[Federal Register Volume 79, Number 165 (Tuesday, August 26, 2014)]
[Proposed Rules]
[Pages 50867-50869]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-20204]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0572; Directorate Identifier 2014-NM-027-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) 98-22-10, 
which applies to certain The Boeing Company Model 737-100, -200, -200C, 
and -300 series airplanes. AD 98-22-10 currently requires repetitive 
inspections for cracking of the aft frame and frame support structure 
of the forward service doorway, and repair if necessary. AD 98-22-10 
also provides for an optional terminating action for the repetitive 
inspection requirements of that AD. Since we issued AD 98-22-10, we 
have determined that additional inspections are needed, and that 
additional airplanes may be subject to the identified unsafe condition. 
This proposed AD would add inspections and add airplanes to the 
applicability. For certain airplanes, this proposed AD provides a 
preventive modification, which would terminate the repetitive 
inspections. We are proposing this AD to detect and correct fatigue 
cracking of the aft frame and frame support structure of the forward 
service doorway around the six doorstop fittings, which could result in 
door deflection and loss of pressurization.

DATES: We must receive comments on this proposed AD by October 10, 
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 review 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-
0572; 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 proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0572; 
Directorate Identifier 2014-NM-027-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 October 19, 1998, we issued AD 98-22-10, Amendment 39-10858 (63 
FR 57240, October 27, 1998), for certain The Boeing Company Model 737-
100, -200, -200C, and -300 series airplanes. AD 98-22-10 requires 
repetitive inspections to detect cracking of the aft frame and aft 
frame support structure of the forward service doorway, and repair if 
necessary. AD 98-22-10 resulted from reports of fatigue cracking of the 
aft frame and frame support structure of the forward service doorway. 
We issued AD 98-22-10 to prevent fatigue cracking of the aft frame and 
frame support structure of the forward service doorway, which could 
result in loss of the door, and consequent rapid decompression of the 
fuselage.
    Tables 9 through 12 in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, 
specify post-repair inspections, which may be used in support of 
compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal 
Aviation Regulations (14 CFR 121.1109(c)(2) or 129.109(b)(2)). However, 
this NPRM does not propose to require those post-repair inspections. 
This difference has been coordinated with Boeing.

Actions Since AD 98-22-10, Amendment 39-10858 (63 FR 57240, October 27, 
1998), Was Issued

    Since we issued AD 98-22-10, Amendment 39-10858 (63 FR 57240, 
October 27, 1998), we received reports of cracking in the forward 
galley service doorway surround structure between body station (STA) 
332.1 and STA 344, which are outside the inspection area of AD 98-22-
10, and we have received reports that cracking has been discovered on 
airplanes outside the applicability of AD 98-22-10. We have determined 
that additional inspections are needed, and that additional airplanes 
are subject to the identified unsafe condition.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 737-53A1108, Revision 7, 
dated July 7, 2014. For information on the procedures and compliance 
times,

[[Page 50868]]

see this service information at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2014-0572.

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 state the 
requirements of AD 98-22-10, Amendment 39-10858 (63 FR 57240, October 
27, 1998), this proposed AD would retain certain requirements of AD 98-
22-10. Those requirements are referenced in the service information 
identified previously, which, in turn, is referenced in paragraphs (g) 
and (h) of this proposed AD. This proposed AD would require additional 
inspections and add airplanes to the applicability. This proposed AD 
would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between This Proposed AD and the Service Information.''
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary actions, and (2) further 
investigate the nature of any condition found. Related investigative 
actions in an AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' correct or address any condition found. 
Corrective actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated 
July 7, 2014, specifies to contact the manufacturer for instructions on 
how to repair certain conditions, this proposed AD would require 
repairing those conditions in one of the following ways:
     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:

                                      Estimated Costs for Required Actions
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                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  Up to 28 work-      None..............  Up to $2,380 per    Up to $997,220 per
                                   hours x $85 per                         inspection cycle.   inspection cycle.
                                   hour = $2,380 per
                                   inspection cycle.
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                                    Estimated Costs for Optional Modification
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                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Repair/preventive modification.......  12 to 17 work-hours x    $90 to $913............  Up to $2,358.
                                        $85 per hour = up to
                                        $1,445.
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    We have received no definitive data that would enable us to provide 
cost estimates for any on-condition actions specified in this proposed 
AD. We have no way of determining the number of aircraft that might 
need this repair.

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) 
98-22-10, Amendment 39-10858 (63 FR 57240, October 27, 1998), and 
adding the following new AD:


[[Page 50869]]


The Boeing Company: Docket No. FAA-2014-0572; Directorate Identifier 
2014-NM-027-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by October 10, 
2014.

(b) Affected ADs

    This AD supersedes AD 98-22-10, Amendment 39-10858 (63 FR 57240, 
October 27, 1998).

(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-
53A1108, Revision 7, dated July 7, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracking of the aft 
frame and frame support structure of the forward service doorway 
around the six doorstop fittings; a determination that additional 
inspections are needed; and that additional airplanes may be subject 
to the identified unsafe condition. We are issuing this AD to detect 
and correct fatigue cracking of the aft frame and frame support 
structure of the forward service doorway around the six doorstop 
fittings, which could result in door deflection and loss of 
pressurization.

(f) Compliance

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

(g) Inspections and Corrective Actions

    At the applicable times specified in tables 1 through 6 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1108, Revision 7, dated July 7, 2014, except as required by 
paragraph (j)(1) of this AD: Do detailed inspections of the frame 
web between body station (STA) 332.1 and STA 344, intercostal T-
brackets, intercostal T-chords, intercostals, and stringers, as 
applicable; and do high frequency eddy current (HFEC) inspections 
for cracking of door stop intercostal T-brackets, intercostal web, 
door stop intercostal T-chords, intercostals, and stringers, as 
applicable; and do all applicable related investigative and 
corrective actions; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1108, Revision 
7, dated July 7, 2014, except as required by paragraph (j)(2) of 
this AD. Do all applicable related investigative and corrective 
actions before further flight. Repeat the inspections at the 
applicable times specified in tables 1 through 6 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1108, 
Revision 7, dated July 7, 2014, until a terminating action specified 
in paragraph (h) of this AD is done.

(h) Optional Terminating Action

    For Group 1, Configuration 1; Group 1, Configuration 2; Group 2; 
Group 3; Group 4, Configuration 1; and Group 4, Configuration 2 
airplanes identified in Boeing Alert Service Bulletin 737-53A1108, 
Revision 7, dated July 7, 2014: Accomplishment of a preventative 
modification in accordance with Part 5 of Boeing Alert Service 
Bulletin 737-53A1108, Revision 7, dated July 7, 2014, terminates the 
repetitive inspections required by paragraph (g) of this AD.

(i) Inspections and Corrective Actions for Group 5 Airplanes

    For Group 5 airplanes identified in Boeing Alert Service 
Bulletin 737-53A1108, Revision 7, dated July 7, 2014: Within 120 
days after the effective date of this AD, inspect and repair any 
cracking using a method approved in accordance with the procedures 
specified in paragraph (l) of this AD.

(j) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, 
dated July 7, 2014, specifies a compliance time ``after the issue 
date of Revision 6 of this service bulletin,'' this AD requires 
compliance within the specified time after the effective date of 
this AD.
    (2) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, 
dated July 7, 2014, specifies to contact Boeing for repair 
instructions: Before further flight, repair the cracking using a 
method approved in accordance with the procedures specified in 
paragraph (l) of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 737-53A1108, Revision 6, dated January 9, 2014.

(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)(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.
    (4) AMOCs approved for AD 98-22-10, Amendment 39-10858 (63 FR 
57240, October 27, 1998), are approved as AMOCs for the 
corresponding provisions of this AD.
    (5) Accomplishment of the preventative modification in 
accordance with Boeing Service Bulletin 737-53A1108, Revision 7, 
dated July 7, 2014, as required by paragraph (h) of this AD, is an 
AMOC to the structural modification specified in Boeing Service 
Bulletin 737-53A1108 that is required by paragraph A. of AD 90-06-
02, Amendment 39-6489, (55 FR 8372, March 7, 1990).

(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, 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 August 15, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-20204 Filed 8-25-14; 8:45 am]
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