Category: navion, Continental, oil, filter
Applicability: Airplanes that have an affected full flow engine oil adapter installed by field approval, including, but not limited to Navion Rangemaster 17 Series. Any aircraft with the following Cessna Engine Oil Filter Adapters:
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)
1250922-(all dash numbers)
Airplanes equipped with any of the
following Teledyne Continental Motors model or model series engines:
0-200
0-470, I0-470, TSI0-470
0-520, I0-520, TSI0-520, GTSIO-520
I0-550, TSI0-550
This AD applies to each airplane 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.
This AD does not apply to engine oil filter adapter assemblies manufactured by Teledyne Continental Motors.
Supersedes: n/a
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.
Procedure: 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.
(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: Information concerning the existence of approved alternative methods of compliance with this AD, if ny, 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 becomes effective on July 31, 1996.
Notes: For more information, contact:
Mr. Paul 0. Pendleton, Aerospace Engineer, FAA, Wichita
Aircraft Certification Office
1801 Airport Road, Room 100
Wichita, Kansas 67209
telephone (316) 946-4143; facsimile (316) 946-4407
AD-96-12-22