TCDS A21SO

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A21SO Revision 9 Embraer S.A. EMB-110P1 EMB-110P2 January 21, 2022 TYPE CERTIFICATE DATA SHEET NO A21SO This data sheet which is part of Type Certificate No. A21SO 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 Embraer S.A. Av. Brigadeiro Faria Lima, 2.170 12227-901 São José dos Campos, SP Brazil Type Certificate Holder Record Yaborã Indústria Aeroná utica S.A. transferred TC No. A21SO to Embraer S.A. on January 1, 2022. Embraer S.A. transferred TC No. A21SO to Yaborã Indústria Aeronáutica S.A. on January 31, 2020. Empresa Brasileira de Aeronáutica S.A. (EMBRAER) changed company name to Embraer S.A. effective November 2010. I. - Model EMB-110P1 Bandeirante (Normal Category), Approved August 18, 1978 Engine 2 Pratt & Whitney of Canada Ltd. Pratt & Whitney PT6A-34 Fuel JP-4, JP-5, Jet A, Jet A-1 and Jet B, to conforming to P&W specifications PWA522 or CPW 46. See NOTE 4. Oil In accordance with P&W Specification PWA521 or CPW202 (MIL-L-23699A). Engine Limits PROP N1 GAS SHAFT GENERATOR SHP SPEED SPEED TIT_(°_C) Take-off 750 2200 101.5 790 Max. Continuous 750 2200 101.5 790 Starting --- --- --- 1090 (2 sec.) 925 (10 sec.) Max. Reverse (1 min.) 400 2068 790 Propeller and Propeller Limits 2 Hartzell HC-B3TN-3C/T10178H-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434- 5, 5P, 6P, 12P, 17P or 2 Hartzell HC-B3TN-3D/T10178HB-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434-6, 6P, 12P 17P; or 2 Hartzell HC-B3TN-3C/T10178-HB-8R Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434-6, 6P, 12P, 17P or Page No. 1 2 3 4 5 6 7 Rev. No. 9 8 7 8 9 8 6 A21SO Page 2 2 Hartzell HC-B3TN-3C/T10178-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434- 5, 5P, 6P, 12P, 17P or 2 Hartzell HC-B3TN-3D/T10178B-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434-6, 6P, 12P, 17P or 2 Hartzell HC-B3TN-3C/T10178B-8R Diameter: 93 in. (No further reduction permitted.) Spinner: Hartzell D3434-6, 6P, 12P, 17P. Pitch settings at 30 in. sta. Reverse: -11° ± 0.5° Feather: +88.1° ± 0.1° Primary pick-up angle: +20.2° ± 0.2° Secondary low pitch stop angle: 14° ± 1° Airspeed Limits Max. Operating Speed (See POH and ANAC approved AFM) Maneuvering Speed (See POH and ANAC approved AFM) Maximum Landing Gear Extended and Operating (Extension and Retraction) Speed Maximum Flap Extension Speed 25% (9.5°) 100 % (38°) 265 mph 195 mph 168 mph 207 mph 170 mph (230 knots) (169 knots) (146 knots) (180 knots) (148 knots) C. G. Range (Landing Gear Extended) (See NOTE 5) (+255.5) to (+272.0) at 12,500 lbs. (+251.3) to (+272.0) at 8818 lbs. or less Straight line variation between points given. Moment change due to retraction of landing gear: 10068 in. lbs. (The C. G. is shifted forward with retraction of landing gear). Empty Weight C. G. Range (See NOTE 5) None Maximum Weight (See NOTE 5) Take-off Landing Zero Fuel Ramp 12,500 lbs. 12,015 lbs. 12,015 lbs. 12,566 lbs. (See NOTE 8) (See NOTE 1) Minimum Crew Day VFR operations - (1) pilot All other operations - See POH/AFM. Number of Seats 21 seats Crew (+19) See loading instructions for passenger loading. See NOTE 9 for cargo version. Maximum Baggage (Passenger Configuration) 705 lbs. (+409.0) or, as optional 926 lbs. (+409.0) (per EMBRAER Drawing Nos. 110P1-863-40-51 and 110P1-856-24 Maximum Cargo (Cargo Configuration) Class "E" Compartment 3977 lbs. See cargo loading instructions. Maximum floor loading 100 lbs. / sq. ft. Fuel Capacity 454 gallons (227 gallons each tank) (+283.5) A21SO Page 3 Unusable fuel 7.4 gallons (3.7 gallons each tank) Oil Capacity 9.2 quarts in each engine (+226.4) 1 quart in each oil radiator (+226.0) Max. Operating Altitude 25,000 ft. Temperature Operating Limits Maximum: 43° C or ISA + 40° C, whichever is lower Minimum: -50° C II - Model EMB-110P2 Bandeirante (Normal Category) Approved October 1, 1979 Engine 2 Pratt & Whitney of Canada Ltd. Pratt & Whitney PT6A-34 Fuel JP-4, JP-5, Jet A, Jet A-1 and Jet B, conforming to P&W specifications PWA522 or CPW46. See NOTE 4. Oil In accordance with P&W Specification PWA521 or CPW202 (MIL-L-23699A). Engine Limits PROP N1 GAS SHAFT GENERATOR SHP SPEED SPEED TIT(°C) Take-off 750 2200 101.5 790 Max. Conditions 750 2200 101.5 790 Starting --- --- --- 1090 (2 sec.) 925 (10 sec.) Max. Reverse (1 min.) 400 2068 790 Propeller and Propeller Limits 2 Hartzell HC-B3TN-3C/T10178H-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434-5, 5P, 6P, 12P 17P; or 2 Hartzell HC-B3TN-3D/T10178HB-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434-6, 6P, 12P, 17P; or 2 Hartzell HC-B3TN-3C/T10178HB-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434-6, 6P, 12P, 17P, or 2 Hartzell HC-B3TN-3C/T10178-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434- 5, 5P, 6P, 12P, 17P or 2 Hartzell HC-B3TN-3C/T10178B-8R, Diameter: 93 in. (No further reduction permitted). Spinner: Hartzell D3434-6, 6P, 12P, 17P. Pitch settings at 30 in. sta. Reverse: -11° ± 0.5° Feather: +88.1° ± 0.1° Primary pick-up angle: +20.2° ± 0.2° Secondary low pitch stop angle: 14° ± 1° Airspeed Limits (IAS) Max. Operating Speed 265 mph (230 knots) (See POH and ANAC approved AFM) Maneuvering Speed 195 mph (169 knots) (See POH and ANAC approved AFM) A21SO Page 4 Maximum Landing Gear Extended and Operating (Extension and Retraction) Speed 168 (146 knots) Maximum Flap Extension Speed 25% (9.5°) 207 mph (180 knots) 100 % (38°) 170 mph (148 knots) C. G. Range (+255.5) to (+272.0) at 12,500 lbs. (Landing Gear Extended) (+251.3) to (+272.0) at 8818 lbs. or less (See NOTE 5) Straight line variation between points given. Moment change due to retraction of landing gear: 10068 in. lbs. (The C. G. is shifted forward with retraction of landing gear). Empty Weight C. G. Range None (See NOTE 5) Maximum Weight Take-off 12,500 lbs. (See NOTE 5) Landing 12,015 lbs. (See NOTE 8) Zero Fuel 12,015 lbs. Ramp 12,566 lbs. (See NOTE 1) Minimum Crew Day VFR operations - (1) pilot All other operations - See POH/AFM. Number of Seats 21 seats Crew (+19), passenger variable See loading instructions for passenger loading. Maximum Baggage 529 lbs. (+417.0) or , as optional 705 lbs. (+409.0) (per EMBRAER Drawing 110P1-856-10) Fuel Capacity 454 gallons (227 gallons each tank) (+283.5) Unusable fuel 7.4 gallons (3.7 gallons, each tank) Oil Capacity 9.2 quarts in each engine (+226.4) 1 quart in each oil radiator (+226.0) Max. Operating Altitude 25,000 ft. Temperature Operating Limits Maximum 43° C or ISA + 40° C, whichever is lower Minimum -50° C DATA PERTINENT TO ALL MODELS Datum 269.68 in. forward of the 28% wing chord line (frame 16). The 28% wing chord line is 37.13 in. forward of the rear jack points. Leveling Means Plumb from the support in the upper internal part of frame 16 using as reference a mark on the floor. Control Surface Movements Elevator 22° ± 1° Up 20° ± 1° Down Rudder 25° ± 1° Left 25° ± 1° Right Aileron 22° ± 1° Up 14° ± 1° Down Flap 38° ± 1° Down Elevator Tab ± 1° Left Tab 32° ± 2° Up and Down A21SO Page 5 Right Tab fixed (non-operational) Aileron Tab (left): Manual 18° ± 3° Up and Down Automatic Aileron Up 22° Aileron Tab Up 16° ± 2° (anti servo) Aileron Down 14° Aileron Tab Down 8° ± 2° (anti-servo) Rudder Tab Manual Right 12° ± 2° Left 11° ± 2° Automatic Rudder Right 25° - rudder Tab 12° ± 1° Left (servo) Rudder Left 25° - rudder tab 4.5° ± 1° Left (anti-servo) Serial Numbers Eligible A Brazilian Certificate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for U.S. certification is made. Import Requirements An FAA Standard Airworthiness Certificate may be issued on the basis of a Brazilian Certificate of Airworthiness for Export signed by a representative of the Agência Nacional de Aviação Civil (ANAC) of Brazil, formerly the Centro Tecnico Aeroespacial (CTA) of Brazil, containing the following statement: "The airplane covered by the certificate has been examined, tested, and found to conform to the type design approved under Type Certificate No. A21SO and to be in condition for safe operation." (See NOTE 6). 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 The EMB-110P1 was certificated showing compliance with: FAR 23 through Amendment 7, effective September 14, 1969, FAR 23.1529, Amendment 8, effective February 5, 1970: FAR 23.1441 through 23.1449, Amendment 9, effective June 17, 1970; FAR 23.1351(c)(4), Amendment 14, effective December 20, 1973; FAR 23.977, Amendment 17, effective February 1, 1977; FAR 23.785, Amendment 19, effective July 18, 1977; FAR 23.49, 23.65, 23.67, 23.77, and 23.1581 through 23.1589, Amendment 21, effective March 1, 1978; Equivalent safety level for FAR 23.1545(a) (Air Speed Indicator Marked in IAS); FAR 25.1439; Basic, effective December 24, 1964; FAR 25.787, 25.853., 25.855, 25.857, Amendment 32, effective May 1, 1972; (FAR 25 requirements for all cargo operations only) SFAR 27 through Amendment 1, effective January 1, 1975; FAR 36 through Amendment 6, effective June 24, 1977, FAR 135, Appendix A, effective June 19, 1970. Compliance has been shown with the ice protection requirements of FAR 23.1419, Amendment 23-14, effective December 20, 1973. Service Bulletins are approved by the ANAC. This approval is considered FAA approval. (This approval pertains to the design data only). Date of application for EMB-110P1; June 22, 1978. Type Certificate No. A21SO issued August 18, 1978. A21SO Page 6 Date of application for EMB-110P2 is March 22, 1977. T.C. A21SO amended to include P2. The EMB-110P2 was certificated showing compliance with the same regulations as EMB-110P1, except FAR 25.1439 and 25.857, which are applicable to cargo configurations only. Certain models of the EMB-110P1 and EMB-110P2 also comply with SFAR 41A, effective April 14, 1980. See NOTE 5. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. The "Basic Equipment Checklist," "Chart A," lists all the required and optional equipment and is included in the POH and ANAC approved AFM. Notes NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight and loading instructions must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center-of-gravity location must include system (undrainable) oil (not included in oil capacity) and unusable fuel (not included in usable fuel) as follows: Fuel 93 lbs. at (+285.8) Oil 1.1 lbs. at (+226.4) NOTE 2. All placards required in the Pilots Operating Handbook and ANAC Approved Airplane Flight Manual must be installed in the appropriate locations. The following Pilot's Operating Handbook and ANAC Approved Airplane Flight Manual is required: EMBRAER Publication No. TP-110P1/176, dated August 18, 1978 (with appropriate revisions). In addition, for those aircraft which have been approved for operation at increased weights permitted by SFAR 41A, a placard must be installed in the cockpit, in clear view of the pilot, which reads as follows: "THIS AIRPLANE IS APPROVED IN ACCORDANCE WITH SFAR 41A FOR MAXIMUM TAKEOFF WEIGHT OF 13,007 LBS. AND MAXIMUM LANDING WEIGHT OF 12,566 LBS." NOTE 3. The service life limits of the main structural parts are listed in the EMBRAER Maintenance Planning Guide, T.P. 110P2/145. These are summarized below: Wing and wing carry-through structure - 30,000 hours Front spar, lower boom to fuselage attachments (P/N's 4A-2111.00.03, 4A-2111.00.04, 4A-1231.50.04, 4A-1231.50.06) - 17,000 hours Engine mount - 21,000 hours Main landing gear: Piston tube, P/N 14333: 15,900 landings (for all models), or 12,700 landings (for SFAR 41A aircraft - See NOTE 5), or As determined by the equation: N = (15,900 - Nl)N1 + No 15,900 for aircraft modified per SB 110-32-047 (increase in maximum landing weight) or per SB 110-00- 003 (modifications to permit operation according to SFAR 41A) N = new life limit of the piston tube. Nl = accumulated landings of the piston tube at the date of modification No = 12,700 landings for SB 110-00-003, or 13,700 landings for SB 110-32-047 Half drag strut, P/N 14284-A and 14334-A: 18,750 landings. A21SO Page 7 NOTE 4. If fuel conforming to specifications PWA522 or CPW46 is not available it is permissible to use aviation gasoline MIL-G-7752 of all grades for a total time period not exceeding 150 hours during any overhaul period. NOTE 5. Aircraft modified in accordance with EMBRAER Drawing Number 110-P1-9000, Rev. 1, or S.B. 110-00-003 comply with requirements of SFAR 41A, effective April 14, 1980. For those aircraft, the following C. G. Ranges and Weights are applicable: C. G. Range For Landing: (+256. 9) to (+272.0) at 12,566 lbs. (Landing Gear (+255.0) to (+272.0) at 12,015 lbs. Extended) (+251.3) to (+272.0) at 8,818 lbs. or less Straight line variation between points given. For Takeoff: (+257.8) to (+272.0) at 13,007 lbs. (+256.9) to (+272.0) at 12,566 lbs. (+255.6) to (+272.0) at 12,566 lbs. (+251.3) to (+272.0) at 8818 lbs. or less Straight line variation between points given. Moment change due to retraction of landing gear: 10068 in lbs. (The CG is shifted forward with retraction of the landing gear). Empty Weight CG Range None Maximum Weight Ta keoff: 13,007 lbs. Landing: 12,566 lbs. Zero Fuel: 12,015 lbs. (See NOTE 1) Ramp 13,073 lbs. NOTE 6. The airworthiness certificate on those aircraft wh ich have been approved for operation at increased weights as permitted by SFAR 41A shall be endorsed as follows: "This airplane at weights in excess of 5,700 kg does not meet the airworthiness requirements of ICAO, as prescribed by Annex 8 of the Convention of International Civil Aviation." NOTE 7. For cargo version operation, Model EMB-110P1 must be equipped with: - Cargo net for 9 g (EMBRAER Drawing 110P1-9878-10-01). - Anti-smoke curtain (EMBRAER Drawing 110P1-9878-10-15). - Smoke detection system (EMBRAER Drawing 110P1-9788-10-01). - Protective breathing system and full face oxygen masks (EMBRAER Drawing 110P1-710-10). - Retention cargo net ( 3 g). NOTE 8. Models EMB-110P1 and EMB- 110P2 may increase the maximum landing weight to 12,500 lbs. if modified in accordance with EMBRAER SB 110-32-047. The following C.G. range is applicable. C. G. Range For Landing: (+256. 5) to (+272.0) at 12,500 lbs. (Landing Gear (+255.0) to (+272.0) at 12,015 lbs. Extended) (+251.3) to (+272.0) at 8,818 lbs. or less For Takeoff: (+255.6) to (+272.0) at 12,500 lbs. (+251.3) to (+272.0) at 8,818 lbs. or less Straight line variation between points given. NOTE 9. Cargo version must be maintained in accordance w ith the original certification requirements of a 10 or more passenger aircraft. ....END....