[Federal Register Volume 59, Number 45 (Tuesday, March 8, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-4951]
[[Page Unknown]]
[Federal Register: March 8, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-NM-145-AD; Amendment 39-8847; AD 94-05-09]
Airworthiness Directives; Beech Model 400A Airplanes Equipped
With Certain Tosington Cabin Seat Frames
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Beech Model 400A airplanes, that requires an
inspection to detect fatigue-related cracking in certain cabin seat
frames; measurement to determine gap size between the bearing shafts
and certain seat frames; and repair, if necessary. This amendment is
prompted by in-service inspection reports of fatigue-related cracking
radiating outward from the bushings welded into the cabin seat frames.
The actions specified by this AD are intended to prevent separation of
the cabin seat frames from their bases during an emergency landing.
DATES: Effective April 7, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 7, 1994.
ADDRESSES: The service information referenced in this AD may be
obtained from Tosington Enterprises, Inc., 2261 Madera Road, Simi
Valley, California 93065. This information may be examined at the
Federal Aviation Administration (FAA), Transport Airplane Directorate,
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA,
Small Airplane Directorate, Wichita Aircraft Certification Office
(ACO), 1801 Airport Road, room 100, Mid-Continent Airport, Wichita,
Kansas; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Laurence Engler, Aerospace Engineer,
Airframe Branch, ACE-120W, FAA, Small Airplane Directorate, Wichita
ACO, 1801 Airport Road, room 100, Mid-Continent Airport, Wichita,
Kansas 67209; telephone (316) 946-4122; fax (316) 946-4407.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations to include an airworthiness directive (AD) that is
applicable to certain Beech Model 400A airplanes was published in the
Federal Register on November 8, 1993 (58 FR 59223). That action
proposed to require a one-time visual inspection to detect fatigue-
related cracking in certain cabin seat frames; measurement to determine
gap size between the bearing shafts and certain seat frames; and
repair, if necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
There are approximately 41 Beech Model 400A airplanes of the
affected design in the worldwide fleet. The FAA estimates that 29
airplanes of U.S. registry will be affected by this AD, that it will
take approximately 1 work hour per airplane to accomplish the required
actions, and that the average labor rate is $55 per work hour. Based on
these figures, the total cost impact of the AD on U.S. operators is
estimated to be $1,595, or $55 per airplane.
The total cost impact figure discussed above is based on
assumptions that no operator has yet accomplished any of the
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
The regulations adopted herein will 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 final
rule does 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) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 14 CFR part
39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
94-05-09 Beech Aircraft Corporation: Amendment 39-8847. Docket 93-
NM-145-AD.
Applicability: Model 400A airplanes; serial numbers RK-1 through
RK-40 inclusive, and RK-45; equipped with Tosington Cabin Seat
Frames having serial numbers prior to 5606, on which Modification
Kit Number 303-307 has not been installed; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent separation of the cabin seat frames from their bases
during an emergency landing, accomplish the following: (a) Within
200 hours time-in-service after the effective date of this AD,
perform a visual inspection to detect fatigue-related cracking
extending radially outward from the bushings welded into the cabin
seat frames, in accordance with Tosington Enterprises, Inc., Service
Bulletin 001, dated July 1993. If any cracking is found, prior to
further flight, repair by welding in accordance with the service
bulletin.
(b) Within 200 hours time-in-service after the effective date of
this AD, measure the gap size between the bearing shaft and the
lower aft and/or forward seat frames in accordance with Tosington
Enterprises, Inc., Service Bulletin 001, dated July 1993.-
(1) If the gap size is 0.32 inch or greater, prior to further
flight, repair by reinforcing the cabin seat frame in accordance
with the service bulletin.
(2) If the gap size is less than 0.32 inch, no further action is
required.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Wichita Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Wichita ACO.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(d) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the
airplane to a location where the requirements of this AD can be
accomplished.
(e) The inspection, repairs, and measurement shall be done in
accordance with Tosington Enterprises, Inc., Service Bulletin 001,
dated July 1993. This incorporation by reference was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be obtained from Tosington
Enterprises, Inc., 2261 Madera Road, Simi Valley, California 93065.
Copies may be inspected at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small
Airplane Directorate, Wichita Aircraft Certification Office (ACO),
1801 Airport Road, room 100, Mid-Continent Airport, Wichita, Kansas;
or at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
(f) This amendment becomes effective on April 7, 1994.
Issued in Renton, Washington, on February 28, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-4951 Filed 3-7-94; 8:45 am]
BILLING CODE 4910-13-U
