Federal Register, Volume 65 Issue 54 (Monday, March 20, 2000)

[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:

(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]
BILLING CODE 4910-13-U