AD 2001-24-34

[Federal Register Volume 66, Number 239 (Wednesday, December 12, 2001)]
[Rules and Regulations]
[Pages 64097-64099]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-30210]



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Federal Register / Vol. 66, No. 239 / Wednesday, December 12, 2001 / 
Rules and Regulations

[[Page 64097]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-222-AD; Amendment 39-12551; AD 2001-24-34]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-70 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all McDonnell Douglas Model DC-8-70 series 
airplanes, that currently requires repetitive inspections and repair or 
replacement, if necessary, of the generator power feeder cables, 
supporting brackets, and clamps at all the engine pylons. This 
amendment requires accomplishment of a terminating action for the 
repetitive inspections. This amendment also requires replacement of the 
support clamps of the generator power feeder cable on engine nacelles/
pylons 1, 2, 3, and 4 with new support clamps. This amendment is 
prompted by the FAA's determination that further rulemaking is 
necessary. The actions specified by this AD are intended to prevent a 
fire on the ground if a fuel leak exists in an engine pylon.

DATES: Effective January 16, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 16, 2002.

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: Data 
and Service Management, Dept. C1-L5A (D800-0024). 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 the FAA, 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.

FOR FURTHER INFORMATION CONTACT: Elvin Wheeler, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5344; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 88-11-03, 
amendment 39-5922 (53 FR 17018, May 13, 1988), which is applicable to 
all McDonnell Douglas Model DC-8-70 series airplanes, was published in 
the Federal Register on July 23, 2001 (66 FR 38220). The action 
proposed to continue to require repetitive inspections and repair or 
replacement, if necessary, of the generator power feeder cables, 
supporting brackets, and clamps at all the engine pylons. The action 
also proposed to require accomplishment of a terminating action for the 
repetitive inspections, and replacement of the support clamps of the 
generator power feeder cable on engine nacelles/pylons 1, 2, 3, and 4 
with new support clamps.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 108 Model DC-8-70 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 98 
airplanes of U.S. registry will be affected by this AD.
    The inspection that is currently required by AD 88-11-03, and 
retained in this AD, takes approximately 12 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $70,560, or $720 per airplane, per 
inspection cycle.
    The new replacement specified in McDonnell Douglas DC-8-70 Service 
Bulletin 24-72, dated January 14, 1992, that is required in this AD 
will take approximately 3 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Required parts will cost 
approximately $675 per airplane. Based on these figures, the cost 
impact of this replacement required by this AD on U.S. operators is 
estimated to be $83,790, or $855 per airplane.
    The new inspection and application of sealants specified in 
McDonnell Douglas DC-8-70 Service Bulletin 24-71, Revision 1, dated 
February 25, 1991, that are required in this AD will take approximately 
5 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of the 
inspection and application of sealants required by this AD on U.S. 
operators is estimated to be $29,400, or $300 per airplane.
    The new replacement specified in McDonnell Douglas DC-8-70 Service 
Bulletin 24-73, dated May 30, 1990, that is required in this AD will 
take approximately 16 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Required parts will cost 
approximately $715 per airplane. Based on these figures, the cost 
impact of this replacement required by this AD on U.S. operators is 
estimated to be $164,150, or $1,675 per airplane.
    The cost impact figures discussed above are 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up,

[[Page 64098]]

planning time, or time necessitated by other administrative actions.

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 removing amendment 39-5922 (53 FR 
17018, May 13, 1988), and by adding a new airworthiness directive (AD), 
amendment 39-12551, to read as follows:

2001-24-34  McDonnell Douglas: Amendment 39-12551. Docket 2001-NM-
222-AD. Supersedes AD 88-11-03, Amendment 39-5922.

    Applicability: All Model DC-8-70 airplanes, 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 (g) 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 a fire on the ground if a fuel leak exists in an 
engine pylon, accomplish the following:

Restatement of Requirements of
AD 88-11-03

Repetitive Inspections, Verification, and Corrective Actions, if 
Necessary

    (a) Within 30 days after June 3, 1988 (the effective date of AD 
88-11-03, amendment 39-5922), unless previously accomplished within 
the last 3,500 flight hours, inspect the generator power feeder 
cables, support brackets, and clamps between bulkhead feed-through 
at station YN=278.500 and terminal strip S3-7000 at engine pylons 1, 
2, 3, and 4, for evidence of arcing, burning, chafing, damage, or 
cable droop, in accordance with the Accomplishment Instructions of 
McDonnell Douglas DC-8-70 Alert Service Bulletin A24-72, dated April 
6, 1988.
    (1) If no evidence of arcing, burning, chafing, damage, or 
drooping exists, proceed to paragraph (a)(3) of this AD.
    (2) If any evidence of arcing, burning, chafing, damage, or 
drooping exists, prior to further flight, repair or replace parts, 
as required, in accordance with the service bulletin.
    (3) Verify that the nuts securing cable terminals to terminal 
strip S3-7000 are tightened to a torque of 120 to 130 inch-pounds.

Repetitive Inspection Interval

    (b) Repeat the procedures specified in paragraph (a) of this AD 
at intervals not to exceed 3,500 flight hours.

New Actions Required by This AD

Terminating Actions for Repetitive Inspections and Verification

    (c) Within 1 year after the effective date of this AD, replace 
the support clamps of the generator power feeder cable on engine 
pylons 1, 2, 3, and 4 with new support clamps, in accordance with 
McDonnell Douglas DC-8-70 Service Bulletin 24-72, dated January 14, 
1992. The requirements of paragraphs (a)(1) and (a)(2) of this AD 
must be done prior to or in conjunction with the requirements of 
this paragraph.
    (d) Within 1 year after the effective date of this AD, do the 
actions specified in paragraphs (d)(1) and (d)(2) of this AD in 
accordance with McDonnell Douglas DC-8-70 Service Bulletin 24-71, 
Revision 1, dated February 25, 1991. The requirements of paragraph 
(a)(3) of this AD must be done prior to or in conjunction with the 
requirements of this paragraph.
    (1) Do a general visual inspection of the terminal strip of the 
terminal connections of the generator power feeder cable for general 
condition (i.e., loose connections) and to verify that the ground 
studs are tight and that the nuts securing the cable terminals to 
the terminal strip are tightened to a torque of 120 to 130 inch-
pound, in accordance with the service bulletin. If any terminal 
connection is loose, not tight, or torqued improperly, prior to 
further flight, tighten terminal connection in accordance with the 
service bulletin.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (2) Apply a coat of certain sealants per Figure 1 of the service 
bulletin.
    (e) Accomplishment of the actions required by paragraphs (c) and 
(d) of this AD constitute terminating action for the requirements of 
paragraphs (a) and (b) of this AD.

Replacement of Certain Support Clamps

    (f) Within 1 year after the effective date of this AD, replace 
the support clamps of the generator power feeder cable in the 
forward pylon on engine nacelles 1, 2, 3, and 4 with new support 
clamps, in accordance with McDonnell Douglas DC-8-70 Service 
Bulletin 24-73, dated May 30, 1990.

Alternative Methods of Compliance

    (g) 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. 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 3: 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

    (h) 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

    (i) The actions shall be done in accordance with of McDonnell 
Douglas DC-8-70 Alert Service Bulletin A24-72, dated April 6, 1988; 
McDonnell Douglas DC-8-70 Service Bulletin 24-72, dated January 14, 
1992; McDonnell Douglas DC-8-70 Service Bulletin 24-71, Revision 1, 
dated February 25, 1991; and McDonnell Douglas DC-8-70 Service 
Bulletin 24-73, dated May 30, 1990; as applicable. This 
incorporation by

[[Page 64099]]

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: 
Data and Service Management, Dept. C1-L5A (D800-0024). Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the the FAA, 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.

Effective Date

    (j) This amendment becomes effective on January 16, 2002.

    Issued in Renton, Washington, on November 28, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-30210 Filed 12-11-01; 8:45 am]
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