AD 98-08-20

This amendment adopts a new airworthiness directive (AD) that applies to certain AlliedSignal Aerospace Bendix/King Model KSA 470 autopilot servo actuators, part numbers 065-0076-10 through 065-0076-15, that are installed on aircraft. This AD requires replacing the autopilot servo actuator with a modified actuator. This is the result of two reports of the affected autopilot servo actuators containing loose roll pins within the servo housing. Loose roll pins could fall out, become lodged in the output shaft clutch mechanism, and prevent this mechanism from disengaging. The actions specified by this AD are intended to prevent such an occurrence, which could result in increased effort by the pilot to control the aircraft and possible loss of control of the affected flight control axis.

Final rule.

98-08-20 ALLIEDSIGNAL AEROSPACE: Amendment 39-10469; Docket No. 97-CE-74-AD.

Applicability: Bendix/King Model KSA 470 Autopilot Servo Actuators; part numbers 065-0076-10 through 065-0076-15; serial numbers 0001 through 3081; that are installed on, but not limited to, the following aircraft, certificated in any category:

NOTE 1: This subject is addressed in AlliedSignal Bendix/King Service Bulletin No. SB KSA 470-3, dated May 1997. This service bulletin references serial number 3082. Regardless of this reference, serial number 3082 is not affected by this AD.

Aircraft
FD/AP System
KSA 470 Part No.
Location
Raytheon 400 Series
KFC 400
065-0076-11
Yaw Axis

065-0076-15
Roll Axis
Raytheon 200 Series
KFC 400
065-0076-11
Yaw Axis
Raytheon 300 Series
KFC 400
065-0076-15
Yaw Axis
Dassault Falcon 20
KFC 400
065-0076-15
Pitch Axis

065-0076-15
Roll Axis
Fairchild C26A/C26B
KFC400
065-0076-11
Yaw Axis
Fairchild SA227-AC/
AT/BC/CC/DC
KFC400
065-0076-15
Roll Axis
Learjet 31A
KFC 3100
065-0076-12
Pitch Axis

065-0076-14
Yaw Axis

065-0076-15
Roll Axis
Lockheed S-2 Tracker
KFC 325
065-0076-10
Special
Piper 400LS and PA-42-1000
KFC 400
065-0076-15
Yaw Axis

NOTE 2: This AD applies to each airplane identified in the preceding applicability provision that has one of the affected actuators installed, 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 within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished.

To prevent the servo actuator roll pins from becoming loose; falling out; becoming lodged in the output shaft clutch mechanism; and preventing this mechanism from disengaging, which could result in increased effort by the pilot to control the aircraft and possible loss of control of the affected flight control axis, accomplish the following:

(a) Replace the autopilot servo actuator with an actuator that incorporates Mod 3 in accordance with the applicable maintenance manual. This modification changes the size of the servo actuator roll pin holes to assure that the pins do not become loose and fall out.

(b) As of the effective date of this AD, no person may install, on aircraft, one of the affected servo actuators that does not incorporate Mod 3.

(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 times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO.

(e) All persons affected by this directive may obtain copies of the documents referred to herein upon request to AlliedSignal Aerospace, Technical Publications, Department 65-70, P.O. Box 52170, Phoenix, Arizona 85072-2170; or may examine these documents at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

(f) This amendment becomes effective on June 2, 1998.

Events Leading to the Issuance of 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 AlliedSignal Aerospace Bendix/King Model KSA 470 autopilot servo actuators, part numbers 065-0076-10 through 065-0076-15, that are installed on aircraft was published in the Federal Register as a notice of proposed rulemaking (NPRM) on December 19, 1997 (62 FR 66565). The NPRM proposed to require replacing the autopilot servo actuator with a modified actuator. Accomplishment of the proposed action as specified in the NPRM would be in accordance with Bendix/King Service Bulletin No. SB KSA 470-3, dated May 1997.

The NPRM was the result of two reports of the affected autopilot servo actuators containing loose roll pins within the servo housing. Loose roll pins could fall out, become lodged in the output shaft clutch mechanism, and prevent this mechanism from disengaging.

Interestedpersons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the one comment received. No comments were received on the FAA's determination of the cost to the public.

Comment Disposition
The commenter states that the reference to the Raytheon 350 series aircraft in the proposal is incorrect. The commenter explains that the Raytheon 350 series is actually a Raytheon 300 series aircraft. The commenter requests that the FAA reference these aircraft accordingly.

The FAA concurs that these aircraft should be referenced as Raytheon 300 series instead of Raytheon 350 series. Since the Raytheon 300 series is already referenced in the AD, the FAA will remove all reference to the Raytheon 350 series in the final rule.

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 adoptionof the rule as proposed except for the change referenced above and minor editorial corrections. The FAA has determined that this change 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.

Cost Impact
The FAA estimates that 500 of the affected servo actuators could be installed on aircraft in the U.S. registry. This replacement will take approximately 2 workhours per aircraft to accomplish, at an average labor rate of approximately $60 an hour. Servo actuators with Mod 3 incorporated cost $2,350. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $1,235,000, or $2,470 per aircraft. These figures are based on the presumption that no owner/operator of the affected aircraft has accomplished this replacement.

AlliedSignal has informed the FAA that costs of the required labor and modification of the servo actuators on affected aircraft may berecovered under an AlliedSignal conditional warranty program. Information regarding warranty claims associated with this action can be obtained directly from AlliedSignal at the address included in the "ADDRESSES" section of 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, 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.

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