[Federal Register Volume 61, Number 37 (Friday, February 23, 1996)]
[Rules and Regulations]
[Pages 6922-6924]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-844]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-20-AD; Amendment 39-9493; AD 96-02-05]
Airworthiness Directives; McDonnell Douglas Model DC-9 and Model
DC-9-80 Series Airplanes; Model MD-88 Airplanes; and C-9 (Military)
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-9 and Model DC-
9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) series
[[Page 6923]]
airplanes, that currently requires visual and eddy current inspections
to detect cracking of the rudder pedals adjuster hub assembly, and
replacement of the assembly, if necessary. That amendment was prompted
by several occurrences of failure of the rudder pedals adjuster hub
assembly due to broken detent lugs. This amendment provides an optional
terminating action for the required inspections, and expands the
applicability of the existing AD to include additional airplanes. The
actions specified by this AD are intended to prevent loss of rudder
pedals control and reduction of braking capability.
DATES: Effective March 25, 1996.
The incorporation by reference of certain publications, as listed
in the regulations, is approved by the Director of the Federal Register
as of March 25, 1996.
The incorporation by reference of McDonnell Douglas DC-9 Alert
Service Bulletin A27-325, Revision 1, dated February 3, 1992, as listed
in the regulations, was approved previously by the Director of the
Federal Register as of January 22, 1993 (57 FR 60116, December 18,
1992).
ADDRESSES: The service information referenced in this AD may be
obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard,
Long Beach, California 90846, Attention: Technical Publications
Business Administration, Department 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, Los Angeles Aircraft Certification Office,
Transport Airplane Directorate, 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: Augusto Coo, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712; telephone (310) 627-5225; fax (310) 627-
5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 92-27-07,
amendment 39-8441 (57 FR 60116, December 18, 1992), which is applicable
to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series
airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes,
was published in the Federal Register on April 6, 1995 (60 FR 17489).
The action proposed to continue to require visual and eddy current
inspections to detect cracking of the rudder pedals adjuster hub
assembly, and replacement of the assembly, if necessary. The action
also proposed to expand the applicability of the existing AD to include
additional airplanes.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Two commenters support the proposed rule.
Two other commenters also support the proposed rule, but request
that the FAA allow the replacement of the magnesium casting rudder
pedal adjuster hub assembly with an aluminum assembly, as described in
McDonnell Douglas DC-9 Service Bulletin 27-325, as terminating action
for the requirements of this AD.
The FAA concurs. The FAA has reviewed and approved McDonnell
Douglas DC-9 Service Bulletin 27-325, Revision 1, dated November 30,
1994, which describes procedures for replacement of the rudder pedal
adjustment hub assembly in the rudder pedal mechanism. The FAA has
determined that replacement of the existing magnesium casting with a
new aluminum part, as specified in the service bulletin, provides
optional terminating action for the repetitive inspections required by
this AD. Accordingly, the FAA has revised the final rule to add a new
paragraph (c) to specify this optional terminating action.
McDonnell Douglas Alert Service Bulletin number ``A27-325,''
Revision 1, was inadvertently omitted in paragraph (a) of the proposed
rule and a typographical error in the date of that alert service
bulletin also appeared in paragraph (a) of the proposed rule.
Additionally, McDonnell Douglas DC-9 Alert Service Bulletin number
``A27-325,'' Revision 2, dated January 27, 1995, was inadvertently
omitted in paragraph (b) of the proposed rule. The FAA has revised the
final rule to correct these typographical errors.
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 changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
There are approximately 909 Model DC-9 and Model DC-9-80 series
airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes
of the affected design in the worldwide fleet. The FAA estimates that
561 airplanes of U.S. registry will be affected by this AD, that it
would take approximately 3 work hours per airplane to accomplish the
required actions, and that the average labor rate is $60 per work hour.
Based on these figures the cost impact of this AD on U.S. operators is
estimated to be $180 per airplane.
The actions specified in this AD previously were required by AD 92-
27-07, which was applicable to approximately 373 airplanes. Based on
the figures discussed above, the cost impact of the current
requirements of that AD on U.S. operators is estimated to be $67,140.
In consideration of the compliance time and effective date of AD 92-27-
07, the FAA assumes that operators of the 373 airplanes subject to that
AD have already initiated the required actions. This AD action adds no
new costs associated with those airplanes.
This AD action is applicable to approximately 188 additional
airplanes. Based on the figures discussed above, the new costs to U.S.
operators that are imposed by this AD are estimated to be $33,840. This
figure is based on assumptions that no operator of these additional
airplanes 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 regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 6924]]
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 39-8441 (57 FR
60116, December 18, 1992), and by adding a new airworthiness directive
(AD), amendment 39-9493, to read as follows:
96-02-05 McDonnell Douglas: Amendment 39-9493. Docket 95-NM-20-AD.
Supersedes AD 92-27-07, Amendment 39-8441.
Applicability: Model DC-9-10, -20, -30, -40, and -50 series
airplanes; Model DC-9-81 (MD-81), -82 (MD-82) -83 (MD-83), and -87
(MD-87) series airplanes; Model MD-88 airplanes; and Model C-9
(military) series airplanes; as listed in McDonnell Douglas DC-9
Alert Service Bulletin A27-325, Revision 2, dated January 27, 1995;
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 use the authority
provided in paragraph (d) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously. To prevent loss of rudder pedals control and reduction
of braking capability, accomplish the following:
(a) For airplanes listed in McDonnell Douglas Alert Service
Bulletin A27-325, 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 92-27-07, amendment 39-8441),
whichever occurs later, conduct a visual and eddy current inspection
to detect cracks of the rudder pedals adjuster hub assembly, part
number 4616066, in accordance with McDonnell Douglas DC-9 Alert
Service Bulletin A27-325, Revision 1, dated February 3, 1992, or
Revision 2, dated January 27, 1995.
(1) If no cracks are detected as a result of the inspections
required by this paragraph, repeat the inspections at intervals not
to exceed 3,500 landings.
(2) If cracks are detected as a result of the inspections
required by this paragraph, prior to further flight, replace the
rudder pedals adjuster hub assembly, part number 4616066, with a new
assembly having the same part number, in accordance with McDonnell
Douglas DC-9 Alert Service Bulletin A27-325, Revision 2, dated
January 27, 1995. Thereafter, conduct visual and eddy current
inspections of the replacement rudder pedals adjuster hub assembly
in accordance with this paragraph.
(b) For airplanes listed in McDonnell Douglas DC-9 Alert Service
Bulletin A27-325, Revision 2, dated January 27, 1995, and not
subject to paragraph (a) of this AD: Prior to the accumulation of
15,000 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, part number 4616066, in accordance with McDonnell Douglas
DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3,
1992, or Revision 2, dated January 27, 1995.
(1) If no cracks are detected as a result of the inspections
required by this paragraph, repeat the inspections at intervals not
to exceed 3,500 landings.
(2) If cracks are detected as a result of the inspections
required by this paragraph, prior to further flight, replace the
rudder pedals adjuster hub assembly, part number 4616066, with a new
assembly having the same part number, in accordance with McDonnell
Douglas DC-9 Alert Service Bulletin A27-325, Revision 2, dated
January 27, 1995. Thereafter, conduct visual and eddy current
inspections of the replacement rudder pedals adjuster hub assembly
in accordance with this paragraph.
(c) Installation of the aluminum rudder pedal adjustment hub
assembly in the rudder pedal mechanism between stations X=69 and
X=120.000 in the flight compartment, in accordance with McDonnell
Douglas DC-9 Service Bulletin 27-325, Revision 1, dated November 30,
1994, constitutes terminating action for the requirements of this
AD.
(d) 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. Alternative methods of compliance
previously granted for AD 92-27-07, Amendment 39-8441, continue to
be considered as acceptable alternative methods of compliance with
this amendment.
(e) 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.
(f) The actions shall be done in accordance with McDonnell
Douglas DC-9 Alert Service Bulletin A27-325, Revision 2, dated
January 27, 1995; McDonnell Douglas DC-9 Service Bulletin 27-325,
Revision 1, dated November 30, 1994; and McDonnell Douglas DC-9
Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992.
Revision 2 of McDonnell Douglas DC-9 Alert Service Bulletin A27-325
contains the following list of effective pages:
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Revision
level
Page No. shown on Date shown on page
page
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1-22.............................. 2 Jan. 27, 1995.
23-30............................. 1 Feb. 3, 1992.
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Revision 1 of McDonnell Douglas DC-9 Service Bulletin 27-325
contains the following list of effective pages:
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Revision level
Page No. shown on page Date shown on page
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1-22.......................... 1................ Nov. 30, 1994.
23-28......................... Original......... Sept. 13, 1993.
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The incorporation by reference of McDonnell Douglas DC-9 Alert
Service Bulletin A27-325, Revision 1, dated February 3, 1992, was
approved previously by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of January 22,
1993 (57 FR 60116, December 18, 1992). The incorporation by
reference of the remainder of 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. Copies may be obtained from McDonnell Douglas
Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Technical Publications Business Administration,
Department 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.
(g) This amendment becomes effective on March 25, 1996.
Issued in Renton, Washington, on January 17, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-844 Filed 2-22-96; 8:45 am]
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