AD 2001-24-28

[Federal Register Volume 66, Number 239 (Wednesday, December 12, 2001)]
[Rules and Regulations]
[Pages 64107-64109]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-30204]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-210-AD; Amendment 39-12545; AD 2001-24-28]
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 supersedes an existing airworthiness directive 
(AD), applicable to certain McDonnell Douglas Model DC-8 series 
airplanes, that currently requires repetitive visual and eddy current 
inspections to detect cracking of the rudder pedals adjuster hub 
assembly, and replacement of the assembly with a new assembly, if 
necessary. This amendment requires accomplishment of a terminating 
action for the repetitive inspections. This amendment also adds 
airplanes to the applicability of the existing AD. This amendment is 
prompted by the FAA's determination that further rulemaking is 
necessary. The actions specified by this AD are intended to prevent 
loss of rudder pedals control and reduction of braking capability.

DATES: Effective January 16, 2002.
    The incorporation by reference of McDonnell Douglas DC-8 Alert 
Service Bulletin A27-275, Revision 1, dated February 3, 1992, was 
approved previously by the Director of the Federal Register as of 
January 22, 1993 (57 FR 60115, December 18, 1992).
    The incorporation by reference of the remaining service documents 
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 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: Wahib Mina, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone 
(562) 627-5324; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 92-27-06, 
amendment 39-8440 (57 FR 60115, December 18, 1992), which is applicable 
to certain McDonnell Douglas Model DC-8 series airplanes, was published 
in the Federal Register on July 23, 2001 (66 FR 38203). The action 
proposed to continue to require repetitive visual and eddy current 
inspections to detect cracking of the rudder pedals adjuster hub 
assembly, and replacement of the assembly with a new assembly, if 
necessary. That action also proposed to require accomplishment of a 
terminating action for the repetitive inspections, and to add airplanes 
to the applicability of the existing AD.

[[Page 64108]]

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Request To Withdraw Notice of Proposed Rulemaking (NPRM) or Remove 
Mandatory Requirement for Replacement

    The commenter requests that the FAA withdraw the NPRM, since the 
inspections required by existing AD 92-27-06 provide an appropriate 
degree of safety assurance. The commenter states that there have been 
no loss of rudder pedal control incidents reported since the start of 
the inspections required by AD 92-27-06. The commenter further states 
that the loss of rudder pedal control by a flightcrew member is a 
temporary unsafe condition, since the other flightcrew member can 
immediately control the airplane with his/her rudder pedals. The 
commenter also states that of the 107 inspections it has performed on 
DC-8 rudder pedal adjuster hub assemblies since June 1994, no 
inspections have resulted in finding cracks. The commenter points out 
that a review of the FAA Service Difficulty Reports database reveals 
that no DC-8 rudder pedal control has been lost during flight or taxi 
because of a cracked rudder pedal adjuster hub assembly.
    This same commenter suggests in lieu of withdrawing the NPRM to 
remove the compliance time of ``Prior to the accumulation of 15,000 
total landings, or within 3,500 landings after the effective date of 
this AD'' in paragraph (e) of the NPRM, so that the replacement 
requirement is optional.
    The FAA does not agree with the commenter to withdraw the NPRM or 
remove the mandatory replacement requirement. As specified in the 
``Background'' section of the NPRM, the FAA has determined that, based 
on the results of investigations described in the NPRM and 
recommendations of the Aging Transport Systems Rulemaking Advisory 
Committee (ATSRAC), corrective action is necessary to minimize the 
potential hazards associated with wire and mechanical flight control 
systems degradation and related causal factors (e.g., inadequate 
maintenance, contamination, improper repair, and mechanical damage).
    In addition, the FAA has determined that long-term continued 
operational safety will be better assured by modifications or design 
changes to remove the source of the problem, rather than by repetitive 
inspections. Long-term inspections may not be providing the degree of 
safety assurance necessary for the transport airplane fleet. This, 
coupled with a better understanding of the human factors associated 
with numerous repetitive inspections, has led the FAA to consider 
placing less emphasis on special procedures and more emphasis on design 
improvements. The terminating action required by paragraph (e) of this 
final rule is consistent with these considerations.

Clarification of Paragraph Reference

    Paragraph (c) of the proposed AD states ``If no crack is detected 
as a result of the inspections required by paragraph (a) of this AD, 
repeat the inspections at intervals not to exceed 3,500 landings.'' The 
FAA's intent was that the repeat inspections be accomplished if no 
crack is detected as a result of the inspection required by paragraph 
(a) or (b) of this AD, as indicated in service bulletins referenced in 
the AD. Therefore, we have revised the final rule accordingly.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 264 Model DC-8 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 245 
airplanes of U.S. registry will be affected by this AD.
    The inspection that is currently required by AD 92-27-06 takes 
approximately 3 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 $44,100, or $180 per airplane, per inspection cycle.
    The new actions that are required by this AD will take 
approximately 8 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$4,296 per airplane. Based on these figures, the cost impact of the new 
requirements of this AD on U.S. operators is estimated to be 
$1,170,120, or $4,776 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, 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 39-8440 (57 FR 
60115, December 18, 1992), and by adding a new airworthiness directive 
(AD), amendment 39-12545, to read as follows:


[[Page 64109]]


2001-24-28  McDonnell Douglas: Amendment 39-12545. Docket 2001-NM-
210-AD. Supersedes AD 92-27-06, Amendment 39-8440.

    Applicability: Model DC-8 series airplanes, serial numbers 45646 
and 45928, and as listed in McDonnell Douglas DC-8 Alert Service 
Bulletin A27-275, Revision 1, dated February 3, 1992; 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 loss of rudder pedals control and reduction of 
braking capability, accomplish the following:

Inspection

    (a) For airplanes listed in McDonnell Douglas DC-8 Alert Service 
Bulletin A27-275, Revision 1, dated February 3, 1992: Prior to the 
accumulation of 15,000 landings or within 270 days after January 22, 
1993 (the effective date of AD 92-27-06, amendment 39-8440), 
whichever occurs later, conduct a visual and eddy current inspection 
to detect cracks of the rudder pedals adjuster hub assembly, part 
number (P/N) 4616066, in accordance with McDonnell Douglas DC-8 
Alert Service Bulletin A27-275, Revision 1, dated February 3, 1992, 
or Revision 2, dated August 5, 1992; or McDonnell Douglas Alert 
Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996. As 
of the effective date of this AD only McDonnell Douglas Alert 
Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996, 
shall be used.
    (b) For airplanes having serial numbers 45646 and 45928: Prior 
to the accumulation of 15,000 total landings, or within 270 days 
after the effective date of this AD, whichever occurs later, conduct 
a visual and eddy current inspection to detect cracks of the rudder 
pedals adjuster hub assembly, P/N 4616066, in accordance with 
McDonnell Douglas DC-8 Alert Service Bulletin A27-275, Revision 1, 
dated February 3, 1992, or Revision 2, dated August 5, 1992; or 
McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, 
dated April 5, 1996. As of the effective date of this AD, only 
McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, 
dated April 5, 1996, shall be used.

No Crack Found During Inspection Required by Paragraph (a) or (b) of 
This AD: Repetitive Inspections

    (c) If no crack is detected as a result of the inspections 
required by paragraph (a) or (b) of this AD, repeat the inspections 
at intervals not to exceed 3,500 landings.

Any Crack Found: Replacement and Repetitive Inspections

    (d) If any crack is detected as a result of the inspections 
required by paragraph (a), (b), or (c) of this AD, prior to further 
flight, replace the rudder pedals adjuster hub assembly, P/N 
4616066, with a new assembly, P/N 5965435-1, in accordance with 
McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, 
dated April 5, 1996. Accomplishment of the replacement constitutes 
terminating action for the repetitive inspection requirements of 
this AD.

Terminating Action

    (e) Prior to the accumulation of 15,000 total landings, or 
within 3,500 landings after the effective date of this AD, whichever 
occurs later, replace the existing adjuster hub assembly with a new 
assembly, P/N 5965435-1, per McDonnell Douglas Alert Service 
Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996. 
Accomplishment of the replacement constitutes terminating action for 
the requirements of this AD.

Spares

    (f) As of the effective date of this AD, no person shall install 
an adjuster hub assembly, P/N 4616066, on any airplane.

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 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

    (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 McDonnell 
Douglas DC-8 Alert Service Bulletin A27-275, Revision 1, dated 
February 3, 1992; McDonnell Douglas DC-8 Alert Service Bulletin A27-
275, Revision 2, dated August 5, 1992; or McDonnell Douglas Alert 
Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996; as 
applicable.
    (1) The incorporation by reference of McDonnell Douglas DC-8 
Alert Service Bulletin A27-275, Revision 1, dated February 3, 1992, 
was approved previously by the Director of the Federal Register as 
of January 22, 1993 (57 FR 60115, December 18, 1992).
    (2) The incorporation by reference of the remaining service 
documents is approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (3) 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 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. 01-30204 Filed 12-11-01; 8:45 am]
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