[Federal Register Volume 60, Number 138 (Wednesday, July 19, 1995)]
[Proposed Rules]
[Pages 37037-37038]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-17749]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-17-AD]
Airworthiness Directives; Fairchild Aircraft SA226 and SA227
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to Fairchild Aircraft SA226 and SA227 series
airplanes. The proposed action would require replacing the nuts that
attach the power control cable to the lever attach point clevis with
nuts that have safety wire holes, and safety wiring the power control
cable to the lever attach point clevis; and inspecting to assure that
the power cable is securely attached to the power control cable
bracket, and correcting any attachment problems. Reports of power
control cable attaching hardware failure on two of the affected
airplanes prompted the proposed action. In one of these instances, the
power control cable disconnected from the lever attach point clevis,
resulting in engine shutdown. The actions specified by the proposed AD
are intended to prevent such power control cable disconnection, which,
if not detected and corrected, could result in engine shutdown and
subsequent loss of control of the airplane.
DATES: Comments must be received on or before September 15, 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-17-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; facsimile (210) 820-8609. This
information may also be examined at the FAA, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
FOR FURTHER INFORMATION CONTACT: Alma Ramirez-Hodge, Aerospace
Engineer, FAA, Airplane Certification Office, 2601 Meacham Boulevard,
Fort Worth, Texas 76193-0150; telephone (817) 222-5147; facsimile (817)
222-5959.
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-17-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-17-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has received reports of power control cable attaching
hardware failure on two Fairchild Aircraft SA226 and SA227 series
airplanes. In one of these incidents, the jam nut came loose and the
threaded portion of the ball joint backed completely out of the clevis.
This caused the power lever to disconnect from the clevis, which caused
one of the engines to shut down.
Fairchild Aircraft has issued Service Bulletin (SB) 226-76-009; SB
227-76-004; and SB CC7-76-001, all Issued: January 6, 1995. These
service bulletins specify procedures for accomplishing the following on
Fairchild Aircraft SA226 and SA227 series airplanes:
Replacing the nuts that attach the power control cable to
the lever attach point clevis with nuts that have safety wire holes,
and safety wiring the power control cable to the lever attach point
clevis; and
Inspecting to assure that the power cable is securely
attached to the power control cable bracket, and correcting any
attachment problems.
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD action should be taken to prevent the power control
cable from disconnecting from the lever attach point clevis, which, if
not detected and corrected, could result in engine shutdown and
subsequent 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
replacing the nuts that attach the power control cable to the lever
attach point clevis with nuts that have safety wire holes, and safety
wiring the power control cable to the lever attach point clevis; and
inspecting to assure that the power cable is securely attached to the
power control cable bracket, and correcting any attachment problems.
Accomplishment of the proposed actions would be in accordance with the
previously referenced service bulletins, as applicable.
The FAA estimates that 779 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 4
workhours per airplane to accomplish the proposed action, and that the
average labor rate is approximately $60 an hour. Parts would consist of
common hardware and the cost would vary; however, for the purposes of
this AD, a figure of $20 is used. Based on these figures, the total
cost impact of the proposed AD on U.S. operators is estimated to be
$202,540. This figure is based on the assumption that no owner/operator
of the affected
[[Page 37038]]
airplanes has accomplished the proposed actions. Since parts are
obtained locally, the FAA has no readily available means of determining
how many owners/operators have incorporated the proposed actions.
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. 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 a new AD to read as
follows:
Fairchild Aircraft: Docket No. 95-CE-17-AD.
Applicability: Models SA226-T, SA226-T(B), SA226-AT, SA226-TC,
SA227-TT, SA227-AT, SA227-AC, SA227-BC, SA227-CC, and SA227-DC
airplanes, all serial numbers, 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 use the authority
provided in paragraph (c) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition, or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required within the next 100 hours time-in-service
after the effective date of this AD, unless already accomplished.
To prevent the power control cable from disconnecting from the
lever attach point clevis, which, if not detected and corrected,
could result in engine shutdown and subsequent loss of control of
the airplane, accomplish the following:
(a) Replace the nuts that attach the power control cable to the
lever attach point clevis with nuts that have safety wire holes, and
safety wire the power control cable to the lever attach clevis; and
inspect to assure that the power cable is securely attached to the
power control cable bracket, and correct any attachment problems.
Accomplish these actions in accordance with the following service
bulletins, as applicable:
(1) Fairchild Service Bulletin (SB) 226-76-009, dated January 6,
1995;
(2) Fairchild SB 227-76-004, dated January 6, 1995; or
(3) Fairchild SB CC7-76-001, dated January 6, 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
compliance times that provides an equivalent level of safety may be
approved by the Manager, Fort Worth ACO, FAA, 2601 Meacham
Boulevard, Fort Worth, Texas 76137-0150. 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.
(d) All persons affected by this directive may obtain copies of
the documents referred to herein upon request to Fairchild Aircraft,
P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine these
documents 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 July 13, 1995.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-17749 Filed 7-18-95; 8:45 am]
BILLING CODE 4910-13-U
