[Federal Register Volume 59, Number 180 (Monday, September 19, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-23080]
[[Page Unknown]]
[Federal Register: September 19, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-CE-54-AD]
Airworthiness Directives; Cessna Aircraft Company Engine Oil
Filter Adapters, Part Numbers 0450404-1, 0450404-3, 0556004-1, 0556010-
1, 1250403-6, 1250922-1, and 1250922-2, Installed on Aircraft
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to Cessna Aircraft Company (Cessna) engine oil
filter adapters, part numbers 0450404-1, 0450404-3, 0556004-1, 0556010-
1, 1250403-6, 1250922-1, and 1250922-2, installed on aircraft. The
proposed action would require applying torque paint between the engine
filter adapter assembly, nut, and oil pump housing; inspecting the oil
filter and adapter assembly for oil leakage and proper installation of
the adapter retaining nut and fretting of associated threads
(security), and replacing any oil filter and adapter assembly with oil
leakage or security problems; and repetitively inspecting the torque
paint for cracks or misalignment, and reinspecting the oil filter and
adapter assembly if torque paint cracks or misalignment is found.
Reports of loose or separated engine oil filter adapters on several
airplanes prompted the proposed action. The actions specified by the
proposed AD are intended 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.
DATES: Comments must be received on or before November 28, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 93-CE-54-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106. Comments may be inspected at
this location between 8 a.m. and 4 p.m., Monday through Friday,
holidays excepted.
Service information that applies to the proposed AD may be obtained
from the Cessna Aircraft Company, Customer Services, P.O. Box 1521,
Wichita, Kansas 67201. This information also may be examined at the
Rules Docket at the address above.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 93-CE-54-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 93-CE-54-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has received 10 reports of loose or separated engine oil
filter adapters on in-service airplanes. The affected adapters are
Cessna engine oil filter adapters, part numbers 0450404-1, 0450404-3,
0556004-1, 0556010-1, 1250403-6, 1250922-1, and 1250922-2. Three of the
incidents resulted in an airplane accident, one serious. These engine
oil filter adapters are installed on, but not limited to the following:
(1) The following Cessna model and series airplanes with an
affected adapter installed at manufacture:
------------------------------------------------------------------------
Model or series Serial Nos.
------------------------------------------------------------------------
150................. 17001 through 17999, 59001 through 59018, and
15059019 through 15079405.
A150................ A1500001 through A1500734.
F150................ F150-0001 through F150-0529 and F15000530 through
F15001428.
FA150............... FA1500001 through FA1500120.
FRA150.............. FRA1500121 through FRA1500336.
172................. 28000 through 47746 and 17247747 through 17256512.
F172................ F172-0001 through F172-0654 and F17200655 through
F17200804.
FR172............... FR172-0001 through FR17200559 and FR17200561.
180................. 30000 through 50911 and 18050912 through 18053203.
182................. 33000 through 53007 and 18253008 through 18268293.
A182................ A182-0057 through A182-0148.
F182................ F18200001 through F182000169.
185................. 185-0001 through 185-1599 and 18501600 through
18504410.
188................. 188-0001 through 188-0572, 18800573 through
18803945, 18800967T through 18803968T, and
T18803307T through T18803968T.
205................. 205-0001 through 205-577.
206................. 206-0001 through 206-0275.
P206/TP206.......... P206-0001 through P206-0603 and P20600604 through
P20600647.
U206/TU206.......... U206-0276 through U206-1444 and U20601445 through
U20606459.
207/T207............ 20700001 through 20700734.
210................. 57001 through 57575 and 21057576 through 21064780.
P210................ P21000001 through P21000811.
T210................ T210-0001 through T210-0454.
------------------------------------------------------------------------
(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:
------------------------------------------------------------------------
Manufacturer Series/Models
------------------------------------------------------------------------
Twin Commander...... Models 200D, 500A, 500C, 500D, and 685.
Beech............... 33, 35, 36, 55, 58, and 95 Series.
Piper............... PA46 Series.
Navion.............. Rangemaster.
Ryan Navion......... Model L-17.
Wren................ Model 460.
Bellanca............ Models 260 and 300.
------------------------------------------------------------------------
(3) Airplanes equipped with one of the following Teledyne
Continental Motors model or model series engines:
O-470 IO-470 TSIO-470
O-520 IO-520 TSIO-520
GTSIO-520 IO-550 TSIO-550
Cessna has issued Service Bulletin (SB) SEB93-1, dated January 29,
1993, which specifies procedures for inspecting the engine oil filter
and adapter assembly. Oil filter and assembly installation procedures
and torque values are included in the applicable Cessna maintenance
manual.
After examining the circumstances and reviewing all available
information related to the incidents described above including the
referenced service instructions, the FAA has determined that AD action
should be taken 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.
Since an unsafe condition has been identified that is likely to
exist or develop in other airplanes utilizing a Cessna engine oil
filter adapter, part number 0450404-1, 0450404-3, 0556004-1, 0556010-1,
1250403-6, 1250922-1, or 1250922-2, of the same type design, the
proposed AD would require (1) applying torque paint between the engine
filter adapter assembly, nut, and oil pump housing; (2) inspecting the
oil filter and adapter assembly for oil leakage and proper installation
of the adapter retaining nut and fretting of associated threads
(security), and replacing any oil filter and adapter assembly with oil
leakage or security problems; and (3) repetitively inspecting the
torque paint for cracks or misalignment, and reinspecting the oil
filter and adapter assembly if torque paint cracks or misalignment is
found.
The FAA estimates that 70,000 airplanes in the U.S. registry
incorporate this engine oil filter and assembly and would be affected
by the proposed AD, that it would take approximately 1 workhour per
airplane to accomplish the proposed initial inspection and torque paint
application, and that the average labor rate is approximately $55 an
hour. Based on these figures, the total cost impact of the proposed AD
on U.S. operators is estimated to be $3,850,000. This cost is based on
the assumption that no operator has accomplished the initial
inspection, and does not take into account the cost for repetitive
inspections. The FAA has no way of determining how many repetitive
inspections each individual operator would incur.
The regulations proposed herein would 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
proposal would 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) if promulgated,
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 draft regulatory evaluation
prepared for this action has been placed 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [AMENDED]
2. Section 39.13 is amended by adding a new AD to read as follows:
Cessna Aircraft Company: Docket No. 93-CE-54-AD.
Applicability: Engine Oil Filter Adapters, part numbers 0450404-
1, 0450404-3, 0556004-1, 0556010-1, 1250403-6, 1250922-1, and
1250922-2, installed on, but not limited to the following:
(1) The following Cessna model and series airplanes with an
affected adapter installed at manufacture:
------------------------------------------------------------------------
Model or series Serial Nos.
------------------------------------------------------------------------
150................. 17001 through 17999, 59001 through 59018, and
15059019 through 15079405.
A150................ A1500001 through A1500734.
F150................ F150-0001 through F150-0529 and F15000530 through
F15001428.
FA150............... FA1500001 through FA1500120.
FRA150.............. FRA1500121 through FRA1500336.
172................. 28000 through 47746 and 17247747 through 17256512.
F172................ F172-0001 through F172-0654 and F17200655 through
F17200804.
FR172............... FR172-0001 through FR17200559 and FR17200561.
180................. 30000 through 50911 and 18050912 through 18053203.
182................. 33000 through 53007 and 18253008 through 18268293.
A182................ A182-0057 through A182-0148.
F182................ F18200001 through F182000169.
185................. 185-0001 through 185-1599 and 18501600 through
18504410.
188................. 188-0001 through 188-0572, 18800573 through
18803945, 18800967T through 18803968T, and
T18803307T through T18803968T.
205................. 205-0001 through 205-577.
206................. 206-0001 through 206-0275.
P206/TP206.......... P206-0001 through P206-0603 and P20600604 through
P20600647.
U206/TU206.......... U206-0276 through U206-1444 and U20601445 through
U20606459.
207/T207............ 20700001 through 20700734.
210................. 57001 through 57575 and 21057576 through 21064780.
P210................ P21000001 through P21000811.
T210................ T210-0001 through T210-0454.
------------------------------------------------------------------------
(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:
------------------------------------------------------------------------
Manufacturer Series/Models
------------------------------------------------------------------------
Twin Commander...... Models 200D, 500A, 500C, 500D, and 685.
Beech............... 33, 35, 36, and 55 Series.
Piper............... PA46 Series.
Navion.............. Rangemaster.
Ryan Navion......... Model L-17.
Wren................ Model 460.
Bellanca............ Models 260 and 300.
------------------------------------------------------------------------
(3) Airplanes equipped with one of the following Teledyne
Continental Motors model or model series engines:
O-470 IO-470 TSIO-470
O-520 IO-520 TSIO-520
GTSIO-520 IO-550 TSIO-550
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
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) Within the next 100 hours time-in-service or upon removal of
the engine oil filter, whichever occurs first, disassemble the
engine oil filter assembly in accordance with the applicable
maintenance manual, and accomplish the following:
(1) Inspect the oil filter and adapter assembly for oil leakage
and proper installation of the adapter retaining nut and fretting of
the associated threads (security) in accordance with Cessna Service
Bulletin SEB93-1, dated January 29, 1993.
(2) Prior to further flight, replace any oil filter and adapter
assembly with oil leakage or security problems.
(3) Apply torque paint between the engine filter adapter
assembly, nut, and oil pump housing.
(4) Reassemble the engine oil filter assembly.
(5) The disassembly, replacement (if necessary), and assembly
required by the paragraphs above shall be accomplished in accordance
with the applicable Cessna maintenance manual.
Note 1: If the airplane has one of the applicable engine oil
filter assemblies installed by field approval, it is the
responsibility of the airplane owner/operator to obtain the
applicable Cessna maintenance manual information, which includes
torque values.
(b) Within 100 hours TIS after the inspection required by
paragraph (a) of this AD, and thereafter at intervals not to exceed
100 hours TIS or upon removal of the engine oil filter, whichever
occurs first, accomplish the following:
(1) Inspect the torque paint for cracks or misalignment.
(2) If any torque paint cracks or misalignment is found, prior
to further flight, accomplish the requirements specified in
paragraph (a) of this AD, including all subparagraphs.
(c) Replacing the engine oil filter assembly does not eliminate
the repetitive inspection requirement of this AD.
(d) 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.
(e) An alternative method of compliance or adjustment of the
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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(f) All persons affected by this directive may obtain copies of
the document referred to herein upon request to the Cessna Aircraft
Company, P.O. Box 7704, Wichita, Kansas 67277; or may examine this
document at the FAA, Central Region, Office of the Assistant Chief
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
Issued in Kansas City, Missouri, on September 12, 1994.
Barry D. Clements,
Manager, Small Airplane Directorate, Aircraft Certification Office.
[FR Doc. 94-23080 Filed 9-16-94; 8:45 am]
BILLING CODE 4910-13-P
