AD 97-02-02

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.

Final rule; request for comments.

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 addressit.

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 forevidence 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 becomes effective on February 6, 1997.

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 attachingnut,

(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.

Comments InvitedAlthough 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 USC 106(g), 40113, 44701.

39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows: