Airworthiness Directives; The Boeing Company Model 747-200C, -200F, -400, -400D, and -400F Series Airplanes, 81427-81430 [2010-31992]

Download as PDF Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations (5) Revise the Operating Limitations section of the RFM by inserting a copy of this AD into the appropriate section of the RFM. (b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Boston Aircraft Certification Office, FAA, Attn: Tony Pigott, Aviation Safety Engineer, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7158, fax (781) 238– 7170. (c) The Joint Aircraft System/Component (JASC) Code is 3420: Navigation. (d) Installing the placards shall be done by following the specified portions of Sikorsky Alert Service Bulletin No. 76–34–11, dated May 17, 2010. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone (203) 383–4866, e-mail address tsslibrary@sikorsky.com, or at http://www. sikorsky.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or 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: http://www.archives. gov/federal_register/code_of_federal_ regulations/ibr_locations.html. (e) This amendment becomes effective on January 12, 2011. Issued in Fort Worth, Texas, on December 13, 2010. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2010–31962 Filed 12–27–10; 8:45 am] BILLING CODE 4910–13–P requires repetitive inspections for cracks in the overlapping (upper) skin of the upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46; and related investigative and corrective actions, if necessary. This new AD expands the inspection area in the existing AD, and adds a modification of certain lap joints and certain post-repair inspections of the lap joints. Accomplishing the modification would end the repetitive inspections required by the existing AD for the length of lap joint that is modified. This AD results from a structural review of affected skin lap joints for widespread fatigue damage. We are issuing this AD to prevent fatigue cracking in certain lap joints, which could result in rapid depressurization of the airplane. This AD becomes effective February 1, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of February 1, 2011. On April 13, 2006 (71 FR 12122, March 9, 2006), the Director of the Federal Register approved the incorporation by reference of a certain other publication listed in the AD. DATES: 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. ADDRESSES: Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0232; Directorate Identifier 2009–NM–032–AD; Amendment 39–16549; AD 2010–26–10] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 747–200C, –200F, –400, –400D, and –400F Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. srobinson on DSKHWCL6B1PROD with RULES AGENCY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 747– 200C, –200F, –400, –400D, and –400F series airplanes. That AD currently SUMMARY: VerDate Mar<15>2010 18:14 Dec 27, 2010 Jkt 223001 You may examine the AD docket on the Internet at http:// 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: Nicholas Han, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6449; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00057 Fmt 4700 Sfmt 4700 81427 Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2006–05–09, Amendment 39–14506 (71 FR 12122, March 9, 2006). The existing AD applies to certain Model 747–200C, –200F, –400, –400D, and –400F series airplanes. That NPRM was published in the Federal Register on March 18, 2010 (75 FR 13046). That NPRM proposed to continue to require repetitive inspections for cracks in the overlapping (upper) skin of the upper fastener row of the lap joints of the fuselage skin in Sections 41, 42, and 46; and related investigative and corrective actions, if necessary. That NPRM also proposed to expand the inspection area in the existing AD, and add a modification of certain lap joints and certain post-repair inspections of the lap joints. Accomplishing the modification would end the repetitive inspections required by the existing AD. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Request To Revise Certain Language in Paragraph (k) of the NPRM Boeing asked that we revise the language in paragraph (k) of the NPRM to indicate that additional actions are required in the area of the modification for operation beyond 15,000 total flight cycles after doing the proposed modification. Boeing stated that Revision 2 of Boeing Alert Service Bulletin 747–53A2499 is currently in work at the Boeing Company, and that Revision 2 recommends accomplishing additional actions after doing the modification. Since this comment was submitted, we have received and reviewed Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. Boeing Alert Service Bulletin 747–53A2499, dated August 11, 2005; and Revision 1, dated October 30, 2008; were referred to in the NPRM as the appropriate source of service information for accomplishing the actions. No more work is necessary for airplanes on which Boeing Alert Service Bulletin 747–53A2499, Revision 1, dated October 30, 2008, was used for doing the required actions. Revision 2 of this service bulletin moves certain airplanes from Group 1 to Groups 15 and 16, adds post-modification actions, and contains editorial changes. We have revised paragraphs (c), (g), (h), (i), (j), and (k) of this AD to refer to E:\FR\FM\28DER1.SGM 28DER1 81428 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations srobinson on DSKHWCL6B1PROD with RULES Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. In addition, we have removed Notes 1 and 2 of this AD since that information is incorporated into Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. We have also added a new paragraph (n) to the AD to give credit for accomplishing the specified actions in accordance with Boeing Alert Service Bulletin 747– 53A2499, Revision 1, dated October 30, 2008. Although Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010, includes post-modification actions, this AD will not mandate those actions. The threshold for the skin lap joint modification mandated by this AD is 30,000 total flight cycles. Adding 15,000 flight cycles to the threshold would extend the compliance time for the recommended additional actions to 45,000 total flight cycles. We have determined that it is highly unlikely that a Model 747 airplane will reach that number of total flight cycles. This determination also takes into consideration the proposed wide spread fatigue damage (WFD) operating rules imposing operating limits that could be significantly lower than 45,000 total flight cycles. In light of these factors, we have determined that this final rule must be issued without any further delay due to the severity of the unsafe condition addressed by this AD. Further rulemaking might be issued in the future to mandate the additional actions included in Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. We have not changed the AD in this regard. Request To Delay AD Pending New Service Information Japan Airlines (JAL) asked that we delay issuance until the manufacturer can release Revision 2 of Boeing Alert Service Bulletin 747–53A2499. JAL stated that Boeing has issued Service Bulletin Information Notices 747– 53A2499 IN 01, dated April 2, 2009; and 747–53A2499 IN 02, dated September 10, 2009; to Boeing Alert Service Bulletin 747–53A2499, Revision 1, dated October 30, 2008, to notify operators of a typo and revised drawings. JAL noted that operators cannot accomplish a correct inspection and modification unless the information provided in Boeing Service Bulletin Information Notices 747–53A2499 IN 01 and 747–53A2499 IN 02 is used. JAL added that including Revision 2 of this service bulletin would reduce unnecessary burden on both operators and the manufacturer. VerDate Mar<15>2010 18:14 Dec 27, 2010 Jkt 223001 All Nippon Airways (ANA) also asked that the modification be done in accordance with Revision 2 of Boeing Alert Service Bulletin 747–53A2499 instead of Boeing Alert Service Bulletin 747–53A2499, Revision 1, dated October 30, 2008. ANA stated that it has already performed the terminating modification at stringer 6 using Boeing Alert Service Bulletin 747–53A2499, Revision 1, and had to request AMOCs during the modification because certain drawings in Boeing Alert Service Bulletin 747–53A2499, dated August 11, 2005; and Revision 1, dated October 30, 2008; were not specific to the modification. ANA added that this will reduce the AMOC requests to this proposed AD, in addition to reducing the maintenance burden. We partially agree with the commenters. We do not agree to delay this AD, due to the severity of the unsafe condition. However, as described previously, Boeing has issued Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. Therefore, we have revised the requirements in this AD to allow the use of Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010, for accomplishing the specified actions. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance There are about 735 airplanes of the affected design in the worldwide fleet. This AD affects 96 airplanes of U.S. registry. The actions that are required by AD 2006–05–09 and retained in this AD take about 541 work-hours per airplane, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the currently required actions is $45,985 per airplane, per inspection cycle. The new Area 2 inspections take about 124 work-hours per airplane, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the new inspections specified in this AD for U.S. operators is $1,011,840, or $10,540 per airplane, per inspection cycle. The new modification takes about 4,799 work hours per airplane, at an average labor rate of $85 per work-hour. Required parts cost per airplane will be PO 00000 Frm 00058 Fmt 4700 Sfmt 4700 minimal. Based on these figures, the estimated cost of the new modification specified in this AD for U.S. operators is $39,159,840, or $407,915 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ E:\FR\FM\28DER1.SGM 28DER1 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations Applicability 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] (c) This AD applies to The Boeing Company Model 747–200C, –200F, –400, –400D, and –400F series airplanes, certificated in any category; as identified in Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. Subject 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing Amendment 39–14506 (71 FR 12122, March 9, 2006) and by adding the following new airworthiness directive (AD): ■ 2010–26–10 The Boeing Company: Amendment 39–16549. FAA–2010–0232; Directorate Identifier 2009–NM–032–AD. Effective Date (a) This AD becomes effective February 1, 2011. Affected ADs (b) This AD supersedes AD 2006–05–09. (d) Air Transport Association (ATA) of America Code 53: Fuselage. Unsafe Condition (e) This AD results from a structural review of affected skin lap joints for widespread fatigue damage. The Federal Aviation Administration is issuing this AD to prevent fatigue cracking in certain lap joints, which could result in rapid depressurization of the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. 81429 Restatement of Requirements of AD 2006– 05–09, With Revised Service Information Initial Inspections and Related Investigative and Corrective Actions (g) For airplanes identified in Boeing Alert Service Bulletin 747–53A2499, dated August 11, 2005: At the applicable time specified in Table 1 of this AD, do an external surface high frequency eddy current (HFEC), external low frequency eddy current (LFEC), and internal LFEC inspection, as applicable, for cracks in the overlapping (upper) skin of the upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46, and any applicable related investigative and corrective actions by doing all of the actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2499, dated August 11, 2005; Revision 1, dated October 30, 2008; or Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. Do any applicable related investigative and corrective actions before further flight. As of the effective date of this AD, only Boeing Service Bulletin 747– 53A2499, Revision 2, dated August 12, 2010, may be used. TABLE 1—INITIAL COMPLIANCE TIME For airplanes on which Structural Significant Items (SSIs) F–25G, F–25H, and F–25I— Inspect— (1) Have not been inspected in accordance with paragraph (i) of AD 2004–07–22 R1, Amendment 39– 15326, using the HFEC method. (2) Have been inspected in accordance with paragraph (i) of AD 2004–07–22 R1, using the HFEC method. Before the accumulation of 22,000 total flight cycles, or within 1,000 flight cycles after April 13, 2006 (the effective date of AD 2006–05–09), whichever occurs later. Repetitive Inspections (h) Repeat the applicable inspections required by paragraph (g) of this AD thereafter at intervals not to exceed those specified in paragraph 1.E., ‘‘Compliance,’’ (including the note) of Boeing Alert Service Bulletin 747–53A2499, dated August 11, 2005; Revision 1, dated October 30, 2008; or Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. As of the effective date of this AD, only Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010, may be used. srobinson on DSKHWCL6B1PROD with RULES New Requirements of This AD Repetitive Inspections/Investigative and Corrective Actions (i) For all airplanes: Do an external HFEC inspection of the lap joints in Sections 41, 42, and 46 for cracks, by doing all the actions, including all applicable related investigative and corrective actions, specified in the Accomplishment Instructions of Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. Do the inspection at the applicable time specified in paragraph 1.E. of Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010; except as required by paragraph (m) of this AD. Do all applicable related investigative and corrective actions before further flight. VerDate Mar<15>2010 20:48 Dec 27, 2010 Jkt 223001 Within 3,000 flight cycles after the most recent supplemental structural inspection document (SSID) inspection of each applicable structural significant item (as given in Boeing Document D6–35022, ‘‘SSID for Model 747 Airplanes,’’ Revision G, dated December 2000), or within 1,000 flight cycles after April 13, 2006, whichever occurs later. Repeat the inspection thereafter at the times specified in paragraph 1.E. of Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010. Accomplishment of the inspections required by this paragraph terminates the inspections required by paragraphs (g) and (h) of this AD. (j) For areas on which a lap joint repair was installed and the repair doubler is greater than or equal to 40 inches long: Do initial and repetitive internal HFEC inspections for cracks by doing all the actions, including all applicable corrective actions, specified in the Accomplishment Instructions of Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010, except as required by paragraph (l) of this AD. Do the inspections and corrective actions at the times specified in paragraph 1.E. of Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010, except as required by paragraph (m) of this AD. Terminating Action (k) Modify the applicable lap joints in Sections 41 and 42 by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010, at the time specified in paragraph 1.E. of Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, PO 00000 Frm 00059 Fmt 4700 Sfmt 4700 2010; except as required by paragraphs (l) and (m) of this AD. Accomplishing this modification terminates the repetitive inspections of the skin lap joints in Sections 41 and 42 required by paragraphs (i) and (j) of this AD for the length of lap joint that is modified. Exceptions to Service Bulletin Procedures (l) Where Boeing Service Bulletin 747– 53A2499, Revision 2, dated August 12, 2010, specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (m) Where Boeing Service Bulletin 747– 53A2499, Revision 2, dated August 12, 2010, specifies a compliance time after the date of that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Credit for Actions Done Using Previous Service Information (n) Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin 747–53A2499, Revision 1, dated October 30, 2008, are acceptable for compliance with the corresponding requirements of this AD. E:\FR\FM\28DER1.SGM 28DER1 81430 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations srobinson on DSKHWCL6B1PROD with RULES Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Nicholas Han, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6449; fax (425) 917–6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) or other person authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) AMOCs approved previously in accordance with AD 2006–05–09 are approved as alternative methods of compliance with the corresponding requirements of this AD. Material Incorporated by Reference (p) You must use Boeing Alert Service Bulletin 747–53A2499, dated August 11, 2005; or Boeing Service Bulletin 747– 53A2499, Revision 2, dated August 12, 2010; 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 Boeing Service Bulletin 747–53A2499, Revision 2, dated August 12, 2010, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2499, dated August 11, 2005, on April 13, 2006 (71 FR 12122, March 9, 2006). (3) 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. (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. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For VerDate Mar<15>2010 18:14 Dec 27, 2010 Jkt 223001 information on the availability of this material at 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 December 13, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–31992 Filed 12–27–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0674; Directorate Identifier 2010–NM–012–AD; Amendment 39–16546; AD 2010–26–07] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 747 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for cracking in the body skin around the aft corners of the nose wheel well; for certain airplanes, repetitive inspections for cracking in the skin splice plate at the aft corners of the nose wheel well; and related investigative and corrective actions if necessary. This AD also requires repetitive post-modification inspections for cracking in the body skin and the skin splice plate; for certain airplanes, an inspection for steel cross-shaped doublers on the larger aluminum doublers; and corrective action if necessary. This AD also requires repetitive surface high frequency eddy current (HFEC) inspections of a certain bulkhead outer chord, skin splice plate, and outer chord radius filler for cracking; repetitive detailed inspections for cracking of the bulkhead frame web and body skin; and corrective actions if necessary. This AD provides for optional terminating action for certain repetitive inspections. This AD was prompted by reports of cracking of the fuselage skin and adjacent internal skin splice plate at the left and right nose wheel well aft corners, and the outer chord of the body station (BS) 400 bulkhead. We are issuing this AD to detect and correct cracking of the fuselage skin or splice plate, which, together with cracking of the bulkhead outer chord, could result in large skin SUMMARY: PO 00000 Frm 00060 Fmt 4700 Sfmt 4700 cracks and subsequent in-flight rapid decompression of the airplane. DATES: This AD is effective February 1, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of February 1, 2011. 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. You may review copies of the referenced 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// 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 (phone: 800–647–5527) is 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: Steven Fox, Senior Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6425; fax (425) 917–6590; email: steven.fox@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That NPRM published in the Federal Register on July 8, 2010 (75 FR 39189). That NPRM proposed to require repetitive inspections for cracking in the body skin around the aft corners of the nose wheel well; for certain airplanes, repetitive inspections for cracking in the skin splice plate at the aft corners of the nose wheel well; and related investigative and corrective actions if E:\FR\FM\28DER1.SGM 28DER1

Agencies

[Federal Register Volume 75, Number 248 (Tuesday, December 28, 2010)]
[Rules and Regulations]
[Pages 81427-81430]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-31992]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0232; Directorate Identifier 2009-NM-032-AD; 
Amendment 39-16549; AD 2010-26-10]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747-200C, -
200F, -400, -400D, and -400F 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 certain Model 747-200C, -200F, -400, -400D, and 
-400F series airplanes. That AD currently requires repetitive 
inspections for cracks in the overlapping (upper) skin of the upper 
fastener row of the lap joints of the fuselage skin in sections 41, 42, 
and 46; and related investigative and corrective actions, if necessary. 
This new AD expands the inspection area in the existing AD, and adds a 
modification of certain lap joints and certain post-repair inspections 
of the lap joints. Accomplishing the modification would end the 
repetitive inspections required by the existing AD for the length of 
lap joint that is modified. This AD results from a structural review of 
affected skin lap joints for widespread fatigue damage. We are issuing 
this AD to prevent fatigue cracking in certain lap joints, which could 
result in rapid depressurization of the airplane.

DATES: This AD becomes effective February 1, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 1, 
2011.
    On April 13, 2006 (71 FR 12122, March 9, 2006), the Director of the 
Federal Register approved the incorporation by reference of a certain 
other publication listed in the AD.

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 http://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: Nicholas Han, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6449; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-05-09, Amendment 
39-14506 (71 FR 12122, March 9, 2006). The existing AD applies to 
certain Model 747-200C, -200F, -400, -400D, and -400F series airplanes. 
That NPRM was published in the Federal Register on March 18, 2010 (75 
FR 13046). That NPRM proposed to continue to require repetitive 
inspections for cracks in the overlapping (upper) skin of the upper 
fastener row of the lap joints of the fuselage skin in Sections 41, 42, 
and 46; and related investigative and corrective actions, if necessary. 
That NPRM also proposed to expand the inspection area in the existing 
AD, and add a modification of certain lap joints and certain post-
repair inspections of the lap joints. Accomplishing the modification 
would end the repetitive inspections required by the existing AD.

Comments

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

Request To Revise Certain Language in Paragraph (k) of the NPRM

    Boeing asked that we revise the language in paragraph (k) of the 
NPRM to indicate that additional actions are required in the area of 
the modification for operation beyond 15,000 total flight cycles after 
doing the proposed modification. Boeing stated that Revision 2 of 
Boeing Alert Service Bulletin 747-53A2499 is currently in work at the 
Boeing Company, and that Revision 2 recommends accomplishing additional 
actions after doing the modification.
    Since this comment was submitted, we have received and reviewed 
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010. 
Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005; and 
Revision 1, dated October 30, 2008; were referred to in the NPRM as the 
appropriate source of service information for accomplishing the 
actions. No more work is necessary for airplanes on which Boeing Alert 
Service Bulletin 747-53A2499, Revision 1, dated October 30, 2008, was 
used for doing the required actions. Revision 2 of this service 
bulletin moves certain airplanes from Group 1 to Groups 15 and 16, adds 
post-modification actions, and contains editorial changes.
    We have revised paragraphs (c), (g), (h), (i), (j), and (k) of this 
AD to refer to

[[Page 81428]]

Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010. 
In addition, we have removed Notes 1 and 2 of this AD since that 
information is incorporated into Boeing Service Bulletin 747-53A2499, 
Revision 2, dated August 12, 2010. We have also added a new paragraph 
(n) to the AD to give credit for accomplishing the specified actions in 
accordance with Boeing Alert Service Bulletin 747-53A2499, Revision 1, 
dated October 30, 2008.
    Although Boeing Service Bulletin 747-53A2499, Revision 2, dated 
August 12, 2010, includes post-modification actions, this AD will not 
mandate those actions. The threshold for the skin lap joint 
modification mandated by this AD is 30,000 total flight cycles. Adding 
15,000 flight cycles to the threshold would extend the compliance time 
for the recommended additional actions to 45,000 total flight cycles. 
We have determined that it is highly unlikely that a Model 747 airplane 
will reach that number of total flight cycles. This determination also 
takes into consideration the proposed wide spread fatigue damage (WFD) 
operating rules imposing operating limits that could be significantly 
lower than 45,000 total flight cycles.
    In light of these factors, we have determined that this final rule 
must be issued without any further delay due to the severity of the 
unsafe condition addressed by this AD. Further rulemaking might be 
issued in the future to mandate the additional actions included in 
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010. 
We have not changed the AD in this regard.

Request To Delay AD Pending New Service Information

    Japan Airlines (JAL) asked that we delay issuance until the 
manufacturer can release Revision 2 of Boeing Alert Service Bulletin 
747-53A2499. JAL stated that Boeing has issued Service Bulletin 
Information Notices 747-53A2499 IN 01, dated April 2, 2009; and 747-
53A2499 IN 02, dated September 10, 2009; to Boeing Alert Service 
Bulletin 747-53A2499, Revision 1, dated October 30, 2008, to notify 
operators of a typo and revised drawings. JAL noted that operators 
cannot accomplish a correct inspection and modification unless the 
information provided in Boeing Service Bulletin Information Notices 
747-53A2499 IN 01 and 747-53A2499 IN 02 is used. JAL added that 
including Revision 2 of this service bulletin would reduce unnecessary 
burden on both operators and the manufacturer.
    All Nippon Airways (ANA) also asked that the modification be done 
in accordance with Revision 2 of Boeing Alert Service Bulletin 747-
53A2499 instead of Boeing Alert Service Bulletin 747-53A2499, Revision 
1, dated October 30, 2008. ANA stated that it has already performed the 
terminating modification at stringer 6 using Boeing Alert Service 
Bulletin 747-53A2499, Revision 1, and had to request AMOCs during the 
modification because certain drawings in Boeing Alert Service Bulletin 
747-53A2499, dated August 11, 2005; and Revision 1, dated October 30, 
2008; were not specific to the modification. ANA added that this will 
reduce the AMOC requests to this proposed AD, in addition to reducing 
the maintenance burden.
    We partially agree with the commenters. We do not agree to delay 
this AD, due to the severity of the unsafe condition. However, as 
described previously, Boeing has issued Boeing Service Bulletin 747-
53A2499, Revision 2, dated August 12, 2010. Therefore, we have revised 
the requirements in this AD to allow the use of Boeing Service Bulletin 
747-53A2499, Revision 2, dated August 12, 2010, for accomplishing the 
specified actions.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We also determined that 
these changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Costs of Compliance

    There are about 735 airplanes of the affected design in the 
worldwide fleet. This AD affects 96 airplanes of U.S. registry.
    The actions that are required by AD 2006-05-09 and retained in this 
AD take about 541 work-hours per airplane, at an average labor rate of 
$85 per work-hour. Based on these figures, the estimated cost of the 
currently required actions is $45,985 per airplane, per inspection 
cycle.
    The new Area 2 inspections take about 124 work-hours per airplane, 
at an average labor rate of $85 per work-hour. Based on these figures, 
the estimated cost of the new inspections specified in this AD for U.S. 
operators is $1,011,840, or $10,540 per airplane, per inspection cycle.
    The new modification takes about 4,799 work hours per airplane, at 
an average labor rate of $85 per work-hour. Required parts cost per 
airplane will be minimal. Based on these figures, the estimated cost of 
the new modification specified in this AD for U.S. operators is 
$39,159,840, or $407,915 per airplane.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

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

[[Page 81429]]

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 39-14506 (71 FR 12122, March 9, 2006) and by adding 
the following new airworthiness directive (AD):

2010-26-10 The Boeing Company: Amendment 39-16549. FAA-2010-0232; 
Directorate Identifier 2009-NM-032-AD.

Effective Date

    (a) This AD becomes effective February 1, 2011.

Affected ADs

    (b) This AD supersedes AD 2006-05-09.

Applicability

    (c) This AD applies to The Boeing Company Model 747-200C, -200F, 
-400, -400D, and -400F series airplanes, certificated in any 
category; as identified in Boeing Service Bulletin 747-53A2499, 
Revision 2, dated August 12, 2010.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from a structural review of affected skin 
lap joints for widespread fatigue damage. The Federal Aviation 
Administration is issuing this AD to prevent fatigue cracking in 
certain lap joints, which could result in rapid depressurization of 
the airplane.

Compliance

    (f) 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 2006-05-09, With Revised Service 
Information

Initial Inspections and Related Investigative and Corrective Actions

    (g) For airplanes identified in Boeing Alert Service Bulletin 
747-53A2499, dated August 11, 2005: At the applicable time specified 
in Table 1 of this AD, do an external surface high frequency eddy 
current (HFEC), external low frequency eddy current (LFEC), and 
internal LFEC inspection, as applicable, for cracks in the 
overlapping (upper) skin of the upper fastener row of the lap joints 
of the fuselage skin in sections 41, 42, and 46, and any applicable 
related investigative and corrective actions by doing all of the 
actions in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2499, dated August 11, 2005; Revision 
1, dated October 30, 2008; or Boeing Service Bulletin 747-53A2499, 
Revision 2, dated August 12, 2010. Do any applicable related 
investigative and corrective actions before further flight. As of 
the effective date of this AD, only Boeing Service Bulletin 747-
53A2499, Revision 2, dated August 12, 2010, may be used.

                    Table 1--Initial Compliance Time
------------------------------------------------------------------------
 For airplanes on which Structural
Significant Items (SSIs) F-25G, F-                Inspect--
         25H, and F-25I--
------------------------------------------------------------------------
(1) Have not been inspected in      Before the accumulation of 22,000
 accordance with paragraph (i) of    total flight cycles, or within
 AD 2004-07-22 R1, Amendment 39-     1,000 flight cycles after April 13,
 15326, using the HFEC method.       2006 (the effective date of AD 2006-
                                     05-09), whichever occurs later.
(2) Have been inspected in          Within 3,000 flight cycles after the
 accordance with paragraph (i) of    most recent supplemental structural
 AD 2004-07-22 R1, using the HFEC    inspection document (SSID)
 method.                             inspection of each applicable
                                     structural significant item (as
                                     given in Boeing Document D6-35022,
                                     ``SSID for Model 747 Airplanes,''
                                     Revision G, dated December 2000),
                                     or within 1,000 flight cycles after
                                     April 13, 2006, whichever occurs
                                     later.
------------------------------------------------------------------------

Repetitive Inspections

    (h) Repeat the applicable inspections required by paragraph (g) 
of this AD thereafter at intervals not to exceed those specified in 
paragraph 1.E., ``Compliance,'' (including the note) of Boeing Alert 
Service Bulletin 747-53A2499, dated August 11, 2005; Revision 1, 
dated October 30, 2008; or Boeing Service Bulletin 747-53A2499, 
Revision 2, dated August 12, 2010. As of the effective date of this 
AD, only Boeing Service Bulletin 747-53A2499, Revision 2, dated 
August 12, 2010, may be used.

New Requirements of This AD

Repetitive Inspections/Investigative and Corrective Actions

    (i) For all airplanes: Do an external HFEC inspection of the lap 
joints in Sections 41, 42, and 46 for cracks, by doing all the 
actions, including all applicable related investigative and 
corrective actions, specified in the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 
2010. Do the inspection at the applicable time specified in 
paragraph 1.E. of Boeing Service Bulletin 747-53A2499, Revision 2, 
dated August 12, 2010; except as required by paragraph (m) of this 
AD. Do all applicable related investigative and corrective actions 
before further flight. Repeat the inspection thereafter at the times 
specified in paragraph 1.E. of Boeing Service Bulletin 747-53A2499, 
Revision 2, dated August 12, 2010. Accomplishment of the inspections 
required by this paragraph terminates the inspections required by 
paragraphs (g) and (h) of this AD.
    (j) For areas on which a lap joint repair was installed and the 
repair doubler is greater than or equal to 40 inches long: Do 
initial and repetitive internal HFEC inspections for cracks by doing 
all the actions, including all applicable corrective actions, 
specified in the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2499, Revision 2, dated August 12, 2010, except as 
required by paragraph (l) of this AD. Do the inspections and 
corrective actions at the times specified in paragraph 1.E. of 
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 
2010, except as required by paragraph (m) of this AD.

Terminating Action

    (k) Modify the applicable lap joints in Sections 41 and 42 by 
doing all the applicable actions specified in the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2499, Revision 2, 
dated August 12, 2010, at the time specified in paragraph 1.E. of 
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 
2010; except as required by paragraphs (l) and (m) of this AD. 
Accomplishing this modification terminates the repetitive 
inspections of the skin lap joints in Sections 41 and 42 required by 
paragraphs (i) and (j) of this AD for the length of lap joint that 
is modified.

Exceptions to Service Bulletin Procedures

    (l) Where Boeing Service Bulletin 747-53A2499, Revision 2, dated 
August 12, 2010, specifies to contact Boeing for appropriate action: 
Before further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.
    (m) Where Boeing Service Bulletin 747-53A2499, Revision 2, dated 
August 12, 2010, specifies a compliance time after the date of that 
service bulletin, this AD requires compliance within the specified 
compliance time after the effective date of this AD.

Credit for Actions Done Using Previous Service Information

    (n) Actions done before the effective date of this AD in 
accordance with Boeing Alert Service Bulletin 747-53A2499, Revision 
1, dated October 30, 2008, are acceptable for compliance with the 
corresponding requirements of this AD.

[[Page 81430]]

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
Attn: Nicholas Han, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6449; fax (425) 917-6590. Information may 
be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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 principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) or other person authorized by the Manager, Seattle ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane and the approval 
must specifically refer to this AD.
    (4) AMOCs approved previously in accordance with AD 2006-05-09 
are approved as alternative methods of compliance with the 
corresponding requirements of this AD.

Material Incorporated by Reference

    (p) You must use Boeing Alert Service Bulletin 747-53A2499, 
dated August 11, 2005; or Boeing Service Bulletin 747-53A2499, 
Revision 2, dated August 12, 2010; 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 Boeing Service Bulletin 747-53A2499, 
Revision 2, dated August 12, 2010, under 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2499, dated August 11, 2005, on April 13, 2006 (71 FR 12122, 
March 9, 2006).
    (3) 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.
    (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.
    (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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 13, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-31992 Filed 12-27-10; 8:45 am]
BILLING CODE 4910-13-P