[Federal Register Volume 61, Number 29 (Monday, February 12, 1996)]
[Rules and Regulations]
[Pages 5279-5280]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-1574]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-CE-17-AD; Amendment 39-9499; AD 96-03-03]
Airworthiness Directives; Fairchild Aircraft SA226 and SA227
Series 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 Fairchild Aircraft SA226 and SA227 series airplanes.
This action requires replacing the nuts that attach the power control
cable to the lever attach point clevis with nuts that have safety wire
holes, safety-wiring the power control cable to the lever attach point
clevis, 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 this 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
this AD are intended to prevent such power control cable disconnection,
which could result in engine shutdown and subsequent loss of control of
the airplane.
DATES: Effective March 15, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 15, 1996.
ADDRESSES: Service information that applies to this AD may be obtained
from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-
0490; telephone (210) 824-9421. 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-17-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: 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that would apply
to certain Fairchild Aircraft SA226 and SA227 series airplanes was
published in the Federal Register on July 19, 1995 (60 FR 37037). The
action proposed to require replacing the nuts that attach the power
control cable to the lever attach point clevis with nuts that have
safety wire holes, safety-wiring the power control cable to the lever
attach point clevis, 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 Fairchild Service Bulletin (SB) 226-76-009;
Fairchild SB 227-76-004; or Fairchild SB CC7-76-001, all Issued:
January 6, 1995, as applicable.
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 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
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 779 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 4 workhours per
airplane to accomplish the required 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 this 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
airplanes has accomplished the required actions. Since parts are
obtained locally, the FAA has no readily available means of determining
how many owners/operators have incorporated the required actions.
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:
[[Page 5280]]
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 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:
96-03-03 Fairchild Aircraft: Amendment 39-9499; 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 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 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 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,
safety-wire the power control cable to the lever attach clevis,
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 time that provides an equivalent level of safety may be
approved by the Manager, Fort Worth Airplane Certification Office
(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) The replacement required by this AD shall be done in
accordance with Fairchild Service Bulletin 226-76-009; Fairchild
Service Bulletin 227-76-004; or Fairchild Service Bulletin CC7-76-
001, all Issued: January 6, 1995, as applicable. 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 Fairchild Aircraft, P.O. Box 790490, San Antonio,
Texas 78279-0490. 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 (39-9499) becomes effective on March 15,
1996.
Issued in Kansas City, Missouri, on January 23, 1996.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-1574 Filed 2-9-96;8:45am]
BILLING CODE 4910-13-U
