AD 2000-05-24

This amendment adopts a new airworthiness directive (AD) that applies to all aircraft equipped with a certain Honeywell International Inc. (Honeywell) KAP 140 or KFC 225 autopilot system. AlliedSignal Avionics Inc. manufactured these autopilot systems before transferring the design data to Honeywell. This AD requires that you inspect the autopilot servo actuator for a loose fastener and modify the autopilot servo actuator when a loose fastener is found. This AD is the result of a report of failure of the autopilot servo actuator to disengage when the autopilot power was removed. The actions specified by this AD are intended to detect and correct a loose fastener in the autopilot servo actuator, which could cause the autopilot servo actuator to not disengage when power to the autopilot is removed. This could cause the pilot to experience additional control forces.

Final rule; request for comments

2000-05-24 HONEYWELL INTERNATIONAL INC.: Amendment 39-11634; Docket No. 2000-CE-11-AD.

(a) What aircraft are affected by this AD?: Any aircraft, certificated in any category, that is equipped with a Honeywell KAP 140 or KFC 225 autopilot system and incorporates any autopilot servo actuator referenced in the Honeywell service information and the chart presented below. AlliedSignal Avionics Inc. manufactured the KAP 140 and KFC 225 autopilot systems before transferring the design data to Honeywell:

Service Bulletin No.:
Date:
Applies To:
SB KS 270C-4 ALERT
Part number (P/N): 600-01514-0041
Revision 1: February/2000
KS 270C Pitch Servo Actuators, P/N 065-00178-XXXX (all versions), serial numbers (S/N) 2701 and below.
SB KS 271C-5 ALERT
P/N: 600-01516-0051
Revision 1: February/2000
KS 271C Primary Servo Actuators, P/N 065-00179-XXXX (all versions), S/N 4201, 4158 through 4148, and 4103 and below.
SB KS 272C-4 ALERT
P/N: 600-01518-0042
Revision 2: February/2000
KS 272C Trim Servo Actuators, P/N 065-00180-XXXX (all versions), S/N 2435 and below.

(b) Who must comply with this AD?: Anyone who wishes to operate an aircraft on the U.S. Register, where the aircraft incorporates one of the above-referenced autopilot servo actuators. These autopilot systems and autopilot servo actuators could be installed on, but not limited to, the following aircraft:

Type Certificate Holder
Aircraft Models
Autopilot Installed
Cessna Aircraft Company
172R, 172S, 182S, 206H, and T206H airplanes
Model KAP 140
Commander Aircraft Company
114B and 114TC airplanes
Model KFC 225
Mooney Aircraft Corporation
M20R and M20S airplanes
Model KFC 225
The New Piper Aircraft, Inc.
PA-28-181 airplanes
Model KAP 140
The New Piper Aircraft, Inc.
PA-46-350P airplanes
Model KFC 225
Raytheon Aircraft Company
Beech A36 airplanes, S/N E3157, E3218 through E3293, E3295, and E3297 through E3301
Model KFC 225
Raytheon Aircraft Company
Beech B36TC airplanes, S/N EA611, EA620, EA629 through EA649, and EA651
Model KFC 225
Raytheon Aircraft Company
Beech 58 airplanes, S/N TH1841, TH1870, TH1884 through TH1932, and TH1934
Model KFC 225

(c) What problem does this AD address?: The actions specified by this AD are intended to detect and correct a loose fastener in an autopilot servo actuator, which could cause the autopilot servo actuator to not disengage when power to the autopilot is removed. This could cause the pilot to experience additional control forces.

(d) What must I do to address this problem?: To address this problem, you must accomplish the following:

Action
When
In Accordance With
Inspect the autopilot servo actuator for a loose fastener.
Within 15 hours time-in-service after the effective date of this AD.
The applicable service information referenced in paragraph (a) of this AD.
Modify the autopilot servo actuator when a loose fastener is found.
Prior to further flight after the requiredinspection.
The applicable service information referenced in paragraph (a) of this AD.

(e) Is it permissible to just not use the autopilot since it is optional equipment?: You may do this provided you accomplish the following:

(1) Check the primary flight controls for normal feel and motion and make any necessary adjustments;

(2) Pull and tie off the applicable circuit breakers as referenced in the Compliance section of the applicable service information referenced in paragraph (a) of this AD;

(3) Fabricate a placard, using letters of 1/8-inch in height, with the words "Autopilot Not Operational"; and

(4) Install this placard in the cockpit within the pilot's clear view.

(f) Can I comply with this AD in any other way?: Yes.

(1) You may use an alternative method of compliance or adjust the compliance time if:

(i) Your alternative method of compliance provides an equivalent level of safety; and

(ii) The Manager, Wichita Aircraft Certification Office (ACO), approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.

(2) This AD applies to each aircraft 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 aircraft 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 (f)(1) 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 you have not eliminated the unsafe condition, specific actions you propose to address it.

(g) Where can I get information about any already-approved alternative methods of compliance?:Contact Clyde Erwin, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4149; facsimile: (316) 946-4407.

(h) What if I need to fly the aircraft to another location to comply with this AD?: The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your aircraft to a location where you can accomplish the requirements of this AD.

(i) Are any service bulletins incorporated into this AD by reference?: Yes. Actions required by this AD must be done in accordance with Honeywell Service Bulletin No. SB KS 270C-4 ALERT, P/N: 600-01514-0041, Revision 1: February/2000, Honeywell Service Bulletin No. SB KS 271C-5 ALERT, P/N: 600-01516-0051, Revision 1: February/2000, or Honeywell Service Bulletin No. SB KS 272C-4 ALERT, P/N: 600-01518-0042, Revision 2: February/2000. The Director of the FederalRegister approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You can get copies from Honeywell International Inc., 23500 West 105th Street, Olathe, Kansas 66061. You can look at copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

(j) When does this amendment become effective?: This amendment becomes effective on April 12, 2000.

Discussion
What events have caused this AD?: We recently received a field report describing an instance of excessive flight control friction associated with an airplane equipped with a Honeywell KS 271C aileron servo actuator. This event occurred during ground operations with no power applied to the airplane. The Honeywell KS 270C, KS 271C, and KS 272 series autopilot servo actuators are utilized on aircraft equipped with a Honeywell KAP 140 or KFC 225 autopilot system. AlliedSignal Avionics Inc. manufactured these autopilot systems before transferring the design data to Honeywell.

Examination of the subject actuator revealed a loose fastener, which inhibited free motion of the servo actuator engagement and disengagement mechanism. This autopilot servo actuator failed to properly disengage when power to the autopilot was removed.

What are the consequences if the condition is not corrected?: This condition, if not detected and corrected, could cause the autopilot servo actuator to not disengage when power to the autopilot is removed. This could cause the pilot to experience additional control forces.

Relevant Service Information
Is there service information that applies to this subject?: Yes. Honeywell has issued the following service bulletins:

Service Bulletin No.:
Date:
Applies To:
SB KS 270C-4 ALERT
Part number (P/N): 600-01514-0041
Revision 1: February/2000
KS 270C Pitch Servo Actuators, P/N 065-00178-XXXX (all versions), serial numbers (S/N) 2701 and below.
SB KS 271C-5 ALERT
P/N: 600-01516-0051
Revision 1: February/2000
KS 271C Primary Servo Actuators, P/N 065-00179-XXXX (all versions), S/N 4201, 4158 through 4148, and 4103 and below.
SB KS 272C-4 ALERT
P/N: 600-01518-0042
Revision 2: February/2000
KS 272C Trim Servo Actuators, P/N 065-00180-XXXX (all versions), S/N 2435 and below.

What are the provisions of the service bulletins?: The service bulletins specify and include procedures for inspecting the autopilot servo actuator for a loose fastener and modifying the autopilot servo actuator when a loose fastener is found.

The FAA's Determination and an Explanation of the Provisions of the AD
What has the FAA decided?: After examining the circumstances and reviewing all available information related to the events described above, including the relevant service information, the FAA has determined that:

- an unsafe condition exists or could develop on all aircraft that are certificated in any category and are equipped with a certain Honeywell KAP 140 or KFC 225 autopilot system;

- the actions of the above-referenced service bulletins should be accomplished on aircraft with an affected autopilot servo actuator installed; and

- AD action should be taken in order to detect and correct a loose fastener in the autopilot servo actuator, which could cause an autopilot servo actuator to not disengage when power to the autopilot is removed. This could cause the pilot to experience additional control forces.

What does this AD require?: This AD requires that you inspect the autopilot servo actuators for a loose fastener and modify the autopilot servo actuator when a loose fastener is found. This AD also gives you the option of accomplishing the following actions as an alternative to the inspection and modification actions:

- Check the primary flight controls for normal feel and motion and make any necessary adjustments;

- Pull and tie off the applicable circuit breakers as referenced in the Compliance section of the applicable service information; and

- Fabricate a placard, using letters of 1/8-inch in height, with the words "Autopilot Not Operational", and install this placard in the cockpit within the pilot's clear view.

What is the compliance time of this AD?: Within 15 hours time-in-service (TIS) after the effective date of this AD.

Will the public have the opportunity tocomment prior to the issuance of the rule?: No. Since a situation exists that requires the immediate adoption of this regulation, the FAA finds 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 Invited
Although this action is in the form of a final rule and was not preceded by notice and opportunity for public comment, the FAA invites comments on this rule. You may submit whatever written data, views, or arguments you choose. You need to include the rule's docket number and submit your comments in triplicate to the address specified under the caption "ADDRESSES." The FAA will consider all comments received on or before the closing date. We may amend this rule in light of comments received. Factual information that supports your ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether we need totake additional rulemaking action.

The FAA is re-examining the writing style we currently use in regulatory documents, in response to the Presidential memorandum of June 1, 1998. That memorandum requires federal agencies to communicate more clearly with the public. We are interested in your comments on whether the style of this document is clearer, and any other suggestions you might have to improve the clarity of FAA communications that affect you. You can get more information about the Presidential memorandum and the plain language initiative at http://www.plainlanguage.gov.

The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. You may examine all comments we receive before and after the closing date of the rule in the Rules Docket. We will file a report in the Rules Docket that summarizes each FAA contact with the public that concerns the substantive partsof this AD.

If you want us to acknowledge the receipt of your comments, you must include a self-addressed, stamped postcard. On the postcard, write "Comments to Docket No. 2000-CE-11-AD." We will date stamp and mail the postcard back to you.

Regulatory Impact
These regulations will not have a substantial direct effect 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, the FAA has determined that this final rule does not have federalism implications under Executive Order 13132.

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.

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