[Federal Register Volume 65, Number 228 (Monday, November 27, 2000)]
[Rules and Regulations]
[Pages 70654-70656]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-29496]



[[Page 70654]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-16-AD; Amendment 39-11994; AD 2000-23-21]
RIN 2120-AA64


Airworthiness Directives; Teledyne Continental Motors IO-360, 
TSIO-360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-
520, IO-550, TSIO-550, and TSIOL-550 Series Reciprocating Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes emergency airworthiness directive 
(AD) 2000-08-51. Emergency AD 2000-08-51 was sent to all known U.S. 
owners and operators of Teledyne Continental Motors (TCM) IO-360, TSIO-
360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-520, 
IO-550, TSIO-550, and TSIOL-550 series reciprocating engines by 
individual letters. This amendment requires removing a core sample of 
material from the propeller mounting flange of certain crankshafts, and 
sending the core sample to TCM for evaluation. This amendment is 
prompted by reports of crankshaft failures, and by the addition of 
additional crankshaft serial numbers (SN) that have been added to the 
suspect population. The actions specified by this AD are intended to 
prevent fracture of the crankshaft connecting rod journal, which could 
result in total engine power loss, in-flight engine failure and 
possible forced landing.

DATES: Effective December 12, 2000. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of December 12, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before January 26, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-16-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#29100448474c04484d4a4644444c475d694f4848074e465f"><span class="__cf_email__" data-cfemail="8fb6a2eee1eaa2eeebece0e2e2eae1fbcfe9eeeea1e8e0f9">[email protected]</span></a>.'' Comments sent via the Internet must contain the 
docket number in the subject line.
    The service information referenced in this AD may be obtained from 
Teledyne Continental Motors, PO Box 90, Mobile, AL 36601; telephone 
toll free 1-888-200-7565, or on the TCM internet site 
``www.tcmlink.com.'' This information may be examined at the FAA, New 
England Region, Office of the Regional 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, Senior Engineer, 
Propulsion, Atlanta Aircraft Certification Office, FAA, Small Airplane 
Directorate, One Crown Center, 1895 Phoenix Blvd., Suite 450, Atlanta, 
GA 30349; telephone: (770) 703-6096, fax: (770) 703-6097.

SUPPLEMENTARY INFORMATION: On April 28, 2000, the Federal Aviation 
Administration (FAA) issued emergency airworthiness directive (AD) 
2000-08-51 that is applicable to Teledyne Continental Motors IO-360, 
TSIO-360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-
520, IO-550, TSIO-550, and TSIOL-550 series reciprocating engines. That 
AD requires removing a core sample of material from the propeller 
mounting flange and sending the core sample to TCM for evaluation. That 
action was prompted by reports of crankshafts on which the connecting 
rod journals had fractured. On November 24, 1999, the FAA was notified 
of a crankshaft failure on a TCM engine. Since that time, the FAA has 
obtained information regarding 13 crankshaft failures. The 
investigation revealed that the crankshafts failed due to subsurface 
defects in the number one crankshaft connecting rod journal. The FAA 
has determined that all of the defects were due to unique material 
composition characteristics combined with process control variations 
that occurred during the material melt process. This occurred during 
several discrete periods, i.e. certain lots, of steel production or 
forming operations. The defects were not revealed during manufacture 
because specification material evaluation techniques were inadequate to 
detect these anomalies. Continued evaluation of crankshafts lots with 
serial numbers (SN's) other than those that were listed in AD 2000-08-
51, has detected the same condition in those crankshaft lots. TCM 
mandatory service bulletin (MSB) 005B, dated May 25, 2000, and MSB 
005C, dated October 10, 2000, were issued to include the SN's of those 
additional suspect crankshafts. The specification material evaluation 
techniques have been improved to preclude a reoccurrence of this 
condition. Crankshafts with this type of subsurface defect will fail. 
All of the fractures have been grouped around certain manufacturing 
dates between April 1, 1998, and March 31, 2000, inclusive. This 
condition, if not corrected, could result in crankshaft connecting rod 
journal fracture, which could result in total engine power loss, in-
flight engine failure and possible forced landing.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of TCM 
Mandatory Service Bulletin (MSB) 005C, dated October 10, 2000. MSB 005C 
lists additional serial numbers (SN's) of affected engines and suspect 
crankshafts that were manufactured between April 1, 1998, and March 31, 
2000, inclusive. The MSB also describes procedures for removing a core 
sample of material from the propeller mounting flange of the crankshaft 
and for cleaning, chamfering, dye checking, and painting the core 
sample holes.

Requirements of This AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of this same type design, this 
airworthiness directive (AD) requires removing a core sample of 
material from the propeller mounting flange and sending the core sample 
to TCM for evaluation. TCM has informed the FAA that it intends to 
maintain a 24 to 48 hour turn-around time for notification of the 
crankshaft airworthiness. All crankshafts that are found to be 
unserviceable must be replaced with a serviceable crankshaft prior to 
further flight. The actions are required to be accomplished in 
accordance with the service bulletin described previously.

Immediate Adoption

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

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

[[Page 70655]]

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 2000-NE-16-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    This proposed rule does not have federalism implications, as 
defined in Executive Order No. 13132, because it would not have a 
substantial direct effect 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. 
Accordingly, the FAA has not consulted with state authorities prior to 
publication of this proposed rule.
    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 No. 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 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 Code of Federal 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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-23-21 Teledyne Continental Motors: Amendment 39-11994. Docket 
2000-NE-16-AD.

Applicability

    This Airworthiness Directive (AD) is applicable to Teledyne 
Continental Motors (TCM) IO-360, TSIO-360, LTSIO-360, O-470, IO-470, 
TSIO-470, IO-520, TSIO-520, LTSIO-520, IO-550, TSIO-550 and TSIOL-
550 series reciprocating engines that were assembled, rebuilt, or 
overhauled using a crankshaft that was manufactured between April 1, 
1998, and March 31, 2000, listed by engine and crankshaft serial 
number (SN) in TCM Mandatory Service Bulletin (MSB) 00-5C, dated 
October 10, 2000.

    Note 1: The engines and crankshafts that are the subject of this 
AD were manufactured by TCM from April 1, 1998 through March 31, 
2000. However the dates that the engines and crankshafts were 
delivered may not coincide with their dates of manufacture. For 
crankshafts identified in paragraph (a) of this AD, TCM has already 
determined which engines have a new suspect crankshaft installed and 
have identified those engines by engine SN. The crankshaft SN is 
only used to determine the need for taking a core sample for those 
crankshafts identified in paragraph (a) and (b) of this AD. The 
engine SN can be found in logbooks or other maintenance records. For 
those engines that were overhauled in the field with factory new 
crankshafts, the crankshaft SN should be shown in work orders, log 
books or other maintenance records. If the engine was assembled new, 
rebuilt, or overhauled on or before March 31, 1998, or on or after 
April 1, 2000, no action is required.


    Note 2: This airworthiness directive (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 request 
approval for an alternative method of compliance in accordance with 
paragraph (d) 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.

Compliance

    Compliance with the requirements of this AD is required within 
the next 10 hours time-in-service from the effective date of this 
AD, unless already done.
    To prevent crankshaft connecting rod journal fracture, which 
could result in total engine power loss, in-flight engine failure 
and possible forced landing, do the following:

    Note 3: TCM supplies an instructional video in the tool kit for 
MSB 00-5C. It is recommended that the technician views and 
understands ``Instructional Video for Compliance with Teledyne 
Continental Motors Mandatory Service Bulletin MSB 00-5C'' before 
performing these procedures.

Crankshaft Material Inspection

    (a) For those engines and crankshafts listed by SN in TCM MSB 
00-5C, dated October 10, 2000, do the crankshaft material inspection 
(crankshaft propeller flange core sample) as follows:

    Note 4: The engine SN's listed in TCM MSB 00-5C contain only the 
numerical portion of the SN. Engines that have been rebuilt by TCM 
will have a letter ``R'' at the end of the six digit numerical 
portion. Disregard the letter ``R.''

    (1) Do the crankshaft material inspection (crankshaft propeller 
flange core sample) in accordance with sections A through J of TCM 
MSB 00-5C, dated October 10, 2000, as follows:
    (i) Use the specialized tools and equipment provided by TCM as 
listed in section A of TCM MSB 00-5C, dated October 10, 2000.
    (ii) You may use each rotobroach bit to obtain up to six core 
samples. Replace the rotobroach after the sixth core sample, or 
before if the rotobroach does not cut with the maximum torque 
applied.
    (iii) Maintain a record of each core sample obtained with each 
rotobroach bit used. Contact TCM to obtain additional rotobroach 
bits.
    (iv) Do not exceed the torque limits specified in TCM MSB 00-5C, 
dated October 10, 2000, when obtaining the core sample.
    (2) After obtaining the results of the core sample evaluation, 
disposition the crankshaft as follows:
    (i) If TCM notifies you that the crankshaft is not serviceable, 
replace the crankshaft with a serviceable crankshaft of the same 
part number before further flight.
    (ii) If TCM notifies you that the crankshaft is serviceable, the 
propeller assembly may be reinstalled.

Installation of Crankshafts

    (b) After the effective date of this AD, do not install a 
crankshaft with a SN that is

[[Page 70656]]

listed in MSB 00-5C, dated October 10, 2000, unless core samples 
have been taken and TCM has approved it for return to service.
    (c) Crankshaft material inspections (crankshaft propeller flange 
core samples) that were done using TCM MSB 00-5, dated April 14, 
2000; MSB 00-5A, dated April 28, 2000; or MSB 00-5B, dated May 25, 
2000, comply with this AD and must not be repeated.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Atlanta Aircraft Certification 
Office (ACO). Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Atlanta ACO.

    Note 5: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Atlanta ACO.

Incorporation by Reference Material

    (e) The actions required by this AD shall be performed in 
accordance with Teledyne Continental Motors MSB 00-5C, dated October 
10, 2000. 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, PO Box 90, Mobile, AL 36601; telephone toll free 1-888-200-
7565, or on the TCM internet site ``www.tcmlink.com''. Copies may be 
inspected at the FAA, New England Region, Office of the Regional 
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.

Effective Date of This AD

    (f) This amendment becomes effective on December 12, 2000.

    Issued in Burlington, Massachusetts, on November 13, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-29496 Filed 11-24-00; 8:45 am]
BILLING CODE 4910-13-U


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