AD 76-15-02

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AD Number:
76-15-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Alexander Schleicher Model Rhonlerche II Gliders
Subject:
Torsion Tube Mount Area
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/02/1976
Make:
Alexander Schleicher GmbH & Co.
Model:
Rhonlerche II
Product Type:
Aircraft
Product Subtype:
Glider
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 76-15-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2674

AD NUMBER:   76-15-02

SUBJECT HEADING:   Airworthiness Directives; Alexander Schleicher Model Rhonlerche II Gliders

ACTION:  

SUMMARY:  

DATES:   Effective August 2, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   76-15-02 ALEXANDER SCHLEICHER: Amendment 39-2674. Applies to Rhonlerche II gliders, all serial numbers, certificated in all categories.

Compliance is required as indicated, unless already accomplished.

To detect cracks in the welded area between the flight control horizontal torsion tube and the front control stick mount and to prevent front control stick separation from the mount, accomplish the following:

(a) Within the next 10 hours time in service after the effective date of this AD visually inspect with a 5 power magnifier the welded area between the flight control horizontal torsion tube and the front control stick mount in accordance with Alexander Schleicher Technical Note No. 13, page 1, dated June 23, 1975, and page 2, dated July 1, 1975, or an FAA-approved equivalent.

(b) If a crack is found in performing the inspection required by paragraph (a) of this AD, prior to further flight, repair cracks and reinforce the torsion tube-mount area in accordance with Alexander Schleicher Technical Note No. 13, page 1, dated June 23, 1975, and page 2, dated July 1, 1975, or an FAA-approved equivalent.

(c) If no crack is found in performing the inspection required by paragraph (a) of this AD, within the next 100 hours time in service after the effective date of this AD, reinforce the torsion tube-mount area in accordance with Alexander Schleicher Technical Note No. 13, page 1, dated June 23, 1975, and page 2, dated July 1, 1975, or an FAA-approved equivalent.

This amendment becomes effective August 2, 1976.

FOOTER: