[Federal Register: November 26, 2008 (Volume 73, Number 229)]
[Proposed Rules]
[Page 71963-71965]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26no08-33]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1239; Directorate Identifier 2008-NM-131-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 747 airplanes. This proposed AD would require
repetitive external surface high frequency eddy current inspections to
detect cracks in the radius detail of the upper lobe doubler on both
sides of the airplane, and applicable corrective action. This proposed
AD results from reports of cracks in the radius detail of the upper
lobe doublers. We are proposing this AD to detect and correct cracks in
the upper lobe doublers. Such cracks could result in significant
degradation of the fuselage structure and reduce its ability to carry
flight loads from the vertical stabilizer, which could adversely affect
the controllability of the airplane.
DATES: We must receive comments on this proposed AD by January 12,
2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
[[Page 71964]]
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-1239;
Directorate Identifier 2008-NM-131-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of cracks in the radius detail of the
upper lobe doublers on Boeing Model 747 airplanes. The upper lobe
doublers are located between the fuselage skin and vertical stabilizer
attach fittings. Cracks in the upper lobe doublers, if not detected and
corrected, could result in significant degradation of the fuselage
structure and reduce its ability to carry flight loads from the
vertical stabilizer, which could adversely affect the controllability
of the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2651, dated
June 12, 2008. The service bulletin describes procedures for repetitive
external surface high frequency eddy current (HFEC) inspections to
detect cracks in the radius detail of the upper lobe doubler on both
sides of the airplane, and applicable corrective action. The corrective
action involves either repairing or replacing any cracked upper lobe
doubler with a new upper lobe doubler.
The compliance time for the initial external surface HFEC
inspection is at the later of the following times, depending on the
airplane configuration:
Before the accumulation of 9,000 or 10,000 total flight
cycles, or
Within 48 months or 1,000 or 4,000 flight cycles,
whichever occurs first.
The compliance time for the repetitive external surface HFEC
inspections is within 1,500 or 4,000 flight cycles after the initial
inspection, and thereafter at intervals not to exceed 1,500 or 4,000
flight cycles, depending on the airplane configuration.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This proposed AD 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
We estimate that this proposed AD would affect 164 airplanes of
U.S. registry. We also estimate that it would take about 9 work-hours
per product to comply with this proposed AD. The average labor rate is
$80 per work-hour. Based on these figures, we estimate the cost of this
proposed AD to the U.S. operators to be $118,080 or $720 per product,
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 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 this 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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:
[[Page 71965]]
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 AD:
Boeing: Docket No. FAA-2008-1239; Directorate Identifier 2008-NM-
131-AD.
Comments Due Date
(a) We must receive comments by January 12, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SR, and 747SP series airplanes, certificated in any
category; as identified in Boeing Alert Service Bulletin 747-
53A2651, dated June 12, 2008.
Unsafe Condition
(d) This AD results from reports of cracks in the radius detail
of the upper lobe doublers. We are issuing this AD to detect and
correct cracks in the upper lobe doublers. Such cracks could result
in significant degradation of the fuselage structure and reduce its
ability to carry flight loads from the vertical stabilizer, which
could adversely affect the controllability of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Inspection(s) and Corrective Action
(f) At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2651, dated
June 12, 2008, do repetitive external surface high frequency eddy
current inspections to detect cracks in the radius detail of the
upper lobe doubler on both sides of the airplane, and the applicable
corrective action by accomplishing all the applicable actions
specified in Accomplishment Instructions of the service bulletin,
except as provided by paragraph (g) of this AD. The applicable
corrective action must be done before further flight.
(g) Where Boeing Alert Service Bulletin 747-53A2651, dated June
12, 2008, specifies to contact Boeing for repair instructions
instead of repairing or replacing any cracked upper lobe doubler in
accordance with the service bulletin, this AD requires, before
further flight, repairing any cracked upper lobe doubler using a
method approved in accordance with the procedures specified in
paragraph (h) of this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6437; fax (425) 917-6590; has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-28167 Filed 11-25-08; 8:45 am]
BILLING CODE 4910-13-P