# TCDS A86EU: Aermacchi S.p.A. - Type: Type certificate data sheet - Status: Current - Holder: Aermacchi S.p.A. - Revision: 4 - Revised: March 11, 2022 - Product: Aircraft, Small Airplane - Certification basis: Part 23 - Data sheet PDF: https://openairdocs.org/files/sha256/06/a6/06a652db52ceb514f9d7985b8b82b6c071786483b83241f11b992d6f94533d38 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/E53A71DE1B58B87B86258805006FFCD3.0001 - Page: https://openairdocs.org/tcds/A86EU ## Models (1) As the data sheet lists them. - S.211A ## 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 TYPE CERTIFICATE DATA SHEET No. A86EU This data sheet which is a part of Type Certificate No. A86EU 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. AERMACCHI S.p.A. Via P. Foresio, 1 21040 Venegono Superiore (VA) Italy I - Model SIAI Marchetti S.211A (Acrobatic Category), Approved June 16, 1995 Engine 1 Pratt & Whitney Aircraft of Canada, JT15D-5C turbofan Fuel Jet A-1 or Jet B conforming to ASTM-D-1655 JP-4 conforming to MIL-6-83133 JP-5 conforming to MIL-T-5624 JP-8 conforming to MIL-T-83133 Anti-icing additive: for operations at external temperatures lower than +5 ºC, Ethylene Glycol Monomethyl Ether conforming to MIL-I-27686E must be blended into the aircraft fuel in concentrations not less than 0.06 percent or more than 0.15 percent by volume. For emergency use of Aviation Gasoline and fueling procedures, refer to Airplane Flight Manual. Oil According to Airplane Flight Manual. Engine Limits Static Thrust standard day, sea level: Take-off 1,418.9 daN (3190 Lbs) Maximum continuous 1,418.9 daN (3190 Lbs) Max permissible engine rotor operating speeds: NL (Fan) 16,540 r.p.m. 104 percent NH (Gas gen) 31,450 r.p.m. 96 percent Max permissible interturbine gas temperatures: Take-off 700º C Maximum continuous 700º C Page No. 1 2 3 4 5 6 Rev. No. 4 - - 3 4 - A86EU Revision 4 AEROMACCHI S.p.A. S.211A March 11, 2022 Airspeed Limits VMO (maximum operating) KIAS KCAS Between 8,000 ft e 17,500 ft 350 353 at 8,000 ft 210 (*) 213 at sea level 250 (*) 253 (*) linear variation for intermediate altitudes. MMO above 17,500 ft 0.72 Mach .72 Mach VA (design maneuvering) at 2900 Kg (6.394 Lbs) 280 283 See A.F.M. for variations with weight VO (operational maneuvering) at 2900 Kg. (6394 lbs) 260 263 See A.F.M. for variations with weight. VFE (flap extended) 160 162 VLE (landing gear extended) 160 162 VLO (landing gear operating) 160 162 C.G. Range FORWARD: (Landing gear retracted) +5.235 m.(206.1 in) (18.0% MAC) at 2,350 Kg (5181 Lbs) or less +5.296 m. (208.5 in) (21.66% MAC) at 2,900 Kg (6394 Lbs). AFT: +5.391 m. (212.3 in) (27.5% MAC) at all weights Linear variation between weights. Mean Aerodynamic 1.646 m. (64.80 in); % MAC at 4.939 m. (194.44 in) Chord (MAC) (from Datum) Datum 1.775 m. (69.88 in) in front of the forward cabin pressurized bulkhead Leveling Lateral: traverse bar placed on the cockpit sills Longitudinal: left hand cockpit sill Maximum Weight Take-off 2,900 Kg (6394 Lbs) Landing 2,900 Kg (6394 Lbs) Zero Wing Fuel 2,420 Kg (5335 Lbs) Equipment and Baggage 20 Kg (44 Lbs) in the ventral fuselage compartment, arm 4.337 m (170.75 in). Weight Minimum Crew 1 pilot (front cockpit) Number of Seats 2 (front and rear cockpit) Fuel Capacity Total: 894 Lt. (236 U.S. Gal.); Total usable: 867 Lt. (229 U.S. Gal.). (See Note 1). 3 A86EU Engine oil Capacity Total 9.0 Lt. (2.39 U.S. Gal.) Usable 9.9 Lt. (0.5 U.S. Gal.) (See Note 1). Maximum Operating Altitude. 40,000 ft Outside Temperature Limits. Between -25º C and + 45º C at sea level. Control Surface Flap Down 35º ± 1º Movements Aileron Up 24 º ± 1º Down 16º ± 1º Aileron trim Up 6º 20´ ± 1º Down 5º 40´ ± 1º Elevator Up 25º ± 1º Down 12º 30´ ± 1º Elevator servo Up 8º 45´± 1º Down 17º 30´ ± 1º tab Rudder Right 20º ± 1º Left 20º ± 1º Rudder trim Up 10º ± 1º Down 10º ± 1º Stabilizer trim Up 0º 30´ ± 15' Down 5º ± 15' Speedbrake Down 37º Serial Nos. Eligible. Each individual aircraft manufactured under this type certificate must be accompanied by an Export Certificate of Airworthiness as noted below under "Import Requirements" when an application for a U.S. airworthiness certificate is made. Model No. Siai Marchetti S211A: 201 and 202. Instructions to be accomplished to bring aircraft to the configuration required for receiving a U.S. Airworthiness Certificate are reported in SIAI Marchetti Technical Instruction Notes 211A-00-22-11 (S/N 201) and 211A-00-22-12 (S/N 202). Import Requirements. Country of Manufacturer: A U.S. airworthiness certificate may be issued on the basis of an Export Certificate of Airworthiness approved by an authorized representative of the Registro Aeronautico Italiano including the following statement: "The aircraft covered by this certificate has been examined, tested, and found to conform to the type design approved under Type Certificate A86EU and is in a condition for safe operation." Country other than Manufacturer (U.S. bilateral agreement and the original Export Certificate of Airworthiness issued by the country of manufacture must exist): A U.S. airworthiness certificate may be issued on the basis of a log book certifying statement endorsed by an authorized representative of the civil aviation authority of the exporting country. It is incumbent upon the exporting civil aviation authority to determine that the certifying statement includes evidence of acceptable service history and modification deviations and the following statement: "The aircraft covered by this certificate has been examined, tested, inspected in accordance with the provisions of FAR 21.183(d) or its equivalent, and found to conform to the type design approved under Type Certificate A86EU and is in a condition for safe operation." 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 - FAR Part 23 dated February 1, 1965 as amended through amendment 23-44 effective August 18, 1993. - Special Conditions (SC-23-ACE-80) effective June 16, 1995 in lieu of FAR 23.45, 23.51, 23.53, 23.65; 23.75; 23.77; 23.1581; 23.1583; 23.1585; 23.1587; 23.1589, and SC23.63; SC23.69; SC23.71; SC23.73. - Equivalent level of safety for FAR 23.562, [ACE No. 95-4], 23.677 (a) [ACE No. 95-5], 23.777 (f) (1) [ACE No. 95-6], 23.807 (b)(5) [ACE No. 95-11], 23.841 (a) and (b) (5) (6) [ACE No. 95-7], 23.971 (a) and (b) [ACE No. 95-8] 23.1182 [ACE No. 95-10], 23.1557 (d) [ACE No. 95-9] effective April 6, 1995. - FAR PART 34 effective September 10, 1990. - FAR PART 36 dated December 1, 1969, as amended through Amendment 36-20 effective September 16, 1992. Date of application for Type Certificate, July 9, 1993. The ENTE NAZIONALE per L’AVIAZONE CIVILE (ENAC) originally type Certificated this aircraft under its Type Certificate Number A 317 Effective September 29, 2005, and it is an Italian Annex II product. Validation Basis. Type Certificate A86EU was issued pursuant to FAR 21.29 in validation of Registro Aeronautico Italiano certification of compliance with the aforementioned certification basis, and in accordance with the standard airworthiness certificate provisions of FAR 21.183(c). NOTE: The airworthiness provisions of FAR 21.183(d) may be cited as the basis for issuance of standard airworthiness certificates for aircraft imported from a country other than the country of manufacture. Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. In addition, the following items of equipment are required: (a) Siai Marchetti S211A-R.A.I. approved Airplane Flight Manual P/N 211A- 00-38-01, dated June 6, 1995, or later RAI approved revisions. Import requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the ENTE NAZIONALE per L’AVIAZONE CIVILE (ENAC) 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 comply with ENAC’s Type Certificate No A317 approved under U.S. Type Certificate No. A 86EU and to be in a condition for safe operation”. 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. Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003- by ENTE NAZIONALE per L’AVIAZONE CIVILE (ENAC). Any such documents are accepted by the FAA and are considered FAA approved. · Service bulletins · Structural Repair Manuals · Vendor Manuals · Aircraft Flight Manuals, and · Overhaul and Maintenance Manuals NOTE 1. Current weight and balance report including list of equipment in the certificated empty weight, and loading instructions, must be provided for each aircraft at the time of original airworthiness certification, and at all time thereafter. The certificated empty weight and corresponding center of gravity location must include: - Unusable fuel: 20.5 Kg (45 Lbs) at 5.185 m. (204.13 in) and 1.6 Kg (3,6 Lbs) at 5.561 m. (218.93 in) for JP-5. 20.1 Kg (44 Lbs) at 5.185 m. (204.13 in) and 1.6 Kg (3,6 Lbs) at 5.561 m. (218.93 in) for JP-8/JET A-1 18.9 Kg (41,5 Lbs) at 5.185 m. (204.13 in) and 1.5 Kg (3,3 Lbs) at 5.561 m. (218.93 in) for JP-4 17.8 Kg (39 Lbs) at 5.185 m. (204.13 in) and 1.4 Kg (3 Lbs) at 5.561 m. (218.93 in) for AVGAS - Full Engine Oil: 8.6 Kg (19 lbs) at 7.3 m (287.4 in). - Undrainable Engine Oil: 0.5 Kg (1,1 Lbs) at 7.300 m. (287,4 in). NOTE 2 Placards (Refer to SIAI Marchetti Dwgs. B2-85001, B2-00416, B2- 21637, B2-25330, B2-21807, for a complete listing): All required placards as listed in the approved Airplane Flight Manual must be installed in the appropriate locations. (1) The following placard must be displayed in clear view of the pilot: "THE MARKING AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE ACROBATIC CATEGORY. OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THIS CATEGORY ARE CONTAINED IN THE AIRPLANE FLIGHT MANUAL." (2) Refer to the Airplane Flight Manual, Section 2, Limitations for a listing of other required placards. NOTE 3 Instructions for Continued Airworthiness and Service Life Limits of components are contained in the S211A Maintenance Manual (SIAI Marchetti Report 211A-00-39-01). Revisions to Airworthiness Limitations must be FAA approved. All manufacturer's service bulletins (and other manual material) which contain a statement that the document is approved by the exporting airworthiness authority (RAI) may be interpreted as FAA approved. These approvals pertain to the type design only. All service bulletins classified as Mandatory by the Italian Civil Aviation Authority are identified to that effect and are subject to an Airworthiness Directive issued by the FAA. Service documents required: S211A Maintenance Manual. Aircraft eligible for a standard airworthiness certificate must not be issued an airworthiness certificate unless the FAA has approved the Instructions for Continued Airworthiness. NOTE 4. As of January 1, 1997, AERMACCHI S.p.A. has acquired SIAI Marchetti S.r.L. .....END..... ``` ## ADs (1, in force first) - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 ## STCs approved under this data sheet (27) - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation - [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation - [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc - [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC - [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation - [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc - [STC SA00243BO](https://openairdocs.org/stc/SA00243BO): Installation of Centurion Consulting, Inc. GPS Steering Assist Module (SAM) with roll steering (p/n 0025-5100), or without roll steering (p/n 0025-5200).. Icarus Avionics, LLC - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA01473SE](https://openairdocs.org/stc/SA01473SE): Installation of a GTX 32 (mode C), GTX 33 (mode S), or GTX 33D (mode S with diversity) Remote Transponde. Garmin AT Inc. - [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc. - [STC SA01487SE](https://openairdocs.org/stc/SA01487SE): Installation of a GDL 69 or GDL 69A XM Satellite Receiver in accordance with Garmin Supplemental Type Certificate Master Data List, P/N 005-C0217-00, Revision A, dated December 20, 2004, or later FAA approved revision.. Garmin AT Inc. - [STC SA01157LA](https://openairdocs.org/stc/SA01157LA): Installation of Electronics International Model FP-5 or FP-5L fuel flow/fuel pressure instrument as a replacement instrument.. Electronics International Inc. - [STC SA02154AK](https://openairdocs.org/stc/SA02154AK): Installation of the UPS Aviation Technologies Inc. Apollo MX20 multi-function display, P/N 430-0270-500.. Garmin AT Inc. - [STC SA02217AK](https://openairdocs.org/stc/SA02217AK): Installation of Garmin AT Model GDL90 UAT Data Link System, in accordance with Garmin AT, Inc., GDL 90 UAT Master Data List, P/N 560-0278-01, Revision A, dated November 12, 2004, or later FAA approved revision.. Garmin AT Inc. - [STC SA02153LA](https://openairdocs.org/stc/SA02153LA) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. Garmin AT Inc. - [STC SA01933LA](https://openairdocs.org/stc/SA01933LA) (historical): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin AT Inc. - [STC SA01229SE](https://openairdocs.org/stc/SA01229SE) (historical): Installation of CNX80 GPS WAAS Navigator with integrated VHF Navigation and Communication radios.. UPS Aviation Technologies --- 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.