[Federal Register: November 26, 2002 (Volume 67, Number 228)]
[Rules and Regulations]
[Page 70680-70682]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26no02-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-270-AD; Amendment 39-12959; AD 2002-23-15]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, -200B, -200C, -
200F, -300, -400, -400F, and 747SR Series Airplanes, Equipped with a
Main Deck Side Cargo Door (MDSCD) Manufactured by Boeing
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Boeing Model 747-100, -200B, -200C, -200F, -
300, -400, -400F, and 747SR series airplanes equipped with a MCSCD
manufactured by Boeing. This action requires repetitive inspections for
cracking of the lower lobe panel of the fuselage skin of the aft cargo
bay, and repair if necessary. This action is necessary to find and fix
cracking of the skin, which could lead to reduced structural integrity
of the side cargo door cutout of the main deck, and result in rapid
depressurization of the airplane. This action is intended to address
the identified unsafe condition.
DATES: Effective December 11, 2002.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 11, 2002.
Comments for inclusion in the Rules Docket must be received on or
before January 27, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-270-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-270-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 for Windows or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
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) 227-2131;
fax (425) 227-1181.
SUPPLEMENTARY INFORMATION: The FAA recently received a report of
cracking of the lower lobe panel of the fuselage skin of the aft cargo
bay, between Station (STA) 1720 and 1740, on a Model 747-200F series
airplane. The crack was 11.6 inches long and was located below the
stringer 34L lap joint and the upper fastener row of the external
reinforcing doubler of the cargo door cutout of the main deck. The
airplane had accumulated 18,688 total flight cycles and 81,902 total
flight hours. Subsequent examination and analysis of the cracked skin
revealed that the crack originated from scratches in the skin exterior
surface at multiple locations. Such cracking, if not found and fixed,
could lead to reduced structural integrity of the side cargo door
cutout of the main deck, and result in rapid depressurization of the
airplane.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
747-53A2487, Revision 1, dated October 31, 2002, which describes
procedures for repetitive internal detailed or eddy current inspections
for cracking of the lower lobe panel of the fuselage skin of the aft
cargo bay at section 46, below stringer 34L, from STA 1640 through 1740
inclusive. If any cracking is found, the service bulletin specifies
contacting the manufacturer for repair information. The service
bulletin also recommends that operators submit inspection findings to
Boeing following each inspection. Accomplishment of the actions
specified in the service bulletin is intended to adequately address the
identified unsafe condition.
Explanation of the Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, this AD
requires
[[Page 70681]]
accomplishment of the actions specified in the service bulletin
described previously, except as discussed below.
Differences Between AD and Service Bulletin
The service bulletin specifies that the manufacturer may be
contacted for disposition of repairs; however, this AD requires all
repairs to be accomplished per a method approved by 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 Manager, Seattle Aircraft Certification Office, to
make such findings.
Although the service bulletin recommends that operators report
findings to the manufacturer after each inspection, this AD does not
include such a reporting requirement.
Interim Action
This is considered to be interim action. The manufacturer has
advised that it currently is developing a modification that will
address the unsafe condition addressed by this AD. Once this
modification is developed, approved, and available, we may consider
additional rulemaking.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the AD is
being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2002-NM-270-AD.'' The postcard will be date stamped
and returned to the commenter.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:
2002-23-15 Boeing: Amendment 39-12959. Docket 2002-NM-270-AD.
Applicability: Model 747-100, -200B, -200C, -200F, -300, -400, -
400F, and 747SR series airplanes; equipped with a main deck side
cargo door manufactured by Boeing; certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (d) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To find and fix cracking of the lower lobe panel of the fuselage
skin of the aft cargo bay, which could lead to reduced structural
integrity of the side cargo door cutout of the main deck, and result
in rapid depressurization of the airplane, accomplish the following:
Repetitive Inspections
(a) Do either an internal detailed or eddy current inspection to
find cracking of the lower lobe panel of the fuselage skin of the
aft cargo bay, below stringer 34L, from Station (STA) 1640 through
1740 inclusive, per Boeing Alert Service Bulletin 747-53A2487,
Revision 1, dated October 31, 2002. Do the initial inspection at the
time shown in paragraph (a)(1) or (a)(2) of this AD, as applicable.
If the initial inspection was a detailed inspection, repeat that
inspection at least every 50 flight cycles; if the initial
inspection was an eddy current inspection, repeat that inspection at
least every 250 flight cycles; as applicable. Although the service
bulletin references a reporting requirement in paragraph 1.D., such
reporting is not required by this AD.
[[Page 70682]]
Note 2: For the purposes of this AD, a detailed inspection is
defined as: ``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.''
(1) For airplanes on which the main deck side cargo door (MDSCD)
was installed after the date of manufacture of the airplane: Do the
inspection within 10,000 flight cycles after installation of the
MDSCD, or within 90 days after the effective date of this AD,
whichever is later.
(2) For airplanes on which the MDSCD was installed before the
date of manufacture of the airplane: Do the inspection prior to the
accumulation of 15,000 total flight cycles on the airplane, or
within 90 days after the effective date of this AD, whichever is
later.
(b) Inspections done before the effective date of this AD per
Boeing Alert Service Bulletin 747-53A2487, dated October 24, 2000;
are considered acceptable for compliance with paragraph (a) of this
AD.
Repair
(c) If any crack is found during any inspection required by
paragraph (a) of this AD: Before further flight, repair 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 by the
Manager, Seattle ACO, as required by this paragraph, the Manager's
approval letter must specifically reference this AD.
Alternative Methods of Compliance
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Seattle ACO. Operators shall submit
their requests through an appropriate FAA Principal Maintenance
Inspector, who may add comments and then send it to the Manager,
Seattle ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
Special Flight Permits
(e) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
Incorporation by Reference
(f) Unless otherwise provided by this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin 747-53A2487,
Revision 1, dated October 31, 2002. This incorporation by reference
was approved by the Director of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from
Boeing Commercial Airplane Group, PO Box 3707, Seattle, Washington
98124-2207. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
Effective Date
(g) This amendment becomes effective on December 11, 2002.
Issued in Renton, Washington, on November 14, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-29675 Filed 11-25-02; 8:45 am]
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