SOCATA TB-9 Tampico — Primary-Source Technical Documentation Collection

The SOCATA TB-9 Tampico is a French all-metal, low-wing, four-seat light aircraft developed by Socata (Groupe Aérospatiale / EADS) as a primary and instrument flight trainer. Powered by the Lycoming O-320-D2A (160 HP), the TB-9 became a cornerstone of European flight training fleets from the late 1980s through the 2000s, prized for its structural robustness, positive stability characteristics, and high demonstrated crosswind capability (25 knots).

This Living Collection brings together 15 original factory documents spanning the complete technical lifecycle of the TB-9 airframe — from airframe maintenance and structural inspection to parts identification, flight operations, and pilot information.

Document Manifest — 15 Original Factory Documents

Maintenance Manual Series (Socata / EADS-Socata):

• Maintenance Manual — Tome 1
• Maintenance Manual — Tome 2
• Maintenance Manual — Tome 3
• Maintenance Manual — Tome 4
• Maintenance Manual — Tome 5
• Electrical Maintenance Manual (TB 9–10–200) — Tome 1 (Référence: Z00.18320310E0R6)
• Electrical Maintenance Manual (TB 9–10–200) — Tome 2 (Référence: Z00.18320310E0R6)

Illustrated Parts Catalog Series (EADS-Socata, P/N Z00.18082009E0R15):

• Illustrated Parts Catalog — Tome 1
• Illustrated Parts Catalog — Tome 2
• Illustrated Parts Catalog — Tome 3
• Illustrated Parts Catalog — Tome 4
• Illustrated Parts Catalog — Tome 5

Flight Operations & Pilot Documentation:

• Manuel de Vol / Flight Manual — TB 9 (French, Socata / Groupe Aérospatiale)
• Pilot's Operating Handbook (POH) — TB-9
• Pilot's Information Manual — TB-9 (from S/N 948, Socata / Aérospatiale Matra, P/N T00.DUOPHPYE, September 1989)

Airframe & Engine Technical Reference

• Airframe: All-metal, low-wing monoplane — continuous heavy single milled spar construction
• Engine: Lycoming O-320-D2A — 4-cylinder, horizontally opposed, air-cooled, direct-drive
• Power Output: 160 HP (120 kW) at 2,700 RPM
• Fuel System: Carburetor induction — 40-gallon total capacity
• Electrical System: 28V DC — 70-amp engine-mounted alternator + backup battery
• MTOW: 1,060 kg (2,332 lbs)
• Max Cruise Speed: 109–115 KIAS
• VNE: 144 KIAS
• Rate of Climb (ISA, SL): 665–738 FPM
• Service Ceiling: 11,000 ft
• Max Range: 505–532 NM
• Max Demonstrated Crosswind: 25 knots
• Intentional Spins: Prohibited

Airworthiness & Engineering Bulletin Reference

Key mandatory actions tracked in this documentation set:

• SB 10-152 — Horizontal stabilizer spar inspection and corrosion repair (airframes >4 years or >2,000 flight hours)
• EASA AD F-1994-264R1 — Front wing attachment fitting NDT inspection (every 3,000 landings or 2,000 flight hours)
• SB 10-064 — Fuel tank venting line retrofit and replacement intervals

Active fleet documentation is managed via the Veryon Publications Service Catalog or Daher's official MySocata Portal.

⚠️ Regulatory Notice: Under FAA 14 CFR § 43.13 and EASA Part-M, any mechanic performing maintenance on an active aircraft must use current, manufacturer-approved revision-controlled data. This archival document does not satisfy that requirement.

This is an archival, static-copy edition fixed at its original publication date. Intended for historical reference, flight simulation, museum restoration, and educational use only. Not approved for active airworthiness maintenance under FAA 14 CFR § 43.13, EASA Part-M, or equivalent international regulations. Operators of active aircraft must use current, revision-controlled publications from the Type Certificate holder or an authorized distributor.

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