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[Federal Register Volume 78, Number 206 (Thursday, October 24, 2013)]
[Proposed Rules]
[Pages 63431-63433]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-24975]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0866; Directorate Identifier 2013-NM-131-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This proposed AD was prompted by reports of cracks 
found in the aft support fitting, the rear spar upper chord, and the 
rear spar web. This proposed AD would require repetitive inspections 
for cracking of the aft support fitting for the main landing gear (MLG) 
beam, and the rear spar upper chord and rear spar web in the area of 
rear spar station (RSS) 224.14; and repair if necessary. We are 
proposing this AD to detect and correct such cracks, which could grow 
and result in a fuel leak and possible fire.

DATES: We must receive comments on this proposed AD by December 9, 
2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://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, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, 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 http://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: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-
917-6440; fax: 425-917-6590; email: nancy.marsh@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-2013-0866; 
Directorate Identifier 2013-NM-131-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 http://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 five reports of cracks found in the aft support 
fitting for the MLG beam, and the rear spar upper chord and rear spar 
web in the area of rear spar station (RSS) 224.14. One report was of a 
vertical crack found in the rear spar web, along with cracks in the aft 
support fitting and rear spar upper chord. A second report indicated 
cracks found in two holes in the rear spar upper chord and rear spar 
web. A third report was of a crack in the rear spar upper chord that 
extended downward to the edge of the vertical flange and upward to the 
horizontal flange. The affected airplanes had accumulated between 
42,988 and 66,572 total flight hours, and between 29,015

[[Page 63432]]

and 60,238 total flight cycles. Analysis shows that cracks in the aft 
support fitting, rear spar web, and rear spar upper chord are caused by 
operating load fatigue. Such cracks, if not corrected, could grow and 
result in a fuel leak and possible fire.

Related Rulemaking

    AD 2005-18-08, Amendment 39-14248 (70 FR 52899, September 6, 2005) 
(``AD 2005-18-08''), affects certain Model 737-100, -200, -200C, and -
300 series airplanes. AD 2005-18-08 requires--as one of two options for 
corrective action--replacement of the support fitting of the MLG beam 
in accordance with Boeing Special Attention Service Bulletin 737-57-
1216. This replacement also terminates the inspections required by AD 
2005-18-08. The compliance times for certain inspections specified in 
this proposed AD depend on accomplishment of that optional action in AD 
2005-18-08.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 737-57-1318, 
dated May 15, 2013. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2013-0866.

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 the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information identified previously, except as discussed 
below.

Differences Between the Proposed AD and the Service Information

    Boeing Special Attention Service Bulletin 737-57-1318, dated May 
15, 2013, specifies to contact the manufacturer for instructions on how 
to inspect certain airplanes, and how to repair cracks detected on all 
airplanes, but this proposed AD would require that those actions be 
done in one of the following ways:
     In accordance with 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.

Costs of Compliance

    We estimate that this proposed AD affects 353 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost         Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  Up to 86 work-hours x             $0   Up to $7,310 per     Up to $2,580,430
                                  $85 per hour = $7,310                  inspection cycle.    per inspection
                                  per inspection cycle.                                       cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2013-0866; Directorate Identifier 
2013-NM-131-AD.

(a) Comments Due Date

    We must receive comments by December 9, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracks found in the aft 
support fitting for the main

[[Page 63433]]

landing gear (MLG) beam, and the rear spar upper chord and rear spar 
web. We are issuing this AD to detect and correct such cracks, which 
could grow and result in a fuel leak and possible fire.

(f) Compliance

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

(g) Inspections: Group 1

    For airplanes identified in Group 1 of Boeing Special Attention 
Service Bulletin 737-57-1318, dated May 15, 2013: At the applicable 
time specified in paragraph 1.E., ``Compliance,'' of Boeing Special 
Attention Service Bulletin 737-57-1318, dated May 15, 2013, except 
as required by paragraph (i) of this AD, do inspections and 
applicable corrective actions using a method approved in accordance 
with the procedures specified in paragraph (j) of this AD.

(h) Inspection: Groups 2-7

    For airplanes identified in Groups 2 through 7 of Boeing Special 
Attention Service Bulletin 737-57-1318, dated May 15, 2013: At the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 
2013, except as required by paragraph (i) of this AD, do high 
frequency eddy current inspections to detect cracking of the aft 
support fitting for the MLG beam, and the rear spar upper chord and 
rear spar web in the area of rear spar station 224.14, as 
applicable, in accordance with Option 1, 2, or 3 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-57-1318, dated May 15, 2013.
    (1) If no crack is found, repeat the inspection thereafter at 
the time specified in paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 737-57-1318, dated May 15, 2013, 
as applicable. Accomplishment of the inspection of the 12 fastener 
holes (locations 1-12) in accordance with Option 2, Action 3; or 
Option 3, Action 3; as specified in note (b) of tables 2 through 5 
of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 737-57-1318, dated May 15, 2013, terminates only 
the corresponding inspections that include note (b) in the ``Repeat 
Interval'' column of the applicable table.
    (2) If any crack is found during any inspection required by this 
paragraph, repair before further flight using a method approved in 
accordance with the procedures specified in paragraph (j) of this 
AD.

(i) Exception to Service Information Specifications

    Where Boeing Special Attention Service Bulletin 737-57-1318, 
dated May 15, 2013, specifies a compliance time ``after the original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.

(j) Alternative Methods of Compliance (AMOCs)

    (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 emailed 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), which 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.

(k) Related Information

    (1) For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6440; fax: 425-917-6590; email: 
nancy.marsh@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; 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.

    Issued in Renton, Washington, on October 17, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-24975 Filed 10-23-13; 8:45 am]
BILLING CODE 4910-13-P
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