[Federal Register Volume 66, Number 57 (Friday, March 23, 2001)]
[Rules and Regulations]
[Pages 16105-16107]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-6643]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-254-AD; Amendment 39-12151; AD 2001-06-04]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-33, -42, -
55, and -61 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to McDonnell Douglas Model DC-8-33, -42, -55, and -61 series 
airplanes. This action requires detailed visual and eddy current 
inspections of the lower wing skin at the 3 outboard fasteners of 
stringer 64 end fitting to detect cracks; and corrective actions, if 
necessary. This action is necessary to prevent fatigue cracking of the 
lower wing skin, which could reduce structural integrity and loss of 
fail-safe capability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective April 9, 2001.
    The incorporation by reference of McDonnell Douglas Service 
Bulletin
    DC8-57-100, Revision 02, dated June 21, 2000, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
April 9, 2001.
    The incorporation by reference of McDonnell Douglas Service 
Bulletin DC8-57-100, Revision 01, dated August 26, 1998, as listed in 
the regulations, was approved previously by the Director of the Federal 
Register as of February 29, 2000 (65 FR 3794, January 25, 2000).
    Comments for inclusion in the Rules Docket must be received on or 
before May 22, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-254-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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. 2000-NM-254-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 this AD may be obtained from 
Boeing Commercial Aircraft Group, Long Beach

[[Page 16106]]

Division, 3855 Lakewood Boulevard, Long Beach, California 90846, 
Attention: Technical Publications Business Administration, Dept. C1-L51 
(2-60). This information may be examined at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, 
Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Greg DiLibero, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5231; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: On January 13, 2000, the FAA issued AD 2000-
02-01, amendment 39-11518 (65 FR 3794, January 25, 2000), applicable to 
certain McDonnell Douglas Model DC-8 series airplanes, to require 
detailed visual and eddy current inspections of the lower wing skin at 
the 3 outboard fasteners of stringer 64 end fitting to detect cracks; 
and corrective actions, if necessary. The actions required by that AD 
are intended to prevent fatigue cracking of the lower wing skin, which 
could reduce structural integrity and loss of fail-safe capability of 
the airplane.

Actions Since Issuance of AD 2000-02-01

    Since the issuance of AD 2000-02-01, the FAA has received a report 
indicating that certain serial numbers of the affected airplanes were 
inadvertently omitted from McDonnell Douglas Service Bulletin DC8-57-
100, Revision 01, dated August 26, 1998 (which was referenced in AD 
2000-02-01 as the appropriate source of service information). These 
additional airplanes are subject to the addressed unsafe condition.

Explanation of Relevant Service Information

    The FAA has reviewed and approved McDonnell Douglas Service 
Bulletin DC8-57-100, Revision 02, dated June 21, 2000. The detailed 
visual and eddy current inspections and corrective actions are 
identical to those described in Revision 01 of the service bulletin. 
Revision 02 of the service bulletin expands the effectivity listing to 
include additional airplanes and clarifies information about a non-
destructive testing reference standards and test equipment. 
Accomplishment of the actions specified in either of the service 
bulletins is intended to adequately address the identified unsafe 
condition.

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 fatigue cracking of the lower wing skin, which 
could reduce structural integrity and loss of fail-safe capability of 
the airplane. This AD requires accomplishment of the actions specified 
in the service bulletin (either revision level) described previously.

Cost Impact

    None of the Model McDonnell Douglas Model DC-8-33, -42, -55, and -
61 series airplanes affected by this action are on the U.S. Register. 
All airplanes included in the applicability of this rule currently are 
operated by non-U.S. operators under foreign registry; therefore, they 
are not directly affected by this AD action. However, the FAA considers 
that this rule is necessary to ensure that the unsafe condition is 
addressed in the event that any of these subject airplanes are imported 
and placed on the U.S. Register in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 4 work hours to 
accomplish the required actions, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$240 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and 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 2000-NM-254-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.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

[[Page 16107]]

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:

2001-06-04  McDonnell Douglas: Amendment 39-12151. Docket 2000-NM-
254-AD.

    Applicability: Model DC-8-33, -42, -55, and -61 series 
airplanes, manufacturer's fuselage numbers 0079, 0115, 0246, and 
0325; 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 (b) 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 fatigue cracking of the lower wing skin, which could 
reduce structural integrity and loss of fail-safe capability of the 
airplane, accomplish the following:

    Note 2: This AD will affect Principal Structural Elements (PSE) 
57.08.037, 57.08.038, 57.08.021, and 57.08.022 of the DC-8 
Supplemental Inspection Document (SID).

Inspection, Repair, and Modification

    (a) Within 24 months after the effective date of this AD, do 
detailed visual and eddy current inspections to detect cracks in the 
lower wing skin fastener holes in the area surrounding 3 outboard 
fasteners of stringer 64 end fitting, per McDonnell Douglas Service 
Bulletin DC8-57-100, Revision 01, dated August 26, 1998; or Revision 
02, dated June 21, 2000.

    Note 3: 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) If any crack is detected in the skin fastener holes and it 
is less than 3.1 inches long, before further flight, repair per the 
service bulletin. Within 14,100 landings after accomplishment of the 
repair, inspect the lower wing skin to detect cracks, per a method 
approved by the Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA.
    (2) If any crack is detected in the skin fastener holes and it 
is greater than or equal to 3.1 inches long, before further flight, 
repair per a method approved by the Manager, Los Angeles ACO.
    (3) If no crack is found, within 24 months after the effective 
date of this AD, do the preventative modification (including stress 
or split sleeve coining the three fastener holes in the skin, and 
installing new pins), per the service bulletin. Accomplishment of 
this action constitutes terminating action for the requirements of 
this AD.

    Note 4: This AD does not terminate the inspection requirements 
for PSE's 57.08.037, 57.08.038, 57.08.021, and 57.08.022 of the DC-8 
SID per AD 93-01-15, amendment 39-6330.

Alternative Methods of Compliance

    (b) 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, Los Angeles ACO, FAA. Operators 
shall submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angeles ACO.

    Note 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
Secs. 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

    (d) Except as provided by paragraphs (a)(1) and (a)(2) of this 
AD, the actions shall be done in accordance with McDonnell Douglas 
Service Bulletin DC8-57-100, Revision 01, dated August 26, 1998; or 
McDonnell Douglas Service Bulletin DC8-57-100, Revision 02, dated 
June 21, 2000.
    (1) The incorporation by reference of McDonnell Douglas Service 
Bulletin DC8-57-100, Revision 02, dated June 21, 2000, is approved 
by the Director of the Federal Register per 5 U.S.C. 552(a) and 1 
CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Service 
Bulletin DC8-57-100, Revision 01, dated August 26, 1998, was 
approved previously by the Director of the Federal Register as of 
February 29, 2000 (65 FR 3794, January 25, 2000).
    (3) Copies may be obtained from Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Technical Publications Business 
Administration, Dept. C1-L51 (2-60). Copies may be inspected at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on April 9, 2001.

    Issued in Renton, Washington, on March 12, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-6643 Filed 3-22-01; 8:45 am]
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