[Federal Register Volume 64, Number 90 (Tuesday, May 11, 1999)]
[Proposed Rules]
[Pages 25218-25219]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-11779]
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Proposed Rules
Federal Register
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This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 64, No. 90 / Tuesday, May 11, 1999 / Proposed
Rules
[[Page 25218]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-15-AD]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft, Inc. Models SA226-
T, SA226-T(B), SA226-AT, and SA226-TC Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede Airworthiness Directive
(AD) 77-25-03, which currently requires repetitively inspecting the
landing gear actuator rod ends that are equipped with grease fittings
for cracks on Fairchild Aircraft, Inc. (Fairchild Aircraft) Models
SA226-T, SA226-AT, and SA226-TC airplanes. AD 77-25-03 also requires
replacing the landing gear actuator rod ends with an improved part
either immediately or at a certain time period depending on the results
of the inspections. Replacement of all six rod ends terminates the
repetitive inspection requirements of AD 77-25-03. The AD proposed in
this document is the result of failures of the landing gear rod ends on
airplanes where the rod ends were replaced in accordance with AD 77-25-
03. Fairchild has re-designed the landing gear rod ends as a result of
these failures. The proposed AD would require replacing all landing
gear rod ends with these improved design parts on all SA226 series
airplanes, including those manufactured since AD 77-25-03 was issued
(i.e., the Model SA226-T(B) airplanes). The actions specified by the
proposed AD are intended to prevent failure of the landing gear
actuator caused by cracks in the rod ends, which could result in the
inability to lower the landing gear during a landing with consequent
possible loss of control of the airplane.
DATES: Comments must be received on or before July 16, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 99-CE-15-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, Inc., P.O. Box 790490, San Antonio, Texas
78279-0490; telephone: (210) 824-9421; facsimile: (210) 820-8609. This
information also may be examined at the Rules Docket at the address
above.
FOR FURTHER INFORMATION CONTACT: Hung Viet Nguyen, FAA, Airplane
Certification Office, 2601 Meacham Boulevard, Fort Worth, Texas 76193-
0150; telephone: (817) 222-5133; facsimile: (817) 222-5960.
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. 99-CE-15-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 Regional Counsel, Attention:
Rules Docket No. 99-CE-15-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
AD 77-25-03, Amendment 39-3090, currently requires repetitively
inspecting the landing gear actuator rod ends that are equipped with
grease fittings for cracks on Fairchild Aircraft, Inc. (Fairchild
Aircraft) Models SA226-T, SA226-AT, and SA226-TC airplanes. AD 77-25-03
also requires replacing the landing gear actuator rod ends with
improved design parts either immediately or at a certain time period
depending on the results of the inspections. Replacement of all six rod
ends terminates the repetitive inspection requirement of AD 77-25-03.
Accomplishment of the actions of AD 77-25-03 is required in
accordance with Swearingen Aviation Corporation Service Bulletin A32-
014, dated November 17, 1977.
Actions Since Issuance of Previous Rule
The FAA has received reports of failures of the landing gear rod
ends on airplanes where the rod ends were replaced in accordance with
AD 77-25-03. The flight time accumulated on the landing gear actuators
varies between the failures; however, the reports show that these parts
are not meeting their life limits. Fairchild has re-designed the
landing gear rod ends, part number (P/N) VTA00350, as a result of these
failures.
Cracks in the landing gear actuator rod ends, if not detected and
corrected in a timely manner, could result in failure of the landing
gear actuator and the inability to lower the landing gear during a
landing with consequent possible loss of control of the airplane.
Relevant Service Information
Fairchild has issued Service Bulletin SB A32-014, Revised: January
26, 1999, which specifies procedures for replacing the existing landing
gear actuator rod ends with ones of improved design, P/N VTA00350.
[[Page 25219]]
The FAA's Determination
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 above-
referenced condition from occurring on all SA226 series airplanes,
including those manufactured since AD 77-25-03 was issued (i.e., the
Model SA226-T(B) airplanes).
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild Models SA226-T, SA226-T(B), SA226-
AT, and SA226-TC airplanes of the same type design that are equipped
with any landing gear actuator rod end other than P/N VTA00350 (or FAA-
approved equivalent part number), the FAA is proposing AD action. The
proposed AD would supersede AD 77-25-03, and would require replacing
all landing gear rod ends with these improved design parts, P/N
VTA00350 (or FAA-approved equivalent part number).
Accomplishment of the proposed replacements would be required in
accordance with Fairchild Aircraft Service Bulletin SB A32-014,
Revised: January 26, 1999.
Cost Impact
The FAA estimates that 190 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 6
workhours per airplane to accomplish the proposed replacements, and
that the average labor rate is approximately $60 an hour. Parts cost
approximately $169 per rod (6 rods per airplane). Based on these
figures, the total cost impact of the proposed AD on U.S. operators is
estimated to be $261,060, or $1,374 per airplane.
This figure is based upon the presumption that no affected airplane
owner/operator has accomplished the proposed replacement.
Regulatory Impact
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 14
CFR part 39 of the Federal Aviation Regulations 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 removing Airworthiness Directive
(AD) 77-25-03, Amendment 39-3090, and by adding a new AD to read as
follows:
Fairchild Aircraft, Inc.: Docket No. 99-CE-15-AD; Supersedes AD 77-
25-03, Amendment 39-3090.
Applicability: The following airplanes models and serial
numbers, certificated in any category; that are equipped with any
landing gear actuator rod end other than part number (P/N) VTA00350
(or FAA-approved equivalent part number).
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Model Serial No.
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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 TC396, TC398 through
TC413, and TC418 through TC419.
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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 (d) 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 indicated in the body of this AD, unless
already accomplished.
To prevent failure of the landing gear actuator caused by cracks
in the rod ends, which could result in the inability to lower the
landing gear during a landing with consequent possible loss of
control of the airplane, accomplish the following:
(a) Within the next 500 hours time-in-service (TIS) after the
effective date of this AD, replace any landing gear actuator rod end
that is not P/N VTA00350 (or FAA-approved equivalent part number)
with one that incorporates this part number. Accomplish this
replacement in accordance with Fairchild Aircraft Service Bulletin
SB A32-014, Revised: January 26, 1999.
(b) As of the effective date of this AD, no person may install,
on any affected airplane, any landing gear actuator rod end that is
other than P/N VTA00350 (or FAA-approved equivalent part number).
(c) 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.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, FAA, Airplane Certification Office (ACO),
2601 Meacham Boulevard, Fort Worth, Texas 76193-0150.
(1) 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.
(2) Alternative methods of compliance approved in accordance
with AD 77-25-03 are not considered approved as alternative methods
of compliance for this AD.
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.
(e) All persons affected by this directive may obtain copies of
the document referred to herein upon request to Fairchild Aircraft,
Inc., P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine
this document at the FAA, Central Region, Office of the Regional
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
(f) This amendment supersedes AD 77-25-03, Amendment 39-3090.
Issued in Kansas City, Missouri, on May 4, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-11779 Filed 5-10-99; 8:45 am]
BILLING CODE 4910-13-P
