[Federal Register Volume 60, Number 192 (Wednesday, October 4, 1995)]
[Proposed Rules]
[Pages 51942-51944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-24605]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-46-AD]
Airworthiness Directives; Beech Aircraft Corporation Models 1900,
1900C, and 1900D 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)
Models 1900, 1900C, and 1900D airplanes that do not have canted
bulkhead Repair Kit No. 129-4005-1 S incorporated. The proposed action
would require repetitively inspecting the canted bulkhead located at
Fuselage Station 588.10 for cracks, and, if cracks are found that
exceed certain limits, incorporating canted bulkhead Repair Kit No.
129-4005-1 S as terminating action for the repetitive inspection
requirement. Numerous reports of multi-site cracks occurring in the
canted bulkhead at Fuselage Station 588.10 on the affected airplanes
prompted the proposed action. The actions specified by the proposed AD
are intended to prevent the inability of the bulkhead to carry its
ultimate design load because of cracks in the canted bulkhead, which,
if not detected and corrected, could affect rudder cable tension and
result in reduced rudder power.
DATES: Comments must be received on or before December 4, 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-46-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
[[Page 51943]]
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-46-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-46-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has received numerous reports of multi-site cracks in the
canted bulkhead at Fuselage Station 588.10 on three Beech Models 1900,
1900C, and 1900D airplanes. Specifically, these cracks were found at
the outer flange radius and outer flange stringer cutouts of the canted
bulkhead. This condition, if not detected and corrected, could prevent
the bulkhead from carrying its ultimate design load because of cracks
in the canted bulkhead, which, if not detected and corrected, could
affect rudder cable tension and result in reduced rudder power.
Beech has issued Service Bulletin (SB) No. 2564, Revision 1, dated
April 1995, which specifies procedures for inspecting the canted
bulkhead at Fuselage Station 588.10. This service bulletin also
references canted bulkhead Repair Kit No. 129-4005-1 S, which, when
incorporated on the affected airplanes, reinforces this area at
Fuselage Station 588.10.
After examining the circumstances and reviewing all available
information related to the incidents described above including the
referenced service information, the FAA has determined that AD action
should be taken to prevent the inability of the bulkhead to carry its
ultimate design load because of cracks in the canted bulkhead, which,
if not detected and corrected, could affect rudder cable tension and
result in reduced rudder power.
Since an unsafe condition has been identified that is likely to
exist or develop in other Beech Models 1900, 1900C, and 1900D airplanes
of the same type design that do not have canted bulkhead Repair Kit No.
129-4005-1 S incorporated, the proposed AD would require repetitively
inspecting the canted bulkhead located at Fuselage Station 588.10 for
cracks, and, if cracks are found that exceed certain limits,
incorporating canted bulkhead Repair Kit No. 129-4005-1 S as
terminating action for the repetitive inspection requirement.
Accomplishment of the proposed inspections would be in accordance with
Beech SB No. 2564, Revision 1, dated April 1995. Accomplishment of the
proposed possible reinforcement would be in accordance with the
instructions included with the above referenced kit.
The FAA estimates that 364 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 2
workhours per airplane to accomplish the proposed inspections, and that
the average labor rate is approximately $60 an hour. Based on these
figures, the total cost impact of the proposed AD on U.S. operators is
estimated to be $43,680. This figure does not take into account the
number of repetitive inspections an affected airplane owner/operator
would incur and is based on the assumption that no canted bulkhead
would be found cracked during the inspection. The FAA has no way of
determining the number of repetitive inspections a particular airplane
owner/operator would incur or how many canted bulkheads would be found
cracked during the proposed inspections. This figure also does not take
into account the number of affected airplane owners/operators that may
have incorporated the inspection-terminating reinforcement kit.
Beech has notified the FAA that 36 reinforcement kits have been
distributed to the affected airplane owners/operators. If each of the
kits has been installed on an affected airplane, then the inspection
requirement for these airplanes is eliminated. Based on this
assumption, the cost impact of the proposed AD upon U.S. owners/
operators of the affected airplanes would be reduced $4,320 from
$43,680 to $39,360.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Beech Aircraft Corporation: Docket No. 95-CE-46-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category, that do not have canted bulkhead
Repair Kit No. 129-4005-1 S incorporated:
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Model Serial Nos.
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1900............................... UA-1 through UA-3.
1900C.............................. UB-1 through UB-74 and UC-1 through
UC-174.
1900C (C12J)....................... UD-1 through UD-6.
1900D.............................. UE-1 through UE-113.
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Note 1: This AD applies to each airplane identified in the
preceding applicability revision, 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 (e) 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 in the
[[Page 51944]]
body of this AD, unless already accomplished.
To prevent the inability of the bulkhead to carry its ultimate
design load because of cracks in the canted bulkhead, which, if not
detected and corrected, could affect rudder cable tension and result
in reduced rudder power, accomplish the following:
Note 2: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 2 structures are designations of the Level 1 paragraph
they immediately follow.
(a) Upon the accumulation of 5,000 hours time-in-service (TIS)
or within the next 600 hours TIS, whichever occurs later, inspect
the canted bulkhead at Fuselage Station 588.10. Accomplish this
inspection in accordance with the Accomplishment Instructions
section of Beech Service Bulletin (SB) No. 2564, Revision 1, dated
April 1995.
(b) If, during the inspection, one or more of the limits
specified in paragraphs (b)(1), (b)(2), or (b)(3) of this AD are
found (also specified in Beech SB No. 2564), prior to further
flight, incorporate Beech Kit No. 129-4005-1 S, which reinforces the
canted bulkhead at Fuselage Station 588.10.
(1) Any one crack that is greater than 2.5 inches in length.
(2) The sum of all crack lengths in any 12 inches of consecutive
frame length is greater than 4.0 inches
(3) Any crack that progresses through the width of the bulkhead.
(c) If no cracks are found during an inspection or a crack is
found that does not exceed one of the limits specified in paragraphs
(b)(1), (b)(2), or (b)(3) of this AD, accomplish one of the
following:
(1) Repeat the inspection specified in paragraph (a) of this AD
at intervals not to exceed 600 hours TIS, and prior to further
flight, reinforce the canted bulkhead as specified in paragraph (b)
of this AD if cracks are found that exceed one or more of the limits
specified in paragraphs (b)(1), (b)(2), or (b)(3) of this AD; or
(2) Within 600 hours after the last canted bulkhead inspection,
incorporate Beech Kit No. 129-4005-1 S. Incorporating this kit
reinforces the canted bulkhead at Fuselage Station 588.10.
(d) Special flight permits may be issued in accordance with
Secs. 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.
(e) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(f) 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 September 26, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-24605 Filed 10-3-95; 8:45 am]
BILLING CODE 4910-13-U
