[Federal Register: July 15, 2004 (Volume 69, Number 135)]
[Proposed Rules]
[Page 42365-42368]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15jy04-16]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18601; Directorate Identifier 2004-NM-34-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, -200B, -200F, -
200C, -100B, -300, -100B SUD, -400, -400D, -400F, and 747SR 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 747 series airplanes. This proposed AD would
require a one-time inspection for discrepancies of the frame web and
inner chords on the forward edge frame of the number 5 main entry door
cutout, and related corrective action. This proposed AD is prompted by
a report of cracking of the frame web and inner chords on the forward
edge frame of the number 5 main entry door. We are proposing this AD to
find and fix discrepancies of the frame web and inner chords, which
could result in cracking, subsequent severing of the frame, and
consequent rapid depressurization of the airplane.
DATES: We must receive comments on this proposed AD by August 30, 2004.
[[Page 42366]]
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.
You can get the service information identified in this proposed AD
from Boeing Commercial Airplanes, 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: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
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 ADDRESSES. Include ``Docket No. FAA-2004-18601;
Directorate Identifier 2004-NM-34-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 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 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 a report of cracking of the frame web and inner
chords at body station (BS) 2231, stringer 26L, on a Model 747 series
airplane. The service history shows that both chords (forward and aft)
and the web on the forward edge frame of the number 5 main entry door
(MED) cutout were severed. The inboard chord of the number 5 MED lower
main sill goes through a cutout in the BS 2231 frame at stringer 26.
Investigation revealed that, during production, the inboard chord of
the lower main sill of the door can rub against the BS 2231 frame. Such
rubbing can cause nicks, scratches and/or gouges in the frame inner
chords and web, and subsequent cracking. Cracks in the inner chords and
web could extend and fully sever the frame, which could result in rapid
depressurization of the airplane.
Related AD
On July 26, 2001, we issued AD 2001-16-02, amendment 39-12370 (66
FR 41440, August 8, 2001), which is applicable to certain Boeing Model
747 series airplanes. That AD requires repetitive inspections to find
cracking of the frame web, strap, inner chords, and inner chord angle
of the forward edge frame of the number 5 main entry door cutout, and
repair if necessary. The actions specified by that AD are intended to
find and fix such cracking, which could result in severing of the
frame, inability of the edge frame to react door stop loads, and
consequent rapid depressurization of the airplane.
Relevant Service Information
We have reviewed and approved Boeing Alert Service Bulletin 747-
53A2494, dated September 18, 2003, which describes procedures for a
one-time detailed visual inspection for discrepancies (nicks,
scratches, and/or gouges) of the frame web and inner chords (forward
and aft) of the forward edge frame of the number 5 main entry door
cutout, and related corrective action. The corrective action includes a
surface high frequency eddy current inspection for cracking on the
frame inner chords of BS 2231, rework of any discrepancies, and repair
of any cracking. The service bulletin references certain 747 Structural
Repair Manuals for rework/repair procedures. The service bulletin also
recommends contacting the manufacturer for repair instructions. The
service bulletin indicates that if the repetitive inspections
recommended in Boeing Alert Service Bulletin 747-53A2450, Revision 2,
dated January 4, 2001 (required by AD 2001-16-02) are being done, the
one-time inspection is not necessary. We have determined that
accomplishing the actions specified in the service bulletin will
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 a one-time inspection for discrepancies of the frame web
and inner chords of the forward edge frame of the number 5 main entry
door cutout, and related corrective action. The proposed AD would
require you to use the service
[[Page 42367]]
information described previously to perform these actions, except as
discussed under ``Differences Between the Proposed AD and Service
Bulletin.'' Accomplishment of the actions required by this proposed AD
would not terminate the repetitive inspections required by AD 2001-16-
02.
Differences Between the Proposed AD and Service Bulletin
The service bulletin refers to a ``detailed visual inspection'' for
discrepancies of the frame web and inner chords. We have determined
that the procedures in the service bulletin should be described as a
``detailed inspection.'' We have included Note 1 to define this type of
inspection.
As discussed previously, the referenced service bulletin specifies
that if the repetitive inspections recommended in Boeing Alert Service
Bulletin 747-53A2450 (and required by AD 2001-16-02) are currently
being done, the one-time inspection required by this proposed AD is not
necessary. However, we have determined that the repetitive inspections
required by AD 2001-16-02 would not address the unsafe condition
identified in this proposed AD. The one-time inspection required by
this proposed AD is to find nicks, scratches, and/or gouges that can
lead to cracking, and repair of those discrepancies. Therefore, we have
determined that the proposed one-time inspection is required prior to
or concurrently with the next inspection required by AD 2001-16-02.
The referenced service bulletin also specifies that operators may
contact the manufacturer for disposition of certain repair conditions,
but this proposed AD would require operators to repair those conditions
per a method approved by the Manager of the Seattle Aircraft
Certification Office of 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 220 airplanes of U.S. registry
and 1,055 airplanes worldwide. The proposed inspection would take about
2 work hours per airplane, at an average labor rate of $65 per work
hour. Based on these figures, the estimated cost of the inspection
proposed by this AD for U.S. operators is $28,600, or $130 per
airplane.
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.
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-2004-18601; Directorate Identifier 2004-NM-
34-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by August 30, 2004.
Affected ADs
(b) Accomplishing this AD will not terminate the repetitive
inspections required by AD 2001-16-02, amendment 39-12370.
Applicability
(c) This AD applies to certain Model 747-100, -200B, -200F, -
200C, -100B, -300, -100B SUD, -400, -400D, -400F, and 747SR series
airplanes; line numbers 1 through 1333 inclusive; certificated in
any category.
Unsafe Condition
(d) This AD was prompted by a report of cracking of the frame
web and inner chords on the forward edge frame of the number 5 main
entry door. We are issuing this AD to find and fix discrepancies of
the frame web and inner chords, which could result in cracking,
subsequent severing of the frame, and consequent rapid
depressurization of the airplane.
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.
One-Time Inspection
(f) For airplanes on which the repetitive inspections required
by AD 2001-16-02, amendment 39-12370, have not been done as of the
effective date of this AD: Do a one-time detailed inspection for
discrepancies (nicks, scratches, and/or gouges) of the frame web and
inner chords (forward and aft) of the forward edge frame of the
number 5 main entry door cutout, by doing all the applicable actions
by using the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2494, dated September 18, 2003. Do the inspection at
the latest of the times specified in paragraphs (f)(1), (f)(2), and
(f)(3) of this AD.
(1) Before the accumulation of 10,000 total flight cycles.
(2) Within 1,500 flight cycles after the effective date of this
AD.
(3) Within 24 months after the effective date of this AD.
(g) For airplanes on which the repetitive inspections required
by AD 2001-16-02, amendment 39-12370, have been done as of the
effective date of this AD: Do the one-time inspection required by
paragraph (f) of this AD before or concurrently with the next
inspection required by AD 2001-16-02.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive visual examination of a specific structural area,
system, installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a
direct source of good lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror, magnifying lenses,
etc., may be used. Surface cleaning and elaborate access procedures
may be required.''
Related Corrective Action
(h) If any discrepancy is found during the inspection required
by paragraph (f) or (g) of this AD: Before further flight, do all
the related corrective actions by using the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2494, dated
September 18, 2003. Where the service bulletin specifies contacting
the manufacturer for disposition of certain repair conditions,
repair before further flight 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 refer
to this AD.
[[Page 42368]]
Alternative Methods of Compliance (AMOCs)
(i)(1) 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.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by a
Boeing Company Designated Engineering Representative who has been
authorized by the Manager, Seattle ACO, to make those findings. For
a repair method to be approved, the approval must specifically refer
to this AD.
Issued in Renton, Washington, on July 8, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-16030 Filed 7-14-04; 8:45 am]
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