AD 76-13-11 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | K & L Soaring LLC | SGS 2-33 | Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, and SGU 2-22EK |
| aircraft | K & L Soaring LLC | SGS 2-33A | Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, and SGU 2-22EK |
| aircraft | K & L Soaring LLC | SGU 2-22C | Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, and SGU 2-22EK |
| aircraft | K & L Soaring LLC | SGU 2-22CK | Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, and SGU 2-22EK |
| aircraft | K & L Soaring LLC | SGU 2-22E | Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, and SGU 2-22EK |
| aircraft | K & L Soaring LLC | SGU 2-22EK | Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, and SGU 2-22EK |
Unsafe Condition
Failure of the forward and aft fuselage tubular longerons due to internal corrosion caused by trapped water.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Drill No. 41 holes in the forward keel tube and aft longerons, inspect for corrosion using x-ray or approved equivalent if water is present, repair or replace corroded parts, seal holes with screw or rivet and waterproof sealant. Equivalent means of compliance may be approved.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 30 days or 25 hours in service, whichever occurs first, after the effective date of this Airworthiness Directive.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Schweizer Models SGS 2-33, SGS 2-33A (S/N 1 thru 424), SGU 2-22C, SGU 2-22CK, SGU 2-22E, SGU 2-22EK (S/N 98 thru 258).
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Aft Fuselage Longerons
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_76-13-11_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 76-13-11 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, an...Show more Subject: Aft Fuselage Longerons Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/25/1988 Make: K & L Soaring LLC Model: SGS 2-33 | SGS 2-33A | SGU 2-22C | SGU 2-22CK | SGU 2-22E | SGU 2-22EK 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: 76-13-11 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5924 AD NUMBER: 76-13-11 R1 SUBJECT HEADING: Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, and SGU 2-22EK ACTION: SUMMARY: DATES: Effective May 25, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 76-13-11 R1 SCHWEIZER: Amendment 39-2659 as amended by Amendment 39-5924. Applies to SGS 2-33, SGS 2-33A, S/N's 1 thru 424, and SGU 2-22C, CK, E, EK, S/N's 98 thru 258. To prevent failure of the forward and aft fuselage tubular longerons due to internal corrosion caused by trapped water accomplish the following: Within the next 30 days or 25 hours in service, whichever occurs first, after the effective date of this Airworthiness Directive, unless already accomplished, perform the following or an approved equivalent inspection. (a) In the forward keel tube drill a No. 41 hole just ahead of the tow release slot. (b) In the aft longerons drill a No. 41 hole approximately one inch forward of the weld cluster at the tail skid in the lower longerons. (c) If there is any water drainage inspect for corrosion using x-ray or an approved equivalent inspection. (d) Repair corroded parts prior to further flight, in accordance with an approved repair or replace with an unused part of the same part number or an approved equivalent part. (e) Subsequent to the inspections, the No. 41 holes must be sealed with either a drive screw or a self plugging blind rivet. Holes may be enlarged to .125 inches for installation of a blind rivet. A waterproof sealant must be applied when installing the screw or rivet. (f) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, New England Region, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (g) Upon submission of substantiating data, by an owner or operator through an FAA Airworthiness Inspector, the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. (Schweizer Service Bulletin No. 102-33-1.1, covers this subject and is considered an approved equivalent inspection). Amendment 39-2659, became effective July 7, 1976. This Amendment 39-5924 amends AD 76-13-11, Amendment 39-2659 (41 FR 27029; July 1, 1976). This Amendment 39-5924 becomes effective on May 25, 1988. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_76-13-11_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 76-13-11 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, an...Show more Subject: Aft Fuselage Longerons Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/25/1988 Make: K & L Soaring LLC Model: SGS 2-33 | SGS 2-33A | SGU 2-22C | SGU 2-22CK | SGU 2-22E | SGU 2-22EK 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: 76-13-11 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5924 AD NUMBER: 76-13-11 R1 SUBJECT HEADING: Airworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, SGU 2-22C, SGU 2-22CK, SGU 2-22E, and SGU 2-22EK ACTION: SUMMARY: DATES: Effective May 25, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 76-13-11 R1 SCHWEIZER: Amendment 39-2659 as amended by Amendment 39-5924. Applies to SGS 2-33, SGS 2-33A, S/N's 1 thru 424, and SGU 2-22C, CK, E, EK, S/N's 98 thru 258. To prevent failure of the forward and aft fuselage tubular longerons due to internal corrosion caused by trapped water accomplish the following: Within the next 30 days or 25 hours in service, whichever occurs first, after the effective date of this Airworthiness Directive, unless already accomplished, perform the following or an approved equivalent inspection. (a) In the forward keel tube drill a No. 41 hole just ahead of the tow release slot. (b) In the aft longerons drill a No. 41 hole approximately one inch forward of the weld cluster at the tail skid in the lower longerons. (c) If there is any water drainage inspect for corrosion using x-ray or an approved equivalent inspection. (d) Repair corroded parts prior to further flight, in accordance with an approved repair or replace with an unused part of the same part number or an approved equivalent part. (e) Subsequent to the inspections, the No. 41 holes must be sealed with either a drive screw or a self plugging blind rivet. Holes may be enlarged to .125 inches for installation of a blind rivet. A waterproof sealant must be applied when installing the screw or rivet. (f) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, New England Region, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (g) Upon submission of substantiating data, by an owner or operator through an FAA Airworthiness Inspector, the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. (Schweizer Service Bulletin No. 102-33-1.1, covers this subject and is considered an approved equivalent inspection). Amendment 39-2659, became effective July 7, 1976. This Amendment 39-5924 amends AD 76-13-11, Amendment 39-2659 (41 FR 27029; July 1, 1976). This Amendment 39-5924 becomes effective on May 25, 1988. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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Related Airworthiness Directives
87-17-01
final ruleAirworthiness Directives; SCHWEIZER AIRCRAFT CORP Models (including kit built) SGU 1-7; SGS 2-8 (TG-2); SGS 2-12 (TG-3); SGU 1-19; SGU 1-20; SGU 1-21; SGU 2-22, 2-22A, 2-22C, 2- 22CK, 2-22E, 2-22EK; SGS 1-23, 1-23B, 1-23C, 1-23D, 1-23E, 1-23F, 1-23G, 1-23H, 1-23H15; SGS 1-24; SGS 1-26, 1-26A, 1-26B, 1-26C, 1-26D, 1-26E; SGS 2-32; SGS 2-33, 2-33A, 2- 33AK; SGS 1-34, 1-34R; SGS 1-35C; SGS 1-36 (SPRITE) Gliders,
Unsafe Condition: The possibility of the tow release assembly creating a jammed condition during towing and subsequent failure of the tow line to release, which could result in a forced landing.
87-02-01
final ruleAirworthiness Directives; SCHWEIZER AIRCRAFT CORP. All Schweizer Gliders (including kit built)
Unsafe Condition: The possibility of the tow-hook inadvertently slipping out of the release-arm and releasing the tow-line, which could result in a forced landing.
77-23-10
final ruleAirworthiness Directives; Schweizer Models SGS 2-33, SGS 2-33A, and 2-33AK Gliders
Unsafe Condition: Cracked vertical stabilizer spar-to-fuselage attachment bolts and spar web or elongated holes in the vertical stabilizer spar-to-fuselage attachment structure.
