[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]



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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).

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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