Airworthiness Directives; The Boeing Company Model 747-100B SUD, -200B, -300, -400, and -400D Series Airplanes, 3147-3149 [E9-30970]

Download as PDF Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Issued in Renton, Washington, on January 8, 2010. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–701 Filed 1–19–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Related Information 14 CFR Part 39 (h) Refer to MCAI DGAC Airworthiness Directive 2002–504(AB), effective October 12, 2002; and Sicma Aero Seat Service Bulletin 92–25–005, Issue 3, dated January 17, 2003, including Annex 1, dated July 17, 2002; for related information. (i) Contact Jeffrey Lee, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate; 12 New England Executive Park, Burlington, MA 01803; telephone 781–238–7161; fax 781– 238–7170, for more information about this AD. [Docket No. FAA–2009–0636; Directorate Identifier 2009–NM–031–AD; Amendment 39–16158; AD 2010–01–02] Material Incorporated by Reference (j) You must use Sicma Aero Seat Service Bulletin 92–25–005, Issue 3, dated January 17, 2003, including Annex 1, dated July 17, 2002, to do the actions required by this AD, unless the AD specifies otherwise. The Sicma Aero Seat service bulletin contains the following effective pages: Page No. Issue level shown on page Date shown on page 1–30 ....... 3 ................ January 17, 2003. ANNEX 1 pwalker on DSK8KYBLC1PROD with RULES 1–3 ......... Original ...... July 17, 2002. (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 Sicma Aero Seat, 7 Rue Lucien Coupet, 36100 Issoudun, France; telephone +33 (0) 2 54 03 39 39; fax +33 (0) 2 54 03 15 16; e-mail: customerservices@sicma.zodiac.com; Internet https://www.sicma.zodiac.com/en/. (3) 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. (4) 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_of_federal_regulations/ibr_ locations.html. VerDate Nov<24>2008 15:59 Jan 19, 2010 Jkt 220001 RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 747–100B SUD, –200B, –300, –400, and –400D 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– 100B SUD, –200B, –300, –400, and –400D series airplanes. That AD currently requires repetitive inspections for cracking in fuselage stringers 8L, 8R, 10L, and 10R at body stations 460, 480, and 500 frame locations; and repair if necessary. This new AD requires revising the applicability to include an additional airplane, and reduces compliance times for the initial inspection and repetitive intervals for Model 747–400 series airplanes that have been converted to the large cargo freighter configuration. This AD results from findings of cracking in fuselage stringers 8L, 8R, 10L, and 10R at body stations 460, 480, and 500 frame locations. We are issuing this AD to detect and correct fatigue cracking in certain fuselage stringers, which, if left undetected, could result in fuselage skin cracking that reduces the structural integrity of the skin panel, and consequent rapid depressurization of the airplane. DATES: This AD becomes effective February 24, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of February 24, 2010. The Director of the Federal Register previously approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003, as of August 30, 2005 (70 FR 43020, July 26, 2005). PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 3147 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, Seattle Aircraft Certification Office, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6437; 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 2005–15–08, amendment 39–14197 (70 FR 43020, July 26, 2005). The existing AD applies to certain Model 747–100B SUD, –200B, –300, –400, and –400D series airplanes. That NPRM was published in the Federal Register on July 14, 2009 (74 FR 33928). That NPRM proposed to require repetitive inspections for cracking in fuselage stringers 8L, 8R, 10L, and 10R at body stations 460, 480, and 500 frame locations; and repair if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been received on the NPRM. Request for Change to Paragraph (g) of This AD Boeing requests a change to paragraph (g) of the NPRM. The NPRM proposes to require repeating the inspections specified in paragraph (g) at intervals not to exceed 3,000 flight cycles until the requirements of paragraph (l) of the proposed AD are accomplished. Boeing E:\FR\FM\20JAR1.SGM 20JAR1 3148 Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations states that accomplishing the repair specified in paragraph (k) of the proposed AD terminates the repetitive inspections required by paragraph (g). Boeing therefore requests that we revise paragraph (g) of the proposed AD to also refer to paragraph (k) as a terminating action. We partially agree. The repetitive inspections are terminated after accomplishment of paragraph (k) or (l) of this AD, but only at the stringer locations that are modified or repaired. 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. We have revised paragraphs (g), (i), (j), and (l) of this final rule accordingly. Explanation of Changes Made to This AD We have revised this AD to identify the legal name of the manufacturer as published in the most recent type certificate data sheet for the affected airplane models. Costs of Compliance There are about 246 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. Conclusion We have carefully reviewed the available data, including the comment that has been received, and determined ESTIMATED COSTS Action Average labor rate per hour Work hours Inspection (required by AD 2005–15–08). Inspection required by this AD. pwalker on DSK8KYBLC1PROD with RULES Fleet cost $80 $240 per inspection cycle 69 $16,560 per inspection cycle. 3 $80 $240 per inspection cycle 70 $16,800 per inspection cycle. 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 15:59 Jan 19, 2010 Number of U.S.-registered airplanes 3 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. VerDate Nov<24>2008 Cost per airplane Jkt 220001 (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: ■ 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 39–14197 (70 FR 43020, July 26, 2005) and by adding the following new airworthiness directive (AD): ■ 2010–01–02 The Boeing Company: Amendment 39–16158. Docket No. FAA–2009–0636; Directorate Identifier 2009–NM–031–AD. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Effective Date (a) This AD becomes effective February 24, 2010. Affected ADs (b) This AD supersedes AD 2005–15–08, Amendment 39–14197. Applicability (c) This AD applies to The Boeing Company Model 747–100B SUD, –200B, –300, –400, and –400D series airplanes, certificated in any category; as identified in Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Unsafe Condition (e) This AD results from findings of cracking in fuselage stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame locations. We are issuing this AD to detect and correct fatigue cracking in the specified fuselage stringers, which, if left undetected, could result in fuselage skin cracking that reduces the structural integrity of the skin panel, and consequent 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. Requirements of AD 2005–15–08 Inspection for Certain Airplanes Subject to AD 2005–15–08 With New Service Bulletin (g) For airplanes identified in Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003, except airplanes identified in paragraph (j) of this AD, do a detailed inspection for cracking in fuselage stringers E:\FR\FM\20JAR1.SGM 20JAR1 Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame locations, in accordance with Part 1 of the Accomplishment Instructions in Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003; or Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009. Do the inspections at the applicable time specified in paragraph (g)(1) or (g)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles until the requirements of paragraph (k) or (l) of this AD are accomplished. No further action is required by this AD for any stringer that is repaired or modified in accordance with paragraph (k) or (l) of this AD. After the effective date of this AD, use only Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009. (1) For airplanes with 19,000 total flight cycles or less as of August 30, 2005 (the effective date of AD 2005–15–08): Prior to the accumulation of 8,000 total flight cycles, or within 2,000 flight cycles after August 30, 2005, whichever is later, not to exceed 20,000 total flight cycles. (2) For airplanes with more than 19,000 total flight cycles as of August 30, 2005: Within 1,000 flight cycles after August 30, 2005. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ New Requirements of This AD pwalker on DSK8KYBLC1PROD with RULES Inspection: Variable Number RS699 (h) For Model 747 airplane variable number RS699, do a detailed inspection for cracking in fuselage stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame locations, in accordance with Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009, at the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Before the accumulation of 8,000 total flight cycles. (2) Within 2,000 flight cycles after the effective date of this AD. (i) For Model 747 airplane variable number RS699, repeat the inspection specified in paragraph (h) of this AD thereafter at intervals not to exceed 3,000 flight cycles until the actions specified in paragraph (k) or (l) of this AD are accomplished. No further action is required by this AD for any stringer that is repaired or modified in accordance with paragraph (k) or (l) of this AD. Inspection: Group 4 Airplanes (j) For Group 4 airplanes as identified in Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009, do a detailed inspection for cracking in fuselage stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame locations, within 1,000 flight cycles after the effective date of VerDate Nov<24>2008 15:59 Jan 19, 2010 Jkt 220001 this AD. Do the actions in accordance with Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009. Repeat the inspection thereafter at intervals not to exceed 1,500 flight cycles until the actions specified in paragraph (k) or (l) of this AD are accomplished. No further action is required by this AD for any stringer that is repaired or modified in accordance with paragraph (k) or (l) of this AD. Repair (k) If cracking is found during any inspection required by this AD: Before further flight, repair the affected stringer in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003; or Boeing Service Bulletin 747– 53A2484, Revision 1, dated February 12, 2009. After the effective date of this AD, use only Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009. Accomplishing the repair terminates the repetitive inspections required by this AD for that repaired stringer location only. Optional Terminating Action (l) Installing new frame clips and new doublers, and repairing as applicable, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003; or Boeing Service Bulletin 747– 53A2484, Revision 1, dated February 12, 2009; terminates the repetitive inspections required by this AD for that modified stringer only. After the effective date of this AD, use only Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle 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: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6437; fax (425) 917–6590; or e-mail information to 9-ANMSeattle-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 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 2005–15–08, are PO 00000 Frm 00025 Fmt 4700 Sfmt 9990 3149 approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (n) You must use Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003; and Boeing Service Bulletin 747–53A2484, Revision 1, dated February 12, 2009; 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 747–53A2484, Revision 1, dated February 12, 2009, 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 747–53A2484, dated June 26, 2003, on August 30, 2005 (70 FR 43020, July 26, 2005). (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 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_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 17, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–30970 Filed 1–19–10; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\20JAR1.SGM 20JAR1

Agencies

[Federal Register Volume 75, Number 12 (Wednesday, January 20, 2010)]
[Rules and Regulations]
[Pages 3147-3149]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-30970]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0636; Directorate Identifier 2009-NM-031-AD; 
Amendment 39-16158; AD 2010-01-02]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747-100B SUD, 
-200B, -300, -400, and -400D 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 747-100B SUD, -200B, -300, -400, 
and -400D series airplanes. That AD currently requires repetitive 
inspections for cracking in fuselage stringers 8L, 8R, 10L, and 10R at 
body stations 460, 480, and 500 frame locations; and repair if 
necessary. This new AD requires revising the applicability to include 
an additional airplane, and reduces compliance times for the initial 
inspection and repetitive intervals for Model 747-400 series airplanes 
that have been converted to the large cargo freighter configuration. 
This AD results from findings of cracking in fuselage stringers 8L, 8R, 
10L, and 10R at body stations 460, 480, and 500 frame locations. We are 
issuing this AD to detect and correct fatigue cracking in certain 
fuselage stringers, which, if left undetected, could result in fuselage 
skin cracking that reduces the structural integrity of the skin panel, 
and consequent rapid depressurization of the airplane.

DATES: This AD becomes effective February 24, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 24, 
2010.
    The Director of the Federal Register previously approved the 
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2484, dated June 26, 2003, as of August 30, 2005 (70 FR 43020, July 
26, 2005).

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, Seattle Aircraft Certification Office, FAA, 1601 Lind 
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437; 
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 2005-15-08, amendment 
39-14197 (70 FR 43020, July 26, 2005). The existing AD applies to 
certain Model 747-100B SUD, -200B, -300, -400, and -400D series 
airplanes. That NPRM was published in the Federal Register on July 14, 
2009 (74 FR 33928). That NPRM proposed to require repetitive 
inspections for cracking in fuselage stringers 8L, 8R, 10L, and 10R at 
body stations 460, 480, and 500 frame locations; and repair if 
necessary.

Comments

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

Request for Change to Paragraph (g) of This AD

    Boeing requests a change to paragraph (g) of the NPRM. The NPRM 
proposes to require repeating the inspections specified in paragraph 
(g) at intervals not to exceed 3,000 flight cycles until the 
requirements of paragraph (l) of the proposed AD are accomplished. 
Boeing

[[Page 3148]]

states that accomplishing the repair specified in paragraph (k) of the 
proposed AD terminates the repetitive inspections required by paragraph 
(g). Boeing therefore requests that we revise paragraph (g) of the 
proposed AD to also refer to paragraph (k) as a terminating action.
    We partially agree. The repetitive inspections are terminated after 
accomplishment of paragraph (k) or (l) of this AD, but only at the 
stringer locations that are modified or repaired. We have revised 
paragraphs (g), (i), (j), and (l) of this final rule accordingly.

Explanation of Changes Made to This AD

    We have revised this AD to identify the legal name of the 
manufacturer as published in the most recent type certificate data 
sheet for the affected airplane models.

Conclusion

    We have carefully reviewed the available data, including the 
comment that has 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 246 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                           Number of U.S.-
              Action                  Work hours     Average labor    Cost per airplane      registered                      Fleet cost
                                                     rate per hour                            airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2005-15-              3             $80  $240 per inspection                69  $16,560 per inspection cycle.
 08).                                                                cycle.
Inspection required by this AD....               3             $80  $240 per inspection                70  $16,800 per inspection cycle.
                                                                     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 39-14197 (70 FR 43020, July 26, 2005) and by adding 
the following new airworthiness directive (AD):

2010-01-02 The Boeing Company: Amendment 39-16158. Docket No. FAA-
2009-0636; Directorate Identifier 2009-NM-031-AD.

Effective Date

    (a) This AD becomes effective February 24, 2010.

Affected ADs

    (b) This AD supersedes AD 2005-15-08, Amendment 39-14197.

Applicability

    (c) This AD applies to The Boeing Company Model 747-100B SUD, -
200B, -300, -400, and -400D series airplanes, certificated in any 
category; as identified in Boeing Service Bulletin 747-53A2484, 
Revision 1, dated February 12, 2009.

Subject

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

Unsafe Condition

    (e) This AD results from findings of cracking in fuselage 
stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 
frame locations. We are issuing this AD to detect and correct 
fatigue cracking in the specified fuselage stringers, which, if left 
undetected, could result in fuselage skin cracking that reduces the 
structural integrity of the skin panel, and consequent 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.

Requirements of AD 2005-15-08

Inspection for Certain Airplanes Subject to AD 2005-15-08 With New 
Service Bulletin

    (g) For airplanes identified in Boeing Alert Service Bulletin 
747-53A2484, dated June 26, 2003, except airplanes identified in 
paragraph (j) of this AD, do a detailed inspection for cracking in 
fuselage stringers

[[Page 3149]]

8L, 8R, 10L, and 10R at body station 460, 480, and 500 frame 
locations, in accordance with Part 1 of the Accomplishment 
Instructions in Boeing Alert Service Bulletin 747-53A2484, dated 
June 26, 2003; or Boeing Service Bulletin 747-53A2484, Revision 1, 
dated February 12, 2009. Do the inspections at the applicable time 
specified in paragraph (g)(1) or (g)(2) of this AD. Repeat the 
inspection thereafter at intervals not to exceed 3,000 flight cycles 
until the requirements of paragraph (k) or (l) of this AD are 
accomplished. No further action is required by this AD for any 
stringer that is repaired or modified in accordance with paragraph 
(k) or (l) of this AD. After the effective date of this AD, use only 
Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 
2009.
    (1) For airplanes with 19,000 total flight cycles or less as of 
August 30, 2005 (the effective date of AD 2005-15-08): Prior to the 
accumulation of 8,000 total flight cycles, or within 2,000 flight 
cycles after August 30, 2005, whichever is later, not to exceed 
20,000 total flight cycles.
    (2) For airplanes with more than 19,000 total flight cycles as 
of August 30, 2005: Within 1,000 flight cycles after August 30, 
2005.

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

New Requirements of This AD

Inspection: Variable Number RS699

    (h) For Model 747 airplane variable number RS699, do a detailed 
inspection for cracking in fuselage stringers 8L, 8R, 10L, and 10R 
at body station 460, 480, and 500 frame locations, in accordance 
with Boeing Service Bulletin 747-53A2484, Revision 1, dated February 
12, 2009, at the later of the times specified in paragraphs (h)(1) 
and (h)(2) of this AD.
    (1) Before the accumulation of 8,000 total flight cycles.
    (2) Within 2,000 flight cycles after the effective date of this 
AD.
    (i) For Model 747 airplane variable number RS699, repeat the 
inspection specified in paragraph (h) of this AD thereafter at 
intervals not to exceed 3,000 flight cycles until the actions 
specified in paragraph (k) or (l) of this AD are accomplished. No 
further action is required by this AD for any stringer that is 
repaired or modified in accordance with paragraph (k) or (l) of this 
AD.

Inspection: Group 4 Airplanes

    (j) For Group 4 airplanes as identified in Boeing Service 
Bulletin 747-53A2484, Revision 1, dated February 12, 2009, do a 
detailed inspection for cracking in fuselage stringers 8L, 8R, 10L, 
and 10R at body station 460, 480, and 500 frame locations, within 
1,000 flight cycles after the effective date of this AD. Do the 
actions in accordance with Boeing Service Bulletin 747-53A2484, 
Revision 1, dated February 12, 2009. Repeat the inspection 
thereafter at intervals not to exceed 1,500 flight cycles until the 
actions specified in paragraph (k) or (l) of this AD are 
accomplished. No further action is required by this AD for any 
stringer that is repaired or modified in accordance with paragraph 
(k) or (l) of this AD.

Repair

    (k) If cracking is found during any inspection required by this 
AD: Before further flight, repair the affected stringer in 
accordance with Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2484, dated June 26, 2003; or Boeing 
Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009. 
After the effective date of this AD, use only Boeing Service 
Bulletin 747-53A2484, Revision 1, dated February 12, 2009. 
Accomplishing the repair terminates the repetitive inspections 
required by this AD for that repaired stringer location only.

Optional Terminating Action

    (l) Installing new frame clips and new doublers, and repairing 
as applicable, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2484, dated 
June 26, 2003; or Boeing Service Bulletin 747-53A2484, Revision 1, 
dated February 12, 2009; terminates the repetitive inspections 
required by this AD for that modified stringer only. After the 
effective date of this AD, use only Boeing Service Bulletin 747-
53A2484, Revision 1, dated February 12, 2009.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle 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: Ivan Li, Aerospace 
Engineer, Airframe Branch, ANM-120S, Seattle Aircraft Certification 
Office (ACO), FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6437; fax (425) 917-6590; or e-mail 
information 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 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 2005-15-08, 
are approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (n) You must use Boeing Alert Service Bulletin 747-53A2484, 
dated June 26, 2003; and Boeing Service Bulletin 747-53A2484, 
Revision 1, dated February 12, 2009; 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 747-53A2484, 
Revision 1, dated February 12, 2009, 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-
53A2484, dated June 26, 2003, on August 30, 2005 (70 FR 43020, July 
26, 2005).
    (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 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_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 17, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-30970 Filed 1-19-10; 8:45 am]
BILLING CODE 4910-13-P
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