[Federal Register Volume 61, Number 27 (Thursday, February 8, 1996)]
[Proposed Rules]
[Pages 4756-4758]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-2683]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-89-AD]
Airworthiness Directives; Beech Aircraft Corporation Model 58P
and 58PA 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)
Model 58P and 58PA airplanes. The proposed action would require
inspecting for cracks and missing rivets in the cabin structure
(longeron) adjacent to and aft of the second right hand cabin window,
and repairing any cracked structure and installing rivets, if missing.
The Federal Aviation Administration (FAA) has received reports of
airplanes with cracks in the cabin structure. The airplanes are missing
rivets that should have been installed in the cabin structure to secure
the frame, splice, and longeron together. The missing rivets, which
could lead to cabin structure cracks, prompted the proposed AD action.
The actions specified by the proposed AD are intended to prevent
structural damage to the cabin caused by missing rivets, which if not
corrected, could cause decompression injuries to passengers, structural
damage to the fuselage, and loss of the airplane.
DATES: Comments must be received on or before April 12, 1996.
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-89-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: David Ostrodka, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room
100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-
4129, 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
[[Page 4757]]
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-89-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-89-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has received reports of cracks in the fuselage on Beech
airplane Models 58P and 58PA. Upon investigating the source of the
cracks, FAA has learned that four rivets attaching the longeron to the
frame and splice had been omitted during the manufacturing process in
some of these airplanes. These four rivets are installed to secure the
cabin structure to the airplane frame and splice. Without the rivets in
place to reinforce the area around the cabin windows, cracking can
occur in this area resulting in possible cabin decompression or
structural failure of the fuselage.
Beech Service Bulletin (SB) No. 2630, Issued: November, 1995,
specifies procedures for inspecting for cracks and repairing any cracks
found in the longeron around certain cabin windows, and installing any
rivets, if missing.
After examining the circumstances and reviewing all available
information related to the reports described above, including the
referenced service information, the FAA has determined that AD action
should be taken to prevent structural damage to the cabin caused by
missing rivets, which if not corrected, could cause decompression
injuries to passengers, structural damage to the fuselage, and loss of
the airplane.
Since an unsafe condition has been identified that is likely to
exist or develop in other Beech 58P and 58PA airplanes of the same type
design, the proposed AD would require inspecting the cabin window upper
longeron (next to the upper aft splice) between the second and third
right hand windows for cracks and missing rivets, repairing any cracks
found, and installing rivets if missing. Accomplishment of the proposed
action would be in accordance with Beech SB No. 2630, Issued: November,
1995.
The FAA estimates that 386 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 3
workhours to accomplish the inspection and that the average labor rate
is approximately $60 an hour. In estimating the total cost impact of
the proposed AD on U.S. operators, the FAA is only using the proposed
inspection criteria (3 workhours). This estimate is based on the
assumption that no affected airplane will have missing rivets or a
cracked longeron.
Based on these figures, the total cost impact of the proposed AD on
U.S. operators is estimated to be $69,480 or $180 per airplane.
If during the proposed inspection cracks are found and rivets are
missing, the estimated costs for accomplishing the following proposed
actions would be:
--2 workhours to install rivets at an estimated cost of $125 per
airplane ($120 for labor and $5 for rivets) and,
--8 workhours to repair any crack in the desiginated area at an
estimated cost of $675 per airplane ($480 for labor and $195 for
parts).
Beech has informed FAA that parts have been distributed to equip
approximately 19 airplanes. Assuming that each set of these parts is
installed on an affected airplane, the estimated cost impact of the
proposed AD on U.S. operators would be reduced by $3,420 from $59,480
to $66,060.
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), 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-89-AD.
Applicability: Models 58P and 58PA airplanes, having the
following serial numbers, and certificated in any category:
TJ-2 through TJ-177
TJ-179
TJ-181 through TJ-212
TJ-214 through TJ-270
TJ-272 through TJ-283
TJ-285 through TJ-288
TJ-290 through TJ-313
TJ-315 through TJ-321
TJ-323, TJ-324
TJ-326 through TJ-368, and
TJ-370 through TJ-497
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 (c) 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 within the next 100 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished:
To prevent structural damage to the cabin caused by missing
rivets, which if not corrected, could cause decompression injuries
to passengers, structural failure of the fuselage, and loss of the
airplane, accomplish the following:
(a) Inspect cabin window upper longeron (next to the upper aft
splice) between the second and third right hand cabin side windows
for cracks and missing rivets in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of Beech Service Bulletin No. 2630, Issued:
November 1995.
(1) If cracks are found in the longeron, prior to further
flight, repair the cracks in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of Beech Service Bulletin No. 2630, Issued:
November 1995.
[[Page 4758]]
(2) If rivets are found missing, prior to further flight,
install the rivets in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of Beech Service Bulletin No. 2630, Issued:
November 1995.
(b) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviations Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(c) 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, 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 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.
(d) All persons affected by this directive may obtain copies of
the 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 February 2, 1996.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-2683 Filed 2-7-96; 8:45 am]
BILLING CODE 4910-13-U
