[Federal Register Volume 67, Number 152 (Wednesday, August 7, 2002)]
[Rules and Regulations]
[Pages 51065-51068]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-19879]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 67, No. 152 / Wednesday, August 7, 2002 /
Rules and Regulations
[[Page 51065]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-130-AD; Amendment 39-12840; AD 2002-16-01]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-8-21, -31, -
32, -33, -41, -42, and -43 Airplanes; and Model DC-8-50, -60, and -70
Series Airplanes; Modified per Supplemental Type Certificates SA1063SO,
SA1862SO, or SA1832SO
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 McDonnell Douglas Model DC-8-21, -31, -32, -
33, -41, -42, and -43 airplanes; and certain Model DC-8-50, -60, and -
70 series airplanes; that have been converted from a passenger-to a
cargo-carrying (``freighter'') configuration. This action requires
gaining access to the floor beam attachments to the lower door jamb
within the main cargo door area; performing repetitive inspections to
detect cracking or damage of such attachments, including splice plates,
angles, and clips; and, if necessary, expanding the inspection area and
replacing any cracked or damaged part with a new part. This action is
necessary to prevent failure of such floor beam attachments during
ground or flight operations, which could cause damage to the floor
structure and consequent jamming of the flight control cables, and
result in loss of controllability of the airplane in flight.
DATES: Effective August 22, 2002.
Comments for inclusion in the Rules Docket must be received on or
before October 7, 2002.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-130-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:
[email protected]. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-130-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.
Information pertaining to this amendment may be examined at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Atlanta Certification Office, One Crown
Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia.
FOR FURTHER INFORMATION CONTACT: Technical Information: Hassan Amini,
Aerospace Engineer, Airframe and Propulsion Branch, ACE-117A, FAA,
Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix
Boulevard, suite 450, Atlanta, Georgia 30349; telephone (770) 703-6080;
fax (770) 703-6097.
Other Information: Sandi Carli, Airworthiness Directive Technical
Editor/Writer; telephone (425) 687-4243, fax (425) 687-4271. Questions
or comments may also be sent via the Internet using the following
address: [email protected]. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.
SUPPLEMENTARY INFORMATION: The FAA has received several reports of
findings of cracked or broken angles and splice plates on floor beam
attachments to the lower door jamb of the main cargo door area on
certain McDonnell Douglas Model DC-8-21, -31, -32, -33, -41, -42, and -
43 airplanes; and Model DC-8-50, -60, and -70 series airplanes. One
report revealed that, during a routine C-check on a Model DC-8-62
airplane, fractures were found in 9 of 11 of the floor beam attachments
to the lower door jamb. Findings indicate that such fractures could be
due to factors associated with flight operations and/or loading
operations on the ground. Such conditions, if not corrected, could
cause failure of such floor beam attachments during ground or flight
operations. This could cause damage to the floor structure and
consequent jamming of the control cables, and result in loss of
controllability of the airplane in flight.
Explanation of 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 is
being issued to prevent failure of the floor beam attachments to the
lower door jamb. Such failure could cause damage to the floor structure
and consequent jamming of the flight control cables, and result in loss
of controllability of the airplane in flight. This AD requires gaining
access to the floor beam attachments to the lower door jamb within the
main cargo door area; and performing repetitive inspections to detect
cracking or damage of such attachments, including splice plates,
angles, and clips. If any cracking or damage is found, this AD also
requires extending the area of inspection 60 inches forward and aft of
the main cargo door area, and replacing any cracked or damaged part
with a new part. Figure 1 of Appendix 1 of this AD identifies the
inspection area and parts to be inspected.
This AD also requires operators to report the results of any
detailed inspection required by paragraph (a) of this AD to the FAA.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Because the cause of the addressed cracking or damage is not currently
known, the intent of the required inspection report is to enable the
FAA to determine how widespread such cracking or damage may be in the
affected fleet. Based on the results of this report, further corrective
action may be warranted.
[[Page 51066]]
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:
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.
For each issue, state what specific change to the AD is
being requested.
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-130-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, 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:
2002-16-01 McDonnell Douglas:Amendment 39-12840. Docket 2002-NM-
130-AD.
Applicability: This AD applies to airplanes that have been
converted from a passenger-to a cargo-carrying (``freighter'')
configuration per Supplemental Type Certificate SA1063SO, SA1862SO,
or SA1832SO; certificated in any category; as listed in the
following table:
Table--Applicability
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Airplane Models
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DC-8-21, -31, -32, -33, -41, -42, and -43 airplanes;
DC-8-51, -52, -53, and -55 airplanes;
DC-8-61, -62, and -63 airplanes; and
DC-8-71, -72, and -73 airplanes.
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Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 prevent failure of the floor beam attachments to the lower
door jamb of the main cargo door due to cracking or damage during
ground or flight operations, which could cause damage to the floor
structure and consequent jamming of the flight control cables, and
result in loss of controllability of the airplane in flight;
accomplish the following:
Gaining Access and Repetitive Inspections
(a) Within 50 flight hours or 60 days after the effective date
of this AD, whichever occurs later, accomplish the actions required
by paragraphs (a)(1) and (a)(2) of this AD.
(1) Gain access to the floor beam attachments to the lower door
jamb within the main cargo door area by removing the cargo handling
system (including ball mats, roller trays, and pallet locks), floor
panels, and cargo liner of the lower baggage compartment as
necessary to access both sides of the floor beam attachments.
(2) Perform a detailed inspection of the main cargo door area to
detect any cracking or damage of the floor beam attachments to the
lower door jamb, including the splice plates, angles, and clips
identified in Figure 1 of Appendix 1 of this AD Thereafter, repeat
the inspection at intervals not to exceed 2,500 flight cycles or 18
months, whichever occurs earlier.
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.''
[[Page 51067]]
Extending Inspection Area and Replacement
(b) If any cracking or damage is found during any inspection
required by paragraph (a)(2) of this AD, before further flight,
extend the area of inspection 60 inches forward and aft of the main
cargo door area, and replace any cracked or damaged part with a new
part identified in Figure 1 of Appendix 1 of this AD.
Reporting Requirement
(c) Within 10 days after performing any inspection required by
paragraph (a)(2) of this AD: Send a report of the inspection
findings to the Manager, Atlanta Aircraft Certification Office
(ACO), One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta,
Georgia 30349; telephone (770) 703-6080; fax (770) 703-6097. The
report must include the inspection results, including a description
of any cracking or damage found, crack location and length, part
number of any cracked or damaged part, airplane serial number,
number of flight cycles and flight hours on the airplane, and number
of flight cycles and flight hours after the airplane was converted
from a passenger-to a cargo-carrying (``freighter'') configuration.
Information collection requirements contained in this AD have been
approved by the Office of Management and Budget (OMB) under the
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control Number 2120-0056.
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, Atlanta ACO. Operators shall submit
their requests through an appropriate FAA Principal Maintenance
Inspector, who may add comments and then send it to the Manager,
Atlanta ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta 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.
Effective Date
(f) This amendment becomes effective on August 22, 2002.
Appendix 1
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[GRAPHIC] [TIFF OMITTED] TR07AU02.010
[[Page 51068]]
Issued in Renton, Washington, on July 29, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-19879 Filed 8-6-02; 8:45 am]
BILLING CODE 4910-13-C