[Federal Register Volume 61, Number 36 (Thursday, February 22, 1996)]
[Rules and Regulations]
[Pages 6768-6770]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-2588]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-CE-32-AD; Amendment 39-9510; AD 96-03-13]
Airworthiness Directives; Beech Aircraft Corporation 90, 99, 100,
and 200 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to Beech Aircraft Corporation (Beech) 90, 99, 100, and 200
series airplanes. This action requires inspecting the main landing gear
drag leg lock link to ensure that the hole for the roll pin is drilled
completely through both walls of the main landing gear drag leg lock
link and, if not drilled completely through both link walls, replacing
any main landing gear drag leg lock link. An incident in which the left
main landing gear collapsed on one of the affected airplanes prompted
this action. Investigation revealed that the roll pin hole was not
completely drilled
[[Page 6769]]
through both walls of the drag leg lock link. The actions specified by
this AD are intended to prevent main landing gear collapse caused by
drag leg lock link failure, which could result in loss of control of
the airplane.
DATES: Effective April 1, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 1, 1996.
ADDRESSES: Service information that applies to this AD may be obtained
from Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may also be examined at the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket 95-CE-32-AD, room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106; or at the Office of the Federal
Register, 800 North Capitol Street NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Steve Potter, Aerospace Engineer,
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4124;
facsimile (316) 946-4407.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that would apply
to Beech Aircraft Corporation 90, 99, 100, and 200 series airplanes was
published in the Federal Register on August 16, 1995 (60 FR 42479). The
action proposed to require inspecting the main landing gear drag leg
lock link to ensure that the hole for the roll pin is drilled through
both walls of the link and, if not drilled completely through both link
walls, replacing any main landing gear drag leg lock link.
Accomplishment of the proposed action would be in accordance with Beech
Service Bulletin No. 2607, Revision 1, dated April 1995.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
The FAA estimates that 2,229 airplanes in the U.S. registry will be
affected by this AD action, that it will take approximately 5 work
hours per airplane to accomplish this action, and that the average
labor rate is approximately $60 an hour. Parts cost approximately $100
per airplane. Based on these figures, the total cost impact of this AD
on U.S. operators is estimated to be $891,600. This figure is based on
the assumption that all of the affected airplanes have incorrectly
drilled drag leg lock links and that none of the owners/operators of
the affected airplanes have replaced the incorrectly drilled links.
Beech has informed the FAA that parts have been distributed to
equip approximately 648 airplanes. Assuming that these distributed
parts are incorporated on the affected airplanes, the cost of the
proposed AD would be reduced by $259,200 from $891,600 to $632,400. In
addition, the FAA believes that a majority of the affected airplanes
will not have incorrectly drilled links, thereby further reducing the
cost impact of the proposed AD upon the public.
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 copy of the final evaluation prepared for this
action is contained in the Rules Docket. A copy of it may be obtained
by contacting 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 a new airworthiness directive
(AD) to read as follows:
AD No.96-03-13 Beech Aircraft Corporation: Amendment 39-9510; Docket
No. 95-CE-32-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category:
------------------------------------------------------------------------
Models Serial Numbers
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F90....................................... LA-2 through LA-236.
99, 99A, A99A, B99, and C99............... U-1 through U-239.
100 and A100.............................. B-1 through B-94 and B-100
through B-247.
B100...................................... BE-1 through BE-137.
200 and B200.............................. BB-2, BB-6 through BB-1157,
BB-1159 through BB-1166, and
BB-1168 through BB-1192.
200T and B200T............................ BT-1 through BT-30.
200C and B200C............................ BL-1 through BL-72.
200CT and B200CT.......................... BN-1 through BN-4.
65-A90-2(RU-21B).......................... LS-1 through LS-3.
65-A90-3(RU-21C).......................... LT-1 through LT-2.
200 (A100-1).............................. BB-3 through BB-5.
A100 (U-21F).............................. B-95 through B-99.
A200 (C-12A and C-12C).................... BC-1 through BC-75, and BD-1
through BD-30.
A200C (UC-12B)............................ BJ-1 through BJ-66.
A200CT (C-12D)............................ BP-1, BP-22, and BP-24
through BP-45.
A200CT (FWC-12D).......................... BP-7 through BP-11.
A200CT (RC-12D)........................... GR-1 through GR-13.
A200CT (RC-12H)........................... GR-14 through GR-19.
A200CT (RC-12G)........................... FC-1 through FC-3.
------------------------------------------------------------------------
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 (d) 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
[[Page 6770]]
been eliminated, the request should include specific proposed actions
to address it.
Compliance: Required within the next 100 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished.
To prevent main landing gear collapse caused by drag leg lock
link failure, which could result in loss of control of the airplane,
accomplish the following:
(a) Inspect the main landing gear drag leg lock link to ensure
that the hole for the roll pin is drilled completely through both
walls of the link in accordance with the ACCOMPLISHMENT INSTRUCTIONS
section of Beech Service Bulletin No. 2607, Revision 1, dated April
1995.
(b) Prior to further flight, replace any drag leg lock link that
does not have the roll pin hole drilled through both walls of the
link. Accomplish this replacement in accordance with the applicable
maintenance manual.
(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) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Wichita Aircraft Certification Office, FAA,
1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The
request shall be forwarded through an appropriate FAA Maintenance
Inspector, who may add comments and then send it to the Manager,
Wichita Aircraft Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita Aircraft Certification Office.
(e) The inspections and replacements required by this AD shall
be done in accordance with Beech Service Bulletin No. 2607, Revision
1, dated April 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 Beech Aircraft
Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be
inspected at the FAA, Central Region, Office of the Assistant Chief
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
7th Floor, suite 700, Washington, DC.
(f) This amendment (39-9510) becomes effective on April 1, 1996.
Issued in Kansas City, Missouri, on January 31, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-2588 Filed 2-21-96; 8:45 am]
BILLING CODE 4910-13-P
