# TCDS 7A3: Jet Set Aviation Holdings SAS - Type: Type certificate data sheet - Status: Current - Holder: Jet Set Aviation Holdings SAS - Revision: 5 - Revised: July 27, 2012 - Product: Aircraft, Small Airplane - Certification basis: Part 3, Part 21, CAR 10 - Registered aircraft: 7, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/20/44/20440f0fc542f7070b085e03b7871b69b12b6fbb76194cdc96df920aa55e2d9b - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DF8E9CB74868C3F38625815900722950.0001 - Page: https://openairdocs.org/tcds/7A3 ## Models (3) As the data sheet lists them. - M.S. 760B (Paris II) - M.S. 760 (Paris I) - M.S. 760.A (Paris IA) ## 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 Rev. No. 5 2 4 4 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 7A3 Revision 5 JET SET AVIATION HOLDINGS M.S. 760 M.S. 760 A M.S. 760 B July 27, 2012 TYPE CERTIFICATE DATA SHEET NO. 7A3 This data sheet which is a part of type certificate No. 7A3 prescribe s conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Jet Set Aviation Holdings SAS 38 rue de Berri 75008 - PARIS France Type Certificate Holder Record SOCATA transferred TC No. 7A3 to Jet Set Aviation Holdings SAS on July 28, 2010. I - Model M.S. 760 (Paris I) - (Utility Category), Approved July 3, 1958. Engines 2 Turbomeca Marbore II C turbojets Fuel Aviation Kerosene or JP.1 or JP.4 or JP.5 or Aviation Gasoline 100/130 and 80/87 Engine limits For all operations, 22,600 rpm (880 lb. sea level static thrust) Airspeed limits (CAS) Vne (Never exceed) 403 mph (350 knots) Vno (Max. structural cruising) 345 mph (300 knots) Vp (Maneuvering) 265 mph (230 knots) Vfe (Flaps down 0° to 20°) 184 mph (160 knots) Vfe (Flaps down 20° to 55°) 161 mph (140 knots) Vle (Landing gear extended) 184 mph (160 knots) Vmc (Minimum control) 115 mph (100 knots) For values of never exceed speed at other altitudes (never exceed Mach number Mne = 0.70) see Approved Flight Manual C.G. range (+109.2) to (+116.7) inches from datum at 6175 lb. or less (landing gear extended) (+110.7) to (+116.7) inches from datum at 7650 lb. Straight line variation between points given. Landing gear retraction moment (1002 in.lb.) (moves the C.G. aft) Maximum weight Take-off : 7650 lb. Landing : 6960 lb. Fuel capacity (370 U.S. gal.) total Main tank (246 U.S. gal.) (+120) 2 wing tip tanks (62 U.S. gal.) each (+110) Page 2 of 5 7A3 II - Model M.S. 760.A (Paris IA) - (Utility Category), Approved December 22, 1965 (Same as M.S. 760 except for engine installation) Engines 2 Turbomeca Marbore VI C turbojets Fuel Aviation Kerosene or JP.1 or JP.4 or JP.5 or Aviation Gasoline 100/130 and 80/87 Engine limits For all operations, 21,500 rpm (1060 lb. sea level static thrust)) Airspeed limits (CAS) Vne (Never exceed) (tips tanks empty) 403 mph (350 knots) (tips tanks not empty) 345 mph (300 knots) Vno (Max. structural cruising) 345 mph (300 knots) Vp (Maneuvering) 265 mph (230 knots) Vfe (Flaps down 0° to 20°) 184 mph (160 knots) Vfe (Flaps down 20° to 55°) 161 mph (140 knots) Vle (Landing gear extended) 184 mph (160 knots) Vmc (minimum control) 115 mph (100 knots) For values of never exceed speed at other altitudes (never exceed Mach number Mne = 0.70) see Approved Flight Manual. C.G. range (+109.2) to (+116.7) at 6175 lb. or less (landing gear extended) (+110.7) to (+116.7) at 7720 lb. Straight line variation between points given. Landing gear retraction moment (1002 in.lb.) (moves the C.G. aft) Maximum weight Take-off : 7720 lb. Landing : 6960 lb. Fuel capacity (370 U.S. gal.) total Main tank (246 U.S. gal.) (+120) 2 wing tip tanks (62 U.S. gal.) each (+110) III - Model M.S. 760 B (Paris II) - (Utility Category), Approved December 22, 1965 (Same as M.S. 760 except for engine installation, reinforced landing gear, new wheels and brakes, leading edge fuel tanks, main tank fuel dump system, reinforcement of fuselage nose structure, and increase in thickness of center-wing skin.) Engines 2 Turbomeca Marbore VI C turbojets Fuel Aviation Kerosene or JP.1 or JP.4 or JP.5 or Aviation Gasoline 100/130 and 80/87 Engine limits For all operations, 21,500 rpm (1060 lb. sea level static thrust) Airspeed limits (CAS) Vne (Never exceed) (tips tanks empty) 403 mph (350 knots) (tips tanks not empty) 345 mph (300 knots) Vno (Max. structural cruising) 345 mph (300 knots) Vp (Maneuvering) 258 mph (215 knots) Vfe (Flaps down 0° to 20°) 184 mph (160 knots) Vfe (Flaps down 20° to 55°) 161 mph (140 knots) Vle (Landing gear extended) 184 mph (160 knots) Vmc (minimum control) 115 mph (100 knots) For values of never exceed speed at other altitudes (never exceed Mach number Mne = 0.70) see Approved Flight Manual Page 3 of 5 7A3 III - Model M.S. 760 B (Paris II) (cont'd) C.G. range (+109.2) to (+116.7) at 6175 lb. or less (landing gear extended) (+110.7) to (+116.7) at 8650 lb. Straight line variation between points given. Landing gear retraction moment (1002 in.lb.) (moves the C.G. aft) Maximum weight Take-off : 8650 lb. Landing : 6960 lb. Fuel capacity (485 U.S. gal.) total Main tank (246 U.S. gal.) (+120) 2 wing tip tanks (leading edge) (57 U.S. gal.) each (+110) 2 wing tip tanks (62 U.S. gal.) each (+110) IV - SPECIFICATIONS PERTINENT TO ALL MODELS Maximum operating altitude 25,000 ft. Empty weight C.G. range None Number of seats Four. 2 at (+45.9), 2 at (+78.5) Maximum baggage Forward compartment under rear seats 33 lb. ( +81) Rearward compartment rear fuselage baggage box 66 lb. (+206) Datum Forward face of the front bulkhead of the pressurized cabin, forward of rudder pedals. Leveling means Level from red painted rivets and nine rivnuts (three on the bottom of the fuselage, four on the lower surface of the wing, two on the horizontal tailplane). Use plumb bob. Three level points on the floor of the fuselage nose may be used for a level-gauge. Oil capacity 1.85 U.S. gal, each engine (+150) (total: 3.7 U.S. gal.) Control surface movements Flaps Down 55° Elevator (stab. at -2°30') Up 13° Down 12° Aileron Up 15° Down 9° Rudder Left 20° Right 20° Aileron Trim Tab Up 10° Down 10° Stabilizer M.S.760, M.S.760A Up 2°30' Down 2°30' M.S.760B Up 3° Down 2°30' Air brakes Upper 59°30' Lower 65°45' Serial numbers eligible A 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. Certification basis CAR 10, dated March 1955. CAR 3 November 1, 1949 including amendments 3-1 through 3-12, and Special Requirements notified to the Government of France by the Government of the United States of America. Type Certificate Number 7A3 issued July 3, 1958. Date of Application for Type Certificate, July 19, 1955. The Direction Générale de l’Aviation Civile (DGAC) originally type certificated this aircraft under its type certificate Number TC 3. The FAA validated this product under U.S. Type Certificate Number 7A3. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of France. Page 4 of 5 7A3 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 Direction Générale de l’Aviation Civile (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 comply with U.S. airworthiness regulations Civil Air Regulation Part 3 dated November 1, 1949, including amendments 3-1 through 3-12 approved under U.S. Type Certificate No. 7A3 and to be in a condition for safe operation.’ Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. Fire detection two installations A.B.G. Edison 1 lb. (+10.5) 2. Oxygen system (a) one oxygen bottle 264 U.S. gal. capacity (1.75 U.S. gal. under 2175 psi) SMG 40 17 lb. ( -18) (b) two oxygen regulator (front seats) Bronzavia 331 or 335 or 337 1.5 lb. (+23) (c) two oxygen regulators (rear seats) Bronzavia 331 or 335, or 337 1 lb. (+62) (d) four masks - Ulmer 16 M. 1 lb. each 2 at (+45) at (+57) 3. Stall warning indicator Safe Flight Instrument M.S. 760 4 lb. (+36) 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 the Direction Générale de l’Aviation Civile (DGAC). • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. NOTE 1. Current weight and balance report, including list of equipment in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of operators having an approved weight control system). NOTE 2. The following placards must be displayed on the instrument panel in full view of the pilot: Page 5 of 5 7A3 (a) THIS AIRPLANE MUST BE OPERATED AS A UTILITY CATEGORY AIRPLANE IN COMPLIANCE WITH THE APPROVED AIRPLANE FLIGHT MANUAL. ACROBATIC MANEUVERS, INCLUDING SPINS, ARE PROHIBITED EXCEPT THE FOLLOWING: LAZY EIGHTS, STEEP TURNS, CHANDELLES. (b) C.A.S. Minimum control speed, one engine inoperative 100 knots Max. speed flaps extended 0 to 20° 160 knots 20 to 55° 140 knots Max. speed gear extended 160 knots Max. speed rough air 300 knots (c) Never Exceed Speed Altitude C.A.S. Knots M.S. 760 M.S. 760A and B Empty Tip Tanks With any Fuel SL to 16,000 feet 350 350 300 20,000 feet 325 325 300 23,000 feet 305 305 300 25,000 feet 295 295 295 Max operating altitude 25,000 feet. Never exceed Mach Number 0.70 NOTE 3. The M.S. 760 can be converted to the M.S. 760A by installation of Marbore VI engine in accordance with the approved MORANE-SAULNIER modifications No. 4573, 4600, 4607 and 4639. Approved M.S. 760A Flight Manual must be used. NOTE 4. The M.S. 760 can be converted to the M.S. 760B by installation of the Marbore VI engine in accordance with the approved MORANE-SAULNIER modifications No. 4572, 4573, 4591, 4592, 4595, 4600, 4607, 4617, 4639. Approved M.S. 760B Flight Manual must be used. .....END..... ``` ## ADs (5, in force first) - [AD 2007-05-05](https://openairdocs.org/ad/2007-05-05): Limitations Section of the Airplane Flight Manual (AFM) · SOCATA - Groupe Aerospatiale M.S. 760 (Paris I), M.S. 760B (Paris II) and M.S. 760.A (Paris IA). Effective Apr 9, 2007 - [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 - [AD 77-15-14](https://openairdocs.org/ad/77-15-14): Landing Gear Wheels · SOCATA - Groupe Aerospatiale M.S. 760 (Paris I) and M.S. 760.A (Paris IA). Effective Aug 29, 1977 - [AD 76-06-07](https://openairdocs.org/ad/76-06-07): Inflight Fire · SOCATA - Groupe Aerospatiale M.S. 760B (Paris II). Effective Mar 25, 1976 - [AD 66-08-05](https://openairdocs.org/ad/66-08-05): Rudder Control System Rod · SOCATA - Groupe Aerospatiale M.S. 760 (Paris I), M.S. 760.A (Paris IA) and M.S. 760B (Paris II). Effective Apr 16, 1966 ## Registered aircraft by registry model (OpenAirDocs) - [Morane-Saulnier MS760](https://openairdocs.org/model/morane-saulnier-ms760): 5 aircraft (registry code 5910102) - [Morane-Saulnier MS760B](https://openairdocs.org/model/morane-saulnier-ms760b): 2 aircraft (registry code 5910106) - [Morane-Saulnier MS760 II](https://openairdocs.org/model/morane-saulnier-ms760-ii): 0 aircraft (registry code 5910108) ## STCs approved under this data sheet (34) - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc. - [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [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 SA02153LA-D PAGE 2](https://openairdocs.org/stc/SA02153LA-D%20PAGE%202): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [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 2](https://openairdocs.org/stc/SA00352BO%20PAGE%202): 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 2](https://openairdocs.org/stc/SA01229SE%20PAGE%202): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc - [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 SA02717NY PAGE 2](https://openairdocs.org/stc/SA02717NY%20PAGE%202): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC - [STC SA01692SE](https://openairdocs.org/stc/SA01692SE): Installation of a Garmin GMX 200 Multi-Function Display. Garmin International Inc - [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 SA02018SE-D](https://openairdocs.org/stc/SA02018SE-D): Provisions installation of Garmin GPS/XM Antennas in accordance with FAA Approved Model List (AML) SA02018SE-D, dated January 4, 2011, or later FAA approved revision, and FAA Approved GPS/XM Antenna STC Master Drawing List, Document No.: 005-00638-01, Revision 1 , approved on January 4, 2011, or later FAA approved revision.. Garmin International Inc - [STC SA1527SW](https://openairdocs.org/stc/SA1527SW): Modification of oxygen system. Airline Fueling Inc. - [STC SA1618SW](https://openairdocs.org/stc/SA1618SW): Installation of auxiliary fuel tank in nose compartment area. Airline Fueling Inc. - [STC SA2311SW](https://openairdocs.org/stc/SA2311SW): Install Bendix FCS-810 Automatic Flight Control System. Airline Fueling 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 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 SA2537WE](https://openairdocs.org/stc/SA2537WE): Installation of modified fuel system.. Aviation Research Corporation - [STC SA2554WE](https://openairdocs.org/stc/SA2554WE): Installation of antiskid power brake system, new main landing gear legs and Goodyear wheels and brakes.. Aviation Research Corporation - [STC SA2751WE](https://openairdocs.org/stc/SA2751WE): Installation of rear seat assembly, P/N N76091.. Aviation Research Corporation - [STC SA8907SW-D](https://openairdocs.org/stc/SA8907SW-D): Installation of S-TEC System 55 two axis automatic flight guidance system, Model ST-564, with optional automatic electric trim system.. S-TEC Corporation - [STC SA1-632](https://openairdocs.org/stc/SA1-632): Radome 2017, P/N 2017X-R for12-inch AVQ-50 antenna.. Chamberlain Aviation Inc - [STC SA02153LA-D](https://openairdocs.org/stc/SA02153LA-D) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International 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. --- 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.