[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