AD 76-06-07

76-06-07 MORANE SAULNIER (SOCATA): Amendment 39-2543. Applies to all MS 760B Paris II airplanes certificated in all categories, all serial numbers. Compliance is required as indicated, unless already accomplished. To prevent a possible inflight fire caused by overpressure in the auxiliary fuel tanks accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, install an operating limitation placard on the instrument panel in full view of the pilot that reads as follows:

FUEL TRANSFER SYSTEM OPERATING LIMITATIONS 1. Ground test PROHIBITED 2. Takeoff and climb TIP TANK OPEN LEADING EDGE CLOSED 3. Cruise LESS THAN 200 L. IN MAIN TANKS LEADING EDGE OPEN ONLY DURING TRANSFER 4. Descent LEADING EDGE OPEN

(b) Within the next 10 hours' time in service after the effective date of this AD, visually inspect the wing leading edge electric spot welds for proper weld integrity. (c) If a weld is found to be defectiveduring the inspection required by paragraph (b) of this AD, before further flight, repair the wing leading edge associated with the defective welds. (d) Within the next 100 hours' time in service after the effective date of this AD - (1) Visually inspect the engine bleed apertures for proper diameter; and (2) Inspect the auxiliary fuel tank overpressure valve for proper valve opening pressure. (e) If, during the inspection required by paragraph (d)(1) of this AD, an engine bleed aperture diameter is found not to be as follows, replace the engine bleed overpressure valve with a serviceable valve of the same part number or an FAA-approved equivalent: (1) For aircraft equipped with neither pneumatic deicers nor pneumatic gyros, 2 mm in diameter; (2) For aircraft equipped with pneumatic gyros only, 3 mm in diameter; (3) For aircraft equipped with pneumatic deicers with or without pneumatic gyros, 6 mm in diameter. (f) If, during the inspection required by paragraph (d)(2) of this AD, the auxiliary fuel tank overpressure valve is found not to begin opening at a fuel pressure of 250 +20 or -10 grams/cm (squared), replace the valve with a serviceable valve of the same part number or an FAA-approved equivalent. (g) For aircraft equipped with pneumatic deicers, within the next 100 hours' time in service after the effective date of this AD, install a 2.8 mm restrictor, P/N TN-0176-56.4.093, in the union at the entrance of the pressure reducing valve. (Socata Service Bulletin No. 14/1 dated July 1971 pertains to this AD.) This amendment becomes effective March 25, 1976.