[Federal Register Volume 61, Number 14 (Monday, January 22, 1996)]
[Proposed Rules]
[Pages 1534-1538]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-480]
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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 Adapter Assemblies Installed on Aircraft
AGENCY: Federal Aviation Administration, DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); Reopening of
the comment period.
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SUMMARY: This document revises an earlier proposed airworthiness
directive (AD) that would have required the following on aircraft
equipped with certain engine oil filter adapter assemblies manufactured
by the Cessna Aircraft Company (Cessna): repetitively inspecting the
engine oil filter adapter assembly or torque putty if installed, and
replacing any oil filter adapter assembly with oil leakage or security
problems. Since issuance of the proposed AD, the Federal Aviation
Administration (FAA) has determined that the proposed action should
apply to all oil filter adapter assemblies manufactured by Cessna and
installed on aircraft. The FAA has also determined that the procedures
specified to accomplish the proposed AD should be revised and, that,
based on comments submitted on the NPRM, other changes to the AD should
be incorporated. Since the addition of oil filter adapter assembly part
numbers to the proposal expands the scope of what was originally
proposed, the FAA is allowing the public additional time for public
comment. The actions specified by the proposed 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.
DATES: Comments must be received on or before March 21, 1996.
ADDRESSES: Submit comments in triplicate 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.
Comments may be inspected at this location between 8 a.m. and 4 p.m.,
Monday through Friday, holidays excepted.
Information that relates to the proposed AD 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 Supplemental NPRMs
Any person may obtain a copy of this supplemental 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
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to include an AD that would apply to airplanes utilizing a
Cessna engine oil filter adapter assembly, part number 0450404-1,
0450404-3, 0556004-1, 0556010-1, 1250403-6, 1250922-1, or 1250922-2,
was published in the Federal Register on September 19, 1994 (59 FR
47821). The action proposed to require (1) applying torque putty
between the engine oil filter adapter assembly, nut, and oil pump
housing; (2) inspecting the oil filter 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 putty for cracks or misalignment, and
reinspecting the oil filter adapter assembly if misalignment or torque
putty cracks are found.
Interested persons have been afforded an opportunity to participate
in the making of the proposed amendment. Due consideration has been
given to the comments received.
One commenter recommends that the FAA require a one-time
modification rather than relying on repetitive inspections to eliminate
the unsafe condition of loose oil filter adapter assemblies. This
commenter states that the repetitive inspections become too time-
consuming and expensive, and that a one-time modification would
eliminate both of these problems. The FAA concurs that, for the most
part, a one-time modification is less time-consuming and less expensive
than repetitive inspections. The FAA also believes that if the one-time
modification provides an equivalent level of safety to the repetitive
inspections, then the chance of further damage to the aircraft is less
likely by incorporating the modification than by accomplishing
repetitive inspections of the affected engine oil filter adapter
assemblies. However, in this case, a one-time modification for the
engine oil filter adapter assemblies is not available. If one becomes
available that the FAA determines provides an equivalent level of
safety to that provided by the repetitive inspections, further
rulemaking action may be taken. Until such a modification is developed,
the FAA has determined that repetitive inspections of the affected
engine oil filter adapter assemblies are necessary. The notice of
proposed rulemaking (NPRM) is unchanged as a result of this comment.
[[Page 1535]]
Two commenters recommend that the FAA revise the NPRM to give
inspection credit for those airplanes already equipped with torque
putty. One of these commenters states that the initial removal of the
engine oil filter adapter is not necessary as long as the torque putty
applied at the last installation is not cracked or otherwise
compromised. The FAA concurs. The NPRM was written to require torque
putty application to aid in repetitive inspections. The intent was to
provide ``unless already accomplished'' credit for the initial
inspection for airplanes already equipped with torque putty, and then
require repetitive inspections of the torque putty provided no
misalignment, evidence of oil leakage, or torque putty cracks are
found. Removal of the engine oil filter and inspection of the oil
adapter threads would be required if misalignment, evidence of oil
leakage, or torque putty cracks are found during any of the torque
putty repetitive inspections. The NPRM has been revised accordingly.
The Twin Commander Aircraft Corporation (Twin Commander) requests
that the NPRM not reference certain Twin Commander airplane models.
Twin Commander states that while it holds a type certificate for Models
500A and 685D, it does not hold a type certificate for the Models 200D,
500C, and 500D airplanes, and is not aware of these models being type
certificated for operation in the United States. The FAA concurs and
has deleted all reference to Twin Commander Models 200D, 500C, and 500D
airplanes from the proposal.
The Cessna Pilots Association (CPA) recommends that the FAA include
a drawing in the NPRM to aid in accomplishing the proposed AD. The FAA
concurs, and has developed and incorporated Figure 1 into the proposal.
The CPA states that the AD should not reference accomplishment of
any actions in accordance with Cessna Service Bulletin (SB) SEB93-1,
dated January 29, 1993. This service bulletin does not include
procedures for accomplishing any of the proposed actions. In addition,
the CPA provides proposed procedures for inspecting the engine oil
filter adapter assemblies and applying and inspecting the torque putty.
The FAA concurs that Cessna SB SEB93-1, dated January 29, 1993, does
not specify procedures for accomplishing the proposed actions, and the
FAA has removed reference to the service bulletin from the AD. The FAA
utilized the procedures submitted by the CPA in revising the proposal.
In addition, the CPA states that the pilot should be allowed to
accomplish the repetitive inspections of the torque putty. The FAA
concurs that the pilot may inspect the torque putty for misalignment,
evidence of oil leakage, or torque putty cracks, as specified in
section 43.7(f) of the Federal Aviation Regulations (14 CFR 43.7). The
proposal has been revised accordingly.
Cessna recommends that the FAA revise the proposal to include
additional engine oil filter adapter assembly part numbers. The FAA
concurs and has revised the applicability of the proposed AD to include
these additional engine oil filter adapter assembly part numbers.
After examining the circumstances and reviewing all available
information related to the subject described above including the
comments received, the FAA has determined that the NPRM should be
revised and that AD action should still be taken to prevent loss of
engine oil caused by loose or separated oil filter adapters assemblies,
which, if not detected and corrected, could result in engine stoppage
while in flight and loss of control of the airplane.
Since the revision of the NPRM to add certain engine oil filter
adapter assembly part numbers goes beyond the scope of what was already
proposed, the FAA is reopening the comment period to allow the public
additional time to comment on this proposed action.
Since an unsafe condition has been identified that is likely to
exist or develop in other airplanes of any type design that utilize any
Cessna engine oil filter adapter, the proposed AD would 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.
The FAA estimates that 70,000 airplanes in the U.S. registry
incorporate one of the affected engine oil filter adapter assemblies
and would, therefore, be affected by the proposed AD; that it would
take approximately 1 workhour per airplane to accomplish the proposed
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 the proposed 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 proposed initial inspection, and does not take
into account the cost for the proposed repetitive inspections. Since
the pilot would be allowed to repetitively inspect the torque putty,
the only cost of the proposed repetitive inspections would be 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 would incur over the life of the
airplane.
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 USC 106(g), 40101, 40113, 44701.
[[Page 1536]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Cessna Aircraft Company: Docket No. 93-CE-54-AD.
Applicability: 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 Model 100, 200, 300, and 400 Series airplanes (all
serial numbers) 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:
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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.
Navion.................................... Rangemaster 17 Series.
Wren...................................... Model 460.
Bellanca.................................. 260 and 300 Series.
------------------------------------------------------------------------
(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 pounds.
(3) If evidence of oil leakage is found or the torque is not
within the 50 through 60-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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(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 in 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 January 5, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-480 Filed 1-19-96; 8:45 am]
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