AD 98-13-35 R1
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-9-11 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-12 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-13 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-14 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-15 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-15F | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-21 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-31 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-32 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-32 (VC-9C) | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-32F | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-32F (C-9A) | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-32F (C-9B) | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-33F | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-34 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-34F | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-41 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-51 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-81 (MD-81) | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-82 (MD-82) | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-83 (MD-83) | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | DC-9-87 (MD-87) | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
| aircraft | The Boeing Company | MD-88 | Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes |
Unsafe Condition
Fatigue cracks in the skin and longerons of the fuselage, which could result in loss of structural integrity and rapid depressurization 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 of the fuselage skin between stations Y=160.000 and Y=218.000, and skin at longeron attachments between Y=160.000 and Y=180.000 for left longerons 4 and 5. Repairs must be done prior to further flight if cracks are found. Operators may choose repetitive inspections every 10,000 landings or install a preventative modification with clips and doublers to terminate inspections.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Required as indicated, with inspections due before 30,000 total landings or within 8,000 landings after the AD's effective date (July 30, 1998), whichever is later. For previously inspected airplanes, inspections are due within 12,000 landings after the effective date. The preventative modification must be done before 100,000 total landings or within 4 years after the effective date, whichever is later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas Model DC-9-10, -20, -30, -40, -50 series; DC-9-81 (MD-81), -82 (MD-82), -83 (MD-83), -87 (MD-87); Model MD-88; and C-9 military series airplanes listed in Service Bulletin 53-235.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Fatigue Cracks In External Areas Of Fuselage
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_98-13-35_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-13-35 R1 Document Type: AD Final Rules Docket Number: 96-NM-203-AD Subject Heading: Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Air...Show more Subject: Fatigue Cracks In External Areas Of Fuselage Status: Current Citation: (Federal Register: March 23, 1999 (Volume 64, Number 55)) Citation Publish Date: 03/23/1999 Effective Date: 07/30/1998 Make: The Boeing Company Model: DC-9-11 | DC-9-12 | DC-9-13 | DC-9-14 | DC-9-15 | DC-9-15F | DC-9-21 | DC-9-31 | DC-9-32 | DC-9-32 (...Show more 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 13890 No. 55 03/23/99) Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-13-35 R1 CITATION: [Federal Register: March 23, 1999 (Volume 64, Number 55)] PAGE NUMBER: [Page 13890] DOCKET NUMBER: 96-NM-203-AD AMENDMENT: 39-11086 AD NUMBER: 98-13-35 R1 SUBJECT HEADING: Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes ACTION: Final rule; correction. SUMMARY: This amendment corrects information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that currently requires repetitive high frequency eddy current inspections of certain areas of the fuselage to detect cracks of the skin and/or longeron, and various follow-on actions. That AD also requires installation of a preventative modification, which terminates the repetitive inspections. The actions specified in that AD are intended to prevent fatigue cracks, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane. This amendment corrects the requirements of the current AD by indicating the specific area in which the subject inspection must be conducted. This amendment is prompted by communication received from the manufacturer that the current requirements of the AD are different than the service information referenced as the appropriate service information in the current AD. DATES: Effective July 30, 1998. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Brent Bandley, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone (562) 627-5237; fax (562) 627-5210. SUPPLEMENTARY INFORMATION: On June 17, 1998, the FAA issued AD 98-13-35, amendment 39-10626 (63 FR 34585, June 25, 1998), which is applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes. That AD requires repetitive high frequency eddy current inspections of certain areas of the fuselage to detect cracks of the skin and/or longeron, and various follow-on actions. That AD also requires installation of a preventative modification, which terminates the repetitive inspections. That action was prompted by reports indicating that, due to material fatigue caused by installation preload and cabin pressurization cycles, fatigue cracks were found in the skin and longerons of the fuselage. The actions required by that AD are intended to prevent such fatigue cracks, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane. Actions Since Issuance of Previous Rule Since the issuance of AD 98-13-35, the FAA has received information from the manufacturer that the specified area of the initial inspection requirements of paragraph (a) of that AD differs from the service information provided in McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993 (cited in the AD as the appropriate source of service information for accomplishment of the required actions). The FAA’s intent in AD 98-13-35 was to require the actions described in McDonnell Douglas DC-9 Service Bulletin 53-235. In order to prevent operators from misinterpreting the specific area of the initial inspection, the FAA finds that the inspection requirements of paragraph (a) must be revised to specify inspection only of the fuselage, in lieu of the fuselage skin and/or longeron. Accordingly, this action revises paragraph (a) of the existing AD to remove reference to inspection of the longeron and to limit the area that is subject to the inspection (skin between stations Y=160.000 and Y=218.000; skin at the longeron attachments). Action is taken herein to clarify and correct these requirements of AD 98-13-35 and to correctly add the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13). The final rule is being reprinted in its entirety for the convenience of affected operators. The effective date remains July 30, 1998. Since this action only clarifies and corrects a current requirement, it has no adverse economic impact and imposes no additional burden on any person. Therefore, notice and public procedures hereon are unnecessary. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Correction 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 39-10626 (63 FR 34585, June 25, 1998), and by adding a new airworthiness directive (AD), amendment 39-11086, to read as follows: REGULATORY TEXT: 98-13-35 R1 MCDONNELL DOUGLAS: Amendment 39-11086. Docket 96-NM-203-AD. Revises AD 98-13-35, Amendment 39-10626. Applicability: Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81 (MD-81), -82 (MD-82), -83 (MD-83), and -87 (MD-87) series airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes; as listed in McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993; 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 (f) 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 cracks in the skin and longerons of the fuselage, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane, accomplish the following: (a) Perform a high frequency eddy current (HFEC) inspection of the external areas of the fuselage to detect cracks of the skin between stations Y=160.000 and Y=218.000, and of the skin at the longeron attachments between stations Y=160.000 and Y=180.000, longeron 4 left and longeron 5 left, in accordance with McDonnell Douglas DC-9 Service Bulletin 53-235 dated September 15, 1993. Perform the inspection at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. NOTE 2: Where there are differences between this AD and the referenced service bulletin, the AD prevails. (1) For airplanes other than those identified in paragraph (a)(2) of this AD: Inspect prior to the accumulation of 30,000 total landings, or within 8,000 landings after the effective date of this AD, whichever occurs later. (2) For airplanes that have been inspected previously in accordance with Task C46-53300 of the Corrosion Prevention and Control Program (CPCP), as required by AD 92-22-8-R1, amendment 39-8591, within 6,000 flight cycles prior to the effective date of this AD: Inspect within 12,000 landings after the effective date of this AD. (b) Condition 1 (No Cracks). If no crack is detected during any inspection required by this AD, accomplish either paragraph (b)(1) or (b)(2) of this AD, in accordance with McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993. (1) Condition 1, Option I (Repetitive Inspection). Repeat the HFEC inspection required by paragraph (a) of this AD, and the aided visual inspection specified in paragraph 2.E. of the Accomplishment Instructions of the service bulletin, at intervals not to exceed 10,000 landings. (2) Condition 1, Option II (Terminating Action Modification). Accomplish the preventative modification installation of clips and doublers between stations Y=160.000 and Y=218.000, in accordance with the service bulletin. Accomplishment of the modification constitutes terminating action for the repetitive inspection requirements of this AD. (c) Condition 2 (Skin Cracks). If any skin crack is detected during any inspection required by this AD, prior to further flight, repair it in accordance with McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993. After repair, accomplish either paragraph (b)(1) or (b)(2) of this AD. (d) Condition 3 (Longeron Cracks). If any longeron crack is detected during any inspection required by this AD, prior to further flight, repair it in accordance with McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993. After repair, accomplish either paragraph (b)(1) or (b)(2) of this AD. (e) Prior to the accumulation of 100,000 total landings, or within 4 years after the effective date of this AD, whichever occurs later, accomplish the preventative modification specified in paragraph 2.J. of the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993. Accomplishment of the modification constitutes terminating action for the requirements of this AD. Alternative Methods of Compliance (f) 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, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. Special Flight Permits (g) 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. (h) The effective date of this amendment remains July 30, 1998. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_98-13-35_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 98-13-35 R1 Document Type: AD Final Rules Docket Number: 96-NM-203-AD Subject Heading: Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Air...Show more Subject: Fatigue Cracks In External Areas Of Fuselage Status: Current Citation: (Federal Register: March 23, 1999 (Volume 64, Number 55)) Citation Publish Date: 03/23/1999 Effective Date: 07/30/1998 Make: The Boeing Company Model: DC-9-11 | DC-9-12 | DC-9-13 | DC-9-14 | DC-9-15 | DC-9-15F | DC-9-21 | DC-9-31 | DC-9-32 | DC-9-32 (...Show more 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 13890 No. 55 03/23/99) Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 98-13-35 R1 CITATION: [Federal Register: March 23, 1999 (Volume 64, Number 55)] PAGE NUMBER: [Page 13890] DOCKET NUMBER: 96-NM-203-AD AMENDMENT: 39-11086 AD NUMBER: 98-13-35 R1 SUBJECT HEADING: Airworthiness Directives; McDonnell Douglas Model DC-9 and DC-9-80 Series Airplanes, Model MD-88 Airplanes, and C-9 (Military) Series Airplanes ACTION: Final rule; correction. SUMMARY: This amendment corrects information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that currently requires repetitive high frequency eddy current inspections of certain areas of the fuselage to detect cracks of the skin and/or longeron, and various follow-on actions. That AD also requires installation of a preventative modification, which terminates the repetitive inspections. The actions specified in that AD are intended to prevent fatigue cracks, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane. This amendment corrects the requirements of the current AD by indicating the specific area in which the subject inspection must be conducted. This amendment is prompted by communication received from the manufacturer that the current requirements of the AD are different than the service information referenced as the appropriate service information in the current AD. DATES: Effective July 30, 1998. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Brent Bandley, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone (562) 627-5237; fax (562) 627-5210. SUPPLEMENTARY INFORMATION: On June 17, 1998, the FAA issued AD 98-13-35, amendment 39-10626 (63 FR 34585, June 25, 1998), which is applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes. That AD requires repetitive high frequency eddy current inspections of certain areas of the fuselage to detect cracks of the skin and/or longeron, and various follow-on actions. That AD also requires installation of a preventative modification, which terminates the repetitive inspections. That action was prompted by reports indicating that, due to material fatigue caused by installation preload and cabin pressurization cycles, fatigue cracks were found in the skin and longerons of the fuselage. The actions required by that AD are intended to prevent such fatigue cracks, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane. Actions Since Issuance of Previous Rule Since the issuance of AD 98-13-35, the FAA has received information from the manufacturer that the specified area of the initial inspection requirements of paragraph (a) of that AD differs from the service information provided in McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993 (cited in the AD as the appropriate source of service information for accomplishment of the required actions). The FAA’s intent in AD 98-13-35 was to require the actions described in McDonnell Douglas DC-9 Service Bulletin 53-235. In order to prevent operators from misinterpreting the specific area of the initial inspection, the FAA finds that the inspection requirements of paragraph (a) must be revised to specify inspection only of the fuselage, in lieu of the fuselage skin and/or longeron. Accordingly, this action revises paragraph (a) of the existing AD to remove reference to inspection of the longeron and to limit the area that is subject to the inspection (skin between stations Y=160.000 and Y=218.000; skin at the longeron attachments). Action is taken herein to clarify and correct these requirements of AD 98-13-35 and to correctly add the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13). The final rule is being reprinted in its entirety for the convenience of affected operators. The effective date remains July 30, 1998. Since this action only clarifies and corrects a current requirement, it has no adverse economic impact and imposes no additional burden on any person. Therefore, notice and public procedures hereon are unnecessary. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Correction 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 39-10626 (63 FR 34585, June 25, 1998), and by adding a new airworthiness directive (AD), amendment 39-11086, to read as follows: REGULATORY TEXT: 98-13-35 R1 MCDONNELL DOUGLAS: Amendment 39-11086. Docket 96-NM-203-AD. Revises AD 98-13-35, Amendment 39-10626. Applicability: Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81 (MD-81), -82 (MD-82), -83 (MD-83), and -87 (MD-87) series airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes; as listed in McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993; 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 (f) 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 cracks in the skin and longerons of the fuselage, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane, accomplish the following: (a) Perform a high frequency eddy current (HFEC) inspection of the external areas of the fuselage to detect cracks of the skin between stations Y=160.000 and Y=218.000, and of the skin at the longeron attachments between stations Y=160.000 and Y=180.000, longeron 4 left and longeron 5 left, in accordance with McDonnell Douglas DC-9 Service Bulletin 53-235 dated September 15, 1993. Perform the inspection at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. NOTE 2: Where there are differences between this AD and the referenced service bulletin, the AD prevails. (1) For airplanes other than those identified in paragraph (a)(2) of this AD: Inspect prior to the accumulation of 30,000 total landings, or within 8,000 landings after the effective date of this AD, whichever occurs later. (2) For airplanes that have been inspected previously in accordance with Task C46-53300 of the Corrosion Prevention and Control Program (CPCP), as required by AD 92-22-8-R1, amendment 39-8591, within 6,000 flight cycles prior to the effective date of this AD: Inspect within 12,000 landings after the effective date of this AD. (b) Condition 1 (No Cracks). If no crack is detected during any inspection required by this AD, accomplish either paragraph (b)(1) or (b)(2) of this AD, in accordance with McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993. (1) Condition 1, Option I (Repetitive Inspection). Repeat the HFEC inspection required by paragraph (a) of this AD, and the aided visual inspection specified in paragraph 2.E. of the Accomplishment Instructions of the service bulletin, at intervals not to exceed 10,000 landings. (2) Condition 1, Option II (Terminating Action Modification). Accomplish the preventative modification installation of clips and doublers between stations Y=160.000 and Y=218.000, in accordance with the service bulletin. Accomplishment of the modification constitutes terminating action for the repetitive inspection requirements of this AD. (c) Condition 2 (Skin Cracks). If any skin crack is detected during any inspection required by this AD, prior to further flight, repair it in accordance with McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993. After repair, accomplish either paragraph (b)(1) or (b)(2) of this AD. (d) Condition 3 (Longeron Cracks). If any longeron crack is detected during any inspection required by this AD, prior to further flight, repair it in accordance with McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993. After repair, accomplish either paragraph (b)(1) or (b)(2) of this AD. (e) Prior to the accumulation of 100,000 total landings, or within 4 years after the effective date of this AD, whichever occurs later, accomplish the preventative modification specified in paragraph 2.J. of the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 53-235, dated September 15, 1993. Accomplishment of the modification constitutes terminating action for the requirements of this AD. Alternative Methods of Compliance (f) 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, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. Special Flight Permits (g) 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. (h) The effective date of this amendment remains July 30, 1998. FOOTER:
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