Airworthiness Directives; Fairchild Aircraft, Inc. Models SA226- T, SA226-T(B), SA226-AT, and SA226-TC Airplanes

[Federal Register Volume 64, Number 194 (Thursday, October 7, 1999)]
[Rules and Regulations]
[Pages 54512-54513]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25745]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-15-AD; Amendment 39-11348; AD 99-21-05]
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: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 77-25-
03, which currently requires repetitively inspecting for cracks on the 
landing gear actuator rod ends that are equipped with grease fittings, 
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. This AD 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. This AD 
requires 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 this 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: Effective November 16, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 16, 1999.

ADDRESSES: Service information that applies to this 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 may also be examined at 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; or at the Office of the Federal Register, 800 North 
Capitol Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Hung Viet Nguyen, FAA, Airplane 
Certification Office, 2601 Meacham Boulevard, Fort Worth, Texas 76193-
0150; telephone: (817) 222-5155; facsimile: (817) 222-5960.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This AD

    AD 77-25-03, Amendment 39-3090, currently requires repetitively 
inspecting for cracks on the landing gear actuator rod ends that are 
equipped with grease fittings, on Fairchild Aircraft Models SA226-T, 
SA226-AT, and SA226-TC airplanes; and replacing the landing gear 
actuator rod ends.
    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Fairchild Aircraft 
Models SA226-T, SA226-T(B), SA226-AT, and SA226-TC airplanes that are 
equipped with any landing gear actuator rod end other than part number 
(P/N) VTA00350 (or FAA-approved equivalent part number) was published 
in the Federal Register as a notice of proposed rulemaking (NPRM) on 
May 11, 1999 (64 FR 25218). The NPRM proposed to supersede AD 77-25-03 
with a new AD that would require replacing all landing gear rod ends 
with improved design parts, P/N VTA00350 (or FAA-approved equivalent 
part number). Accomplishment of the proposed replacements as specified 
in the NPRM would be required in accordance with Fairchild Aircraft 
Service Bulletin SB A32-014, Revised: January 26, 1999.
    The NPRM was 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. One comment was received in favor of 
the NPRM and no comments were received on the FAA's determination of 
the cost to the public.

The FAA's Determination

    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 minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 190 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 6 workhours per 
airplane to accomplish the 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 this AD on U.S. operators is estimated to be $261,060, or 
$1,374 per airplane.
    These figures are based upon the presumption that no affected 
airplane owner/operator has accomplished the replacement.

Regulatory Impact

    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

[[Page 54513]]

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:

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:

99-21-05  Fairchild Aircraft, Inc.: Amendment 39-11348; 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).

------------------------------------------------------------------------
                 Model                             Serial No.
------------------------------------------------------------------------
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.
------------------------------------------------------------------------

    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 Alert 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) The replacements required by this AD shall be done in 
accordance with Fairchild Aircraft Alert Service Bulletin SB A32-
014, Revised: January 26, 1999. 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, Inc., P.O. Box 790490, San Antonio, Texas 78279-
0490. Copies may be inspected at the FAA, Central Region, Office of 
the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW, suite 700, Washington, DC.
    (f) This amendment supersedes AD 77-25-03, Amendment 39-3090.
    (g) This amendment becomes effective on November 16, 1999.

    Issued in Kansas City, Missouri, on September 27, 1999.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-25745 Filed 10-6-99; 8:45 am]
BILLING CODE 4910-13-P

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