Airworthiness Directives; Teledyne Continental Motors IO-346, IO- 520, and IO-550 Series Reciprocating Engines

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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