[Federal Register Volume 61, Number 206 (Wednesday, October 23, 1996)]
[Proposed Rules]
[Pages 54965-54967]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-27138]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-CE-27-AD]
RIN 2120-AA64
Airworthiness Directives; Beech Aircraft Corporation Model 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 Beech Aircraft Corporation (Beech) Model 1900D
airplanes. The proposed action would require inspecting the stabilon
attachment angles for the correct thickness, repetitively inspecting
for cracks in the attachment angles and replacing the attachment angles
with ones of the correct thickness. Recent reports of installing the
incorrect size of stabilon attachment angles on certain Beech 1900D
airplanes prompted the proposed action. The actions specified by the
proposed AD are intended to prevent separation of the stabilon from the
airplane, which could cause loss of airplane stability during flight.
DATES: Comments must be received on or before December 30, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 96-CE-27-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 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. Steven E. Potter, Aerospace
Engineer, Wichita Aircraft Certification Office,
[[Page 54966]]
1801 Airport Rd., Rm. 100, 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. 96-CE-27-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. 96-CE-27-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has recently been notified that certain stabilons with pre-
assembled attachment angles, part number (P/N) 114-620024-43 (left) and
P/N 114-620024-44 (right), installed on certain Beech Model 1900D
airplanes are undersized and may crack and separate from the fuselage
of the airplane. Although there have not been any incidents or
accidents, these particular attachment angles, which are .071-inch
thick, were not designed for use on the Beech Model 1900D airplane.
Instead, these particular attachment angles were designed for the
Beech Model 1900C airplane and are not able to support the increased
stabilon load of the Model 1900D airplane. Beech Model 1900D airplanes
should have a different stabilon attachment angle installed, having a
thickness of .090-inch and having P/N 114-620024-47 (left-hand upper),
114-620024-48 (right-hand upper), 114-620024-49 (left-hand lower), and
P/N 114-620024-50 (right-hand lower).
Related Service Information
Beech has issued a Mandatory Service Bulletin (SB) No. 2651, Issued
January 1996, which specifies inspecting the stabilon attachment angles
for proper thickness, repetitively inspecting for cracks, and replacing
the attachment angles if either cracks or incorrect size are found.
Evaluation of All Applicable Information
After examining the circumstances and reviewing all available
information related to the conditions described above, the FAA has
determined that AD action should be taken to prevent separation of the
stabilon from the airplane, which could cause loss of airplane
stability during flight.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Beech Model 1900D airplanes of the same type
design, the proposed AD would require:
--Inspecting the left (upper and lower) and right (upper and lower)
stabilon attachment angles for proper thickness, which is .090-inch
thick.
--If the attachment angles are the correct thickness, then no further
action is required.
--If the attachment angles are not the correct thickness (.090-inch
thick), the proposed AD would require:
--Repetitively inspecting the stabilon attachment angles for visible
cracks at intervals not to exceed 50 hours time-in-service (TIS), until
cracks are visible or until the replacement of the angles is
accomplished.
--Replacing the attachment angles with attachment angles of the correct
thickness (.090-inch) when cracks become visible.
--If no cracks are visible during any of the required inspections of
the proposed AD, replacing the attachment angles with attachment angles
of the correct thickness upon the accumulation of 600 hours TIS, after
the effective date of the proposed AD.
--The replacement of the stabilon attachment angles with the correct
angles P/N 114-620024-47 (left-hand upper), 114-620024-48 (right-hand
upper), 114-620024-49 (left-hand lower), and P/N 114-620024-50 (right-
hand lower), at any time after the effective date of the proposed AD
will terminate the inspection requirements of the proposed AD.
Cost Impact
The FAA estimates that 215 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 1 hour
per airplane to accomplish the proposed initial inspection, and that
the average labor rate is approximately $60 an hour. The manufacturer's
warranty is providing the labor for the proposed installation and parts
at no cost to the owners/operators. Based on these figures, the total
cost impact of the proposed AD on U.S. operators is estimated to be
$12,900 or $60 per airplane. This figure is only accounting for the
initial inspection and possible replacement of the stabilon attachment
angles and is not considering the number of repetitive inspections that
may be incurred over the life of the airplane.
Regulatory Impact
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.
[[Page 54967]]
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), 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. 96-CE-27-AD.
Applicability: Model 1900D airplanes (serial numbers UE-1
through UE-215), 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 (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 been
eliminated, the request should include specific proposed actions to
address it.
Note 2: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 2 and Level 3 structures are designations of the Level 1
paragraph they immediately follow.
Compliance: Required within the next 50 hours time-in-service
(TIS) after the effective date of this AD, and thereafter as
indicated in the body of this AD, unless already accomplished.
To prevent separation of the stabilons from the airplane, which
could cause loss of airplane stability during flight, accomplish the
following:
(a) Inspect the left upper and lower, and the right upper and
lower stabilon attachment angles for proper thickness, which is
.090-inch, in accordance with the ACCOMPLISHMENT INSTRUCTIONS
section of Beechcraft Mandatory Service Bulletin (MSB) 2651, issued
January 1996.
(1) If the attachment angles are the correct thickness, then no
further action is required.
(2) If the attachment angles are not the correct thickness,
accomplish the following in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of Beechcraft MSB 2651, issued January 1996:
(i) Repetitively inspect the stabilon attachment angles for
cracks, at intervals not to exceed 50 hours TIS, until cracks are
visible or until the attachment angles are replaced.
(ii) If cracks are visible, prior to further flight, replace the
attachment angles with attachment angles of the correct thickness
(.090-inch).
(iii) If no cracks are visible during any of the required
inspections of this AD, replace the attachment angles with
attachment angles of the correct thickness (.090-inch) upon the
accumulation of 600 hours TIS, after the effective date of this AD.
(b) The replacement of the correct stabilon attachment angles at
any time after the effective date of this AD will terminate the
repetitive inspection requirements of this AD.
(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
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Wichita Aircraft
Certification Office, 1801 Airport Rd., Rm. 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 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) All persons affected by this directive may obtain copies of
this document referred to herein upon request to 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 October 16, 1996.
Bobby W. Sexton,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-27138 Filed 10-22-96; 8:45 am]
BILLING CODE 4910-13-U
