AD 2000-06-01

[Federal Register Volume 65, Number 56 (Wednesday, March 22, 2000)]
[Rules and Regulations]
[Pages 15232-15234]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-6615]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-114-AD; Amendment 39-11641; AD 2000-06-01]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company 150, 152, 172, 
177, 180, 182, 185, 188, 206, 207, 210, and 337 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Cessna Aircraft Company (Cessna) 150, 152, 172, 177, 180, 
182, 185, 188, 206, 207, 210, and 337 series airplanes. This AD 
requires measuring the visible length of standpipe (tube) in the top 
assembly of the fuel strainer assembly for the correct length, and 
replacing any fuel strainer assembly that does not have the correct 
length of standpipe. This AD is the result of reports that the fuel 
strainer assemblies on the affected airplanes were manufactured with 
the fuel standpipes incorrectly installed in the assembly housing top. 
The actions specified by this AD are intended to prevent foreign 
material from entering the fuel system and engine, which could result 
in loss of engine power or complete engine stoppage during flight.

DATES: Effective May 5, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 5, 2000.

ADDRESSES: 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. 97-CE-114-AD, Room 506, 901 Locust, 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: Paul O. Pendleton, Aerospace Engineer, 
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 
100, 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 Cessna 150, 152, 172, 
177, 180, 182, 185, 188, 206, 207, 210, and 337 series airplanes was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on July 22, 1998 (63 FR 39244). The NPRM proposed to require 
measuring the fuel strainer assembly standpipe, and replacing any fuel 
strainer assembly that does not have a standpipe of the correct 
measurement. Accomplishment of the proposed action as specified in the 
NPRM would be required in accordance with Cessna Service Bulletins 
SEB97-9, dated November 17, 1997, and MEB97-12, dated November 17, 
1997.
    The NPRM was the result of reports that the fuel strainer 
assemblies on the affected airplanes were manufactured with the fuel 
standpipes incorrectly installed in the assembly housing top.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received from six different entities.

Comment Disposition

    All six commenters request that the FAA include a provision for the 
owners/operators of the affected airplanes to check the logbook to 
determine whether one of the affected fuel strainer assemblies is 
installed. This would reduce the impact of the AD by not requiring 
operators who do not have the affected fuel strainer assemblies 
installed to have their airplanes unnecessarily inspected.
    The FAA concurs. Cessna part number (P/N) 0756005-2 top assemblies, 
Cessna P/N 0756005-8 fuel strainer assemblies, or Cessna P/N 0756005-9 
fuel strainer assemblies, that were shipped between December 12, 1996, 
and September 5, 1997, may have been manufactured with an internal tube 
installed to a depth less than specified. These parts may become loose 
and dislodge from the strainer top assembly. If the owner/operator can 
make the determination by checking the logbooks that one of these parts 
is not installed or was installed prior to December 12, 1996, the 
measurement and possible replacement requirements of paragraphs (a) and 
(b) of this AD would not apply and the owner/operator must make an 
entry into the aircraft records showing compliance with this portion of 
the AD in accordance with section 43.9 of the Federal Aviation 
Regulations (14 CFR 43.9). This final rule has been changed to reflect 
this provision.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above including the comments discussed, the FAA has 
determined that air safety and the public interest require the adoption 
of the rule as proposed except for the addition of the provision to 
check the logbooks and minor editorial corrections. The FAA has 
determined that this addition and the 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 50,000 airplanes in the U.S. registry will 
be affected by this AD.
    The measurement required by this AD is estimated to take 1 workhour 
per airplane with the average labor rate at approximately $60 an hour. 
The total cost impact to accomplish the inspection will be $3,000,000 
for the U.S. fleet, or $60 per airplane.
    The replacement of the fuel strainer assembly is estimated to take 
2

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workhours per airplane with an average labor rate of approximately $60 
per hour. Approximately 300 of the affected parts are thought to have 
been manufactured. The cost of parts is approximately $180 per 
airplane. Therefore, based on these figures, the total cost impact to 
accomplish the replacement, if applicable, on U.S. operators is 
estimated to be $90,000, or $300 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.

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:

2000-06-01  Cessna Aircraft Company: Amendment 39-11641; Docket No. 
97-CE-114-AD.

    Applicability: All serial numbers of the following airplane 
models, certificated in any category, including those manufactured 
in France that have a capital ``F'' or ``FR'' prefix on the model 
number: Models 150F, 150G, 150H, 150J, 150K, 150L, 150M, A150K, 
A150L, A150M, A-150L, A-A150L, F150F, F150G, F150H, F150J, F150K, 
F150L, F150M, FA150K, FA150L, FA150M, FRA150L, FRA150M, 152, A152, 
F152, FA152, 172F, 172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 
172Q, R172E (T41), R172F (T41), R172G (T41), R172H (T41), R172J, 
R172K, 172RG, F172F, F172G, F172H, F172K, F172L, F172M, F172N, 
F172P, FR172E, FR172F, FR172G, FR172H, FR172J, FR172K, 177, 177A, 
177B, 177RG, F177RG, 180H, 180J, 180K, 182H, 182J, 182K, 182L, 182M, 
182N, 182P, 182Q, 182R/T182, 182R, R182, R182/TR182, A182J, A182K, 
A182L, A182N, F182P, F182Q, FR182, 185D, 185E, A185E, A185F, 188, 
A188, 188A, A188A, 188B, A188B, T188C, A-A188B, U206, U206A, TU206A, 
U206B/TU206B, U206C/TU206C, U206D/TU206D, U206E/TU206E, U206F/
TU206F, U206G/TU206G, P206, P206A, TP206A, P206B/TP206B, P206C/
TP206C, P206D/TP206D, P206E/TP206E, 207/T207, 207A/T207A, 210E, 
210F, 210G, 210H, 210J, 210K/T210K, 210L/T210L, 210M/T210M, 210N/
T210N, T210F, T210G, T210H, T210J, P210N, 337, 337A, 337B/T337B, 
M337B, 337C/T337C, 337D/T337D, 337E/T337E, 337F, T337F, 337G, 337H/
T337H, T337H-SP, T337G, P337H, F337E/FT337E, F337F/FT337F, F337G, 
F337H, FTB337, FT337GP, and FT337HP.

    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 (f) 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.
    To prevent foreign material from entering the fuel system and 
engine, which could result in loss of engine power or complete 
engine stoppage during flight, accomplish the following:

    Note 2:
    This AD allows the aircraft owner or pilot to check the 
maintenance records to determine whether a Cessna part number (P/N) 
0756005-2 top assembly, Cessna P/N 0756005-8 fuel strainer assembly, 
or a Cessna P/N 0756005-9 fuel strainer assembly was installed after 
December 12, 1996. Those parts that were shipped between December 
12, 1996, and September 5, 1997, may have been manufactured with an 
internal tube installed to a depth less than specified and may 
become loose and dislodge from the strainer top assembly. See 
paragraph (c) of this AD for authorization.

    (a) Within the next 12 calendar months after the effective date 
of this AD, unless already accomplished, measure the standpipe in 
the fuel strainer assembly (tube in the filter strainer top 
assembly) for a visible maximum length of 1.68 inches, in accordance 
with the ACCOMPLISHMENT INSTRUCTIONS section and Detail A in Cessna 
Single Engine Service Bulletin (SB) No. SEB97-9, dated November 17, 
1997; or Cessna Multi-engine SB No. MEB97-12, dated November 17, 
1997, whichever is applicable.
    (b) If the standpipe does not measure a maximum length of 1.68 
inches, prior to further flight, replace the filter strainer top 
assembly in accordance with the ACCOMPLISHMENT INSTRUCTIONS section 
in Cessna Single Engine SB No. SEB97-9, dated November 17, 1997; or 
Cessna Multi-engine SB No. MEB97-12, dated November 17, 1997, 
whichever is applicable.
    (c) 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) may check the maintenance records to 
determine whether a Cessna part number (P/N) 0756005-2 top assembly, 
Cessna P/N 0756005-8 fuel strainer assembly, or a Cessna P/N 
0756005-9 fuel strainer assembly was installed after December 12, 
1996. Those parts that were shipped between December 12, 1996, and 
September 5, 1997, may have been manufactured with an internal tube 
installed to a depth less than specified and may become loose and 
dislodge from the strainer top assembly. If, by checking the 
maintenance records, the owner/operator can make an absolute 
determination that one of these parts is not installed or was 
installed prior to December 12, 1996, the requirements of paragraphs 
(a) and (b) of this AD do not apply. The owner/operator must make an 
entry into the aircraft records showing compliance with this portion 
of the AD in accordance with section 43.9 of the Federal Aviation 
Regulations (14 CFR 43.9).
    (d) As of the effective date of this AD, no person may install, 
on any of the affected Cessna airplanes, a fuel filter assembly 
where the maximum length of the standpipe does not measure 1.68 
inches.
    (e) 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.
    (f) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, FAA, Wichita Aircraft Certification Office 
(ACO), 1801 Airport Road, Room 100, 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.
    (g) The measurement and replacement required by this AD shall be 
done in

[[Page 15234]]

accordance with Cessna Single Engine Service Bulletin (SB) No. 
SEB97-9, dated November 17, 1997, or Cessna Multi-engine SB No. 
MEB97-12, dated November 17, 1997. 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 506, 901 Locust, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North Capitol Street, NW, 
suite 700, Washington, DC.
    (h) This amendment becomes effective on May 5, 2000.


    Issued in Kansas City, Missouri, on March 10, 2000.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 00-6615 Filed 3-21-00; 8:45 am]
BILLING CODE 4910-13-P