AD 89-12-08
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Israel Aircraft Industries, Ltd. | 1121 | Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, Series Airplanes |
| aircraft | Israel Aircraft Industries, Ltd. | 1121A | Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, Series Airplanes |
| aircraft | Israel Aircraft Industries, Ltd. | 1121B | Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, Series Airplanes |
| aircraft | Israel Aircraft Industries, Ltd. | 1123 | Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, Series Airplanes |
| aircraft | Israel Aircraft Industries, Ltd. | 1124 | Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, Series Airplanes |
| aircraft | Israel Aircraft Industries, Ltd. | 1124A | Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, Series Airplanes |
Unsafe Condition
Cracks in the hinge lugs of the horizontal stabilizer aft spar splice fitting (hinge assembly), Part Number 453005-501.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct a visual inspection of the horizontal stabilizer aft spar splice fitting per specified IAI service bulletins within 75 flight hours after AD effective date (or within last 225 flight hours). If cracks found, replace the splice fitting before further flight per applicable service bulletins. Repeat inspections every 300 flight hours post-replacement.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 75 flight hours time-in-service after the effective date of this AD, unless previously accomplished within the last 225 flight hours time-in-service.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Israel Aircraft Industries, Ltd. Models 1121, 1121A, 1121B, 1123, 1124, and 1124A, series airplanes, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Horizontal Stabilizer
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_89-12-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-12-08 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and...Show more Subject: Horizontal Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/10/1989 Make: Israel Aircraft Industries, Ltd. Model: 1121 | 1121A | 1121B | 1123 | 1124 | 1124A Product Type: Aircraft Product Subtype: Large 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: 89-12-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-6233 AD NUMBER: 89-12-08 SUBJECT HEADING: Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, Series Airplanes ACTION: SUMMARY: DATES: Effective July 10, 1989. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-12-08 ISRAEL AIRCRAFT INDUSTRIES (IAI): Amendment 39-6233. Applicability: Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the hinge lugs of the horizontal stabilizer aft spar splice fitting (hinge assembly), accomplish the following: A. Within the next 75 flight hours time-in-service after the effective date of this AD, unless previously accomplished within the last 225 flight hours time-in-service, conduct a visual inspection of the horizontal stabilizer aft spar splice fitting (hinge assembly), Part Number 453005-501, in accordance with the following IAI service bulletins entitled "Horizontal Stabilizer Aft Spar Splice Fitting P/N 453005-501 (Hinge Assembly) Inspection", as appropriate: Model Service Bulletin 1121, 1121A, 1121B 1121-55-003, Revision 1, dated August 8, 1988 1123 1123-55-006, Revision 1, dated August 8, 1988 1124, 1124A 1124-55-020, Revision 2, dated August 8, 1988 B. If no cracks are found, repeat the inspection required by paragraph A., above, at intervals not to exceed 300 hours time-in-service. C. If cracks are found, replace the splice fitting prior to further flight, in accordance with the following IAI service bulletins entitled "Horizontal Stabilizer Assembly - Inspection, Repair, and Improvement (AFC 2037)," as appropriate: Model Service Bulletin 1121, 1121A, 1121B 1121-55-004, Revision 2, dated October 21, 1988 1123 1123-55-007, Revision 2, dated October 21, 1988 1124, 1124A 1124-55-021, Revision 3, dated October 21, 1988 D. Following replacement of the splice fitting, described in the above service bulletins, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 300 hours time-in-service. E. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Standardization Branch, ANM-113. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Israel Aircraft Industries, Delaware Office, P.O. Box 10086, Wilmington, Delaware 19850. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This AD supersedes AD 86-14-02, Amendment 39-5341, which became effective on August 4, 1986. This amendment (39-6233, AD 89-12-08) becomes effective on July 10, 1989. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_89-12-08.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-12-08 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and...Show more Subject: Horizontal Stabilizer Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/10/1989 Make: Israel Aircraft Industries, Ltd. Model: 1121 | 1121A | 1121B | 1123 | 1124 | 1124A Product Type: Aircraft Product Subtype: Large 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: 89-12-08 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-6233 AD NUMBER: 89-12-08 SUBJECT HEADING: Airworthiness Directives; ISRAEL AIRCRAFT INDUSTRIES (IAI) Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, Series Airplanes ACTION: SUMMARY: DATES: Effective July 10, 1989. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-12-08 ISRAEL AIRCRAFT INDUSTRIES (IAI): Amendment 39-6233. Applicability: Model 1121, 1121A, 1121B, 1123, 1124, and 1124A, series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the hinge lugs of the horizontal stabilizer aft spar splice fitting (hinge assembly), accomplish the following: A. Within the next 75 flight hours time-in-service after the effective date of this AD, unless previously accomplished within the last 225 flight hours time-in-service, conduct a visual inspection of the horizontal stabilizer aft spar splice fitting (hinge assembly), Part Number 453005-501, in accordance with the following IAI service bulletins entitled "Horizontal Stabilizer Aft Spar Splice Fitting P/N 453005-501 (Hinge Assembly) Inspection", as appropriate: Model Service Bulletin 1121, 1121A, 1121B 1121-55-003, Revision 1, dated August 8, 1988 1123 1123-55-006, Revision 1, dated August 8, 1988 1124, 1124A 1124-55-020, Revision 2, dated August 8, 1988 B. If no cracks are found, repeat the inspection required by paragraph A., above, at intervals not to exceed 300 hours time-in-service. C. If cracks are found, replace the splice fitting prior to further flight, in accordance with the following IAI service bulletins entitled "Horizontal Stabilizer Assembly - Inspection, Repair, and Improvement (AFC 2037)," as appropriate: Model Service Bulletin 1121, 1121A, 1121B 1121-55-004, Revision 2, dated October 21, 1988 1123 1123-55-007, Revision 2, dated October 21, 1988 1124, 1124A 1124-55-021, Revision 3, dated October 21, 1988 D. Following replacement of the splice fitting, described in the above service bulletins, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 300 hours time-in-service. E. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Standardization Branch, ANM-113. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Israel Aircraft Industries, Delaware Office, P.O. Box 10086, Wilmington, Delaware 19850. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This AD supersedes AD 86-14-02, Amendment 39-5341, which became effective on August 4, 1986. This amendment (39-6233, AD 89-12-08) becomes effective on July 10, 1989. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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