Airworthiness Directives; McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes; McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; McDonnell Douglas Model MD-88 Airplanes; McDonnell Douglas Model MD-90-30 Airplanes; and McDonnell Douglas Model 717-200 Airplanes, 52046-52050 [05-17402]

Download as PDF 52046 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules airplanes, remove from service stage 5 LPT disks and stage 6 LPT disks listed in Figure 4 of GE ASB No. CF34–BJ S/B 72–A0148 Revision 02, dated May 24, 2005. Optional Terminating Action (m) Replacement of an affected stage 5 LPT disk or affected stage 6 LPT disk, with a disk not listed in Figure 3 or Figure 4 of GE ASB No. CF34–AL S/B 72–A0173 Revision 05, dated May 24, 2005 or not listed in Figure 3 or Figure 4 of GE ASB No. CF34–BJ S/B 72– A0148, Revision 02, dated May 24, 2005 is terminating action to the repetitive inspections and removals required by this AD for that disk. Terminating Action (n) As terminating action to the repetitive inspections and removals in this AD, replace all disks by January 1, 2013 that are listed in Figure 3 and Figure 4 of GE ASB No. CF34– AL S/B 72–A0173, Revision 05, dated May 24, 2005, and that are listed in Figure 3 and Figure 4 of GE ASB No. CF34-BJ 72–A0148, Revision 02, dated May 24, 2005. Actions Completed Per Previous Releases of Alert Service Bulletins (o) Actions completed before the effective date of this AD using GE ASB No. CF34–AL S/B 72–A0173, dated April 2, 2004; or Revision 01, dated May 20, 2004; or Revision 02, dated June 22, 2004; or Revision 03, dated July 20, 2004; or Revision 04, dated February 7, 2005; or GE ASB No. CF34–BJ S/B 72– A0148, dated September 2, 2004; or Revision 01, dated March 10, 2005, are considered acceptable for compliance with the corresponding action in this AD. Serviceable LPT Disk Definition (p) For the purpose of this AD, a serviceable LPT disk is a disk not listed in Figure 3 or Figure 4 of GE ASB No. CF34– AL S/B 72–A0173 Revision 05, dated May 24, 2005, or Figure 3 or Figure 4 of GE ASB No. CF34–BJ 72–A0148, Revision 02, dated May 24, 2005. Piece-Part Exposure Definitions (q) For the purpose of this AD, the definition of piece part exposure for the stage 5 LPT disk is when the disk is separated from the forward and aft bolted joints. (r) For the purpose of this AD, the definition of piece part exposure for the stage 6 LPT disk is when the disk is separated from the forward bolted joint. Replacement Engine or Replacement LPT Module Definition (s) For the purpose of this AD, the definition of a replacement engine or replacement LPT module is an engine or LPT module that does not have installed any of the suspect disks listed in Figure 3 or Figure 4 of GE ASB No. CF34–AL S/B 72–A0173 Revision 05, dated May 24, 2005, or Figure 3 or Figure 4 of GE ASB No. CF34–BJ 72– A0148, Revision 02, dated May 24, 2005. Alternative Methods of Compliance (t) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. VerDate Aug<18>2005 15:01 Aug 31, 2005 Jkt 205001 Related Information (u) GE ASB No. CF34–AL S/B 72–A0178 and ASB No. CF34–BJ S/B 72–A0152 contain the information necessary to identify and inspect the suspect disks that are the subject of this AD. Issued in Burlington, Massachusetts, on August 26, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–17400 Filed 8–31–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22254; Directorate Identifier 2005–NM–001–AD] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–9–10, DC–9–20, DC–9–30, DC–9–40, and DC–9–50 Series Airplanes; McDonnell Douglas Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), and DC–9– 87 (MD–87) Airplanes; McDonnell Douglas Model MD–88 Airplanes; McDonnell Douglas Model MD–90–30 Airplanes; and McDonnell Douglas Model 717–200 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This proposed AD would require an inspection to determine the part number of the upper and lower stop pad support fittings of all the lower cargo doors, repetitive inspections of all early configuration stop pad support fittings, and corrective action if necessary. This proposed AD would also provide an optional terminating action for the repetitive inspections. This proposed AD is prompted by a report of cracks found in the area of the upper and lower stop pad support fittings of the cargo door pan on numerous airplanes. We are proposing this AD to prevent cracks in the cargo door pan, which could result in the inability to fully pressurize an airplane and possible rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by October 17, 2005. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800– 0024). You can examine the contents of this AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 22254; the directorate identifier for this docket is 2005–NM–001–AD. FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5238; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: ADDRESSES: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–22254; Directorate Identifier 2005–NM–001–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal E:\FR\FM\01SEP1.SGM 01SEP1 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit http:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion We have received a report indicating that an operator found cracks in the area of the upper and lower stop pad support fittings of the cargo door pan, on numerous McDonnell Douglas Model DC–9 airplanes. These airplanes had accumulated between 23,944 and 32,735 total flight hours (and between 23,626 and 30,598 total flight cycles, respectively). We have also been notified that these early configuration stop pad support fittings could have been installed on the lower cargo doors of Model MD–90–30 and Model 717– 200 airplanes during airplane production. Early configuration stop pad support fittings could fail and cause cracks along the top and bottom of the cargo door pan. This condition, if not corrected, could result in the inability to fully pressurize an airplane and possible rapid decompression of the airplane. Other Related Rulemaking On May 8, 1996, we issued AD 96– 10–11, amendment 39–9618 (61 FR 24675, May 16, 1996), applicable to certain McDonnell Douglas Model DC– 9 and DC–9–80 series airplanes, Model MD–88 airplanes, and C–9 (military) series airplanes. Paragraph (b) of that AD requires initial and repetitive inspections to detect cracks in several areas in accordance with the DC–9/MD– 80 Aging Aircraft Service Action Requirements Document, McDonnell VerDate Aug<18>2005 15:01 Aug 31, 2005 Jkt 205001 Douglas Report No. MDC K1572, Revision B, dated January 15, 1993 (hereafter referred to as SARD, Revision B). SARD, Revision B, refers to several McDonnell Douglas service bulletins as additional sources of service information for accomplishing those various inspections. In particular, SARD, Revision B, refers to McDonnell Douglas DC–9 Service Bulletin 52–89 (for Model DC–9–10, DC–9–20, DC–9–30, DC–9–40, and DC– 9–50 series airplanes), Revision 5, dated February 26, 1991, for inspecting the forward and aft lower cargo doors to detect cracks. Those inspections are identical to the repetitive inspections that would be required by this proposed AD, in accordance with Boeing Service Bulletin DC9–52–189, Revision 01, dated March 20, 2003. Therefore, accomplishing the repetitive inspections, which would be required by this proposed AD, terminates the repetitive inspections of the forward and aft lower cargo doors required by paragraph (b) of AD 96–10–11. McDonnell Douglas DC–9 Service Bulletin 52–89, Revision 5; and Revision 6, dated January 11, 1993; also describe procedures for doing a preventative modification. The preventative modification includes installing doublers, fittings, webs, angles, clips, and other structural parts in the forward and aft lower cargo doors. If early configuration stop pad support fittings are installed on a lower cargo door, this proposed AD would reinstate inspections of the lower cargo doors at the same inspection interval, regardless of whether the preventative modification of McDonnell Douglas DC– 9 Service Bulletin DC9–52–89, Revision 5, or Revision 6, has been previously accomplished. Relevant Service Information We have reviewed the following Boeing Service Bulletins: • DC9–52–189, Revision 01, excluding Appendix A, dated March 20, 2003, for McDonnell Douglas Model DC–9–10, DC–9–20, DC–9–30, DC–9–40, DC–9–50 series airplanes; Model DC–9– 81 (MD–81), DC–9–82 (MD–82), DC–9– 83 (MD–83), and DC–9–87 (MD–87) airplanes; and Model MD–88 airplanes; • MD90–52–014, dated December 14, 2004, for McDonnell Douglas Model MD–90–30 airplanes; and • 717–52–0007, dated December 14, 2004, for McDonnell Douglas Model 717–200 airplanes. The service bulletins describe the following procedures: • For certain airplanes, inspecting to determine the part number of the upper PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 52047 and lower stop pad support fittings of lower cargo doors. • If any early configuration stop pad support fitting is installed on a lower cargo door, doing either repetitive visual or repetitive eddy current inspections for cracks in the lower cargo door. For Boeing Service Bulletins MD90– 52–014 and 717–52–0007, the corrective action includes contacting the manufacturer for repair instructions if any crack is found in the door jamb or jamb structure of a lower cargo door. For Boeing Service Bulletin DC9–52– 189, the corrective action includes the following: • Repairing any crack found in the door outer skin. • Replacing cracked parts, if cracks are found in the two adjacent beam end fittings; or if cracks are found in any beam end fitting with the intercostal web, angle, or tee fitting for any cracked upper or lower stop pad support fitting. • Repetitively inspecting for crack growth and additional cracks, if cracks are found inside any pressure seal other than the outer pan; if multiple cracks totaling 10 inches or less are found inside the pressure seal of the outer pan; if no more than two cracks, each 1.25 inches or less in length, are found outside the pressure seal of the outer pan; or if only one crack 2.0 inches or less in length is found outside the pressure seal of the outer pan. • Repairing any cracked outer pan, if multiple cracks totaling more than 10 inches are found inside the pressure seal of the outer pan; if more than 2 cracks, or any crack longer than 2.5 inches or two cracks with either one longer than 1.75 inches, are found outside the pressure seal of the outer pan; if no more than 2 cracks, each longer than 1.25 inches in length but less than 1.75 inches, are found outside the pressure seal of the outer pan; or if no more than one crack, longer than 2.0 inches in length but less than 2.5 inches, is found in the outer pressure boundary of the outer pan. The service bulletins also describe the following procedures, which would end the applicable repetitive visual or repetitive eddy current inspections: • Replacing all early configuration stop pad support fittings installed on any lower cargo door with new configuration or new stop pad support fittings. • Reidentifying the applicable lower cargo door after replacement of the early configuration stop pad support fittings. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. E:\FR\FM\01SEP1.SGM 01SEP1 52048 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and Service Bulletins.’’ Differences Between the Proposed AD and Service Bulletins The service bulletins specify that you may contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require you to repair those conditions in one of the following ways: • Using a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization whom we have authorized to make those findings. For airplanes identified as Group 1 in Boeing Service Bulletin DC9–52–189, Revision 01, the service bulletin recommends doing the initial inspection of the lower cargo doors for cracks ‘‘* * * within the next 300 flight hours on airplanes having in excess of 8,000 flight hours, if not currently inspected * * * .’’ This proposed AD, however, would require a compliance time of within 300 flight hours after the effective date of this AD, since all Group 1 airplanes already have exceeded the 8,000 total-flight-hour threshold. The service bulletins recommend not to remove and reinstall a lower cargo door on another airplane after that lower cargo door has been inspected in accordance with the applicable service bulletin. This proposed AD, however, does not prohibit reinstallation of a lower cargo door on another airplane. We have coordinated this difference with the manufacturer. Clarification of Inspection Terminology ‘‘Visually inspecting’’ as specified in the service bulletins is referred to as a ‘‘general visual inspection’’ in this proposed AD. We have included the definition for a general visual inspection in a note in this proposed AD. Costs of Compliance There are about 2,016 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators, at an average labor rate of $65 per hour, to comply with this proposed AD. ESTIMATED COSTS Action Work hours Inspection to determine part numbers for Group 2, 3, and 4 airplanes identified in Boeing Service Bulletin DC9–52– 189; Model MD–90–30 airplanes; and Model 717–200 airplanes. Inspection for cracks for Group 1 airplanes identified in Boeing Service Bulletin DC9–52–189, per inspection cycle. 1 Per Parts Number of U.S.-registered airplanes Cost per airplane Fleet cost 1 None ........... $65 1,218 $79,170 4 None ........... 1$260 368 1$95,680 inspection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order VerDate Aug<18>2005 15:01 Aug 31, 2005 Jkt 205001 13132. This proposed AD would not have a substantial direct effect 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. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas: Docket No. FAA–2005– 22254; Directorate Identifier 2005–NM– 001–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by October 17, 2005. Affected ADs (b) Accomplishing paragraph (g) or (h), as applicable, of this AD terminates certain requirements of AD 96–10–11, amendment E:\FR\FM\01SEP1.SGM 01SEP1 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules 39–9618, as specified in McDonnell Douglas DC–9 Service Bulletin 52–89, Revision 5, dated February 26, 1991. Applicability (c) This AD applies to the airplanes specified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) All McDonnell Douglas 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 (VC–9C), DC–9–32F, DC–9–33F, DC–9–34, DC–9–34F, DC–9–32F (C–9A, C– 9B), DC–9–41, and DC–9–51 airplanes; Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC– 9–83 (MD–83), DC–9–87 (MD–87) airplanes; Model MD–88 airplanes; and Model MD–90– 30 airplanes; and (2) Model 717–200 airplanes, as identified in Boeing Service Bulletin 717–52–0007, dated December 14, 2004. Unsafe Condition (d) This AD was prompted by a report of cracks found in the area of the upper and lower stop pad support fittings of the cargo door pan on numerous airplanes. We are issuing this AD to prevent cracks in the cargo door pan, which could result in the inability to fully pressurize an airplane and possible rapid decompression of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin References (f) The term ‘‘service bulletin,’’ as used in this AD, means the following service bulletins, as applicable: (1) For 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 (VC–9C), DC– 9–32F, DC–9–33F, DC–9–34, DC–9–34F, DC– 9–32F (C–9A, C–9B), DC–9–41, and DC–9–51 airplanes; Model DC–9–81 (MD–81) airplanes; Model DC–9–82 (MD–82), DC–9– 83 (MD–83), DC–9–87 (MD–87) airplanes; and Model MD–88 airplanes: Boeing Service Bulletin DC9–52–189, Revision 01, excluding Appendix A, dated March 20, 2003; (2) For Model MD–90–30 airplanes: Boeing Service Bulletin MD90–52–014, dated December 14, 2004; and (3) For Model 717–200 airplanes: Boeing Service Bulletin 717–52–0007, dated December 14, 2004. Determine Part Numbers (P/Ns) and Inspect if Necessary (g) For airplanes identified in Table 1 of this AD: At the compliance time specified in Table 1 of this AD, inspect to determine the part number of the upper and lower stop pad support fittings of the lower cargo doors, in accordance with the Accomplishment Instructions of the service bulletin, as applicable. If new configuration or new upper and lower stop pad support fittings, as identified in the applicable service bulletin, are found installed on all lower cargo doors, then no further action is required by this paragraph. If any early configuration stop pad 52049 support fitting is found installed on any lower cargo door, within 300 flight hours, do the inspection specified in either paragraph (g)(1) or (g)(2) of this AD, in accordance with the Accomplishment Instructions of the service bulletin, until the replacement specified in paragraph (k) of this AD is accomplished. (1) Do a general visual inspection for cracks in any lower cargo door having an early configuration stop pad support fitting. Repeat the general visual inspection thereafter at intervals not to exceed 1,700 flight hours. (2) Do an eddy current inspection for cracks in any lower cargo door having an early configuration stop pad support fitting. Repeat the eddy current inspection thereafter at intervals not to exceed 3,900 flight hours. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ TABLE 1.—COMPLIANCE TIMES TO DETERMINE P/N Applicable airplanes Compliance time Airplanes identified as Group 2, 3, and 4 in paragraph 1.D. of Boeing Service Bulletin DC9–52–189, Revision 01, dated March 20, 2003. Model MD–90–30 airplanes and Model 717–200 airplanes .................... Repetitive Inspections for Certain Airplanes (h) For airplanes identified as Group 1 in paragraph 1.D. of Boeing Service Bulletin DC9–52–189, Revision 01, dated March 20, 2003: At the applicable compliance time specified in Table 2 of this AD, do the Within 300 flight hours after the effective date of this AD. Before the accumulation of 25,000 total flight hours, or within 3,900 flight hours after the effective date of this AD, whichever is later. inspection specified in either paragraph (g)(1) or (g)(2) of this AD, in accordance with the Accomplishment Instructions of the service bulletin. Repeat the inspection thereafter at the interval specified in paragraph (g)(1) or (g)(2), as applicable, until the replacement specified in paragraph (k) of this AD is accomplished. Inspections also may be done in accordance with the Accomplishment Instructions of McDonnell Douglas DC–9 Service Bulletin 52–89, Revision 5, dated February 26, 1991; or Revision 6, dated January 11, 1993. TABLE 2.—COMPLIANCE TIMES FOR INSPECTION For airplanes that have— Compliance time Been inspected before the effective date of this AD in accordance with paragraph (b) of AD 96–10–11 as specified in Phase I of the Accomplishment Instructions of McDonnell Douglas DC–9 Service Bulletin 52–89, Revision 5, dated February 26, 1991, or Revision 6, dated January 11, 1993. Not been inspected before the effective date of this AD in accordance with paragraph (b) of AD 96–10–11 as specified in Phase I of the Accomplishment Instructions of McDonnell Douglas DC–9 Service Bulletin 52–89, Revision 5, dated February 26, 1991, or Revision 6, dated January 11, 1993. Within 1,700 flight hours after the last general visual inspection, or within 3,900 flight hours after the last eddy current inspection, as applicable. VerDate Aug<18>2005 15:01 Aug 31, 2005 Jkt 205001 PO 00000 Frm 00013 Fmt 4702 Within 300 flight hours after the effective date of this AD. Sfmt 4702 E:\FR\FM\01SEP1.SGM 01SEP1 52050 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules Corrective Actions for Certain Airplanes (i) For Model MD–90–30 airplanes and Model 717–200 airplanes: If any crack is found in the door jamb or jamb structure of a lower cargo door during any inspection required by paragraph (g)(1) or (g)(2) of this AD, and the service bulletin specifies contacting Boeing for appropriate action, before further flight, repair the crack using a method in accordance with paragraph (o) of this AD. Corrective Actions for Certain Other Airplanes (j) For 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 (VC–9C), DC– 9–32F, DC–9–33F, DC–9–34, DC–9–34F, DC– 9–32F (C–9A, C–9B), DC–9–41, DC–9–51 airplanes; Model DC–9–81 (MD–81), DC–9– 82 (MD–82), DC–9–83 (MD–83), and DC–9– 87 (MD–87) airplanes; and Model MD–88 airplanes: If any crack is found during any inspection required by paragraph (g)(1), (g)(2), or (h) of this AD, do the corrective action at the applicable compliance time specified in paragraph 1.E. of the service bulletin, in accordance with the Accomplishment Instructions of the service bulletin, as applicable. Optional Replacement of Stop Pad Support Fittings (k) For all airplanes: Replacement of all early configuration stop pad support fittings installed on a lower cargo door with new configuration or new stop pad support fittings, as identified in the applicable service bulletin; and reidentification of the applicable lower cargo door; in accordance with the Accomplishment Instructions of the applicable service bulletin; terminates the repetitive inspections required by paragraphs (g)(1), (g)(2), and (h) of this AD, as applicable, for that lower cargo door only. (l) For all airplanes: As of the effective date of this AD, no person may install an early configuration stop pad support fitting having P/N 3925046–1, –501, –505, –507, or –509, or P/N 3926046–1 or –501, on any airplane. Credit for Previous Service Bulletin (m) Actions done before the effective date of this AD in accordance with Boeing Service Bulletin DC9–52–189, dated August 10, 2001, are acceptable for compliance with the corresponding requirements of this AD. Terminating Action for Certain Requirements of AD 96–10–11 (n) For 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 (VC–9C), DC– 9–32F, DC–9–33F, DC–9–34, DC–9–34F, DC– 9–32F (C–9A, C–9B), DC–9–41, and DC–9–51 airplanes: Accomplishing the replacement specified in paragraph (k) of this AD for the forward and aft lower cargo doors terminates the repetitive inspections of the forward and aft lower cargo doors for cracks required by paragraph (b) of AD 96–10–11 as specified in McDonnell Douglas DC–9 Service Bulletin 52–89, Revision 5, dated February 26, 1991. 15:01 Aug 31, 2005 • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments. • Agency Web site: http:// www.fda.gov/dockets/ecomments. Follow the instructions for submitting comments on the agency Web site. Issued in Renton, Washington, on August 24, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–17402 Filed 8–31–05; 8:45 am] To ensure more timely processing of comments, FDA is no longer accepting comments submitted to the agency by e-mail. FDA encourages you to continue to submit electronic comments by using the Federal eRulemaking Portal or the agency Web site, as described in the Electronic Submissions portion of this paragraph. BILLING CODE 4910–13–U DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 310 [Docket No. 2005N–0345] RIN 0910–AF72 Drug Approvals: Circumstances Under Which an Active Ingredient May Be Simultaneously Marketed in Both a Prescription Drug Product and an Over-the-Counter Drug Product AGENCY: Parts Installation VerDate Aug<18>2005 Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. Jkt 205001 Food and Drug Administration, HHS. Advance notice of proposed rulemaking. ACTION: SUMMARY: The Food and Drug Administration (FDA) is issuing this advance notice of proposed rulemaking to request comment on whether to initiate a rulemaking to codify its interpretation of section 503(b) of the Federal Food, Drug, and Cosmetic Act (21 U.S.C. 301, et seq.), regarding when an active ingredient may be simultaneously marketed in both a prescription drug product and an overthe-counter (OTC) drug product. DATES: Submit written or electronic comments by November 1, 2005. ADDRESSES: You may submit comments, identified by Docket No. 2005N–0345 and/or RIN number 0910–AF72, by any of the following methods: Electronic Submissions Submit electronic comments in the following ways: PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Written Submissions Submit written submissions in the following ways: • FAX: 301–827–6870. • Mail/Hand delivery/Courier [For paper, disk, or CD-ROM submissions]: Division of Dockets Management, 5630 Fishers Lane, rm. 1061, Rockville, MD 20852 Instructions: All submissions received must include the agency name and Docket No. or Regulatory Information Number (RIN) for this rulemaking. All comments received will be posted without change to http://www.fda.gov/ ohrms/dockets/default.htm, including any personal information provided. For detailed instructions on submitting comments and additional information on the rulemaking process, see the ‘‘Comments’’ heading of the SUPPLEMENTARY INFORMATION section of this document. Docket: For access to the docket to read background documents or comments received, go to http:// www.fda.gov/ohrms/dockets/ default.htm and insert the docket number, found in brackets in the heading of this document, into the ‘‘Search’’ box and follow the prompts and/or go to the Division of Dockets Management, 5630 Fishers Lane, rm. 1061, Rockville, MD 20852. FOR FURTHER INFORMATION CONTACT: For further information contact the FDA at 301–827–0002 or by e-mail at pcomments@fda.gov. This phone number and this e-mail account have been set-up to address questions relating to this notice. SUPPLEMENTARY INFORMATION: I. Background Since Congress first enacted the Federal Food, Drug, and Cosmetic act (the act) in 1938, there has been a great deal of discussion about when drug products should be sold as prescription drugs as opposed to OTC drugs. E:\FR\FM\01SEP1.SGM 01SEP1

Agencies

[Federal Register Volume 70, Number 169 (Thursday, September 1, 2005)]
[Proposed Rules]
[Pages 52046-52050]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-17402]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22254; Directorate Identifier 2005-NM-001-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-9-10, DC-9-
20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes; McDonnell Douglas 
Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 
(MD-87) Airplanes; McDonnell Douglas Model MD-88 Airplanes; McDonnell 
Douglas Model MD-90-30 Airplanes; and McDonnell Douglas Model 717-200 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain McDonnell Douglas transport category airplanes. This 
proposed AD would require an inspection to determine the part number of 
the upper and lower stop pad support fittings of all the lower cargo 
doors, repetitive inspections of all early configuration stop pad 
support fittings, and corrective action if necessary. This proposed AD 
would also provide an optional terminating action for the repetitive 
inspections. This proposed AD is prompted by a report of cracks found 
in the area of the upper and lower stop pad support fittings of the 
cargo door pan on numerous airplanes. We are proposing this AD to 
prevent cracks in the cargo door pan, which could result in the 
inability to fully pressurize an airplane and possible rapid 
decompression of the airplane.

DATES: We must receive comments on this proposed AD by October 17, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024).
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-22254; the directorate identifier for this docket is 
2005-NM-001-AD.

FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5238; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-22254; 
Directorate Identifier 2005-NM-001-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal

[[Page 52047]]

information you provide. We will also post a report summarizing each 
substantive verbal contact with FAA personnel concerning this proposed 
AD. Using the search function of that Web site, anyone can find and 
read the comments in any of our dockets, including the name of the 
individual who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc.). You can review DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78), or you can visit http://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    We have received a report indicating that an operator found cracks 
in the area of the upper and lower stop pad support fittings of the 
cargo door pan, on numerous McDonnell Douglas Model DC-9 airplanes. 
These airplanes had accumulated between 23,944 and 32,735 total flight 
hours (and between 23,626 and 30,598 total flight cycles, 
respectively). We have also been notified that these early 
configuration stop pad support fittings could have been installed on 
the lower cargo doors of Model MD-90-30 and Model 717-200 airplanes 
during airplane production. Early configuration stop pad support 
fittings could fail and cause cracks along the top and bottom of the 
cargo door pan. This condition, if not corrected, could result in the 
inability to fully pressurize an airplane and possible rapid 
decompression of the airplane.

Other Related Rulemaking

    On May 8, 1996, we issued AD 96-10-11, amendment 39-9618 (61 FR 
24675, May 16, 1996), applicable to certain McDonnell Douglas Model DC-
9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 
(military) series airplanes. Paragraph (b) of that AD requires initial 
and repetitive inspections to detect cracks in several areas in 
accordance with the DC-9/MD-80 Aging Aircraft Service Action 
Requirements Document, McDonnell Douglas Report No. MDC K1572, Revision 
B, dated January 15, 1993 (hereafter referred to as SARD, Revision B). 
SARD, Revision B, refers to several McDonnell Douglas service bulletins 
as additional sources of service information for accomplishing those 
various inspections.
    In particular, SARD, Revision B, refers to McDonnell Douglas DC-9 
Service Bulletin 52-89 (for Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, 
and DC-9-50 series airplanes), Revision 5, dated February 26, 1991, for 
inspecting the forward and aft lower cargo doors to detect cracks. 
Those inspections are identical to the repetitive inspections that 
would be required by this proposed AD, in accordance with Boeing 
Service Bulletin DC9-52-189, Revision 01, dated March 20, 2003. 
Therefore, accomplishing the repetitive inspections, which would be 
required by this proposed AD, terminates the repetitive inspections of 
the forward and aft lower cargo doors required by paragraph (b) of AD 
96-10-11.
    McDonnell Douglas DC-9 Service Bulletin 52-89, Revision 5; and 
Revision 6, dated January 11, 1993; also describe procedures for doing 
a preventative modification. The preventative modification includes 
installing doublers, fittings, webs, angles, clips, and other 
structural parts in the forward and aft lower cargo doors. If early 
configuration stop pad support fittings are installed on a lower cargo 
door, this proposed AD would reinstate inspections of the lower cargo 
doors at the same inspection interval, regardless of whether the 
preventative modification of McDonnell Douglas DC-9 Service Bulletin 
DC9-52-89, Revision 5, or Revision 6, has been previously accomplished.

Relevant Service Information

    We have reviewed the following Boeing Service Bulletins:
     DC9-52-189, Revision 01, excluding Appendix A, dated March 
20, 2003, for McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-
40, DC-9-50 series airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), 
DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 
airplanes;
     MD90-52-014, dated December 14, 2004, for McDonnell 
Douglas Model MD-90-30 airplanes; and
     717-52-0007, dated December 14, 2004, for McDonnell 
Douglas Model 717-200 airplanes.
    The service bulletins describe the following procedures:
     For certain airplanes, inspecting to determine the part 
number of the upper and lower stop pad support fittings of lower cargo 
doors.
     If any early configuration stop pad support fitting is 
installed on a lower cargo door, doing either repetitive visual or 
repetitive eddy current inspections for cracks in the lower cargo door.
    For Boeing Service Bulletins MD90-52-014 and 717-52-0007, the 
corrective action includes contacting the manufacturer for repair 
instructions if any crack is found in the door jamb or jamb structure 
of a lower cargo door.
    For Boeing Service Bulletin DC9-52-189, the corrective action 
includes the following:
     Repairing any crack found in the door outer skin.
     Replacing cracked parts, if cracks are found in the two 
adjacent beam end fittings; or if cracks are found in any beam end 
fitting with the intercostal web, angle, or tee fitting for any cracked 
upper or lower stop pad support fitting.
     Repetitively inspecting for crack growth and additional 
cracks, if cracks are found inside any pressure seal other than the 
outer pan; if multiple cracks totaling 10 inches or less are found 
inside the pressure seal of the outer pan; if no more than two cracks, 
each 1.25 inches or less in length, are found outside the pressure seal 
of the outer pan; or if only one crack 2.0 inches or less in length is 
found outside the pressure seal of the outer pan.
     Repairing any cracked outer pan, if multiple cracks 
totaling more than 10 inches are found inside the pressure seal of the 
outer pan; if more than 2 cracks, or any crack longer than 2.5 inches 
or two cracks with either one longer than 1.75 inches, are found 
outside the pressure seal of the outer pan; if no more than 2 cracks, 
each longer than 1.25 inches in length but less than 1.75 inches, are 
found outside the pressure seal of the outer pan; or if no more than 
one crack, longer than 2.0 inches in length but less than 2.5 inches, 
is found in the outer pressure boundary of the outer pan.
    The service bulletins also describe the following procedures, which 
would end the applicable repetitive visual or repetitive eddy current 
inspections:
     Replacing all early configuration stop pad support 
fittings installed on any lower cargo door with new configuration or 
new stop pad support fittings.
     Reidentifying the applicable lower cargo door after 
replacement of the early configuration stop pad support fittings.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

[[Page 52048]]

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. Therefore, we are proposing this AD, which 
would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the Proposed AD and Service Bulletins.''

Differences Between the Proposed AD and Service Bulletins

    The service bulletins specify that you may contact the manufacturer 
for instructions on how to repair certain conditions, but this proposed 
AD would require you to repair those conditions in one of the following 
ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Delegation Option Authorization Organization whom we 
have authorized to make those findings.
    For airplanes identified as Group 1 in Boeing Service Bulletin DC9-
52-189, Revision 01, the service bulletin recommends doing the initial 
inspection of the lower cargo doors for cracks ``* * * within the next 
300 flight hours on airplanes having in excess of 8,000 flight hours, 
if not currently inspected * * * .'' This proposed AD, however, would 
require a compliance time of within 300 flight hours after the 
effective date of this AD, since all Group 1 airplanes already have 
exceeded the 8,000 total-flight-hour threshold.
    The service bulletins recommend not to remove and reinstall a lower 
cargo door on another airplane after that lower cargo door has been 
inspected in accordance with the applicable service bulletin. This 
proposed AD, however, does not prohibit reinstallation of a lower cargo 
door on another airplane. We have coordinated this difference with the 
manufacturer.

Clarification of Inspection Terminology

    ``Visually inspecting'' as specified in the service bulletins is 
referred to as a ``general visual inspection'' in this proposed AD. We 
have included the definition for a general visual inspection in a note 
in this proposed AD.

Costs of Compliance

    There are about 2,016 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators, at an average labor rate of $65 per hour, to comply 
with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
            Action               Work hours          Parts           Cost per       registered      Fleet cost
                                                                     airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Inspection to determine part                1  None.............             $65           1,218         $79,170
 numbers for Group 2, 3, and
 4 airplanes identified in
 Boeing Service Bulletin DC9-
 52-189; Model MD-90-30
 airplanes; and Model 717-200
 airplanes.
Inspection for cracks for                   4  None.............         \1\$260             368     \1\$95,680
 Group 1 airplanes identified
 in Boeing Service Bulletin
 DC9-52-189, per inspection
 cycle.
----------------------------------------------------------------------------------------------------------------
\1\ Per inspection cycle.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect 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.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2005-22254; Directorate Identifier 
2005-NM-001-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by October 17, 2005.

Affected ADs

    (b) Accomplishing paragraph (g) or (h), as applicable, of this 
AD terminates certain requirements of AD 96-10-11, amendment

[[Page 52049]]

39-9618, as specified in McDonnell Douglas DC-9 Service Bulletin 52-
89, Revision 5, dated February 26, 1991.

Applicability

    (c) This AD applies to the airplanes specified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) All McDonnell Douglas 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 (VC-9C), 
DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-
41, and DC-9-51 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), 
DC-9-83 (MD-83), DC-9-87 (MD-87) airplanes; Model MD-88 airplanes; 
and Model MD-90-30 airplanes; and
    (2) Model 717-200 airplanes, as identified in Boeing Service 
Bulletin 717-52-0007, dated December 14, 2004.

Unsafe Condition

    (d) This AD was prompted by a report of cracks found in the area 
of the upper and lower stop pad support fittings of the cargo door 
pan on numerous airplanes. We are issuing this AD to prevent cracks 
in the cargo door pan, which could result in the inability to fully 
pressurize an airplane and possible rapid decompression of the 
airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Bulletin References

    (f) The term ``service bulletin,'' as used in this AD, means the 
following service bulletins, as applicable:
    (1) For 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 (VC-9C), DC-9-32F, DC-9-33F, 
DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and DC-9-51 
airplanes; Model DC-9-81 (MD-81) airplanes; Model DC-9-82 (MD-82), 
DC-9-83 (MD-83), DC-9-87 (MD-87) airplanes; and Model MD-88 
airplanes: Boeing Service Bulletin DC9-52-189, Revision 01, 
excluding Appendix A, dated March 20, 2003;
    (2) For Model MD-90-30 airplanes: Boeing Service Bulletin MD90-
52-014, dated December 14, 2004; and
    (3) For Model 717-200 airplanes: Boeing Service Bulletin 717-52-
0007, dated December 14, 2004.

Determine Part Numbers (P/Ns) and Inspect if Necessary

    (g) For airplanes identified in Table 1 of this AD: At the 
compliance time specified in Table 1 of this AD, inspect to 
determine the part number of the upper and lower stop pad support 
fittings of the lower cargo doors, in accordance with the 
Accomplishment Instructions of the service bulletin, as applicable. 
If new configuration or new upper and lower stop pad support 
fittings, as identified in the applicable service bulletin, are 
found installed on all lower cargo doors, then no further action is 
required by this paragraph. If any early configuration stop pad 
support fitting is found installed on any lower cargo door, within 
300 flight hours, do the inspection specified in either paragraph 
(g)(1) or (g)(2) of this AD, in accordance with the Accomplishment 
Instructions of the service bulletin, until the replacement 
specified in paragraph (k) of this AD is accomplished.
    (1) Do a general visual inspection for cracks in any lower cargo 
door having an early configuration stop pad support fitting. Repeat 
the general visual inspection thereafter at intervals not to exceed 
1,700 flight hours.
    (2) Do an eddy current inspection for cracks in any lower cargo 
door having an early configuration stop pad support fitting. Repeat 
the eddy current inspection thereafter at intervals not to exceed 
3,900 flight hours.


    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''


               Table 1.--Compliance Times To Determine P/N
------------------------------------------------------------------------
          Applicable airplanes                   Compliance time
------------------------------------------------------------------------
Airplanes identified as Group 2, 3, and  Within 300 flight hours after
 4 in paragraph 1.D. of Boeing Service    the effective date of this AD.
 Bulletin DC9-52-189, Revision 01,
 dated March 20, 2003.
Model MD-90-30 airplanes and Model 717-  Before the accumulation of
 200 airplanes.                           25,000 total flight hours, or
                                          within 3,900 flight hours
                                          after the effective date of
                                          this AD, whichever is later.
------------------------------------------------------------------------

Repetitive Inspections for Certain Airplanes

    (h) For airplanes identified as Group 1 in paragraph 1.D. of 
Boeing Service Bulletin DC9-52-189, Revision 01, dated March 20, 
2003: At the applicable compliance time specified in Table 2 of this 
AD, do the inspection specified in either paragraph (g)(1) or (g)(2) 
of this AD, in accordance with the Accomplishment Instructions of 
the service bulletin. Repeat the inspection thereafter at the 
interval specified in paragraph (g)(1) or (g)(2), as applicable, 
until the replacement specified in paragraph (k) of this AD is 
accomplished. Inspections also may be done in accordance with the 
Accomplishment Instructions of McDonnell Douglas DC-9 Service 
Bulletin 52-89, Revision 5, dated February 26, 1991; or Revision 6, 
dated January 11, 1993.

                Table 2.--Compliance Times for Inspection
------------------------------------------------------------------------
       For airplanes that have--                 Compliance time
------------------------------------------------------------------------
Been inspected before the effective      Within 1,700 flight hours after
 date of this AD in accordance with       the last general visual
 paragraph (b) of AD 96-10-11 as          inspection, or within 3,900
 specified in Phase I of the              flight hours after the last
 Accomplishment Instructions of           eddy current inspection, as
 McDonnell Douglas DC-9 Service           applicable.
 Bulletin 52-89, Revision 5, dated
 February 26, 1991, or Revision 6,
 dated January 11, 1993.
Not been inspected before the effective  Within 300 flight hours after
 date of this AD in accordance with       the effective date of this AD.
 paragraph (b) of AD 96-10-11 as
 specified in Phase I of the
 Accomplishment Instructions of
 McDonnell Douglas DC-9 Service
 Bulletin 52-89, Revision 5, dated
 February 26, 1991, or Revision 6,
 dated January 11, 1993.
------------------------------------------------------------------------


[[Page 52050]]

Corrective Actions for Certain Airplanes

    (i) For Model MD-90-30 airplanes and Model 717-200 airplanes: If 
any crack is found in the door jamb or jamb structure of a lower 
cargo door during any inspection required by paragraph (g)(1) or 
(g)(2) of this AD, and the service bulletin specifies contacting 
Boeing for appropriate action, before further flight, repair the 
crack using a method in accordance with paragraph (o) of this AD.

Corrective Actions for Certain Other Airplanes

    (j) For 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 (VC-9C), DC-9-32F, DC-9-33F, 
DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, DC-9-51 
airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), 
and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes: If any 
crack is found during any inspection required by paragraph (g)(1), 
(g)(2), or (h) of this AD, do the corrective action at the 
applicable compliance time specified in paragraph 1.E. of the 
service bulletin, in accordance with the Accomplishment Instructions 
of the service bulletin, as applicable.

Optional Replacement of Stop Pad Support Fittings

    (k) For all airplanes: Replacement of all early configuration 
stop pad support fittings installed on a lower cargo door with new 
configuration or new stop pad support fittings, as identified in the 
applicable service bulletin; and reidentification of the applicable 
lower cargo door; in accordance with the Accomplishment Instructions 
of the applicable service bulletin; terminates the repetitive 
inspections required by paragraphs (g)(1), (g)(2), and (h) of this 
AD, as applicable, for that lower cargo door only.

Parts Installation

    (l) For all airplanes: As of the effective date of this AD, no 
person may install an early configuration stop pad support fitting 
having P/N 3925046-1, -501, -505, -507, or -509, or P/N 3926046-1 or 
-501, on any airplane.

Credit for Previous Service Bulletin

    (m) Actions done before the effective date of this AD in 
accordance with Boeing Service Bulletin DC9-52-189, dated August 10, 
2001, are acceptable for compliance with the corresponding 
requirements of this AD.

Terminating Action for Certain Requirements of AD 96-10-11

    (n) For 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 (VC-9C), DC-9-32F, DC-9-33F, 
DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and DC-9-51 
airplanes: Accomplishing the replacement specified in paragraph (k) 
of this AD for the forward and aft lower cargo doors terminates the 
repetitive inspections of the forward and aft lower cargo doors for 
cracks required by paragraph (b) of AD 96-10-11 as specified in 
McDonnell Douglas DC-9 Service Bulletin 52-89, Revision 5, dated 
February 26, 1991.

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Los Angeles ACO, to make those findings. For a 
repair method to be approved, the repair must meet the certification 
basis of the airplane and 14 CFR 25.571, Amendment 45, and the 
approval must specifically refer to this AD.

    Issued in Renton, Washington, on August 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-17402 Filed 8-31-05; 8:45 am]
BILLING CODE 4910-13-U