Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400, 747-400D, and 747SR Series Airplanes, 25926-25928 [06-4054]

Download as PDF 25926 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations and 1 CFR part 51. Contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, NJ 07606, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Federal Aviation Administration On May 5, 1999 (64 FR 15298, March 31, 1999), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2408, dated April 25, 1996. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, WA 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, WA 98055–4056; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 Examining the Docket [Docket No. FAA–2005–23358; Directorate Identifier 2005–NM–206–AD; Amendment 39–14576; AD 2006–09–06] You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Issued in Renton, Washington, on April 20, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–4053 Filed 5–2–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747–400, 747–400D, and 747SR Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. sroberts on PROD1PC70 with RULES AGENCY: Discussion SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747–100, –200, and –300 series airplanes. That AD currently requires repetitive inspections to detect cracking of certain lower lobe fuselage frames, and repair if necessary. This new AD retains all the requirements of the existing AD, and adds airplanes to the applicability. This AD results from reports indicating that fatigue cracks were found in lower lobe frames on the left side of the fuselage. We are issuing this AD to detect and correct fatigue cracking of certain lower lobe fuselage frames, which could lead to fatigue cracks in the fuselage skin, and consequent rapid decompression of the airplane. DATES: This AD becomes effective June 7, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 7, 2006. VerDate Aug<31>2005 18:14 May 02, 2006 Jkt 208001 The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 99–07–12, amendment 39–11097 (64 FR 15298, March 31, 1999). The existing AD applies to certain Boeing Model 747–100, –200, and –300 series airplanes. That NPRM was published in the Federal Register on December 20, 2005 (70 FR 75426). That NPRM proposed to retain all the requirements of AD 99–07–12, and add airplanes to the applicability. 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 Include Structural Repair Manual as Optional Terminating Action for Group 2 Airplanes Boeing requests that we revise paragraph (h)(1)(ii) of the NPRM to include the following sentence: ‘‘The Boeing 747–400 Structural Repair PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Manual, Subject 53–60–07, Repair 1 or 2 is one approved method.’’ Boeing states that these repairs are applicable to Group 2 airplanes, and are equivalent to the repairs in the Boeing 747 Structural Repair Manual (SRM), Subject 53–10– 04, Figure 67 or 90. Doing the actions in one of those figures is one approved method of repair as specified in paragraph (h)(1)(i) of the NPRM for Group 1 airplanes. We agree. Repair 1 or 2 of Subject 53– 60–07 of the Boeing 747–400 SRM constitutes equivalent repairs to those called out in paragraph (h)(1)(ii) of the AD. We have revised paragraph (h)(1)(ii) to refer to Boeing 747–400 SRM, Subject 53–60–07, Repair 1 or 2. Request To Revise Paragraph (i) of the NPRM to Include Terminating Action for Group 2 Airplanes Boeing requests that we revise paragraph (i) of the NPRM to include the action in NPRM Directorate Identifier 2005–NM–008–AD, Docket No. FAA–2005–22526 (70 FR 56860, September 29, 2005), as a terminating action for Group 2 airplanes. Boeing points out that this action is equivalent to the terminating action that AD 2005– 20–30, amendment 39–14327 (70 FR 59252, October 12, 2005), provides for Group 1 airplanes in the same paragraph. (Note: AD 99–07–12, which is superseded by this new AD, refers to AD 93–08–12, amendment 39–8559 (58 FR 27927, May 12, 1993). We superseded AD 93–08–12, with AD 2002–10–10, amendment 39–12756 (67 FR 36081, May 23, 2002), which we subsequently superseded with AD 2005–20–30—the reference that Boeing requests). We agree. We have revised paragraph (i) of the final rule to refer to AD 2006– 05–02, amendment 39–14499 (71 FR 10605, March 2, 2006), as an optional terminating action for Group 2 airplanes. AD 2006–05–02 is the final rule for NPRM Directorate Identifier 2005–NM–008–AD, Docket No. FAA– 2005–22526. Conclusion We have carefully reviewed the available data, including the comments that have been received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 681 airplanes of the affected design in the worldwide fleet. E:\FR\FM\03MYR1.SGM 03MYR1 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations This AD affects about 99 airplanes of U.S. registry. The actions that are required by AD 99–07–12 and retained in this AD take about 2 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of both the retained and new actions for U.S. operators is $12,870, or $130 per airplane, per inspection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. sroberts on PROD1PC70 with RULES 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. VerDate Aug<31>2005 18:14 May 02, 2006 Jkt 208001 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–11097 (64 FR 15298, March 31, 1999) and by adding the following new airworthiness directive (AD): I 2006–09–06 Boeing: Amendment 39–14576. Docket No. FAA–2005–23358; Directorate Identifier 2005–NM–206–AD. Effective Date (a) This AD becomes effective June 7, 2006. Affected ADs (b) This AD supersedes AD 99–07–12. Applicability (c) This AD applies to Boeing Model 747– 100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747–400, 747–400D, and 747SR series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2408, Revision 1, dated April 4, 2002. Unsafe Condition (d) This AD results from reports indicating that fatigue cracks were found in lower lobe frames on the left side of the fuselage. We are issuing this AD to detect and correct fatigue cracking of certain lower lobe fuselage frames, which could lead to fatigue cracks in the fuselage skin, and consequent rapid decompression of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of the Requirements of AD 99– 07–12, With Additional Information for Group 2 Airplanes Initial Inspections (f) For airplanes on which the initial detailed internal inspection of the Section 46 lower lobe frames required by paragraph (f)(2) or (i)(2) of AD 2005–20–30, amendment 39–14327, has not been accomplished: Perform a detailed visual inspection to detect cracking of the lower lobe fuselage frames from Body Station 1820 to Body Station 2100, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2408, dated April 25, 1996; or Boeing Alert Service Bulletin 747–53A2408, Revision 1, dated April 4, 2002; as applicable; at the later of the PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 25927 applicable times specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. (1) For all airplanes: Prior to the accumulation of 15,000 total flight cycles; or (2) For Group 1 airplanes identified in Revision 1 of the service bulletin: Within 1,500 flight cycles or 18 months after May 5, 1999 (the effective date of AD 99–07–12), whichever occurs first. (3) For Group 2 airplanes identified in Revision 1 of the service bulletin: Within 1,500 flight cycles or 18 months after the effective date of this AD, whichever occurs first. Note 1: Paragraphs (f)(2) and (i)(2) of AD 2005–20–30 require a detailed inspection to detect cracks in the Section 46 lower lobe frames, in accordance with Boeing Service Bulletin 747–53A2349, Revision 2, dated April 3, 2003. The initial inspection is required prior to the accumulation of 22,000 total flight cycles; or within 1,000 flight cycles after June 11, 1993 (the effective date of AD 93–08–12, amendment 39–8559), or November 16, 2005 (the effective date of AD 2005–20–30), depending on previous inspections accomplished; whichever occurs later. Note 2: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Repetitive Inspections (g) If no cracking is detected during the inspection required by paragraph (f) of this AD, repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. Corrective Actions (h) If any cracking is detected during any inspection required by paragraph (f) of this AD, prior to further flight, accomplish paragraphs (h)(1) and (h)(2) of this AD: (1) Within 20 inches of the crack location on the frame, perform a detailed inspection of the adjacent structure to detect cracking in accordance with Boeing Service Bulletin 747–53A2349, Revision 2, dated April 3, 2003. If any cracking is detected during any detailed inspection done in accordance with paragraph (f) or (h)(1) of this AD, prior to further flight, repair in accordance with paragraph (h)(1)(i) or (h)(1)(ii) of this AD, as applicable. (i) For Group 1 airplanes: Using a method approved in accordance with the procedures specified in paragraph (j) of this AD. The Boeing 747–400 Structural Repair Manual, Subject 53–10–04, Figure 67 or 90, is one approved method. (ii) For Group 2 airplanes: Using a method approved in accordance with the procedures specified in paragraph (j) of this AD. The Boeing 747–400 Structural Repair Manual, Subject 53–60–07, Repair 1 or 2, is one approved method. E:\FR\FM\03MYR1.SGM 03MYR1 25928 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations (2) Repeat the inspection required by paragraph (f) of this AD thereafter at intervals not to exceed 3,000 flight cycles. Optional Terminating Inspection (i) Accomplishment of the initial detailed inspection of the Section 46 lower lobe frames required by paragraph (f)(2) or (i)(2) of AD 2005–20–30 constitutes terminating action for the requirements of this AD only for airplanes identified in Boeing Alert Service Bulletin 747–53A2408, Revision 1, dated April 4, 2002, as Group 1 airplanes. Accomplishment of the initial detailed inspection of the Section 46 lower lobe frames required by paragraph (f) of AD 2006– 05–02 constitutes terminating action for the requirements of this AD only for airplanes identified in Boeing Alert Service Bulletin 747–53A2408, Revision 1, dated April 4, 2002, as Group 2 airplanes. sroberts on PROD1PC70 with RULES Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. (4) AMOCs approved previously in accordance with AD 99–07–12, are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (k) You must use Boeing Alert Service Bulletin 747–53A2408, dated April 25, 1996; or Boeing Alert Service Bulletin 747– 53A2408, Revision 1, dated April 4, 2002; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2408, Revision 1, dated April 4, 2002, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On May 5, 1999 (64 FR 15298, March 31, 1999), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2408, dated April 25, 1996. (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124– 2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or VerDate Aug<31>2005 18:14 May 02, 2006 Jkt 208001 at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http://www. archives.gov/federal_register/code_of_federal _regulations/ibr_locations.html. Issued in Renton, Washington, on April 20, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–4054 Filed 5–2–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23762; Directorate Identifier 2005–NM–226–AD; Amendment 39–14580; AD 2006–09–09] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This AD requires repetitive inspections for cracking in the skin, the bulkhead outer chord, and the strap of the bulkhead outer chord at station (STA) 1725.5; and repair if necessary. This AD also provides for repairs, which are optional for airplanes on which no cracking is found, that terminate certain inspections. This AD results from reports of cracking in the skin panel common to stringer 7R and aft of the STA 1725.5 butt splice, and in the strap of the bulkhead outer chord at STA 1725.5. We are issuing this AD to detect and correct cracking in the skin, the bulkhead outer chord, or the strap of the bulkhead outer chord in this area, which could progress into surrounding areas and result in reduced structural integrity of the support structure for the vertical or horizontal stabilizer and subsequent loss of control of the airplane. This AD becomes effective June 7, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 7, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket DATES: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6428; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to all Boeing Model 767 airplanes. That NPRM was published in the Federal Register on February 2, 2006 (71 FR 5623). That NPRM proposed to require repetitive inspections for cracking in the skin, the bulkhead outer chord, and the strap of the bulkhead outer chord at station (STA) 1725.5; and repair if necessary. That NPRM also proposed to provide for repairs, which are optional for airplanes on which no cracking is found, that terminate certain inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. The commenter, Boeing, supports the NPRM. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 905 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. E:\FR\FM\03MYR1.SGM 03MYR1

Agencies

[Federal Register Volume 71, Number 85 (Wednesday, May 3, 2006)]
[Rules and Regulations]
[Pages 25926-25928]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-4054]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23358; Directorate Identifier 2005-NM-206-AD; 
Amendment 39-14576; AD 2006-09-06]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-300, 747-400, 747-400D, and 747SR 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 Boeing Model 747-100, -200, and -300 
series airplanes. That AD currently requires repetitive inspections to 
detect cracking of certain lower lobe fuselage frames, and repair if 
necessary. This new AD retains all the requirements of the existing AD, 
and adds airplanes to the applicability. This AD results from reports 
indicating that fatigue cracks were found in lower lobe frames on the 
left side of the fuselage. We are issuing this AD to detect and correct 
fatigue cracking of certain lower lobe fuselage frames, which could 
lead to fatigue cracks in the fuselage skin, and consequent rapid 
decompression of the airplane.

DATES: This AD becomes effective June 7, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of June 7, 2006.
    On May 5, 1999 (64 FR 15298, March 31, 1999), the Director of the 
Federal Register approved the incorporation by reference of Boeing 
Alert Service Bulletin 747-53A2408, dated April 25, 1996.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, WA 
98124-2207, for service information identified in this AD.

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

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 99-07-12, amendment 39-
11097 (64 FR 15298, March 31, 1999). The existing AD applies to certain 
Boeing Model 747-100, -200, and -300 series airplanes. That NPRM was 
published in the Federal Register on December 20, 2005 (70 FR 75426). 
That NPRM proposed to retain all the requirements of AD 99-07-12, and 
add airplanes to the applicability.

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 Include Structural Repair Manual as Optional Terminating 
Action for Group 2 Airplanes

    Boeing requests that we revise paragraph (h)(1)(ii) of the NPRM to 
include the following sentence: ``The Boeing 747-400 Structural Repair 
Manual, Subject 53-60-07, Repair 1 or 2 is one approved method.'' 
Boeing states that these repairs are applicable to Group 2 airplanes, 
and are equivalent to the repairs in the Boeing 747 Structural Repair 
Manual (SRM), Subject 53-10-04, Figure 67 or 90. Doing the actions in 
one of those figures is one approved method of repair as specified in 
paragraph (h)(1)(i) of the NPRM for Group 1 airplanes.
    We agree. Repair 1 or 2 of Subject 53-60-07 of the Boeing 747-400 
SRM constitutes equivalent repairs to those called out in paragraph 
(h)(1)(ii) of the AD. We have revised paragraph (h)(1)(ii) to refer to 
Boeing 747-400 SRM, Subject 53-60-07, Repair 1 or 2.

Request To Revise Paragraph (i) of the NPRM to Include Terminating 
Action for Group 2 Airplanes

    Boeing requests that we revise paragraph (i) of the NPRM to include 
the action in NPRM Directorate Identifier 2005-NM-008-AD, Docket No. 
FAA-2005-22526 (70 FR 56860, September 29, 2005), as a terminating 
action for Group 2 airplanes. Boeing points out that this action is 
equivalent to the terminating action that AD 2005-20-30, amendment 39-
14327 (70 FR 59252, October 12, 2005), provides for Group 1 airplanes 
in the same paragraph. (Note: AD 99-07-12, which is superseded by this 
new AD, refers to AD 93-08-12, amendment 39-8559 (58 FR 27927, May 12, 
1993). We superseded AD 93-08-12, with AD 2002-10-10, amendment 39-
12756 (67 FR 36081, May 23, 2002), which we subsequently superseded 
with AD 2005-20-30--the reference that Boeing requests).
    We agree. We have revised paragraph (i) of the final rule to refer 
to AD 2006-05-02, amendment 39-14499 (71 FR 10605, March 2, 2006), as 
an optional terminating action for Group 2 airplanes. AD 2006-05-02 is 
the final rule for NPRM Directorate Identifier 2005-NM-008-AD, Docket 
No. FAA-2005-22526.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 681 airplanes of the affected design in the 
worldwide fleet.

[[Page 25927]]

This AD affects about 99 airplanes of U.S. registry.
    The actions that are required by AD 99-07-12 and retained in this 
AD take about 2 work hours per airplane, at an average labor rate of 
$65 per work hour. Based on these figures, the estimated cost of both 
the retained and new actions for U.S. operators is $12,870, or $130 per 
airplane, per inspection cycle.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-11097 (64 FR 15298, March 31, 1999) and by adding 
the following new airworthiness directive (AD):

2006-09-06 Boeing: Amendment 39-14576. Docket No. FAA-2005-23358; 
Directorate Identifier 2005-NM-206-AD.

Effective Date

    (a) This AD becomes effective June 7, 2006.

Affected ADs

    (b) This AD supersedes AD 99-07-12.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B 
SUD, 747-200B, 747-300, 747-400, 747-400D, and 747SR series 
airplanes, certificated in any category, as identified in Boeing 
Alert Service Bulletin 747-53A2408, Revision 1, dated April 4, 2002.

Unsafe Condition

    (d) This AD results from reports indicating that fatigue cracks 
were found in lower lobe frames on the left side of the fuselage. We 
are issuing this AD to detect and correct fatigue cracking of 
certain lower lobe fuselage frames, which could lead to fatigue 
cracks in the fuselage skin, and consequent rapid decompression of 
the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of the Requirements of AD 99-07-12, With Additional 
Information for Group 2 Airplanes

Initial Inspections

    (f) For airplanes on which the initial detailed internal 
inspection of the Section 46 lower lobe frames required by paragraph 
(f)(2) or (i)(2) of AD 2005-20-30, amendment 39-14327, has not been 
accomplished: Perform a detailed visual inspection to detect 
cracking of the lower lobe fuselage frames from Body Station 1820 to 
Body Station 2100, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2408, dated 
April 25, 1996; or Boeing Alert Service Bulletin 747-53A2408, 
Revision 1, dated April 4, 2002; as applicable; at the later of the 
applicable times specified in paragraph (f)(1), (f)(2), or (f)(3) of 
this AD.
    (1) For all airplanes: Prior to the accumulation of 15,000 total 
flight cycles; or
    (2) For Group 1 airplanes identified in Revision 1 of the 
service bulletin: Within 1,500 flight cycles or 18 months after May 
5, 1999 (the effective date of AD 99-07-12), whichever occurs first.
    (3) For Group 2 airplanes identified in Revision 1 of the 
service bulletin: Within 1,500 flight cycles or 18 months after the 
effective date of this AD, whichever occurs first.


    Note 1:
    Paragraphs (f)(2) and (i)(2) of AD 2005-20-30 require a detailed 
inspection to detect cracks in the Section 46 lower lobe frames, in 
accordance with Boeing Service Bulletin 747-53A2349, Revision 2, 
dated April 3, 2003. The initial inspection is required prior to the 
accumulation of 22,000 total flight cycles; or within 1,000 flight 
cycles after June 11, 1993 (the effective date of AD 93-08-12, 
amendment 39-8559), or November 16, 2005 (the effective date of AD 
2005-20-30), depending on previous inspections accomplished; 
whichever occurs later.


    Note 2:
    For the purposes of this AD, a detailed inspection is: ``An 
intensive examination of a specific item, installation, or assembly 
to detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at an 
intensity deemed appropriate. Inspection aids such as mirror, 
magnifying lenses, etc., may be necessary. Surface cleaning and 
elaborate procedures may be required.''

Repetitive Inspections

    (g) If no cracking is detected during the inspection required by 
paragraph (f) of this AD, repeat the inspection thereafter at 
intervals not to exceed 3,000 flight cycles.

Corrective Actions

    (h) If any cracking is detected during any inspection required 
by paragraph (f) of this AD, prior to further flight, accomplish 
paragraphs (h)(1) and (h)(2) of this AD:
    (1) Within 20 inches of the crack location on the frame, perform 
a detailed inspection of the adjacent structure to detect cracking 
in accordance with Boeing Service Bulletin 747-53A2349, Revision 2, 
dated April 3, 2003. If any cracking is detected during any detailed 
inspection done in accordance with paragraph (f) or (h)(1) of this 
AD, prior to further flight, repair in accordance with paragraph 
(h)(1)(i) or (h)(1)(ii) of this AD, as applicable.
    (i) For Group 1 airplanes: Using a method approved in accordance 
with the procedures specified in paragraph (j) of this AD. The 
Boeing 747-400 Structural Repair Manual, Subject 53-10-04, Figure 67 
or 90, is one approved method.
    (ii) For Group 2 airplanes: Using a method approved in 
accordance with the procedures specified in paragraph (j) of this 
AD. The Boeing 747-400 Structural Repair Manual, Subject 53-60-07, 
Repair 1 or 2, is one approved method.

[[Page 25928]]

    (2) Repeat the inspection required by paragraph (f) of this AD 
thereafter at intervals not to exceed 3,000 flight cycles.

Optional Terminating Inspection

    (i) Accomplishment of the initial detailed inspection of the 
Section 46 lower lobe frames required by paragraph (f)(2) or (i)(2) 
of AD 2005-20-30 constitutes terminating action for the requirements 
of this AD only for airplanes identified in Boeing Alert Service 
Bulletin 747-53A2408, Revision 1, dated April 4, 2002, as Group 1 
airplanes. Accomplishment of the initial detailed inspection of the 
Section 46 lower lobe frames required by paragraph (f) of AD 2006-
05-02 constitutes terminating action for the requirements of this AD 
only for airplanes identified in Boeing Alert Service Bulletin 747-
53A2408, Revision 1, dated April 4, 2002, as Group 2 airplanes.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane.
    (4) AMOCs approved previously in accordance with AD 99-07-12, 
are approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (k) You must use Boeing Alert Service Bulletin 747-53A2408, 
dated April 25, 1996; or Boeing Alert Service Bulletin 747-53A2408, 
Revision 1, dated April 4, 2002; as applicable; to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2408, Revision 1, dated April 4, 2002, in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) On May 5, 1999 (64 FR 15298, March 31, 1999), the Director 
of the Federal Register approved the incorporation by reference of 
Boeing Alert Service Bulletin 747-53A2408, dated April 25, 1996.
    (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_ locations. html.

    Issued in Renton, Washington, on April 20, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-4054 Filed 5-2-06; 8:45 am]
BILLING CODE 4910-13-P