[Federal Register: January 7, 2005 (Volume 70, Number 5)]
[Rules and Regulations]
[Page 1340-1341]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ja05-9]
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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;
Amendment 39-13933; AD 2005-01-09]
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: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 747 series airplanes. This AD requires 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 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 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.
DATES: This AD becomes effective February 11, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of
February 11, 2005.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, PO Box 3707, Seattle, Washington 98124-
2207. You can examine this information at the National Archives and
Records Administration (NARA). For information on the availability of
this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
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:
Technical information: 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.
Plain language information: Marcia Walters, marcia.walters@faa.gov.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with an AD for certain Boeing Model 747 series airplanes. That action,
published in the Federal Register on July 15, 2004 (69 FR 42365),
proposed to 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.
Examining the Docket
The AD docket contains the proposed AD, comments, and any final
disposition. 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.
Comment
We provided the public the opportunity to participate in the
development of this AD. We have considered the single comment that has
been submitted on the proposed AD.
Request To Change Paragraph (g)
The commenter (the manufacturer) asks that paragraph (g) of the
proposed AD be changed to read ``For those 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, no further action
is required.'' The commenter states that the inspection required by AD
2001-16-02 (referenced as a related AD in the proposed AD) is a surface
eddy current inspection and is more intensive than the detailed
inspection specified in the proposed AD. The commenter notes that the
repetitive inspections in AD 2001-16-02 adequately detect any cracking
prior to loss of residual strength of the chord. The commenter adds
that a nick or gouge does not affect the crack growth rate, so the
safety concern in the proposed AD is addressed by the repetitive
inspections.
We agree with the commenter. The repetitive inspections for
cracking required by AD 2001-16-02 are more extensive than the one-time
inspection required by this AD, and must be repeated at intervals not
to exceed 3,000 flight cycles. Initiating those inspections will find
cracking before it reaches critical length; therefore, the one-time
inspection required by this AD is not necessary if the repetitive
inspections are currently being done. For airplanes that are at or near
the 10,000-flight-cycle threshold, and have not been inspected per AD
2001-16-02, the purpose of this AD is to close the gap between the
compliance time for the initial inspection required by AD 2001-16-02
(before the accumulation of 16,000 total flight cycles) and the one-
time inspection required by this AD. The AD requires that operators
inspect the airplane at or before 10,000 total flight cycles, or within
the specified grace period. Therefore, paragraph (g) of this AD has
been changed to specify that operators currently accomplishing the
repetitive inspections required by AD 2001-16-02 are not required to
accomplish the one-time inspection required by this AD.
Conclusion
We have carefully reviewed the available data, including the
comment that has been submitted, and determined that air safety and the
public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 1,055 airplanes worldwide of the affected design,
this AD affects about 220 airplanes of U.S. registry. The inspection
takes 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 required by this AD for U.S. operators is $28,600, or $130
per airplane.
Authority for This Rulemaking
The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. 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.
This rulemaking is promulgated under the authority described in
[[Page 1341]]
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 AD.
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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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. 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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-01-09 Boeing: Amendment 39-13933. Docket No. FAA-2004-18601;
Directorate Identifier 2004-NM-34-AD.
Effective Date
(a) This AD becomes effective February 11, 2005.
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 Boeing 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 cords 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 cords, 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 have not been accomplished 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 cords
(forward and aft) of the forward edge frame of the number 5 main
entry door cutout, by doing all the applicable actions specified in
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 have been accomplished as of the effective date of
this AD: No further action is required by this AD.
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) of this AD: Before further flight, do all the
related corrective actions specified in 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.
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.
Material Incorporated by Reference
(j) You must use Boeing Alert Service Bulletin 747-53A2494,
dated September 18, 2003, to perform the actions that are required
by this AD, unless the AD specifies otherwise. The Director of the
Federal Register approves the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For
copies of the service information, contact Boeing Commercial
Airplanes, PO Box 3707, Seattle, Washington 98124-2207. For
information on the availability of this material at the National
Archives and Records Administration (NARA), call (202) 741-6030, or
go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
You may view the AD docket at the
Docket Management Facility, Department of Transportation, 400
Seventh Street SW., room PL-401, Nassif Building, Washington, DC.
Issued in Renton, Washington, on December 27, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-160 Filed 1-6-05; 8:45 am]
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