[Federal Register: July 22, 2005 (Volume 70, Number 140)]
[Rules and Regulations]
[Page 42269-42271]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22jy05-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20690; Directorate Identifier 2003-NM-230-AD;
Amendment 39-14195; AD 2005-15-06]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-200C and 747-200F
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 747-200C and 747-200F series airplanes. This AD
requires one-time inspections for cracks and material loss in the
fuselage skin above the stringer (STR) 23 lap splice, between Body
Station (BS) 282 and BS 298, and repair if necessary. This AD is
prompted by a report of a crack above the STR 23 lap splice on one
airplane. We are issuing this AD to detect and correct cracks or
material loss in the fuselage skin, and consequent reduced structural
integrity of the skin panel, which could result in rapid
depressurization of the airplane.
DATES: This AD becomes effective August 26, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of August
26, 2005.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
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 U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Washington, DC. This docket number is FAA-2005-20690; the directorate
identifier for this docket is 2003-NM-230-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: The FAA proposed to amend 14 CFR part 39
with an AD for certain Boeing Model 747-200C and 747-200F series
airplanes. That action, published in the Federal Register on March 23,
2005 (70 FR 14587), proposed to require one-time inspections for cracks
and material loss in the fuselage skin above the stringer (STR) 23 lap
splice, between Body Station (BS) 282 and BS 298, and repair if
necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
submitted on the proposed AD.
Request To Re-Evaluate Need for the Proposed Rule
One commenter, an airplane operator, notes that it has previously
inspected the fuselage skin thickness at the affected area on two of
its ten production freighter airplanes. The inspections, which the
commenter points out were conducted at the manufacturer's
recommendation, showed skin thickness of 0.060 inch or greater on both
airplanes. The commenter asserts that our justification for adopting
the proposed AD should cite the results of its inspections and any
similar inspections conducted at the manufacturer's request by other
operators; and notes that Boeing Special Attention Service Bulletin
747-53-2493, dated July 3, 2003, cites only one instance of the problem
that is prompting the proposed AD. The commenter acknowledges the
significance of fuselage skin cracking, and recognizes the fact that
the maintenance program for the affected Model 747-200C and 747-200F
series airplanes includes external visual inspections of the affected
area at regular intervals. However, the commenter questions our
justification for adopting the proposed AD.
[[Page 42270]]
We infer that the commenter is questioning whether the proposed AD
addresses a safety issue and, if not, we further infer that the
commenter requests that we withdraw the proposed AD. We disagree.
Although the commenter had no findings of cracking or blended skin on
two of its airplanes, other respondents to the manufacturer's survey
did report airplanes with skin thickness that was below the minimum. In
addition, there are many airplanes affected by this proposed AD that
have not yet been inspected.
However, we do agree that we should clarify the unsafe condition.
Investigation of the crack report that prompted this proposed AD showed
that the skin at the crack location was not the correct thickness.
Boeing audited its manufacturing processes and discovered that assembly
techniques of the skin panels during final assembly at the factory were
the likely cause of the thin skin at the affected sections. It is very
likely that the same condition may exist on other airplanes that were
manufactured using the same techniques. Furthermore, the finding that
precipitated this proposed AD was a three-inch crack in the upper row
of the lap splice just above the upper row. Cracking in this area is
critical due to its proximity to the upper row and possible interaction
of cracks between the blended area and the upper row. Therefore, the
crack finding, coupled with the likelihood that the thin skin condition
exists on other airplanes, provides sufficient justification for
adopting the proposed AD to detect and correct cracks or material loss
in the fuselage skin.
We have not changed the final rule in this regard.
Conclusion
We have carefully reviewed the available data, including the
comment that was submitted, and determined that air safety and the
public interest require adopting the AD as proposed.
Costs of Compliance
There are about 77 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD.
Estimated Costs
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Number of
Work Average Cost per U.S.-
Action hours labor rate Parts airplane registered Fleet cost
per hour airplanes
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Inspections................. 6 $65 None........... $390 20 $7,800
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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 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):
2005-15-06 Boeing: Amendment 39-14195. Docket No. FAA-2005-20690;
Directorate Identifier 2003-NM-230-AD.
Effective Date
(a) This AD becomes effective August 26, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-200C and 747-200F series
airplanes, equipped with a nose cargo door, certificated in any
category; as identified in paragraph 1.A.1 of Boeing Special
Attention Service Bulletin 747-53-2493, dated July 3, 2003.
Unsafe Condition
(d) This AD was prompted by a report of a crack above the
stringer (STR) 23 lap splice on a Model 747-200F series airplane. We
are issuing this AD to detect and correct cracks or material loss in
the fuselage skin, and consequent reduced structural integrity of
the skin panel, which could result in 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.
Inspections and Repair
(f) Before the accumulation of 15,000 total flight cycles, or
within 1,200 flight cycles after the effective date of this AD,
whichever occurs later: Do a detailed inspection for cracking, and a
low frequency eddy current inspection for material loss, in the
fuselage skin. Repair any crack or material loss prior
[[Page 42271]]
to further flight. Do all actions in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2493, dated July 3, 2003.
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.''
Alternative Methods of Compliance (AMOCs)
(g)(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) 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 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
(h) You must use Boeing Special Attention Service Bulletin 747-
53-2493, dated July 3, 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.
To get copies of the service information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view
the AD docket, go to the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC. To review copies of the service
information, go to 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 July 11, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-14174 Filed 7-21-05; 8:45 am]
BILLING CODE 4910-13-P