| AD Number | 89-12-08 | Status | Active |
| Effective Date | July 10, 1989 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-6233 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Israel Aircraft Industries, Ltd. |
| Model(s) | 1121 1121A 1121B 1123 1124 1124A |
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, datedAugust 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.