AD 76-06-07

AD Final Rules - DRS_76-06-07.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
76-06-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Morane Saulnier Model 760B Paris II Airplanes
Subject:
Inflight Fire
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/25/1976
Make:
SOCATA - Groupe Aerospatiale
Model:
M.S. 760B (Paris II)
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 76-06-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2543

AD NUMBER:   76-06-07

SUBJECT HEADING:   Airworthiness Directives; Morane Saulnier Model 760B Paris II Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 25, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   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 defective during 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.

FOOTER: