Airworthiness Directives; The Boeing Company Model 737-900ER Series Airplanes, 48281-48283 [2010-19695]

Download as PDF 48281 Proposed Rules Federal Register Vol. 75, No. 153 Tuesday, August 10, 2010 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0764; Directorate Identifier 2009–NM–260–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 737–900ER Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Model 737–900ER series airplanes. This proposed AD would require doing a one-time general visual inspection for a keyway in two fuel tank access door cutouts, and related investigative and corrective actions if necessary. This proposed AD results from reports of cracks emanating from the keyway of the fuel tank access hole. We are proposing this AD to detect and correct such cracking, which could result in the loss of the lower wing skin load path and consequent structural failure of the wing. DATES: We must receive comments on this proposed AD by September 24, 2010. SUMMARY: 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. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 ADDRESSES: VerDate Mar<15>2010 15:16 Aug 09, 2010 Jkt 220001 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. personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion 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 ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: We have received reports of cracks, ranging from 0.02 to 0.380 inch in length emanating from the keyway of the fuel tank access hole on the wing lower skin between wing rib numbers 8 and 9 on Model 777–200LR and 777– 300ER series airplanes. The fuel tank access door at this location has a fuel measuring stick installed, and the keyway is used to ensure that the fuel measuring stick is oriented correctly when the fuel tank access door is installed. The crack is believed to be the result of fatigue due to the position of the keyway. The lower wing skins on Model 737–900ER series airplanes have fuel tank access holes with the same configuration as that of the affected fuel tank access holes on Model 777–300ER series airplanes. The affected fuel tank access holes on the Model 737–900ER series airplanes are located between ribs 4 and 5, between wing stations 180 and 204.25. These fuel tank access holes are for fuel tank access doors 531BB and 631BB. Although cracks have not yet been reported on any Model 737–900ER series airplanes, damage tolerance analysis shows potential for Model 737– 900ER series airplanes lower wing skins to crack at the noted locations. This condition, if not corrected, could result in the loss of the lower wing skin load path and consequent structural failure of the wing. Comments Invited Relevant Service Information We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0764; Directorate Identifier 2009–NM–260–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 We have reviewed Boeing Alert Service Bulletin 737–57A1308, Revision 1, dated October 1, 2009. The service bulletin describes procedures for a general visual inspection for a keyway in the fuel tank access door cutout on the left and right wings, and related investigative and corrective actions if necessary. The related investigative action is a high frequency eddy current inspection for cracking of the keyway. The corrective actions include changing the profile of the keyway for the fuel tank access door cutout, repairing any cracking of the keyway of the access door cutout, and contacting Boeing for certain repair instructions and doing the repair. Examining the AD Docket PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\10AUP1.SGM 10AUP1 48282 Federal Register / Vol. 75, No. 153 / Tuesday, August 10, 2010 / Proposed Rules FAA’s Determination and Requirements of This Proposed AD We are proposing this AD because we evaluated all relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Difference Between the Proposed AD and Service Bulletin.’’ Difference Between the Proposed AD and Service Bulletin Boeing Alert Service Bulletin 737– 57A1308, Revision 1, dated October 1, 2009, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: Using a method that we approve; or Using data that 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. Other Relevant Rulemaking The lower wing skins on Model 777– 200LR and 777–300ER series airplanes have fuel tank access holes with the same configuration as those of the affected fuel tank access holes on the Model 737–900ER airplanes. Therefore, Model 777–200LR and 777–300ER series airplanes may be subject to the identified unsafe condition. We are considering similar rulemaking related to the identified unsafe condition for certain Model 777–200LR and 777– 300ER series airplanes. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 Costs of Compliance We estimate that this proposed AD would affect 30 airplanes of U.S. registry. We also estimate that it would take 3 work-hours per product to comply with this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD to the U.S. operators to be $7,650, or $255 per product. 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. VerDate Mar<15>2010 15:16 Aug 09, 2010 Jkt 220001 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. Comments Due Date (a) We must receive comments by September 24, 2010. Regulatory Findings Unsafe Condition (e) This AD results from reports of cracks emanating from the keyway of the fuel tank access hole. The Federal Aviation Administration is issuing this AD to detect and correct such cracking, which could result in the loss of the lower wing skin load path and consequent structural failure of the wing. 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), 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. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: The Boeing Company: Docket No. FAA– 2010–0764; Directorate Identifier 2009– NM–260–AD. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Affected ADs (b) None. Applicability (c) This AD applies to The Boeing Company Model 737–900ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737–57A1308, Revision 1, dated October 1, 2009. Subject (d) Air Transport Association (ATA) of America Code 57: Wings. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection (g) Before the accumulation of 7,500 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later, do a one-time general visual inspection for a keyway in the fuel tank access door cutouts 531BB and 631BB, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–57A1308, Revision 1, dated October 1, 2009 (‘‘the service bulletin’’). Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ (1) If both access door cutouts do not have a keyway, no further action is required by this AD. (2) If any access door has a keyway, before the accumulation of 7,500 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later, do a high frequency eddy current (HFEC) inspection for cracking of the keyway, in accordance with the Accomplishment Instructions of the service bulletin. (i) If no cracking is found during the HFEC inspection, before further flight, modify the profile of the keyway of the fuel tank access door cutout, in accordance with the E:\FR\FM\10AUP1.SGM 10AUP1 Federal Register / Vol. 75, No. 153 / Tuesday, August 10, 2010 / Proposed Rules Accomplishment Instructions of the service bulletin. (ii) If any cracking is found and the crack is 0.030 inch or less in length, before further flight repair the keyway, in accordance with the Accomplishment Instructions of the service bulletin. (iii) If any cracking is found and the crack is greater than 0.030 inch in length, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (h) of this AD Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590. Information may be e-mailed to: 9–ANM– Seattle-ACO–AMOC–Request@faa.gov. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) 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. Issued in Renton, Washington, on July 30, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–19695 Filed 8–9–10; 8:45 am] BILLING CODE 4910–13–P PENSION BENEFIT GUARANTY CORPORATION Introduction Pension Benefit Guaranty Corporation (PBGC) administers the pension plan termination insurance program under title IV of the Employee Retirement Income Security Act of 1974 (ERISA). Under ERISA section 4002(b)(3), PBGC has authority to adopt, amend, and repeal regulations to carry out the purposes of title IV. wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1 29 CFR Parts 4062 and 4063 RIN 1212–AB20 Liability for Termination of SingleEmployer Plans; Treatment of Substantial Cessation of Operations Pension Benefit Guaranty Corporation. ACTION: Proposed rule. AGENCY: Background of Proposed Rule ERISA section 4062(e) provides for reporting of and liability for SUMMARY: VerDate Mar<15>2010 15:16 Aug 09, 2010 Jkt 220001 certain substantial cessations of operations by employers that maintain single-employer plans. PBGC proposes to amend its current regulation on Liability for Termination of SingleEmployer Plans to provide guidance on the applicability and enforcement of ERISA section 4062(e). DATES: Comments must be submitted on or before October 12, 2010. ADDRESSES: Comments, identified by Regulation Identifier Number (RIN) 1212–AB20, may be submitted by any of the following methods: • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the Web site instructions for submitting comments. • E-mail: reg.comments@pbgc.gov. • Fax: 202–326–4224. • Mail or Hand Delivery: Legislative and Regulatory Department, Pension Benefit Guaranty Corporation, 1200 K Street, NW., Washington, DC 20005– 4026. All submissions must include the Regulation Identifier Number for this rulemaking (RIN 1212–AB20). Comments received, including personal information provided, will be posted to https://www.pbgc.gov. Copies of comments may also be obtained by writing to Disclosure Division, Office of the General Counsel, Pension Benefit Guaranty Corporation, 1200 K Street, NW., Washington, DC 20005–4026, or calling 202–326–4040 during normal business hours. (TTY and TDD users may call the Federal relay service tollfree at 1–800–877–8339 and ask to be connected to 202–326–4040.) FOR FURTHER INFORMATION CONTACT: Catherine B. Klion, Manager, or Deborah C. Murphy, Attorney, Regulatory and Policy Division, Legislative and Regulatory Department, Pension Benefit Guaranty Corporation, 1200 K Street, NW., Washington, DC 20005–4026; 202– 326–4024. (TTY/TDD users may call the Federal relay service toll-free at 1–800– 877–8339 and ask to be connected to 202–326–4024.) SUPPLEMENTARY INFORMATION: ERISA section 4062(e) provides that ‘‘[i]f an employer ceases operations at a PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 48283 facility in any location and, as a result of such cessation of operations, more than 20 percent of the total number of his employees who are participants under a plan established and maintained by him are separated from employment, the employer shall be treated with respect to that plan as if he were a substantial employer under a plan under which more than one employer makes contributions and the provisions of [ERISA sections] 4063, 4064, and 4065 shall apply.’’ ERISA section 4063(a) requires the plan administrator of a multiple employer plan (that is, a singleemployer plan with at least two contributing sponsors that are not under common control) to notify PBGC within 60 days after a substantial employer withdraws from the plan, and section 4063(b) and (c) makes the withdrawn employer liable to provide a bond or escrow in a specified amount for five years from the date of withdrawal, to be applied—if the plan terminates within that period—against the plan’s underfunding. Section 4063(e) allows PBGC to waive this liability if there is an appropriate indemnity agreement among contributing sponsors of the plan, and ERISA section 4067 authorizes PBGC to make alternative arrangements for satisfaction of liability under sections 4062 and 4063. (ERISA sections 4064 and 4065 deal with plan termination liability and annual reports by plan administrators.) The method described in section 4063(b) for computing the amount of liability focuses on relative amounts of contributions by more than one employer and is thus impracticable for calculating liability triggered by an event involving a plan of a single employer under section 4062(e). However, section 4063(b) provides that PBGC ‘‘may also determine the liability on any other equitable basis prescribed by [PBGC] in regulations.’’ Pursuant to that authority, on June 16, 2006 (at 71 FR 34819), PBGC published a final rule providing a formula for computing liability under section 4063(b) when there is an event described in section 4062(e). The formula provided by the 2006 rule apportions to an employer affected by an event under section 4062(e) a fraction of plan termination liability based on the number of participants affected by the event. Over the next three-and-a-half years, PBGC resolved 37 cases under section 4062(e) through negotiated settlements valued at nearly $600 million, providing protection to over 65,000 participants. E:\FR\FM\10AUP1.SGM 10AUP1

Agencies

[Federal Register Volume 75, Number 153 (Tuesday, August 10, 2010)]
[Proposed Rules]
[Pages 48281-48283]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-19695]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 75, No. 153 / Tuesday, August 10, 2010 / 
Proposed Rules

[[Page 48281]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0764; Directorate Identifier 2009-NM-260-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 737-900ER 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Model 737-900ER series airplanes. This proposed AD would 
require doing a one-time general visual inspection for a keyway in two 
fuel tank access door cutouts, and related investigative and corrective 
actions if necessary. This proposed AD results from reports of cracks 
emanating from the keyway of the fuel tank access hole. We are 
proposing this AD to detect and correct such cracking, which could 
result in the loss of the lower wing skin load path and consequent 
structural failure of the wing.

DATES: We must receive comments on this proposed AD by September 24, 
2010.

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 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6440; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0764; 
Directorate Identifier 2009-NM-260-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 cracks, ranging from 0.02 to 0.380 inch 
in length emanating from the keyway of the fuel tank access hole on the 
wing lower skin between wing rib numbers 8 and 9 on Model 777-200LR and 
777-300ER series airplanes. The fuel tank access door at this location 
has a fuel measuring stick installed, and the keyway is used to ensure 
that the fuel measuring stick is oriented correctly when the fuel tank 
access door is installed. The crack is believed to be the result of 
fatigue due to the position of the keyway. The lower wing skins on 
Model 737-900ER series airplanes have fuel tank access holes with the 
same configuration as that of the affected fuel tank access holes on 
Model 777-300ER series airplanes. The affected fuel tank access holes 
on the Model 737-900ER series airplanes are located between ribs 4 and 
5, between wing stations 180 and 204.25. These fuel tank access holes 
are for fuel tank access doors 531BB and 631BB. Although cracks have 
not yet been reported on any Model 737-900ER series airplanes, damage 
tolerance analysis shows potential for Model 737-900ER series airplanes 
lower wing skins to crack at the noted locations. This condition, if 
not corrected, could result in the loss of the lower wing skin load 
path and consequent structural failure of the wing.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 737-57A1308, 
Revision 1, dated October 1, 2009. The service bulletin describes 
procedures for a general visual inspection for a keyway in the fuel 
tank access door cutout on the left and right wings, and related 
investigative and corrective actions if necessary. The related 
investigative action is a high frequency eddy current inspection for 
cracking of the keyway. The corrective actions include changing the 
profile of the keyway for the fuel tank access door cutout, repairing 
any cracking of the keyway of the access door cutout, and contacting 
Boeing for certain repair instructions and doing the repair.

[[Page 48282]]

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously, except as discussed under 
``Difference Between the Proposed AD and Service Bulletin.''

Difference Between the Proposed AD and Service Bulletin

    Boeing Alert Service Bulletin 737-57A1308, Revision 1, dated 
October 1, 2009, specifies to contact the manufacturer for instructions 
on how to repair certain conditions, but this proposed AD would require 
repairing those conditions in one of the following ways:
    Using a method that we approve; or
    Using data that 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.

Other Relevant Rulemaking

    The lower wing skins on Model 777-200LR and 777-300ER series 
airplanes have fuel tank access holes with the same configuration as 
those of the affected fuel tank access holes on the Model 737-900ER 
airplanes. Therefore, Model 777-200LR and 777-300ER series airplanes 
may be subject to the identified unsafe condition. We are considering 
similar rulemaking related to the identified unsafe condition for 
certain Model 777-200LR and 777-300ER series airplanes.

Costs of Compliance

    We estimate that this proposed AD would affect 30 airplanes of U.S. 
registry. We also estimate that it would take 3 work-hours per product 
to comply with this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of this 
proposed AD to the U.S. operators to be $7,650, or $255 per product.

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), 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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 AD:

The Boeing Company: Docket No. FAA-2010-0764; Directorate Identifier 
2009-NM-260-AD.

Comments Due Date

    (a) We must receive comments by September 24, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 737-900ER series 
airplanes, certificated in any category, as identified in Boeing 
Alert Service Bulletin 737-57A1308, Revision 1, dated October 1, 
2009.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Unsafe Condition

    (e) This AD results from reports of cracks emanating from the 
keyway of the fuel tank access hole. The Federal Aviation 
Administration is issuing this AD to detect and correct such 
cracking, which could result in the loss of the lower wing skin load 
path and consequent structural failure of the wing.

Compliance

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

Inspection

    (g) Before the accumulation of 7,500 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later, do a one-time general visual inspection for 
a keyway in the fuel tank access door cutouts 531BB and 631BB, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-57A1308, Revision 1, dated October 1, 2009 
(``the service bulletin'').

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

    (1) If both access door cutouts do not have a keyway, no further 
action is required by this AD.
    (2) If any access door has a keyway, before the accumulation of 
7,500 total flight cycles, or within 1,000 flight cycles after the 
effective date of this AD, whichever occurs later, do a high 
frequency eddy current (HFEC) inspection for cracking of the keyway, 
in accordance with the Accomplishment Instructions of the service 
bulletin.
    (i) If no cracking is found during the HFEC inspection, before 
further flight, modify the profile of the keyway of the fuel tank 
access door cutout, in accordance with the

[[Page 48283]]

Accomplishment Instructions of the service bulletin.
    (ii) If any cracking is found and the crack is 0.030 inch or 
less in length, before further flight repair the keyway, in 
accordance with the Accomplishment Instructions of the service 
bulletin.
    (iii) If any cracking is found and the crack is greater than 
0.030 inch in length, before further flight, repair the crack using 
a method approved in accordance with the procedures specified in 
paragraph (h) of this AD

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., 
Renton, Washington 98057-3356; telephone (425) 917-6440; fax (425) 
917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Request@faa.gov.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) 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.

    Issued in Renton, Washington, on July 30, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-19695 Filed 8-9-10; 8:45 am]
BILLING CODE 4910-13-P

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