[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
