AD 82-17-02

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AD Number:
82-17-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; ROLLADEN SCHNEIDER Model LS1-f and LS3 Sailplanes
Subject:
Airspeed Indicator
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/16/1982
Make:
DG Flugzeugbau GmbH
Model:
LS-3 | LS1-f
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Superseded AD: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Superseded By: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: 82-17-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4438

AD NUMBER:   82-17-02

SUBJECT HEADING:   Airworthiness Directives; ROLLADEN SCHNEIDER Model LS1-f and LS3 Sailplanes

ACTION:  

SUMMARY:  

DATES:   Effective August 16, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
82-17-02 ROLLADEN SCHNEIDER: Amendment 39-4438. Applies to Model Nos. LS1-f and LS3 sailplanes, certificated in any category, which do not have Rolladen Schneider Technical Bulletin No. 38/3013, dated June 18, 1979, incorporated.

Compliance is required as indicated, unless already accomplished.

To prevent potential sailplane structural failure or loss of control due to elevator flutter, accomplish the following:

a. Within the next 15 hours time in service after the effective date of this AD, unless already accomplished or unless the modification required by paragraph b of this AD has been accomplished, apply red tape to the air speed indicator and alter the airspeed limit placard restricting "never exceed airspeed" (VNE) to 124 MPH (200 km/H, 108 knots) in accordance with Rolladen Schneider Technical Bulletin No. 38/3013, dated June 18, 1979, paragraphs 1(a) and (b), or an FAA approved equivalent.

b. Modify the elevator control system in accordance with Rolladen Schneider Technical Bulletin No. 38/3013, dated June 18, 1979, paragraphs 2 and 3, or an FAA approved equivalent, by December 15, 1982. The placard and airspeed indicator alterations required by paragraph a of this AD may be removed when this modification is accomplished.

NOTE: Elevator control system modification consists of replacing the spring assembly in the elevator drive parallelogram mechanism with a solid link.

An equivalent means of compliance may be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, Brussels, Belgium, or the Chief, Boston Aircraft Certification Branch, ANE- 150, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803.

This amendment becomes effective August 16, 1982.

FOOTER: