[Federal Register Volume 63, Number 99 (Friday, May 22, 1998)]
[Rules and Regulations]
[Pages 28217-28218]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-13407]
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Rules and Regulations
Federal Register
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This section of the FEDERAL REGISTER contains regulatory documents
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to and codified in the Code of Federal Regulations, which is published
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Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 / Rules and
Regulations
[[Page 28217]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-251-AD; Amendment 39-10537; AD 98-11-10]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9 and 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 adopts a new airworthiness directive (AD),
applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series
airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes,
that requires an inspection to determine if the latching lever pin of
the speed brake passes an axial force check, and a visual inspection to
determine if the staking of the latching lever pin is acceptable; and
follow-on corrective action, if necessary. This amendment is prompted
by reports that the speed brake handle jammed in the ground spoiler
position. The actions specified by this AD are intended to prevent a
jammed speed brake handle pin, which could result in retraction of the
spoilers and full advancement of the left throttle during a go-around.
DATES: Effective June 26, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 26, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from The Boeing Company, Douglas Products 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.
FOR FURTHER INFORMATION CONTACT: Walter Eierman, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California
90712; telephone (562) 627-5336; 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-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9
(military) series airplanes was published in the Federal Register on
February 19, 1998 (63 FR 8371). That action proposed to require an
inspection to determine if the latching lever pin of the speed brake
passes an axial force check, and a visual inspection to determine if
the staking of the latching lever pin is acceptable; and follow-on
corrective action, 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 2,050 McDonnell Douglas Model DC-9 and 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 1,250 airplanes of U.S. registry will be affected by
this AD, that it will take approximately 5 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 the AD on
U.S. operators is estimated to be $375,000, or $300 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 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.
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:
[[Page 28218]]
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:
98-11-10 McDonnell Douglas: Amendment 39-10537. Docket 97-NM-251-
AD.
Applicability: Model DC-9-10, -20, -30, -40, and -50, and DC-9-
81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87)
series airplanes; Model MD-88 airplanes; and C-9 (military) series
airplanes; as listed in McDonnell Douglas Service Bulletin DC9-27-
346, Revision 01, dated July 29, 1997; 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 a jammed speed brake handle pin, which could result
in retraction of the spoilers and full advancement of the left
throttle during a go-around, accomplish the following:
(a) Within 12 months after the effective date of this AD,
perform an inspection to determine if the latching lever pin of the
speed brake passes an axial force check, and a visual inspection to
determine if the staking of the latching lever pin is
``acceptable'', in accordance with McDonnell Douglas Service
Bulletin DC9-27-346, Revision 01, dated July 29, 1997.
Note 2: The criteria for determining whether the staking is
``acceptable'' are defined in Figure 1 of the service bulletin.
(1) Condition 1. If the pin passes the axial force check and the
staking is found to be acceptable, no further action is required by
this AD.
(2) Condition 2. If the pin passes the axial force check and the
staking is found to be unacceptable, accomplish the actions
specified in Condition 2, Option 1, or Condition 2, Option 2 of the
Accomplishment Instructions of the service bulletin. These actions
shall be accomplished at the times specified in paragraph E.
``Compliance'' of the service bulletin. Accomplishment of the
replacement of the speed brake latching lever constitutes
terminating action for the repetitive inspection requirements of
this AD.
(3) Condition 3. If the pin fails the axial force check and the
staking is found to be unacceptable, accomplish the actions
specified in Condition 3, Option 1, or Condition 3, Option 2 of the
Accomplishment Instructions of the service bulletin. These actions
shall be accomplished at the times specified in paragraph E.
``Compliance'' of the service bulletin. Accomplishment of the
replacement of the speed brake latching lever constitutes
terminating action for the repetitive inspection requirements of
this AD.
(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 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
(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.
(d) The actions shall be done in accordance with McDonnell
Douglas Service Bulletin DC9-27-346, Revision 01, dated July 29,
1997. 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 The Boeing Company, Douglas
Products 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 June 26, 1998.
Issued in Renton, Washington, on May 14, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-13407 Filed 5-21-98; 8:45 am]
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