Airworthiness Directives; 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, 8719-8722 [E9-3272]

Download as PDF Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations 2009–04–12 Boeing: Amendment 39–15818. Docket No. FAA–2008–0150; Directorate Identifier 2007–NM–325–AD. Effective Date (a) This AD becomes effective April 2, 2009. Affected ADs (b) This AD supersedes AD 2001–26–19. Applicability (c) This AD applies to Boeing Model 767– 200, –300, and –400ER series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 767–25–0428, dated August 23, 2007. Unsafe Condition (d) This AD results from reports that entry and service doors did not open fully during deployment of emergency escape slides, and additional reports of missing snap rings. We are issuing this AD to prevent failure of an entry or service door to open fully in the event of an emergency evacuation, which could impede exit from the airplane. This condition could result in injury to passengers or crewmembers. 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. Replacement (f) Within 48 months after the effective date of this AD, replace the separation link assembly on the deployment bar of the emergency escape system on all the applicable entry and service doors with an improved separation link assembly, and do all the applicable related investigative and corrective actions before further flight, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–25–0428, dated August 23, 2007; or Revision 1, dated May 8, 2008. After the effective date of this AD only Boeing Special Attention Service Bulletin 767–25–0428, Revision 1, may be used. Material Incorporated by Reference (h) You must use Boeing Special Attention Service Bulletin 767–25–0428, dated August 23, 2007; or Boeing Special Attention Service Bulletin 767–25–0428, Revision 1, dated May 8, 2008; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207; telephone 206– 544–9990; fax 206–766–5682; e-mail DDCS@boeing.com; Internet https:// www.myboeingfleet.com. (3) You may review copies of the service information that is incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on January 22, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3263 Filed 2–25–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0731; Directorate Identifier 2008–NM–058–AD; Amendment 39–15812; AD 2009–04–06] Alternative Methods of Compliance (AMOCs) RIN 2120–AA64 (g)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Keith Ladderud, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6435; fax (425) 917–6590; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Airworthiness Directives; 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 VerDate Nov<24>2008 14:57 Feb 25, 2009 Jkt 217001 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 detailed inspections of the aft pressure bulkhead for PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 8719 indications of ‘‘oil cans’’ and previous oil can repairs, and corrective actions if necessary. An oil can is an area on a pressure dome web that moves when pushed from the forward side. This new AD requires a reduced compliance time for the initial detailed inspection and revises the applicability. This AD results from a report that cracks in oilcanned areas were found during an inspection of the aft pressure bulkhead. We are issuing this AD to detect and correct the propagation of fatigue cracks in the vicinity of oil cans on the web of the aft pressure bulkhead, which could result in rapid decompression of the airplane and overpressurization of the tail section, and consequent loss of control of the airplane. DATES: This AD becomes effective April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 2, 2009. On September 13, 2004 (69 FR 48133, August 9, 2004), the Director of the Federal Register approved the incorporation by reference of a certain other publication. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: E:\FR\FM\26FER1.SGM 26FER1 8720 Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2004–16–09, amendment 39–13765 (69 FR 48133, August 9, 2004). The existing AD applies to all Boeing Model 747 series airplanes. That NPRM was published in the Federal Register on July 2, 2008 (73 FR 37900). That NPRM proposed to require a reduced initial threshold for repetitive detailed inspections of the aft pressure bulkhead for indications of ‘‘oil cans’’ and previous oil can repairs, and corrective actions if necessary. 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. Two commenters, the Air Line Pilots Association, International (ALPA), and Northwest Airlines, support the NPRM. Request to Remove Certain Airplanes From Applicability Section Boeing requests that we remove Model 747–400 airplanes with the following variable numbers from paragraph (c) of this proposed AD: RT631, RT632, RT743, and RT876. Those airplanes have been or are being converted to a 747–400 LCF (large cargo freighter) configuration. The aft pressure bulkhead is removed from these airplanes; therefore, the proposed AD would not apply to those airplanes. We agree that airplanes that have been converted to a Model 747–400 LCF configuration no longer have an aft pressure bulkhead to inspect. We have revised the applicability section of this AD to exclude airplanes that have been converted. We have not excluded specific variable numbers as suggested by Boeing since more airplanes might be converted to the Model 747–400 LCF configuration in the future. Explanation of Change to Paragraph (f) of This AD We have removed the ‘‘Service Bulletin Reference’’ paragraph from this AD. (That paragraph was identified as paragraph (f) in the NPRM.) Instead, we have spelled out the service bulletin citations throughout this AD. We also re-identified the subsequent paragraphs. 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 VerDate Nov<24>2008 14:57 Feb 25, 2009 Jkt 217001 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 917 airplanes of the affected design in the worldwide fleet. This AD affects about 165 airplanes of U.S. registry. The actions that are required by AD 2004–16–09 and retained in this AD take about 2 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the currently required actions to the U.S. operators is $26,400, or $160 per airplane, per inspection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this 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 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ 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 removing amendment 39–13765 (69 FR 48133, August 9, 2004) and by adding the following new airworthiness directive (AD): ■ 2009–04–06 Boeing: Amendment 39–15812. Docket No. FAA–2008–0731; Directorate Identifier 2008–NM–058–AD. Effective Date (a) This AD becomes effective April 2, 2009. Affected ADs (b) This AD supersedes AD 2004–16–09. Applicability (c) This AD applies to 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, except those that have been converted to a Model 747–400 LCF configuration. Unsafe Condition (d) This AD results from a report that cracks in oil-canned areas were found during an inspection of the aft pressure bulkhead. We are issuing this AD to detect and correct the propagation of fatigue cracks in the vicinity of oil cans on the web of the aft pressure bulkhead, which could result in rapid decompression of the airplane and overpressurization of the tail section, and consequent loss of control 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. Note 1: This AD refers to certain portions of Boeing Alert Service Bulletin 747– 53A2482, dated October 3, 2002; and Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008; for inspections and repair information. In addition, this AD specifies requirements E:\FR\FM\26FER1.SGM 26FER1 Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations beyond those included in Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; and Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008. Where the AD and Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; and Boeing Alert Service Bulletin 747– 53A2482, Revision 1, dated February 21, 2008; differ, the AD prevails. Requirements of AD 2004–16–09, With Reduced Threshold Initial and Repetitive Inspections (f) At the earlier of the times specified in paragraphs (f)(1) and (f)(2) of this AD, perform a detailed inspection of the aft pressure bulkhead for indications of oil cans and previous oil can repairs, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008. After the effective date of this AD, Revision 1 must be used. (1) Prior to the accumulation of 30,000 total flight cycles, or within 1,000 flight cycles after September 13, 2004 (the effective date of AD 2004–16–09), whichever is later. (2) Prior to the accumulation of 20,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. Note 2: 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 mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.’’ (g) If no indication of an oil can is found and no indication of a previous oil can repair is found during the detailed inspection required by paragraph (f) of this AD, repeat the detailed inspection thereafter at intervals not to exceed 2,000 flight cycles. Indication of Oil Can (h) If any indication of an oil can is found during the detailed inspection required by paragraph (f) or (g) of this AD, before further flight, perform an eddy current inspection of the web around the periphery of the oil can indication for cracks, as shown in Figure 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008. After the effective date of this AD, Revision 1 must be used. (i) If no crack is found during the eddy current inspection required by paragraph (i) of this AD, do the actions specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. (1) For the oil can that meets the allowable limits specified in Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747– 53A2482, Revision 1, dated February 21, 2008: Repeat the eddy current inspection specified in paragraph (h) of this AD VerDate Nov<24>2008 14:57 Feb 25, 2009 Jkt 217001 thereafter at intervals not to exceed 1,000 flight cycles. As an option, repair the oil can in accordance with paragraph (i)(2) of this AD. (2) For the oil can that does not meet the allowable limits specified in Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008: Before further flight, repair the oil can in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008. After the effective date of this AD, Revision 1 must be used. If the repair eliminates the oil can, accomplishment of this repair constitutes terminating action for the repetitive eddy current inspection requirements of paragraph (i)(1) of this AD for that location only. However, the repetitive detailed inspection required by paragraph (g) of this AD is still required. If any oil can remains after the repair, repeat the eddy current inspection specified in paragraph (h) of this AD thereafter at intervals not to exceed 1,000 flight cycles. Indication of Previous Oil Can Repairs (j) If any previous oil can repair is found during the detailed inspection required by paragraph (f) or (g) of this AD, before further flight, do a detailed inspection of the web for cracks and oil cans, as shown in Figure 4 or Figure 5, as applicable, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008. After the effective date of this AD, Revision 1 must be used. (1) If no crack and no oil can are found, repeat the detailed inspection in accordance with paragraph (f) of this AD. (2) If any oil can is found, before further flight, do the eddy current inspection for cracks, as shown in Figure 3 of Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008. After the effective date of this AD, Revision 1 must be used. If no crack is found during the eddy current inspection required by this paragraph, do the actions specified in paragraph (i)(1) or (i)(2) of this AD, as applicable, at the time specified in the applicable paragraph. Repair of Cracks (k) If any crack is found during any inspection required by this AD, before further flight, repair in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008. After the effective date of this AD, Revision 1 must be used. If any crack or damage exceeds limits specified in Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008; and Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747– PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 8721 53A2482, Revision 1, dated February 21, 2008; specifies to contact Boeing for appropriate action: Before further flight, repair per a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or per data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Seattle ACO, to make such findings; or using a method approved in accordance with the procedures specified in paragraph (m) of this AD. For a repair method to be approved, the approval must specifically reference this AD. New Requirements of This AD (l) As of the effective date of this AD, if any crack or damage is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2482, Revision 1, dated February 21, 2008, specifies to contact Boeing for appropriate action (repair data): Before further flight, repair the crack or damage using a method approved in accordance with the procedures specified in paragraph (m) of this AD. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 917–6437; fax (425) 917–6590, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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 in accordance with AD 2004–16–09 are not approved as AMOCs for the corresponding provisions of paragraph (f) of this AD. They are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), (i), (j), (k), and (l) of this AD. Material Incorporated by Reference (n) You must use Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 747– 53A2482, Revision 1, dated February 21, 2008; 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 Alert Service Bulletin 747–53A2482, E:\FR\FM\26FER1.SGM 26FER1 8722 Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations Revision 1, dated February 21, 2008, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On September 13, 2004 (69 FR 48133, August 9, 2004), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2482, dated October 3, 2002. (3) Contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com; for a copy of this service information. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_oflowbar;federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on January 29, 2009. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3272 Filed 2–25–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1119; Directorate Identifier 2008–NM–112–AD; Amendment 39–15800; AD 2009–02–10] RIN 2120–AA64 Airworthiness Directives; Fokker F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Several reports have been received about roll control problems due to frozen moisture on the aileron pulleys that are located in the VerDate Nov<24>2008 14:57 Feb 25, 2009 Jkt 217001 LH [left-hand] and RH [right-hand] Main Landing Gear (MLG) wheel bays on the centre wing rear spar, under the wing to fuselage fairings. Investigation revealed that improper sealing of the aerodynamic seals of the Wing-to-Fuselage Fairings can cause rainor washwater and de-icing fluids to leak onto the affected aileron pulleys. Exposure of the aileron pulleys to the leaked moisture in freezing condition can result in restricted aileron control movement (partly jammed) and/or higher control forces. This condition, if not corrected, could lead to partial loss of control of the aircraft. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of April 3, 2008 (73 FR 10650, February 28, 2008). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on October 30, 2008 (73 FR 64571) and proposed to supersede AD 2008–04–22, Amendment 39–15394 (73 FR 10650, February 28, 2008). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Several reports have been received about roll control problems due to frozen moisture on the aileron pulleys that are located in the LH [left-hand] and RH [right-hand] Main Landing Gear (MLG) wheel bays on the centre wing rear spar, under the wing to fuselage fairings. Investigation revealed that improper sealing of the aerodynamic seals of the Wing-to-Fuselage Fairings can cause rainor washwater and de-icing fluids to leak onto the affected aileron pulleys. Exposure of the PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 aileron pulleys to the leaked moisture in freezing condition can result in restricted aileron control movement (partly jammed) and/or higher control forces. This condition, if not corrected, could lead to partial loss of control of the aircraft. To address this unsafe condition, Fokker Services originally introduced SBF100–53–101 which was made mandatory through CAA Netherlands (CAA– NL) AD NL–2005–013 [which corresponds to FAA AD 2008–04–22] with a compliance time of 12 months after November 1, 2005. Following this, new reports of problems due to freezing moisture in the same area have been received. This has prompted Fokker Services to publish SBF100–53–107, which introduces an additional one-time inspection [for deviations] of the aerodynamic seals of the Wing-to-Fuselage Fairings and the application of an improved sealing of the aerodynamic seal by means of a fillet seam between the upper left and right fairings and the fuselage skin. For the reasons described above, this EASA AD supersedes CAA–NL AD NL–2005–013 and requires an additional one-time inspection [for deviations] and application of improved sealing. This action retains the inspection in AD 2008–04–22. Doing the additional inspection terminates the requirement to do the inspection required by the existing AD. The additional inspection for deviations includes inspecting for fit between the left-hand and right-hand wing-to-fuselage fairings and the fuselage skin; inspecting for damage to the aerodynamic seal on the fairings; inspecting for fit of the aerodynamic seal to the fuselage; and doing related investigative and corrective actions if necessary. The related investigative actions include inspecting the aerodynamic seal for damage (including wear); inspecting the abrasion resistant coating for damage (including wear); and re-inspecting for fit. The corrective actions include installing a new seal, restoring the protective coating, correcting the position of the fairing, and sealing the gaps between the fairings and the surrounding structure. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in E:\FR\FM\26FER1.SGM 26FER1

Agencies

[Federal Register Volume 74, Number 37 (Thursday, February 26, 2009)]
[Rules and Regulations]
[Pages 8719-8722]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3272]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0731; Directorate Identifier 2008-NM-058-AD; 
Amendment 39-15812; AD 2009-04-06]
RIN 2120-AA64


Airworthiness Directives; 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

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 detailed inspections of the aft pressure 
bulkhead for indications of ``oil cans'' and previous oil can repairs, 
and corrective actions if necessary. An oil can is an area on a 
pressure dome web that moves when pushed from the forward side. This 
new AD requires a reduced compliance time for the initial detailed 
inspection and revises the applicability. This AD results from a report 
that cracks in oil-canned areas were found during an inspection of the 
aft pressure bulkhead. We are issuing this AD to detect and correct the 
propagation of fatigue cracks in the vicinity of oil cans on the web of 
the aft pressure bulkhead, which could result in rapid decompression of 
the airplane and overpressurization of the tail section, and consequent 
loss of control of the airplane.

DATES: This AD becomes effective April 2, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 2, 
2009.
    On September 13, 2004 (69 FR 48133, August 9, 2004), the Director 
of the Federal Register approved the incorporation by reference of a 
certain other publication.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue SW., Renton, Washington 98057-3356; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

[[Page 8720]]

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2004-16-09, amendment 
39-13765 (69 FR 48133, August 9, 2004). The existing AD applies to all 
Boeing Model 747 series airplanes. That NPRM was published in the 
Federal Register on July 2, 2008 (73 FR 37900). That NPRM proposed to 
require a reduced initial threshold for repetitive detailed inspections 
of the aft pressure bulkhead for indications of ``oil cans'' and 
previous oil can repairs, and corrective actions if necessary.

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. Two commenters, the Air Line Pilots Association, 
International (ALPA), and Northwest Airlines, support the NPRM.

Request to Remove Certain Airplanes From Applicability Section

    Boeing requests that we remove Model 747-400 airplanes with the 
following variable numbers from paragraph (c) of this proposed AD: 
RT631, RT632, RT743, and RT876. Those airplanes have been or are being 
converted to a 747-400 LCF (large cargo freighter) configuration. The 
aft pressure bulkhead is removed from these airplanes; therefore, the 
proposed AD would not apply to those airplanes.
    We agree that airplanes that have been converted to a Model 747-400 
LCF configuration no longer have an aft pressure bulkhead to inspect. 
We have revised the applicability section of this AD to exclude 
airplanes that have been converted. We have not excluded specific 
variable numbers as suggested by Boeing since more airplanes might be 
converted to the Model 747-400 LCF configuration in the future.

Explanation of Change to Paragraph (f) of This AD

    We have removed the ``Service Bulletin Reference'' paragraph from 
this AD. (That paragraph was identified as paragraph (f) in the NPRM.) 
Instead, we have spelled out the service bulletin citations throughout 
this AD. We also re-identified the subsequent paragraphs.

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 917 airplanes of the affected design in the 
worldwide fleet. This AD affects about 165 airplanes of U.S. registry.
    The actions that are required by AD 2004-16-09 and retained in this 
AD take about 2 work hours per airplane, at an average labor rate of 
$80 per work hour. Based on these figures, the estimated cost of the 
currently required actions to the U.S. operators is $26,400, or $160 
per airplane, per inspection cycle.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this 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 39-13765 (69 FR 48133, August 9, 2004) and by adding 
the following new airworthiness directive (AD):

2009-04-06 Boeing: Amendment 39-15812. Docket No. FAA-2008-0731; 
Directorate Identifier 2008-NM-058-AD.

Effective Date

    (a) This AD becomes effective April 2, 2009.

Affected ADs

    (b) This AD supersedes AD 2004-16-09.

Applicability

    (c) This AD applies to 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, except those that have been converted to a Model 747-400 
LCF configuration.

Unsafe Condition

    (d) This AD results from a report that cracks in oil-canned 
areas were found during an inspection of the aft pressure bulkhead. 
We are issuing this AD to detect and correct the propagation of 
fatigue cracks in the vicinity of oil cans on the web of the aft 
pressure bulkhead, which could result in rapid decompression of the 
airplane and overpressurization of the tail section, and consequent 
loss of control 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.

    Note 1: This AD refers to certain portions of Boeing Alert 
Service Bulletin 747-53A2482, dated October 3, 2002; and Boeing 
Alert Service Bulletin 747-53A2482, Revision 1, dated February 21, 
2008; for inspections and repair information. In addition, this AD 
specifies requirements

[[Page 8721]]

beyond those included in Boeing Alert Service Bulletin 747-53A2482, 
dated October 3, 2002; and Boeing Alert Service Bulletin 747-
53A2482, Revision 1, dated February 21, 2008. Where the AD and 
Boeing Alert Service Bulletin 747-53A2482, dated October 3, 2002; 
and Boeing Alert Service Bulletin 747-53A2482, Revision 1, dated 
February 21, 2008; differ, the AD prevails.

Requirements of AD 2004-16-09, With Reduced Threshold

Initial and Repetitive Inspections

    (f) At the earlier of the times specified in paragraphs (f)(1) 
and (f)(2) of this AD, perform a detailed inspection of the aft 
pressure bulkhead for indications of oil cans and previous oil can 
repairs, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2482, dated October 3, 2002; or 
Boeing Alert Service Bulletin 747-53A2482, Revision 1, dated 
February 21, 2008. After the effective date of this AD, Revision 1 
must be used.
    (1) Prior to the accumulation of 30,000 total flight cycles, or 
within 1,000 flight cycles after September 13, 2004 (the effective 
date of AD 2004-16-09), whichever is later.
    (2) Prior to the accumulation of 20,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later.

    Note 2: 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 
mirrors, magnifying lenses, etc. may be necessary. Surface cleaning 
and elaborate procedures may be required.''

    (g) If no indication of an oil can is found and no indication of 
a previous oil can repair is found during the detailed inspection 
required by paragraph (f) of this AD, repeat the detailed inspection 
thereafter at intervals not to exceed 2,000 flight cycles.

Indication of Oil Can

    (h) If any indication of an oil can is found during the detailed 
inspection required by paragraph (f) or (g) of this AD, before 
further flight, perform an eddy current inspection of the web around 
the periphery of the oil can indication for cracks, as shown in 
Figure 3 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2482, dated October 3, 2002; or Boeing Alert Service 
Bulletin 747-53A2482, Revision 1, dated February 21, 2008. After the 
effective date of this AD, Revision 1 must be used.
    (i) If no crack is found during the eddy current inspection 
required by paragraph (i) of this AD, do the actions specified in 
paragraph (i)(1) or (i)(2) of this AD, as applicable.
    (1) For the oil can that meets the allowable limits specified in 
Boeing Alert Service Bulletin 747-53A2482, dated October 3, 2002; or 
Boeing Alert Service Bulletin 747-53A2482, Revision 1, dated 
February 21, 2008: Repeat the eddy current inspection specified in 
paragraph (h) of this AD thereafter at intervals not to exceed 1,000 
flight cycles. As an option, repair the oil can in accordance with 
paragraph (i)(2) of this AD.
    (2) For the oil can that does not meet the allowable limits 
specified in Boeing Alert Service Bulletin 747-53A2482, dated 
October 3, 2002; or Boeing Alert Service Bulletin 747-53A2482, 
Revision 1, dated February 21, 2008: Before further flight, repair 
the oil can in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2482, dated October 3, 2002; or 
Boeing Alert Service Bulletin 747-53A2482, Revision 1, dated 
February 21, 2008. After the effective date of this AD, Revision 1 
must be used. If the repair eliminates the oil can, accomplishment 
of this repair constitutes terminating action for the repetitive 
eddy current inspection requirements of paragraph (i)(1) of this AD 
for that location only. However, the repetitive detailed inspection 
required by paragraph (g) of this AD is still required. If any oil 
can remains after the repair, repeat the eddy current inspection 
specified in paragraph (h) of this AD thereafter at intervals not to 
exceed 1,000 flight cycles.

Indication of Previous Oil Can Repairs

    (j) If any previous oil can repair is found during the detailed 
inspection required by paragraph (f) or (g) of this AD, before 
further flight, do a detailed inspection of the web for cracks and 
oil cans, as shown in Figure 4 or Figure 5, as applicable, of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 
747-53A2482, Revision 1, dated February 21, 2008. After the 
effective date of this AD, Revision 1 must be used.
    (1) If no crack and no oil can are found, repeat the detailed 
inspection in accordance with paragraph (f) of this AD.
    (2) If any oil can is found, before further flight, do the eddy 
current inspection for cracks, as shown in Figure 3 of Boeing Alert 
Service Bulletin 747-53A2482, dated October 3, 2002; or Boeing Alert 
Service Bulletin 747-53A2482, Revision 1, dated February 21, 2008. 
After the effective date of this AD, Revision 1 must be used. If no 
crack is found during the eddy current inspection required by this 
paragraph, do the actions specified in paragraph (i)(1) or (i)(2) of 
this AD, as applicable, at the time specified in the applicable 
paragraph.

Repair of Cracks

    (k) If any crack is found during any inspection required by this 
AD, before further flight, repair in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 
747-53A2482, Revision 1, dated February 21, 2008. After the 
effective date of this AD, Revision 1 must be used. If any crack or 
damage exceeds limits specified in Boeing Alert Service Bulletin 
747-53A2482, dated October 3, 2002; or Boeing Alert Service Bulletin 
747-53A2482, Revision 1, dated February 21, 2008; and Boeing Alert 
Service Bulletin 747-53A2482, dated October 3, 2002; or Boeing Alert 
Service Bulletin 747-53A2482, Revision 1, dated February 21, 2008; 
specifies to contact Boeing for appropriate action: Before further 
flight, repair per a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA; or per data meeting the 
type certification basis of the airplane approved by a Boeing 
Company Designated Engineering Representative who has been 
authorized by the Manager, Seattle ACO, to make such findings; or 
using a method approved in accordance with the procedures specified 
in paragraph (m) of this AD. For a repair method to be approved, the 
approval must specifically reference this AD.

New Requirements of This AD

    (l) As of the effective date of this AD, if any crack or damage 
is found during any inspection required by this AD, and Boeing Alert 
Service Bulletin 747-53A2482, Revision 1, dated February 21, 2008, 
specifies to contact Boeing for appropriate action (repair data): 
Before further flight, repair the crack or damage using a method 
approved in accordance with the procedures specified in paragraph 
(m) of this AD.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, Washington 98057-
3356; telephone (425) 917-6437; fax (425) 917-6590, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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 in accordance with AD 2004-16-09 
are not approved as AMOCs for the corresponding provisions of 
paragraph (f) of this AD. They are approved as AMOCs for the 
corresponding provisions of paragraphs (g), (h), (i), (j), (k), and 
(l) of this AD.

Material Incorporated by Reference

    (n) You must use Boeing Alert Service Bulletin 747-53A2482, 
dated October 3, 2002; or Boeing Alert Service Bulletin 747-53A2482, 
Revision 1, dated February 21, 2008; 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 Alert Service Bulletin 747-
53A2482,

[[Page 8722]]

Revision 1, dated February 21, 2008, in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) On September 13, 2004 (69 FR 48133, August 9, 2004), the 
Director of the Federal Register approved the incorporation by 
reference of Boeing Alert Service Bulletin 747-53A2482, dated 
October 3, 2002.
    (3) Contact Boeing Commercial Airplanes, Attention: Data & 
Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 
98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; 
e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com; 
for a copy of this service information.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal_register/code_oflowbar;federal--
regulations/ibr--locations.html.

    Issued in Renton, Washington, on January 29, 2009.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E9-3272 Filed 2-25-09; 8:45 am]
BILLING CODE 4910-13-P
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