[Federal Register Volume 60, Number 158 (Wednesday, August 16, 1995)]
[Proposed Rules]
[Pages 42479-42481]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-20274]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-32-AD]
Airworthiness Directives; Beech Aircraft Corporation 90, 99, 100,
and 200 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain Beech Aircraft Corporation (Beech) 90,
99, 100, and 200 series airplanes. The proposed action would require
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 where the left main landing gear collapsed on one of
the affected airplanes prompted the proposed action. Investigation
revealed that the roll pin hole was not completely drilled through both
walls of the drag leg lock link. The actions specified by the proposed
AD are intended to prevent main landing gear collapse caused by drag
leg lock link failure, which, if not detected and corrected, could
result in loss of control of the airplane.
DATES: Comments must be received on or before October 20, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-CE-32-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106. Comments may be inspected at
this location between 8 a.m. and 4 p.m., Monday through Friday,
holidays excepted.
Service information that applies to the proposed AD may be obtained
from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas
67201-0085. This information also may be examined at the Rules Docket
at the address above.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 95-CE-32-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 95-CE-32-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA received a report of an incident where the left main
landing gear collapsed on a Beech Model 99 airplane. Investigation of
this incident revealed that the hole for the roll pin was not
completely drilled through both walls of the drag leg lock link.
Further investigation shows that spare drag leg lock links were
delivered to the field with the roll pin hole only drilled halfway
through the link. When drilled only halfway through the link, the roll
[[Page 42480]]
pin will not hold the pivot pin secure in the drag leg lock link. In
this scenario, the drag leg lock link does not hold the landing gear in
the down position, which could cause main landing gear collapse. These
drag leg lock links may be installed on certain Beech 90, 99, 100, and
200 series airplanes.
Beech has issued Service Bulletin No. 2607, Revision 1, dated April
1995, which specifies procedures for inspecting the main landing gear
drag leg lock link on Beech 90, 99, 100, and 200 series airplanes to
ensure that the roll pin hole is drilled through both walls of the
link.
After examining the circumstances and reviewing all available
information related to the incident described above, the FAA has
determined that AD action should be taken to prevent main landing gear
collapse caused by drag leg lock link failure, which, if not detected
and corrected, could result in loss of control of the airplane.
Since an unsafe condition has been identified that is likely to
exist or develop in other Beech 90, 99, 100, and 200 series airplanes
of the same type design, the proposed AD would 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
lock link. Accomplishment of the proposed inspection would be in
accordance with Beech Service Bulletin No. 2607, Revision 1, dated
April 1995. The possible replacement would be accomplished in
accordance with the applicable maintenance manual.
The FAA estimates that 2,229 airplanes in the U.S. registry would
be affected by the proposed AD, that it would take approximtely 5 work
hours per airplane to accomplish the proposed 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 the proposed 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 proposed herein would 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
proposal would 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) if promulgated,
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 draft regulatory evaluation
prepared for this action has been placed 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, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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); 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new AD to read as follows:
Beech Aircraft Corporation: Docket No. 95-CE-32-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category:
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Models Serial Nos.
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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 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 aircraft from the applicability of this AD.
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, if not detected and corrected, 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
section 21.197 and 21.199 of
[[Page 42481]]
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
(ACO), 1801 Airport Road, Room 100, 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 ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(e) All persons affected by this directive may obtain copies of
the document referred to herein upon request to the Beech Aircraft
Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine
this document at the FAA, Central Region, Office of the Assistant
Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri
64106.
Issued in Kansas City, Missouri, on August 10, 1995.
Gerald W. Pierce,
Acting Manger, Small Airplane, Aircraft Certification Service.
[FR Doc. 95-20274 Filed 8-15-95; 8:45 am]
BILLING CODE 4910-13-M
