AD 2000-01-18

[Federal Register Volume 65, Number 12 (Wednesday, January 19, 2000)]
[Rules and Regulations]
[Pages 2862-2864]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-1119]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-217-AD; Amendment 39-11516; AD 2000-01-18]
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 a one-time eddy current conductivity test to determine 
the material type of the lower cap of the wing front spar; and 
modification of the lower cap of the wing front spar, if necessary. 
This amendment is prompted by reports of stress corrosion cracking in 
the forward tang of the lower caps of the wing front spar. The actions 
specified by this AD are intended to prevent such stress corrosion 
cracking, which if not corrected, could result in reduced structural 
integrity of the wing.

DATES:  Effective February 23, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 23, 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, 3960 Paramount Boulevard, 
Lakewood, California; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

[[Page 2863]]


FOR FURTHER INFORMATION CONTACT:  Greg DiLibero, 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 57792). That action proposed to require a one-time eddy 
current conductivity test to determine the material type of the lower 
cap of the wing front spar; and modification of the lower cap of the 
wing front spar, 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 3 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 AD on U.S. operators is estimated to be $45,180, or 
$180 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed 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:

2000-01-18 McDonnell Douglas: Amendment 39-11516. Docket 99-NM-21-
AD.
    Applicability: Model DC-8 series airplanes, as listed in 
McDonnell Douglas Service Bulletin DC8-57-030, Revision 05, dated 
April 28, 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 (c) 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 stress corrosion cracking of the lower cap of the 
wing front spar, which if not corrected, could result in reduced 
structural integrity of the wing, accomplish the following:
    (a) Within 48 months after the effective date of this AD, 
perform a one-time eddy current conductivity test to determine the 
material type of the forward tang of the lower cap of the front spar 
in the center section of the wing, in accordance with McDonnell 
Douglas Service Bulletin DC8-57-030, Revision 05, dated April 28, 
1998, or Revision 04, dated August 17, 1995.
    (1) If 7079-T6 aluminum is not found, no further action is 
required by this AD.
    (2) If any 7079-T6 aluminum is found, within 48 months after the 
effective date of this AD, modify the forward tang of the lower cap 
of the front spar, in accordance with the service bulletin.
    (b) Accomplishment of the eddy current conductivity test, and 
modification, if necessary, specified in paragraph (a) of this AD 
constitutes terminating action for the repetitive inspection 
requirements of paragraph (a) of AD 90-16-05, amendment 39-6614, as 
it applies to the inspections of the forward tang of the lower cap 
of the front spar specified in McDonnell Douglas Service Bulletin 
DC8-57-030, Revision 3, dated December 10, 1970.

Alternative Methods of Compliance

    (c) 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 Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate. 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 2:  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

    (d) 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

    (e) The actions shall be done in accordance with McDonnell 
Douglas Service Bulletin DC8-57-030, Revision 05, dated April 28, 
1998, or McDonnell Douglas Service Bulletin DC8-57-030, Revision 04, 
dated August 17, 1995. 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

[[Page 2864]]

Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (f) This amendment becomes effective on February 23, 2000.

    Issued in Renton, Washington, on January 11, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-1119 Filed 1-18-00; 8:45 am]
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