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[Federal Register Volume 78, Number 191 (Wednesday, October 2, 2013)]
[Proposed Rules]
[Pages 60804-60807]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-24040]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0836; Directorate Identifier 2013-NM-126-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 supersede airworthiness directive (AD) 2005-07-
12 that applies to certain The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes. AD 2005-07-12 requires 
detailed and eddy current inspections to detect cracking of the frame 
web around the cutout for the doorstop intercostal strap at the aft 
side of the station (STA) 291.5 frame at stringer 16R, and corrective 
action if necessary. Since we issued AD 2005-07-12, we received reports 
of new findings of cracking at various locations of the STA 277 to STA 
291.5 frames and intercostals, including webs, chords, clips, and shear 
ties, between stringers 7R and 17R. This proposed AD would add new 
inspections for cracking at the forward galley door cutout, and 
corrective actions if necessary. This proposed AD would also reduce a 
certain inspection threshold required by AD 2005-07-12. We are 
proposing this AD to detect and correct fatigue cracking of the aft 
frame and frame support structure of the forward galley door, which 
could result in a severed fuselage frame web, rapid decompression of 
the airplane, and possible loss of the forward galley door.

DATES: We must receive comments on this proposed AD by November 18, 
2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 60805]]

     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 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 Ave. 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: Alan Pohl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6450; fax: 425-917-6590; email: alan.pohl@faa.gov.

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-2013-0836; 
Directorate Identifier 2013-NM-126-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

    On March 25, 2005, we issued AD 2005-07-12, Amendment 39-14036 (70 
FR 17596, April 7, 2005), for certain The Boeing Company Model 737-100, 
-200, -300, -400, and -500 series airplanes. AD 2005-07-12 requires 
repetitive detailed and eddy current inspections to detect cracking of 
the frame web around the cutout for the doorstop intercostal strap at 
the aft side of STA 291.5 frame at stringer 16R, and corrective actions 
if necessary. We issued AD 2005-07-12 to detect and correct fatigue 
cracking of the aft frame and frame support structure of the forward 
galley door.

Actions Since AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 
2005) Was Issued

    Since we issued AD 2005-07-12, Amendment 39-14036 (70 FR 17596, 
April 7, 2005) Boeing has received 24 reports of cracking of the STA 
291.5 frame web around the doorstop intercostal strap cutout at 
stringer 16R. There have been 23 reports of cracks propagating down 
from the lower radius of the cutout on airplanes that had accumulated 
between 35,597 and 68,133 total flight cycles. Boeing also received one 
report of a crack propagating outboard from the upper radius through 
two countersunk fastener locations on an airplane that had accumulated 
31,611 total flight cycles. In addition, Boeing received reports of 
cracking in other areas of the forward galley door cutout that are 
determined to be safety related.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 737-53A1241, Revision 1, 
dated June 11, 2013. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2013-0836.

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

    Although this proposed AD does not explicitly restate the 
requirements of AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 
7, 2005) this proposed AD would retain all of the requirements of AD 
2005-07-12. Those requirements are referenced in the service 
information identified previously, which, in turn, is referenced in 
paragraph (h) of this proposed AD. For certain airplanes, this proposed 
AD would reduce the compliance threshold for a certain inspection. This 
proposed AD would also require accomplishing the actions identified in 
the service information identified previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.''
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Differences Between the Proposed AD and the Service Information

    Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 
11, 2013, 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:
     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 419 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 60806]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                  Labor cost           Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained from AD    2 work-hours x $85  None...............  $170 per            $71,230 per
 2005-07-12, Amendment            per hour = $170                          inspection cycle.   inspection cycle.
 39[dash]14036 (70 FR 17596)].    per inspection
                                  cycle.
Inspections [new proposed        40 work-hours x     None...............  $3,400 per          $1,424,600 per
 action].                         $85 per hour =                           inspection cycle.   inspection cycle.
                                  $3,400 per
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in the service 
information.

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 proposed 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),
    (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 removing airworthiness directive (AD) 
2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005), and adding 
the following new AD:

The Boeing Company: Docket No. FAA-2013-0836; Directorate Identifier 
2013-NM-126-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by November 18, 
2013.

(b) Affected ADs

    This AD supersedes AD 2005-07-12, Amendment 39-14036 (70 FR 
17596, April 7, 2005).

(c) Applicability

    This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, as identified in Boeing 
Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of new findings of cracking at 
various locations of the stations (STA) 277 to STA 291.5 frames and 
intercostals, including webs, chords, clips, and shear ties, between 
stringers 7R and 17R. We are issuing this AD to detect and correct 
fatigue cracking of the aft frame and frame support structure of the 
forward galley door, which could result in a severed fuselage frame 
web, rapid decompression of the airplane, and possible loss of the 
forward galley door.

(f) Compliance

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

(g) Group 1 Airplanes: Inspections and Corrective Actions

    For airplanes identified as Group 1 in Boeing Alert Service 
Bulletin 737-53A1241, Revision 1, dated June 11, 2013: Within 120 
days after the effective date of this AD, do inspections for 
cracking from STA 277 to STA 328, stringer 7R to 17R of the forward 
galley door cutout, using a method approved in accordance with the 
procedures specified in paragraph (l) of this AD. Do all applicable 
corrective actions before further flight using a method approved in 
accordance with the procedures specified in paragraph (l) of this 
AD.

(h) Group 2 and Group 3 Airplanes: Inspections and Corrective Actions

    (1) For airplanes identified as Group 2 and Group 3 in Boeing 
Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013: 
Except as provided by paragraph (j)(2) of this AD, at the applicable 
times specified in tables 1 and 2 in paragraph 1.E, ``Compliance,'' 
of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 
11, 2013, do detailed and surface HFEC inspections, as applicable, 
for cracking in the forward galley door cutout, in accordance with 
Part 2 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-53A1241, Revision 1, dated June 11, 2013. Repeat the 
detailed and surface HFEC inspections thereafter at the applicable 
intervals specified in tables 1 and 2 in paragraph 1.E, 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1241, 
Revision 1, dated June 11, 2013. If any crack is found, before 
further flight, do all applicable corrective actions in accordance 
with Part 2 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, 
except as required by paragraph (j)(1) of this AD. Doing the repair 
in accordance with Part 2 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 
11, 2013, terminates the repetitive inspections required by this 
paragraph for the repaired area only.
    (2) Removal and replacement of a cracked part, in accordance 
with Part 2 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, does 
not terminate the

[[Page 60807]]

repetitive inspections required by paragraph (h)(1) of this AD.

(i) Optional Terminating Action

    Accomplishment of the preventive modification on the STA 291.5 
frame web, in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 
1, dated June 11, 2013, terminates the repetitive inspections 
required by paragraph (h)(1) of this AD for the area that is common 
to the preventive modification.

(j) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 737-53A1241, Revision 1, 
dated June 11, 2013, specifies to contact Boeing for a corrective 
action: Before further flight, do the applicable action using a 
method approved in accordance with the procedures specified in 
paragraph (l) of this AD.
    (2) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, 
specifies a compliance time ``after the date on Revision 1 of this 
service bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (h)(1) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Alert Service Bulletin 
737-53A1241, dated June 13, 2002, which is not incorporated by 
reference in this AD.

(l) 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 paragraph (m) 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) 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.
    (4) AMOCs approved for the actions specified in AD 2005-07-12, 
Amendment 39-14036 (70 FR 17596, April 7, 2005), are approved as 
AMOCs for the corresponding provisions of this AD.

(m) Related Information

    (1) For more information about this AD, contact Alan Pohl, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: 
alan.pohl@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 Ave. SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington on September 25, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-24040 Filed 10-1-13; 8:45 am]
BILLING CODE 4910-13-P
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