[Federal Register: December 6, 2005 (Volume 70, Number 233)]
[Proposed Rules]
[Page 72599-72601]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06de05-5]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 72599]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23196; Directorate Identifier 2005-NM-187-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-200C, -200F, -400, -
400D, and -400F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (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 747-200C, -200F, -400, -400D, and -400F series
airplanes. This proposed AD would require repetitive inspections for
cracks in the overlapping (upper) skin, upper fastener row of the lap
joints of the fuselage skin in sections 41, 42, and 46; and related
investigative and corrective actions, if necessary. This proposed AD
results from fatigue tests and an analysis that identified areas of the
fuselage lap joints where fatigue cracks can occur. We are proposing
this AD to detect and correct fatigue cracks in the overlapping (upper)
skin, upper fastener row of the lap joints of the fuselage skin in
sections 41, 42, and 46, which could adversely affect the structural
integrity of the airplane.
DATES: We must receive comments on this proposed AD by January 20,
2006.
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.
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 the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Nick Kusz, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6432; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2005-
23196; Directorate Identifier 2005-NM-187-AD'' at the beginning 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 received 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 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 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 Docket
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.
Discussion
We have received a report indicating that the airplane manufacturer
has completed extended pressure fatigue tests on 747-100SR and 747-400
fuselage test articles. Analysis of these test results have identified
areas of the fuselage lap joints where fatigue cracks can occur on
Boeing Model 747-200C, -200F, -400, -400D, and -400F series airplanes.
Fatigue cracks in the overlapping (upper) skin, upper fastener row of
the lap joints of the fuselage skin in sections 41, 42, and 46, if not
detected and corrected in a timely manner, could adversely affect the
structural integrity of the airplane.
Other Relevant Rulemaking
We have previously issued AD 94-12-04, amendment 39-8932 (59 FR
30277, June 13, 1994), applicable to certain Boeing Model 747-100, -
200, -300, 747SP, and 747SR series airplanes. That AD requires
repetitive inspections to detect cracking in the upper row of certain
fuselage skin lap joints, and repair, if necessary. This proposed AD
addresses a similar unsafe condition on a different group of airplanes
and would not affect the current requirements of AD 94-12-04.
We also previously issued AD 2004-07-22, amendment 39-13566 (69 FR
18250, April 7, 2004), applicable to all Boeing Model 747 series
airplanes. (A final rule correction was published in the Federal
Register on May 3, 2004 (69 FR 24063)). That AD requires that the FAA-
approved maintenance inspection program be revised to include
inspections that will give no less than the required damage tolerance
rating for each structural significant item, and repair or cracked
structure. The proposed AD would not affect the current requirements of
that AD.
[[Page 72600]]
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2499, dated
August 11, 2005. The service bulletin describes procedures for
repetitive external surface high frequency eddy current (HFEC),
external low frequency eddy current (LFEC), and internal LFEC
inspections, as applicable, for cracks in the overlapping (upper) skin,
upper fastener row of the lap joints of the fuselage skin in sections
41, 42, and 46; and any applicable related investigative and corrective
actions, if necessary. The related investigative actions involve doing
open-hole HFEC inspections of the fastener holes to find the total
crack length. The corrective actions involve repairing any cracked lap
joint and doing open-hole HFEC inspection of the skin at all existing
fastener locations common to the repair. The intervals for doing the
repetitive inspections are 1,500, 2,400, or 3,000 flight cycles,
depending on the airplane configuration. 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. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously, except as discussed under
``Difference Between the Proposed AD and Service Bulletin.''
Difference Between Proposed Rule and Service Bulletin
The service bulletin 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:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Costs of Compliance
There are about 796 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 153 airplanes of
U.S. registry. The proposed inspections would take about 534 work hours
per airplane, at an average labor rate of $65 per work hour. Based on
these figures, the estimated cost of the proposed AD for U.S. operators
is $5,310,630, or $34,710 per airplane, per inspection cycle.
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;
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 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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2005-23196; Directorate Identifier 2005-NM-
187-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
20, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-200C, -200F, -400, -
400D, and -400F series airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletin 747-53A2499, dated
August 11, 2005.
Unsafe Condition
(d) This AD results from fatigue tests and an analysis that
identified areas of the fuselage lap joints where fatigue cracks can
occur. We are issuing this AD to detect and correct fatigue cracks
in the overlapping (upper) skin, upper fastener row of the lap
joints of the fuselage skin in sections 41, 42, and 46, which could
adversely affect the structural integrity 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.
Initial Inspections and Related Investigative and Corrective Actions
(f) At the applicable time specified in Table 1 of this AD: Do
an external surface high frequency eddy current (HFEC), external low
frequency eddy current (LFEC), and internal LFEC inspections, as
applicable, for cracks in the overlapping (upper) skin, upper
fastener row of the lap joints of the fuselage skin in sections 41,
42, and 46, and any applicable related investigative and corrective
actions by doing all of the actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2499, dated August 11, 2005, except as provided by paragraph (h)
of this AD. Do any applicable related investigative and corrective
actions before further flight.
[[Page 72601]]
Table 1.--Initial Compliance Time
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For airplanes on which
Structural Significant Items
(SSIs) F-25G, F-25H, and F- Inspect--
25I--
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(1) Have not been inspected Before the accumulation of 22,000 total
in accordance with paragraph flight cycles, or within 1,000 flight
(d) of AD 2004-07-22, cycles after the effective date of this
amendment 39-13566, using AD, whichever occurs later.
the HFEC method.
(2) Have been inspected in Within 3,000 flight cycles after the most
accordance with paragraph recent Supplemental Structural
(d) of AD 2004-07-22, Inspection Document (SSID) inspection of
amendment 39-13566, using each applicable structural significant
the HFEC method. item (as given in Boeing Document D6-
35022, ``SSID for Model 747 Airplanes,''
Revision G, dated December 2000), or
within 1,000 flight cycles after the
effective date of this AD, whichever
occurs later.
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Repetitive Inspections
(g) Repeat the applicable inspections required by paragraph (f)
of this AD thereafter at intervals not to exceed those specified in
paragraph 1.E., ``Compliance'' (including the note) of Boeing Alert
Service Bulletin 747-53A2499, dated August 11, 2005.
Exception to Service Bulletin Instructions
(h) Where the service bulletin specifies to contact Boeing for
appropriate action, before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (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.
Issued in Renton, Washington, on November 17, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23654 Filed 12-5-05; 8:45 am]
BILLING CODE 4910-13-P