comply with the following CFR 14 part 25 sections at Amendment 25-139: SUBPART E - POWERPLANT 25.901 (a2), (a3) SUBPART F - EQUIPMENT 25.1322 (e2) 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. C-295 is listed in CASA Document No. DT-5-C-99-5005, C-295 Equipment List. Federal Aviation Administration (FAA) approved Airplane Flight Manual . Construcciones Aeronauticas S.A. Model C-295, Document No. D.T. 5-C-97-5006, published in the English language (DGAC approved on behalf of the FAA). C-295FW “FW variant” For C-295FW variant, the approved equipment is related in the TC-holder document number: TEA-5-DT-200289 “C-295FW Equipment List. Federal Aviation Administration (FAA) approved Airplane Flight Manual TAE-5-DT- 160180 “C-295FW EASA-Approved Airplane Flight Manual” • TAE-5-DT-160180_FAA C-295FW EASA-Approved Airplane Flight Manual • TAE-5-DT-160180_FAA Basic Revision No.1 C-295FW EASA-Approved AFM TAE-5-DT-160180 • TAE-5-DT-160180 Basic Revision No.2_FAA - A Basic Revision No.2 C- 295FW EASA-Approved AFM TAE-5-DT-160180 • TAE-5-DT-160180 Basic revision nº 3 C-295FW EASA-Approved Airplane Flight Manual Or later FAA AFM approved Revision 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 31 of 31 A21NM 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.5-C-97-5007. - Maintenance Review Board Report, Document No. MRB C-295 PV.01. NOTES NOTE 1 Weight and Balance: (a) A current Weight and Balance must be in each aircraft at the time of original airworthiness certification and at all time thereafter except in the case of an operator having an FAA approved loading system for weight and balance control. (b) 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 applicable 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 components are listed in the Airworthiness Limitation as presented in section 1.4 of Construcciones Aeronauticas, S.A. Document No. D.T. 5-C-99-5008. 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. 5-C-99-5008. NOTE 5 On December 20, 2000, the DGAC submitted a statement (Ref. No: 61/C-255/00-354 ) that the C- 295 design complies with FAR §25.723 based on analysis of the CASA C-295 Main Landing Gear and Nose Landing Gear shock absorption tests, contingent on the inclusion of modification S30429. The FAA has accepted the DGAC’s statement of compliance, and finds the CASA C-295 aircraft complies with FAR §25.723. Consequently the CASA Model C-295 Type Certificate, with Type Design Document (Master Drawing List) DT-98-3308 Rev C and modification S30429 will be valid after December 31, 2000, the date of expiration for Partial Grant of Exemption No. 7088. Accordingly, all CASA Model C-295 aircraft certificated in the United States must include modification S30429. NOTE 6 For C-295FW variant Airworthiness Limitations are provided as follow: Safe Life Airworthiness Limitation Items are provided in the C-295FW Airworthiness Limitations Section (ALS) Part 1 of document TAE-5-DT-170120, “C-295FW Version Airworthiness Limitations”. Damage-Tolerant Airworthiness Limitation Items are provided in the C-295FW Airworthiness Limitations Section (ALS) Part 2 of document TAE-5-DT-170120, “C-295FW Version Airworthiness Limitations”. Certification Maintenance Requirements are provided in the C-295FW Airworthiness Limitations Section (ALS) Part 3 of document TAE-5-DT-170120, “C-295FW Version Airworthiness Limitations”. C-295FW System Equipment Maintenance Requirements are provided in the C-295FW Airworthiness Limitations Section (ALS) Part 4 of document TAE-5-DT-170120, “C-295FW Version Airworthiness Limitations”. C-295FW Fuel System Airworthiness Limitations are provided in in the C-295FW Airworthiness Limitations Section (ALS) Part 5 of document TAE-5-DT-170120, “C-295FW Version Airworthiness Limitations”. Maintenance Review Board Report (MRBR), TC holder document number MRBR C-295-PV01. . .END ``` ## ADs (52, first 50, in force first) - [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025 - [AD 2024-25-05](https://openairdocs.org/ad/2024-25-05): Landing Gear · Airbus Defense and Space CN-235, CN-235-200 and CN-235-300. Effective Feb 12, 2025 - [AD 2024-24-04](https://openairdocs.org/ad/2024-24-04): Stabilizers · Airbus Defense and Space CN-235, CN-235-200, CN-235-300 and 1 more. Effective Jan 13, 2025 - [AD 2023-25-11](https://openairdocs.org/ad/2023-25-11): Fuselage · Airbus Defense and Space CN-235, CN-235-100, CN-235-200 and 2 more. Effective Feb 7, 2024 - [AD 2021-25-06](https://openairdocs.org/ad/2021-25-06): Time Limits/Maintenance Checks, Fuselage · Airbus Defense and Space CN-235, CN-235-100, CN-235-200 and 1 more. Effective Feb 15, 2022 - [AD 2021-06-08](https://openairdocs.org/ad/2021-06-08): Fuel · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective May 10, 2021 - [AD 2018-18-10](https://openairdocs.org/ad/2018-18-10): Doors · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective Oct 18, 2018 - [AD 2017-19-07](https://openairdocs.org/ad/2017-19-07): Fire protection · Airbus Defense and Space CN-235, CN-235-100, CN-235-200 and 1 more. Effective Oct 25, 2017 - [AD 2017-18-09](https://openairdocs.org/ad/2017-18-09): Stabilizers · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective Oct 10, 2017 - [AD 2017-10-15](https://openairdocs.org/ad/2017-10-15): Doors · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective Jun 29, 2017 - [AD 2017-01-05](https://openairdocs.org/ad/2017-01-05): Fuselage · Airbus Defense and Space CN-235, CN-235-100, CN-235-200 and 1 more. Effective Feb 15, 2017 - [AD 2016-26-03](https://openairdocs.org/ad/2016-26-03): Fuel · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective Feb 8, 2017 - [AD 2016-17-17](https://openairdocs.org/ad/2016-17-17): Doors · Airbus Defense and Space CN-235, CN-235-200 and CN-235-300. Effective Oct 5, 2016 - [AD 2016-11-08](https://openairdocs.org/ad/2016-11-08): Engine Controls · Airbus Defense and Space CN-235, CN-235-100 and CN-235-200. Effective Jul 6, 2016 - [AD 2016-07-18](https://openairdocs.org/ad/2016-07-18): Fire Protection · Airbus Defense and Space CN-235-200 and CN-235-300. Effective May 16, 2016 - [AD 2016-06-11](https://openairdocs.org/ad/2016-06-11): Wings · Airbus Defense and Space CN-235, CN-235-100, CN-235-200 and 1 more. Effective May 3, 2016 - [AD 2016-04-19](https://openairdocs.org/ad/2016-04-19): Flight Controls · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective Mar 14, 2016 - [AD 2014-13-15](https://openairdocs.org/ad/2014-13-15): Fuselage · EADS CASA CN-235-300. Effective Aug 19, 2014 - [AD 2012-01-04](https://openairdocs.org/ad/2012-01-04): Engine controls · EADS CASA CN-235-100, CN-235-200 and CN-235-300. Effective Mar 13, 2012 - [AD 2010-23-05](https://openairdocs.org/ad/2010-23-05): Fuel · EADS CASA C-295, CN-235, CN-235-100 and 2 more. Effective Dec 10, 2010 - [AD 2009-26-14](https://openairdocs.org/ad/2009-26-14): Wings · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Feb 4, 2010 - [AD 2009-18-06](https://openairdocs.org/ad/2009-18-06): Ice and rain protection · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Oct 1, 2009 - [AD 2004-07-16](https://openairdocs.org/ad/2004-07-16): Rudder trim control unit · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective May 11, 2004 - [AD 2001-12-12](https://openairdocs.org/ad/2001-12-12): Fuselage Skin Reinforcements · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Jul 23, 2001 - [AD 2001-09-08](https://openairdocs.org/ad/2001-09-08): Electrical Connector in the Electrical Master Central Unit. · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Jun 11, 2001 - [AD 2001-01-12](https://openairdocs.org/ad/2001-01-12): Fittings Connecting the Fuselage to Stiffener Rods · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective Feb 28, 2001 - [AD 99-23-22 R2](https://openairdocs.org/ad/99-23-22-R2): Transponders · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 74 more. Effective Apr 20, 2000 - [AD 2000-05-05](https://openairdocs.org/ad/2000-05-05): Anti-Icing Distributor Valves · EADS CASA CN-235-100 and CN-235-200. Effective Apr 12, 2000 - [AD 99-19-15](https://openairdocs.org/ad/99-19-15): AFM - Limitations Section - Ice Protection Systems · EADS CASA C-212-CB, C-212-CC, C-212-CD and 8 more. Effective Dec 27, 1999 - [AD 99-22-06](https://openairdocs.org/ad/99-22-06): Nose Landing Gear Turning Tube · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Nov 26, 1999 - [AD 98-16-23](https://openairdocs.org/ad/98-16-23): Inspect Flap Transmission Shafts For Cracking · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Sep 11, 1998 - [AD 98-12-34](https://openairdocs.org/ad/98-12-34): Forward Beam Of Vertical Stabilizer · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Jul 20, 1998 - [AD 98-11-23](https://openairdocs.org/ad/98-11-23): Fastener Holes Of Center Wing · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective Jul 8, 1998 - [AD 98-11-11](https://openairdocs.org/ad/98-11-11): Passenger And Crew Doors · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Jun 30, 1998 - [AD 98-06-14](https://openairdocs.org/ad/98-06-14): Contactor In Battery Circuit · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective Apr 20, 1998 - [AD 97-21-06](https://openairdocs.org/ad/97-21-06): Torsion Tubes and Fittings · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective Nov 24, 1997 - [AD 97-21-12](https://openairdocs.org/ad/97-21-12): Center Wing-To Fuselage Attachment Fitting · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective Nov 24, 1997 - [AD 97-10-07](https://openairdocs.org/ad/97-10-07): Propeller Brake System · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective Jun 16, 1997 - [AD 97-10-08](https://openairdocs.org/ad/97-10-08): Cargo Door Guide Hooks · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective Jun 16, 1997 - [AD 97-07-13](https://openairdocs.org/ad/97-07-13): Center Wing Attachment Rods · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective May 12, 1997 - [AD 96-09-22](https://openairdocs.org/ad/96-09-22): AFM - Icing · EADS CASA C-212-CB, C-212-CC, C-212-CD and 7 more. Effective Jun 11, 1996 - [AD 92-26-01](https://openairdocs.org/ad/92-26-01): Unsymmetrical Wing Surfaces · EADS CASA CN-235, CN-235-100 and CN-235-200. Effective Jan 12, 1993 - [AD 90-07-08 R1](https://openairdocs.org/ad/90-07-08-R1): Fluorescent Lighting and Remote Power Units · British Aerospace Regional Jetstream 3201, Jetstream Series 3101, Falcon 10 and 10 more. Effective Jul 2, 1990 - [AD 2021-02-18](https://openairdocs.org/ad/2021-02-18) (historical): Fuselage. · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective Mar 30, 2021 - [AD 2018-25-16](https://openairdocs.org/ad/2018-25-16) (historical): Time Limits/Maintenance Checks · Airbus Defense and Space CN-235, CN-235-200 and CN-235-300. Effective Jan 22, 2019 - [AD 2018-18-09](https://openairdocs.org/ad/2018-18-09) (historical): Horizontal stabilizer · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective Oct 10, 2018 - [AD 2017-19-25](https://openairdocs.org/ad/2017-19-25) (historical): Fuel · Airbus Defense and Space C-295, CN-235, CN-235-100 and 2 more. Effective Nov 1, 2017 - [AD 2013-23-02](https://openairdocs.org/ad/2013-23-02) (historical): Fuel · EADS CASA C-295, CN-235, CN-235-100 and 2 more. Effective Dec 2, 2013 - [AD 2013-02-12](https://openairdocs.org/ad/2013-02-12) (historical): Fire protection · EADS CASA CN-235, CN-235-100, CN-235-200 and 1 more. Effective Mar 8, 2013 - [AD 2008-09-22](https://openairdocs.org/ad/2008-09-22) (historical): Fuel Tank System · Construcciones Aeronauticas C-295, CN-235, CN-235-100 and 2 more. Effective Jun 5, 2008 All 52: https://openairdocs.org/tcds/A21NM/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Airbus Defense And Space S A C-295](https://openairdocs.org/model/airbus-defense-and-space-s-a-c-295): 5 aircraft (registry code 3950012) - [Construcciones Aeronauticas CN-235-300](https://openairdocs.org/model/construcciones-aeronauticas-cn-235-300): 5 aircraft (registry code 2410307) - [Construcciones Aeronauticas CN-235](https://openairdocs.org/model/construcciones-aeronauticas-cn-235): 4 aircraft (registry code 2410306) - [CASA CN235](https://openairdocs.org/model/casa-cn235): 1 aircraft (registry code 2410256) - [Construcciones Aeronauticas CN 235-200](https://openairdocs.org/model/construcciones-aeronauticas-cn-235-200): 1 aircraft (registry code 2410308) - [C A S A CN-235-100](https://openairdocs.org/model/c-a-s-a-cn-235-100): 0 aircraft (registry code 2410305) - [EADS CASA CN-235-300](https://openairdocs.org/model/eads-casa-cn-235-300): 0 aircraft (registry code 241030B) ## STCs approved under this data sheet (25) - [STC ST01305WI-D](https://openairdocs.org/stc/ST01305WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation in accordance with Collins Drawing Index as listed on AML No. ST01305WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST00342BO](https://openairdocs.org/stc/ST00342BO): Installation of an NVIS / NVG Compatible Lighting System. ATI Engineering Services LLC - [STC ST03424CH](https://openairdocs.org/stc/ST03424CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC - [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc. - [STC ST01887WI](https://openairdocs.org/stc/ST01887WI): Installation of non-essential radome and component provisions, antennas, associated wiring and mounting provisions, and associated non-essential mission system components.. Sierra Nevada Corporation/Integrated Mission Systems - [STC ST01888WI](https://openairdocs.org/stc/ST01888WI): Installation of non-essential mission equipment configurable pallet assemblies.. Sierra Nevada Corporation-Integrated Mission Systems - [STC ST01889WI](https://openairdocs.org/stc/ST01889WI): Installation of a non-essential mission power and distribution system.. Sierra Nevada Corporation/Integrated Mission Systems - [STC ST01890WI](https://openairdocs.org/stc/ST01890WI): Installation of an EO/IR sensor and lift system in the left sponson.. Sierra Nevada Corporation-Integrated Mission Systems - [STC ST01891WI](https://openairdocs.org/stc/ST01891WI): Installation of an optional nose extension. Sierra Nevada Corporation-Integrated Mission Systems - [STC ST03776NY](https://openairdocs.org/stc/ST03776NY): Modification to upgrade existing Rockwell Collins TCAS (Model: TTR-920, TTR-921, and TTR-4000) at VERSION 7.0 to Rockwell Collins TCAS (Model: TTR-921, TTR-4000, and TTR-4100) at VERSION 7.1 (ACAS II). Scandinavian Avionics Design ApS - [STC ST00881WI-D](https://openairdocs.org/stc/ST00881WI-D): Modification of a TCAS II system installation to Change 7.0 or Change 7.1. Rockwell Collins Inc - [STC ST04211AT](https://openairdocs.org/stc/ST04211AT): Replace original equipment Nickel-Cadmium (NiCd) main batteries with Concorde Lead-Acid, main batteries along with associated hardware. Concorde Battery Corporation - [STC ST00266BO](https://openairdocs.org/stc/ST00266BO): Installation of a BAE Systems AN/AAR-57 Missile Warning System with an AN/ALE-47 Threat Adaptive Countermeasures Dispensing System. BAE Systems Information and Electronic Systems Integration Inc. - [STC ST01635WI-D](https://openairdocs.org/stc/ST01635WI-D): Modification of Rockwell Collins, Inc. VHF-4000 and VHF-4000E installations. Rockwell Collins Inc - [STC ST00234BO](https://openairdocs.org/stc/ST00234BO): Installation of a modified exhaust.. BAE SYSTEMS Information and Electronic Systems Integration Inc. - [STC ST02887CH-D](https://openairdocs.org/stc/ST02887CH-D): Installation of Universal Avionics Systems Corporation (UASC) EFI-890r Electronic Flight Display System. Duncan Aviation Inc - [STC ST00673WI-D](https://openairdocs.org/stc/ST00673WI-D): Modification of Collins VHF-22A/VHF-22B VHF COMM Receiver Transmitter with CTL-22 Control Pro Line II System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System installation.. Rockwell Collins Inc - [STC ST02887CH](https://openairdocs.org/stc/ST02887CH): Installation of Universal Avionics Systems Corporation (UASC) EFI-890r Electronic Flight Display System. Duncan Aviation Inc - [STC ST03537AT](https://openairdocs.org/stc/ST03537AT): Installation of a Single Class-A Sandel ST3400 Terrain Awareness Warning System with Remote Magnetic Indicator Function on copilot upper left instrument panel.. Presidential Airways Inc. - [STC ST02131LA](https://openairdocs.org/stc/ST02131LA): Installation of Cabin Interior Noise Reduction Kit. Aerocon Engineering Co. - [STC ST01142WI-D](https://openairdocs.org/stc/ST01142WI-D): Modification of a single or dual Collins TDR-94 or TDR-94D Mode S Transponder System installation with CTL-92 control head to a Flight ID capable Collins TDR-94 or TDR-94D Mode S Transponder System installation with CTL-92E control head.. Rockwell Collins Inc - [STC ST00844WI-D](https://openairdocs.org/stc/ST00844WI-D): Modification of Collins TCAS II or TCAS-94 (TCAS II) system installation with Collins TTR-920 Change 7.0 Receiver Transmitter to a Collins TCAS II or TCAS-94 OTCAS II) system installation with Collins TTR-921 or Collins TTR-4000 Change 7.0 TCAS Receiver Transmitter.. Rockwell Collins Inc - [STC ST01307WI-D](https://openairdocs.org/stc/ST01307WI-D): Modification of a Collins TVI-920/TVI-920D Vertical Speed/TCAS Indicator installation. Rockwell Collins Inc - [STC SA9169SC-D](https://openairdocs.org/stc/SA9169SC-D): Incorporated GPS approach capability to the existing certified GPS and EFIS installation.. L-3 Communications Integrated Systems LP --- 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.