[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:

------------------------------------------------------------------------
               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.                
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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[GRAPHIC] [TIFF OMMITTED] TP22JA96.000



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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]
BILLING CODE 4910-13-U