[Federal Register Volume 65, Number 18 (Thursday, January 27, 2000)]
[Rules and Regulations]
[Pages 4351-4352]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-1771]



[[Page 4351]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-125-AD; Amendment 39-11532; AD 2000-02-14]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Model 182S 
Airplanes

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Final rule.

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SUMMARY:  This amendment supersedes Airworthiness Directive (AD) 98-13-
10, which currently requires repetitively inspecting all engine exhaust 
muffler end plates (four total) for cracks on all Cessna Aircraft 
Company (Cessna) Model 182S airplanes, and replacing any muffler where 
an end plate is found cracked. AD 98-13-10 also requires fabricating 
and installing a placard that specifies immediate inspection of all 
engine exhaust muffler end plates any time the engine backfires upon 
start-up. This AD is the result of Cessna developing an improved design 
exhaust system for the Model 182S airplanes. This AD retains the 
actions of AD 98-13-10 on all affected airplanes, and requires 
replacing the exhaust system with an improved design exhaust system 
within a certain period of time, as terminating action for those 
requirements retained from AD 98-13-10. This AD also limits the 
effectivity to exclude those airplanes manufactured with the improved 
design exhaust system. The actions specified by this AD are intended to 
detect and correct damage to the engine exhaust mufflers caused by 
cracking and the high stresses imposed on the attachment of the exhaust 
system at the area the firewall, which could result in exhaust gases 
entering the airplane cabin with consequent crew and passenger injury.

DATES:  Effective March 17, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 17, 2000.

ADDRESSES:  Service information that applies to this AD may be obtained 
from the Cessna Aircraft Company, Product Support, P.O. Box 7706, 
Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-
9006. 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-125-AD, 901 Locust, Room 506, 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. 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:  

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to all Cessna Model 182S 
airplanes was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on April 26, 1999 (64 FR 20221). The NPRM proposed to 
supersede AD 98-13-10, Amendment 39-10598. AD 98-13-10 currently 
requires repetitively inspecting all engine exhaust muffler end plates 
(four total) for cracks; replacing any muffler where an end plate is 
found cracked; and fabricating and installing a placard that specifies 
an inspection of all engine exhaust muffler end plates any time the 
engine backfires upon start-up. The NPRM proposed to retain the actions 
of AD 98-13-10 on all affected airplanes, and would require replacing 
the exhaust system with an improved design exhaust system within a 
certain period of time, as terminating action for the actions retained 
from AD 98-13-10. The NPRM also proposed to limit the effectivity to 
exclude those airplanes manufactured with the improved design exhaust 
system. Accomplishment of the proposed replacement as specified in the 
NPRM would be required in accordance with Cessna Service Bulletin SB98-
78-03, dated December 14, 1998.
    The NPRM was the result of Cessna developing an improved design 
exhaust system for the Model 182S airplanes.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 150 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 1 workhour per 
airplane to accomplish the inspection, and that the average labor rate 
is approximately $60 an hour. Based on these figures, the total cost 
impact of the inspection on U.S. operators is estimated to be $9,000, 
or $60 per airplane. These figures only take into account the cost of 
the initial inspection and do not take into account the costs of any 
repetitive inspections or replacements needed if cracks were found.
    The inspection cost of this AD is the same as that presented in AD 
98-13-10. Therefore, this AD imposes no inspection cost impact on U.S. 
operators of the affected airplanes over that already required in AD 
98-13-10.
    The FAA estimates that it will take approximately 4 workhours per 
airplane to accomplish the replacement, and that the average labor rate 
is approximately $60 an hour. Parts cost approximately $463 per muffler 
assembly (2 required) per airplane. Based on these figures, the total 
cost impact of the replacement on U.S. operators is estimated to be 
$174,900, or $1,166 per airplane.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act.
    A copy of the final evaluation prepared for this action is 
contained in the Rules Docket. A copy of it may be obtained by 
contacting the Rules Docket at the location provided under the caption 
ADDRESSES.

[[Page 4352]]

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 removing Airworthiness Directive 
(AD) 98-13-10, Amendment 39-10598, and by adding a new AD to read as 
follows:

2000-02-14  Cessna Aircraft Company: Amendment 39-11532; Docket No. 
98-CE-125-AD; Supersedes AD 98-13-10, Amendment 39-10598.

    Applicability: Model 182S airplanes, serial numbers 18280001 
through 18280286, 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 as indicated in the body of this AD, unless 
already accomplished.
    To detect and correct damage to the engine exhaust mufflers 
caused by cracking and the high stresses imposed on the attachment 
of the exhaust system at the area the firewall, which could result 
in exhaust gases entering the airplane cabin with consequent crew 
and passenger injury, accomplish the following:
    (a) Within 5 days after the effective date of this AD, unless 
already accomplished (compliance with AD 98-13-10), 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. ''

    (2) Insert a copy of this AD into the Limitations Section of the 
airplane flight manual (AFM).
    (b) Within 25 hours time-in-service (TIS) after the effective 
date of this AD, unless already accomplished (compliance with AD 98-
13-10), and thereafter at intervals not to exceed 25 hours TIS after 
each inspection (including any inspection accomplished after an 
engine backfire) until the replacements required by paragraphs 
(b)(1) and (d) of this AD are accomplished, inspect all engine 
exhaust muffler end plates (four total) for cracks on the forward 
(upstream) or aft (downstream) end of each muffler can.
    (1) Prior to further flight, replace any engine exhaust muffler 
where an end plate is found cracked with one of improved design, 
part number (P/N) 1254017-19 or P/N 9954200-9 (or FAA-approved 
equivalent part number). Accomplish these replacements in accordance 
with Cessna Service Bulletin SB98-78-03, dated December 14, 1998.
    (2) This replacement terminates the repetitive inspection 
required by this AD for that particular engine exhaust muffler. The 
repetitive inspections would still be required for any other engine 
exhaust muffler not replaced with the improved design parts.
    (3) The placard requirements of this AD are still required until 
all engine exhaust system mufflers are replaced with the improved 
design parts.

    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 this service bulletin. 
Accomplishment of Cessna Service Bulletin SB98-78-02, Issued: June 
6, 1998, is not considered an alternative method of compliance to 
the actions of this AD.

    (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) Within 12 calendar months after the effective date of this 
AD, replace the engine exhaust mufflers with ones of improved 
design, part number (P/N) 1254017-19 or P/N 9954200-9 (or FAA-
approved equivalent part number). Accomplish these replacements in 
accordance with Cessna Service Bulletin SB98-78-03, dated December 
14, 1998.
    (1) These replacements terminate the repetitive inspection and 
placard requirements of this AD, as specified in paragraphs (a) and 
(b), including all subparagraphs, of this AD.
    (2) The replacements may be accomplished prior to 12 calendar 
months after the effective date of this AD, as terminating action 
for the repetitive inspection and placard requirements of this AD.
    (e) As of the effective date of this AD, no person may install, 
on any affected airplane, an engine exhaust muffler that is not of 
improved design, P/N 1254017-19 or P/N 9954200-9 (or FAA-approved 
equivalent part number).
    (f) 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.
    (g) An alternative method of compliance or adjustment of the 
initial or repetitive 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.
    (1) The request shall be forwarded through an appropriate FAA 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Wichita ACO.
    (2) Alternative methods of compliance approved in accordance 
with AD 98-13-10 are not considered approved as alternative methods 
of compliance for this AD.

    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 replacements required by this AD shall be done in 
accordance with Cessna Service Bulletin SB98-78-03, dated December 
14, 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, Product Support, P.O. Box 7706, Wichita, Kansas 67277. 
Copies may be inspected at the FAA, Central Region, Office of the 
Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North Capitol Street, NW, 
suite 700, Washington, DC.
    (i) This amendment supersedes AD 98-13-10, Amendment 39-10598.
    (j) This amendment becomes effective on March 17, 2000.

    Issued in Kansas City, Missouri, on January 18, 2000.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 00-1771 Filed 1-26-00; 8:45 am]
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