[Federal Register Volume 63, Number 157 (Friday, August 14, 1998)]
[Rules and Regulations]
[Pages 43615-43617]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-21651]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-53-AD; Amendment 39-10706; AD 98-17-04]
RIN 2120-AA64
Airworthiness Directives; Hartzell Propeller Inc. HC-E4A-3(A,I,J)
Series Propellers
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Hartzell Propeller Inc. HC-E4A-3(A,I,J) series
propellers. This action requires a one-time inspection of the propeller
blade counterweight clamps for thread damage in the bolt holes, and, if
necessary, replacement with serviceable parts. This amendment is
prompted by a report of a counterweight clamp bolt hole thread failure
that resulted in the separation of the counterweight and the separation
of a blade following impact with the counterweight. The actions
specified in this AD are intended to prevent propeller blade
counterweight clamp bolt hole thread failure, which can result in
counterweight and propeller blade separation, and possible damage to
the aircraft.
DATES: Effective August 31, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 31, 1998.
Comments for inclusion in the Rules Docket must be received on or
before October 13, 1998.
[[Page 43616]]
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 98-ANE-53-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``engineprop@faa.dot.gov''. Comments sent via the Internet must contain
the docket number in the subject line.
The service information referenced in this AD may be obtained from
Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2634,
ATTN: Product Support; telephone (937) 778-4200, fax (937) 778-4321.
This information may be examined at the FAA, New England Region, Office
of the Regional 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.
FOR FURTHER INFORMATION CONTACT: Tomaso DiPaolo, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate,
2300 East Devon Ave., Des Plaines, IL 60018; telephone (847) 294-7031,
fax (847) 294-7834.
SUPPLEMENTARY INFORMATION: On May 4, 1998, a Raytheon (Beech) 1900D
aircraft experienced a Hartzell Propeller Inc. HC-E4A-3(A,I,J) series
propeller blade separation in Syracuse, NY. The investigation revealed
that a propeller counterweight clamp bolt pulled out from the
counterweight clamp assembly and the counterweight separated inflight.
The departing counterweight broke the adjacent propeller blade about 12
inches from the hub. Inspection of the counterweight clamp bolt holes
revealed that threads in the counterweight clamp bolt hole failed and
that the threads had been damaged by cross threading. During the
failure investigation, additional counterweight clamps with damaged
threads were found. This condition, if not corrected, could result in
propeller blade counterweight clamp bolt hole thread failure, which can
result in counterweight and propeller blade separation, and possible
damage to the aircraft.
The FAA has reviewed and approved the technical contents of
Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. HC-ASB-61-237,
dated July 17, 1998, that describes procedures for inspection of the
propeller blade counterweight clamps for thread damage in the bolt
holes, and, if necessary, replacement with serviceable parts.
Since an unsafe condition has been identified that is likely to
exist or develop on other propellers of the same type design, this AD
is being issued to prevent propeller blade counterweight clamp bolt
hole thread failure. This AD requires a one-time inspection of the
propeller blade counterweight clamps for thread damage in the bolt
holes. Based upon the results of the inspection, operators must, if
necessary, replace propeller blade counterweight clamps with
serviceable parts.
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 98-ANE-53-AD.'' 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 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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
98-17-04 Hartzell Propeller Inc.: Amendment 39-10706. Docket 98-
ANE-53-AD.
Applicability: Hartzell Propeller Inc. HC-E4A-3(A,I,J) series
propellers, with serial numbers (S/Ns) HJ1 through HJ1040, that have
been previously overhauled or have had a counterweight clamp bolt
removed for any reason. These propellers are installed on but not
limited to Raytheon (Beech) 1900D series aircraft.
Note 1: This airworthiness directive (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
[[Page 43617]]
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 request approval for an
alternative method of compliance in accordance with paragraph (b) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent propeller blade counterweight clamp bolt hole thread
failure, which can result in counterweight and propeller blade
separation, and possible damage to the aircraft, accomplish the
following:
(a) Perform a one-time inspection of the propeller blade
counterweight clamps for thread damage in the bolt holes in
accordance with the Accomplishment Instructions of Hartzell
Propeller Inc. Alert Service Bulletin (ASB) No. HC-ASB-61-237, dated
July 17, 1998, as follows:
(1) For propellers with 2,500 or more hours time in service
(TIS) since last overhaul, inspect within 300 hours time in service
(TIS), or 45 days after the effective date of this AD, whichever
occurs first.
(2) For all other propellers inspect within 600 hours TIS, or 90
days after the effective date of this AD, whichever occurs first.
(3) For propeller blade counterweight clamps that do not meet
the return to service criteria stated in the ASB, prior to further
flight remove from service propeller blade counterweight clamps and
replace and reassemble with serviceable parts in accordance with the
ASB.
(4) For propeller blade counterweight clamps that meet the
return to service criteria stated in the ASB, reassemble in
accordance with the ASB.
(b) 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, Chicago Aircraft Certification
Office. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then
send it to the Manager, Chicago Aircraft Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Chicago Aircraft Certification
Office.
(c) 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.
(d) The actions required by this AD shall be done in accordance
with the following Hartzell Propeller Inc. service documents:
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Document No. Pages Date
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HC-ASB-61-237...................... 1-20 July 17, 1998
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Total pages: 20.
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 Hartzell Propeller Inc., One
Propeller Place, Piqua, OH 45356-2634, ATTN: Product Support;
telephone (937) 778-4200, fax (937) 778-4321. Copies may be
inspected at the FAA, New England Region, Office of the Regional
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.
(e) This amendment becomes effective on August 31, 1998.
Issued in Burlington, Massachusetts, on August 5, 1998.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-21651 Filed 8-13-98; 8:45 am]
BILLING CODE 4910-13-U
