[Federal Register Volume 60, Number 121 (Friday, June 23, 1995)]
[Rules and Regulations]
[Pages 32581-32583]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-15151]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-ANE-18; Amendment 39-9282; AD 95-08-10]


Airworthiness Directives; Teledyne Continental Motors (TCM) Model 
TSIO-360 and LTSIO-360 Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule, request for comments.

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SUMMARY: This document publishes in the Federal Register Airworthiness 
Directive (AD) 95-08-10 that was sent previously to all known U.S. 
owners and operators of Teledyne Continental Motors (TCM) Model TSIO-
360 E, EB, F, FB, G, GB, KB, LB, MB, and Model LTSIO-360 E, EB, and KB 
reciprocating engines by individual letters. This AD requires 
replacement of the suspect turbocharger check valves prior to further 
flight, and prohibits special flight permits. This amendment is 
prompted by three reported engine failures caused by incorrectly 
assembled turbocharger oil outlet check valves, resulting in an 
improperly expanded rivet that held the check valve flapper assembly 
together as one unit. The actions specified by this AD are intended to 
prevent complete engine failure due to an incorrectly assembled 
turbocharger oil outlet check valve.

DATES: Effective July 10, 1995, to all persons except those persons to 
whom it was made immediately effective by [[Page 32582]] priority 
letter AD 95-08-10, issued on April 6, 1995, which contained the 
requirements of this amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 10, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before August 22, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 95-ANE-18, 12 New England 
Executive Park, Burlington, MA 01803-5299.
    The applicable service information may be obtained from Teledyne 
Continental Motors, P.O. Box 90, Mobile, Alabama, 36601, telephone 
(334) 438-3411, fax (334) 432-2922. This information may be examined at 
the FAA, New England Region, Office of the Assistant Chief Counsel, 12 
New England Executive Park, Burlington, MA; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Jerry Robinette, Aerospace Engineer, 
Atlanta Aircraft Certification Office, FAA, Small Airplane Directorate, 
Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, GA, 
30337-2748; telephone (404) 305-7371, fax (404) 305-7348.

SUPPLEMENTARY INFORMATION: On April 6, 1995, the Federal Aviation 
Administration (FAA) issued priority letter airworthiness directive 
(AD) 95-08-10, applicable to Teledyne Continental Motors (TCM) Model 
TSIO-360 E, EB, F, FB, G, GB, KB, LB, MB, and Model LTSIO-360 E, EB, 
and KB reciprocating engines, which requires removal of suspect 
turbocharger oil outlet check valves. That action was prompted by three 
reported cases of check valve failures, two of which resulted in 
complete loss of engine power. The three reported failures were caused 
by incorrectly assembled turbocharger oil outlet check valves, 
resulting in an improperly expanded rivet which held the check valve 
flapper assembly together as one unit. The improperly expanded rivet 
allowed the rivet, washer, retainer, and seal components to separate 
and shift within the check valve unit.
    One reported case showed that a part of the flapper assembly 
blocked the oil flow to the scavenge pump, and resulted in engine 
failure. Another reported case showed that the scavenge pump was 
disabled when one part of the flapper assembly shifted through the 
unit, again resulting in engine failure. These failures occurred early 
in the life of the check valve, ranging from one hour to 40 hours total 
time since new.
    The incorrectly assembled check valves were manufactured between 
August 1, 1994, through March 20, 1995. Accordingly, all have date code 
ink stamps of either A3Q94, A4Q94, or A1Q95, indicating they were 
manufactured either during the third quarter of 1994, the fourth 
quarter of 1994, or the first quarter of 1995. Since an incorrectly 
assembled check valve can not be visually identified by other than by 
this date code, this AD must consider all check valves with these date 
codes as suspect, and require their removal prior to further flight. 
This condition, if not corrected, could result in damage to the oil 
scavenge pump, internal engine damage and subsequent loss of complete 
engine power.
    The FAA has reviewed and approved the technical contents of 
Teledyne Continental Motors (TCM) Critical Service Bulletin (CSB) 95-
1A, Revision A, dated April 5, 1995, that describes inspection and 
replacement of suspect oil outlet check valves.
    Since the unsafe condition described is likely to exist or develop 
on other engines of the same type design, the FAA issued priority 
letter AD 95-08-10 to prevent damage to the oil scavenge pump, internal 
engine damage and subsequent loss of complete engine power. The AD 
requires removal prior to further flight, of suspect turbocharger oil 
outlet check valves. The actions are required to be accomplished in 
accordance with the service bulletin described previously.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual letters 
issued on April 6, 1995, to all known U.S. owners and operators of 
Teledyne Continental Motors (TCM) Model TSIO-360 E, EB, F, FB, G, GB, 
KB, LB, MB, and Model LTSIO-360 E, EB, and KB reciprocating engines. 
These conditions still exist, and the AD is hereby published in the 
Federal Register as an amendment to section 39.13 of part 39 of the 
Federal Aviation Regulations (14 CFR part 39) to make it effective to 
all persons.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 
AD 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 Number 95-ANE-18.'' The postcard will be date stamped and 
returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy [[Page 32583]] of 
it, if filed, may be obtained from the Rules Docket at the location 
provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 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 the following new 
airworthiness directive:

95-08-10  Teledyne Continental Motors: Amendment 39-9282. Docket 95-
ANE-18.

    Applicability: Teledyne Continental Motors (TCM) engine Model 
TSIO-360 E, EB, F, FB, G, GB, KB, LB, MB, and Model LTSIO-360 E, EB, 
and KB reciprocating engines with turbocharger oil outlet check 
valve, TCM part number (P/N) 641068, shipped directly or indirectly 
from the manufacturer on or after August 1, 1994. These check valves 
are installed on but not limited to the following serial numbered 
engines:
    New engine model TSIO-360-FB, serial number (S/N) 318019; new 
engine model TSIO-360-KB, S/N 320223, 320229, 320233, through 
320235, 320239, 320242 through 320250, 320254 through 320259, 
320261, 320262, 320264, 320266, 320292, 320293; new engine model 
LTSIO-360-KB, S/N 319226, 319232, 319235 through 319237, 319241, 
319244 through 319246, 319248 through 319253, 319257, 319258, 319260 
through 319268, 319270, 319271, 319273, 319297, 319322; rebuilt 
engine model TSIO-360-E, S/N 225140-R; rebuilt engine model TSIO-
360-EB, S/N 265937-R, 265938-R, 265942-R through 265944-R, 265946-R 
through 265968-R, 265970-R through 265973-R, 265975-R, 265977-R 
through 265982-R; rebuilt engine model LTSIO-360-E, S/N 225648-R; 
rebuilt engine model LTSIO-360-EB, S/N 266471-R, 266480-R, 266482-R 
266486-R, 266487-R, 266489-R through 266495-R, 266497-R through 
266499-R, 807251-R through 807254-R, 807256-R through 807259-R, 
807261-R through 807265-R, 807267-R, 807268-R, 807271-R through 
807275-R, 807276-R; rebuilt engine model TSIO-360-F, S/N 232814-R 
through 232817-R; rebuilt engine model TSIO-360-FB, S/N 281183-R, 
281187-R, 281189-R, 281190-R, 281193-R through 281197-R, 281199-R, 
299501-R through 299523-R, 299525-R through 299528-R, 299532-R; 
rebuilt engine model TSIO-360-KB, S/N 268192-R, 268195-R through 
268201-R, 268205-R through 268207-R; rebuilt engine model LTSIO-360-
KB, S/N 268428-R, 268430-R, 268431-R, 268433-R, 268434-R, 268436-R, 
268437-R, 268440-R through 268445-R; rebuilt engine model TSIO-360-
LB, S/N 247257-R, 247259-R, 247260-R, 247262-R, 247267-R through 
247271-R, 247273-R through 247275-R; and rebuilt engine model TSIO-
360-MB, S/N 279245-R through 279247-R, 279249-R, 279250-R.
    These engines are installed on but not limited to: Mooney Model 
M20K, Piper Models PA28-201T, PA28R-201T, PA28RT-201T, PA34-200T and 
PA34-220T aircraft.

    Note: This AD applies to each engine 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 engines that have been modified, altered, or repaired so 
that the performance of the requirements of this AD is affected, the 
owner/operator must use the authority provided in paragraph (e) to 
request approval from the FAA. This approval may address either no 
action, if the current configuration eliminates the unsafe 
condition, or different actions necessary to address the unsafe 
condition described in this AD. Such a request should include an 
assessment of the effect of the changed configuration on the unsafe 
condition addressed by this AD. In no case does the presence of any 
modification, alteration, or repair remove any engine from the 
applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent engine failure due to incorrectly assembled 
turbocharger oil outlet check valve, which could result in complete 
engine failure, accomplish the following:
    (a) Prior to further flight, determine if the turbocharger oil 
outlet check valve has been installed or repaired on or after August 
1, 1994. This AD is not applicable to engines that did not have the 
turbocharger oil outlet check valve installed or repaired on or 
after August 1, 1994.
    (b) Prior to further flight, inspect the turbocharger oil outlet 
check valve, TCM P/N 641068, in accordance with section B of 
Teledyne Continental Motors (TCM) Critical Service Bulletin (CSB) 
95-1A, Revision A, dated April 5, 1995, and replace any check valve 
with an ink stamped date code of A3Q94, A4Q94 or A1Q95, or with no 
readable date code, with a serviceable check valve as defined in 
paragraph (c) of this AD.
    (c) For the purpose of this AD, serviceable turbocharger oil 
outlet check valve is defined as one with a date stamp code 
indicating that it was manufactured before July 1, 1994, i.e., 
A2Q94, or earlier, or that it was manufactured after March 31, 1995, 
i.e., A2Q95, or later.
    (d) Install replacement valve in the turbocharger oil outlet 
line with the flow arrow on the valve body pointing in the direction 
of oil flow toward the scavenge pump in accordance with section B of 
TCM CSB95-1A, Revision A, dated April 5, 1995.
    (e) An alternative method of compliance that provides an 
acceptable level of safety may be used if approved by the Manager, 
Atlanta Aircraft Certification Office. The request should be 
forwarded through an appropriate FAA Maintenance Inspector, who may 
add comments and then send it to the Manager, Atlanta Aircraft 
Certification Office.

    Note: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Atlanta Aircraft Certification 
Office.

    (f) Special flight permits may not be issued.
    (g) Copies of the applicable service information may be obtained 
from Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama, 
36601, telephone (334) 438-3411, fax (334) 432-2922.
    (h) The turbocharger oil outlet check valve inspections shall be 
done in accordance with the following service bulletin:

------------------------------------------------------------------------
            Document No.                Pages    Revision       Date    
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TCM CSB95-1A........................     1, 2          A   April 5,     
                                                            1995.       
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Total pages: 2.

This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Teledyne Continental Motors, P.O. 
Box 90, Mobile, Alabama, 36601, telephone (334)438-3411, fax (334) 
432-2922. Copies may be inspected at the FAA, New England Region, 
Office of the Assistant Chief Counsel, 12 New England Executive 
Park, Burlington, MA; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (i) This amendment becomes effective July 10, 1995, to all 
persons except those persons to whom it was made immediately 
effective by priority letter AD 95-08-10, issued April 6, 1995, 
which contained the requirements of this amendment.

    Issued in Burlington, Massachusetts, on June 12, 1995.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 95-15151 Filed 6-22-95; 8:45 am]
BILLING CODE 4910-13-U