[Federal Register Volume 61, Number 117 (Monday, June 17, 1996)]
[Rules and Regulations]
[Pages 30501-30505]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14631]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-CE-54-AD; Amendment 39-9665; AD 96-12- 22]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Engine Oil 
Filter Adapter Assemblies Installed on Aircraft

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) engine oil filter adapter 
assemblies installed on aircraft. This action requires inspecting the 
oil filter and adapter assembly (or torque putty,

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if installed) for oil leakage and proper installation of the adapter 
retaining nut and fretting of associated threads (security), and 
replacing any oil filter adapter assembly with security problems; 
applying torque putty between the engine filter adapter assembly, nut, 
and oil pump housing (unless already equipped with torque putty); and 
repetitively inspecting the torque putty for misalignment, evidence of 
oil leakage, or torque putty cracks, and reinspecting the oil filter 
and adapter assembly threads if misalignment, evidence of oil leakage, 
or torque putty cracks are found. Reports of loose or separated engine 
oil filter adapters on several airplanes prompted this action. The 
actions specified by this AD are intended to prevent loss of engine oil 
caused by loose or separated oil filter adapters, which, if not 
detected and corrected, could result in engine stoppage while in flight 
and loss of control of the airplane.

EFFECTIVE DATE: July 31, 1996.

ADDRESSES: Information that applies to this AD may be examined at the 
Federal Aviation Administration (FAA), Central Region, Office of the 
Assistant Chief Counsel, Attention: Rules Docket 93-CE-54-AD, Room 
1558, 601 E. 12th Street, Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr. 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 AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to airplanes of any type 
design that utilize any Cessna engine oil filter adapter was published 
in the Federal Register on January 22, 1996 (61 FR 1534). The action 
proposed to require (1) inspecting the oil filter and adapter assembly 
(or torque putty, if installed) for oil leakage and proper installation 
of the adapter retaining nut and fretting of associated threads 
(security), and replacing any oil filter adapter assembly with security 
problems; (2) applying torque putty between the engine filter adapter 
assembly, nut, and oil pump housing (unless already equipped with 
torque putty); and (3) repetitively inspecting the torque putty for 
misalignment, evidence of oil leakage, or torque putty cracks, and 
reinspecting the oil filter and adapter assembly threads if 
misalignment, evidence of oil leakage, or torque putty cracks are 
found. This proposal revised a previous proposal that was published in 
the Federal Register on September 19, 1994 (59 FR 47821).
    Reports of loose or separated engine oil filter adapters on several 
airplanes prompted the proposal.
    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.
    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 70,000 airplanes in the U.S. registry 
incorporate one of the affected engine oil filter adapter assemblies 
and will, therefore, be affected by this AD; that it will take 
approximately 1 workhour per airplane to accomplish the initial 
inspection and torque putty application; and that the average labor 
rate is approximately $60 an hour. Based on these figures, the total 
cost impact of this AD on U.S. operators is estimated to be $4,200,000. 
This figure is based on the assumption that no operator has 
accomplished the initial inspection, and does not take into account the 
cost for the repetitive inspections. Since the pilot is allowed to 
repetitively inspect the torque putty, the only cost of the repetitive 
inspections is the time incurred by the pilot and the cost of an 
inspection required if misalignment, evidence of oil leakage, or torque 
putty cracks are found. The FAA has no way of determining how many 
repetitive inspections each individual operator will incur over the 
life of the airplane.

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.
    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, 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 USC 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:

96-12-22  Cessna Aircraft Company: Amendment 39-9665; Docket No. 93-
CE-54-AD.

    Applicability: Cessna Engine Oil Filter Adapters Assemblies, 
part numbers 0450404-(all dash numbers), 0556004-(all dash numbers), 
0556010-(all dash numbers), 0756023-(all dash numbers), 0756024-(all 
dash numbers), 1250403-(all dash numbers), 1250417-(all dash 
numbers), 1250418-(all dash numbers), 1250921-(all dash numbers), 
and 1250922-(all dash numbers), installed on, but not limited to, 
the following:
    (1) Cessna Models 100, 200, 300, and 400 Series airplanes (all 
serial numbers), certificated in any category, that are equipped 
with at least one Teledyne Continental Motors (TCM) engine.
    (2) Airplanes that have an affected full flow engine oil adapter 
installed by field approval, including, but not limited to, the 
following model or series airplanes, certificated in any category:

------------------------------------------------------------------------
               Manufacturer                         Series/models       
------------------------------------------------------------------------
Rockwell/Aero Commander/Meyers............  200 Series.                 
Twin Commander............................  Models 500A and 685.        
Beech.....................................  33, 35, 36, and 55 Series.  
Piper.....................................  PA46 Series.                

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Navion....................................  Rangemaster 17 Series.      
Wren......................................  Model 460.                  
Bellanca..................................  260 and 300 Series.         
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    (3) Airplanes equipped with any of the following Teledyne 
Continental Motors model or model series engines:
O-200
TSIO-470
TSIO-520
TSIO-550
O-470
O-520
GTSIO-520
IO-470
IO-520
IO-550

    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.
    Note 2: This AD does not apply to engine oil filter adapter 
assemblies manufactured by Teledyne Continental Motors (See Figure 1 
of this AD). Compliance: Required initially as specified in both of 
the following, and thereafter as indicated in the body of this AD:

    1. Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD or when the engine oil filter is removed, 
whichever occurs first; and
    2. Every time the engine oil filter is removed.
    To prevent loss of engine oil caused by loose or separated oil 
filter adapters, which could result in engine stoppage while in 
flight and loss of control of the airplane, accomplish the 
following:
    (a) For airplanes with engine oil filter adapter assemblies that 
do not have torque putty between the engine filter adapter assembly, 
nut, and oil pump housing, accomplish the following:
    (1) Inspect the adapter locking nut installation for evidence of 
oil leakage.
    (2) Check the torque of the adapter nut installation and ensure 
that the torque value is within the limits of 50 through 60 foot 
pounds.
    (3) If evidence of oil leakage is found or the torque is not 
within the 50 through 60-foot pound limit, prior to further flight, 
remove the adapter and filter assembly, and:
    (i) Inspect the threads of the adapter assembly and engine for 
signs of damaged or cracked threads; and
    (ii) Replace any adapter assembly and engine oil pump housing 
(if necessary) that have evidence of thread damage or cracks.
    (4) Apply torque putty between the engine filter adapter 
assembly, nut, and oil pump housing as specified in Figure 1 of this 
AD.
    (5) Reassemble the engine oil filter assembly.

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[GRAPHIC] [TIFF OMITTED] TR17JN96.015


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    (b) For airplanes with torque putty between the engine filter 
adapter assembly, nut, and oil pump housing, inspect the torque 
putty for misalignment, evidence of oil leakage, or cracks.
    (1) If any misalignment, evidence of oil leakage, or torque 
putty cracks are found, prior to further flight, accomplish the 
requirements specified in paragraph (a) of this AD, including all 
subparagraphs.
    (2) If no misalignment, evidence of oil leakage, or torque putty 
cracks are found, reinspect at intervals not to exceed 100 hours TIS 
until the engine oil filter is removed.
    (c) Replacing the engine oil filter adapter assembly does not 
eliminate the repetitive inspection requirement of this AD.
    (d) The repetitive inspections of the torque putty as required 
by 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 43.11 of the Federal Aviation Regulations (14 CFR 
43.11).
    (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 
initial or repetitive 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

    (g) Information related to this AD may be examined at the FAA, 
Central Region, Office of the Assistant Chief Counsel, Room 1558, 
601 E. 12th Street, Kansas City, Missouri 64106.
    (h) This amendment (39-9665) becomes effective on July 31, 1996.

    Issued in Kansas City, Missouri, on June 3, 1996.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-14631 Filed 6-14-96; 8:45 am]
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