[Federal Register Volume 79, Number 112 (Wednesday, June 11, 2014)]
[Proposed Rules]
[Pages 33484-33486]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-13609]
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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.
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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).
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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: [email protected].
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
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspection............................. 3 work-hours x $85 per $0 $255 $94,605
hour = $255.
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Estimated Costs: Optional Actions
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Action Labor cost Parts cost Cost per product
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Preventive modification.......... 44 work-hours x $85 Up to $3,912............... Up to $7,652.
per hour = $3,740.
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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
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Action Labor cost Parts cost Cost per product
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Repair........................... 60 work-hours x $85 Up to $4,964............... Up to $10,064.
per hour = $5,100.
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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: [email protected].
(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: [email protected].
(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