AD 84-02-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A300 B2-1A | Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes |
| aircraft | Airbus | A300 B2-1C | Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes |
| aircraft | Airbus | A300 B2-203 | Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes |
| aircraft | Airbus | A300 B2K-3C | Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes |
| aircraft | Airbus | A300 B4-103 | Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes |
| aircraft | Airbus | A300 B4-203 | Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes |
| aircraft | Airbus | A300 B4-2C | Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes |
Unsafe Condition
Failure of certain main landing gear components, including shock absorber sliding rod attachment fittings (part numbers C61643-4 and C61643-5) and hinge arm trunnions (part numbers C65381-2 and C65381-4), due to corrosion, cracks, or material removal exceeding one millimeter from the original profile.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Replace shock absorber sliding rod attachment fittings per MHB SB 470-32-172 Rev 1; inspect trunnion on actuating cylinder side of hinge arm per MHB SB 470-32-386 Rev 1, address corrosion/cracks by rework or replacement, and install seal per MHB SB 470-32-385; inspect lateral inboard trunnion for cracks per MHB SB 470-32-442, with recurring inspections at intervals not exceeding specified landings. Alternate means of compliance may be approved.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 180 days after February 27, 1984, or prior to accumulation of specified landings (13,000 for part C61643-4/5, 5,000 for initial inspection of C65381-2, 6,500 for C65381-2/4), whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Airbus Model A300 B2-1A, B2-1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 series airplanes with serial numbers specified in Airbus Industrie Service Bulletins A300-32-148 Rev 1, A300-32-328, and A300-32-365.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Landing Gear Components
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_84-02-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-02-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, ...Show more Subject: Main Landing Gear Components Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/27/1984 Make: Airbus Model: A300 B2-1A | A300 B2-1C | A300 B2-203 | A300 B2K-3C | A300 B4-103 | A300 B4-203 | A300 B4-2C 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: 84-02-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4795 AD NUMBER: 84-02-04 SUBJECT HEADING: Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes ACTION: SUMMARY: DATES: Effective February 27, 1984. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-02-04 AIRBUS INDUSTRIE: Amendment 39-4795. Applies to the Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 series airplanes, certificated in all categories. To prevent failure of certain main landing gear components, within 180 days after the effective date of this AD or prior to accumulation of the number of landings specified in each paragraph below, whichever occurs later, accomplish the following, unless previously accomplished: A. Prior to the accumulation of 13,000 landings, replace the shock absorber sliding rod attachment fittings, part numbers C61643-4 and C61643-5, with reinforced components in accordance with the instructions of Messier-Hispano-Bugatti (MHB) Service Bulletin 470-32-172, Revision 1, dated June 10, 1981, for aircraft having the serial numbers specified in Airbus Industrie (AI) Service Bulletin A300-32-148, Revision 1, dated December 29, 1978. B. Prior to the accumulation of 5,000 landings, inspect the trunnion on the actuating cylinder side of the hinge arm, part number C65381-2, in accordance with the instructions of MHB Service Bulletin 470-32-386, Revision 1, dated September 30, 1981, on airplanes having serial numbers specified in AI Service Bulletin A300-32-328, dated August 31, 1981. 1. If no corrosion is found, install a seal to improve the lubrication of the hinge arm trunnion in accordance with the instructions of MHB Service Bulletin 470-32-385, dated August 14, 1981 (related to AI Service Bulletin A300-32-326, dated August 31, 1981), and repeat the above inspections at intervals not to exceed 2,000 landings. 2. If corrosion or cracks are found, remove the corrosion and cracks in accordance with the instructions of MHB Service Bulletin 470-32-386, Revision 1, dated September 30, 1981, and install the seal in accordance with paragraph B.1, above. Repeat the above inspections at intervals not to exceed 250 landings. 3. If the depth of material removed when performing the rework of subparagraph B.2 is greater than one millimeter from the original profile, replace the hinge arm prior to further flight. C. Prior to the accumulation of 6,500 landings and thereafter at intervals not to exceed 400 landings, inspect the lateral inboard trunnion of the hinge arms, part numbers C65381- 2 and C65381-4, for cracks in accordance with the instructions of MHB Service Bulletin 470-32- 442, dated March 31, 1983, for aircraft having serial numbers specified in AI Service Bulletin A300-32-365, dated June 27, 1983. 1. For hinge arms that have incorporated modification MHB 595 in the trunnion located in the inboard position on the actuating cylinder side, the time limit is to be counted from the date of reconditioning. For all other cases, the time limit is to be counted from the day the arm was put into service. 2. The repetitive inspections required in paragraph C, above, may be terminated when the actions described in paragraph 2.C of MHB Service Bulletin 470-32-442, on the inboard, outboard, and forward trunnions are accomplished. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective February 27, 1984. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_84-02-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-02-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, ...Show more Subject: Main Landing Gear Components Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 02/27/1984 Make: Airbus Model: A300 B2-1A | A300 B2-1C | A300 B2-203 | A300 B2K-3C | A300 B4-103 | A300 B4-203 | A300 B4-2C 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: 84-02-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4795 AD NUMBER: 84-02-04 SUBJECT HEADING: Airworthiness Directives; AIRBUS INDUSTRIE Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 Series Airplanes ACTION: SUMMARY: DATES: Effective February 27, 1984. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-02-04 AIRBUS INDUSTRIE: Amendment 39-4795. Applies to the Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 series airplanes, certificated in all categories. To prevent failure of certain main landing gear components, within 180 days after the effective date of this AD or prior to accumulation of the number of landings specified in each paragraph below, whichever occurs later, accomplish the following, unless previously accomplished: A. Prior to the accumulation of 13,000 landings, replace the shock absorber sliding rod attachment fittings, part numbers C61643-4 and C61643-5, with reinforced components in accordance with the instructions of Messier-Hispano-Bugatti (MHB) Service Bulletin 470-32-172, Revision 1, dated June 10, 1981, for aircraft having the serial numbers specified in Airbus Industrie (AI) Service Bulletin A300-32-148, Revision 1, dated December 29, 1978. B. Prior to the accumulation of 5,000 landings, inspect the trunnion on the actuating cylinder side of the hinge arm, part number C65381-2, in accordance with the instructions of MHB Service Bulletin 470-32-386, Revision 1, dated September 30, 1981, on airplanes having serial numbers specified in AI Service Bulletin A300-32-328, dated August 31, 1981. 1. If no corrosion is found, install a seal to improve the lubrication of the hinge arm trunnion in accordance with the instructions of MHB Service Bulletin 470-32-385, dated August 14, 1981 (related to AI Service Bulletin A300-32-326, dated August 31, 1981), and repeat the above inspections at intervals not to exceed 2,000 landings. 2. If corrosion or cracks are found, remove the corrosion and cracks in accordance with the instructions of MHB Service Bulletin 470-32-386, Revision 1, dated September 30, 1981, and install the seal in accordance with paragraph B.1, above. Repeat the above inspections at intervals not to exceed 250 landings. 3. If the depth of material removed when performing the rework of subparagraph B.2 is greater than one millimeter from the original profile, replace the hinge arm prior to further flight. C. Prior to the accumulation of 6,500 landings and thereafter at intervals not to exceed 400 landings, inspect the lateral inboard trunnion of the hinge arms, part numbers C65381- 2 and C65381-4, for cracks in accordance with the instructions of MHB Service Bulletin 470-32- 442, dated March 31, 1983, for aircraft having serial numbers specified in AI Service Bulletin A300-32-365, dated June 27, 1983. 1. For hinge arms that have incorporated modification MHB 595 in the trunnion located in the inboard position on the actuating cylinder side, the time limit is to be counted from the date of reconditioning. For all other cases, the time limit is to be counted from the day the arm was put into service. 2. The repetitive inspections required in paragraph C, above, may be terminated when the actions described in paragraph 2.C of MHB Service Bulletin 470-32-442, on the inboard, outboard, and forward trunnions are accomplished. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective February 27, 1984. FOOTER:
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Retrieved: Apr 8, 2026
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