Airworthiness Directives; McDonnell Douglas Model DC-8 Series Airplanes

[Federal Register Volume 65, Number 16 (Tuesday, January 25, 2000)]
[Rules and Regulations]
[Pages 3794-3796]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-1368]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-309-AD; Amendment 39-11518; AD 2000-02-01]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8 Series 
Airplanes

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Final rule.

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SUMMARY:  This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model DC-8 series airplanes, 
that requires detailed visual and eddy current inspections of the lower 
wing skin at the 3 outboard fasteners of the stringer 64 end fitting to 
detect cracks; and corrective actions, if necessary. This amendment is 
prompted by reports of fatigue cracks found in the lower wing skin 
initiating from the outboard fasteners of the stringer 64 end fitting. 
The actions specified by this AD are intended to prevent such fatigue 
cracking, which could reduce structural integrity and loss of fail-safe 
capability of the airplane.

DATES:  Effective February 29, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 29, 2000.

ADDRESSES:  The service information referenced in this AD 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). 
This information may be examined at the Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, 
Los Angeles Aircraft Certification Office,

[[Page 3795]]

3960 Paramount Boulevard, Lakewood, California; 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, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5231; fax (562) 
627-5210.

SUPPLEMENTARY INFORMATION:  A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
DC-8 series airplanes was published in the Federal Register on October 
27, 1999 (64 FR 57806). That action proposed to require detailed visual 
and eddy current inspections of the lower wing skin at the 3 outboard 
fasteners of the stringer 64 end fitting to detect cracks; and 
corrective actions, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    There are approximately 294 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 251 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 4 work 
hours per airplane to accomplish the required inspection, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the inspection required by this AD on U.S. operators is 
estimated to be $60,240, or $240 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.

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.

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:

2000-02-01  McDonnell Douglas: Amendment 39-11518. Docket 98-NM-309-
AD.

    Applicability: Model DC-8 series airplanes, as listed in 
McDonnell Douglas Service Bulletin DC8-57-100, Revision 01, dated 
August 26, 1998; 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, 
perform detailed visual and eddy current inspections to detect 
cracks in the lower wing skin fastener holes in the area surrounding 
3 outboard fasteners of the stringer 64 end fitting, in accordance 
with McDonnell Douglas Service Bulletin DC8-57-100, Revision 01, 
dated August 26, 1998.

    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, prior to further flight, repair in 
accordance with the service bulletin. Within 14,100 landings after 
accomplishment of the repair, inspect the lower wing skin to detect 
cracks, in accordance with a method approved by the Manager, Los 
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate.
    (2) If any crack is detected in the skin fastener holes and it 
is greater than or equal to 3.1 inches long, prior to further 
flight, repair in accordance with 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, accomplish the preventative modification (including 
stress or split sleeve coining the three fastener holes in the skin, 
and installing new pins), in accordance with 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 in accordance with 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. 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.

[[Page 3796]]


    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 
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

    (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. 
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 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, Transport Airplane Directorate, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, 
California; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (e) This amendment becomes effective on February 29, 2000.

    Issued in Renton, Washington, on January 13, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-1368 Filed 1-24-00; 8:45 am]
BILLING CODE 4910-13-U

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