Airworthiness Directives; Boeing Model 747-100B, 747-200B, 747-200F, 747-300, 747-400, 747-400F, and 747SP Series Airplanes, 32818-32822 [06-5125]

Download as PDF 32818 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations Credit for Previous Service Bulletin (m) For Model A300 B4–601, B4–603, B4– 620, and B4–622 airplanes and Model A300 C4–605R Variant F airplanes: Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300–28–6089, dated July 18, 2005, are acceptable for compliance with the requirements of paragraph (l) of this AD. Alternative Methods of Compliance (AMOCs) (n)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, 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. Related Information (o) French airworthiness directive F–2005– 199, dated December 7, 2005, also addresses the subject of this AD. Material Incorporated by Reference (p) You must use the Airbus service information identified in Table 1 of this AD to perform the actions that are required by this AD, as applicable, unless the AD specifies otherwise. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Airbus service information Revision level Date All Operators Telex A300–600–28A6075 ...................................................................................................... All Operators Telex A300–28A6075 .............................................................................................................. Service Bulletin A300–28–0084, excluding Appendix 01 .............................................................................. Service Bulletin A300–28–0085 .................................................................................................................... Service Bulletin A300–28–6089 .................................................................................................................... Service Bulletin A310–28–2159, excluding Appendix 01 .............................................................................. Service Bulletin A310–28–2160 .................................................................................................................... Original .......... 01 ................... Original .......... Original .......... 01 ................... Original .......... Original .......... February 20, 2003. October 24, 2005. June 28, 2005. July 18, 2005. November 28, 2005. June 28, 2005. July 18, 2005. (1) The Director of the Federal Register approved the incorporation by reference of the Airbus service information identified in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 2.—NEW MATERIAL INCORPORATED BY REFERENCE Revision level Date All Operators Telex A300–28A6075 .............................................................................................................. Service Bulletin A300–28–0084, excluding Appendix 01 .............................................................................. Service Bulletin A300–28–0085 .................................................................................................................... Service Bulletin A300–28–6089 .................................................................................................................... Service Bulletin A310–28–2159, excluding Appendix 01 .............................................................................. Service Bulletin A310–28–2160 .................................................................................................................... sroberts on PROD1PC70 with RULES Airbus service information 01 ................... Original .......... Original .......... 01 ................... Original .......... Original .......... October 24, 2005. June 28, 2005. July 18, 2005. November 28, 2005. June 28, 2005. July 18, 2005. (Only the first page of Airbus All Operators Telex A300–28A6075, Revision 01, dated October 24, 2005, contains the document number and issue date; no other page of this document contains this information.) (2) On May 19, 2004 (69 FR 19756, April 14, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A300–600– 28A6075, dated February 20, 2003. (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, 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 http://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 http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on May 30, 2006. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5122 Filed 6–6–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24950; Directorate Identifier 2006–NM–036–AD; Amendment 39–14627; AD 2006–12–03] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100B, 747–200B, 747–200F, 747–300, 747–400, 747–400F, and 747SP Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Final rule; request for comments. ACTION: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain 747–100B, 747–200B, 747–200F, 747– 300, 747–400, 747–400F, and 747SP series airplanes. This AD requires doing inspections of the midpivot bolt and midpivot bolt access door of the spring beam of the inboard side of the outboard struts for discrepancies, installing a placard on the midpivot bolt access door, and applicable corrective actions if necessary. This AD results from reports indicating that the midpivot bolt and midpivot bolt access door of the spring beam of the inboard side of the outboard struts were installed in the incorrect position. We are issuing this AD to ensure that the subject midpivot bolts and midpivot bolt access doors are installed in the correct position. If not installed in the correct position, a midpivot bolt could be overloaded and crack or fracture, which could result in the loss of the spring load path and consequent separation of the associated E:\FR\FM\07JNR1.SGM 07JNR1 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations outboard strut and engine from the airplane. DATES: This AD becomes effective June 22, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 22, 2006. We must receive comments on this AD by August 7, 2006. ADDRESSES: Use one of the following addresses to submit comments on this 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. • 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. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion We have received reports indicating that the midpivot bolt and midpivot bolt access door of the spring beam of the inboard side of the outboard struts were installed in the incorrect position on two airplanes. On one of the airplanes, the midpivot bolts and midpivot bolt access doors had been installed during accomplishment of the modification of the nacelle strut and wing structure in accordance with Boeing Service Bulletin 747–54A2157 (required by AD 95–13– 05, amendment 39–9285 (60 FR 33333, June 28, 1995)). Investigation revealed that the service bulletin specified incorrect part numbers for the midpivot bolt access doors. In addition, the production installation drawings did not provide clear instructions for installing the midpivot bolts and midpivot bolt access doors, which resulted in the discrepancies on the other airplane. The midpivot bolt access door is attached to the skin of the inboard side of the outboard struts. A midpivot bolt access door has anti-rotation tabs that fit the slots of the midpivot bolt’s head. If any midpivot bolt access door is not installed correctly or if its anti-rotation tabs are not properly aligned with the slots of the midpivot bolt’s head, the midpivot bolt and its internal lubrication channel will not be in correct position. When the lubrication 32819 channel is not in the correct position, a midpivot bolt could be overloaded and crack or fracture. These conditions, if not corrected, could result in the loss of a spring beam load path and consequent separation of the associated outboard strut and engine from the airplane. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 747–54A2225, dated February 16, 2006. The service bulletin describes the inspection procedures specified in the table below. The service bulletin also describes procedures for installing a placard on the midpivot bolt access doors, and doing applicable corrective actions if necessary. The applicable corrective actions include changing or replacing any midpivot bolt access door that is damaged or installed in the incorrect position with a new or serviceable midpivot bolt access door, and under certain conditions, replacing the midpivot bolt with a new bolt. The service bulletin specifies the following compliance time depending on the airplane configuration and accumulated flight cycles: • ‘‘Within 24 months from the release date on this service bulletin or within 90 days from accumulating 8,000 flight cycles from the accomplishment of SB 747–54A2157, whichever occurs first;’’ • ‘‘Within 24 months from the release on this service bulletin or within 90 days from accumulating 8,000 total flight cycles, whichever occurs first;’’ or • ‘‘Within 90 days from the release date on this service bulletin.’’ INSPECTIONS Doing— Of— For— (1) A general visual inspection ........................... The midpivot bolt access doors ....................... (2) A general visual inspection ........................... (3) A general visual inspection ........................... The anti-rotation tabs of the midpivot bolt access doors. The midpivot bolts ............................................ (4) An ultrasonic inspection ................................ The midpivot bolts ............................................ The correct part number, damage (i.e., wear, nicks, gouges, elongated fastener holes, or cracks), or the correct position of its anti-rotation tabs. Damage (i.e., wear, nicks, gouges, or cracks) or any missing tab. Correct position or damage (i.e., nicks, gouges, or cracks). Cracks. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. sroberts on PROD1PC70 with RULES FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other airplanes of the same type design that may be registered in the U.S. at some time in the future. Therefore, we are issuing this AD to ensure that the VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 subject midpivot bolts and midpivot bolt access doors are installed in the correct position. If not installed in the correct position, a midpivot bolt could be overloaded and crack or fracture, which could result in the loss of the spring load path and consequent separation of the associated outboard strut and engine from the airplane. This AD requires accomplishing the actions specified in the service information described previously, except as PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 described under ‘‘Difference Between the Proposed AD and Service Bulletin.’’ Difference Between the Proposed Rule and Service Bulletin Operators should note that, although the Accomplishment Instructions of the referenced service bulletin describe procedures for submitting a report of inspection findings to Boeing, this AD will not require that action. E:\FR\FM\07JNR1.SGM 07JNR1 32820 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations Costs of Compliance Examining the Docket None of the airplanes affected by this action are on the U.S. Register. All airplanes affected by this AD are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported and placed on the U.S. Register in the future. If an affected airplane is imported and placed on the U.S. Register in the future, the required inspection and installation of a placard would take about 6 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the AD would be $480 per airplane. You may 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 Docket Management System receives them. FAA’s Determination of the Effective Date No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in less than 30 days after it is published in the Federal Register. sroberts on PROD1PC70 with RULES Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2006–24950; Directorate Identifier 2006–NM–036–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this 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 may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http://dms.dot.gov. VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 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 the 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 AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 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: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2006–12–03 Boeing: Amendment 39–14627. Docket No. FAA–2006–24950; Directorate Identifier 2006–NM–036–AD. Effective Date (a) This AD becomes effective June 22, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747– 100B, 747–200B, 747–200F, 747–300, 747– 400, 747–400F, and 747SP series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747–54A2225, dated February 16, 2006. Unsafe Condition (d) This AD results from reports indicating that the midpivot bolt and midpivot bolt access door of the spring beam of the inboard side of the outboard struts were installed in the incorrect position. We are issuing this AD to ensure that the subject midpivot bolts and midpivot bolt access doors are installed in the correct position. If not installed in the correct position, a midpivot bolt could be overloaded and crack or fracture, which could result in the loss of the spring load path and consequent separation of the associated outboard strut and engine from 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. Inspections (f) Do the inspections specified in Table 1 of this AD at the applicable compliance time listed in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–54A2225, dated February 16, 2006; except, where the service bulletin specifies a compliance time from the release date of the service bulletin, this AD requires compliance within the specified compliance time after the effective E:\FR\FM\07JNR1.SGM 07JNR1 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations date of this AD. Do the inspections in 32821 accordance with the Accomplishment Instructions of the service bulletin. TABLE 1.—INSPECTIONS Do— Of— For— (1) A general visual inspection ........................... The midpivot bolt access doors ....................... (2) A general visual inspection ........................... (3) A general visual inspection ........................... The anti-rotation tabs of the midpivot bolt access doors. The midpivot bolts ............................................ (4) An ultrasonic inspection ................................ The midpivot bolts ............................................ The correct part number, damage (i.e., wear, nicks, gouges, elongated fastener holes, or cracks), or the correct position of its anti-rotation tabs. Damage (i.e., wear, nicks, gouges, or cracks) or any missing tab. Correct position or damage (i.e., nicks, gouges, or cracks). Cracks. Note 1: There is a discrepancy in Step 2 of Figure 13, Sheet 2, of Boeing Alert Service Bulletin 747–54A2225, dated February 16, 2006. The ‘‘MORE DATA’’ column of the table incorrectly describes the anti-rotation slot installation as being ‘‘horizontal and are perpendicular to the strut skin aft edge.’’ The correct description is ‘‘vertical and are parallel to the strut skin aft edge.’’ Installation of a Placard and Corrective Actions (g) Before further flight after doing the inspections required by paragraph (f) of this AD, do the applicable actions specified in Table 2 of this AD in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2225, dated February 16, 2006. TABLE 2.—INSTALLATION OF A PLACARD AND CORRECTIVE ACTIONS If— And if— Then— (1) Any midpivot bolt access door has the correct part number and no damage. (2) Any midpivot bolt access door has the incorrect part number and no damage. Its anti-rotation tabs are present, are in the correct position, and have no damage. Its anti-rotation tabs are present, are in the incorrect position, and have no damage. Install a placard on the midpivot access door. (3) Any midpivot bolt access door has the incorrect part number, any damage, or any damaged or missing anti-rotation tab. (4) Any midpivot bolt is in the correct position ... None ................................................................. (5) Any midpivot bolt is in the incorrect position Any midpivot bolt has any damage .................... It has no damage ............................................. None ................................................................. It has no damage ............................................. sroberts on PROD1PC70 with RULES Replacement of Midpivot Bolt Parts Installation (h) If any condition in paragraph (h)(1) or (h)(2) of this AD is found on any outboard strut, within 24 months after doing the inspections required by paragraph (f) of this AD, replace the midpivot bolt of the spring beam of the inboard side of that outboard strut with a new midpivot bolt, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2225, dated February 16, 2006. (1) If any midpivot bolt access door of the spring beam of the inboard side of the outboard struts is found in the incorrect position (i.e., the midpivot bolt access door has the incorrect part number or its antirotation tabs are in the incorrect position) and if no damage is found on that bolt during any inspection required by paragraph (f) of this AD. (2) If any midpivot bolt of the spring beam of the inboard side of the outboard struts is found in the incorrect position and if no damage is found on that bolt during any inspection required by paragraph (f) of this AD. (i) As of the effective date of this AD, no person may install, on any airplane, a midpivot access door, part number 65B89670–339, 65B89670–340, 654U6624– 356, or 654U6624–357, unless it has been inspected in accordance with paragraphs (f)(1) and (f)(2) of this AD and found to have the correct part number for the door location, no damage, and no damaged or missing antirotation tab. VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 No Reporting (j) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle 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) 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 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Change the midpivot access door or replace it with a new or serviceable access door, and install a placard on the midpivot access door. Replace the midpivot access door with a new or serviceable door and install a placard on the door. No further action is required by this paragraph. Correct the midpivot bolt position. Replace the midpivot bolt with a new bolt. 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. Material Incorporated by Reference (1) You must use Boeing Alert Service Bulletin 747–54A2225, dated February 16, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, WA 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 E:\FR\FM\07JNR1.SGM 07JNR1 32822 Federal Register / Vol. 71, No. 109 / Wednesday, June 7, 2006 / Rules and Regulations Internet at http://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 http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on May 26, 2006. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5125 Filed 6–6–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–24424; Airspace Docket No. 06–ASO–6] Amendment of Class D Airspace Pompano Beach; FL, Amendment of Class D Airspace, Fort Lauderdale Executive Airport, FL Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: This action will amend Class D airspace at Pompano Beach, FL and Fort Lauderdale Executive Airport, FL. As a result of the decommissioning of the Pompano Beach VHF Omnidirectional Range (VOR), the legal description for the Class D airspace at Pompano Beach, FL, and Fort Lauderdale Executive Airport, FL, must be changed. DATES: Effective Date: 0901 UTC, August 3, 2006. FOR FURTHER INFORMATION CONTACT: Mark D. Ward, Manager, Airspace and Procedures Branch, Air Traffic Division, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320; telephone (404) 305–5586. SUPPLEMENTARY INFORMATION: sroberts on PROD1PC70 with RULES History An internal evaluation determined that the legal description for the Class D airspace at Pompano Beach, FL and Fort Lauderdale Executive Airport, FL contains reference to a line made up of radials off the Pompano Beach VOR, which has been decommissioned. This action will amend the legal description by replacing the reference to a line made up of a VOR radial, with a line now made up of geographic coordinates. Designations for Class D airspace areas extending upward from the surface of the earth are published in Paragraphs VerDate Aug<31>2005 19:09 Jun 06, 2006 Jkt 208001 5000 of FAA Order 7400.9N, dated September 1, 2005, and effective September 16, 2005, which is incorporated by reference in 14 CFR part 71.1. The Class D designations listed in this document will be published subsequently in the Order. Since this action has no impact on the users of the airspace in the vicinity of the Pompano Beach Airpark or Fort Lauderdale Executive Airport, notice and public procedure under 5 U.S.C. 553(b) are not necessary. The Rule This amendment to part 71 of the Federal Aviation Regulations (14 CFR part 71) amends Class D airspace at Pompano Beach, FL and Fort Lauderdale Executive Airport, FL. The FAA has determined that this proposed regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. It, therefore, (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) does not warrant preparation of a Regulatory Evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified that this rule, when promulgated, will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (Air). Adoption of the Amendment In consideration of the foregoing, the Federal Aviation Administration amends 14 CFR part 71 as follows: I PART 71—DESGINATION OF CLASS A, CLASS B, CLASS C, CLASS D, AND CLASS E AIRSPACE AREAS; AIRWAYS; ROUTES; AND REPORTING POINTS 1. The authority citation for part 71 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40103, 40113, 40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959– 1963 Comp., p. 389. § 71.1 Points, dated September 1, 2006, and effective September 16, 2006, is amended as follows: Paragraph 5000 Class D airspace. * * * ASO FL D * Pompano Beach, FL [REVISED] Pompano Beach, Airpark, FL (Lat. 26°14′50″ N, long. 80°06′40″ W) Fort Lauderdale Executive Airport, FL (Lat. 26°11′50″ N, long. 80°10′15″ W) That airspace extending upward from the surface to and including 2,500 feet MSL within a 4-mile radius of Pompano Beach Airpark; excluding that portion southwest of a line between lat. 26°15′48″ N., long. 80°10′59″ W; and lat. 26°13′05″ N.; long. 80°08′36″ W and that portion south of a line 1 mile north of and parallel to the extended runway centerline of Runway 8/26 at Fort Lauderdale Executive Airport. This Class D airspace area is effective during the specific days and times established in advance by a Notice to Airmen. The effective days and times will thereafter be continuously published in the Airport/Facility Directory. * * * * * * Sfmt 4700 * * Issued in College Park, Georgia on May 31, 2006. Mark D. Ward, Acting Area Director, Air Traffic Division, Southern Region. [FR Doc. 06–5185 Filed 6–6–06; 8:45 am] BILLING CODE 4910–13–M 2. The incorporation by reference in 14 CFR 71.1 of Federal Aviation Administration Order 7400.9N, Airspace Designations and Reporting Fmt 4700 * Fort Lauderdale Executive Airport, FL (Lat. 26°11′50″ N, long. 80°10′15″ W) Fort Lauderdale-Hollywood International Airport, FL (Lat. 26°04′21″ N, long. 80°09′10″ W) That airspace extending upward from the surface to and including 2,500 feet MSL within a 4-mile radius of Fort Lauderdale Executive Airport; excluding that portion within the Fort Lauderdale-Hollywood International Airport, FL, Class C airspace area and that portion northeast of a line between lat. 26°15′48″ N; long. 80°10′59″ W; and lat. 26°13′05″ N; long. 80°08′36″ W and that portion north of a line 1 mile north of and parallel to the extended runway centerline of Runway 8/26 at Fort Lauderdale Executive Airport. This Class D airspace area is effective during the specific days and times established in advance by a Notice to Airmen. The effective days and times will thereafter be continuously published in the Airport/Facility Directory. [Amended] Frm 00020 * ASO FL D Fort Lauderdale Executive Airport, FL [REVISED] I PO 00000 * E:\FR\FM\07JNR1.SGM 07JNR1

Agencies

[Federal Register Volume 71, Number 109 (Wednesday, June 7, 2006)]
[Rules and Regulations]
[Pages 32818-32822]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5125]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24950; Directorate Identifier 2006-NM-036-AD; 
Amendment 39-14627; AD 2006-12-03]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100B, 747-200B, 747-
200F, 747-300, 747-400, 747-400F, and 747SP Series Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain 747-100B, 747-200B, 747-200F, 747-300, 747-400, 747-400F, and 
747SP series airplanes. This AD requires doing inspections of the 
midpivot bolt and midpivot bolt access door of the spring beam of the 
inboard side of the outboard struts for discrepancies, installing a 
placard on the midpivot bolt access door, and applicable corrective 
actions if necessary. This AD results from reports indicating that the 
midpivot bolt and midpivot bolt access door of the spring beam of the 
inboard side of the outboard struts were installed in the incorrect 
position. We are issuing this AD to ensure that the subject midpivot 
bolts and midpivot bolt access doors are installed in the correct 
position. If not installed in the correct position, a midpivot bolt 
could be overloaded and crack or fracture, which could result in the 
loss of the spring load path and consequent separation of the 
associated

[[Page 32819]]

outboard strut and engine from the airplane.

DATES: This AD becomes effective June 22, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of June 22, 
2006.
    We must receive comments on this AD by August 7, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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.
     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.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We have received reports indicating that the midpivot bolt and 
midpivot bolt access door of the spring beam of the inboard side of the 
outboard struts were installed in the incorrect position on two 
airplanes. On one of the airplanes, the midpivot bolts and midpivot 
bolt access doors had been installed during accomplishment of the 
modification of the nacelle strut and wing structure in accordance with 
Boeing Service Bulletin 747-54A2157 (required by AD 95-13-05, amendment 
39-9285 (60 FR 33333, June 28, 1995)). Investigation revealed that the 
service bulletin specified incorrect part numbers for the midpivot bolt 
access doors. In addition, the production installation drawings did not 
provide clear instructions for installing the midpivot bolts and 
midpivot bolt access doors, which resulted in the discrepancies on the 
other airplane.
    The midpivot bolt access door is attached to the skin of the 
inboard side of the outboard struts. A midpivot bolt access door has 
anti-rotation tabs that fit the slots of the midpivot bolt's head. If 
any midpivot bolt access door is not installed correctly or if its 
anti-rotation tabs are not properly aligned with the slots of the 
midpivot bolt's head, the midpivot bolt and its internal lubrication 
channel will not be in correct position. When the lubrication channel 
is not in the correct position, a midpivot bolt could be overloaded and 
crack or fracture. These conditions, if not corrected, could result in 
the loss of a spring beam load path and consequent separation of the 
associated outboard strut and engine from the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-54A2225, dated 
February 16, 2006. The service bulletin describes the inspection 
procedures specified in the table below. The service bulletin also 
describes procedures for installing a placard on the midpivot bolt 
access doors, and doing applicable corrective actions if necessary. The 
applicable corrective actions include changing or replacing any 
midpivot bolt access door that is damaged or installed in the incorrect 
position with a new or serviceable midpivot bolt access door, and under 
certain conditions, replacing the midpivot bolt with a new bolt. The 
service bulletin specifies the following compliance time depending on 
the airplane configuration and accumulated flight cycles:
     ``Within 24 months from the release date on this service 
bulletin or within 90 days from accumulating 8,000 flight cycles from 
the accomplishment of SB 747-54A2157, whichever occurs first;''
     ``Within 24 months from the release on this service 
bulletin or within 90 days from accumulating 8,000 total flight cycles, 
whichever occurs first;'' or
     ``Within 90 days from the release date on this service 
bulletin.''

                               Inspections
------------------------------------------------------------------------
           Doing--                    Of--                  For--
------------------------------------------------------------------------
(1) A general visual          The midpivot bolt     The correct part
 inspection.                   access doors.         number, damage
                                                     (i.e., wear, nicks,
                                                     gouges, elongated
                                                     fastener holes, or
                                                     cracks), or the
                                                     correct position of
                                                     its anti-rotation
                                                     tabs.
(2) A general visual          The anti-rotation     Damage (i.e., wear,
 inspection.                   tabs of the           nicks, gouges, or
                               midpivot bolt         cracks) or any
                               access doors.         missing tab.
(3) A general visual          The midpivot bolts..  Correct position or
 inspection.                                         damage (i.e.,
                                                     nicks, gouges, or
                                                     cracks).
(4) An ultrasonic inspection  The midpivot bolts..  Cracks.
------------------------------------------------------------------------

Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design that may be 
registered in the U.S. at some time in the future. Therefore, we are 
issuing this AD to ensure that the subject midpivot bolts and midpivot 
bolt access doors are installed in the correct position. If not 
installed in the correct position, a midpivot bolt could be overloaded 
and crack or fracture, which could result in the loss of the spring 
load path and consequent separation of the associated outboard strut 
and engine from the airplane. This AD requires accomplishing the 
actions specified in the service information described previously, 
except as described under ``Difference Between the Proposed AD and 
Service Bulletin.''

Difference Between the Proposed Rule and Service Bulletin

    Operators should note that, although the Accomplishment 
Instructions of the referenced service bulletin describe procedures for 
submitting a report of inspection findings to Boeing, this AD will not 
require that action.

[[Page 32820]]

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future.
    If an affected airplane is imported and placed on the U.S. Register 
in the future, the required inspection and installation of a placard 
would take about 6 work hours per airplane, at an average labor rate of 
$80 per work hour. Based on these figures, the estimated cost of the AD 
would be $480 per airplane.

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed under the ADDRESSES section. Include ``Docket No. FAA-
2006-24950; Directorate Identifier 2006-NM-036-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the AD that 
might suggest a need to modify it.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this 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 may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you may visit 
http://dms.dot.gov.

Examining the Docket

    You may 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 Docket Management System 
receives them.

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 the 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 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

    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 
adding the following new airworthiness directive (AD):

2006-12-03 Boeing: Amendment 39-14627. Docket No. FAA-2006-24950; 
Directorate Identifier 2006-NM-036-AD.

Effective Date

    (a) This AD becomes effective June 22, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100B, 747-200B, 747-
200F, 747-300, 747-400, 747-400F, and 747SP series airplanes, 
certificated in any category; as identified in Boeing Alert Service 
Bulletin 747-54A2225, dated February 16, 2006.

Unsafe Condition

    (d) This AD results from reports indicating that the midpivot 
bolt and midpivot bolt access door of the spring beam of the inboard 
side of the outboard struts were installed in the incorrect 
position. We are issuing this AD to ensure that the subject midpivot 
bolts and midpivot bolt access doors are installed in the correct 
position. If not installed in the correct position, a midpivot bolt 
could be overloaded and crack or fracture, which could result in the 
loss of the spring load path and consequent separation of the 
associated outboard strut and engine from 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.

Inspections

    (f) Do the inspections specified in Table 1 of this AD at the 
applicable compliance time listed in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 747-54A2225, dated February 16, 
2006; except, where the service bulletin specifies a compliance time 
from the release date of the service bulletin, this AD requires 
compliance within the specified compliance time after the effective

[[Page 32821]]

date of this AD. Do the inspections in accordance with the 
Accomplishment Instructions of the service bulletin.

                          Table 1.--Inspections
------------------------------------------------------------------------
            Do--                      Of--                  For--
------------------------------------------------------------------------
(1) A general visual          The midpivot bolt     The correct part
 inspection.                   access doors.         number, damage
                                                     (i.e., wear, nicks,
                                                     gouges, elongated
                                                     fastener holes, or
                                                     cracks), or the
                                                     correct position of
                                                     its anti-rotation
                                                     tabs.
(2) A general visual          The anti-rotation     Damage (i.e., wear,
 inspection.                   tabs of the           nicks, gouges, or
                               midpivot bolt         cracks) or any
                               access doors.         missing tab.
(3) A general visual          The midpivot bolts..  Correct position or
 inspection.                                         damage (i.e.,
                                                     nicks, gouges, or
                                                     cracks).
(4) An ultrasonic inspection  The midpivot bolts..  Cracks.
------------------------------------------------------------------------


    Note 1: There is a discrepancy in Step 2 of Figure 13, Sheet 2, 
of Boeing Alert Service Bulletin 747-54A2225, dated February 16, 
2006. The ``MORE DATA'' column of the table incorrectly describes 
the anti-rotation slot installation as being ``horizontal and are 
perpendicular to the strut skin aft edge.'' The correct description 
is ``vertical and are parallel to the strut skin aft edge.''

Installation of a Placard and Corrective Actions

    (g) Before further flight after doing the inspections required 
by paragraph (f) of this AD, do the applicable actions specified in 
Table 2 of this AD in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-54A2225, dated 
February 16, 2006.

       Table 2.--Installation of A Placard and Corrective Actions
------------------------------------------------------------------------
            If--                    And if--               Then--
------------------------------------------------------------------------
(1) Any midpivot bolt access  Its anti-rotation     Install a placard on
 door has the correct part     tabs are present,     the midpivot access
 number and no damage.         are in the correct    door.
                               position, and have
                               no damage.
(2) Any midpivot bolt access  Its anti-rotation     Change the midpivot
 door has the incorrect part   tabs are present,     access door or
 number and no damage.         are in the            replace it with a
                               incorrect position,   new or serviceable
                               and have no damage.   access door, and
                                                     install a placard
                                                     on the midpivot
                                                     access door.
(3) Any midpivot bolt access  None................  Replace the midpivot
 door has the incorrect part                         access door with a
 number, any damage, or any                          new or serviceable
 damaged or missing anti-                            door and install a
 rotation tab.                                       placard on the
                                                     door.
(4) Any midpivot bolt is in   It has no damage....  No further action is
 the correct position.                               required by this
                                                     paragraph.
(5) Any midpivot bolt is in   It has no damage....  Correct the midpivot
 the incorrect position.                             bolt position.
Any midpivot bolt has any     None................  Replace the midpivot
 damage.                                             bolt with a new
                                                     bolt.
------------------------------------------------------------------------

Replacement of Midpivot Bolt

    (h) If any condition in paragraph (h)(1) or (h)(2) of this AD is 
found on any outboard strut, within 24 months after doing the 
inspections required by paragraph (f) of this AD, replace the 
midpivot bolt of the spring beam of the inboard side of that 
outboard strut with a new midpivot bolt, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2225, dated February 16, 2006.
    (1) If any midpivot bolt access door of the spring beam of the 
inboard side of the outboard struts is found in the incorrect 
position (i.e., the midpivot bolt access door has the incorrect part 
number or its anti-rotation tabs are in the incorrect position) and 
if no damage is found on that bolt during any inspection required by 
paragraph (f) of this AD.
    (2) If any midpivot bolt of the spring beam of the inboard side 
of the outboard struts is found in the incorrect position and if no 
damage is found on that bolt during any inspection required by 
paragraph (f) of this AD.

Parts Installation

    (i) As of the effective date of this AD, no person may install, 
on any airplane, a midpivot access door, part number 65B89670-339, 
65B89670-340, 654U6624-356, or 654U6624-357, unless it has been 
inspected in accordance with paragraphs (f)(1) and (f)(2) of this AD 
and found to have the correct part number for the door location, no 
damage, and no damaged or missing anti-rotation tab.

No Reporting

    (j) Although the service bulletin referenced in this AD 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle 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) 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.

Material Incorporated by Reference

    (1) You must use Boeing Alert Service Bulletin 747-54A2225, 
dated February 16, 2006, to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approved the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, WA 
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

[[Page 32822]]

Internet at http://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 http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on May 26, 2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-5125 Filed 6-6-06; 8:45 am]
BILLING CODE 4910-13-P