AD 76-11-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Schempp-Hirth Flugzeugbau | Standard-Cirrus | Airworthiness Directives; Schempp Hirth Model Standard Cirrus Gliders |
Unsafe Condition
Tow release lever jamming and consequent crashing of the glider during a winch launch.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect the clearance between the tow release lever and the occupied pilot seat within the next 10 flights. If interference is found, reinforce the pilot seat per Schempp Hirth Technical Note 278-18 steps 2 and 3 before further flight. Otherwise, reinforce the seat within the next 50 flights.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 10 flights after the effective date of this AD (for inspection); within the next 50 flights after the effective date unless earlier compliance is required (for reinforcement).
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Affected Aircraft
Schempp-Hirth Flugzeugbau Standard-Cirrus gliders, serial numbers 1 through 604 for Schempp Hirth and 1G through 200G for Burkhart Grob.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Tow Release Mechanism
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_76-11-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 76-11-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Schempp Hirth Model Standard Cirrus Gliders Subject: Tow Release Mechanism Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/10/1976 Make: Schempp-Hirth Flugzeugbau Model: Standard-Cirrus Product Type: Aircraft Product Subtype: Glider Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 76-11-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2626 AD NUMBER: 76-11-03 SUBJECT HEADING: Airworthiness Directives; Schempp Hirth Model Standard Cirrus Gliders ACTION: SUMMARY: DATES: Effective June 10, 1976. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 76-11-03 SCHEMPP HIRTH and BURKHART GROB: Amendment 39-2626. Applies to Standard Cirrus gliders certificated in all categories, Serial Numbers 1 through 604 for Schempp Hirth and Serial Numbers 1G through 200G for Burkhart Grob. Compliance is required as indicated, unless already accomplished. To prevent possible tow release lever jamming and consequent crashing of the glider during a winch launch, accomplish the following: (a) Within the next 10 flights after the effective date of this AD, visually inspect the clearance between the tow release lever and the occupied pilot seat by performing a functional inspection of the operation of the tow release mechanism. If the occupied seat interferes with the operation of the tow release mechanism, before further flight, comply with paragraph (c) of this AD. (b) Within the next 50 flights after the effective date of this AD, unless earlier compliance is required pursuant to paragraph (a) of this AD, comply with paragraph (c) of this AD. (c) Reinforce the pilot seat in accordance with steps 2 and 3 of the paragraph entitled "Instructions" of Schempp Hirth Technical Note 278-18, dated December 8, 1975, or an FAA-approved equivalent, except that the minimum overall depth of the stiffening material used under step 2b should be 1/3 its width. This amendment becomes effective June 10, 1976. FOOTER:
Document Text
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AD Final Rules - DRS_76-11-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 76-11-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Schempp Hirth Model Standard Cirrus Gliders Subject: Tow Release Mechanism Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/10/1976 Make: Schempp-Hirth Flugzeugbau Model: Standard-Cirrus 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: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 76-11-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2626 AD NUMBER: 76-11-03 SUBJECT HEADING: Airworthiness Directives; Schempp Hirth Model Standard Cirrus Gliders ACTION: SUMMARY: DATES: Effective June 10, 1976. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 76-11-03 SCHEMPP HIRTH and BURKHART GROB: Amendment 39-2626. Applies to Standard Cirrus gliders certificated in all categories, Serial Numbers 1 through 604 for Schempp Hirth and Serial Numbers 1G through 200G for Burkhart Grob. Compliance is required as indicated, unless already accomplished. To prevent possible tow release lever jamming and consequent crashing of the glider during a winch launch, accomplish the following: (a) Within the next 10 flights after the effective date of this AD, visually inspect the clearance between the tow release lever and the occupied pilot seat by performing a functional inspection of the operation of the tow release mechanism. If the occupied seat interferes with the operation of the tow release mechanism, before further flight, comply with paragraph (c) of this AD. (b) Within the next 50 flights after the effective date of this AD, unless earlier compliance is required pursuant to paragraph (a) of this AD, comply with paragraph (c) of this AD. (c) Reinforce the pilot seat in accordance with steps 2 and 3 of the paragraph entitled "Instructions" of Schempp Hirth Technical Note 278-18, dated December 8, 1975, or an FAA-approved equivalent, except that the minimum overall depth of the stiffening material used under step 2b should be 1/3 its width. This amendment becomes effective June 10, 1976. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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