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