Airworthiness Directives; Boeing Model 747-200B, 747-200C, 747-200F, 747-300, 747-400, and 747SP Series Airplanes, 6400-6402 [E6-1679]

Download as PDF 6400 Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules purposes of demonstration or support of a presentation, are subject to inspection. We cannot assume responsibility for coordinating the receipt, transfer, transport, storage, set-up, safety, or timely arrival of any personal belongings or items used for demonstration or support of a presentation. Signed at Washington, DC, February 1, 2006. Teresa C. Lasseter, Administrator, Farm Service Agency, and Executive Vice-President, Commodity Credit Corporation. [FR Doc. 06–1193 Filed 2–6–06; 8:56 am] BILLING CODE 3410–05–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23819; Directorate Identifier 2005–NM–223–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–200B, 747–200C, 747–200F, 747–300, 747–400, and 747SP Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). rmajette on PROD1PC67 with PROPOSALS1 AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 747–200B, 747– 200C, 747–200F, 747–300, 747–400, and 747SP series airplanes. This proposed AD would require doing a detailed inspection of the left and right longeron extension fittings, and corrective action if necessary. This proposed AD results from cracking found in the longeron extension fitting at body station 1480 due to accidental damage during production. We are proposing this AD to detect and correct cracking in the longeron extension fitting, which could result in rapid decompression of the airplane and possible in-flight breakup of the airplane fuselage. DATES: We must receive comments on this proposed AD by March 27, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov VerDate Aug<31>2005 15:24 Feb 07, 2006 Jkt 208001 and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Nicholas Kusz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6432; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–23819; Directorate Identifier 2005–NM–223–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http:// dms.dot.gov. Examining the Docket You may examine the 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received a report indicating that a crack was found in the longeron extension fitting at body station 1480, on a Boeing Model 747–400 series airplane. (The airplane had accumulated 12,676 total flight cycles.) Investigation revealed that the crack occurred where a drill start had been made accidentally during airplane production. Cracking in the longeron extension fitting could extend and lead to reduced structural integrity of the bulkhead structure at body station 1480. This condition, if not corrected, could result in rapid decompression of the airplane and possible in-flight breakup of the airplane fuselage. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 747–53A2515, dated October 20, 2005. The service bulletin describes procedures for doing a detailed inspection of the left and right longeron extension fittings for damage and corrective action if necessary. The corrective action includes the following: • Repairing any damage found to a longeron extension fitting, which includes removing any visibly damaged material, doing a high frequency eddy current inspection of the cut edge of the gusset for cracks and removing any damage if necessary, and making an insurance cut to remove any possible crack tip. • If damage cannot be repaired in accordance with the service bulletin, replacing the damaged longeron extension fitting with a new longeron extension fitting. The service bulletin refers to Boeing Alert Service Bulletin 747–53A2390, dated July 31, 1997, or Revision 1, dated July 6, 2000, as an additional source of service information for replacing a damaged longeron fitting with a new longeron extension fitting. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described E:\FR\FM\08FEP1.SGM 08FEP1 Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules previously. The proposed AD would also require sending the inspection results to the Manager, Seattle Aircraft Certification Office, FAA, if applicable. Interim Action This is considered to be interim action. The inspection reports that would be required by this proposed AD will enable the FAA to obtain better insight into the nature, cause, and extent of the cracking. Once we have received the inspection reports, we may consider further rulemaking to include additional airplanes. Costs of Compliance There are about 126 airplanes of the affected design in the worldwide fleet. This AD affects about 25 airplanes of U.S. registry The proposed inspection would take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $1,625, or $65 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. rmajette on PROD1PC67 with PROPOSALS1 Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; VerDate Aug<31>2005 15:24 Feb 07, 2006 Jkt 208001 2. Is not a ‘‘significant rule’’ under the 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 proposed 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2006–23819; Directorate Identifier 2005–NM–223–AD. Comments Due Date (a) The FAA must receive comments on this AD action by March 27, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747– 200B, 747–200C, 747–200F, 747–300, 747– 400, and 747SP series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747–53A2515, dated October 20, 2005. Unsafe Condition (d) This AD results from cracking found in the longeron extension fitting at body station 1480 due to accidental damage during production. We are issuing this AD to detect and correct cracking in the longeron extension fitting, which could result in rapid decompression of the airplane and possible in-flight breakup of the airplane fuselage. 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. Detailed Inspection (f) At the applicable compliance time specified in paragraph (f)(1) or (f)(2) of this PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 6401 AD, do a detailed inspection of the left and right longeron extension fittings for damage, and before further flight do the corrective action if applicable, by accomplishing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2515, dated October 20, 2005. Note 1: Boeing Alert Service Bulletin 747– 53A2515, dated October 20, 2005, refers to Boeing Alert Service Bulletin 747–53A2390, dated July 31, 1997, or Revision 1, dated July 6, 2000, as an additional source of service information for replacing a damaged longeron fitting with a new longeron extension fitting. (1) For airplanes that have accomplished the inspection of the splice area for cracking as specified in Boeing Alert Service Bulletin 747–53A2390, dated July 31, 1997, or Revision 1, dated July 6, 2000: Inspect in accordance with paragraph (f) of this AD before the airplane has accumulated 10,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever is later. (2) For airplanes that have not accomplished the inspection of the splice area for cracking as specified in Boeing Alert Service Bulletin 747–53A2390, dated July 31, 1997, or Revision 1, dated July 6, 2000: Inspect in accordance with paragraph (f) of this AD before the airplane has accumulated 10,000 total flight cycles, or within 250 flight cycles after the effective date of this AD, whichever is later. Reporting Requirement (g) If any damage is found to any longeron extension fitting during the inspection required by paragraph (f) of this AD: Submit a report of the findings of the inspection required by paragraph (f) of this AD to the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; fax (425) 917–6590, at the applicable time specified in paragraph (g)(1) or (g)(2) of this AD. The report must include the airplane serial number and line number, identify the operator of the affected airplane, specify whether the cracking is within the limits given in the service bulletin, and specify if the cracking was found on the left or right or both longeron extension fittings. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 20 days after the inspection. (2) If the inspection was accomplished prior to the effective date of this AD: Submit the report within 20 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. E:\FR\FM\08FEP1.SGM 08FEP1 6402 Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules (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, and the approval must specifically refer to this AD. Issued in Renton, Washington, on January 27, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–1679 Filed 2–7–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23817; Directorate Identifier 2005–NM–176–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 777 Airplanes Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking. rmajette on PROD1PC67 with PROPOSALS1 AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 777 airplanes. This proposed AD would require repetitive inspections for corrosion or missing corrosion inhibiting compound of the fuselage skin under the forward and aft wing-to-body fairings for certain airplanes, or the fuselage skin under the forward wing-to-body fairings only for other airplanes; and corrective action if necessary. The proposed AD would also provide an optional preventive modification of the wing-to-body fairing panels, which would terminate the repetitive inspections. This proposed AD results from several reports indicating that significant levels of corrosion were found on the external surface of the fuselage skin under the forward and aft wing-to-body fairings. We are proposing this AD to detect and correct corrosion, and prevent subsequent fatigue cracks, on the fuselage skin under the forward and aft wing-to-body fairings, which could result in rapid decompression of the airplane. VerDate Aug<31>2005 15:24 Feb 07, 2006 Jkt 208001 We must receive comments on this proposed AD by March 27, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6443; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: DATES: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–23817; Directorate Identifier 2005–NM–176–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http:// dms.dot.gov. Examining the Docket You may examine the 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received several reports indicating that significant levels of corrosion were found on the external surface of the fuselage skin under the forward and aft wing-to-body fairings. The depth of the corrosion was up to 67 percent of the original skin thickness, and corrosion was found on some airplanes as early as four years after original delivery of the airplane. During an evaluation done by the manufacturer it was determined that water can enter the wing-to-body area through the seal and drain holes in the fairings, causing corrosion. Inadequate or missing corrosion-inhibiting compound (CIC) on the fuselage skin also contributes to early corrosion. This condition, if not corrected, could result in corrosion and subsequent fatigue cracks on the fuselage skin under the forward and aft wing-to-body fairings, and consequent rapid decompression of the airplane. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 777–53A0044, dated July 28, 2005. The service bulletin describes procedures for repetitive detailed inspections for corrosion or missing CIC of the fuselage skin under the forward and aft wing-to-body fairings for Group 1 airplanes, or the fuselage skin under the forward wing-tobody fairings only for Group 2 airplanes; and corrective action if necessary. The corrective action includes performing a detailed inspection to determine the extent of the corrosion, removing any corrosion found, and applying CIC. The service bulletin also describes procedures for an optional preventive modification of the wing-to-body fairing panels. The modification involves applying sealant to certain fasteners, removing and replacing the seal, installing scuppers, and applying CIC on the fuselage skin. Accomplishing the E:\FR\FM\08FEP1.SGM 08FEP1

Agencies

[Federal Register Volume 71, Number 26 (Wednesday, February 8, 2006)]
[Proposed Rules]
[Pages 6400-6402]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1679]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23819; Directorate Identifier 2005-NM-223-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-200B, 747-200C, 747-
200F, 747-300, 747-400, and 747SP Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 747-200B, 747-200C, 747-200F, 747-300, 747-
400, and 747SP series airplanes. This proposed AD would require doing a 
detailed inspection of the left and right longeron extension fittings, 
and corrective action if necessary. This proposed AD results from 
cracking found in the longeron extension fitting at body station 1480 
due to accidental damage during production. We are proposing this AD to 
detect and correct cracking in the longeron extension fitting, which 
could result in rapid decompression of the airplane and possible in-
flight breakup of the airplane fuselage.

DATES: We must receive comments on this proposed AD by March 27, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Nicholas Kusz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6432; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
23819; Directorate Identifier 2005-NM-223-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the 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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    We have received a report indicating that a crack was found in the 
longeron extension fitting at body station 1480, on a Boeing Model 747-
400 series airplane. (The airplane had accumulated 12,676 total flight 
cycles.) Investigation revealed that the crack occurred where a drill 
start had been made accidentally during airplane production. Cracking 
in the longeron extension fitting could extend and lead to reduced 
structural integrity of the bulkhead structure at body station 1480. 
This condition, if not corrected, could result in rapid decompression 
of the airplane and possible in-flight breakup of the airplane 
fuselage.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2515, dated 
October 20, 2005. The service bulletin describes procedures for doing a 
detailed inspection of the left and right longeron extension fittings 
for damage and corrective action if necessary. The corrective action 
includes the following:
     Repairing any damage found to a longeron extension 
fitting, which includes removing any visibly damaged material, doing a 
high frequency eddy current inspection of the cut edge of the gusset 
for cracks and removing any damage if necessary, and making an 
insurance cut to remove any possible crack tip.
     If damage cannot be repaired in accordance with the 
service bulletin, replacing the damaged longeron extension fitting with 
a new longeron extension fitting.
    The service bulletin refers to Boeing Alert Service Bulletin 747-
53A2390, dated July 31, 1997, or Revision 1, dated July 6, 2000, as an 
additional source of service information for replacing a damaged 
longeron fitting with a new longeron extension fitting.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described

[[Page 6401]]

previously. The proposed AD would also require sending the inspection 
results to the Manager, Seattle Aircraft Certification Office, FAA, if 
applicable.

Interim Action

    This is considered to be interim action. The inspection reports 
that would be required by this proposed AD will enable the FAA to 
obtain better insight into the nature, cause, and extent of the 
cracking. Once we have received the inspection reports, we may consider 
further rulemaking to include additional airplanes.

Costs of Compliance

    There are about 126 airplanes of the affected design in the 
worldwide fleet. This AD affects about 25 airplanes of U.S. registry 
The proposed inspection would take about 1 work hour per airplane, at 
an average labor rate of $65 per work hour. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $1,625, or $65 
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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2006-23819; Directorate Identifier 2005-NM-
223-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 27, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-200B, 747-200C, 747-
200F, 747-300, 747-400, and 747SP series airplanes, certificated in 
any category; as identified in Boeing Alert Service Bulletin 747-
53A2515, dated October 20, 2005.

Unsafe Condition

    (d) This AD results from cracking found in the longeron 
extension fitting at body station 1480 due to accidental damage 
during production. We are issuing this AD to detect and correct 
cracking in the longeron extension fitting, which could result in 
rapid decompression of the airplane and possible in-flight breakup 
of the airplane fuselage.

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.

Detailed Inspection

    (f) At the applicable compliance time specified in paragraph 
(f)(1) or (f)(2) of this AD, do a detailed inspection of the left 
and right longeron extension fittings for damage, and before further 
flight do the corrective action if applicable, by accomplishing all 
the applicable actions specified in the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2515, dated October 20, 
2005.


    Note 1: Boeing Alert Service Bulletin 747-53A2515, dated October 
20, 2005, refers to Boeing Alert Service Bulletin 747-53A2390, dated 
July 31, 1997, or Revision 1, dated July 6, 2000, as an additional 
source of service information for replacing a damaged longeron 
fitting with a new longeron extension fitting.


    (1) For airplanes that have accomplished the inspection of the 
splice area for cracking as specified in Boeing Alert Service 
Bulletin 747-53A2390, dated July 31, 1997, or Revision 1, dated July 
6, 2000: Inspect in accordance with paragraph (f) of this AD before 
the airplane has accumulated 10,000 total flight cycles, or within 
1,000 flight cycles after the effective date of this AD, whichever 
is later.
    (2) For airplanes that have not accomplished the inspection of 
the splice area for cracking as specified in Boeing Alert Service 
Bulletin 747-53A2390, dated July 31, 1997, or Revision 1, dated July 
6, 2000: Inspect in accordance with paragraph (f) of this AD before 
the airplane has accumulated 10,000 total flight cycles, or within 
250 flight cycles after the effective date of this AD, whichever is 
later.

Reporting Requirement

    (g) If any damage is found to any longeron extension fitting 
during the inspection required by paragraph (f) of this AD: Submit a 
report of the findings of the inspection required by paragraph (f) 
of this AD to the Manager, Seattle Aircraft Certification Office 
(ACO), FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056; fax (425) 917-6590, at the applicable 
time specified in paragraph (g)(1) or (g)(2) of this AD. The report 
must include the airplane serial number and line number, identify 
the operator of the affected airplane, specify whether the cracking 
is within the limits given in the service bulletin, and specify if 
the cracking was found on the left or right or both longeron 
extension fittings. Under the provisions of the Paperwork Reduction 
Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and 
Budget (OMB) has approved the information collection requirements 
contained in this AD and has assigned OMB Control Number 2120-0056.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 20 days after the inspection.
    (2) If the inspection was accomplished prior to the effective 
date of this AD: Submit the report within 20 days after the 
effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.

[[Page 6402]]

    (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, and the approval must specifically refer to this 
AD.

    Issued in Renton, Washington, on January 27, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-1679 Filed 2-7-06; 8:45 am]
BILLING CODE 4910-13-P