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[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
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