# TCDS G29EU: Agusta S.p.A. - Type: Type certificate data sheet - Status: Current - Holder: Agusta S.p.A. - Revision: 4 - Revised: March 1, 2012 - Product: Aircraft, Glider - Certification basis: Part 21 - Registered aircraft: 3, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/bc/b4/bcb48a46704fd48e9fbc035c0c52fe3f760fecffdb00a7f224028d0bdcf3f3ad - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/05D7E174DD99195E862579B30072D25A.0001 - Page: https://openairdocs.org/tcds/G29EU ## Models (2) As the data sheet lists them. - Calif A21 - Calif A21S ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 Rev No. 4 3 4 3 3 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION G29EU Revision 4 CAPRONI "Calif" A21 "Calif" A21S March 1, 2012 TYPE CERTIFICATE DATA SHEET No. G29EU This data sheet which is part of Type Certificate No. G29EU 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 Agusta S.p.A. Via Giovanni Agusta 520 21017 Cascina Costa Samarate (VA) Italy Type Certificate Ownership Record (1) This TC was considered not valid by the state of design on April 6, 2011, and has been replaced by European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) number EASA.SAS.A.118, issued April 6, 2011. Only standard airworthiness certificates issued prior to March 1, 2012 are valid. (2) Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness certificates of the aircraft if there is no entity to comply with 14 CFR § 21.99(a), “Required design changes.” (3) Replacement parts may not be available in the future. I. Model "Calif" A21 Glider, approved May 30, 1973. Airspeed Limits (I.A.S.) Never exceed speed 156 m.p.h. (136 knots) Maximum air brakes operating speed 156 m.p.h. (136 knots) Maximum maneuvering and rough air speed 105 m.p.h. (91 knots) Maximum flap speed (with any flap setting below the 8 "UP" setting) 100 m.p.h. (86 knots) Maximum landing gear extension speed 100 m.p.h. (86 knots) Maximum aero-tow speed 87 m.p.h. (75 knots) C.G. Range (+87.1 inches) to (98.0 inches) Empty Weight C.G. Range None Datum 78.7 inches forward of wing leading edge at root. Leveling Means Template P/N 001 on rear top surface of fuselage (Slope 206' tail down) Weight Limitations 1420 lb. maximum Number of Seats 2 (at +56.4 inches) Maximum Baggage None G29EU 2 Control Surface Movements Elevator Up 18   2  (see NOTE 4) Down 7   2  Rudder Right 5.7  1/2 inches Left 5.7  1/2 inches Flaps Up 8   1  The flap root ribs aligns with the fuselage Down 8   1  wing fairings when flaps are in the 8  "UP" position. Ailerons Up 45   3  Down 24   3  Air Brakes: The plane of the spoilers on the upper wing surface rotates 76  when air brakes are selected. Flap sections are driven down by spoilers. Weak Link for Towing 1200 lb. max. II. Model "Calif" A21S Glider, approved July 13, 1976. (Similar to "Calif" A21 except for: horizontal a nd vertical tail, trim device, flap down setting.) Airspeed Limits (I.A.S.) Never exceed speed 156 m.p.h. (136 knots) Maximum air brakes operating speed 156 m.p.h. (136 knots) Maximum maneuvering and rough air speed 105 m.p.h. (91 knots) Maximum flap speed (with any flap setting below the 8 UP setting) 98 m.p.h. (84 knots) Maximum landing gear extension speed 100 m.p.h. (86 knots) Maximum aero-tow speed 87 m.p.h. (75 knots) C.G. Range (+87.1 inches) to (+98.0 inches) Empty Weight C.G. Range None Datum 78.7 inches forward of wing leading edge at root. Leveling Means Template P/N 001 on rear top surface of fuselage (Slope 206' tail down). Weight Limitations 1420 lb. maximum Number of Seats 2 (at +56.4 inches) Maximum Baggage None Control Surface Movements Elevator Up 30   3  Down 25   3  Rudder Right 26   2  Left 26   2  Flaps Up 8   1  The flap root ribs aligns with the fuselage Down 12   2  wing fairings when flaps are in the 8  "UP" position. Ailerons Up 45   3  Down 24   3  Air Brakes: The plane of the spoilers on the upper wing surface rotates 76  when air brakes are selected. Flap sections are driven down by spoilers. Weak Link for Towing 1200 lb. max. 3 G29EU DATA PERTINENT TO ALL MODELS Serial Numbers Eligible Only those aircraft serials hol ding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. The Registro Aeronautico Italiano Certifi cate of Airworthiness for Export endorsed as noted below under "Import Requirements" mu st be submitted for each individual glider for which application for standard airworthiness certification is made. Certification Basis FAR 21.29 and FA R 21.23, effective 1 February 1965. Type Certificate No. G29EU, issued 30 May 1973. Date of Application for Type Certificate: 18 September 1970. Validation Basis Type Certificate No. G29EU was issued pursuant to FAR 21.29(a)(1)(ii), effective 1 December 1969, in validation of the Regist ro Aeronautico Italiano's certification of compliance with the British Ci vil Airworthiness Requirements, Section E, Issue 2, dated 16 May 1960 (Italian Certification Basis) whic h was found to provide a level of safety equivalent to the aforemen tioned FAA Certification Basis. Import Requirements None elig ible after March 1, 2012. Previous to this date: A U.S. airworthiness certificate may be issued on the basis of a Certificate of Airworthiness for Export signed by a represen tative of the Registro Aeronautico Italiano, containing the following statement: a) For the Model "Calif" A21 "The glider covered by this certificat e has been examined, tested, and found to conform to the type design approved unde r FAA Certificate No. G29EU and is in a condition for safe operation". In addition, for glider Serial Nu mber 201, 204, 205, 206, 207, and 208, as applicable, the glider must be modi fied in accordance with the following Caproni- Vizzola Service Bulletins before origin al Standard Airworthiness Certification: (1) Service Bulletin No. 72-02, RAI-a pproved on 3 January 1973 for modification of the landing gear retraction lever. (Not applicable to S/N 208). (2) Service Bulletin No. 72-03, RAI-approved on 3 January 1973 to ensure correct angular travel of the ailerons. (Not applicable to S/N 208). (3) Service Bulletin No. 72-04, RAI-approved on 3 January 1973 to provide a means to visually inspect the fin front attachment. b) For the Model "Calif" A21S "The glider covered by this certificat e has been examined, tested, and found to conform to the type design approved under FAA Type Certificate No. G29EU and is in a condition for safe operation". Service Information Service bulletins, structural repa ir manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a st atement that the document is Registro Aeronautico Italiano (RAI) approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. G29EU 4 Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installe d in the glider for standard airworthiness certification. In addition the following equipment must be installed: A. For the Model "Calif" A21 (1) Instruments (non-cloud flying): a) Airspeed indicator marked as follows: Red Radial 156 m.p.h. (136 knots) Yellow Arc 105-156 m.p.h. (91-136 knots) Green Arc 43.5-105 m.p.h. (38-91 knots) White Arc 39.0-100 m.p.h. (34-86 knots) b) Altimeter c) Magnetic Compass (2) Additional instruments required for cloud flying: a) Turn and Bank Indicator b) Variometer B. For the Model "Calif" A21S (1) Instruments (non-cloud flying): a) Airspeed indicator marked as follows: Red Radial 156 m.p.h. (136 knots) Yellow Arc 105-156 m.p.h. (91-136 knots) Green Arc 43.5-105 m.p.h. (38-91 knots) White Arc 39.0-98 m.p.h. (84 knots) b) Altimeter c) Magnetic Compass (2) Additional instruments required for cloud flying: a) Turn and Bank Indicator b) Variometer (3) RAI approved Model "Calif" A21S Flight Manual. NOTE 1. Current weight and balance report including list of equipment in certificated empty weight, and loading instructions, when necessary, must be provided for each glider at the time of original certification. 5 G29EU NOTE 2. a) The following placard must be installed in full view of the pilot: (1) "This glider must be operated in compliance with the Operating Limitations stated in the form of placards, markings, and manuals". (2) "Cloud flying: permitted only when the following instruments are installed: 1) Airspeed Indicator 2) Altimeter 3) Magnetic Compass 4) Turn and Bank 5) Variometer" (3) "The following acrobatic maneuvers are approved: Spins (Flap up), spins (airbrakes extended), steep turns, and chandelles. Spins with flaps down are prohibited". Recommended entry speeds: - Steep Turns 150 km/h. 81 knots 98 m.p.h. - Chandelles 160 km/h. 86 knots 99 m.p.h. - Spins See Flight Manual (4) "Night flying is prohibited". (5) i) (For the Model "Calif" A21) Max. Air Brakes Operating Speed 156 m.p.h. (136 knots) Max. Maneuvering, and Rough Air Speed 105 m.p.h. (91 knots) Max. Flap Speed 100 m.p.h. (86 knots) Max. Landing Gear Extensi on Speed 100 m.p.h. (86 knots) Max. Aero-Tow Speed 87 m.p.h. (75 knots) Stall Speed - Air Brakes Extended 38.5 m.p.h. (33 knots) The max. flap speed limit applies to all flap positions below the 8 "Up" position. ii) (For the Model "Calif" A21S) Max. Air Brakes Operating Speed 156 m.p.h. (136 knots) Max. Maneuvering, and Rough Air Speed 105 m.p.h. (91 knots) Max. Flap Speed 98 m.p.h. (84 knots) Max. Landing Gear Extensi on Speed 100 m.p.h. (86 knots) Max. Aero-Tow Speed 87 m.p.h. (75 knots) Stall Speed - Air Brakes Extended 38.5 m.p.h. (33 knots) The max. flap speed limit applies to all flap positions below the 8 UP position. (6) "Maximum Weight: 1420 lb. C.G. Range: 87.1 inches to 98.0 inches". (7) "Weak Link - 1200 lb." (8) "Auto or winch launching prohibited". b) The following placard must be installed on the wing center carry-through section in the cabin. "No baggage allowed" G29EU 6 NOTE 3. (Reserved) NOTE 4. a) For the Model "Calif" A21 Locations for measuring the elevator, rudder, flaps, and aileron control surface movements are given in Table 4 of the RAI-approved "Calif" A21 Flight and Service Manual". Rigging information for the flaps and air brake spoilers, when the flap control ha ndle is in the air brake position is given in the Calif A21 Maintenance Manual. b) For the Model "Calif" A21S Locations for measuring the elevator, rudder, flap s and aileron control surface movements as well as rigging information for the flaps and air brake spoilers when the flap control handle is in the air brake position, are given in the Calif A21S Maintenance Manual. NOTE 5. a) For the Model "Calif" A21 Information essential for the prope r operation, maintenance, and inspection of the glider is contained in the RAI-approved "Calif A21 Flight and Service Manual". b) For the Model "Calif" A21S Information essential for the prope r operation, maintenance, and inspection of the glider is contained in the RAI-approved "Calif A21S Flight Manual" and in the "Calif A21S Maintenance Manual". NOTE 6. As of November 30, 1989, Caproni Vizzola Costru zioni Aeronautiche S.p.A. became a member of the Agusta S.p.A. Group. ...END... ``` ## ADs (1, in force first) - [AD 75-18-02](https://openairdocs.org/ad/75-18-02): Aileron Flutter · Agusta Calif A21 and Calif A21S. Effective Sep 30, 1976 ## Registered aircraft by registry model (OpenAirDocs) - [Caproni Vizzola CALIF A-21](https://openairdocs.org/model/caproni-vizzola-calif-a-21): 2 aircraft (registry code 1870101) - [Caproni Vizzola CALIF A 21 S](https://openairdocs.org/model/caproni-vizzola-calif-a-21-s): 1 aircraft (registry code 1870121) --- 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.