[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]



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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).

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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