[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
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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.

-----------------------------------------------------------------------

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
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
                             Airplane Models
------------------------------------------------------------------------
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.
------------------------------------------------------------------------


    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

BILLING CODE 4910-13-P
[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