[Federal Register Volume 61, Number 204 (Monday, October 21, 1996)]
[Rules and Regulations]
[Pages 54538-54540]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-26705]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-40-AD; Amendment 39-9782; AD 96-21-05]
RIN 2120-AA64
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
that do not have a certain elevator torque tube installed. This action
requires drilling inspection access holes in the elevator torque tube
arm, inspecting the elevator torque tube for corrosion, replacing any
corroded elevator torque tube, and applying a corrosion preventive
compound. Several reports of corrosion found in the elevator torque
tube area on the affected airplanes prompted this action. The actions
specified by this AD are intended to prevent failure of the flight
control system caused by a corroded elevator torque tube, which could
result in loss of control of the airplane.
DATES: Effective November 29, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 29, 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
[[Page 54539]]
(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-40-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: Mr. Hung Viet Nguyen, Aerospace
Engineer, 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 This AD
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 September 19, 1995 (60 FR 48431). The action proposed to
require drilling inspection access holes in the elevator torque tube
arm, inspecting the elevator torque tube for corrosion, replacing any
corroded elevator torque tube, and applying a corrosion preventive
compound. Accomplishment of the proposed inspection access hole
drilling, the inspection, and the corrosion preventive compound
application as specified in the notice of proposed rulemaking (NPRM)
would be in accordance with either Fairchild Service Bulletin (SB) 226-
27-050 or Fairchild SB 227-27-028, both Issued: January 22, 1990.
Several reports of corrosion found in the elevator torque tube area
on the affected airplanes prompted the proposal.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. One comment was received in favor of
the proposal and no comments were received regarding the FAA's
determination of the cost to the public.
Since issuing Fairchild SB 226-27-050, Fairchild Aircraft has
designed an improved elevator torque tube, part number (P/N) 27-44026-
007. The FAA has determined that airplane owners/operators of Fairchild
Aircraft SA226 and SA227 series airplanes that have a P/N 27-44026-007
elevator torque tube installed should not have to accomplish the
actions specified in the NPRM.
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
the exemption of those airplanes with a P/N 27-44026-007 elevator
torque tube installed and minor editorial corrections. The FAA has
determined that this exemption and the minor corrections will not
change the meaning of the AD and will not add any additional burden
upon the public than was already proposed.
Compliance Time of This AD
The compliance time for this AD is presented in calendar time
instead of hours time-in-service (TIS). The FAA has determined that a
calendar time for compliance would be the most desirable method because
the unsafe condition described by this AD is caused by corrosion.
Corrosion can occur on airplanes regardless of whether the airplane is
in service or on the ground.
Cost Impact
The FAA estimates that 390 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 10 workhours per
airplane to accomplish the required action, and that the average labor
rate is approximately $60 an hour. Based on these figures, the total
cost impact of the AD on U.S. operators is estimated to be $234,000.
This figure is based on the assumption that no owner/operator of the
affected airplanes has accomplished the required inspection access hole
drilling, inspection, or corrosion preventive compound application. It
also is based on the assumption that no elevator torque tube would be
found corroded and need to be replaced. The FAA has no way of
determining how many owners/operators of the affected airplanes may
have already complied with this AD.
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
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 adding a new airworthiness directive
(AD) to read as follows:
96-21-05 Fairchild Aircraft: Amendment 39-9782; Docket No. 95-CE-
40-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category, that do not have a part number (P/N)
27-44026-007 elevator torque tube installed:
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
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 TC419.
SA227-TT............................ TT421 through TT541.
SA227-AT............................ AT423 through AT695.
SA227-AC............................ AC406, AC415, AC416, and AC420
through AC772.
------------------------------------------------------------------------
Note 1: This AD applies to each airplane identified in the
preceding applicability revision, 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
[[Page 54540]]
specific proposed actions to address it. Compliance: Required within
the next six calendar months after the effective date of this AD,
unless already accomplished.
To prevent failure of the flight control system caused by a
corroded elevator torque tube, which could result in loss of control
of the airplane, accomplish the following:
(a) Drill two .5-inch diameter holes in the inboard side of the
elevator torque tube arm in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of and as specified in Figure 1 of Fairchild
Aircraft Service Bulletin (SB) 226-27-050 or Fairchild Aircraft SB
227-27-028, both Issued: January 22, 1990, as applicable.
(b) Inspect the elevator torque tube in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft SB 226-27-
050 or Fairchild Aircraft SB 227-27-028, both Issued: January 22,
1990, as applicable.
(1) If corrosion is found inside the elevator torque tube, prior
to further flight after the inspection required by paragraph (b) of
this AD, replace the corroded elevator torque tube with a P/N 27-
44026-007 elevator torque tube in accordance with the applicable
maintenance manual.
(2) If corrosion is not found inside the elevator torque tube,
prior to further flight after the inspection required by paragraph
(b) of this AD, apply a corrosion preventive compound in accordance
with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft
SB 226-27-050 or Fairchild Aircraft SB 227-27-028, both Issued:
January 22, 1990, as applicable.
(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, Airplane Certification Office (ACO), FAA,
2601 Meacham Boulevard, Fort Worth, Texas 76193-0150. 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.
(e) The drilling, inspection, and application required by this
AD shall be done in accordance with Fairchild Aircraft Service
Bulletin 226-27-050 or Fairchild Service Bulletin 227-27-028, both
Issued: January 22, 1990. 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., suite 700, Washington, DC.
(f) This amendment (39-9782) becomes effective on November 29,
1996.
Issued in Kansas City, Missouri, on October 10, 1996.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-26705 Filed 10-18-96; 8:45 am]
BILLING CODE 4910-13-U
