Airworthiness Directives; Boeing Model 727 Airplanes, 16477-16481 [06-3065]

Download as PDF 16477 Rules and Regulations Federal Register Vol. 71, No. 63 Monday, April 3, 2006 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21593; Directorate Identifier 2002–NM–328–AD; Amendment 39–14537; AD 2006–07–10] RIN 2120–AA64 Airworthiness Directives; Boeing Model 727 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. cchase on PROD1PC60 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 727 airplanes. That AD currently requires repetitive visual inspections for cracking of the forward entry doorway forward frame and repair if necessary. That AD also provides an optional modification that constitutes terminating action. This new AD requires adding new post-repair and post-modification inspections for previously repaired or modified airplanes, mandating the optional modification, and adding airplanes to the applicability of the AD. This AD results from reports of cracking of the forward entry doorway forward frame of airplanes previously modified. We are issuing this AD to prevent the loss of the structural integrity of the forward entry doorway due to cracking of the frame at Body Station 303.9, and consequent cracking of the fuselage skin and rapid decompression of the airplane. DATES: This AD becomes effective May 8, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 8, 2006. VerDate Aug<31>2005 16:38 Mar 31, 2006 Jkt 208001 You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6456; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: ADDRESSES: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 91–09–07, amendment 39–6982 (56 FR 18687, April 24, 1991). The existing AD applies to certain Boeing Model 727 series airplanes. That NPRM was published in the Federal Register on June 22, 2005 (70 FR 36064). That NPRM proposed to require adding new post-repair and post-modification inspections for previously repaired or modified airplanes, mandating the optional modification, and adding airplanes to the applicability of the AD. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Request To Revise Paragraph (l) of the NPRM The Boeing Company requests that paragraph (l) of the NPRM be revised to apply the one-time inspections only to PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 most Group 1 airplanes. The commenter states that operators of most Group 1 airplanes have been planning on doing the modification in accordance with AD 90–06–09, amendment 39–6488 (55 FR 8370, March 7, 1990) and Boeing Document D6–54860. The commenter asserts that mandating the modification in the final rule is redundant because it is already required by AD 90–06–09. The commenter further explains that Revision 7 of Boeing Alert Service Bulletin (ASB) 727–53A0153, dated August 14, 2003, added some new airplanes to the Group 1 list as well as all of the Group 2 airplanes. We do not agree. We do acknowledge that, for most Group 1 airplanes, AD 90– 06–09 also mandates the same modification as paragraph (l) of this AD, in that Boeing ASB 727–53–153 is referenced in Boeing Document D6– 54860, ‘‘Aging Airplane Service Bulletin Structural Modification Program— Model 727,’’ Revision C, dated December 11, 1989, which is the appropriate source of service information required by AD 90–06–09. We do not agree to require only the inspection for most of Group 1, since the service bulletin does not distinguish those airplanes that were added to Group 1. We have provided an alternative method of compliance statement in paragraph (n)(4) of this AD to allow credit for the modification accomplished in accordance with AD 90–06–09. Request To Revise the Compliance Time The Boeing Company also requests that paragraph (l) of the NPRM be revised to extend the grace period for some Group 1 airplanes and all of the Group 2 airplanes. The commenter suggests using the wording, ‘‘Before the accumulation of 60,000 total flight cycles, or within the earlier of 4 years or 7,200 flight cycles after the effective date of this AD.’’ The commenter notes that some Group 1 airplanes and all of the Group 2 airplanes have been added to Revision 7 of Boeing ASB 727– 53A0153, and consequently, they were not addressed by Boeing Document D6– 54860 or AD 90–06–09. The commenter explains that both Revision 7 of Boeing ASB 727–53A0153 and Boeing Document D6–54860 have a 60,000 flight cycle threshold to do the modification. However, the commenter E:\FR\FM\03APR1.SGM 03APR1 16478 Federal Register / Vol. 71, No. 63 / Monday, April 3, 2006 / Rules and Regulations states that the grace period in Boeing Document D6–54860 allows up to 4 years beyond the 60,000 flight cycle threshold to allow operators to schedule the airplane modification during a major maintenance check period. The commenter advises that Model 727 airplanes fly an average of 1,800 flight cycles per year or 7,200 flight cycles in 4 years. For those airplanes past the 60,000 flight cycle threshold, safety would be mitigated by the inspections at 3,700 flight cycle intervals until reaching the 7,200 flight cycle or 4-year limit, whichever occurs first. The commenter states that revising the grace period also would provide the consistency with the compliance times specified in Boeing Document D6– 54860. We agree that the compliance time may be revised for the reasons given by the commenter. We have revised paragraph (l) and added a new paragraph (m) of this AD to accommodate revision of the compliance time. This revision does not change the grace period for modification of Group 1 airplanes applicable to AD 90–06–09. Editorial Changes We have revised paragraph (f) of this AD to correctly reference subparagraphs (f)(1) and (f)(2) of this AD. We also have revised this AD to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. In addition, we inadvertently specified in paragraph (k) of the NPRM that any cracking found during any HFEC inspection required certain corrective actions. Our intention was to specify that any cracking found during any inspection would require certain corrective actions. We have revised paragraph (k) of this AD to state that, if any cracking is detected during any inspection, certain corrective actions must be accomplished. cchase on PROD1PC60 with RULES Explanation of Change To Applicability We have revised the applicability of the existing AD to identify model designations as published in the most recent type certificate data sheet for the affected models. Conclusion We have carefully reviewed the available data, including the comments that have been received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden VerDate Aug<31>2005 16:38 Mar 31, 2006 Jkt 208001 on any operator nor increase the scope of the AD. Costs of Compliance There are about 1,038 Model 727 airplanes of the affected design in the worldwide fleet. This AD will affect about 616 airplanes of U.S. registry. The actions that are required by AD 91–09–07 and retained in this AD take about 58 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the currently required actions is $3,770 per airplane, per inspection cycle. The new inspections will take about 5 to 6 work hours per airplane, depending on the airplane configuration, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the new actions required by this AD is between $325 and $390 per airplane, per inspection cycle. The terminating action specified in this AD will affect airplanes on which the previous optional modification has not been accomplished, and will take between 14 and 40 work hours per airplane, depending on the airplane configuration, at an average labor rate of $65 per work hour. Required parts for the terminating modification will cost between $877 and $6,749 per airplane, depending on the airplane configuration. Based on these figures, the estimated cost of the terminating action specified in this AD is between $1,787 and $9,349 per airplane. 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 AD will not have federalism implications under PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Executive Order 13132. This AD will 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–6982 (56 FR 18687, April 24, 1991) and by adding the following new airworthiness directive (AD): I 2006–07–10 Boeing: Amendment 39–14537. Docket No. FAA–2005–21593; Directorate Identifier 2002–NM–328–AD. Effective Date (a) This AD becomes effective May 8, 2006. Affected ADs (b) This AD supersedes AD 91–09–07. Applicability (c) This AD applies to Boeing Model 727, 727C, 727–100, 727–100C, 727–200, and 727–200F airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 727–53A0153, Revision 7, dated August 14, 2003. Unsafe Condition (d) This AD was prompted by reports of cracking of the forward frame of the forward E:\FR\FM\03APR1.SGM 03APR1 16479 Federal Register / Vol. 71, No. 63 / Monday, April 3, 2006 / Rules and Regulations entry doorway of airplanes previously modified. We are issuing this AD to prevent the loss of the structural integrity of the forward entry doorway due to cracking at Body Station (BS) 303.9, and consequent cracking of the fuselage skin and 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. Restatement of Certain Requirements of AD 91–09–07 (f) For airplanes listed in Boeing Service Bulletin 727–53–0153, Revision 5, dated December 14, 1989: Visually inspect the forward entry doorway frame for cracks in accordance with Boeing Service Bulletin 727–53–0153, dated February 1, 1980, or Revisions 1 through 5, at the earlier of the times indicated in subparagraphs (f)(1) or (f)(2) of this AD. Repeat the inspection at intervals not to exceed 3,700 landings until accomplishment of the one-time high frequency eddy current (HFEC) inspection for cracking and the one-time dimensional inspection for anomalies required by paragraph (i) of this AD, or the one-time dimensional inspection for anomalies and the initial HFEC inspection for cracking of the forward frame of the forward entry doorway at BS 303.9 specified in paragraph (h) of this AD, as applicable. (1) Within the next 1,850 landings after March 11, 1983 (the effective date of AD 83– 03–01, amendment 39–4561), or prior to accumulating a total of 25,000 landings, whichever occurs later; or (2) Within the next 1,850 landings after May 16, 1986 (the effective date of AD 83– 03–01 R1, amendment 39–5283), or prior to accumulating a total of 15,000 landings, whichever occurs later. (g) For airplanes modified in accordance with Boeing Service Bulletin 727–53–0153, dated February 1, 1980; through Revision 4, dated November 8, 1985; conduct the inspections described in paragraph (f) of this AD prior to the accumulation of 10,000 landings after the modification or within the next 3,700 landings after May 28, 1991 (the effective date of AD 91–09–07), whichever occurs later. Repeat the inspection at intervals not to exceed 3,700 landings until accomplishment of the one-time HFEC inspection for cracking and the one-time dimensional inspection for anomalies required by paragraph (i) of this AD, or the one-time dimensional inspection for anomalies and the initial HFEC inspection for cracking of the forward frame of the forward entry doorway at BS 303.9 specified in paragraph (h) of this AD, as applicable. New Requirements of This AD Repetitive Inspections for Certain Airplanes (h) For Group 1 airplanes as defined by Boeing Alert Service Bulletin (ASB) 727– 53A0153, Revision 7, dated August 14, 2003, with the exception of certain Group 1 airplanes specified in paragraph (i) of this AD: Perform a one-time dimensional inspection for anomalies (e.g., minimum dimension requirements, jagged edges, chafing, nicks, or gouges) of the web cutouts at stringers S–15 and S–16, and HFEC inspections for cracking of the forward frame of the forward entry doorway at BS 303.9; in accordance with Figure 1 of the Accomplishment Instructions of Revision 7 of the ASB at the times specified in paragraph (h)(1) or (h)(2) of this AD, as applicable. With the exception of the onetime dimensional inspection (Step 1 of Figure 1) of the web cutouts at S–15L and S– 16L, repeat the HFEC inspections for cracking of the forward frame of the forward entry doorway at BS 303.9 at intervals not to exceed 3,700 flight cycles until the requirements of paragraph (l) of this AD have been accomplished. (1) For Group 1 airplanes that have not been modified or repaired in accordance with any issue of the service bulletin through Revision 7 inclusive specified in Table 1 of this AD: Perform the inspection before the accumulation of 15,000 total flight cycles, or within 1,800 flight cycles after the effective date of this AD, whichever occurs later. TABLE 1.—SERVICE BULLETIN REVISIONS Service bulletin Boeing Boeing Boeing Boeing Boeing Boeing Boeing Boeing Service Bulletin 727–53–153 ........................................................................................................ Service Bulletin 727–53–153 ........................................................................................................ Service Bulletin 727–53–153 ........................................................................................................ Service Bulletin 727–53–153 ........................................................................................................ Service Bulletin 727–53–153 ........................................................................................................ Service Bulletin 727–53–0153 ...................................................................................................... Service Bulletin 727–53–0153 ...................................................................................................... Alert Service Bulletin 727–53A153 ............................................................................................... (2) For Group 1 airplanes that have been modified as specified in Boeing Repair Kit 65C20303–1 in accordance with any issue of the service bulletin through Revision 4 inclusive as specified in Table 1 of this AD: Perform the inspection before the accumulation of 10,000 flight cycles after the modification, or within 1,800 flight cycles after the effective date of this AD, whichever occurs later. One-Time Inspections and Terminating Actions for Certain Other Airplanes cchase on PROD1PC60 with RULES Revision level (i) For Group 1 airplanes, as defined by Boeing ASB 727–53A0153, Revision 7, dated August 14, 2003, that have been modified in accordance with Revision 5 or 6 of Boeing Service Bulletin 727–53–0153 as specified in Table 1 of this AD, or that have been repaired in accordance with Boeing Repair Kit 65C20303–8 or –25 as specified in Revision 2 through Revision 6 inclusive of the service bulletin as specified in Table 1 of this AD: Within 4,500 flight cycles after the effective date of this AD, do a one-time HFEC for VerDate Aug<31>2005 16:38 Mar 31, 2006 Jkt 208001 cracking and a dimensional inspection for any anomaly (e.g., minimum dimension requirements, jagged edges, chafing, nicks or gouges) of the web cutouts at stringers S–15L and S–16L of the forward frame of the forward entry doorway at BS 303.9, in accordance with Step 1 and Step 2 of Figure 1 of the Accomplishment Instructions of Boeing ASB 727–53A0153, Revision 7, dated August 14, 2003. For these airplanes, accomplishment of the HFEC, dimensional inspections, and any applicable corrective actions, constitutes terminating action for all the repetitive inspection requirements of this AD. Inspections for Group 2 Airplanes (j) For Group 2 airplanes, as defined by Boeing ASB 727–53A0153, Revision 7, dated August 14, 2003, that have not been modified or repaired in accordance with Revision 7 of the ASB: Before the accumulation of 17,000 total flight cycles, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later, perform a one-time PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Original .......... Revision 1 ...... Revision 2 ...... Revision 3 ...... Revision 4 ...... Revision 5 ...... Revision 6 ...... Revision 7 ...... Date February 1, 1980. June 19, 1981. December 3, 1982. June 17, 1983. November 8, 1985. December 14, 1989. August 27, 1992. August 14, 2003. dimensional inspection for anomalies (e.g., minimum dimension requirements, jagged edges, chafing, nicks, or gouges) of the web cutouts at stringers S–15 and S–16, and HFEC inspections for cracking of the forward frame of the forward entry doorway at BS 303.9; in accordance with Figure 2 of the Accomplishment Instructions of Revision 7 of the ASB. With the exception of the onetime dimensional inspection (Step 1 of Figure 2) of the web cutouts at S–15L and S– 16L, repeat the HFEC inspections for cracking of the forward frame of the forward entry doorway at BS 303.9 at intervals not to exceed 3,700 flight cycles until the requirements of paragraph (l) of this AD have been accomplished. Corrective Actions (k) If any cracking is detected during any inspection, or any anomaly is detected during any dimensional inspection required by this AD: Before further flight, accomplish the actions in paragraph (k)(1) or (k)(2) of this AD, as applicable. E:\FR\FM\03APR1.SGM 03APR1 16480 Federal Register / Vol. 71, No. 63 / Monday, April 3, 2006 / Rules and Regulations (1) For any cracking that is within the limits specified in the Accomplishment Instructions of Boeing ASB 727–53A0153, Revision 7, dated August 14, 2003: Repair the cracking in accordance with Revision 7 of the ASB. (2) For any cracking that is outside the limits specified in the Accomplishment Instructions of Boeing ASB 727–53A0153, Revision 7, dated August 14, 2003, or for any anomaly that is detected during any dimensional inspection required by this AD: Repair in accordance with a method approved by the Manager, Seattle Aircraft Certification (ACO), FAA; or in accordance with the procedures specified in paragraph (n) of this AD. Terminating Actions for Certain Airplanes (l) For airplanes specified in paragraph (l)(1) or (l)(2) of this AD: At the time specified in paragraph (m) of this AD, perform the inspections specified in Figure 1 or Figure 2, as applicable, of Revision 7 of Boeing ASB 727–53A0153, dated August 14, 2003, and as specified by paragraph (h) or (j) of this AD, as applicable. Before further flight, following the inspections, modify the forward frame in accordance with the Accomplishment Instructions of Revision 7 of the ASB. Concurrent accomplishment of the inspections and modification constitutes terminating action for the repetitive inspections required by this AD. (1) Group 1 airplanes that have not been modified or repaired in accordance with Boeing Repair Kit 65C20303–8 or –25, as specified in Boeing Service Bulletin 727–53– 153, Revision 2, dated December 3, 1982; Revision 3, dated June 17, 1983; or Revision 4, dated November 8, 1985; Boeing Service Bulletin 727–53–0153, Revision 5, dated December 14, 1989; or Revision 6, dated August 27, 1992; or Boeing ASB 727– 53A0153, Revision 7, dated August 14, 2003. (2) Group 2 airplanes that have not been repaired or modified in accordance with Revision 7 of Boeing ASB 727–53A0153, dated August 14, 2003. Note 1: Accomplishment of the terminating actions specified in paragraph (i) or (l) of this AD does not relieve the operator of responsibility to comply with the inspection requirements of the operator’s standard structural maintenance program. Compliance Times for the Requirements of Paragraph (l) of This AD (m) Accomplish the actions required in paragraph (l) of this AD at the later of the times specified in paragraph (m)(1) or (m)(2) of this AD. (1) Prior to the accumulation of 60,000 total flight cycles. (2) Within 48 months or 7,200 flight cycles after the effective date of this AD, whichever occurs first. Alternative Methods of Compliance (AMOCs) (n)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) 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, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously in accordance with AD 91–09–07, amendment 39–6982, are approved as AMOCs with the corresponding requirements and provisions of this AD. (5) Accomplishment of the actions specified in paragraph (l) of this AD constitutes an AMOC with paragraph A. of AD 90–06–09, amendment 39–6488, only for the structural modification requirements of Boeing Service Bulletin 727–53–153, as specified in Boeing Document D6–54860, Revision C, dated December 11, 1989, which is the appropriate source of service information specified by AD 90–06–09. Material Incorporated by Reference (o) You must use the applicable service bulletins or alert service bulletin specified in Table 2 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Boeing Service Bulletin 727–53–153, Revision 1, including Addendum, dated June 19, 1981, contains the following effective pages: Page No. Revision level shown on page Date shown on page 1–25 ................ 26 .................... 1 ............. Original .. June 19, 1981. February 1, 1980. Addendum 1–6 .................. 1 ............. June 19, 1981. Boeing Service Bulletin 727–53–153, Revision 4, including Addendum, dated November 8, 1985, contains the following effective pages: Page number Revision level shown on page Date shown on page 4 November 8, 1985. June 17, 1983. 1–11, 13–19, 21. 12, 20, 22 .... 3 Addendum 1, 4 .............. 3 June 17, 1983. 2, 3, 5, 6 ...... 4 November 8, 1985. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. TABLE 2.—MATERIAL INCORPORATED BY REFERENCE Service bulletin cchase on PROD1PC60 with RULES 1. 2. 3. 4. 5. 6. 7. Boeing Boeing Boeing Boeing Boeing Boeing Boeing Revision level Service Bulletin 727–53–153 .............................................................. Service Bulletin 727–53–153, including Addendum ........................... Service Bulletin 727–53–153, including Addendum ........................... Service Bulletin 727–53–153, including Addendum ........................... Service Bulletin 727–53–153, including Addendum ........................... Service Bulletin 727–53–0153, including Addendum ......................... Alert Service Bulletin 727–53A0153 ................................................... VerDate Aug<31>2005 16:38 Mar 31, 2006 Jkt 208001 PO 00000 Frm 00004 Fmt 4700 Original ................................................. Revision 1 ............................................ Revision 2 ............................................ Revision 3 ............................................ Revision 4 ............................................ Revision 5 ............................................ Revision 7 ............................................ Sfmt 4700 E:\FR\FM\03APR1.SGM 03APR1 Date February 1, 1980. June 19, 1981. December 3, 1982. June 17, 1983. November 8, 1985. December 14, 1989. August 14, 2003. Federal Register / Vol. 71, No. 63 / Monday, April 3, 2006 / Rules and Regulations Issued in Renton, Washington, on March 17, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–3065 Filed 3–31–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 524 Ophthalmic and Topical Dosage Form New Animal Drugs; Gentamicin Sulfate, Betamethasone Valerate, Clotrimazole Ointment AGENCY: Food and Drug Administration, HHS. Final rule; technical amendment. cchase on PROD1PC60 with RULES ACTION: SUMMARY: The Food and Drug Administration (FDA) is amending the animal drug regulations to reflect approval of a supplemental abbreviated new animal drug application (ANADA) filed by Med-Pharmex, Inc. The supplemental ANADA provides for a new container size, a 15-gram bottle, from which gentamicin sulfate, betamethasone valerate, clotrimazole ointment may be dispensed for the treatment of acute and chronic canine otitis externa. DATES: This rule is effective April 3, 2006. FOR FURTHER INFORMATION CONTACT: Christopher Melluso, Center for Veterinary Medicine (HFV–104), Food and Drug Administration, 7500 Standish Pl., Rockville, MD 20855, 301–827– 0169, e-mail: christopher.melluso@fda.hhs.gov. SUPPLEMENTARY INFORMATION: MedPharmex, Inc., 2727 Thompson Creek Rd., Pomona, CA 91767–1861, filed a supplement to ANADA 200–229 that provides for use of TRI-OTIC (gentamicin sulfate, USP; betamethasone valerate, USP; and clotrimazole, USP) Ointment for the treatment of canine otitis externa associated with yeast (Malassezia pachydermatis, formerly Pityrosporum canis) and/or bacteria susceptible to gentamicin. The supplement provides for a new container size, a 15-gram bottle. The supplemental ANADA is approved as of February 27, 2006, and the regulations are amended in § 524.1044g (21 CFR 524.1044g) to reflect the approval. The basis of approval is discussed in the freedom of information summary. VerDate Aug<31>2005 16:38 Mar 31, 2006 Jkt 208001 In addition, FDA has noticed that a 215-gram bottle size was approved for this product under ANADA 200–229 but not codified. At this time, that bottle size is being added to § 524.1044g. This action is being taken to improve the accuracy of the regulations. In accordance with the freedom of information provisions of 21 CFR part 20 and 21 CFR 514.11(e)(2)(ii), a summary of safety and effectiveness data and information submitted to support approval of this application may be seen in the Division of Dockets Management (HFA–305), Food and Drug Administration, 5630 Fishers Lane, rm. 1061, Rockville, MD 20852, between 9 a.m. and 4 p.m., Monday through Friday. The agency has determined under 21 CFR 25.33(a)(1) that this action is of a type that does not individually or cumulatively have a significant effect on the human environment. Therefore, neither an environmental assessment nor an environmental impact statement is required. This rule does not meet the definition of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because it is a rule of ‘‘particular applicability.’’ Therefore, it is not subject to the congressional review requirements in 5 U.S.C. 801–808. List of Subjects in 21 CFR Part 524 Animal drugs. I Therefore, under the Federal Food, Drug, and Cosmetic Act and under authority delegated to the Commissioner of Food and Drugs and redelegated to the Center for Veterinary Medicine, 21 CFR part 524 is amended as follows: PART 524—OPHTHALMIC AND TOPICAL DOSAGE FORM NEW ANIMAL DRUGS 1. The authority citation for 21 CFR part 524 continues to read as follows: I Authority: 21 U.S.C. 360b. 2. In § 524.1044g, revise paragraphs (b)(2) and (c)(1)(i) to read as follows: I § 524.1044g Gentamicin sulfate, betamethasone valerate, clotrimazole ointment. * * * * * (b) * * * (2) No. 054925 for use of 7.5- or 15g tubes; 10-, 15-, 25-, or 215-g bottles. * * * * * (c) * * * (1) * * * (i) From 7.5- or 15-g tubes; 10-, 12.5-, 15-, 25-, or 30-g bottles: 4 drops for dogs weighing less than 30 pounds (lb) or 8 drops for dogs weighing 30 lb or more. * * * * * PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 16481 Dated: March 24, 2006. Bernadette A. Dunham, Deputy Director, Office of New Animal Drug Evaluation, Center for Veterinary Medicine. [FR Doc. 06–3149 Filed 3–31–06; 8:45 am] BILLING CODE 4160–01–S DEPARTMENT OF STATE 22 CFR Part 34 [Public Notice: 5310] Debt Collection Department of State. Final rule. AGENCY: ACTION: SUMMARY: The Department of State is revising its debt collection regulations to conform to changes in Federal Government-wide debt collection laws and regulations, including the Debt Collection Improvement Act of 1996 and the revised Federal Claims Collections Standards jointly issued by the Department of the Treasury and Department of Justice in 2000. DATES: This rule is effective May 3, 2006. ADDRESSES: You may submit comments by any of the following methods: • E-mail: AmoryER@state.gov • Mail paper submissions to the Deputy Assistant Secretary for Global Financial Services, Charleston Financial Service Center, P.O. Box 150008, Charleston, S.C. 29415–5008. Persons with access to the internet may also view this notice by going to the regulations.gov Web site at: https:// www.regulations.gov/index.cfm. FOR FURTHER INFORMATION CONTACT: Elizabeth Amory, Office of the Legal Adviser, Charleston Financial Service Center, telephone 843–308–5605. SUPPLEMENTARY INFORMATION: This rule revises the Department of State’s (State) debt collection regulations found at 22 CFR part 34 to conform to the Debt Collection Improvement Act of 1996 (DCIA), Public Law 104–134, 110 Stat. 1321, 1358 (Apr. 26, 1996), the revised Federal Claims Collection Standards, 31 CFR Chapter IX (parts 900 through 904), and other laws applicable to the collection of non-tax debt owed to the Government. This regulation provides procedures for the collection of debts owed to State entities. State adopts the Governmentwide debt collection standards promulgated by the Departments of the Treasury and Justice, known as the Federal Claims Collection Standards (FCCS), as revised on November 22, 2000 (65 FR 70390), and supplements the FCCS by prescribing procedures E:\FR\FM\03APR1.SGM 03APR1

Agencies

[Federal Register Volume 71, Number 63 (Monday, April 3, 2006)]
[Rules and Regulations]
[Pages 16477-16481]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3065]

========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.

========================================================================

Federal Register / Vol. 71, No. 63 / Monday, April 3, 2006 / Rules
and Regulations

[[Page 16477]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21593; Directorate Identifier 2002-NM-328-AD;
Amendment 39-14537; AD 2006-07-10]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 727 Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 727 airplanes. That AD
currently requires repetitive visual inspections for cracking of the
forward entry doorway forward frame and repair if necessary. That AD
also provides an optional modification that constitutes terminating
action. This new AD requires adding new post-repair and post-
modification inspections for previously repaired or modified airplanes,
mandating the optional modification, and adding airplanes to the
applicability of the AD. This AD results from reports of cracking of
the forward entry doorway forward frame of airplanes previously
modified. We are issuing this AD to prevent the loss of the structural
integrity of the forward entry doorway due to cracking of the frame at
Body Station 303.9, and consequent cracking of the fuselage skin and
rapid decompression of the airplane.

DATES: This AD becomes effective May 8, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of May 8, 2006.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

You may examine the airworthiness directive (AD) docket on the
Internet at https://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 street address stated in the ADDRESSES section.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 91-09-07, amendment 39-
6982 (56 FR 18687, April 24, 1991). The existing AD applies to certain
Boeing Model 727 series airplanes. That NPRM was published in the
Federal Register on June 22, 2005 (70 FR 36064). That NPRM proposed to
require adding new post-repair and post-modification inspections for
previously repaired or modified airplanes, mandating the optional
modification, and adding airplanes to the applicability of the AD.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.

Request To Revise Paragraph (l) of the NPRM

The Boeing Company requests that paragraph (l) of the NPRM be
revised to apply the one-time inspections only to most Group 1
airplanes. The commenter states that operators of most Group 1
airplanes have been planning on doing the modification in accordance
with AD 90-06-09, amendment 39-6488 (55 FR 8370, March 7, 1990) and
Boeing Document D6-54860. The commenter asserts that mandating the
modification in the final rule is redundant because it is already
required by AD 90-06-09. The commenter further explains that Revision 7
of Boeing Alert Service Bulletin (ASB) 727-53A0153, dated August 14,
2003, added some new airplanes to the Group 1 list as well as all of
the Group 2 airplanes.
We do not agree. We do acknowledge that, for most Group 1
airplanes, AD 90-06-09 also mandates the same modification as paragraph
(l) of this AD, in that Boeing ASB 727-53-153 is referenced in Boeing
Document D6-54860, ``Aging Airplane Service Bulletin Structural
Modification Program--Model 727,'' Revision C, dated December 11, 1989,
which is the appropriate source of service information required by AD
90-06-09. We do not agree to require only the inspection for most of
Group 1, since the service bulletin does not distinguish those
airplanes that were added to Group 1. We have provided an alternative
method of compliance statement in paragraph (n)(4) of this AD to allow
credit for the modification accomplished in accordance with AD 90-06-
09.

Request To Revise the Compliance Time

The Boeing Company also requests that paragraph (l) of the NPRM be
revised to extend the grace period for some Group 1 airplanes and all
of the Group 2 airplanes. The commenter suggests using the wording,
``Before the accumulation of 60,000 total flight cycles, or within the
earlier of 4 years or 7,200 flight cycles after the effective date of
this AD.'' The commenter notes that some Group 1 airplanes and all of
the Group 2 airplanes have been added to Revision 7 of Boeing ASB 727-
53A0153, and consequently, they were not addressed by Boeing Document
D6-54860 or AD 90-06-09. The commenter explains that both Revision 7 of
Boeing ASB 727-53A0153 and Boeing Document D6-54860 have a 60,000
flight cycle threshold to do the modification. However, the commenter

[[Page 16478]]

states that the grace period in Boeing Document D6-54860 allows up to 4
years beyond the 60,000 flight cycle threshold to allow operators to
schedule the airplane modification during a major maintenance check
period. The commenter advises that Model 727 airplanes fly an average
of 1,800 flight cycles per year or 7,200 flight cycles in 4 years. For
those airplanes past the 60,000 flight cycle threshold, safety would be
mitigated by the inspections at 3,700 flight cycle intervals until
reaching the 7,200 flight cycle or 4-year limit, whichever occurs
first. The commenter states that revising the grace period also would
provide the consistency with the compliance times specified in Boeing
Document D6-54860.
We agree that the compliance time may be revised for the reasons
given by the commenter. We have revised paragraph (l) and added a new
paragraph (m) of this AD to accommodate revision of the compliance
time. This revision does not change the grace period for modification
of Group 1 airplanes applicable to AD 90-06-09.

Editorial Changes

We have revised paragraph (f) of this AD to correctly reference
sub-paragraphs (f)(1) and (f)(2) of this AD.
We also have revised this AD to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
In addition, we inadvertently specified in paragraph (k) of the
NPRM that any cracking found during any HFEC inspection required
certain corrective actions. Our intention was to specify that any
cracking found during any inspection would require certain corrective
actions. We have revised paragraph (k) of this AD to state that, if any
cracking is detected during any inspection, certain corrective actions
must be accomplished.

Explanation of Change To Applicability

We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.

Conclusion

We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

There are about 1,038 Model 727 airplanes of the affected design in
the worldwide fleet. This AD will affect about 616 airplanes of U.S.
registry.
The actions that are required by AD 91-09-07 and retained in this
AD take about 58 work hours per airplane, at an average labor rate of
$65 per work hour. Based on these figures, the estimated cost of the
currently required actions is $3,770 per airplane, per inspection
cycle.
The new inspections will take about 5 to 6 work hours per airplane,
depending on the airplane configuration, at an average labor rate of
$65 per work hour. Based on these figures, the estimated cost of the
new actions required by this AD is between $325 and $390 per airplane,
per inspection cycle.
The terminating action specified in this AD will affect airplanes
on which the previous optional modification has not been accomplished,
and will take between 14 and 40 work hours per airplane, depending on
the airplane configuration, at an average labor rate of $65 per work
hour. Required parts for the terminating modification will cost between
$877 and $6,749 per airplane, depending on the airplane configuration.
Based on these figures, the estimated cost of the terminating action
specified in this AD is between $1,787 and $9,349 per airplane.

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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. 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, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-6982 (56 FR 18687, April 24, 1991) and by adding
the following new airworthiness directive (AD):

2006-07-10 Boeing: Amendment 39-14537. Docket No. FAA-2005-21593;
Directorate Identifier 2002-NM-328-AD.

Effective Date

(a) This AD becomes effective May 8, 2006.

Affected ADs

(b) This AD supersedes AD 91-09-07.

Applicability

(c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F airplanes, certificated in any category;
as identified in Boeing Alert Service Bulletin 727-53A0153, Revision
7, dated August 14, 2003.

Unsafe Condition

(d) This AD was prompted by reports of cracking of the forward
frame of the forward

[[Page 16479]]

entry doorway of airplanes previously modified. We are issuing this
AD to prevent the loss of the structural integrity of the forward
entry doorway due to cracking at Body Station (BS) 303.9, and
consequent cracking of the fuselage skin and 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.

Restatement of Certain Requirements of AD 91-09-07

(f) For airplanes listed in Boeing Service Bulletin 727-53-0153,
Revision 5, dated December 14, 1989: Visually inspect the forward
entry doorway frame for cracks in accordance with Boeing Service
Bulletin 727-53-0153, dated February 1, 1980, or Revisions 1 through
5, at the earlier of the times indicated in subparagraphs (f)(1) or
(f)(2) of this AD. Repeat the inspection at intervals not to exceed
3,700 landings until accomplishment of the one-time high frequency
eddy current (HFEC) inspection for cracking and the one-time
dimensional inspection for anomalies required by paragraph (i) of
this AD, or the one-time dimensional inspection for anomalies and
the initial HFEC inspection for cracking of the forward frame of the
forward entry doorway at BS 303.9 specified in paragraph (h) of this
AD, as applicable.
(1) Within the next 1,850 landings after March 11, 1983 (the
effective date of AD 83-03-01, amendment 39-4561), or prior to
accumulating a total of 25,000 landings, whichever occurs later; or
(2) Within the next 1,850 landings after May 16, 1986 (the
effective date of AD 83-03-01 R1, amendment 39-5283), or prior to
accumulating a total of 15,000 landings, whichever occurs later.
(g) For airplanes modified in accordance with Boeing Service
Bulletin 727-53-0153, dated February 1, 1980; through Revision 4,
dated November 8, 1985; conduct the inspections described in
paragraph (f) of this AD prior to the accumulation of 10,000
landings after the modification or within the next 3,700 landings
after May 28, 1991 (the effective date of AD 91-09-07), whichever
occurs later. Repeat the inspection at intervals not to exceed 3,700
landings until accomplishment of the one-time HFEC inspection for
cracking and the one-time dimensional inspection for anomalies
required by paragraph (i) of this AD, or the one-time dimensional
inspection for anomalies and the initial HFEC inspection for
cracking of the forward frame of the forward entry doorway at BS
303.9 specified in paragraph (h) of this AD, as applicable.

New Requirements of This AD

Repetitive Inspections for Certain Airplanes

(h) For Group 1 airplanes as defined by Boeing Alert Service
Bulletin (ASB) 727-53A0153, Revision 7, dated August 14, 2003, with
the exception of certain Group 1 airplanes specified in paragraph
(i) of this AD: Perform a one-time dimensional inspection for
anomalies (e.g., minimum dimension requirements, jagged edges,
chafing, nicks, or gouges) of the web cutouts at stringers S-15 and
S-16, and HFEC inspections for cracking of the forward frame of the
forward entry doorway at BS 303.9; in accordance with Figure 1 of
the Accomplishment Instructions of Revision 7 of the ASB at the
times specified in paragraph (h)(1) or (h)(2) of this AD, as
applicable. With the exception of the one-time dimensional
inspection (Step 1 of Figure 1) of the web cutouts at S-15L and S-
16L, repeat the HFEC inspections for cracking of the forward frame
of the forward entry doorway at BS 303.9 at intervals not to exceed
3,700 flight cycles until the requirements of paragraph (l) of this
AD have been accomplished.
(1) For Group 1 airplanes that have not been modified or
repaired in accordance with any issue of the service bulletin
through Revision 7 inclusive specified in Table 1 of this AD:
Perform the inspection before the accumulation of 15,000 total
flight cycles, or within 1,800 flight cycles after the effective
date of this AD, whichever occurs later.

Table 1.--Service bulletin Revisions
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin 727-53-153...... Original..................... February 1, 1980.
Boeing Service Bulletin 727-53-153...... Revision 1................... June 19, 1981.
Boeing Service Bulletin 727-53-153...... Revision 2................... December 3, 1982.
Boeing Service Bulletin 727-53-153...... Revision 3................... June 17, 1983.
Boeing Service Bulletin 727-53-153...... Revision 4................... November 8, 1985.
Boeing Service Bulletin 727-53-0153..... Revision 5................... December 14, 1989.
Boeing Service Bulletin 727-53-0153..... Revision 6................... August 27, 1992.
Boeing Alert Service Bulletin 727-53A153 Revision 7................... August 14, 2003.
----------------------------------------------------------------------------------------------------------------

(2) For Group 1 airplanes that have been modified as specified
in Boeing Repair Kit 65C20303-1 in accordance with any issue of the
service bulletin through Revision 4 inclusive as specified in Table
1 of this AD: Perform the inspection before the accumulation of
10,000 flight cycles after the modification, or within 1,800 flight
cycles after the effective date of this AD, whichever occurs later.

One-Time Inspections and Terminating Actions for Certain Other
Airplanes

(i) For Group 1 airplanes, as defined by Boeing ASB 727-53A0153,
Revision 7, dated August 14, 2003, that have been modified in
accordance with Revision 5 or 6 of Boeing Service Bulletin 727-53-
0153 as specified in Table 1 of this AD, or that have been repaired
in accordance with Boeing Repair Kit 65C20303-8 or -25 as specified
in Revision 2 through Revision 6 inclusive of the service bulletin
as specified in Table 1 of this AD: Within 4,500 flight cycles after
the effective date of this AD, do a one-time HFEC for cracking and a
dimensional inspection for any anomaly (e.g., minimum dimension
requirements, jagged edges, chafing, nicks or gouges) of the web
cutouts at stringers S-15L and S-16L of the forward frame of the
forward entry doorway at BS 303.9, in accordance with Step 1 and
Step 2 of Figure 1 of the Accomplishment Instructions of Boeing ASB
727-53A0153, Revision 7, dated August 14, 2003. For these airplanes,
accomplishment of the HFEC, dimensional inspections, and any
applicable corrective actions, constitutes terminating action for
all the repetitive inspection requirements of this AD.

Inspections for Group 2 Airplanes

(j) For Group 2 airplanes, as defined by Boeing ASB 727-53A0153,
Revision 7, dated August 14, 2003, that have not been modified or
repaired in accordance with Revision 7 of the ASB: Before the
accumulation of 17,000 total flight cycles, or within 4,500 flight
cycles after the effective date of this AD, whichever occurs later,
perform a one-time dimensional inspection for anomalies (e.g.,
minimum dimension requirements, jagged edges, chafing, nicks, or
gouges) of the web cutouts at stringers S-15 and S-16, and HFEC
inspections for cracking of the forward frame of the forward entry
doorway at BS 303.9; in accordance with Figure 2 of the
Accomplishment Instructions of Revision 7 of the ASB. With the
exception of the one-time dimensional inspection (Step 1 of Figure
2) of the web cutouts at S-15L and S-16L, repeat the HFEC
inspections for cracking of the forward frame of the forward entry
doorway at BS 303.9 at intervals not to exceed 3,700 flight cycles
until the requirements of paragraph (l) of this AD have been
accomplished.

Corrective Actions

(k) If any cracking is detected during any inspection, or any
anomaly is detected during any dimensional inspection required by
this AD: Before further flight, accomplish the actions in paragraph
(k)(1) or (k)(2) of this AD, as applicable.

[[Page 16480]]

(1) For any cracking that is within the limits specified in the
Accomplishment Instructions of Boeing ASB 727-53A0153, Revision 7,
dated August 14, 2003: Repair the cracking in accordance with
Revision 7 of the ASB.
(2) For any cracking that is outside the limits specified in the
Accomplishment Instructions of Boeing ASB 727-53A0153, Revision 7,
dated August 14, 2003, or for any anomaly that is detected during
any dimensional inspection required by this AD: Repair in accordance
with a method approved by the Manager, Seattle Aircraft
Certification (ACO), FAA; or in accordance with the procedures
specified in paragraph (n) of this AD.

Terminating Actions for Certain Airplanes

(l) For airplanes specified in paragraph (l)(1) or (l)(2) of
this AD: At the time specified in paragraph (m) of this AD, perform
the inspections specified in Figure 1 or Figure 2, as applicable, of
Revision 7 of Boeing ASB 727-53A0153, dated August 14, 2003, and as
specified by paragraph (h) or (j) of this AD, as applicable. Before
further flight, following the inspections, modify the forward frame
in accordance with the Accomplishment Instructions of Revision 7 of
the ASB. Concurrent accomplishment of the inspections and
modification constitutes terminating action for the repetitive
inspections required by this AD.
(1) Group 1 airplanes that have not been modified or repaired in
accordance with Boeing Repair Kit 65C20303-8 or -25, as specified in
Boeing Service Bulletin 727-53-153, Revision 2, dated December 3,
1982; Revision 3, dated June 17, 1983; or Revision 4, dated November
8, 1985; Boeing Service Bulletin 727-53-0153, Revision 5, dated
December 14, 1989; or Revision 6, dated August 27, 1992; or Boeing
ASB 727-53A0153, Revision 7, dated August 14, 2003.
(2) Group 2 airplanes that have not been repaired or modified in
accordance with Revision 7 of Boeing ASB 727-53A0153, dated August
14, 2003.

Note 1: Accomplishment of the terminating actions specified in
paragraph (i) or (l) of this AD does not relieve the operator of
responsibility to comply with the inspection requirements of the
operator's standard structural maintenance program.

Compliance Times for the Requirements of Paragraph (l) of This AD

(m) Accomplish the actions required in paragraph (l) of this AD
at the later of the times specified in paragraph (m)(1) or (m)(2) of
this AD.
(1) Prior to the accumulation of 60,000 total flight cycles.
(2) Within 48 months or 7,200 flight cycles after the effective
date of this AD, whichever occurs first.

Alternative Methods of Compliance (AMOCs)

(n)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) 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, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
(4) AMOCs approved previously in accordance with AD 91-09-07,
amendment 39-6982, are approved as AMOCs with the corresponding
requirements and provisions of this AD.
(5) Accomplishment of the actions specified in paragraph (l) of
this AD constitutes an AMOC with paragraph A. of AD 90-06-09,
amendment 39-6488, only for the structural modification requirements
of Boeing Service Bulletin 727-53-153, as specified in Boeing
Document D6-54860, Revision C, dated December 11, 1989, which is the
appropriate source of service information specified by AD 90-06-09.

Material Incorporated by Reference

(o) You must use the applicable service bulletins or alert
service bulletin specified in Table 2 of this AD to perform the
actions that are required by this AD, unless the AD specifies
otherwise. Boeing Service Bulletin 727-53-153, Revision 1, including
Addendum, dated June 19, 1981, contains the following effective
pages:

------------------------------------------------------------------------
Revision level
Page No. shown on page Date shown on page
------------------------------------------------------------------------
1-25............................ 1.............. June 19, 1981.
26.............................. Original....... February 1, 1980.
------------------------------------------------------------------------
Addendum
------------------------------------------------------------------------
1-6............................. 1.............. June 19, 1981.
------------------------------------------------------------------------

Boeing Service Bulletin 727-53-153, Revision 4, including
Addendum, dated November 8, 1985, contains the following effective
pages:

------------------------------------------------------------------------
Revision
Page number level shown Date shown on page
on page
------------------------------------------------------------------------
1-11, 13-19, 21................... 4 November 8, 1985.
12, 20, 22........................ 3 June 17, 1983.
------------------------------------------------------------------------
Addendum
------------------------------------------------------------------------
1, 4.............................. 3 June 17, 1983.
------------------------------------------------------------------------
2, 3, 5, 6........................ 4 November 8, 1985.
------------------------------------------------------------------------

The Director of the Federal Register approved the incorporation
by reference of these documents in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124-2207, for a copy of this service
information. You may review copies at the Docket Management
Facility, U.S. Department of Transportation, 400 Seventh Street SW.,
room PL-401, Nassif Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

Table 2.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
1. Boeing Service Bulletin 727-53-153.... Original................... February 1, 1980.
2. Boeing Service Bulletin 727-53-153, Revision 1................. June 19, 1981.
including Addendum.
3. Boeing Service Bulletin 727-53-153, Revision 2................. December 3, 1982.
including Addendum.
4. Boeing Service Bulletin 727-53-153, Revision 3................. June 17, 1983.
including Addendum.
5. Boeing Service Bulletin 727-53-153, Revision 4................. November 8, 1985.
including Addendum.
6. Boeing Service Bulletin 727-53-0153, Revision 5................. December 14, 1989.
including Addendum.
7. Boeing Alert Service Bulletin 727- Revision 7................. August 14, 2003.
53A0153.
----------------------------------------------------------------------------------------------------------------

[[Page 16481]]

Issued in Renton, Washington, on March 17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-3065 Filed 3-31-06; 8:45 am]
BILLING CODE 4910-13-P

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