[Federal Register Volume 62, Number 12 (Friday, January 17, 1997)]
[Rules and Regulations]
[Pages 2552-2554]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-814]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-64-AD; Amendment 39-9886; AD 97-02-02]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft, Inc. SA26, SA226,
and SA227 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to Fairchild Aircraft, Inc. (Fairchild) SA26, SA226, and SA227
series airplanes. This action requires applying torque to the control
column pitch bearing attaching nuts, inspecting for any looseness or
movement of the bearing assembly, and inspecting the elevator control
rod end bearing retainer/dust seals for creasing. If either of these
problems are evident, this action requires replacing these parts, as
well as installing a new bolt and washer to the elevator control rod
end bearing assembly at the walking beam connection. Reports of
Fairchild SA227 series airplanes losing pitch control in-flight
prompted this action. The actions specified by this AD are intended to
prevent loss of pitch control, which if not corrected, could result in
loss of the airplane.
DATES: Effective February 6, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 6, 1997.
Comments for inclusion in the Rules Docket must be received on or
before March 6, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket 96-CE-64-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
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. This information may also be examined
at the Federal Aviation Administration (FAA), Central Region, Office of
the Assistant Chief Counsel, Attention: Rules Docket 96-CE-64-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. Werner Koch, Aerospace Engineer,
FAA, Fort Worth Airplane Certification Office, 2601 Meacham Boulevard,
Fort Worth, Texas 76193-0150; telephone (817) 222-5133; facsimile (817)
222-5960.
SUPPLEMENTARY INFORMATION:
Events Leading to This Action
The FAA has recently received two incident reports on Fairchild
SA227 series airplanes in which the airplane lost some pitch control
because of fatigue failure of the pitch pivot bearing shaft. Further
investigation revealed fatigue and wear in the control column pitch
pivot bearings resulting from insufficient torque on the control column
roller bearing stud attaching nuts. While inspecting the pivot bearing
on four other Fairchild airplanes, it was discovered that the rod end
bearing retainer of the elevator control rod at the walking beam
connection was deformed or creased. This creasing is caused by improper
installation and could allow the bearing to come apart, disconnecting
the joint, and possibly resulting in loss of pitch control.
Fairchild has issued four service bulletins (SB) numbered 26-27-30-
046, 226-27-060, 227-27-041, and CC7-27-010, dated December 11, 1996,
which specify applying torque to the control column pitch bearing
attaching nut, inspecting the control column roller bearing assembly
for movement, replacing the bearing and attaching nut if necessary,
inspecting the elevator control rod end bearing retainer/dust covers
for creasing, replacing the rod end assemblies, if necessary, and
installing a new bolt and washer to the elevator control rod end
bearing assembly at the walking beam connection.
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 loss of pitch
control, which if not corrected, could result in loss of the airplane.
Explanation of the Provisions of This AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild SA26, SA226, and SA227 series
airplanes of the same type design, this AD requires:
(1) Applying torque to the control column pitch bearing attaching
nut,
(2) Inspecting for movement in the control column roller bearing
assembly,
(3) Replacing the bearing assembly and attaching nut, if
applicable,
(4) Inspecting the elevator control rod end bearing retainer/dust
covers for creasing,
(5) Replacing the elevator control rod end assemblies, if
applicable, and
(6) Installing a new bolt and adding a washer to the elevator
control rod end bearing assembly at the walking beam connection.
Related Service Information
These actions are to be done in accordance with the ACCOMPLISHMENT
INSTRUCTIONS in Fairchild SBs 26-27-30-046, 226-27-060, 227-27-041, and
CC7-27-010, Issued December 11, 1996.
Since a situation exists (possible loss of in-flight pitch control)
that requires the immediate adoption of this regulation, it is found
that notice and opportunity for public prior comment hereon are
impracticable, and that good cause exists for making this amendment
effective in less than 30 days.
[[Page 2553]]
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting immediate flight safety and, thus, was not
preceded by notice and opportunity to comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 will be considered,
and this rule may be amended in light of the comments received. Factual
information that supports the commenter's ideas and suggestions is
extremely helpful in evaluating the effectiveness of the AD action and
determining whether additional rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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
AD 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. 96-CE-64-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a significant regulatory action under
Executive Order 12866. It has been determined further that this action
involves an emergency regulation under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979). If it is determined that
this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket (otherwise, an evaluation is
not required). A copy of it, if filed, may be obtained from the Rules
Docket.
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:
97-02-02 Fairchild Aircraft, Inc.: Amendment 39-9886; Docket No.
96-CE-64-AD.
Applicability: Models SA26, SA226, SA227-AC, SA227-AT, SA227-BC,
SA227-TT, and SA227-CC/DC (serial numbers CC/DC784, and CC/DC790
through CC/DC884), 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 (e) 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 75 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished.
To prevent loss of pitch control, which if not corrected, could
result in loss of the airplane, accomplish the following:
(a) Apply torque to the control column pitch bearing attaching
nuts and inspect for movement in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of Fairchild Aircraft (Fairchild) Service
Bulletin (SB) No. 26-27-30-046, 226-27-060, 227-27-041, or CC7-27-
010, dated December 11, 1996, whichever is applicable.
(1) If there is no movement, then no further action is
necessary.
(2) If there is movement, prior to further flight, replace the
pitch control column roller bearing and attaching nut in accordance
with Fairchild SB 26-27-30-046, 226-27-060, 227-27-041, or CC7-27-
010, dated December 11, 1996, whichever is applicable.
(b) Inspect the elevator control rod end bearing retainer/dust
seals for evidence of creasing in accordance with Fairchild SB 26-
27-30-046, 226-27-060, 227-27-041, or CC7-27-010, dated December 11,
1996, whichever is applicable.
(1) If no creasing is found, then rod end assembly replacement
is not necessary.
(2) If creasing is found, prior to further flight, replace the
elevator control rod end assembly in accordance with Fairchild SB
26-27-30-046, 226-27-060, 227-27-041, or CC7-27-010, dated December
11, 1996, whichever is applicable.
(c) Install a new washer (part number (P/N) AN970-4) and replace
the bolt (P/N NAS6604D31) with a new bolt (P/N NAS6604D34) on the
elevator control rod end bearing assembly at the walking beam
connections in accordance with Fairchild SB 26-27-30-046, 226-27-
060, 227-27-041, or CC7-27-010, dated December 11, 1996, whichever
is applicable.
(d) 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.
(e) 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,
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
Airplane Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth Airplane Certification Office.
(f) The inspections and replacement required by this AD shall be
done in accordance with FAIRCHILD AIRCRAFT Service Bulletin No. SB
26-27-30-046, 226-27-060, 227-27-041, or CC7-27-010, Issued:
December 11, 1996. 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;
telephone (210) 824-9421. 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.
(g) This amendment (39-9886) becomes effective on February 6,
1997.
[[Page 2554]]
Issued in Kansas City, Missouri, on January 6, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-814 Filed 1-16-97; 8:45 am]
BILLING CODE 4910-13-U
