[Federal Register Volume 60, Number 37 (Friday, February 24, 1995)]
[Rules and Regulations]
[Pages 10308-10310]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-4124]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-ANE-57; Amendment 39-9150; AD 95-03-14]
Airworthiness Directives; Teledyne Continental Motors IO-346, IO-
520, and IO-550 Series Reciprocating Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Teledyne Continental Motors (TCM) IO-346,
IO-520, and IO-550 series reciprocating engines, that currently
requires initial and repetitive inspections of the engine mount
brackets for cracks, and if found cracked, replacement with improved
design engine mount brackets. All engine mount brackets require
replacement with improved design engine mount brackets at the next
engine removal after the effective date of that airworthiness directive
(AD). This amendment clarifies the identification procedures to
determine which engine mount brackets must be inspected. This amendment
is prompted by reports that the engine mount bracket part numbers,
which are ink stamped, can be easily obliterated. The actions specified
by this AD are intended to prevent engine separation from the aircraft
due to cracks in the engine mount brackets.
DATES: Effective March 13, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 13, 1995.
Comments for inclusion in the Rules Docket must be received on or
before April 25, 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. 94-ANE-57, 12 New England
Executive Park, Burlington, MA 01803-5299.
The service information referenced in this AD may be obtained from
Teledyne Continental Motors, P.O. Box 90, Mobile, AL 36601; telephone
(334) 438-3411. This information may be examined at the FAA, New
England Region, Office of the Assistant Chief Counsel, 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 Ave., Suite 2-160, College Park, GA
30337-2748; telephone (404) 305-7371, fax (404) 305-7348.
SUPPLEMENTARY INFORMATION: On April 19, 1994, the Federal Aviation
Administration (FAA) issued airworthiness directive (AD) 94-09-07,
Amendment 39-8896 (59 FR 23148, May 5, 1994), applicable to certain
Teledyne Continental Motors (TCM) IO-346, IO-520, and IO-550 series
reciprocating engines, to require initial and repetitive dye penetrant
inspections for cracks in certain lower left engine mount brackets,
Part Number (P/N) 630695. If the lower left engine mount bracket is
found cracked, that AD requires replacing both the lower left and lower
right engine mount brackets with improved design engine mount brackets,
P/N 653306 and 653305, respectively. If a crack is not detected, the
lower left engine mount bracket requires repetitive inspections at
intervals not to exceed 500 hours time in service (TIS) until the next
engine removal, at which time engine mount brackets, P/N 630694 and
630695, are replaced with improved design engine mount brackets, P/N
653306 and 653305. Installation of these improved design engine mount
brackets constitutes terminating action to the inspection requirements
of that AD. That action was prompted by reports of cracks in engine
mount brackets on engines that have completed at least one overhaul
cycle. That condition, if not corrected, could result in engine
separation from the aircraft due to cracks in the engine mount
brackets.
Since the issuance of that AD, the FAA has received reports of
difficulty in identifying the engine mount brackets that must be
inspected. The P/N is ink-stamped on the part and is quite easily
obliterated. The problem arises when the Casting Number (C/N), which is
different from the P/N, is mistaken for the P/N, and the AD is
incorrectly believed to not apply.
The FAA has reviewed and approved the technical contents of TCM
Mandatory Service Bulletin (MSB) No. MSB94-9, dated October 21, 1994,
that provides positive identification of affected engine mount brackets
that require inspection, and replacement, if necessary.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of this same type design, this AD
supersedes AD 94-09-07 to clarify the identification procedures to
determine which engine mount brackets must be inspected. The actions
are required to be accomplished in accordance with the MSB described
previously.
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
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 94-ANE-57.'' 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
[[Page 10309]] 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 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 removing Amendment 39-8896 (59 FR
23148, May 5, 1994), and by adding a new airworthiness directive,
Amendment 39-9150, to read as follows:
95-03-14 Teledyne Continental Motors: Amendment 39-9150. Docket 94-
ANE-57. Supersedes AD 94-09-07, Amendment 39-8896.
Applicability: Teledyne Continental Motors (TCM) engine models
IO-346A, IO-346B, IO-520C, IO-520CB, and IO-550C; rebuilt engine
model IO-520C with serial numbers (S/N) 287051-R and lower; rebuilt
engine model IO-520CB with S/N 282226-R and lower; rebuilt engine
model IO-550C with S/N 271742-R and lower; and all factory
overhauled IO-520C, IO-520CB, and IO-550C engines with a build date
prior to August 6, 1992. These engines are installed on but not
limited to Beech model A23, A23A, 95-C55, 95-C55A, D55, D55A, E55,
E55A, 58, and 58A airplanes.
Compliance: Required as indicated, unless accomplished
previously.
To prevent engine separation from the aircraft due to cracks in
the engine mount brackets, accomplish the following:
(a) For engines with engine mount brackets that have completed
at least one engine overhaul or rebuild cycle, or have accumulated
2,500 or more hours time in service (TIS) on the effective date of
this airworthiness directive (AD), inspect the lower left engine
mount bracket, Part Number (P/N) 630695 or Casting Number (C/N)
630724, for cracks using the dye penetrant techniques specified in
this paragraph and in accordance with TCM Mandatory Service Bulletin
(MSB) No. MSB94-9, dated October 21, 1994, within the next 50 hours
TIS after the effective date of this AD.
Note 1: TCM MSB No. MSB94-9, dated October 21, 1994, differs
from TCM MSB No. M92-13, dated September 4, 1992, which was
referenced in AD 94-09-07, only in clarification of part
identification by utilizing a cross reference table for P/N and C/N.
Note 2: The P/N is ink stamped on the part and may not be
visible. The engine mount bracket can be identified by the C/N which
is cast in the engine mount bracket.
(1) Perform the dye penetrant inspection as follows:
Note: Military Specification MIL-I-6866 and American Society of
Testing Materials specifications ASTM E1417-93 and E165-9 contain
additional information on dye penetrant inspection processes.
(i) Preparation: clean and dry all parts in such a manner as to
leave the surfaces free from grease, oil, soaps, alkalies, and other
substances which would interfere with inspection. Vapor degreasing
is generally suitable for this purpose.
(ii) Penetrant Application Procedure: after preparation, spray
or brush the parts with the penetrant, and allow to stand for not
less than 5 minutes. The effectiveness of the penetrant increases if
left standing for a longer time, as the penetrant will reach finer
discontinuities.
(iii) Penetrant Cleaning: clean the parts thoroughly using a
medium which will remove penetrant from the surfaces of parts; wash
with water when the penetrant is water soluble. When other than
water soluble penetrants are used, the penetrant shall be removed
with a suitable cleaner. Avoid excessive cleaning which would remove
the penetrant from discontinuities.
(iv) Drying: dry the parts as thoroughly as possible. Drying of
parts may be accomplished by evaporation at room temperature or by
placing the parts in a circulating warm air oven or in the air
stream of a hot air dryer. Avoid excessive drying time or drying
temperatures above 75 deg.C (165 deg.F) to prevent excessive
evaporation of the penetrant. If heat is used for drying parts, cool
parts to approximately 50 deg.C (120 deg.F) before proceeding to the
developing procedure.
(v) Developing: apply the developer to the dry parts as lightly
and as evenly as possible, using as thin a coating of developer as
is possible. A translucent film is adequate. Mix wet developer by
agitation immediately prior to applying it. After applying the
developer, take care that no penetrant indication is disturbed or
obliterated in subsequent handling.
(vi) Examination: examine the developed penetrant indications in
accordance with the dye penetrant manufacturer's instructions.
Examine parts for indications of discontinuities open to the
surface.
(vii) Final cleaning: clean the parts following the inspection
to remove penetrant and developer.
Note 1: Caution: because of differences among penetrants, take
care to ensure that the final cleaner, the penetrant, the penetrant
remover, and the developer are suitable for use with each other.
Note 2: Caution: all penetrant materials should be kept as free
from moisture as possible.
Note 3: Caution: most penetrants, cleaning agents, and developer
suspensions are low flash point material; use caution to prevent
fires.
(2) If no crack is detected, inspect in accordance with
paragraph (a) of this AD at intervals not to exceed 500 hours TIS
since the last inspection.
(3) If a crack is detected, prior to further flight replace both
the lower left engine mount bracket, P/N 630695 or C/N 630724, and
lower right engine mount bracket, P/N 630694 or C/N 630723, with
improved design engine mount brackets, P/N 653306 or C/N 653299, and
P/N 653305 or C/N 653298, respectively.
(b) For all engines, replace both the lower left engine mount
bracket, P/N 630695 or PC/N 630724, and lower right engine mount
bracket, P/N 630694 or C/N 630723, with improved design engine mount
brackets, PP/N 653306 or C/N 653299, and P/N 653305 or C/N 653298,
respectively, at the next engine removal after the effective date of
this AD.
(c) Installation of the improved design engine mount brackets,
P/N 653306 or C/N 653299, and P/N 653305 or C/N 653298, constitutes
terminating action to the inspection requirements of this AD.
(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. 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.
(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 aircraft to a location where
the inspection may be performed. [[Page 10310]]
(f) The inspections and replacement shall be done in accordance
with the following service document:
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Document No. Pages Date
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TCM MSB No. MSB94-9...................... 1-2 Oct. 21, 1994.
Total pages: 2.
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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, AL 36601; telephone (334) 438-3411. 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.
(g) This amendment becomes effective on March 13, 1995.
Issued in Burlington, Massachusetts, on February 8, 1995.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 95-4124 Filed 2-23-95; 8:45 am]
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