[Federal Register Volume 60, Number 235 (Thursday, December 7, 1995)]
[Proposed Rules]
[Pages 62772-62774]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-29843]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-ANE-03]
Airworthiness Directives; Sensenich Propeller Manufacturing
Company Inc. Models M76EMM, M7EMMS, 76EM8, and 76EM8S() Metal
Propellers
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes to revise an existing airworthiness
directive (AD), applicable to Sensenich Propeller Manufacturing Company
Inc. Models M76EMM, M7EMMS, 76EM8, and 76EM8S() metal propellers, that
currently restricts operators from continuously operating the propeller
at engine speeds from 2,150 to 2,350 revolutions per minute (RPM). This
action would remove propellers installed on certain additional Textron
Lycoming O-360 series reciprocating engines with solid crankshafts from
this requirement, and update the referenced Sensenich Propeller Company
Inc. service bulletin to the latest revision. Reworking of all affected
propeller models remains a requirement of the proposed AD, regardless
of engine installation. This proposal is prompted by inquiries
concerning tachometer red arc restrictions on certain Textron Lycoming
O-360 series reciprocating engines with solid crankshafts. The actions
specified by the proposed AD are intended to prevent propeller blade
tip fatigue failure, which can result in loss of control of the
aircraft.
DATES: Comments must be received by February 5, 1996.
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-03, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at
this location between 8:00 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 Sensenich Propeller Manufacturing Company Inc., 519
Airport Road, Lititz, PA 17543; telephone (717) 569-0435, fax (717)
560-3725. 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: Raymond J. O'Neill, Aerospace
Engineer, New York Aircraft Certification Office, FAA, Engine and
Propeller Directorate, 10 Fifth St., Valley Stream, NY 11581; telephone
(516) 256-7505, fax (516) 568-2716.
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 95-ANE-03.'' 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. 95-ANE-03, 12 New England Executive Park,
Burlington, MA 01803-5299.
Discussion
On May 6, 1969, the Federal Aviation Administration (FAA) issued
Airworthiness Directive (AD) 69-09-03, Amendment 39-761 (34 FR 7371,
May 7, 1969), applicable to Sensenich Propeller Manufacturing Company
Inc. Models M76EMM, M7EMMS, 76EM8, and 76EM8S() metal propellers.
Revision 1, Amendment 39-808 (34 FR 12563, August 1, 1969); and
Revision 2, Amendment 39-1102 (35 FR 17030, November 5, 1970), were
subsequently
[[Page 62773]]
issued. That AD restricts operators from continuously operating the
propeller at engine speeds from 2,150 to 2,350 revolutions per minute
(RPM) and requires reworking the propeller by reducing blade thickness
and stiffness. That action was prompted by reports of propeller blade
tip failures due to continuous operation in an RPM range of relatively
high vibration stresses aggravated by impact-related mechanical damage
such as cuts, nicks, and dents. That condition, if not corrected, could
result in propeller blade tip fatigue failure, which can result in loss
of control of the aircraft.
Since the issuance of that AD, the FAA has received numerous
inquiries from the field concerning tachometer red arc restrictions on
certain Textron Lycoming O-360 series reciprocating engines with solid
crankshafts that are identified by suffixes having a digit ``4'' or
higher in the second position, e.g. A4AD, A4M, etc. The FAA has
determined that these additional engines, with solid crankshafts, have
vibration characteristics that closely approximate engines to which the
current AD does not apply, and can therefore also be removed from the
AD's applicability and requirement for tachometer restriction. Contrary
to the requirements of AD 69-09-03 R2, this AD would require reworking
all affected propellers, regardless of engine installation.
When propeller blade reworking is accomplished, the resulting
reduction in blade thickness and stiffness reduces blade second order-
first mode peak resonance RPM to lower values. The reworked propeller
(later adopted in production) is marked with the letter ``K.''
The FAA has reviewed and approved the technical contents of
Sensenich Propeller Service Bulletin (SB) No. R-13, dated April 11,
1969, that describes avoiding continuous operation between 2150 and
2350 RPM; and Sensenich Propeller SB No. R-14A, dated November 15,
1994, that describes reworking the propeller by reducing blade
thickness and stiffness in order to avoid propeller blade tip failures.
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 revise AD 69-09-03 R2 to remove from the AD's
applicability propellers installed on certain Textron Lycoming O-360
series reciprocating engines with solid crankshafts that are identified
by suffixes having a digit ``4'' or higher in the second position, e.g.
A4A, A4G, etc., and from the tachometer restriction, and update the
referenced Sensenich Propeller SB No. R-14 to R-14A, dated November 15,
1994.
There are approximately 100 propellers of the affected design that
may not have been modified to the ``K'' standard in the worldwide
fleet. The FAA estimates that 50 propellers installed on aircraft of
U.S. registry would be affected by this proposed AD, that it would take
approximately 2.5 work hours per propeller to accomplish the proposed
actions, and that the average labor rate is $60 per work hour. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $7,500. However, since this proposed rule
further restricts the applicability by exempting propellers installed
on certain Textron Lycoming engine models from the tachometer
restriction, there is a potential overall cost savings of $4,395,000,
if all the affected Sensenich propellers are installed on the newly
exempted engines.
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
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-1102 (35 FR
17030, November 5, 1970), and by adding a new airworthiness directive,
to read as follows:
Sensenich Propeller Manufacturing Company Inc.: Docket No. 95-ANE-
03. Revises AD 69-09-03, Amendment 39-1102.
Applicability: Sensenich Propeller Manufacturing Company Inc.
Models M76EMM, M7EMMS, 76EM8, and 76EM8S() metal propellers.
Paragraphs (a) and (b) of this airworthiness directive (AD) do not
apply to those propellers installed on the following solid
crankshaft Textron Lycoming O-360 series reciprocating engines: O-
360-A4A, -A4D, -A4G, -A4J, -A4K, -A4M, -A4N, -A4P, and -A5AD, or
additional engines identified by suffixes having a digit ``4'' or
higher in the second position. These propellers are installed on but
not limited to the following aircraft: Piper PA-28-180, PA-28-181,
American General Aircraft Holding Co. Inc. (formerly Gulfstream
American) AA-5 series, Beech B23 and C23, Cessna 172Q, Avions Pierre
Robin R-3000/160, and aircraft modified under various Supplemental
Type Certificates (STC's).
Note: This AD applies to each propeller 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 propellers 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 (f) to request approval from the Federal
Aviation Administration (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 propeller from the
applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent propeller blade tip fatigue failure, which can result
in loss of control of the aircraft, accomplish the following:
(a) Commencing with the next flight after the effective date of
this AD, do not operate the engine in continuous operation between
2,150 and 2,350 RPM.
(b) Within the next 25 hours time in service (TIS) after the
effective date of this AD, mark engine tachometer with a red arc
from 2150 RPM to 2350 RPM, in accordance with Sensenich Propeller
Service Bulletin (SB) No. R-13, dated April 11, 1969.
[[Page 62774]]
(c) For propellers with 500 or more total hours TIS, or unknown
TIS on the effective date of this AD, inspect, and rework or
replace, as necessary, within the next 50 hours TIS after the
effective date of this AD, in accordance with Sensenich Propeller SB
No. R-14A, dated November 15, 1994.
(d) For propellers with less than 500 total hours TIS on the
effective date of this AD, inspect, and rework or replace, as
necessary, prior to accumulating 550 total hours TIS, in accordance
with Sensenich Propeller SB No. R-14A, dated November 15, 1994.
(e) Mark with a suffix letter ``K'' propellers that have been
inspected, reworked, or replaced in accordance with Sensenich
Propeller SB No. R-14A, dated November 15, 1994, and found
satisfactory. New production propellers include change ``K'' or
subsequent changes.
(f) An alternative method of compliance or adjustment of the
initial 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 AD, if any, may be
obtained from the New York Aircraft Certification Office.
(g) 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 requirements of this AD can be accomplished.
Issued in Burlington, Massachusetts, on November 28, 1995.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 95-29843 Filed 12-6-95; 8:45 am]
BILLING CODE 4910-13-P