AD 79-24-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Embraer S.A. | EMB-110P1 | Airworthiness Directives; Empresa Brasileira de Aeronautica, S.A. (Embraer) Models EMB-110P1 and EMB-110P2 Airplanes |
| aircraft | Embraer S.A. | EMB-110P2 | Airworthiness Directives; Empresa Brasileira de Aeronautica, S.A. (Embraer) Models EMB-110P1 and EMB-110P2 Airplanes |
Unsafe Condition
Failure of the flap supports and possible loss of the flaps due to cracks in the components near the attachment bolts.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect all flap supports with specified part numbers using a 10-power magnifying glass or dye-penetrant method for cracks near the attachment bolts. Replace cracked components before further flight. Adjust inspection intervals upon FAA approval if substantiating data is provided.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 50 hours time in service, unless already accomplished, and thereafter at intervals not to exceed 250 hours time in service
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Affected Aircraft
Embraer S.A. Models EMB-110P1 and EMB-110P2, certificated in all categories, with flap supports having part numbers 4A-2611.46.01, 4A-2621.46.01, 4A-2611.47.01, 4A-2611.48.01, 4A-2621.48.01, 4A-2116.01.01, 4A-2116.02.01 or 4A-2116.02.01N, 4A-2216.02.01 or 4A-2216.02.01N, 4A-2116.03.01, or 4A-2216.03.01.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Flap Supports
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_79-24-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 79-24-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Empresa Brasileira de Aeronautica, S.A. (Embraer) Models EMB-110P1 and EM...Show more Subject: Wing Flap Supports Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/21/1979 Make: Embraer S.A. Model: EMB-110P1 | EMB-110P2 Product Type: Aircraft Product Subtype: Small/Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 79-24-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3619 AD NUMBER: 79-24-05 SUBJECT HEADING: Airworthiness Directives; Empresa Brasileira de Aeronautica, S.A. (Embraer) Models EMB-110P1 and EMB-110P2 Airplanes ACTION: SUMMARY: DATES: Effective November 21, 1979. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 79-24-05 EMPRESA BRASILEIRA de AERONAUTICA, S.A. (EMBRAER): Amendment 39-3619. Models EMB-110P1 and EMB-110P2, certificated in all categories. Compliance is required within the next 50 hours time in service, unless already accomplished, and thereafter at intervals not to exceed 250 hours time in service. To prevent failure of the flap supports and possible loss of the flaps, accomplish the following: A. With the wing flaps extended, using a 10-power magnifying glass or dye- penetrant method, conduct an inspection of all the flap supports, part numbers listed below, installed on the wing and on the flaps, for cracks in the components near the attachment bolts. Flap Support Part Numbers 4A-2611.46.01 4A-2621.46.01 4A-2611.47.01 4A-2611.48.01 4A-2621.48.01 4A-2116.01.01 4A-2116.02.01 or 4A-2116.02.01N 4A-2216.02.01 or 4A-2216.02.01N 4A-2116.03.01 4A-2216.03.01 If any cracks are found, replace the component before further flight. B. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Southern Region, may adjust the inspection interval if the request contains substantiating data to justify the increase for that operator. C. Compliance with the provisions of this AD may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Southern Region. This amendment is effective November 21, 1979. FOOTER:
Document Text
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AD Final Rules - DRS_79-24-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 79-24-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Empresa Brasileira de Aeronautica, S.A. (Embraer) Models EMB-110P1 and EM...Show more Subject: Wing Flap Supports Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/21/1979 Make: Embraer S.A. Model: EMB-110P1 | EMB-110P2 Product Type: Aircraft Product Subtype: Small/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: 79-24-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3619 AD NUMBER: 79-24-05 SUBJECT HEADING: Airworthiness Directives; Empresa Brasileira de Aeronautica, S.A. (Embraer) Models EMB-110P1 and EMB-110P2 Airplanes ACTION: SUMMARY: DATES: Effective November 21, 1979. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 79-24-05 EMPRESA BRASILEIRA de AERONAUTICA, S.A. (EMBRAER): Amendment 39-3619. Models EMB-110P1 and EMB-110P2, certificated in all categories. Compliance is required within the next 50 hours time in service, unless already accomplished, and thereafter at intervals not to exceed 250 hours time in service. To prevent failure of the flap supports and possible loss of the flaps, accomplish the following: A. With the wing flaps extended, using a 10-power magnifying glass or dye- penetrant method, conduct an inspection of all the flap supports, part numbers listed below, installed on the wing and on the flaps, for cracks in the components near the attachment bolts. Flap Support Part Numbers 4A-2611.46.01 4A-2621.46.01 4A-2611.47.01 4A-2611.48.01 4A-2621.48.01 4A-2116.01.01 4A-2116.02.01 or 4A-2116.02.01N 4A-2216.02.01 or 4A-2216.02.01N 4A-2116.03.01 4A-2216.03.01 If any cracks are found, replace the component before further flight. B. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Southern Region, may adjust the inspection interval if the request contains substantiating data to justify the increase for that operator. C. Compliance with the provisions of this AD may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Southern Region. This amendment is effective November 21, 1979. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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