[Federal Register Volume 63, Number 116 (Wednesday, June 17, 1998)]
[Rules and Regulations]
[Pages 32973-32975]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16015]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-59-AD; Amendment 39-10598; AD 98-13-10]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Model 182S 
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 all Cessna Aircraft Company (Cessna) Model 182S airplanes. 
This AD requires repetitively inspecting all engine exhaust muffler end 
plates (four

[[Page 32974]]

total) for cracks and replacing any muffler where an end plate is found 
cracked. The AD also requires fabricating and installing a placard that 
specifies immediately inspecting all engine exhaust muffler end plates 
any time the engine backfires upon start-up. This AD is the result of 
incidents where cracks were found in an engine exhaust muffler end 
plate on several of the affected airplanes. These cracks were caused by 
high stresses imposed on the attachment of the exhaust at the area of 
the firewall. The actions specified by this AD are intended to detect 
and correct damage to the engine exhaust mufflers caused by such high 
stress and cracking, which could result in exhaust gases entering the 
airplane cabin with consequent crew and passenger injury.

DATES: Effective July 8, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before August 21, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket 98-CE-59-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.
    Information that relates to this AD may be examined at the Federal 
Aviation Administration (FAA), Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 98-CE-59-AD, Room 1558, 601 E. 
12th Street, Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr. Paul Pendleton, Aerospace 
Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4143; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA has received reports of incidents where cracks were found 
in an engine exhaust muffler end plate on several Cessna Model 182S 
airplanes. These cracks were caused by high stresses imposed on the 
attachment of the exhaust at the area of the firewall.
    The design of the Cessna Model 182S airplanes is such that, during 
start-up, the engine could backfire and high stresses could then be 
imposed on the attachment of the exhaust at the area of the firewall. 
These high stresses cause cracks in the engine exhaust muffler end 
plates.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that AD action should be taken to detect and correct damage 
to the engine exhaust mufflers caused by such high stress and cracking, 
which could result in exhaust gases entering the airplane cabin with 
consequent crew and passenger injury.

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 182S airplanes of the same type 
design, the FAA is issuing an AD. This AD requires repetitively 
inspecting all engine exhaust muffler end plates (four total) for 
cracks and replacing any muffler where an end plate is found cracked. 
The AD also requires fabricating and installing a placard that 
specifies immediately inspecting all engine exhaust muffler end plates 
any time the engine backfires upon start-up.

Compliance Time of This AD

    The compliance time of the placard requirements of this AD is 
presented in calendar time instead of hours time-in-service. The chance 
of the engine backfiring upon start-up is the same for airplanes with 
25 hours TIS as it is for airplanes with 100 hours TIS. Therefore, to 
assure that the engine exhaust muffler end plates are inspected any 
time the engine backfires upon start-up on all of the affected 
airplanes, a compliance based upon calendar time is utilized.

Determination of the Effective Date of the AD

    Since a situation exists (possible engine exhaust system damage and 
exhaust gases entering the airplane cabin with consequent crew and 
passenger injury) 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.
    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-59-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, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the

[[Page 32975]]

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:

98-13-10  Cessna Aircraft Company: Amendment 39-10598; Docket No. 
98-CE-59-AD.

    Applicability: Model 182S airplanes, all serial numbers, 
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 (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 damage to the engine exhaust mufflers 
caused by high stresses imposed on the attachment of the exhaust at 
the area of the firewall and cracking, which could result in exhaust 
gases entering the airplane cabin with consequent crew and passenger 
injury, accomplish the following:
    (a) Within the next 5 days after the effective date of this AD, 
accomplish the following:
    (1) Fabricate a placard that specifies immediately inspecting 
all engine exhaust muffler end plates when the engine backfires upon 
start-up, and install this placard on the instrument panel within 
the pilot's clear view. The placard should utilize letters of at 
least 0.10-inch in height and contain the following words:
    ``If the engine backfires upon start-up, prior to further 
flight, inspect and replace (as necessary) all engine exhaust 
muffler end plates in accordance with AD 98-13-10''
    (2) Insert a copy of this AD into the Limitations Section of the 
airplane flight manual (AFM).
    (b) Within the next 25 hours time-in-service (TIS) after the 
effective date of this AD and thereafter at intervals not to exceed 
25 hours TIS after the previous inspection (including any inspection 
accomplished after an engine backfire), inspect all engine exhaust 
muffler end plates (four total) for cracks on the forward (upstream) 
or aft (downstream) end of each muffler can. Prior to further 
flight, replace any engine exhaust muffler where an end plate is 
found cracked. The replacement does not eliminate the repetitive 
inspection requirement of this AD.

    Note 2: Cessna Service Bulletin SB98-78-02, Issued: June 6, 
1998, depicts the area to be inspected. The actions of this service 
bulletin are different from those required by this AD. This AD takes 
precedence over the actions specified in the service bulletin, and 
accomplishment of the service bulletin is not considered an 
alternative method of compliance to the actions of this AD. Copies 
of this service bulletin may be obtained from the Cessna Aircraft 
Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277.

    (c) Fabricating and installing the placard and inserting this AD 
into the Limitations Section of the AFM, as required by paragraph 
(a) of this AD, may be performed by the owner/operator holding at 
least a private pilot certificate as authorized by section 43.7 of 
the Federal Aviation Regulations (14 CFR 43.7), and must be entered 
into the aircraft records showing compliance with this AD in 
accordance with section 43.9 of the Federal Aviation Regulations (14 
CFR 43.9).
    (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 time 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) Information related to this AD may be examined at the FAA, 
Central Region, Office of the Regional Counsel, Room 1558, 601 E. 
12th Street, Kansas City, Missouri.
    (g) This amendment becomes effective on July 8, 1998.

    Issued in Kansas City, Missouri, on June 10, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-16015 Filed 6-16-98; 8:45 am]
BILLING CODE 4910-13-U