[Federal Register: December 6, 2005 (Volume 70, Number 233)]
[Rules and Regulations]
[Page 72595-72597]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06de05-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23176; Directorate Identifier 2005-NM-220-AD;
Amendment 39-14396; AD 2005-25-03]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, -700C, and
-800 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 737-600, -700, -700C, and -800 series airplanes.
This AD requires replacing the point ``D'' splice fitting between
windows number 1 and 2 with a new splice fitting, performing an eddy
current inspection for cracking of the holes in the structure common to
the new splice fitting, including doing any related investigative
actions; and corrective actions if necessary. This AD results from
full-scale fuselage fatigue testing on the splice fitting that failed
prior to the design objective on Boeing Model 737-800 series airplanes,
and a report of a cracked splice fitting on an operational airplane. We
are issuing this AD to prevent cracking of the existing fitting that
may result in cracking through the skin and consequent decompression of
the flight cabin.
DATES: This AD becomes effective December 21, 2005.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 21,
2005.
We must receive comments on this AD by February 6, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Sue Lucier, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6438; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We have received a report indicating that during the Model 737-800
series airplanes full-scale fuselage fatigue test, the splice fitting
failed prior to the design service objective. Additionally, we have
received a report indicating that a cracked splice fitting was found on
an airplane with less than 13,500 total flight cycles. This condition,
if not corrected, could result in cracking of the existing fitting that
may cause cracking through the skin and consequent decompression of the
flight cabin.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin (ASB) 737-53A1222,
Revision 2, dated October 20, 2005. The ASB describes procedures for
replacing the splice fitting between windows number 1 and 2, at point
``D'' on the windowsill with a new splice fitting, and performing
related investigative actions. Those investigative actions include
performing an open hole eddy current inspection for cracking of the
fastener holes, and a special detailed inspection for cracking of 12
fasteners in the adjacent structure. The ASB also describes procedures
for repetitive external detailed inspections of the skin near the six
skin fasteners below the splice fitting. The ASB specifies that if
cracking is detected, to contact Boeing for further instructions.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. For this reason, we
are issuing this AD to prevent cracking of the existing fitting that
may result in cracking through the skin and consequent decompression of
the flight cabin. This AD requires accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between the AD and the ASB.''
Differences Between the AD and the ASB
Where the ASB specifies contacting Boeing if any cracking is
detected, this AD requires that, repair of any cracking be accomplished
before further flight, in accordance with a method approved by the
Manager, Seattle Aircraft Certification Office (ACO).
Although the ASB specifies performing repetitive external detailed
inspections of the skin near the six skin fasteners below the splice
fitting, this AD does not require those inspections. These differences
have been coordinated with the manufacturer.
Interim Action
We consider this AD to be an interim action. We are currently
considering requiring repetitive external detailed inspections for
cracking of the skin near the six skin fasteners below the splice
fitting. However the planned compliance time for accomplishing those
inspections would necessitate allowing enough time to provide notice
and opportunity for prior public comment on the merits of requiring
those inspections.
[[Page 72596]]
Similar Models
The splice fitting between windows number 1 and 2, at point ``D''
on the windowsill, on certain Boeing Model 737-600, -700, -700C series
airplanes is identical to the splice fitting on the affected Model 737-
800 series airplanes. Therefore, all of these models may be subject to
the same unsafe condition.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists to make this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
23176; Directorate Identifier 2005-NM-220-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
http://dms.dot.gov.
Examining the Dockets
You may examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-25-03 Boeing: Amendment 39-14396. Docket No. FAA-2005-23176;
Directorate Identifier 2005-NM-220-AD.
Effective Date
(a) This AD becomes effective December 21, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-600, -700, -700C, and -
800 series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin (ASB) 737-53A1222, Revision 2, dated
October 20, 2005.
Unsafe Condition
(d) This AD results from full-scale fuselage fatigue testing on
the splice fitting that failed prior to the design objective on
Boeing Model 737-800 series airplanes, and a report of a cracked
splice fitting on an operational airplane. We are issuing this AD to
prevent cracking of the existing fitting that may result in cracking
through the skin and consequent decompression of the flight cabin.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Replacing the Splice Fittings
(f) Replace the splice fittings with new splice fittings in
accordance with the Accomplishment Instructions of Boeing ASB 737-
53A1222, Revision 2, dated October 20, 2005, at the times specified
in paragraph (f)(1) or (f)(2) of this AD, as applicable. Before
further flight, do any related investigative actions by
accomplishing all the applicable actions specified in the
Accomplishment Instructions.
(1) For airplanes that have accumulated less than 13,500 total
flight cycles as of the effective date of this AD: Replace prior to
the accumulation of 13,500 total flight cycles, or within 1,000
flight cycles after the effective date of this AD, whichever occurs
later.
(2) For airplanes that have accumulated 13,500 or more total
flight cycles as of the effective date of this AD: Replace at the
later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii)
of this AD.
(i) Prior the accumulation of 18,000 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever occurs first.
(ii) Within 90 days after the effective date of this AD.
[[Page 72597]]
Corrective Actions
(g) If any cracking is found during any inspection required by
this AD, prior to further flight, repair in accordance with a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA, or with a method approved in accordance with the
procedures specified in paragraph (i) of this AD.
Acceptable Method of Compliance
(h) Replacing the splice fitting before the effective date of
this AD in accordance with Boeing Service Bulletin 737-53-1222,
dated June 6, 2002; or Boeing ASB 737-53A1222, Revision 1, dated
January 30, 2003, is acceptable for compliance with the requirements
of paragraph (f) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
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 an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who 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.
Material Incorporated by Reference
(j) You must use Boeing Alert Service Bulletin 737-53A1222,
Revision 2, dated October 20, 2005, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference of
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Issued in Renton, Washington, on November 25, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23601 Filed 12-5-05; 8:45 am]
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