[Federal Register Volume 63, Number 123 (Friday, June 26, 1998)]
[Rules and Regulations]
[Pages 34800-34803]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-17020]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-60-AD; Amendment 39-10634; AD 98-13-41]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Model 172R 
Airplanes

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 certain Cessna Aircraft Company (Cessna) Model 172R 
airplanes. This action requires: inspecting for incorrectly routed 
aileron control cables in the center console area; inspecting for 
incorrectly routed aileron control cables in the right-hand (RH)

[[Page 34801]]

wing area; inspecting for a loose or improperly installed center lock 
clamp on the forward aileron control cable drum; and inspecting for 
loose or missing elevator trim actuator mounting screws, loose rudder 
circuit pulleys, missing rudder cable guard pins, incorrect elevator 
trim cable routing, aileron control cable clearance, and flight control 
cable tension or rigging outside specification. If any of the above 
conditions are found, this AD requires correcting, repairing, or 
replacing any damaged or missing part, and reporting any of the above 
conditions found to the Wichita Aircraft Certification Office. 
Notification by the manufacturer, service difficulty reports (SDR's), 
and an FAA surveillance audit at the manufacturing facility identifying 
potential deficiencies on the affected airplanes prompted the action. 
The actions specified by this AD are intended to prevent loss of 
aileron and elevator control, which could result in loss of directional 
control of the airplane.

DATES: Effective July 20, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 20, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before August 18, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 98-CE-60-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, 
telephone: (316) 941-7550, facsimile: (316) 942-9008. This information 
may also be examined at the Federal Aviation Administration (FAA), 
Central Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 98-CE-60-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. Joel M. Ligon, Aerospace Engineer, 
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Rm. 100, 
Mid-Continent Airport, Wichita, Kansas, 67209, telephone: (316) 946-
4138; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA has recently been notified by Cessna Aircraft Company of a 
quality control problem in the aileron and elevator control systems on 
certain Cessna Model 172R airplanes. In addition to this disclosure, 
the FAA has received service difficulty reports (SDR's) from the field 
regarding aileron cable control malfunction. The FAA also completed a 
surveillance audit revealing airplanes having incorrectly routed 
aileron cables, mis-rigged aileron and elevator control cables, and 
missing parts in the aileron and elevator systems.

Relevant Service Information

    Cessna has issued the following service bulletins applicable to 
certain Cessna Model 172R airplanes:

--SB98-27-02, dated May 11, 1998, which specifies procedures for 
inspecting for incorrect routing of the aileron cable over the cable 
guard in the center console area, or fraying of the cable. If incorrect 
routing is found and the cable is frayed, the service bulletin 
specifies replacing the cable with a new cable. If incorrect routing is 
found, but no evidence of fraying is found, the service bulletin 
specifies re-routing the cable to its correct position;
--SB98-27-05, dated June 1, 1998, which specifies procedures for 
inspecting the aileron control cable in the right-hand (RH) wing for 
routing over an aileron autopilot actuator pulley instead of the 
aileron flight control pulley in the adjacent location and contains 
instructions to remove the aileron autopilot actuator pulley. If the 
aileron control cable is routed over the autopilot actuator pulley and 
the cable is frayed or damaged, replace the aileron control cable. If 
mis-routing is found, but no evidence of fraying is found, the service 
bulletin specifies re-routing the cable to its proper position;
--SB98-27-03, dated June 1, 1998, which specifies procedures for 
inspecting for a loose or incorrectly installed aileron control cable 
centering and retainer lock clamp on the forward aileron control cable 
drum. This condition can result in the primary aileron cable dislodging 
on the drum which could cause damage to the drum and/or partial or 
complete loss of aileron control. If this condition is found, repair or 
replace any damaged part; and,
--SB98-27-06, dated June 15, 1998, which specifies procedures for 
inspecting for loose or missing elevator trim actuator mounting screws, 
loose rudder circuit pulleys, missing rudder cable guard pins, 
incorrect routing of the elevator trim cable, incorrect aileron 
crossover cable clearance, and incorrect specifications of the flight 
control cable tension and rigging. If any of the above conditions are 
found, the service bulletin specifies repairing, replacing, or 
correcting the part that is damaged, out of alignment, or mis-rigged.

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 AD action 
should be taken to prevent loss of aileron and elevator control, which 
could result in loss of directional control of the airplane.

Explanation of the Provisions of the AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Cessna Model 172R airplanes of the same type 
design, this AD requires:

--Inspecting for incorrectly routed aileron control cable in the center 
console area;
--Inspecting for incorrectly routed aileron control cable in the right-
hand (RH) wing area;
--Inspecting for a loose or incorrectly installed center lock clamp on 
the forward aileron control cable drum;
--Inspecting for loose or missing elevator trim actuator mounting 
screws, loose rudder circuit pulleys, missing rudder cable guard pins, 
improper elevator trim cable routing, aileron control cable clearance, 
and flight control cable tension rigging outside specification; and
--If any of the above conditions are found, this AD would require 
correcting the condition, repairing or replacing any damaged or missing 
part, and reporting any condition found to the Wichita Manufacturing 
Inspection Office.

    The inspections are to be done in accordance with the 
Accomplishment Instructions contained in Cessna Service Bulletins (SB) 
SB98-27-02, dated May 11, 1998, SB98-27-03, dated June 1, 1998, SB98-
27-05, dated June 1, 1998, and SB98-27-06, dated June 15, 1998, 
whichever is applicable.

Determination of the Effective Date of the AD

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for public 
prior comment

[[Page 34802]]

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.
    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. 98-CE-60-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:

98-13-41  Cessna Aircraft Company: Amendment 39-10634; Docket No. 
98-CE-60-AD.

    Applicability: Model 172R airplanes with serial numbers 17280001 
through 17280475 and 17280506, certificated in any category.

    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 (g) 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 within the next 25 hours time-in-service 
(TIS), after the effective date of this AD, unless already 
accomplished.
    To prevent loss of aileron and elevator control, which could 
result in loss of directional control of the airplane, accomplish 
the following:

    Note 2: Some airplane serial numbers may appear in all of the 
actions required by this AD and some airplane serial numbers may 
only appear in one action required by this AD. It is recommended to 
look at each group of serial numbers closely.

    (a) For Cessna Model 172R airplanes with serial numbers 17280001 
through 17280326, 17280328, 17280330 through 17280335, 17280337, 
17280339 through 17280342, 17280345, 17280346, 17280350, 17280353 
through 17280359, 17280361 through 17280364, 17280366, 17280367, 
17280371, 17280377, 17280380 through 17280383, 17280385, 
17280387,17280390, 17280391, 17280393, 17280397, 17280423, 17280432 
through 17280434, 17280440, 17280441, 17280457, 17280460, 17280461, 
17280465 through 17280470, and 17280474:
    (1) Inspect the aileron control cables in the center console 
area for incorrect routing over the cable guard, fraying or damage 
in accordance with the Accomplishment Instructions in Cessna Service 
Bulletin (SB) No. SB98-27-02, dated May 11, 1998.
    (2) Prior to further flight, re-route any aileron control cable 
found out of place, and replace any aileron control cable found 
frayed or damaged in accordance with the Accomplishment Instructions 
in Cessna SB No. SB98-27-02, dated May 11, 1998.
    (b) For Cessna Model 172R airplanes with serial numbers 
17280002, 17280004, 17280021, 17280024, 17280069 through 17280073, 
17280075, 17280077, 17280079 through 17280081, 17280083, 17280086, 
17280092, 17280095, 17280109, 17280114, 17280120 through 17280124, 
17280127, 17280133, 17280136, 17280147, 17280148, 17280150, 
17280159, 17280163, 17280171, 17280207, 17280214, 17280224, 
17280234, 17280239, 17280242, 17280248, 17280251, 17280253, 
17280257, 17280262, 17280275, 17280281, 17280282, 17280285, 
17280287, 17280292, 17280301, 17280305, 17280329, 17280337, 
17280338, 17280341, 17280342, 17280343, 17280345, 17280351, 
17280354, 17280356, 17280357, 17280359, 17280365, 17280429, and 
17280506 that were not factory equipped with an autopilot:
    (1) Inspect the right-hand wing for an incorrectly routed 
aileron control cable in accordance with the Accomplishment 
Instructions in Cessna SB No. SB98-27-05, dated June 1, 1998.
    (2) If the aileron control cable is mis-routed, prior to further 
flight, correct the routing, and if there is fraying or damage to 
the aileron control cable, prior to further flight, replace the 
control cable in accordance with the Accomplishment Instructions in 
Cessna SB No. SB98-27-05, dated June 1, 1998.
    (c) For Cessna Model 172R airplanes with serial numbers 17280001 
through 17280349:
    (1) Inspect for a loose or incorrectly installed center lock 
clamp on the forward aileron control cable drum in accordance with 
the Accomplishment Instructions in Cessna SB No. SB98-27-03, dated 
June 1, 1998.
    (2) If the center lock clamp is loose or is installed 
incorrectly, prior to further flight, correct and adjust 
appropriately in accordance with the Accomplishment Instructions in 
Cessna SB No. SB98-27-03, dated June 1, 1998.
    (d) For Cessna Model 172R airplanes with serial numbers 17280001 
through 17280475:

[[Page 34803]]

    (1) Inspect for loose or missing elevator trim actuator mounting 
screws, loose rudder circuit pulleys, missing rudder cable guard 
pins, incorrect elevator trim cable routing, aileron control cable 
clearance, and flight control cable tension or rigging outside the 
design specifications in accordance with the Accomplishment 
Instructions in Cessna SB No. SB98-27-06, dated June 15, 1998.
    (2) If any condition in paragraph (d)(1) of this AD is found, 
prior to further flight, repair, replace, or correct in accordance 
with the Accomplishment Instructions in Cessna SB No. SB98-27-06, 
dated June 15, 1998.
    (e) If any of the conditions noted above in paragraphs (a), (b), 
(c), or (d) of this AD are found within 10 days of the inspection, 
report the condition found, date of inspection, and the serial 
number of the airplane to Doyle M. King, Jr., Manager, Wichita 
Manufacturing Inspection, Office, 1801 Airport Road, Rm. 101, Mid-
Continent Airport, Wichita, Kansas, 67209. Reporting requirements 
have been approved by the Office of Management and Budget and 
assigned OMB control number 2120-0056.
    (f) Special flight permits may be issued in accordance with 
sections Secs. 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.
    (g) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, Wichita Aircraft Certification Office 
(ACO), 1801 Airport Road, Rm. 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.

    (h) The inspections, repairs, replacements, adjustments, and 
corrections required by this AD shall be done in accordance with 
Cessna Service Bulletins No. SB98-27-02, dated May 11, 1998, No. 
SB98-27-03, dated June 1, 1998, No. SB98-27-05, dated June 1, 1998, 
and No. SB98-27-06, dated June 15, 1998. 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. 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.
    (i) This amendment becomes effective on August 18, 1998.

    Issued in Kansas City, Missouri, on June 19, 1998.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-17020 Filed 6-25-98; 8:45 am]
BILLING CODE 4910-13-U