AD 87-22-02 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | SOCATA | TB 10 | Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes |
| aircraft | SOCATA | TB 20 | Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes |
| aircraft | SOCATA | TB 21 | Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes |
Unsafe Condition
Structural failure of the horizontal stabilizer/elevator attachment and loss of pitch control due to cracks on fuselage frame Number 9 in the area of the hinge and attachment fittings.
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Required Actions
Visually inspect for cracks on the forward and aft surface of fuselage frame Number 9 in the area of the hinge and attachment fittings. If cracks exist, replace the cracked fuselage frame with a new serviceable part. Repetitive inspections at intervals not exceeding 100 hours TIS are required unless modified by installed Modification No. 70 (SOCATA SB No. 35/1).
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Upon the accumulation of 700 hours total time-in-service (TIS) or within the next 25 hours TIS, whichever comes later, unless previously accomplished per AD 87-22-02 (unrevised). Repetitive inspections must be done at intervals not to exceed 100 hours TIS thereafter.
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Affected Aircraft
Socata Models TB 10, TB 20, and TB 21 (Serial Numbers 1 through 795 inclusive)
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Federal Register Abstract
Inspect for Cracks
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_87-22-02_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 87-22-02 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes Subject: Inspect for Cracks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/20/1988 Make: SOCATA Model: TB 10 | TB 20 | TB 21 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 87-22-02 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-6436 AD NUMBER: 87-22-02 R1 SUBJECT HEADING: Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes ACTION: SUMMARY: DATES: Effective February 20, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 87-22-02 R1 SOCATA: Amendment 39-5756 as revised by Amendment 39-6436. Applicability: Models TB 10, TB 20, and TB 21 (Serial Numbers 1 through 795 inclusive) airplanes certificated in any category. Compliance: Required as indicated in the body of the AD, unless already accomplished. To prevent structural failure of the horizontal stabilizer/elevator attachment and loss of pitch control, accomplish the following: (a) Upon the accumulation of 700 hours total time-in-service (TIS) or within the next 25 hours TIS, whichever comes later, unless previously accomplished per AD 87-22-02 (unrevised), visually inspect for cracks on the forward and aft surface of fuselage frame Number 9 (Socata P/N TB 10.21.010.102) in the area of the hinge and attachment fittings of the horizontal stabilizer/elevator. If the existence of a crack is uncertain, remove the horizontal stabilizer and attachment fittings and perform a dye penetrant inspection of the area. (1) If no cracks are found as a result of the inspection in paragraph (a) above, repeat the inspection at intervals not to exceed 100 hours TIS thereafter. (2) If cracks are found as a result of any of the above inspections, prior to further flight replace the cracked fuselage frame Number 9 with a new serviceable part. (b) The repetitive inspections specified in paragraph (a)(1) of this AD may be suspended for a period not to exceed 700 hours TIS after the repairs specified in paragraph (a)(2) have been accomplished. (c) If Modification No. 70, specified in SOCATA Service Bulletin No. 35/1, dated December 1987, has been installed on the airplane, and if no crack existed in the fuselage frame when Modification No. 70 was installed, then the repetitive inspections specified in paragraph (a)(1) are no longer required. (d) Airplanes may be flown in accordance with Section 21.197 of the FAR to a location where these inspections may be performed. Once any crack is detected on fuselage frame Number 9, no further flight is authorized until repairs are completed. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety, may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, 1000 Brussels, Belgium; Telephone 513.38.30, extension 2710/2711. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Product Support Manager, SOCATA-Groupe Aerospatiale, U.S. Marketing and Product Support, 2701 Forum Drive, Grand Prairie, Texas 75053; Telephone (214) 641-3614; or SOCATA-Groupe Aerospatiale, B.P. 38, 65001 Tarbes, France; Telephone 62 51 7300; or may examine these documents at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD revises AD 87-22-02, Amendment 39-5756. This amendment (39-6436, AD 87-22-02 R1) becomes effective on February 26, 1990. FOOTER:
Document Text
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AD Final Rules - DRS_87-22-02_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 87-22-02 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes Subject: Inspect for Cracks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/20/1988 Make: SOCATA Model: TB 10 | TB 20 | TB 21 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: 87-22-02 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-6436 AD NUMBER: 87-22-02 R1 SUBJECT HEADING: Airworthiness Directives; Socata Model TB 10, TB 20, and TB 21 Series Airplanes ACTION: SUMMARY: DATES: Effective February 20, 1988. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 87-22-02 R1 SOCATA: Amendment 39-5756 as revised by Amendment 39-6436. Applicability: Models TB 10, TB 20, and TB 21 (Serial Numbers 1 through 795 inclusive) airplanes certificated in any category. Compliance: Required as indicated in the body of the AD, unless already accomplished. To prevent structural failure of the horizontal stabilizer/elevator attachment and loss of pitch control, accomplish the following: (a) Upon the accumulation of 700 hours total time-in-service (TIS) or within the next 25 hours TIS, whichever comes later, unless previously accomplished per AD 87-22-02 (unrevised), visually inspect for cracks on the forward and aft surface of fuselage frame Number 9 (Socata P/N TB 10.21.010.102) in the area of the hinge and attachment fittings of the horizontal stabilizer/elevator. If the existence of a crack is uncertain, remove the horizontal stabilizer and attachment fittings and perform a dye penetrant inspection of the area. (1) If no cracks are found as a result of the inspection in paragraph (a) above, repeat the inspection at intervals not to exceed 100 hours TIS thereafter. (2) If cracks are found as a result of any of the above inspections, prior to further flight replace the cracked fuselage frame Number 9 with a new serviceable part. (b) The repetitive inspections specified in paragraph (a)(1) of this AD may be suspended for a period not to exceed 700 hours TIS after the repairs specified in paragraph (a)(2) have been accomplished. (c) If Modification No. 70, specified in SOCATA Service Bulletin No. 35/1, dated December 1987, has been installed on the airplane, and if no crack existed in the fuselage frame when Modification No. 70 was installed, then the repetitive inspections specified in paragraph (a)(1) are no longer required. (d) Airplanes may be flown in accordance with Section 21.197 of the FAR to a location where these inspections may be performed. Once any crack is detected on fuselage frame Number 9, no further flight is authorized until repairs are completed. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety, may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, 1000 Brussels, Belgium; Telephone 513.38.30, extension 2710/2711. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Product Support Manager, SOCATA-Groupe Aerospatiale, U.S. Marketing and Product Support, 2701 Forum Drive, Grand Prairie, Texas 75053; Telephone (214) 641-3614; or SOCATA-Groupe Aerospatiale, B.P. 38, 65001 Tarbes, France; Telephone 62 51 7300; or may examine these documents at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD revises AD 87-22-02, Amendment 39-5756. This amendment (39-6436, AD 87-22-02 R1) becomes effective on February 26, 1990. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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