AD 79-18-07

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AD Number:
79-18-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Mooney Mite Models M-18L, M-18C, M-18LA, and M-18C55
Subject:
Wood Deterioration
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/03/1979
Make:
Mooney Mite Aircraft Corporation
Model:
M-18C | M-18C 55 | M-18L | M-18LA
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Superseded AD: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Superseded By: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: 79-18-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3547

AD NUMBER:   79-18-07

SUBJECT HEADING:   Airworthiness Directives; Mooney Mite Models M-18L, M-18C, M-18LA, and M-18C55

ACTION:  

SUMMARY:  

DATES:   Effective September 3, 1979.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   79-18-07 MOONEY: Amendment 39-3547. Applies to Mooney Mite Models M-18L S/N's 2 and up, M- 18C S/N's 201 and up, M-18LA S/N's 100 through 200, M-18C55 S/N's 323 and up, certificated in all categories.
Compliance required as indicated:
To prevent failure of structural areas due to wood deterioration and to detect other wood and glue joint deterioration in the fuselage and wood wing, accomplish the following within the next 30 days after the effective date of this AD, unless already accomplished within the last 35 months, and thereafter at intervals not to exceed 36 months from the last inspection.
(1) Remove the fabric inboard of station 12 on both wings over the main and auxiliary wing spars. Inspect spars for cracks and delaminations especially at all bolt hole locations and in the area of the landing gear attachments.
(2) If not already provided, apply a water resistant cloth or plastic adhesive such as duct tape at the wing to fuselage joint from the wing leading edge to the wing trailing edge under the metal fairing strip, to prevent entry of water at this point.
(3) Inspect all wood and glue joints in the wheel well area for cracks and wood deterioration.
(4) Remove fabric between fuselage stations 29 to 35.5. Inspect plywood joints for wood deteriorations.
(5) Apply hand pressure on top of plywood turtleback in the area of fuselage station 105. If softness is detected, remove fabric and inspect for wood cracks.
(6) Inspect welds for cracks and welds which do not completely fill fillet cross section area at rudder and elevator hinges and control horns with a 10-power glass.
(7) Inspect the fuel tank attachment points to the fuselage in the areas of the attachment bolts for deterioration.
(8) Inspect glue joints in the area of the battery for separation and deterioration.
(9) Clear all drain holes in fuselage.
(10) If any defects noted in paragraphs (1) through (8) above are detected, repair in accordance with FAA Advisory Circular AC 43.13-1A or approved equivalent, or replace with an identical new part or equivalent, prior to further flight. Equivalent repairs or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
(11) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection time in this airworthiness directive.
This amendment is effective September 3, 1979.

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