AD 96-16-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A320-211 | Airworthiness Directives; Airbus Model A320-200 Series Airplanes |
| aircraft | Airbus | A320-212 | Airworthiness Directives; Airbus Model A320-200 Series Airplanes |
| aircraft | Airbus | A320-214 | Airworthiness Directives; Airbus Model A320-200 Series Airplanes |
| aircraft | Airbus | A320-231 | Airworthiness Directives; Airbus Model A320-200 Series Airplanes |
| aircraft | Airbus | A320-232 | Airworthiness Directives; Airbus Model A320-200 Series Airplanes |
| aircraft | Airbus | A320-233 | Airworthiness Directives; Airbus Model A320-200 Series Airplanes |
Unsafe Condition
Internal damage to the shock absorber sub-assembly due to loose screws in the upper bearing dowels could result in overextension of the shock absorber and failure of the torque link, leading to inability of the MLG to retract and subsequent collapse of the MLG.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Modify the shock absorber assembly of the main landing gear (MLG) in accordance with Airbus Service Bulletin A320-32-1144. Compliance must be accomplished prior to the accumulation of 6,000 total landings since the shock absorber was removed, built, or overhauled, or within 6 months after the effective date of this AD, whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 6,000 total landings since the shock absorber of the main landing gear (MLG) was removed, built, or overhauled; or within 6 months after the effective date of this AD; whichever occurs later
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Airbus Model A320-200 series airplanes on which Airbus Modification 24594 (reference Airbus Service Bulletin A320-32-1144) has not been installed, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Landing Gear Shock Absorber Sub-Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_96-16-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 96-16-03 Document Type: AD Final Rules Docket Number: 95-NM-267-AD Subject Heading: Airworthiness Directives; Airbus Model A320-200 Series Airplanes Subject: Main Landing Gear Shock Absorber Sub-Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/03/1996 Make: Airbus Model: A320-211 | A320-212 | A320-214 | A320-231 | A320-232 | A320-233 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 [61 FR 39306 NO. 146 07/29/96] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 96-16-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 95-NM-267-AD AMENDMENT: 39-9703 AD NUMBER: 96-16-03 SUBJECT HEADING: Airworthiness Directives; Airbus Model A320-200 Series Airplanes ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-200 series airplanes, that requires modification of the shock absorber sub-assembly of the main landing gear (MLG). This amendment is prompted by reports of internal damage to the shock absorber sub-assembly due to loose screws in the upper bearing dowels. The actions specified by this AD are intended to prevent such damage, which could result in the overextension of the shock absorber and failure of the torque link. This situation may lead to the inability of the MLG to retract and subsequent collapse of the MLG. DATES: Effective September 3, 1996. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 3, 1996. ADDRESSES: The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-2797; fax (206) 227-1149. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Model A320-200 series airplanes was published in the Federal Register on April 29, 1996 (61 FR 18704). That action proposed to require modification of the shock absorber sub-assembly of the main landing gear (MLG). Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the three comments received. All three commenters support the proposed rule. Conclusion After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact The FAA estimates that 115 airplanes of U.S. registry will be affected by this AD, that it will take approximately 24 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operator. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $165,600, or $1,440 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 - [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 96-16-03 AIRBUS INDUSTRIE: Amendment 39-9703. Docket 95-NM-267-AD. Applicability: Model A320-200 series airplanes on which Airbus Modification 24594 (reference Airbus Service Bulletin A320-32-1144) has not been installed, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent damage to the internal area of the shock absorber sub-assembly, which could cause an overextension of the shock absorber and failure of the torque link, accomplish the following: (a) Prior to the accumulation of 6,000 total landings since the shock absorber of the main landing gear (MLG) was removed, built, or overhauled; or within 6 months after the effective date of this AD; whichever occurs later: Modify the shock absorber assembly of the MLG, in accordance with Airbus Service Bulletin A320-32-1144, dated December 8, 1994. NOTE 2: Airbus Service Bulletin A320-32-1144 references Dowty Aerospace Service Bulletin 200-32-215, dated July 7, 1994, and Dowty Aerospace Service Bulletin 200-32-216, Revision 1, dated November 18, 1994, as additional sources of service information for modification of the shock absorber. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with Airbus Service Bulletin A320-32-1144, dated December 8, 1994. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on September 3, 1996. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_96-16-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 96-16-03 Document Type: AD Final Rules Docket Number: 95-NM-267-AD Subject Heading: Airworthiness Directives; Airbus Model A320-200 Series Airplanes Subject: Main Landing Gear Shock Absorber Sub-Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/03/1996 Make: Airbus Model: A320-211 | A320-212 | A320-214 | A320-231 | A320-232 | A320-233 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 [61 FR 39306 NO. 146 07/29/96] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 96-16-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 95-NM-267-AD AMENDMENT: 39-9703 AD NUMBER: 96-16-03 SUBJECT HEADING: Airworthiness Directives; Airbus Model A320-200 Series Airplanes ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-200 series airplanes, that requires modification of the shock absorber sub-assembly of the main landing gear (MLG). This amendment is prompted by reports of internal damage to the shock absorber sub-assembly due to loose screws in the upper bearing dowels. The actions specified by this AD are intended to prevent such damage, which could result in the overextension of the shock absorber and failure of the torque link. This situation may lead to the inability of the MLG to retract and subsequent collapse of the MLG. DATES: Effective September 3, 1996. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 3, 1996. ADDRESSES: The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-2797; fax (206) 227-1149. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Model A320-200 series airplanes was published in the Federal Register on April 29, 1996 (61 FR 18704). That action proposed to require modification of the shock absorber sub-assembly of the main landing gear (MLG). Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the three comments received. All three commenters support the proposed rule. Conclusion After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact The FAA estimates that 115 airplanes of U.S. registry will be affected by this AD, that it will take approximately 24 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will be provided by the manufacturer at no cost to the operator. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $165,600, or $1,440 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 - [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 96-16-03 AIRBUS INDUSTRIE: Amendment 39-9703. Docket 95-NM-267-AD. Applicability: Model A320-200 series airplanes on which Airbus Modification 24594 (reference Airbus Service Bulletin A320-32-1144) has not been installed, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent damage to the internal area of the shock absorber sub-assembly, which could cause an overextension of the shock absorber and failure of the torque link, accomplish the following: (a) Prior to the accumulation of 6,000 total landings since the shock absorber of the main landing gear (MLG) was removed, built, or overhauled; or within 6 months after the effective date of this AD; whichever occurs later: Modify the shock absorber assembly of the MLG, in accordance with Airbus Service Bulletin A320-32-1144, dated December 8, 1994. NOTE 2: Airbus Service Bulletin A320-32-1144 references Dowty Aerospace Service Bulletin 200-32-215, dated July 7, 1994, and Dowty Aerospace Service Bulletin 200-32-216, Revision 1, dated November 18, 1994, as additional sources of service information for modification of the shock absorber. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with Airbus Service Bulletin A320-32-1144, dated December 8, 1994. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on September 3, 1996. FOOTER:
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