
[Federal Register Volume 79, Number 112 (Wednesday, June 11, 2014)]
[Proposed Rules]
[Pages 33484-33486]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-13609]


 ========================================================================
 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. 79, No. 112 / Wednesday, June 11, 2014 / 
Proposed Rules  

[[Page 33484]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0339; Directorate Identifier 2014-NM-025-AD]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company 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 The Boeing Company Model 737-100, -200, -200C, -300, -400, and 
-500 series airplanes. This proposed AD was prompted by reports of 
fatigue cracks found in the upper corners of the forward entry door 
skin cutout. This proposed AD would require repetitive inspections for 
cracking in the upper corners of the forward entry door skin cutout, 
and repair if necessary. Accomplishment of this repair or a preventive 
modification would terminate the repetitive inspections. This proposed 
AD also would require repetitive post-modification and post-repair 
inspections. We are proposing this AD to detect and correct cracking in 
the doorway upper corners, which could result in cabin 
depressurization.

DATES: We must receive comments on this proposed AD by July 28, 2014.

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 view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. 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 by searching for and locating Docket No. FAA-2014-
0339; 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, WA 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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2014-0339; 
Directorate Identifier 2014-NM-025-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 received reports of fatigue cracks found in the upper corners of 
the forward entry door skin cutout. The airplanes had accumulated 
between 33,150 and 76,242 total flight cycles. The cracking is caused 
by fatigue from cabin pressure loads. This condition, if not corrected, 
could result in cabin depressurization.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 737-53A1163, Revision 1, 
dated January 8, 2014. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2014-0339.

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 repetitive 
inspections for cracking in the upper corners of the forward entry door 
skin cutout, and repair if necessary, as specified in the service 
information described previously, except as discussed under 
``Difference Between this 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.

Explanation of Post-Modification and Post-Repair Inspection

    The Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1163, Revision 1, dated January 8, 2014, states that Group 1 and 
2 airplanes having the repair or preventive modification installed in 
accordance with Boeing Service Bulletin 737-53-1163, dated December 21, 
1993,

[[Page 33485]]

are not required to be inspected; however, this AD would require 
inspections of Group 1 and 2 airplanes in accordance with paragraph (i) 
of this AD, which corresponds with table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1163, Revision 
1, dated January 8, 2014.

Difference Between This Proposed AD and the Service Information

    The service bulletin specifies to contact the manufacturer for 
instructions on how to inspect and repair certain conditions, but this 
proposed AD would require inspecting and 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 371 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                        Estimated Costs: Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                 Action                          Labor cost           Parts cost      product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.............................  3 work-hours x $85 per               $0            $255         $94,605
                                          hour = $255.
----------------------------------------------------------------------------------------------------------------


                                        Estimated Costs: Optional Actions
----------------------------------------------------------------------------------------------------------------
              Action                    Labor cost                Parts cost               Cost per  product
----------------------------------------------------------------------------------------------------------------
Preventive modification..........  44 work-hours x $85   Up to $3,912...............  Up to $7,652.
                                    per hour = $3,740.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                    Labor cost                Parts cost               Cost per  product
----------------------------------------------------------------------------------------------------------------
Repair...........................  60 work-hours x $85   Up to $4,964...............  Up to $10,064.
                                    per hour = $5,100.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the post-repair or post-preventive modification 
inspections 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-2014-0339; Directorate Identifier 
2014-NM-025-AD.

(a) Comments Due Date

    We must receive comments by July 28, 2014.

[[Page 33486]]

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes; certificated in any 
category; as identified in Boeing Alert Service Bulletin 737-
53A1163, Revision 1, dated January 8, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracks found in the 
upper corners of the forward entry door skin cutout. We are issuing 
this AD to detect and correct cracking in the doorway upper corners, 
which could result in cabin depressurization.

(f) Compliance

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

(g) Inspection

    (1) For airplanes identified in Boeing Alert Service Bulletin 
737-53A1163, Revision 1, dated January 8, 2014, as Groups 1 and 2, 
Configuration 2, and Group 3: Before the accumulation of 27,000 
total flight cycles, or within 4,500 flight cycles after the 
effective date of this AD, whichever occurs later, do an external 
detailed inspection for cracking of the skin assembly, and a low 
frequency eddy current (LFEC) inspection for cracking of the skin 
assembly and bear strap, and all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, 
except as required by paragraph (j) of this AD. Repeat the 
inspections thereafter at intervals not to exceed 4,500 flight 
cycles. Do all applicable corrective actions before further flight.
    (2) For airplanes identified as Group 4 in Boeing Alert Service 
Bulletin 737-53A1163, Revision 1, dated January 8, 2014: Within 120 
days after the effective date of this AD, do inspections of the skin 
assembly and bear strap and all applicable corrective actions using 
a method approved in accordance with the procedures specified in 
paragraph (m) of this AD.

(h) Terminating Actions

    (1) Accomplishment of the preventive change specified in Part II 
of the Accomplishment Instructions of Boeing Service Bulletin 737-
53-1163, dated December 21, 1993, or the preventive modification 
specified in Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 
2014, terminates the inspection requirements specified in paragraph 
(g)(1) of this AD.
    (2) Accomplishment of the repair specified in Part III of the 
Accomplishment Instructions of Boeing Service Bulletin 737-53-1163, 
dated December 21, 1993, or Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1163, Revision 
1, dated January 8, 2014, terminates the inspection requirements 
specified in paragraph (g)(1) of this AD.

(i) Post-Modification and Post-Repair Inspections

    For airplanes identified in Boeing Alert Service Bulletin 737-
53A1163, Revision 1, dated January 8, 2014, as Groups 1 and 2, on 
which a repair or preventive modification has been installed in 
accordance with Boeing Service Bulletin 737-53-1163, dated December 
21, 1993, or Boeing Alert Service Bulletin 737-53A1163, Revision 1, 
dated January 8, 2014: At the applicable time specified in table 3 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1163, Revision 1, dated January 8, 2014, inspect the fuselage 
skin assembly, bear strap, and frame and sill outer chords, as 
applicable, for cracking, in accordance with table 3 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1163, 
Revision 1, dated January 8, 2014. Repeat the inspection thereafter 
at the times specified in table 3 of paragraph 1.E., ``Compliance'' 
of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated 
January 8, 2014. 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 (m) of this AD.

(j) Exception to Service Information Specifications

    If any cracking is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated 
January 8, 2014, specifies to contact Boeing for appropriate action: 
Before further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (m) of this 
AD.

(k) Explanation of Service Information and AD

    The Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1163, Revision 1, dated January 8, 2014, states that Group 1 
and 2, Configuration 1 airplanes having the repair or preventive 
modification installed in accordance with Boeing Service Bulletin 
737-53-1163, dated December 21, 1993, are not required to be 
inspected. However, this AD requires inspections of Group 1 and 2 
airplanes, as identified in and in accordance with paragraph (i) of 
this AD, which correspond with table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1163, 
Revision 1, dated January 8, 2014.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (g) and (h) of this AD if those actions were performed 
before the effective date of this AD using Boeing Service Bulletin 
737-53-1163, dated December 21, 1993, which is not incorporated by 
reference in this AD.

(m) 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 (n)(1) 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.

(n) 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, WA 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 view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on May 30, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-13609 Filed 6-10-14; 8:45 am]
BILLING CODE 4910-13-P


