[Federal Register Volume 61, Number 104 (Wednesday, May 29, 1996)]
[Rules and Regulations]
[Pages 26780-26781]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-13273]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-CE-82-AD; Amendment 39-9637; AD 96-11-12]
RIN 2120-AA64
Airworthiness Directives; Beech Aircraft Corporation Model C90A
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to certain Beech Aircraft Corporation (Beech) Model C90A
airplanes equipped with an optional Beech electric trim system or a
Collins autopilot system. This action requires modifying the elevator
electric trim tab actuator assembly. Failure of the elevator electric
trim tab system on a Beech Model C90A prompted the proposed AD action.
The actions specified by the proposed AD are intended to prevent
possible failure of the elevator electric trim tab system, which, if
not detected and corrected, could cause loss of airplane maneuverablity
and possible loss of control of the airplane.
DATES: Effective July 24, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 24, 1996.
ADDRESSES: Service information that applies to this AD may be obtained
from Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may also be examined at the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket 95-CE-82-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Harvey E. Nero, Aerospace Engineer, FAA, Wichita Aircraft Certification
Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita,
Kansas 67209; telephone (316) 946-4137; facsimile (316) 946-4407.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that would apply
to Beech Aircraft Corporation (Beech) Model C90A airplanes equipped
with an optional Beech electric trim system or a Collins autopilot
system was published in the Federal Register on November 28, 1995 (60
FR 58583). The action proposed to require procedures for modifying the
elevator electric trim tab actuator assembly. Accomplishment of this
action will be in accordance with Beech Service Bulletin (SB) No. 2631,
Issued: June 1995, Revised: September 1995.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
After careful review of all available information related to the
subject presented above, the FAA has
[[Page 26781]]
determined that air safety and the public interest require the adoption
of the rule as proposed except for minor editorial corrections. The FAA
has determined that these minor corrections will not change the meaning
of the AD and will not add any additional burden upon the public than
was already proposed.
The FAA estimates that 300 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 6 workhours per
airplane to accomplish this action, and that the average labor rate is
approximately $60 an hour. Parts are estimated to be $160 per airplane.
Based on these figures, the total cost impact of this AD on U.S.
operators is estimated to be $156,000 or $520 per airplane. Beech has
informed FAA that no parts have been distributed to owners/operators
for this modification; therefore, this figure is based on the
assumption that no owners/operators have accomplished the proposed
inspection and modification.
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 copy of the final evaluation prepared for this
action is contained 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, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 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:
96-11-12. Beech Aircraft Corporation: Amendment 39-9637; Docket No.
95-CE-82-AD.
Applicability: The following Model C90A Airplanes, certificated
in any category, that are equipped with an optional Beech electric
trim system or a Collins autopilot system: -
(1) Serial numbers LJ-1111 through LJ-1410 that were equipped at
manufacture assembly with a pin-type cable guard actuator assembly
(P/N 33-524023-51) on the elevator electric trim tab actuator
assembly. -
(2) All serial numbers (except LJ-1 through LJ-1110) equipped
with a pin-type cable guard actuator assembly (P/N 33-524023-51)
installed through field approval.
-Note 1: Steps 1 through 4 of the ACCOMPLISHMENT INSTRUCTIONS
section of Beech Service Bulletin (SB) No. 2631, Issued: June 1995,
Revised: September 1995, provide procedures for determining which
assembly is installed. -
Note 2: 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 as follows, unless already
accomplished: -
(1) Within 150 hours time-in-service (TIS) after the effective
date of this AD; or -
(2) Upon installation of an optional Beech elevator electric
trim tab system or a Collins autopilot system, whichever occurs
first.
-To prevent possible failure of the optional Beech electric trim
system or the Collins autopilot system, which, if not detected and
corrected, could cause loss of airplane maneuverability and possible
loss of control of the airplane, accomplish the following: -
(a) Modify all elevator electric trim tab actuator assemblies,
part number (P/N) 33-524023-51 to the P/N 33-524023-77 or P/N 33-
524023-79 level, by accomplishing the procedures in the
ACCOMPLISHMENT INSTRUCTIONS section of Beechcraft Mandatory Service
Bulletin SB No. 2631, Issued: June 1995, Revised: September 1995. -
(b) 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. -
(c) 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 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 3: 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) The modification required by this AD shall be done in
accordance with Beechcraft Mandatory Service Bulletin No. 2631,
Issued: June 1995, Revised: September 1995. 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 Beech Aircraft Corporation, P.O. Box 85, Wichita,
Kansas 67201-0085. Copies may be inspected at the FAA, Central
Region, Office of the Assistant Chief Counsel, Room 1558, 601 E.
12th Street, Kansas City, Missouri, or at the Office of the Federal
Register, 800 North Capitol Street, NW., 7th Floor, suite 700,
Washington, DC. -
(e) This amendment (39-9637) becomes effective on June 24, 1996.
Issued in Kansas City, Missouri, on May 22, 1996.
Bobby Sexton,
Action Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-13273 Filed 5-28-96; 8:45 am]
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