[Federal Register Volume 79, Number 71 (Monday, April 14, 2014)]
[Proposed Rules]
[Pages 20824-20827]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-08301]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0195; Directorate Identifier 2013-NM-195-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) 2008-17-
03, which applies to certain The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes. AD 2008-17-03 currently
requires repetitive inspections to detect fuselage frame cracking, and
corrective action if necessary. AD 2008-17-03 also provides for
optional terminating action (repair/preventive change) for the
repetitive inspections. Since we issued AD 2008-17-03, we have
determined that additional airplanes may be subject to the identified
unsafe condition. This proposed AD would add airplanes to the
applicability. For the newly added airplanes, however, this proposed AD
would not provide terminating action for the repetitive inspections
because service information has not been provided for a repair/
preventive change. We are proposing this AD to detect and correct
fuselage frame cracking, which could prevent the left forward entry
door from sealing correctly, and could cause in-flight decompression of
the airplane.
DATES: We must receive comments on this proposed AD by May 29, 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-
0195; 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
(ACO), 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 proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0195;
Directorate Identifier 2013-NM-195-AD'' at the beginning of your
comments. We specifically invite
[[Page 20825]]
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 August 6, 2008, we issued AD 2008-17-03, Amendment 39-15641 (73
FR 48288, August 19, 2008), for certain The Boeing Company Model 737-
100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-17-03
required repetitive inspections to detect cracking of the body station
303.9 frame, and corrective action if necessary. AD 2008-17-03 also
provided for optional terminating action for the repetitive
inspections. AD 2008-17-03 resulted from reports of cracks found at the
cutout in the web of body station frame 303.9 inboard of stringer 16L.
We issued AD 2008-17-03 to detect and correct such cracking, which
could prevent the left forward entry door from sealing correctly, and
could cause in-flight decompression of the airplane.
Actions Since AD 2008-17-03, Amendment 39-15641 (73 FR 48288, August
19, 2008), Was Issued
Since we issued AD 2008-17-03, Amendment 39-15641 (73 FR 48288,
August 19, 2008), we have been advised that cracking has been
discovered on an airplane outside the applicability of AD 2008-17-03.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 737-53A1188, Revision 3,
dated September 6, 2013. For information on the procedures and
compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2014-0195.
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 retain the requirements of AD 2008-17-03,
Amendment 39-15641 (73 FR 48288, August 19, 2008). This proposed AD
would 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
the Proposed AD and the Service Information.''
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 the Proposed AD and the Service Information
The service information 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 148 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs: Required Actions
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection........ 31 to 33 work-hours x $85 per hour = $0 Up to $2,805 per Up to $415,140 per
up to $2,805 per inspection cycle. inspection cycle. inspection cycle.
----------------------------------------------------------------------------------------------------------------
Estimated Costs: Optional Modification
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair/preventive change........ 12 to 30 work-hours x $85 per hour $564 to $2,236..... Up to $4,786.
= up to $2,550.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions 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 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,
[[Page 20826]]
(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. Amend Sec. 39.13 by removing Airworthiness Directive (AD) 2008-17-
03, Amendment 39-15641 (73 FR 48288, August 19, 2008), and adding the
following new AD:
The Boeing Company: Docket No. FAA-2014-0195; Directorate Identifier
2013-NM-195-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by May 29, 2014.
(b) Affected ADs
This AD supersedes AD 2008-17-03, Amendment 39-15641 (73 FR
48288, August 19, 2008).
(c) Applicability
This AD applies to The Boeing Company airplanes, certificated in
any category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes, as identified in Boeing Alert Service Bulletin 737-
53A1197, dated August 25, 2006.
(2) Model 737-300, -400, and -500 series airplanes, as
identified in Boeing Alert Service Bulletin 737-53A1188, Revision 3,
dated September 6, 2013.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracks found at the cutout in
the web of body station frame 303.9 inboard of stringer 16L, and a
new report of cracking found on an airplane not included in the
applicability of AD 2008-17-03, Amendment 39-15641 (73 FR 48288,
August 19, 2008). We are issuing this AD to detect and correct such
cracking, which could prevent the left forward entry door from
sealing correctly, and could cause in-flight decompression of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections: Group 1 Airplanes, Boeing Alert
Service Bulletin 737-53A1188, Revision 2, Dated May 9, 2007, or Boeing
Alert Service Bulletin 737-53A1188, Revision 3, Dated September 6,
2013, With Revised Service Information
This paragraph restates the requirements of paragraph (f) of AD
2008-17-03, Amendment 39-15641 (73 FR 48288, August 19, 2008), with
revised service information and airplane groupings. For airplanes
identified as Group 1 in Boeing Alert Service Bulletin 737-53A1188,
Revision 3, dated September 6, 2013: Do detailed and high frequency
eddy current (HFEC) inspections in the web and doubler around the
slotted holes in the frame web at stringers 15L and 16L, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007; or
Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated
September 6, 2013. Do the inspections at the applicable time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1188, Revision 3, dated September 6, 2013. Do all
applicable corrective actions before further flight in accordance
with Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated
May 9, 2007; or Boeing Alert Service Bulletin 737-53A1188, Revision
3, dated September 6, 2013; except as provided by paragraph (j)(3)
of this AD. Repeat the inspections at intervals not to exceed 4,500
flight cycles, until accomplishment of the repair/preventive change
in accordance with Boeing Alert Service Bulletin 737-53A1188,
Revision 2, dated May 9, 2007; or Boeing Alert Service Bulletin 737-
53A1188, Revision 3, dated September 6, 2013; which terminates the
repetitive inspection requirements for the airplanes identified in
this paragraph. A repair/preventive change done using Boeing Alert
Service Bulletin 737-53A1188, dated April 9, 1998; or Boeing Alert
Service Bulletin 737-53A1188, Revision 1, dated March 18, 1999; does
not terminate the repetitive inspections, but the repetitive
inspections may be terminated after the existing kit is replaced
with a new kit in accordance with paragraph 3.B., Part II, step 3,
or Part III, step 3, of Boeing Alert Service Bulletin 737-53A1188,
Revision 2, dated May 9, 2007. As of the effective date of this AD,
only Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated
September 6, 2013, may be used to do the actions required by this
paragraph.
Note 1 to paragraph (g) of this AD: Airplanes identified as
Group 1 in Boeing Alert Service Bulletin 737-53A1188, Revision 3,
dated September 6, 2013, are the same as those identified in Boeing
Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007.
(h) Retained Repetitive Inspections: Boeing Alert Service Bulletin 737-
53A1197, Dated August 25, 2006
This paragraph restates the requirements of paragraph (g) of AD
2008-17-03, Amendment 39-15641 (73 FR 48288, August 19, 2008). For
airplanes identified in Boeing Alert Service Bulletin 737-53A1197,
dated August 25, 2006: Do an ultrasound inspection of the slot-
shaped cutout in the web for the door stop strap at stringer 16L, an
HFEC inspection of the web along the upper and lower edges of the
doubler around the doorstop strap at stringer 16L, and a detailed
inspection of the web around the doubler for the cutout at stringer
16L, in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1197, dated August 25, 2006. Do the
inspections at the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1197, dated
August 25, 2006, except as provided by paragraph (j)(2) of this AD.
Do all applicable corrective actions before further flight in
accordance with Boeing Alert Service Bulletin 737-53A1197, dated
August 25, 2006, except as provided by paragraph (j)(3) of this AD.
Repeat the inspections at intervals not to exceed 4,500 flight
cycles, until accomplishment of the repair/preventive change in
accordance with Boeing Alert Service Bulletin 737-53A1197, dated
August 25, 2006, which terminates the repetitive inspections.
(i) New Repetitive Inspections: Group 2 Airplanes, Boeing Alert Service
Bulletin 737-53A1188, Revision 3, Dated September 6, 2013
For airplanes identified as Group 2 in Boeing Alert Service
Bulletin 737-53A1188, Revision 3, dated September 6, 2013: At the
applicable times specified in Table 3 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1188,
Revision 3, dated September 6, 2013, except as required by paragraph
(j)(1) of this AD: Do detailed and HFEC inspections for cracking in
the web of the body station 303.9 frame at stringer 15L, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1188, Revision
3, dated September 6, 2013, except as required by paragraph (j)(3)
of this AD. Do all applicable corrective actions before further
flight. Repeat the inspection thereafter at the applicable time
specified in Table 3 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1188, Revision 3, dated September 6,
2013. Accomplishment of a repair using a method approved in
accordance with the procedures specified in paragraph (k) of this AD
terminates the repetitive inspections required by this paragraph for
the area covered by the repair.
(j) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 737-53A1188, Revision 3,
dated September 6, 2013, specifies a compliance time ``after the
Revision 3 date of this service bulletin,'' this AD requires
compliance within the
[[Page 20827]]
specified time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin 737-53A1197, dated
August 25, 2006, specifies a compliance time ``After the Date of
this Service Bulletin,'' this AD requires compliance for paragraph
(h) of this AD within the specified time after September 23, 2008
(the effective date of AD 2008-17-03, Amendment 39-15641 (73 FR
48288, August 19, 2008)). For the initial inspection, the grace
period for airplanes that have exceeded the specified threshold is
extended to 4,500 flight cycles after September 23, 2008 (the
effective date of AD 2008-17-03).
(3) Where Boeing Alert Service Bulletin 737-53A1188, Revision 2,
dated May 9, 2007; Boeing Alert Service Bulletin 737-53A1188,
Revision 3, dated September 6, 2013; and Boeing Alert Service
Bulletin 737-53A1197, dated August 25, 2006; specify to contact
Boeing for appropriate action, including repair of damage outside
the scope of the service information, repair using a method approved
in accordance with the procedures specified in paragraph (k) of this
AD.
(k) 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 (l)(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.
(4) AMOCs approved for AD 2008-17-03, Amendment 39-15641 (73 FR
48288, August 19, 2008), are approved as AMOCs for the corresponding
provisions of this AD.
(l) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 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 the 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 April 4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-08301 Filed 4-11-14; 8:45 am]
BILLING CODE 4910-13-P