[Federal Register Volume 60, Number 181 (Tuesday, September 19, 1995)]
[Proposed Rules]
[Pages 48431-48433]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-23216]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-CE-40-AD]
Airworthiness Directives; Fairchild Aircraft SA226 and SA227
Series 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 Fairchild Aircraft SA226 and SA227
series airplanes. The proposed action would require drilling inspection
access holes in the elevator torque tube arm, inspecting the elevator
torque tube for corrosion, replacing any corroded elevator torque tube,
and applying a corrosion preventive compound. Several reports of
corrosion found in the elevator torque tube area on the affected
airplanes prompted the proposed action. The actions specified by the
proposed AD are intended to prevent failure of the flight control
system caused by a corroded elevator torque tube, which, if not
detected and corrected, could result in loss of control of the
airplane.
DATES: Comments must be received on or before November 17, 1995.
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-40-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 Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-
0490; telephone (210) 824-9421. This information also may be examined
at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Hung Viet Nguygen, Aerospace
Engineer, FAA, Airplane Certification Office, 2601 Meacham Boulevard,
Fort Worth, Texas 76193-0150; telephone (817) 222-5155; facsimile (817)
222-5960.
[[Page 48432]]
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. 95-CE-40-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-40-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has received reports of internal corrosion found in the
elevator torque tube on over 20 Fairchild Aircraft SA226 and SA227
series airplanes. This condition, if not detected and corrected, could
result in failure of the airplane flight control system and subsequent
loss of control of the airplane.
Fairchild Aircraft Service Bulletin (SB) 226-27-050 and SB 227-27-
028, both issued: January 22, 1990, specify procedures for the
following:
Drilling inspection access holes in the elevator torque
tube arm;
Inspecting the elevator torque tube for corrosion; and
Applying a corrosion preventive compound.
After examining the circumstances and reviewing all available
information related to the incidents described above including the
referenced service information, the FAA has determined that AD action
should be taken to prevent failure of the flight control system caused
by a corroded elevator torque tube, which, if not detected and
corrected, could result in loss of control of the airplane.
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild Aircraft SA226 and SA227 series
airplanes of the same type design, the proposed AD would require
drilling inspection access holes in the elevator torque tube arm,
inspecting the elevator torque tube for corrosion, replacing any
corroded elevator torque tube, and applying a corrosion preventive
compound. Accomplishment of the proposed inspection access hole
drilling, the inspection, and the corrosion preventive compound
application would be in accordance with either Fairchild SB 226-27-050
or SB 227-27-028, both issued: January 22, 1990.
The compliance time for the proposed AD is presented in calendar
time instead of hours time-in-service (TIS). The FAA has determined
that a calendar time for compliance would be the most desirable method
because the unsafe condition described by the proposed AD is caused by
corrosion. Corrosion can occur on airplanes regardless of whether the
airplane is in service or on the ground.
The FAA estimates that 390 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 10
workhours to accomplish the proposed actions, and that the average
labor rate is approximately $60 an hour. Based on these figures, the
total cost impact of the proposed AD on U.S. operators is estimated to
be $234,000. This figure is based on the assumption that no owner/
operator of the affected airplanes has accomplished the proposed
inspection access hole drilling, inspection, or corrosion preventive
compound application. It also is based on the assumption that no
elevator torque tube would be found corroded and need replaced. The FAA
has no way of determining how many owners/operators of the affected
airplanes may have already complied with the proposed AD.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Fairchild Aircraft: Docket No. 95-CE-40-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category:
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Model Serial Nos.
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SA226-T T201 through T275 and T277 through T291.
SA226-T(B) T(B)276 and T(B)292 through T(B)417.
SA226-AT AT001 through AT074.
SA226-TC TC201 through TC419.
SA227-TT TT421 through TT541.
SA227-AT AT423 through AT695.
SA227-AC AC406, AC415, AC416, and AC420 through AC772.
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Note 1: This AD applies to each airplane identified in the
preceding applicability
[[Page 48433]]
revision, 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 (e) 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 6 calendar months after the effective date
of this AD, unless already accomplished.
To prevent failure of the flight control system caused by a
corroded elevator torque tube, which, if not detected and corrected,
could result in loss of control of the airplane, accomplish the
following:
(a) Drill two .5 inch diameter holes in the inboard side of the
elevator torque tube arm in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of and as specified in Figure 1 of Fairchild
Aircraft Service Bulletin (SB) 226-27-050 or SB 227-27-028, both
Issued: January 22, 1990, as applicable.
(b) Inspect the elevator torque tube in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft SB 226-27-
050 or SB 227-27-028, both Issued: January 22, 1990, as applicable.
Prior to prior further flight, replace any corroded elevator torque
tube with a new part of like design in accordance with the
applicable maintenance manual.
(c) Apply a corrosion preventive compound in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft SB 226-27-
050 or SB 227-27-028, both Issued: January 22, 1990, as applicable.
(d) 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.
(e) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Airplane Certification Office (ACO), FAA,
2601 Meacham Boulevard, Fort Worth, Texas 76193-0150. The request
shall be forwarded through an appropriate FAA Maintenance Inspector,
who may add comments and then send it to the Manager, Fort Worth
ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth ACO.
(f) All persons affected by this directive may obtain copies of
the service bulletins referred to herein upon request to Fairchild
Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490; or may
examine these service bulletins 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 September 13, 1995.
Gerald W. Pierce,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-23216 Filed 9-18-95; 8:45 am]
BILLING CODE 4910-13-U
