AD Amdt-39-11197

[Federal Register Volume 64, Number 117 (Friday, June 18, 1999)]
[Rules and Regulations]
[Pages 32797-32799]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-15220]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-23-AD; Amendment 39-11197; AD 99-13-04]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Models 206H and 
T206H Airplanes

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Cessna Aircraft Company (Cessna) Models 206H and 
T206H airplanes. This AD requires inspecting the left and right wing 
aileron control bellcrank stop bolts and lock nuts for flush and tight 
contact with the surface of the threaded boss on each end of the yoke 
assemblies, and accomplishing follow-on and corrective actions, as 
applicable. This AD is the result of an inspection on one of the

[[Page 32798]]

affected airplanes that showed that the aileron control bellcrank stop 
bolt had partially backed out of the threaded boss. The actions 
specified by this AD are intended to detect and correct loose aileron 
control bellcrank stop bolts, which could result in restricted movement 
of the ailerons with possible partial or complete loss of aileron 
control.

DATES: Effective July 13, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 13, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before August 13, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 99-CE-23-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.
    Service information that applies to this AD may be obtained from 
the Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277-7706; 
telephone: (316) 517-5800; facsimile: (316) 942-9066. This information 
may also be examined at the Federal Aviation Administration (FAA), 
Central Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 99-CE-23-AD, Room 1558, 601 E. 12th Street, 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: Mr. Shane Bertish, Aerospace Engineer, 
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 
100, Mid-Continent Airport, Wichita, Kansas, 67209, telephone: (316) 
946-4156; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA has received information from an inspection of a Cessna 
Model 206H airplane that reveals that the aileron control bellcrank 
stop bolt had partially backed out of the threaded boss on one end of a 
yoke assembly. This restricted the movement of both ailerons, which 
could result in partial or complete loss of aileron control.
    Both the Cessna Models 206H and T206H airplanes with the following 
serial numbers have aileron system designs where the above-referenced 
situation could exist:

------------------------------------------------------------------------
              Models                           Serial numbers
------------------------------------------------------------------------
206H.............................  20608002 through 20608026.
T206H............................  T20608002 through T20608015;
                                    T20608017 through T20608023; and
                                    T20608025 through T20608028
------------------------------------------------------------------------

Relevant Service Information

    Cessna has issued Special Service Project SSP99-27-02, which 
specifies procedures for inspecting the left and right wing aileron 
control bellcrank stop bolts and lock nuts for flush and tight contact 
with the surface of the threaded boss on each end of the yoke 
assemblies, and accomplishing follow-on and corrective actions, as 
applicable.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, including the 
relevant service information, the FAA has determined that:

--the actions referenced in the service information should be 
accomplished on the Cessna Models 206H and T206H airplanes; and
--AD action should be taken to detect and correct loose aileron control 
bellcrank stop bolts, which could result in restricted movement of the 
aileron with possible partial or complete loss of aileron control.

Explanation of the Provisions of the AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Cessna Models 206H and T206H airplanes of the 
same type design, the FAA is taking AD action. This AD requires 
inspecting the left and right wing aileron control bellcrank stop bolts 
and lock nuts for flush and tight contact with the surface of the 
threaded boss on each end of the yoke assemblies, and accomplishing 
follow-on and corrective actions, as applicable.
    Accomplishment of the actions specified in this AD are required in 
accordance with the instructions in Cessna Special Service Project 
SSP99-27-02, dated May 18, 1999.

Compliance Time of This AD

    Although the aileron control bellcrank stop bolts and lock nuts not 
being flush and in tight contact with the surface of the threaded boss 
on each end of the yoke assemblies is only unsafe while the airplane is 
in flight, this condition is not a result of the number of times the 
airplane is operated. The chance of this situation existing is the same 
for an airplane with 200 hours time-in-service (TIS) as it is for an 
airplane with 3,000 hours TIS. In addition, the usage levels of the 
affected airplane vary immensely. Some operators may accumulate 25 
hours TIS in a matter of days, where other operators may only utilize 
their airplanes a few hours in a month.
    For these reasons, the FAA has determined that a compliance based 
on calendar time and hours TIS (with the prevalent one being that which 
occurs first) should be utilized in this AD in order to assure that the 
unsafe condition is addressed on all affected airplanes in a reasonable 
time period without inadvertently grounding certain airplanes. The 
compliance time of the inspection required by this AD will be as 
follows:

    ``Within the next 10 hours TIS after the effective date of this 
AD or within the next 60 calendar days after the effective date of 
this AD, whichever occurs first.''

Determination of the Effective Date of the AD

    Since a situation exists (possible partial or complete loss of 
aileron 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 Invited

    Although 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.

[[Page 32799]]

    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 99-CE-23-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 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:

99-13-04 Cessna Aircraft Company: Amendment 39-11197; Docket No. 99-
CE-23-AD.

    Applicability: The following airplane model and serial number 
airplanes, certificated in any category:

------------------------------------------------------------------------
              Models                           Serial numbers
------------------------------------------------------------------------
206H.............................  20608002 through 20608026.
T206H............................  T20608002 through T20608015;
                                    T20608017 through T20608023; and
                                    T20608025 through T20608028.
------------------------------------------------------------------------

    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 
address it.

    Compliance: Required as indicated in the body of this AD, unless 
already accomplished.
    To detect and correct loose aileron control bellcrank stop 
bolts, which could result in restricted movement of the aileron with 
possible partial or complete loss of aileron control, accomplish the 
following:
    (a) Within the next 10 hours time-in-service after the effective 
date of this AD or within the next 60 calendar days after the 
effective date of this AD, whichever occurs first, inspect the left 
and right wing aileron control bellcrank stop bolts and lock nuts 
for flush and tight contact with the surface of the threaded boss on 
each end of the yoke assemblies. Accomplish this inspection in 
accordance with the INSPECTION/MODIFICATION INSTRUCTIONS section of 
Cessna Special Service Project SSP99-27-02, dated May 18, 1999.
    (b) If the bolts and nuts are flush and tight, or loose but 
flush after tightening, prior to further flight, accomplish the 
following actions in accordance with the INSPECTION/MODIFICATION 
INSTRUCTIONS section of Cessna Special Service Project SSP99-27-02, 
dated May 18, 1999:
    (1) Loosen nuts;
    (2) Clean threads (bolt and nut);
    (3) Wick Loctite 290 into threads; and
    (4) Torque nut.
    (c) If the bolts and nuts are not flush, prior to further 
flight, accomplish the following actions in accordance with the 
INSPECTION/MODIFICATION INSTRUCTIONS section of Cessna Special 
Service Project SSP99-27-02, dated May 18, 1999:
    (1) Remove nut and stop bolt;
    (2) Spotface boss;
    (3) Clean threads (boss, bolt, and nut);
    (4) Apply Loctite 242;
    (5) Adjust stop bolt; and
    (6) Torque bolt.

    Note 2: Paragraphs (b) and (c) of this AD present a basic 
outline of the follow-on work to be accomplished. The detailed 
procedures to accomplish these actions are included in the 
INSPECTION/MODIFICATION INSTRUCTIONS section of Cessna Special 
Service Project SSP99-27-02, dated May 18, 1999.

    (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 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.

    (f) The inspections and follow-on actions required by this AD 
shall be done in accordance with Cessna Special Service Project 
SSP99-27-02, dated May 18, 1999. 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 the 
Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277-7706. 
Copies may be inspected at the FAA, Central Region, Office of the 
Regional 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 July 13, 1999.

    Issued in Kansas City, Missouri, on June 10, 1999.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-15220 Filed 6-17-99; 8:45 am]
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