AD 98-20-31
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A320-111 | Airworthiness Directives; Airbus Model A320 Series Airplanes |
| aircraft | Airbus | A320-211 | Airworthiness Directives; Airbus Model A320 Series Airplanes |
| aircraft | Airbus | A320-212 | Airworthiness Directives; Airbus Model A320 Series Airplanes |
| aircraft | Airbus | A320-214 | Airworthiness Directives; Airbus Model A320 Series Airplanes |
| aircraft | Airbus | A320-231 | Airworthiness Directives; Airbus Model A320 Series Airplanes |
| aircraft | Airbus | A320-232 | Airworthiness Directives; Airbus Model A320 Series Airplanes |
| aircraft | Airbus | A320-233 | Airworthiness Directives; Airbus Model A320 Series Airplanes |
Unsafe Condition
Cracking in the pressurized floor pick-up angles on the rear spar of the wing could result in reduced structural integrity of the airframe.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform an eddy current inspection to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing. If cracking is found, replace each cracked pick-up angle and its associated diaphragms with improved parts. Repeat inspections at intervals not to exceed 10,000 flight cycles for unreplaced angles.
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 60 days 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 as listed in Airbus Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997; certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Pressurized Floor Pick-Up Angles At Rear Spar
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_98-20-31.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-20-31 Document Type: AD Final Rules Docket Number: 98-NM-77-AD Subject Heading: Airworthiness Directives; Airbus Model A320 Series Airplanes Subject: Pressurized Floor Pick-Up Angles At Rear Spar Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/30/1998 Make: Airbus 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 51277 No. 186 09/25/98] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-20-31 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 98-NM-77-AD AMENDMENT: 39-10798 AD NUMBER: 98-20-31 SUBJECT HEADING: Airworthiness Directives; Airbus Model A320 Series Airplanes ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing, and replacement of any cracked pick-up angle and its associated diaphragms with improved parts. Such replacement terminates the repetitive inspections for that angle. 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 detect and correct cracking in the pressurized floor pick-up angles at the rear spar of the wing, which could result in reduced structural integrity of the airframe. 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 certain Airbus Model A320 series airplanes was published in the Federal Register on April 27, 1998 (63 FR 20546). That action proposed to require repetitive inspections to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing, and replacement of any cracked pick-up angle and its associated diaphragms with improved parts. Such replacement would terminate the repetitive inspections for that angle. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received. Request to Accept Additional Versions of Service Bulletins The commenter (the manufacturer) generally supports the proposed rule. However, the commenter states that an inspection performed in accordance with instructions defined in Airbus Service Bulletin A320-57-1090, dated April 19, 1996, complies with the requirements of paragraph (a) of the proposed AD. (The proposed AD cited only Revision 01 of that service bulletin as the appropriate means of compliance.) The commenter adds that accomplishment of the modification, in accordance with Airbus Service Bulletin A320-57-1025, Revision 2, dated November 25, 1994; Revision 3, dated May 22, 1995; or Revision 4, dated December 8, 1995; should be considered acceptable as terminating action for the proposed AD. (The proposed AD cited only Revision 05, dated June 26, 1997, of that service bulletin as the appropriate means of compliance.) The FAA concurs that accomplishment of those earlier versions of the service bulletins, in lieu of the revision levels cited in the proposed rule, is acceptable for compliance with the requirements of this AD. The inspection procedures described in Airbus Service Bulletin A320-57-1090, dated April 19, 1996, are essentially the same as those described in Revision 01, dated June 10, 1997. Likewise, the modification procedures described in Airbus Service Bulletin A320-57-1025, Revision 2, dated November 25, 1994; Revision 3, dated May 22, 1995; and Revision 4, dated December 8, 1995; are essentially the same as those described in Revision 05, dated June 26, 1997. Therefore, the final rule has been revised to include NOTE 2 and NOTE 3, which credit operators for inspections and modifications accomplished prior to the effective date of the final rule in accordance with the referenced additional revision levels. Conclusion After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the change described previously. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Cost Impact The FAA estimates that 120 airplanes of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per airplane (including access and close) to accomplish the required inspection, and that the average labor rate is $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 $57,600, or $480 per airplane, per inspection cycle. 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. Should an operator elect to accomplish the optional terminating action that is provided by this AD, it would take approximately 140 work hours to accomplish, at an average labor rate of $60 per work hour. The cost of required parts would be approximately $10,103 per airplane. Based on these figures, the cost impact of that optional terminating action would be $18,503 per airplane. 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: 98-20-31 AIRBUS INDUSTRIE: Amendment 39-10798. Docket 98-NM-77-AD. Applicability: Model A320 series airplanes, as listed in Airbus Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 (d) 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 detect and correct cracking in the pressurized floor pick-up angles at the rear spar of the wing, which could result in reduced structural integrity of the airframe, accomplish the following: (a) Prior to the accumulation of 20,000 total flight cycles, or within 60 days after the effective date of this AD, whichever occurs later: Perform an eddy current inspection to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing, in accordance with Airbus Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997. NOTE 2: Accomplishment of the inspection prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1090, dated April 19, 1996, is also considered acceptable for compliance with paragraph (a) of this AD. (1) If no cracking is found, repeat the inspection thereafter at intervals not to exceed 10,000 flight cycles. (2) If any cracking is found during any inspection required by this AD, prior to further flight, replace each cracked pick-up angle and its associated diaphragms with improved parts, in accordance with Airbus Service Bulletin A320-57-1025, Revision 05, dated June 26, 1997. For all pick-up angles not replaced with improved angles, repeat the inspection thereafter at intervals not to exceed 10,000 flight cycles. (b) Replacement of a pick-up angle and its associated diaphragms with improved parts, in accordance with Airbus Service Bulletin A320-57-1025, Revision 05, dated June 26, 1997, constitutes terminating action for the repetitive inspection requirements for that pick-up angle. NOTE 3: Accomplishment of the replacement prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1025, Revision 2, dated November 25, 1994; Revision 3, dated May 22, 1995; or Revision 4, dated December 8, 1995; is also considered acceptable for compliance with paragraphs (a)(2) and (b) of this AD. (c) If any crack is detected during any inspection required by this AD, and the applicable service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (or its delegated agent). (d) 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. Operators shall submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (e) 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. (f) The inspections shall be done in accordance with Airbus Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997. Except as provided by paragraph (c) of this AD, the replacement, if accomplished, shall be done in accordance with Airbus Service Bulletin A320-57-1025, Revision 05, dated June 26, 1997, which contains the following effective pages: Page Number Shown on Page Revision Level Shown on Page Date Shown on Page 1, 13, 30-32, 101, 102 05 June 26, 1997 2-5 4 December 8, 1995 10, 15, 19, 24, 28, 29 3 May 22, 1995 6-9, 11, 12, 14, 16-18, 20-23 25-27, 33-100, 103-106 2 November 25, 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. NOTE 5: The subject of this AD is addressed in French airworthiness directive CN 97-084-097 (B), dated March 12, 1997. (g) This amendment becomes effective on October 30, 1998. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_98-20-31.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-20-31 Document Type: AD Final Rules Docket Number: 98-NM-77-AD Subject Heading: Airworthiness Directives; Airbus Model A320 Series Airplanes Subject: Pressurized Floor Pick-Up Angles At Rear Spar Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 10/30/1998 Make: Airbus 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 51277 No. 186 09/25/98] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-20-31 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 98-NM-77-AD AMENDMENT: 39-10798 AD NUMBER: 98-20-31 SUBJECT HEADING: Airworthiness Directives; Airbus Model A320 Series Airplanes ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing, and replacement of any cracked pick-up angle and its associated diaphragms with improved parts. Such replacement terminates the repetitive inspections for that angle. 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 detect and correct cracking in the pressurized floor pick-up angles at the rear spar of the wing, which could result in reduced structural integrity of the airframe. 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 certain Airbus Model A320 series airplanes was published in the Federal Register on April 27, 1998 (63 FR 20546). That action proposed to require repetitive inspections to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing, and replacement of any cracked pick-up angle and its associated diaphragms with improved parts. Such replacement would terminate the repetitive inspections for that angle. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received. Request to Accept Additional Versions of Service Bulletins The commenter (the manufacturer) generally supports the proposed rule. However, the commenter states that an inspection performed in accordance with instructions defined in Airbus Service Bulletin A320-57-1090, dated April 19, 1996, complies with the requirements of paragraph (a) of the proposed AD. (The proposed AD cited only Revision 01 of that service bulletin as the appropriate means of compliance.) The commenter adds that accomplishment of the modification, in accordance with Airbus Service Bulletin A320-57-1025, Revision 2, dated November 25, 1994; Revision 3, dated May 22, 1995; or Revision 4, dated December 8, 1995; should be considered acceptable as terminating action for the proposed AD. (The proposed AD cited only Revision 05, dated June 26, 1997, of that service bulletin as the appropriate means of compliance.) The FAA concurs that accomplishment of those earlier versions of the service bulletins, in lieu of the revision levels cited in the proposed rule, is acceptable for compliance with the requirements of this AD. The inspection procedures described in Airbus Service Bulletin A320-57-1090, dated April 19, 1996, are essentially the same as those described in Revision 01, dated June 10, 1997. Likewise, the modification procedures described in Airbus Service Bulletin A320-57-1025, Revision 2, dated November 25, 1994; Revision 3, dated May 22, 1995; and Revision 4, dated December 8, 1995; are essentially the same as those described in Revision 05, dated June 26, 1997. Therefore, the final rule has been revised to include NOTE 2 and NOTE 3, which credit operators for inspections and modifications accomplished prior to the effective date of the final rule in accordance with the referenced additional revision levels. Conclusion After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the change described previously. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Cost Impact The FAA estimates that 120 airplanes of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per airplane (including access and close) to accomplish the required inspection, and that the average labor rate is $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 $57,600, or $480 per airplane, per inspection cycle. 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. Should an operator elect to accomplish the optional terminating action that is provided by this AD, it would take approximately 140 work hours to accomplish, at an average labor rate of $60 per work hour. The cost of required parts would be approximately $10,103 per airplane. Based on these figures, the cost impact of that optional terminating action would be $18,503 per airplane. 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: 98-20-31 AIRBUS INDUSTRIE: Amendment 39-10798. Docket 98-NM-77-AD. Applicability: Model A320 series airplanes, as listed in Airbus Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 (d) 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 detect and correct cracking in the pressurized floor pick-up angles at the rear spar of the wing, which could result in reduced structural integrity of the airframe, accomplish the following: (a) Prior to the accumulation of 20,000 total flight cycles, or within 60 days after the effective date of this AD, whichever occurs later: Perform an eddy current inspection to detect cracking in the pressurized floor pick-up angles on the rear spar of the wing, in accordance with Airbus Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997. NOTE 2: Accomplishment of the inspection prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1090, dated April 19, 1996, is also considered acceptable for compliance with paragraph (a) of this AD. (1) If no cracking is found, repeat the inspection thereafter at intervals not to exceed 10,000 flight cycles. (2) If any cracking is found during any inspection required by this AD, prior to further flight, replace each cracked pick-up angle and its associated diaphragms with improved parts, in accordance with Airbus Service Bulletin A320-57-1025, Revision 05, dated June 26, 1997. For all pick-up angles not replaced with improved angles, repeat the inspection thereafter at intervals not to exceed 10,000 flight cycles. (b) Replacement of a pick-up angle and its associated diaphragms with improved parts, in accordance with Airbus Service Bulletin A320-57-1025, Revision 05, dated June 26, 1997, constitutes terminating action for the repetitive inspection requirements for that pick-up angle. NOTE 3: Accomplishment of the replacement prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1025, Revision 2, dated November 25, 1994; Revision 3, dated May 22, 1995; or Revision 4, dated December 8, 1995; is also considered acceptable for compliance with paragraphs (a)(2) and (b) of this AD. (c) If any crack is detected during any inspection required by this AD, and the applicable service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (or its delegated agent). (d) 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. Operators shall submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (e) 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. (f) The inspections shall be done in accordance with Airbus Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997. Except as provided by paragraph (c) of this AD, the replacement, if accomplished, shall be done in accordance with Airbus Service Bulletin A320-57-1025, Revision 05, dated June 26, 1997, which contains the following effective pages: Page Number Shown on Page Revision Level Shown on Page Date Shown on Page 1, 13, 30-32, 101, 102 05 June 26, 1997 2-5 4 December 8, 1995 10, 15, 19, 24, 28, 29 3 May 22, 1995 6-9, 11, 12, 14, 16-18, 20-23 25-27, 33-100, 103-106 2 November 25, 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. NOTE 5: The subject of this AD is addressed in French airworthiness directive CN 97-084-097 (B), dated March 12, 1997. (g) This amendment becomes effective on October 30, 1998. FOOTER:
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