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

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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