[Federal Register Volume 65, Number 54 (Monday, March 20, 2000)]
[Rules and Regulations]
[Pages 14831-14834]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-6161]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-11-AD; Amendment 39-11634; AD 2000-05-24]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. KAP 140 
and KFC 225 Autopilot Systems

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 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.

DATES: Effective April 12, 2000.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulation as of April 
12, 2000.
    The FAA must receive any comments on this rule on or before April 
28, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2000-CE-11-AD, 901 Locust, Room 506, Kansas 
City, Missouri 64106.
    You may get the service information referenced in this AD from 
Honeywell International Inc., 23500 West 105th Street, Olathe, Kansas 
66061. You may examine this information at the FAA, Central Region, 
Office of the Regional Counsel, Attention: Rules Docket No. 2000-CE-11-
AD, 901 Locust, Room 506, 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: 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.

SUPPLEMENTARY INFORMATION:

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.

[[Page 14832]]

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/   Revision 1: February/2000..  KS 270C Pitch Servo Actuators, P/N 065-00178-
 N): 600-01514-0041.                                               XXXX (all versions), serial numbers (S/N)
                                                                   2701 and below.
SB KS 271C-5 ALERT P/N: 600-01516-   Revision 1: February/2000..  KS 271C Primary Servo Actuators, P/N 065-00179-
 0051.                                                             XXXX (all versions), S/N 4201, 4158 through
                                                                   4148, and 4103 and below.
SB KS 272C-4 ALERT P/N: 600-01518-   Revision 2: February/2000..  KS 272C Trim Servo Actuators, P/N 065-00180-
 0042.                                                             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 to comment 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 to take 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 parts of 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.

[[Page 14833]]

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:

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/   Revision 1: February/2000..  KS 270C Pitch Servo Actuators, P/N 065-00178-
 N): 600-01514-0041.                                               XXXX (all versions), serial numbers (S/N)
                                                                   2701 and below.
SB KS 271C-5 ALERT P/N: 600-01516-   Revision 1: February/2000..  KS 271C Primary Servo Actuators, P/N 065-00179-
 0051.                                                             XXXX (all versions), S/N 4201, 4158 through
                                                                   4148, and 4103 and below.
SB KS 272C-4 ALERT P/N: 600-01518-   Revision 2: February/2000..  KS 272C Trim Servo Actuators, P/N 065-00180-
 0042.                                                             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        Model KFC 225.
                                  through E3293, E3295, and E3297 through
                                  E3301.
Raytheon Aircraft Company......  Beech B36TC airplaces, S/N EA611, EA620,     Model KFC 225.
                                  EA629 through EA649, and EA651.
Raytheon Aircraft Company......  Beech 58 airplanes, S/N TH1841, TH1870,      Model KFC 225
                                  TH1884 through TH1932, and TH1934.
----------------------------------------------------------------------------------------------------------------

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

[[Page 14834]]

    (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 Federal Register 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.

    Issued in Kansas City, Missouri, on March 6, 2000.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 00-6161 Filed 3-17-00; 8:45 am]
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