[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,
[[Page 30502]]
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
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Rockwell/Aero Commander/Meyers............ 200 Series.
Twin Commander............................ Models 500A and 685.
Beech..................................... 33, 35, 36, and 55 Series.
Piper..................................... PA46 Series.
[[Page 30503]]
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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