Airworthiness Directives; The Boeing Company Model 777 Airplanes, 38072-38074 [2011-16368]

Download as PDF 38072 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules (n) As of the effective date of this AD, no person may install any rudder identified in Table 4 of this AD on any airplane. FAA AD Differences srobinson on DSK4SPTVN1PROD with PROPOSALS Note 1: This AD differs from the MCAI and/or service information as follows: No differences. [FR Doc. 2011–16367 Filed 6–28–11; 8:45 am] BILLING CODE 4910–13–P Other FAA AD Provisions (o) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective 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: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (p) Refer to MCAI EASA Airworthiness Directive 2010–0144, dated July 16, 2010; and Airbus Mandatory Service Bulletins A310–55–2049 and A300–55–6048, both dated March 16, 2010; for related information. VerDate Mar<15>2010 16:52 Jun 28, 2011 Jkt 223001 Issued in Renton, Washington, on June 16, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0644; Directorate Identifier 2010–NM–265–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 777 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD would require repetitive detailed inspection and high frequency eddy current (HFEC) inspections for cracks of the wing center section (WCS) spanwise beams, and repair if necessary. This proposed AD was prompted by reports of cracks found in the web pockets of the WCS spanwise beams. We are proposing this AD to detect and correct cracking in the WCS spanwise beams, which could result in reduced structural integrity of the wings. DATES: We must receive comments on this proposed AD by August 15, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced SUMMARY: PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: (425) 917–6452; Fax: (425) 917–6590; e-mail: duong.tran@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2011–0644; Directorate Identifier 2010– NM–265–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of cracking in the wing center section (WSC) spanwise beams. Two operators reported finding a crack in the web pockets of WCS spanwise beams on two airplanes. In the first report, metallurgical testing showed the cracks were the result of fatigue from reverse bending (diagonal tension buckling). If cracking at multiple locations occurs in multiple spanwise beams, the WCS spanwise beams might not be able E:\FR\FM\29JNP1.SGM 29JNP1 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules to carry design loads. This could result in the loss of the WCS load path. We are proposing this AD to detect and correct cracking in the WCS spanwise beams, which could result in reduced structural integrity of the wings. Relevant Service Information We reviewed Boeing Alert Service Bulletin 777–57A0087, dated November 11, 2010. Boeing Alert Service Bulletin 777–57A0087, dated November 11, 2010 describes procedures for a detailed inspection and high frequency eddy current (HFEC) inspection for cracks in the WCS web pockets of spanwise beams numbers 1, 2, and 3; a detailed inspection for cracks of any previously installed repairs; and repair including doing a related investigation action and all applicable corrective actions, if necessary. Boeing Alert Service Bulletin 777–57A0087, dated November 11, 2010 also describes methods for repairing cracking by following procedures in Appendix A, B, or C or by contacting Boeing for repair instructions, depending on the size and location of the crack. The related investigative action is doing a HFEC inspection for cracking around the edge of the cutout, for which the corrective action is contacting Boeing. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of this same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and the Service Information.’’ 38073 Differences Between the Proposed AD and the Service Information Although Boeing Alert Service Bulletin 777–57A0087, dated November 11, 2010, specifies to contact the manufacturer for instructions on how to repair certain conditions, this proposed AD would require repairing those conditions in one of the following ways: • Per a repair method approved by the FAA or an FAA authorized representative, or • Using data to meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 160 airplanes of U.S. registry and 920 airplanes of international registry (including domestic). We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Detailed inspection and high frequency eddy current inspection of spanwise beams. 50 work-hours × $85 per hour = $4,250 per inspection cycle. srobinson on DSK4SPTVN1PROD with PROPOSALS We have received no definitive data that would enable us to provide cost estimates for the on-condition repair actions specified in this proposed AD. We have no way of determining the number of aircraft that might need these repairs. 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 Mar<15>2010 16:52 Jun 28, 2011 Jkt 223001 Cost per product Cost on U.S. operators $4,250 per inspection cycle ..... $680,000 = 160 airplanes × $4,250 per inspection cycle. Parts cost $0 Regulatory Findings The Proposed Amendment We 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 this 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), (3) Will not affect intrastate aviation in Alaska, and (4) 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 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 FAA amends § 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA– 2011–0644; Directorate Identifier 2010– NM–265–AD. Comments Due Date (a) We must receive comments by August 15, 2011. Affected ADs (b) None. Applicability (c) This AD applies to The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes, certificated in any category, as identified in E:\FR\FM\29JNP1.SGM 29JNP1 38074 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules Boeing Alert Service Bulletin 777–57A0087, dated November 11, 2010. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 57: Wings. Unsafe Condition (e) This AD was prompted by reports of cracks found in the web pockets of the wing center section spanwise beams. We are issuing this AD to detect and correct cracking in the WCS spanwise beams, which could result in reduced structural integrity of the wings. Compliance (f) Comply with this AD within the compliance times specified, unless already done. srobinson on DSK4SPTVN1PROD with PROPOSALS Repetitive Inspections and Corrective Actions (g) At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD, do a detailed inspection and a high frequency eddy current inspection for cracks of the web pockets of the WCS spanwise beams numbers 1, 2, and 3; and a detailed inspection for cracks of any previously installed repairs; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–57A0087, dated November 11, 2010. Repeat the inspections thereafter at intervals not to exceed 8,000 flight cycles. (1) Before the accumulation of 8,000 total flight cycles. (2) Within 6,000 flight cycles, or 1,125 days, after the effective date of this AD, whichever occurs first. (h) If any cracking is found during any inspection required by paragraph (g) of this AD, before further flight, repair the crack, including related investigative actions and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–57A0087, dated November 11, 2010; except where Boeing Alert Service Bulletin 777–57A0087, dated November 11, 2010, specifies to contact Boeing for repair instructions, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. VerDate Mar<15>2010 16:52 Jun 28, 2011 Jkt 223001 (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that 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. Related Information (j) For more information about this AD, contact Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; phone: (425) 917–6452; fax: (425) 917– 6590; e-mail: duong.tran@faa.gov. (k) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on June 17, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–16368 Filed 6–28–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0645; Directorate Identifier 2010–NM–009–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 747–100, 747–100B, 747–200B, 747–200C, 747–200F, 747– 300, 747SR, and 747SP Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Model 747 series airplanes. The existing AD currently requires repetitive inspections for cracks of the fuselage skin lap splice between body station (BS) 400 and BS 520 at stringers S–6L and S–6R, and repair if necessary. This SUMMARY: PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 proposed AD would shorten the interval for the repetitive inspections, require modification for certain airplanes, and require certain post-modification inspections for other airplanes. This proposed AD results from reports of multiple adjacent cracks on an airplane, and a recent fleet-wide evaluation of widespread fatigue damage of skin lap joints, which indicated the need for revised procedures and reduced compliance times. We are proposing this AD to detect and correct cracking of the fuselage skin lap splice between BS 400 and BS 520 at stringers S–6L and S–6R. Such cracking could result in sudden loss of cabin pressurization and the inability of the fuselage to withstand fail-safe loads. DATES: We must receive comments on this proposed AD by August 15, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the E:\FR\FM\29JNP1.SGM 29JNP1

Agencies

[Federal Register Volume 76, Number 125 (Wednesday, June 29, 2011)]
[Proposed Rules]
[Pages 38072-38074]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-16368]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0644; Directorate Identifier 2010-NM-265-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 777 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD would require repetitive 
detailed inspection and high frequency eddy current (HFEC) inspections 
for cracks of the wing center section (WCS) spanwise beams, and repair 
if necessary. This proposed AD was prompted by reports of cracks found 
in the web pockets of the WCS spanwise beams. We are proposing this AD 
to detect and correct cracking in the WCS spanwise beams, which could 
result in reduced structural integrity of the wings.

DATES: We must receive comments on this proposed AD by August 15, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Duong Tran, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: (425) 917-
6452; Fax: (425) 917-6590; e-mail: duong.tran@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2011-0644; 
Directorate Identifier 2010-NM-265-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received reports of cracking in the wing center section 
(WSC) spanwise beams. Two operators reported finding a crack in the web 
pockets of WCS spanwise beams on two airplanes. In the first report, 
metallurgical testing showed the cracks were the result of fatigue from 
reverse bending (diagonal tension buckling).
    If cracking at multiple locations occurs in multiple spanwise 
beams, the WCS spanwise beams might not be able

[[Page 38073]]

to carry design loads. This could result in the loss of the WCS load 
path. We are proposing this AD to detect and correct cracking in the 
WCS spanwise beams, which could result in reduced structural integrity 
of the wings.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 777-57A0087, dated 
November 11, 2010. Boeing Alert Service Bulletin 777-57A0087, dated 
November 11, 2010 describes procedures for a detailed inspection and 
high frequency eddy current (HFEC) inspection for cracks in the WCS web 
pockets of spanwise beams numbers 1, 2, and 3; a detailed inspection 
for cracks of any previously installed repairs; and repair including 
doing a related investigation action and all applicable corrective 
actions, if necessary. Boeing Alert Service Bulletin 777-57A0087, dated 
November 11, 2010 also describes methods for repairing cracking by 
following procedures in Appendix A, B, or C or by contacting Boeing for 
repair instructions, depending on the size and location of the crack. 
The related investigative action is doing a HFEC inspection for 
cracking around the edge of the cutout, for which the corrective action 
is contacting Boeing.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of this same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.''

Differences Between the Proposed AD and the Service Information

    Although Boeing Alert Service Bulletin 777-57A0087, dated November 
11, 2010, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, this proposed AD would require repairing 
those conditions in one of the following ways:
     Per a repair method approved by the FAA or an FAA 
authorized representative, or
     Using data to meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 160 airplanes of U.S. 
registry and 920 airplanes of international registry (including 
domestic).
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                             Parts                              Cost on U.S.
              Action                      Labor cost          cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Detailed inspection and high        50 work-hours x $85           $0  $4,250 per            $680,000 = 160
 frequency eddy current inspection   per hour = $4,250                 inspection cycle.     airplanes x $4,250
 of spanwise beams.                  per inspection cycle.                                   per inspection
                                                                                             cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repair actions specified in this 
proposed AD. We have no way of determining the number of aircraft that 
might need these repairs.

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 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 this 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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

The Boeing Company: Docket No. FAA-2011-0644; Directorate Identifier 
2010-NM-265-AD.

Comments Due Date

    (a) We must receive comments by August 15, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 777-200, -200LR, 
-300, -300ER, and 777F series airplanes, certificated in any 
category, as identified in

[[Page 38074]]

Boeing Alert Service Bulletin 777-57A0087, dated November 11, 2010.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 57: Wings.

Unsafe Condition

    (e) This AD was prompted by reports of cracks found in the web 
pockets of the wing center section spanwise beams. We are issuing 
this AD to detect and correct cracking in the WCS spanwise beams, 
which could result in reduced structural integrity of the wings.

Compliance

    (f) Comply with this AD within the compliance times specified, 
unless already done.

Repetitive Inspections and Corrective Actions

    (g) At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD, do a detailed inspection and a high frequency 
eddy current inspection for cracks of the web pockets of the WCS 
spanwise beams numbers 1, 2, and 3; and a detailed inspection for 
cracks of any previously installed repairs; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
57A0087, dated November 11, 2010. Repeat the inspections thereafter 
at intervals not to exceed 8,000 flight cycles.
    (1) Before the accumulation of 8,000 total flight cycles.
    (2) Within 6,000 flight cycles, or 1,125 days, after the 
effective date of this AD, whichever occurs first.
    (h) If any cracking is found during any inspection required by 
paragraph (g) of this AD, before further flight, repair the crack, 
including related investigative actions and all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-57A0087, dated 
November 11, 2010; except where Boeing Alert Service Bulletin 777-
57A0087, dated November 11, 2010, specifies to contact Boeing for 
repair instructions, before further flight, repair the cracking 
using a method approved in accordance with the procedures specified 
in paragraph (i) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that 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.

Related Information

    (j) For more information about this AD, contact Duong Tran, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; phone: (425) 917-6452; fax: (425) 917-6590; e-mail: 
duong.tran@faa.gov.
    (k) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You 
may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on June 17, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-16368 Filed 6-28-11; 8:45 am]
BILLING CODE 4910-13-P
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