AD 98-20-30
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus SAS | A320-111 | Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door |
| aircraft | Airbus SAS | A320-211 | Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door |
| aircraft | Airbus SAS | A320-212 | Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door |
| aircraft | Airbus SAS | A320-214 | Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door |
| aircraft | Airbus SAS | A320-231 | Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door |
| aircraft | Airbus SAS | A320-232 | Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door |
| aircraft | Airbus SAS | A320-233 | Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door |
Unsafe Condition
Fatigue cracking of the upper frame flanges could result in reduced structural integrity of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a high frequency eddy current inspection to detect fatigue cracking of the upper frame flanges. If no cracking is detected, either repeat the inspection at intervals not exceeding 1,200 flight cycles or modify the upper frame flanges. If cracking is detected, repair the flanges prior to further flight. A modification of the upper frame flanges constitutes terminating action.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 20,000 total flight cycles, or within 1,200 flight cycles after the effective date of this AD, whichever occurs later. For paragraph (b), prior to the accumulation of 26,000 total flight cycles, or within 6,000 flight cycles 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 series airplanes equipped with a bulk cargo door (Airbus Modification 20029), all serial numbers.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Upper Frame Flanges
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_98-20-30.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-20-30 Document Type: AD Final Rules Docket Number: 97-NM-192-AD Subject Heading: Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door Subject: Upper Frame Flanges Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/30/1998 Make: Airbus SAS Model: A320-111 | 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 [63 FR 51279 No. 186 09/25/98] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-20-30 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 97-NM-192-AD AMENDMENT: 39-10797 AD NUMBER: 98-20-30 SUBJECT HEADING: Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A320 series airplanes equipped with a bulk cargo door, that requires repetitive inspections to detect fatigue cracking of the upper frame flanges; and repair, if necessary. This amendment also requires modification of the upper frame flanges of the bulk cargo door, which constitutes terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking of the upper frame flanges, which could result in reduced structural integrity of the airplane. DATES: Effective October 30, 1998. 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: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 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 all Airbus Model A320 series airplanes equipped with a bulk cargo door was published in the Federal Register on August 7, 1998 (63 FR 42286). That action proposed to require repetitive inspections to detect fatigue cracking of the upper frame flanges; and repair, if necessary. That action also proposed to require modification of the upper frame flanges of the bulk cargo door, which constitutes terminating action for the repetitive inspections. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public. Conclusion 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 8 airplanes of U.S. registry will be affected by this AD. It will take approximately 1 work hour per airplane to accomplish the required inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspection required by this AD on U.S. operators is estimated to be $480, or $60 per airplane, per inspection cycle. It will take approximately 4 work hours per airplane to accomplish the required modification, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the modification required by this AD on U.S. operators is estimated to be $1,920, or $240 per airplane. The cost impact figures discussed above are 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: 98-20-30 AIRBUS INDUSTRIE: Amendment 39-10797. Docket 97-NM-192-AD. Applicability: Model A320 series airplanes, equipped with a bulk cargo door (Airbus Modification 20029), 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 (c) 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 fatigue cracking of the upper frame flanges, which could result in reduced structural integrity of the airplane, accomplish the following: (a) Prior to the accumulation of 20,000 total flight cycles, or within 1,200 flight cycles after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current inspection to detect fatigue cracking of the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1022, Revision 1, dated June 18, 1992. (1) If no cracking is detected, accomplish either paragraph (a)(1)(i) or (a)(1)(ii) of this AD. (i) Repeat the eddy current inspection thereafter at intervals not to exceed 1,200 flight cycles until accomplishment of the requirements of paragraph (b) of this AD. Or (ii) Prior to further flight, modify the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. This modification constitutes terminating action for the requirements of this AD. (2) If any cracking is detected, prior to further flight, repair in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. Accomplishment of the repair constitutes terminating action for the requirements of this AD. (b) Prior to the accumulation of 26,000 total flight cycles, or within 6,000 flight cycles after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current inspection to detect fatigue cracking of the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. (1) If no cracking is detected, prior to further flight, modify the upper frame flanges, in accordance with the service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of this AD. (2) If any cracking is detected, prior to further flight, repair in accordance with the service bulletin. Accomplishment of the repair constitutes terminating action for the requirements of this AD. (c) 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, International Branch, ANM-116, 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, International Branch, ANM-116. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (d) 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. (e) The inspections, repairs, and modification shall be done in accordance with the following Airbus service bulletins, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Shown on Page Revision Level Shown on Page Date Shown on Page A320-53-1022, Revision 1, June 18, 1992 1-6 7, 8 1 Original June 18, 1992 October 17, 1991 A320-53-1021, Revision 1, April 13, 1992 1, 4-24 2, 3 1 Original April 13, 1992 October 17, 1991 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. NOTE 3: The subject of this AD is addressed in French airworthiness directive 96-238- 091(B), dated October 23, 1996. (f) This amendment becomes effective on October 30, 1998. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_98-20-30.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-20-30 Document Type: AD Final Rules Docket Number: 97-NM-192-AD Subject Heading: Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door Subject: Upper Frame Flanges Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/30/1998 Make: Airbus SAS Model: A320-111 | 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 [63 FR 51279 No. 186 09/25/98] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-20-30 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 97-NM-192-AD AMENDMENT: 39-10797 AD NUMBER: 98-20-30 SUBJECT HEADING: Airworthiness Directives; Airbus Model A320 Series Airplanes Equipped with a Bulk Cargo Door ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A320 series airplanes equipped with a bulk cargo door, that requires repetitive inspections to detect fatigue cracking of the upper frame flanges; and repair, if necessary. This amendment also requires modification of the upper frame flanges of the bulk cargo door, which constitutes terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking of the upper frame flanges, which could result in reduced structural integrity of the airplane. DATES: Effective October 30, 1998. 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: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 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 all Airbus Model A320 series airplanes equipped with a bulk cargo door was published in the Federal Register on August 7, 1998 (63 FR 42286). That action proposed to require repetitive inspections to detect fatigue cracking of the upper frame flanges; and repair, if necessary. That action also proposed to require modification of the upper frame flanges of the bulk cargo door, which constitutes terminating action for the repetitive inspections. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public. Conclusion 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 8 airplanes of U.S. registry will be affected by this AD. It will take approximately 1 work hour per airplane to accomplish the required inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspection required by this AD on U.S. operators is estimated to be $480, or $60 per airplane, per inspection cycle. It will take approximately 4 work hours per airplane to accomplish the required modification, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the modification required by this AD on U.S. operators is estimated to be $1,920, or $240 per airplane. The cost impact figures discussed above are 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: 98-20-30 AIRBUS INDUSTRIE: Amendment 39-10797. Docket 97-NM-192-AD. Applicability: Model A320 series airplanes, equipped with a bulk cargo door (Airbus Modification 20029), 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 (c) 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 fatigue cracking of the upper frame flanges, which could result in reduced structural integrity of the airplane, accomplish the following: (a) Prior to the accumulation of 20,000 total flight cycles, or within 1,200 flight cycles after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current inspection to detect fatigue cracking of the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1022, Revision 1, dated June 18, 1992. (1) If no cracking is detected, accomplish either paragraph (a)(1)(i) or (a)(1)(ii) of this AD. (i) Repeat the eddy current inspection thereafter at intervals not to exceed 1,200 flight cycles until accomplishment of the requirements of paragraph (b) of this AD. Or (ii) Prior to further flight, modify the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. This modification constitutes terminating action for the requirements of this AD. (2) If any cracking is detected, prior to further flight, repair in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. Accomplishment of the repair constitutes terminating action for the requirements of this AD. (b) Prior to the accumulation of 26,000 total flight cycles, or within 6,000 flight cycles after the effective date of this AD, whichever occurs later: Perform a high frequency eddy current inspection to detect fatigue cracking of the upper frame flanges, in accordance with Airbus Service Bulletin A320-53-1021, Revision 1, dated April 13, 1992. (1) If no cracking is detected, prior to further flight, modify the upper frame flanges, in accordance with the service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of this AD. (2) If any cracking is detected, prior to further flight, repair in accordance with the service bulletin. Accomplishment of the repair constitutes terminating action for the requirements of this AD. (c) 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, International Branch, ANM-116, 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, International Branch, ANM-116. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (d) 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. (e) The inspections, repairs, and modification shall be done in accordance with the following Airbus service bulletins, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Shown on Page Revision Level Shown on Page Date Shown on Page A320-53-1022, Revision 1, June 18, 1992 1-6 7, 8 1 Original June 18, 1992 October 17, 1991 A320-53-1021, Revision 1, April 13, 1992 1, 4-24 2, 3 1 Original April 13, 1992 October 17, 1991 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. NOTE 3: The subject of this AD is addressed in French airworthiness directive 96-238- 091(B), dated October 23, 1996. (f) This amendment becomes effective on October 30, 1998. FOOTER:
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