[Federal Register Volume 69, Number 171 (Friday, September 3, 2004)]
[Proposed Rules]
[Pages 53858-53860]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20125]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18997; Directorate Identifier 2004-NM-19-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. This proposed AD would require 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 the
Body station 291.5 frame at stringer 16R, and corrective actions if
necessary. This proposed AD is prompted by reports of fatigue cracks in
the web of the Body station 291.5 frame near the forward galley door.
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 October 18,
2004.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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.
By 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.
For service information identified in this proposed AD, contact
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington
98124-2207.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Howard Hall, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6430; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES1. Include ``Docket No. FAA-2004-18997;
Directorate Identifier 2004-NM-19-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will
also
[[Page 53859]]
post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that website, 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 can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.
Examining the Docket
You can 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 DMS receives them.
Discussion
We have received reports of fatigue cracks in the web of the Body
station 291.5 frame near the forward galley door of a Model 737-200
series airplane. The cracks initiate at the frame web cutout for the
stringer 16R doorstop intercostal strap. Fatigue cracking of the aft
frame and frame support structure of the forward galley door, if not
detected and corrected, could result in a severed fuselage frame web,
rapid decompression of the airplane, and possible loss of the forward
galley door.
The subject area on certain Boeing Model 737-100, -200C, -300, -
400, and -500 series airplanes is similar to that on the affected Model
737-200 series airplanes. Therefore, those airplanes may be subject to
the unsafe condition revealed on the Model 737-200 series airplanes.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-53A1241, dated
June 13, 2002. The alert service bulletin describes procedures for
performing 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 the Body station 291.5 frame at
stringer 16R, and corrective action if necessary. The alert service
bulletin also specifies to contact Boeing for repair instructions if
any crack is found. Accomplishing the actions specified in the service
information is intended to adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require 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 the Body station 291.5 frame at
stringer 16R, and corrective action if necessary. The proposed AD would
require you to use the service information described previously to
perform these actions, except as discussed under ``Differences Between
the Proposed AD and Service Bulletin.''
Differences Between the Proposed AD and Service Bulletin
The alert service bulletin states that the threshold for the
inspections is 50,000 total flight cycles or 2,250 flight cycles after
the release date of the service bulletin, whichever is later. This
proposed AD would require a threshold of 40,000 total flight cycles or
2,250 flight cycles after the effective date of the AD, whichever is
later. The threshold for the proposed AD is based upon service history
reported after the release of the service bulletin. The manufacturer
intends to issue a revised service bulletin that includes a threshold
of 40,000 total flight cycles.
Although the alert service bulletin specifies that operators may
contact the manufacturer for disposition of certain cracking
conditions, this proposed AD would require operators to repair those
conditions per a method approved by the FAA, or per data meeting the
type certification basis of the airplane approved by a Boeing Company
Designated Engineering Representative who has been authorized by the
FAA to make such findings.
Costs of Compliance
This proposed AD would affect about 3,113 airplanes worldwide. The
following table provides the estimated costs for U.S. operators to
comply with this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
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Inspection, per inspection 2 $65 None................. $130, per inspection 876 $113,880, per
cycle. cycle. inspection cycle.
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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); 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 proposed AD. 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, Safety.
[[Page 53860]]
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
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]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA-2004-18997; Directorate Identifier 2004-NM-
19-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by October 18, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-100, -200, -200C, -300,
-400, and -500 series airplanes, as listed in Boeing Alert Service
Bulletin 737-53A1241, dated June 13, 2002; certificated in any
category.
Unsafe Condition
(d) This AD was prompted by reports of fatigue cracks in the web
of the Body station 291.5 frame near the forward galley door. 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.
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.
Initial and Repetitive Inspections
(f) Prior to the accumulation of 40,000 total flight cycles, or
within 2,250 flight cycles after the effective date of this AD,
whichever occurs later: Do a detailed inspection and an eddy current
inspection to detect cracking of the frame web around the cutout for
the doorstop intercostal strap at the aft side of the Body station
291.5 frame at stringer 16R, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1241, dated
June 13, 2002. If no cracking is found, repeat the inspections
thereafter at intervals not to exceed 4,500 flight cycles.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Corrective Action
(g) If any crack is found during any inspection required by this
AD: Before further flight, repair per a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA; or per
data meeting the type certification basis of the airplane approved
by a Boeing Company Designated Engineering Representative who has
been authorized by the Manager, Seattle ACO, to make such findings.
For a repair method to be approved, the approval must specifically
reference this AD.
Alternative Methods of Compliance (AMOCs)
(h) The Manager, Seattle ACO, has the authority to approve AMOCs
for this AD, if requested in accordance with the procedures found in
14 CFR 39.19.
Issued in Renton, Washington, on August 20, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-20125 Filed 9-2-04; 8:45 am]
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