AD 99-05-11
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus SAS | BAC 1-11 200 Series | Airworthiness Directives; British Aerospace Model BAC 1-11 200 and 400 Series Airplanes |
| aircraft | Airbus SAS | BAC 1-11 400 Series | Airworthiness Directives; British Aerospace Model BAC 1-11 200 and 400 Series Airplanes |
Unsafe Condition
Cracking in the flight deck canopy area, specifically in the top sill joint strap at station 82.5, frame at station 113, and frame at station 160.5 (left-hand side only) between stringers 13 and 15, which could result in reduced structural integrity of the flight deck frame and adjacent fuselage structure.
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Required Actions
Perform detailed visual inspections and eddy current inspections of specified areas to detect cracks, replace cracked parts with new parts or repair top sill members. Conduct a one-time inspection to determine fastener type in specific holes, replacing rivets with bolts if necessary. Follow British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, for compliance.
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Compliance Time
Required as indicated, unless accomplished previously. Inspections must be performed by the later of specific landing or time-in-service thresholds, with subsequent intervals not exceeding 5,000 landings or 7,500 hours (for ≤7.5 psi cabin pressure) or 3,500 landings or 5,250 hours (for >7.5 psi ≤8.2 psi).
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Affected Aircraft
British Aerospace Model BAC 1-11 200 and 400 series airplanes, certificated in any category, including those modified with PM3187.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Inspect Flight Deck Canopy Area
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_99-05-11.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 99-05-11 Document Type: AD Final Rules Docket Number: 98-NM-27-AD Subject Heading: Airworthiness Directives; British Aerospace Model BAC 1-11 200 and 400 Series Airplanes Subject: Inspect Flight Deck Canopy Area Status: Current Citation: Federal Register: March 05, 1999 (Volume 64, Number 43) Citation Publish Date: 03/05/1999 Effective Date: 04/09/1999 Make: Airbus SAS Model: BAC 1-11 200 Series | BAC 1-11 400 Series 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 [64 FR 10555 No. 43 03/05/99] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 99-05-11 CITATION: [Federal Register: March 05, 1999 (Volume 64, Number 43)] PAGE NUMBER: [Page 10555] DOCKET NUMBER: 98-NM-27-AD AMENDMENT: 39-11059 AD NUMBER: 99-05-11 SUBJECT HEADING: Airworthiness Directives; British Aerospace Model BAC 1-11 200 and 400 Series Airplanes ACTION: Final rule SUMMARY: This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently requires repetitive visual inspections to detect cracks in the flight deck canopy area, and repair, if necessary; and repetitive detailed visual and eddy current inspections to detect cracks of the top sill members at station 82.5, and replacement of cracked parts with new parts, or repair of the top sill members. This amendment continues to require detailed visual and eddy current inspections to detect cracks of the top sill members at station 82.5. This amendment also adds a requirement for a one-time inspection to determine the type of fasteners installed in certain holes of the joint strap installation, and replacement of rivets with bolts, if necessary. This amendment is prompted by the 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 flight deck canopy area, which could result in reduced structural integrity of the flight deck frame and adjacent fuselage structure. DATES: Effective April 9, 1999. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 9, 1999. The incorporation by reference of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated 4/ 8/93, as listed in the regulations, was approved previously by the Director of the Federal Register as of 4/22/96 (61 FR 11534, 3/21/96). ADDRESSES: The service information referenced in this AD may be obtained from British Aerospace, Service Support, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. 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) by superseding AD 96-06-07, amendment 39-9544 (61 FR 11534, March 21, 1996), which is applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, was published in the Federal Register on January 6, 1999 (64 FR 785). The action proposed to continue to require detailed visual and eddy current inspections to detect cracks of the top sill members at station 82.5, and replacement of cracked parts with new parts, or repair of the top sill members. The action also proposed to add a requirement for a one-time inspection to determine the type of fasteners installed in certain holes of the joint strap installation, and replacement of rivets with bolts, if necessary. 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 There are approximately 42 airplanes of U.S. registry that will be affected by this AD. The actions that are currently required by AD 96-06-07, and retained in this AD, take approximately 19 work hours per airplane to accomplish (including access and close), at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the currently required actions on U.S. operators is estimated to be $47,880, or $1,140 per airplane, per inspection cycle. The new inspection that is required in this AD action will take approximately 1 work hour per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the new inspection required by this AD on U.S. operators is estimated to be $2,520, or $60 per airplane. Should an operator be required to accomplish the necessary replacement of rivets with bolts, it will take approximately 3 work hours per airplane to accomplish the replacement, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of any necessary replacement of rivets is estimated to be $180 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 removing amendment 39-9544 (61 FR 11534, March 21, 1996), and by adding a new airworthiness directive (AD), amendment 39-11059, to read as follows: REGULATORY TEXT: 99-05-11 BRITISH AEROSPACE AIRBUS LIMITED (Formerly British Aerospace Commercial Aircraft Limited, British Aerospace Aircraft Group): Amendment 39-11059. Docket 98-NM-27-AD. Supersedes AD 96-06-07, Amendment 39-9544. Applicability: All Model BAC 1-11 200 and 400 series airplanes, 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 prevent reduced structural integrity of the flight deck frame and adjacent fuselage structure, accomplish the following: (a) Perform a detailed visual inspection to detect cracks of the top sill joint strap at station 82.5, of the frame at station 113, and of the frame at station 160.5 (left-hand side only) between stringers 13 and 15; and an eddy current inspection to detect cracks of the top sill members at station 82.5. Perform these inspections in accordance with British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993; Issue 4, dated August 23, 1996; or Issue 5, dated April 18, 1997; at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. After the effective date of this AD, only Issue 5 shall be used. (1) For airplanes operating at a maximum cabin differential pressure not exceeding 7.5 pounds per square inch (psi): Perform the inspections at the later of the times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD. Thereafter, repeat these inspections at intervals not to exceed 5,000 landings or 7,500 hours time-in-service, whichever occurs first. (i) Prior to the accumulation of 20,000 total landings. Or (ii) Within 1,200 landings or 12 months after April 22, 1996 (the effective date of AD 96-06-07, amendment 39-9544), whichever occurs later. (2) For airplanes operating at a maximum cabin differential pressure greater than 7.5 psi, but not exceeding 8.2 psi, including those airplanes having incorporated British Aerospace Airbus Limited Modification PM3187: Perform the inspections at the later of the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. Thereafter, repeat these inspections at intervals not to exceed 3,500 landings or 5,250 hours time-in-service, whichever occurs first. (i) Prior to the accumulation of 14,000 total landings. Or (ii) Within 800 landings or 12 months after April 22, 1996, whichever occurs later. NOTE 2: British Aerospace Airbus Limited Modification PM3187 increases the cabin differential pressure from the normal 7.5 psi to 8.2 psi. If Modification PM3187 has been incorporated on the airplane, that airplane is considered to be subject to the requirements of paragraph (a)(2) of this AD. (b) Concurrent with the next detailed visual inspection performed after the effective date of this AD in accordance with paragraph (a) of this AD, perform a one-time visual inspection to determine the type of fasteners installed in the two hole locations specified in Figure 2 of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, dated April 18, 1997. (1) If bolts are found installed in the two hole locations specified in Figure 2 of the alert service bulletin: Prior to further flight, remove the bolts and perform the eddy current inspection specified in paragraph (a) of this AD to detect cracking of the top sill members at station 82.5, in accordance with the alert service bulletin. Repeat the detailed visual and eddy current inspections thereafter as specified in paragraph (a)(1) or (a)(2) of this AD, as applicable; in accordance with the alert service bulletin. (i) If no cracking is detected, prior to further flight, reinstall the bolts. (ii) If any cracking is detected, prior to further flight, repair in accordance with paragraph (c) of this AD, and reinstall the bolts. (2) If rivets are found installed in the two hole locations specified in Figure 2 of the alert service bulletin: Prior to further flight, remove the rivets, and perform the eddy current inspection specified in paragraph (a) of this AD to detect cracking of the top sill members at station 82.5, in accordance with the alert service bulletin. Repeat the detailed visual and eddy current inspections thereafter as specified in paragraph (a)(1) or (a)(2) of this AD, as applicable; in accordance with the alert service bulletin. (i) If no cracking is detected, prior to further flight, oversize the holes specified in Figure 2 of the alert service bulletin, and install bolts in place of the rivets. (ii) If any cracking is detected, prior to further flight, repair in accordance with paragraph (c) of this AD, oversize the holes specified in Figure 2 of the alert service bulletin, and install bolts in place of the rivets. NOTE 3: As specified in British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 4, dated August 23, 1996, and Issue 5, dated April 18, 1997, the procedures for the eddy current inspection necessitate removal of the bolts from the holes specified in Figure 2 of the alert service bulletin. (c) If any crack is found during any inspection required by paragraph (a) or (b) of this AD, prior to further flight, accomplish the requirements of paragraph (c)(1), (c)(2), or (c)(3) of this AD, as applicable. (1) For cracking of the joint strap, doubler, or angle at the sill joint at station 82.5: Replace the cracked part with a new part in accordance with British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993; Issue 4, dated August 23, 1996; or Issue 5, dated April 18, 1997. After the effective date of this AD, only Issue 5 shall be used. (2) For cracking of the frame at station 113: Repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Civil Aviation Authority (or its delegated agent). (3) For cracking of the frame at station 160.5: Repair in accordance with the Structural Repair Manual, as specified in British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993; Issue 4, dated August 23, 1996; or Issue 5, dated April 18, 1997. After the effective date of this AD, only Issue 5 shall be used. Alternative Methods of Compliance (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 requests 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. Special Flight Permits (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. Incorporation by Reference (f) The inspections, removal, and replacement shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993; British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 4, dated August 23, 1996; or British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, dated April 18, 1997. (1) The incorporation by reference of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 4, dated August 23, 1996; and British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, dated April 18, 1997, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 22, 1996 (61 FR 11534, March 21, 1996). (3) Copies may be obtained from British Aerospace, Service Support, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. 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. (g) This amendment becomes effective on April 9, 1999. FOOTER:
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AD Final Rules - DRS_99-05-11.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 99-05-11 Document Type: AD Final Rules Docket Number: 98-NM-27-AD Subject Heading: Airworthiness Directives; British Aerospace Model BAC 1-11 200 and 400 Series Airplanes Subject: Inspect Flight Deck Canopy Area Status: Current Citation: Federal Register: March 05, 1999 (Volume 64, Number 43) Citation Publish Date: 03/05/1999 Effective Date: 04/09/1999 Make: Airbus SAS Model: BAC 1-11 200 Series | BAC 1-11 400 Series 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 [64 FR 10555 No. 43 03/05/99] Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 99-05-11 CITATION: [Federal Register: March 05, 1999 (Volume 64, Number 43)] PAGE NUMBER: [Page 10555] DOCKET NUMBER: 98-NM-27-AD AMENDMENT: 39-11059 AD NUMBER: 99-05-11 SUBJECT HEADING: Airworthiness Directives; British Aerospace Model BAC 1-11 200 and 400 Series Airplanes ACTION: Final rule SUMMARY: This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently requires repetitive visual inspections to detect cracks in the flight deck canopy area, and repair, if necessary; and repetitive detailed visual and eddy current inspections to detect cracks of the top sill members at station 82.5, and replacement of cracked parts with new parts, or repair of the top sill members. This amendment continues to require detailed visual and eddy current inspections to detect cracks of the top sill members at station 82.5. This amendment also adds a requirement for a one-time inspection to determine the type of fasteners installed in certain holes of the joint strap installation, and replacement of rivets with bolts, if necessary. This amendment is prompted by the 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 flight deck canopy area, which could result in reduced structural integrity of the flight deck frame and adjacent fuselage structure. DATES: Effective April 9, 1999. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 9, 1999. The incorporation by reference of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated 4/ 8/93, as listed in the regulations, was approved previously by the Director of the Federal Register as of 4/22/96 (61 FR 11534, 3/21/96). ADDRESSES: The service information referenced in this AD may be obtained from British Aerospace, Service Support, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. 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) by superseding AD 96-06-07, amendment 39-9544 (61 FR 11534, March 21, 1996), which is applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, was published in the Federal Register on January 6, 1999 (64 FR 785). The action proposed to continue to require detailed visual and eddy current inspections to detect cracks of the top sill members at station 82.5, and replacement of cracked parts with new parts, or repair of the top sill members. The action also proposed to add a requirement for a one-time inspection to determine the type of fasteners installed in certain holes of the joint strap installation, and replacement of rivets with bolts, if necessary. 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 There are approximately 42 airplanes of U.S. registry that will be affected by this AD. The actions that are currently required by AD 96-06-07, and retained in this AD, take approximately 19 work hours per airplane to accomplish (including access and close), at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the currently required actions on U.S. operators is estimated to be $47,880, or $1,140 per airplane, per inspection cycle. The new inspection that is required in this AD action will take approximately 1 work hour per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the new inspection required by this AD on U.S. operators is estimated to be $2,520, or $60 per airplane. Should an operator be required to accomplish the necessary replacement of rivets with bolts, it will take approximately 3 work hours per airplane to accomplish the replacement, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of any necessary replacement of rivets is estimated to be $180 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 removing amendment 39-9544 (61 FR 11534, March 21, 1996), and by adding a new airworthiness directive (AD), amendment 39-11059, to read as follows: REGULATORY TEXT: 99-05-11 BRITISH AEROSPACE AIRBUS LIMITED (Formerly British Aerospace Commercial Aircraft Limited, British Aerospace Aircraft Group): Amendment 39-11059. Docket 98-NM-27-AD. Supersedes AD 96-06-07, Amendment 39-9544. Applicability: All Model BAC 1-11 200 and 400 series airplanes, 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 prevent reduced structural integrity of the flight deck frame and adjacent fuselage structure, accomplish the following: (a) Perform a detailed visual inspection to detect cracks of the top sill joint strap at station 82.5, of the frame at station 113, and of the frame at station 160.5 (left-hand side only) between stringers 13 and 15; and an eddy current inspection to detect cracks of the top sill members at station 82.5. Perform these inspections in accordance with British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993; Issue 4, dated August 23, 1996; or Issue 5, dated April 18, 1997; at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. After the effective date of this AD, only Issue 5 shall be used. (1) For airplanes operating at a maximum cabin differential pressure not exceeding 7.5 pounds per square inch (psi): Perform the inspections at the later of the times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD. Thereafter, repeat these inspections at intervals not to exceed 5,000 landings or 7,500 hours time-in-service, whichever occurs first. (i) Prior to the accumulation of 20,000 total landings. Or (ii) Within 1,200 landings or 12 months after April 22, 1996 (the effective date of AD 96-06-07, amendment 39-9544), whichever occurs later. (2) For airplanes operating at a maximum cabin differential pressure greater than 7.5 psi, but not exceeding 8.2 psi, including those airplanes having incorporated British Aerospace Airbus Limited Modification PM3187: Perform the inspections at the later of the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. Thereafter, repeat these inspections at intervals not to exceed 3,500 landings or 5,250 hours time-in-service, whichever occurs first. (i) Prior to the accumulation of 14,000 total landings. Or (ii) Within 800 landings or 12 months after April 22, 1996, whichever occurs later. NOTE 2: British Aerospace Airbus Limited Modification PM3187 increases the cabin differential pressure from the normal 7.5 psi to 8.2 psi. If Modification PM3187 has been incorporated on the airplane, that airplane is considered to be subject to the requirements of paragraph (a)(2) of this AD. (b) Concurrent with the next detailed visual inspection performed after the effective date of this AD in accordance with paragraph (a) of this AD, perform a one-time visual inspection to determine the type of fasteners installed in the two hole locations specified in Figure 2 of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, dated April 18, 1997. (1) If bolts are found installed in the two hole locations specified in Figure 2 of the alert service bulletin: Prior to further flight, remove the bolts and perform the eddy current inspection specified in paragraph (a) of this AD to detect cracking of the top sill members at station 82.5, in accordance with the alert service bulletin. Repeat the detailed visual and eddy current inspections thereafter as specified in paragraph (a)(1) or (a)(2) of this AD, as applicable; in accordance with the alert service bulletin. (i) If no cracking is detected, prior to further flight, reinstall the bolts. (ii) If any cracking is detected, prior to further flight, repair in accordance with paragraph (c) of this AD, and reinstall the bolts. (2) If rivets are found installed in the two hole locations specified in Figure 2 of the alert service bulletin: Prior to further flight, remove the rivets, and perform the eddy current inspection specified in paragraph (a) of this AD to detect cracking of the top sill members at station 82.5, in accordance with the alert service bulletin. Repeat the detailed visual and eddy current inspections thereafter as specified in paragraph (a)(1) or (a)(2) of this AD, as applicable; in accordance with the alert service bulletin. (i) If no cracking is detected, prior to further flight, oversize the holes specified in Figure 2 of the alert service bulletin, and install bolts in place of the rivets. (ii) If any cracking is detected, prior to further flight, repair in accordance with paragraph (c) of this AD, oversize the holes specified in Figure 2 of the alert service bulletin, and install bolts in place of the rivets. NOTE 3: As specified in British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 4, dated August 23, 1996, and Issue 5, dated April 18, 1997, the procedures for the eddy current inspection necessitate removal of the bolts from the holes specified in Figure 2 of the alert service bulletin. (c) If any crack is found during any inspection required by paragraph (a) or (b) of this AD, prior to further flight, accomplish the requirements of paragraph (c)(1), (c)(2), or (c)(3) of this AD, as applicable. (1) For cracking of the joint strap, doubler, or angle at the sill joint at station 82.5: Replace the cracked part with a new part in accordance with British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993; Issue 4, dated August 23, 1996; or Issue 5, dated April 18, 1997. After the effective date of this AD, only Issue 5 shall be used. (2) For cracking of the frame at station 113: Repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Civil Aviation Authority (or its delegated agent). (3) For cracking of the frame at station 160.5: Repair in accordance with the Structural Repair Manual, as specified in British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993; Issue 4, dated August 23, 1996; or Issue 5, dated April 18, 1997. After the effective date of this AD, only Issue 5 shall be used. Alternative Methods of Compliance (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 requests 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. Special Flight Permits (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. Incorporation by Reference (f) The inspections, removal, and replacement shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993; British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 4, dated August 23, 1996; or British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, dated April 18, 1997. (1) The incorporation by reference of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 4, dated August 23, 1996; and British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, dated April 18, 1997, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 22, 1996 (61 FR 11534, March 21, 1996). (3) Copies may be obtained from British Aerospace, Service Support, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. 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. (g) This amendment becomes effective on April 9, 1999. FOOTER:
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