[Federal Register Volume 59, Number 1 (Monday, January 3, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 93-32026]


[[Page Unknown]]

[Federal Register: January 3, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 93-ANE-48]

 

Airworthiness Directives; Textron Lycoming Reciprocating Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to supersede an existing airworthiness 
directive (AD), applicable to certain Textron Lycoming reciprocating 
engines, that currently requires replacement of sintered iron impellers 
in oil pumps. This action would continue to require replacement of 
sintered iron impellers, but would also require replacement of aluminum 
impellers. This proposal is prompted by reports of additional oil pump 
failures caused by aluminum impellers, which do not have the 
reliability of the hardened steel impellers. The actions specified by 
the proposed AD are intended to prevent an oil pump failure due to 
impeller failure, which could result in an engine failure.

DATES: Comments must be received by March 4, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 93-ANE-48, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location between 8 a.m. and 4:30 p.m., Monday through Friday, 
except Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Textron Lycoming, Reciprocating Engine Division, 652 
Oliver St., Williamsport, PA 17701. This information may be examined at 
the FAA, New England Region, Office of the Assistant Chief Counsel, 12 
New England Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Nicholas Minniti, Aerospace Engineer, 
New York Aircraft Certification Office, FAA, Engine and Propeller 
Directorate, 181 South Franklin Ave., Room 202, Valley Stream, NY 
11581; telephone (516) 791-7421, fax (516) 791-9024.

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 summarizing 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 Number 93-ANE-48.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Assistant Chief Counsel, 
Attention: Rules Docket No. 93-ANE-48, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion:

    On August 14, 1981, the Federal Aviation Administration (FAA) 
issued AD 81-18-04, Amendment 39-4199 (46 FR 43134, August 27, 1981), 
to require replacement of sintered iron oil pump impellers and oil pump 
shafts with impellers and shafts made of aluminum or hardened steel in 
certain Textron Lycoming reciprocating engines. That action was 
prompted by reports of oil pump failures. Subsequent to the publication 
of AD 81-18-04, the FAA issued two revisions to AD 81-18-04 they are: 
81-18-04R1, Amendment 39-4258 (46 FR 56157, November 16, 1981), 
effective November 19, 1981, and AD 81-18-04R2, Amendment 39-4395 (47 
FR 23691, June 1, 1982), effective June 7, 1982. That condition, if not 
corrected, could result in an oil pump failure due to impeller failure, 
which could result in an engine failure.
    Since the issuance of AD 81-18-04R2, the FAA has received reports 
of additional oil pump failures. The FAA has determined that some 
sintered iron impellers and shafts are still in service, as some 
engines have not reached the replacement time specified in that AD. The 
FAA has also determined that the aluminum impellers and shafts do not 
have the reliability of the hardened steel impellers and shafts. 
Therefore, aluminum impellers and shafts must be replaced with hardened 
steel impellers and shafts after no more than 750 hours time in 
service.
    The FAA has reviewed and approved the technical contents of the 
following service bulletins (SB): Avco Lycoming SB No. 381, Revision C, 
dated November 7, 1975; Avco Lycoming SB No. 385, Revision C, dated 
October 3, 1975; Avco Lycoming Textron SB No. 454, Revision B, dated 
January 2, 1987; Avco Lycoming Textron SB No. 455, Revision D, dated 
January 2, 1987; and Textron Lycoming SB No. 456, Revision F, dated 
February 8, 1993. These SB's describe procedures for replacing sintered 
iron and aluminum impellers and shafts with hardened steel impellers 
and shafts.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 81-18-04 R2 to require replacing 
sintered iron and aluminum impellers and shafts with hardened steel 
impellers and shafts. Engines affected by Textron Lycoming SB No. 456, 
Revision F, dated February 8, 1993, must have their sintered iron 
impellers replaced with hardened steel impellers and shafts within 100 
hours time in service, or no later than one year after the effective 
date of this AD, whichever occurs first. This calendar end-date has 
been determined based on Textron Lycoming's analysis that the sintered 
iron impellers suffer from rust, and consequently a loss in strength, 
after an extended period of time in service. Some of these impellers 
have been in service for up to 20 years.
    There are approximately 4,000 engines of the affected design in the 
worldwide fleet. The FAA estimates that 2,400 engines installed on 
aircraft of U.S. registry would be affected by this proposed AD, that 
it would take approximately 9 work hours per engine to accomplish the 
proposed actions, and that the average labor rate is $55 per work hour. 
Required parts would cost approximately $740 per engine. Based on these 
figures, the total cost impact of the proposed AD on U.S. operators is 
estimated to be $2,964,000. This figure is based on the assumption that 
none of the affected engines installed on U.S. Registry, have hardened 
steel impellers installed.
    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 proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the 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 is contained 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 14 
CFR part 39 of the Federal Aviation Regulations 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 39-4395, and by 
adding a new airworthiness directive to read as follows:

Textron Lycoming: Docket No. 93-ANE-48. Supersedes AD 81-18-04 R2, 
Amendment 39-4395.

    Applicability: Textron Lycoming O-235, O-290-D, O-290-D2, O-320, 
IO-320, AIO-320, AEIO-320, LIO-320, O-340, O-360, IO-360, AIO-360, 
AEIO-360, AEIO-360, HO-360, HIO-360, LO-360, LIO-360, TIO-360, TO-
360, LTO-360, VO-360, IVO-360, O-540, and IO-540 series 
reciprocating engines, except for the following models: O-320-H2AD, 
O-360-E1A6D, LO-360-E1A6D, TO-360-E1A6D, LTO-360-E1A6D, IO-540-P1A5, 
IO-540-R1A5, IO-540-S1A5, and O-540 and IO-540 series engines built 
with large capacity oil pumps and dual magnetos designated with 
``5D'' in the model suffix; for example, IO-540-K1A5D. These engines 
are installed on but not limited to the following aircraft: various 
models of single and twin engine powered Cessna, Piper, Mooney, 
Beech, Gulfstream American, Maule, and Socata.

    Note: This AD may not contain an exhaustive list of aircraft 
that utilize the affected engines because other aircraft may have an 
affected engine installed through, for example, approvals made by 
Supplemental Type Certificate, or FAA Form 337, ``Major Repair and 
Alteration.'' It is the responsibility of each aircraft owner, 
operator, and person returning that aircraft to service to determine 
if that aircraft has an affected engine.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent oil pump failure due to impeller failure, which could 
result in an engine failure, accomplish the following:
    (a) For Textron Lycoming Model HIO-360-D1A, -E1AD, -E1BD, and -
F1AD engines with serial numbers (S/N) of L-22579-51A or prior, 
except for the following: S/N L-22311-51A through L-22313-51A, L-
22396-51A, L-22397-51A, L-22416-51A, L-22546-51A through L-22549-
51A, L-22563-51A, L-22568-51A through L-22571-51A; for Textron 
Lycoming Model HIO-360-D1A, -E1AD, -E1BD, and -F1AD engines that 
were overhauled in the field or remanufactured prior to April 1, 
1981, regardless of S/N; and for engines listed by S/N in Textron 
Lycoming Service Bulletin (SB) No. 455, Revision D, dated January 2, 
1987; accomplish the following:
    (1) Replace the sintered iron oil pump impeller and shaft with a 
hardened steel impeller and shaft in accordance with Avco Lycoming 
Textron SB No. 454, Revision B, dated January 2, 1987, or Avco 
Lycoming Textron SB No. 455, Revision D, dated January 2, 1987, as 
applicable, within 25 hours time in service (TIS) after the 
effective date of this AD.
    (2) No action is required if engines have complied with AD 81-
18-04, 81-18-04 R1, or 81-18-04 R2, and have incorporated oil pumps 
with a hardened steel impeller and shaft. Engines that incorporate 
oil pumps fitted with an aluminum impeller and shaft must comply 
with paragraph (c) of this AD.
    (b) For engines listed by S/N in Textron Lycoming SB No. 456, 
Revision F, dated February 8, 1993, that incorporate a sintered iron 
impeller, accomplish the following:
    (1) Replace any sintered iron oil pump impeller and shaft with a 
hardened steel impeller and shaft in accordance with Textron 
Lycoming SB No. 456, Revision F, dated February 8, 1993, within 100 
hours TIS after the effective date of this AD, or one year after the 
effective date of this AD, whichever occurs first.
    (2) No action is required if engines have complied with AD 81-
18-04, 81-18-04 R1, or 81-18-04 R2, and have incorporated oil pumps 
with a hardened steel impeller and shaft. Engines that incorporate 
oil pumps fitted with an aluminum impeller and shaft must comply 
with paragraph (c) of this AD.
    (c) For all other affected engines, replace any aluminum oil 
pump impeller and shaft with a hardened steel impeller and shaft in 
accordance with Avco Lycoming Textron SB No. 455, Revision D, dated 
January 2, 1987, or Textron Lycoming SB No. 456, Revision F, dated 
February 8, 1993, as applicable, as follows:
    (1) For oil pumps that have accumulated 650 hours or more TIS on 
the effective date of this AD, replace within 100 hours TIS after 
the effective date of this AD.
    (2) For oil pumps that accumulated less than 650 hours TIS on 
the effective date of this AD, replace prior to accumulating 750 
hours TIS.
    (3) No action is required if engines have complied with AD 81-
18-04, 81-18-04 R1, or 81-18-04 R2, and have incorporated oil pumps 
with a hardened steel impeller and shaft.

    Note: Engines originally manufactured prior to 1970 did not 
incorporate sintered iron impellers. For further information, refer 
to engine maintenance/overhaul logbook records, Lycoming build 
records, and the following SB's provide additional guidance: Avco 
Lycoming SB No. 381, Revision C, dated November 7, 1975, and Avco 
Lycoming SB No. 385, Revision C, dated October 3, 1975, describe a 
method for determining if the early design oil pump with aluminum/
steel impellers are installed. Avco Lycoming SB No. 455, Revision A, 
dated August 18, 1981, and Avco Lycoming SB No. 455, Revision B, 
dated January 2, 1987, and Avco Lycoming SB No. 456, dated August 
21, 1981, and Avco Lycoming SB No. 456, Revision A, dated September 
25, 1981, introduced steel driving impeller, P/N 60746, and aluminum 
driven impeller, P/N LW13775.

    (d) Sintered iron and aluminum impellers approved under FAA 
Parts Manufacturer Approval (PMA) are replacements for affected part 
numbers of Lycoming impellers and must also be replaced in 
accordance with paragraphs (a), (b), or (c), as applicable, of this 
AD.
    (e) 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, New York 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, New York 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 New York Aircraft Certification 
Office.

    (f) Special flight permits may be issued in accordance with FAR 
21.197 and 21.199 to operate the airplane to a location where the 
requirements of this AD can be accomplished.

    Issued in Burlington, Massachusetts, on December 21, 1993.
Jay J. Pardee,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 93-32026 Filed 12-30-93; 8:45 am]
BILLING CODE 4910-13-P