Airworthiness Directives; Boeing Model 747 Airplanes, 64884-64887 [E6-18465]

Download as PDF 64884 Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Airbus Service Bulletin Revision level Date A330–57–3085 .................................................................................................................................... A330–57–3087 .................................................................................................................................... A330–57–3087 .................................................................................................................................... A330–57–3088, including Appendix 01 .............................................................................................. A340–57–4093 .................................................................................................................................... A340–57–4095 .................................................................................................................................... A340–57–4095 .................................................................................................................................... A340–57–4096, including Appendix 01 .............................................................................................. 02 ............................. Original .................... 01 ............................. Original .................... 02 ............................. Original .................... 01 ............................. Original .................... September 29, 2005. February 15, 2005. September 22, 2005. September 21, 2005. September 29, 2005. February 15, 2005. September 22, 2005. September 21, 2005. Issued in Renton, Washington, on October 25, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–18471 Filed 11–3–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23921; Directorate Identifier 2005–NM–205–AD; Amendment 39–14812; AD 2006–22–15] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 747 series airplanes. That AD currently requires repetitive inspections for cracking of the top and side panel webs and panel stiffeners of the nose wheel well (NWW), and corrective actions if necessary. This new AD reduces the interval for certain repetitive inspections and removes a certain optional inspection. This new AD also requires replacing the NWW side and top panels with new panels, which terminates the repetitive inspections. This AD results from the development of a new modification. We are issuing this AD to prevent fatigue cracks in the top and side panel webs and stiffeners of the NWW, which could compromise the structural integrity of the NWW and could lead to the rapid decompression of the airplane. DATES: This AD becomes effective December 11, 2006. The Director of the Federal Register approved the incorporation by reference cprice-sewell on PROD1PC66 with RULES SUMMARY: VerDate Aug<31>2005 15:39 Nov 03, 2006 Jkt 211001 of a certain publication listed in the AD as of December 11, 2006. On May 10, 2005 (70 FR 21141, April 25, 2005), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2465, Revision 4, dated February 24, 2005. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., 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: Nick Kusz, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6432; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (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 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 2005–09–02, amendment 39–14070 (70 FR 21141, April 25, 2005). [A correction of that AD was published in the Federal Register on May 25, 2005 (70 FR 29940).] The existing AD applies to all Boeing Model 747 series airplanes. That NPRM was published in the Federal Register on February 15, 2006 (71 FR 7883). That NPRM proposed to continue to require repetitive inspections for cracking of the top and PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 side panel webs and panel stiffeners of the nose wheel well (NWW), and corrective actions if necessary. That NPRM also proposed to reduce the interval for certain repetitive inspections and remove a certain optional inspection. That NPRM also proposed to require replacing the NWW side and top panels with new panels, which would terminate the repetitive inspections. 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. Support for the NPRM Boeing, the airplane manufacturer, agrees with the contents of the NPRM. Request To Remove Actions for Group 2 Airplanes or Extend Compliance Time The Air Transport Association (ATA), on behalf of one of its members, Northwest Airlines (NWA), requests that either the proposed requirement for terminating action for Group 2 airplanes be removed from the NPRM or the compliance time for doing the termination action be extended from four years to six years. The ATA notes that there are no service instructions for the terminating action for Group 2 airplanes. The ATA also states that extending the compliance time will allow the development of the service instructions and an assessment of the requirement’s impact. NWA adds that it has not experienced extensive cracking that would warrant serious consideration or justification to mandate the terminating action (replacement of the NWW side and top panels). NWA also states that it would be very difficult to accomplish the replacement without a service bulletin. We agree with the commenter’s concern regarding lack of availability of service instructions for Group 2 airplanes; however, we do not consider that removing the terminating action or delaying this action until after the E:\FR\FM\06NOR1.SGM 06NOR1 Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations manufacturer develops a service bulletin for the replacement of the NWW side and top panels for Group 2 airplanes is warranted. We have coordinated with Boeing regarding the availability of service instructions. Boeing states that it will issue a revised service bulletin that includes procedures for Group 2 airplanes by July 2007 and that there will parts available at that time. Therefore, we have revised the compliance time for Group 2 airplanes to allow adequate time to accomplish the actions specified in this final rule. We have extended the compliance time specified in paragraph (o) of the final rule from 48 months to 57 months. We have determined that extending the compliance time will not adversely affect safety. In addition, under the provisions of paragraph (p) of the final rule, we may approve requests for adjustments to the compliance time if 64885 data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. published May 25, 2005 (70 FR 29940). We have revised this final rule accordingly. Explanation of Change Made to NPRM Conclusion For clarification, the FAA has revised the definition of a ‘‘detailed inspection’’ in Note 1 of this final rule. 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. Typographical Errors The date of Revision 4 of Boeing Alert Service Bulletin 747–53A2465 was inadvertently specified as ‘‘February 25’’ instead of ‘‘February 24’’ in paragraph (f) and Table 1 of the NPRM. We have revised this final rule accordingly. The Federal Register number and date of the existing AD was inadvertently specified as ‘‘70 FR 29940, May 25, 2005’’ in paragraph 2. of the NPRM. The existing AD was published April 25, 2005 (70 FR 21141). A correction of the existing AD was Costs of Compliance There are about 1,127 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. Work hours are estimated at an average labor rate of $65 per work hour. ESTIMATED COSTS Action Work hours Area 1 and 3 inspections (required by AD 2005–09–02). Area 2 inspections (required by AD 2005–09–02). Replacement (new action) ..... cprice-sewell on PROD1PC66 with RULES Number of U.S.-registered airplanes $0 $5,135, per inspection cycle 255 8–18 0 255 800 115,765 $520–$1,170, per inspection cycle. $167,765 ............................... 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 15:39 Nov 03, 2006 Cost per airplane 79 Authority for This Rulemaking VerDate Aug<31>2005 Parts Jkt 211001 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. 255 Fleet cost $1,309,425, per inspection cycle. Up to $298,350, per inspection cycle. $42,780,075. 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 39–14070 (70 FR 21141, April 25, 2005), corrected at 70 FR 29940, May 25, 2005, and by adding the following new airworthiness directive (AD): I 2006–22–15 Boeing: Amendment 39–14812. Docket No. FAA–2006–23921; Directorate Identifier 2005–NM–205–AD. Effective Date List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (a) This AD becomes effective December 11, 2006. Adoption of the Amendment Applicability Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (c) This AD applies to all Boeing Model 747–100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category. I PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Affected ADs (b) This AD supersedes AD 2005–09–02. E:\FR\FM\06NOR1.SGM 06NOR1 64886 Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations Unsafe Condition (d) This AD results from the development of a new modification. We are issuing this AD to prevent fatigue cracks in the top and side panel webs and stiffeners of the nose wheel well (NWW), which could compromise the structural integrity of the NWW and lead to the 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 Requirements of AD 2005– 09–02 With New Repetitive Interval and Service Information Initial and Repetitive Inspections of the Top and Side Panel Stiffeners (f) Prior to the accumulation of 16,000 total flight cycles, or within 1,000 flight cycles after January 27, 2005 (the effective date of AD 2004–25–23, amendment 39–13911), whichever is later, do internal detailed and surface high frequency eddy current (HFEC) inspections of the top and side panel stiffeners of the NWW (specified as Area 3 in the service bulletin) for cracks in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin (ASB) 747– 53A2465, Revision 4, dated February 24, 2005. Repeat the inspections thereafter at the compliance times specified in paragraph (f)(1) or (f)(2) of this AD, as applicable. (1) For airplanes on which an inspection has not been done before the effective date of this AD in accordance with any service bulletin listed in Table 1 of this AD: Within 1,500 flight cycles after doing the inspection specified in paragraph (f) of this AD, repeat the inspection. Repeat the inspection thereafter at intervals not to exceed 1,500 flight cycles. (2) For airplanes on which an inspection has been done before the effective date of this AD in accordance with any service bulletin listed in Table 1 of this AD: Within 6,000 flight cycles after doing the inspection specified in paragraph (f) of this AD or within 1,500 flight cycles after the effective date of this AD, whichever occurs first, repeat the inspection. Repeat the inspection thereafter at intervals not to exceed 1,500 flight cycles. TABLE 1.—BOEING SERVICE BULLETINS Service bulletin Boeing Boeing Boeing Boeing Boeing ASB 747–53A2465 ................................................................................................................. ASB 747–53A2465 ................................................................................................................. ASB 747–53A2465 ................................................................................................................. ASB 747–53A2465 ................................................................................................................. Service Bulletin 747–53A2465 ................................................................................................ Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Initial Inspections of the Top and Sidewall Panel Webs (g) Do an external detailed inspection of the top and sidewall panel webs of the NWW (specified as Area 1 and Area 2 in the service bulletin) for cracks, in accordance with the Accomplishment Instructions of Boeing ASB 747–53A2465, Revision 4, dated February 24, 2005, at the earlier of the times specified in paragraphs (g)(1) and (g)(2) of this AD. (1) At the later of the times specified in paragraph (g)(1)(i) and (g)(1)(ii) of this AD: (i) Before accumulating 20,000 total flight cycles. (ii) Within 100 flight cycles or 90 days after May 10, 2005 (the effective date of AD 2005– 09–02), whichever occurs first. (2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: (i) Before accumulating 16,000 total flight cycles. (ii) Within 1,000 flight cycles after May 10, 2005. cprice-sewell on PROD1PC66 with RULES Revision level Repetitive Inspections of the Top and Sidewall Panel Webs (h) Repeat the inspection required by paragraph (g) of this AD at the intervals specified in paragraphs (h)(1) and (h)(2) of this AD, as applicable. VerDate Aug<31>2005 15:39 Nov 03, 2006 Jkt 211001 (1) For airplanes with fewer than 20,000 total flight cycles as of May 10, 2005, repeat at intervals not to exceed 1,000 flight cycles until the first inspection after the airplane reaches 20,000 total flight cycles. (2) For airplanes with 20,000 total flight cycles or more, repeat at intervals not to exceed 500 flight cycles. Ultrasonic (UT) Inspections (i) Do an UT inspection of the top and sidewall panel webs for cracks, in accordance with Boeing ASB 747–53A2465, Revision 4, dated February 24, 2005, at the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD. Repeat the inspections thereafter at intervals not to exceed 500 flight cycles. (1) Prior to the accumulation of 20,000 total flight cycles. (2) Within 100 flight cycles or 90 days after May 10, 2005, whichever occurs first. Additional Inspections and Corrective Actions (j) Except as specified in paragraph (l) of this AD, if any crack is found during any inspection required by this AD, prior to further flight, do any applicable additional detailed inspections of stiffeners and beams and make repairs, in accordance with the Accomplishment Instructions of Boeing ASB 747–53A2465, Revision 4, dated February 24, 2005. Actions Accomplished per Previous Issues of Service Bulletin (k) The actions specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD are acceptable for compliance with the corresponding action specified in the applicable paragraph. (1) Inspections and corrective actions accomplished before January 27, 2005, in PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Date Original .................... 2 ............................... 3 ............................... 4 ............................... 1 ............................... April 5, 2001. November 11, 2004. December 23, 2004. February 24, 2005. October 16, 2003. accordance with Boeing ASB 747–53A2465, dated April 5, 2001, are considered acceptable for compliance with the corresponding inspections specified in paragraph (f) of this AD. (2) Inspections accomplished before the effective date of this AD, in accordance with Boeing Service Bulletin 747–53A2465, Revision 1, dated October 16, 2003; Boeing ASB 747–53A2465, Revision 2, dated November 11, 2004; and Boeing ASB 747– 53A2465, Revision 3, dated December 23, 2004; are considered acceptable for compliance with the corresponding inspections specified in paragraph (f) of this AD. Note 2: The detailed and surface HFEC inspections of the top and side panel stiffeners of the NWW specified in Boeing ASB 747–53A2465, dated April 5, 2001; and Boeing Service Bulletin 747–53A2465, Revision 1, dated October 16, 2003; are acceptable for compliance with the internal detailed and surface HFEC inspections specified in paragraph (f) of this AD. (3) Inspections and corrective actions accomplished before May 10, 2005, in accordance with Boeing Service Bulletin 747–53A2465, Revision 1, dated October 16, 2003; Boeing ASB 747–53A2465, Revision 2, dated November 11, 2004; and Boeing ASB 747–53A2465, Revision 3, dated December 23, 2004; are considered acceptable for compliance with the corresponding inspections specified in paragraphs (g) and (h) of this AD. Certain Other Corrective Actions (l) Where Boeing Service Bulletin and ASB 747–53A2465 specify contacting the manufacturer if certain cracking is found, this AD requires, before further flight, E:\FR\FM\06NOR1.SGM 06NOR1 Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations repairing the cracking using a method approved in accordance with the procedures specified in paragraph (p) of this AD. No Reporting Requirement (m) Although Boeing Service Bulletin and ASB 747–53A2465 specify that operators should report inspection results to the manufacturer, this AD does not require those inspection results to be reported. New Requirements of This AD Terminating Action (n) For Group 1 and 3 airplanes identified in Boeing Service Bulletin 747–53A2562, Revision 1, dated July 28, 2005: Before accumulating 22,000 total flight cycles or within 48 months after the effective date of this AD, whichever occurs later, replace the NWW side and top panels with new panels in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2562, Revision 1, dated July 28, 2005. Doing the replacement terminates the requirements of this AD. (o) For Group 2 airplanes identified in Boeing Service Bulletin 747–53A2562, Revision 1, dated July 28, 2005, and Model 747 airplanes not identified in the service bulletin: Before accumulating 22,000 total flight cycles or within 57 months after the effective date of this AD, whichever occurs later, replace the NWW side and top panels using a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Doing the replacement terminates the requirements of this AD. cprice-sewell on PROD1PC66 with RULES Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, Seattle 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 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. (4) AMOCs approved previously according to AD 2005–09–02 are approved as AMOCs for the corresponding provisions of paragraphs (f) through (j) and (l) of this AD. (5) AMOCs approved previously according to AD 2004–25–23 are approved as AMOCs for the corresponding provisions of paragraph (f) of this AD. Material Incorporated by Reference (q) You must use Boeing Alert Service Bulletin 747–53A2465, Revision 4, dated February 24, 2005; and Boeing Service Bulletin 747–53A2562, Revision 1, dated July 28, 2005; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. VerDate Aug<31>2005 15:39 Nov 03, 2006 Jkt 211001 (1) The Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 747–53A2562, Revision 1, dated July 28, 2005, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On May 10, 2005 (70 FR 21141, April 25, 2005), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2465, Revision 4, dated February 24, 2005. (3) 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 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 October 25, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–18465 Filed 11–3–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–25501; Airspace Docket No. 06–ACE–9] Establishment of Class D Airspace; Ft. Riley, KS Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: This notice amends Part 71 of the Federal Aviation Regulations (14 CFR part 71) by establishing a Class D airspace area extending upward from the surface to and including 3,600 feet above sea level within a 3.7-mile radius of Fort Riley, Marshall Army Airfield, KS. The establishment of an air traffic control tower has made this action necessary. Effective Date: 0901 UTC, November 23, 2006. DATES: FOR FURTHER INFORMATION CONTACT: Grant Nichols, System Support, DOT Regional Headquarters Building, Federal Aviation Administration, 901 Locust, Kansas, City, MO 64106; telephone: (816) 329–2522. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 64887 History On Friday, August 11, 2006, the FAA proposed to amend Part 71 of the Federal Aviation Regulations (14 CFR part 71) to establish Class D airspace at Ft. Riley, KS (71 FR 46130). The proposal was to establish a Class D airspace area to provide controlled airspace for flight operations due to the establishment of an air traffic control tower. Interested parties were invited to participate in this rulemaking proceeding by submitting written comments on the proposal to the FAA. A comment was received regarding the size of Class D airspace area. The size of the Class D airspace area is determined by FAA Order 7400.2F Procedures for Handling Airspace Matters, Chapter 17, Section 2. Class D Airspace Standards. The Rule This notice amends Part 71 of the Federal Aviation Regulations (14 CFR part 71) by establishing a Class D airspace area extending upward from the surface to and including 3,600 feet above sea level within a 3.7-mile radius of Fort Riley, Marshall Army Airfield, KS. The establishment of an air traffic control tower has made this action necessary. The intended effect of this action is to provide controlled airspace for flight operations at Fort Riley, Marshall Army Airfield, KS. The are will be depicted on appropriate aeronautical charts. Class D airspace areas extending upward from the surface of the earth are published in Paragraph 5000 of FAA Order 7400.9P, Airspace Designations and Reporting Points, dated September 1, 2006, and effective September 16, 2006, which is incorporated by reference in 14 CFR 71.1. of the same Order. The Class D airspace designation listed in this document will be published subsequently in the Order. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this regulation—(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 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 E:\FR\FM\06NOR1.SGM 06NOR1

Agencies

[Federal Register Volume 71, Number 214 (Monday, November 6, 2006)]
[Rules and Regulations]
[Pages 64884-64887]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-18465]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23921; Directorate Identifier 2005-NM-205-AD; 
Amendment 39-14812; AD 2006-22-15]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 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 all Boeing Model 747 series airplanes. That AD 
currently requires repetitive inspections for cracking of the top and 
side panel webs and panel stiffeners of the nose wheel well (NWW), and 
corrective actions if necessary. This new AD reduces the interval for 
certain repetitive inspections and removes a certain optional 
inspection. This new AD also requires replacing the NWW side and top 
panels with new panels, which terminates the repetitive inspections. 
This AD results from the development of a new modification. We are 
issuing this AD to prevent fatigue cracks in the top and side panel 
webs and stiffeners of the NWW, which could compromise the structural 
integrity of the NWW and could lead to the rapid decompression of the 
airplane.

DATES: This AD becomes effective December 11, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 11, 
2006.
    On May 10, 2005 (70 FR 21141, April 25, 2005), the Director of the 
Federal Register approved the incorporation by reference of Boeing 
Alert Service Bulletin 747-53A2465, Revision 4, dated February 24, 
2005.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., 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: Nick Kusz, Airframe Branch, ANM-120S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6432; fax (425) 917-
6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (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 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 2005-09-02, amendment 
39-14070 (70 FR 21141, April 25, 2005). [A correction of that AD was 
published in the Federal Register on May 25, 2005 (70 FR 29940).] The 
existing AD applies to all Boeing Model 747 series airplanes. That NPRM 
was published in the Federal Register on February 15, 2006 (71 FR 
7883). That NPRM proposed to continue to require repetitive inspections 
for cracking of the top and side panel webs and panel stiffeners of the 
nose wheel well (NWW), and corrective actions if necessary. That NPRM 
also proposed to reduce the interval for certain repetitive inspections 
and remove a certain optional inspection. That NPRM also proposed to 
require replacing the NWW side and top panels with new panels, which 
would terminate the repetitive inspections.

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.

Support for the NPRM

    Boeing, the airplane manufacturer, agrees with the contents of the 
NPRM.

Request To Remove Actions for Group 2 Airplanes or Extend Compliance 
Time

    The Air Transport Association (ATA), on behalf of one of its 
members, Northwest Airlines (NWA), requests that either the proposed 
requirement for terminating action for Group 2 airplanes be removed 
from the NPRM or the compliance time for doing the termination action 
be extended from four years to six years. The ATA notes that there are 
no service instructions for the terminating action for Group 2 
airplanes. The ATA also states that extending the compliance time will 
allow the development of the service instructions and an assessment of 
the requirement's impact. NWA adds that it has not experienced 
extensive cracking that would warrant serious consideration or 
justification to mandate the terminating action (replacement of the NWW 
side and top panels). NWA also states that it would be very difficult 
to accomplish the replacement without a service bulletin.
    We agree with the commenter's concern regarding lack of 
availability of service instructions for Group 2 airplanes; however, we 
do not consider that removing the terminating action or delaying this 
action until after the

[[Page 64885]]

manufacturer develops a service bulletin for the replacement of the NWW 
side and top panels for Group 2 airplanes is warranted.
    We have coordinated with Boeing regarding the availability of 
service instructions. Boeing states that it will issue a revised 
service bulletin that includes procedures for Group 2 airplanes by July 
2007 and that there will parts available at that time. Therefore, we 
have revised the compliance time for Group 2 airplanes to allow 
adequate time to accomplish the actions specified in this final rule.
    We have extended the compliance time specified in paragraph (o) of 
the final rule from 48 months to 57 months. We have determined that 
extending the compliance time will not adversely affect safety. In 
addition, under the provisions of paragraph (p) of the final rule, we 
may approve requests for adjustments to the compliance time if data are 
submitted to substantiate that such an adjustment would provide an 
acceptable level of safety.

Explanation of Change Made to NPRM

    For clarification, the FAA has revised the definition of a 
``detailed inspection'' in Note 1 of this final rule.

Typographical Errors

    The date of Revision 4 of Boeing Alert Service Bulletin 747-53A2465 
was inadvertently specified as ``February 25'' instead of ``February 
24'' in paragraph (f) and Table 1 of the NPRM. We have revised this 
final rule accordingly.
    The Federal Register number and date of the existing AD was 
inadvertently specified as ``70 FR 29940, May 25, 2005'' in paragraph 
2. of the NPRM. The existing AD was published April 25, 2005 (70 FR 
21141). A correction of the existing AD was published May 25, 2005 (70 
FR 29940). We have revised this final rule accordingly.

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 1,127 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD. Work hours are estimated at an 
average labor rate of $65 per work hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
            Action               Work hours         Parts          Cost per        registered       Fleet cost
                                                                   airplane         airplanes
----------------------------------------------------------------------------------------------------------------
Area 1 and 3 inspections                   79              $0  $5,135, per                  255  $1,309,425, per
 (required by AD 2005-09-02).                                   inspection                        inspection
                                                                cycle.                            cycle.
Area 2 inspections (required             8-18               0  $520-$1,170, per             255  Up to $298,350,
 by AD 2005-09-02).                                             inspection                        per inspection
                                                                cycle.                            cycle.
Replacement (new action).....             800         115,765  $167,765........             255  $42,780,075.
----------------------------------------------------------------------------------------------------------------

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 39-14070 (70 FR 21141, April 25, 2005), corrected at 
70 FR 29940, May 25, 2005, and by adding the following new 
airworthiness directive (AD):

2006-22-15 Boeing: Amendment 39-14812. Docket No. FAA-2006-23921; 
Directorate Identifier 2005-NM-205-AD.

Effective Date

    (a) This AD becomes effective December 11, 2006.

Affected ADs

    (b) This AD supersedes AD 2005-09-02.

Applicability

    (c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP series airplanes, certificated in any 
category.

[[Page 64886]]

Unsafe Condition

    (d) This AD results from the development of a new modification. 
We are issuing this AD to prevent fatigue cracks in the top and side 
panel webs and stiffeners of the nose wheel well (NWW), which could 
compromise the structural integrity of the NWW and lead to the 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 Requirements of AD 2005-09-02 With New Repetitive 
Interval and Service Information

Initial and Repetitive Inspections of the Top and Side Panel 
Stiffeners

    (f) Prior to the accumulation of 16,000 total flight cycles, or 
within 1,000 flight cycles after January 27, 2005 (the effective 
date of AD 2004-25-23, amendment 39-13911), whichever is later, do 
internal detailed and surface high frequency eddy current (HFEC) 
inspections of the top and side panel stiffeners of the NWW 
(specified as Area 3 in the service bulletin) for cracks in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin (ASB) 747-53A2465, Revision 4, dated February 24, 
2005. Repeat the inspections thereafter at the compliance times 
specified in paragraph (f)(1) or (f)(2) of this AD, as applicable.
    (1) For airplanes on which an inspection has not been done 
before the effective date of this AD in accordance with any service 
bulletin listed in Table 1 of this AD: Within 1,500 flight cycles 
after doing the inspection specified in paragraph (f) of this AD, 
repeat the inspection. Repeat the inspection thereafter at intervals 
not to exceed 1,500 flight cycles.
    (2) For airplanes on which an inspection has been done before 
the effective date of this AD in accordance with any service 
bulletin listed in Table 1 of this AD: Within 6,000 flight cycles 
after doing the inspection specified in paragraph (f) of this AD or 
within 1,500 flight cycles after the effective date of this AD, 
whichever occurs first, repeat the inspection. Repeat the inspection 
thereafter at intervals not to exceed 1,500 flight cycles.

                                       Table 1.--Boeing Service Bulletins
----------------------------------------------------------------------------------------------------------------
           Service bulletin                        Revision level                            Date
----------------------------------------------------------------------------------------------------------------
Boeing ASB 747-53A2465................  Original...........................  April 5, 2001.
Boeing ASB 747-53A2465................  2..................................  November 11, 2004.
Boeing ASB 747-53A2465................  3..................................  December 23, 2004.
Boeing ASB 747-53A2465................  4..................................  February 24, 2005.
Boeing Service Bulletin 747-53A2465...  1..................................  October 16, 2003.
----------------------------------------------------------------------------------------------------------------


    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Initial Inspections of the Top and Sidewall Panel Webs

    (g) Do an external detailed inspection of the top and sidewall 
panel webs of the NWW (specified as Area 1 and Area 2 in the service 
bulletin) for cracks, in accordance with the Accomplishment 
Instructions of Boeing ASB 747-53A2465, Revision 4, dated February 
24, 2005, at the earlier of the times specified in paragraphs (g)(1) 
and (g)(2) of this AD.
    (1) At the later of the times specified in paragraph (g)(1)(i) 
and (g)(1)(ii) of this AD:
    (i) Before accumulating 20,000 total flight cycles.
    (ii) Within 100 flight cycles or 90 days after May 10, 2005 (the 
effective date of AD 2005-09-02), whichever occurs first.
    (2) At the later of the times specified in paragraphs (g)(2)(i) 
and (g)(2)(ii) of this AD:
    (i) Before accumulating 16,000 total flight cycles.
    (ii) Within 1,000 flight cycles after May 10, 2005.

Repetitive Inspections of the Top and Sidewall Panel Webs

    (h) Repeat the inspection required by paragraph (g) of this AD 
at the intervals specified in paragraphs (h)(1) and (h)(2) of this 
AD, as applicable.
    (1) For airplanes with fewer than 20,000 total flight cycles as 
of May 10, 2005, repeat at intervals not to exceed 1,000 flight 
cycles until the first inspection after the airplane reaches 20,000 
total flight cycles.
    (2) For airplanes with 20,000 total flight cycles or more, 
repeat at intervals not to exceed 500 flight cycles.

Ultrasonic (UT) Inspections

    (i) Do an UT inspection of the top and sidewall panel webs for 
cracks, in accordance with Boeing ASB 747-53A2465, Revision 4, dated 
February 24, 2005, at the later of the times specified in paragraphs 
(i)(1) and (i)(2) of this AD. Repeat the inspections thereafter at 
intervals not to exceed 500 flight cycles.
    (1) Prior to the accumulation of 20,000 total flight cycles.
    (2) Within 100 flight cycles or 90 days after May 10, 2005, 
whichever occurs first.

Additional Inspections and Corrective Actions

    (j) Except as specified in paragraph (l) of this AD, if any 
crack is found during any inspection required by this AD, prior to 
further flight, do any applicable additional detailed inspections of 
stiffeners and beams and make repairs, in accordance with the 
Accomplishment Instructions of Boeing ASB 747-53A2465, Revision 4, 
dated February 24, 2005.

Actions Accomplished per Previous Issues of Service Bulletin

    (k) The actions specified in paragraphs (k)(1), (k)(2), and 
(k)(3) of this AD are acceptable for compliance with the 
corresponding action specified in the applicable paragraph.
    (1) Inspections and corrective actions accomplished before 
January 27, 2005, in accordance with Boeing ASB 747-53A2465, dated 
April 5, 2001, are considered acceptable for compliance with the 
corresponding inspections specified in paragraph (f) of this AD.
    (2) Inspections accomplished before the effective date of this 
AD, in accordance with Boeing Service Bulletin 747-53A2465, Revision 
1, dated October 16, 2003; Boeing ASB 747-53A2465, Revision 2, dated 
November 11, 2004; and Boeing ASB 747-53A2465, Revision 3, dated 
December 23, 2004; are considered acceptable for compliance with the 
corresponding inspections specified in paragraph (f) of this AD.

    Note 2: The detailed and surface HFEC inspections of the top and 
side panel stiffeners of the NWW specified in Boeing ASB 747-
53A2465, dated April 5, 2001; and Boeing Service Bulletin 747-
53A2465, Revision 1, dated October 16, 2003; are acceptable for 
compliance with the internal detailed and surface HFEC inspections 
specified in paragraph (f) of this AD.

    (3) Inspections and corrective actions accomplished before May 
10, 2005, in accordance with Boeing Service Bulletin 747-53A2465, 
Revision 1, dated October 16, 2003; Boeing ASB 747-53A2465, Revision 
2, dated November 11, 2004; and Boeing ASB 747-53A2465, Revision 3, 
dated December 23, 2004; are considered acceptable for compliance 
with the corresponding inspections specified in paragraphs (g) and 
(h) of this AD.

Certain Other Corrective Actions

    (l) Where Boeing Service Bulletin and ASB 747-53A2465 specify 
contacting the manufacturer if certain cracking is found, this AD 
requires, before further flight,

[[Page 64887]]

repairing the cracking using a method approved in accordance with 
the procedures specified in paragraph (p) of this AD.

No Reporting Requirement

    (m) Although Boeing Service Bulletin and ASB 747-53A2465 specify 
that operators should report inspection results to the manufacturer, 
this AD does not require those inspection results to be reported.

New Requirements of This AD

Terminating Action

    (n) For Group 1 and 3 airplanes identified in Boeing Service 
Bulletin 747-53A2562, Revision 1, dated July 28, 2005: Before 
accumulating 22,000 total flight cycles or within 48 months after 
the effective date of this AD, whichever occurs later, replace the 
NWW side and top panels with new panels in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2562, 
Revision 1, dated July 28, 2005. Doing the replacement terminates 
the requirements of this AD.
    (o) For Group 2 airplanes identified in Boeing Service Bulletin 
747-53A2562, Revision 1, dated July 28, 2005, and Model 747 
airplanes not identified in the service bulletin: Before 
accumulating 22,000 total flight cycles or within 57 months after 
the effective date of this AD, whichever occurs later, replace the 
NWW side and top panels using a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA. Doing the 
replacement terminates the requirements of this AD.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle 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.
    (4) AMOCs approved previously according to AD 2005-09-02 are 
approved as AMOCs for the corresponding provisions of paragraphs (f) 
through (j) and (l) of this AD.
    (5) AMOCs approved previously according to AD 2004-25-23 are 
approved as AMOCs for the corresponding provisions of paragraph (f) 
of this AD.

Material Incorporated by Reference

    (q) You must use Boeing Alert Service Bulletin 747-53A2465, 
Revision 4, dated February 24, 2005; and Boeing Service Bulletin 
747-53A2562, Revision 1, dated July 28, 2005; as applicable, to 
perform the actions that are required by this AD, unless the AD 
specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Boeing Service Bulletin 747-53A2562, 
Revision 1, dated July 28, 2005, in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) On May 10, 2005 (70 FR 21141, April 25, 2005), the Director 
of the Federal Register approved the incorporation by reference of 
Boeing Alert Service Bulletin 747-53A2465, Revision 4, dated 
February 24, 2005.
    (3) 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 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 October 25, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-18465 Filed 11-3-06; 8:45 am]
BILLING CODE 4910-13-P