[Federal Register Volume 61, Number 146 (Monday, July 29, 1996)]
[Rules and Regulations]
[Pages 39309-39311]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-18765]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-ANE-18; Amendment 39-9697; AD 96-15-04]
Airworthiness Directives; Hartzell Propeller Inc. HC-B3TN, HC-
B5MP, HC-E4A, and HC-D4N 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 certain propeller blades, identified by serial number,
installed on Hartzell Propeller Inc. HC-B3TN, HC-B5MP, HC-E4A, and HC-
D4N series propellers. This action requires, within specified hours
time in service after the effective date of this AD, a one-time
fluorescent dye penetrant inspection of a twelve-inch long area on both
the face and camber sides of propeller blade shanks for forging flaws
or cracks, and replacement of defective propeller blades with
serviceable parts. In addition, this action requires this inspection
prior to further flight for propellers that experience sudden or
unusual vibration. This amendment is prompted by a report of an
inflight propeller blade separation. The actions specified in this AD
are intended to prevent propeller blade separation caused by propeller
blade shank cracks emanating from forging flaws, which could result in
loss of control of the aircraft.
DATES: Effective July 29, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 29, 1996.
Comments for inclusion in the Rules Docket must be received on or
before September 27, 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. 96-ANE-18, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be
submitted to the Rules Docket by using the following Internet address:
``[email protected]''. All comments must contain the
Docket No. in the subject line of the comment.
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 (513) 778-4388, fax (513) 778-4321.
This information may be examined 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.
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: The Federal Aviation Administration (FAA)
received a report of an inflight blade separation of a Hartzell
Propeller Inc. Model HC-D4N-5C/D9327K propeller installed on a Short
Brothers plc S-312 Tucano military aircraft in the United Kingdom. The
investigation revealed that the propeller blade separation resulted
from a crack emanating from a forging flaw in the propeller blade. This
condition, if not corrected, could result in propeller blade separation
caused by propeller blade shank cracks emanating from forging flaws,
which could result in loss of control of the aircraft.
The FAA has reviewed and approved the technical contents of
Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. HC-ASB-61-220,
dated July 8, 1996, that contains a list of affected propellers by
model and serial number, and describes procedures for a one-time
fluorescent dye penetrant inspection of a twelve-inch long area on both
the face and camber sides of propeller blade shanks for forging flaws
or cracks. The propeller blades identified by serial numbers are
limited to those manufactured between March 1992 and June 1996, and
represent a group of aluminum propeller blade designs, which are:
D9327(), D9512A(), LT10673(), LT10673()-2Q, M10282()+6, M10876(),
LT10876()-2Q, and E10477K.
Since an unsafe condition has been identified that is likely to
exist or develop on other propeller blades manufactured from the same
forging die and same forging process, this AD is being issued to
prevent propeller blade separation due to propeller blade shank cracks
emanating from forging flaws, which could result in loss of control of
the aircraft. This AD requires a one-time fluorescent dye penetrant
inspection of a twelve-inch long area on both the face and camber sides
of propeller blade shanks for forging flaws or cracks, and replacement
of flawed propeller blades with serviceable parts. For propellers
installed on agricultural or acrobatic aircraft, such as certain Air
Tractor, Inc., Ayres Corporation, Norman, Pilatus Aircraft Ltd., PZL,
and Short Brothers Ltd. aircraft, compliance is required within 10
hours TIS after the effective date of this AD. These agricultural and
acrobatic aircraft operate in an environment that subjects the
propeller to high loads. For all other propellers, regardless of
aircraft installation, compliance is required within 60 hours TIS after
the effective date of this AD. In addition, this AD requires the
fluorescent dye penetrant inspection prior to further flight for
propellers that have not been inspected in accordance with this AD,
which experience a sudden or unusual vibration. This compliance prior
to further flight is necessary because a timely investigation of such
conditions can prevent propeller failure. The actions are required to
be accomplished in accordance with the ASB 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
[[Page 39310]]
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 96-ANE-18.'' 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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
96-15-04 Hartzell Propeller Inc.: Amendment 39-9697. Docket 96-ANE-
18.
Applicability: Hartzell Propeller Inc. HC-B3TN, HC-B5MP, HC-E4A,
and HC-D4N series propellers, equipped with propeller blades
identified by serial number in Hartzell Propeller Inc. Alert Service
Bulletin (ASB) No. HC-ASB-61-220, dated July 8, 1996. The propeller
blades identified by serial numbers are limited to those
manufactured between March 1992 and June 1996, and represent a group
of aluminum propeller blade designs, which are: D9327(), D9512A(),
LT10673(), LT10673()-2Q, M10282()+6, M10876(), LT10876()-2Q, and
E10477K. These propellers are installed on but not limited to the
following aircraft:
Aerospatiale Nord 262 series (STC modified),
Air Tractor, Inc. AT-502, AT-503, and AT-802 series,
Antonov AN-28 series,
Ayres S2R series,
McDonnell Douglas DC-3 series (STC modified),
Norman Aeroplane NAC 6 series,
Pilatus Aircraft Ltd. PC-7 mk II, PC-9, and PC-12 series,
PZL PZL-M18,
Short Brothers plc S-312 Tucano (military), SD3, and C-23 (military)
series.
Twin Commander Aircraft Corp. 690 and 695 series (STC modified).
Note 1: The above is not an exhaustive list of aircraft which
may contain the affected Hartzell Propeller Inc. Models HC-B3TN, HC-
B5MP, HC-E4A, and HC-D4N series propellers because of installation
approvals made by, for example, Supplemental Type Certificate or
field approval under FAA Form 337 ``Major Repair and Alteration.''
It is the responsibility of the owner, operator, and person
returning the aircraft to service to determine if an aircraft has an
affected propeller.
Note 2: 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 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 (d) 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 separation caused by propeller blade
shank cracks emanating from forging flaws, which could result in
loss of control of the aircraft, accomplish the following:
(a) For propellers installed on agricultural or acrobatic
aircraft, such as Air Tractor, Inc., AT-502A, AT-503, AT-802; Ayres
Corporation S2R-T65, S2RHG-265; Norman Aeroplane NAC 6; Pilatus
Aircraft Ltd. PC-7 mk II, PC-9; PZL PZL-M18, and Short Brothers Ltd.
S-312 Tucano (military) aircraft, accomplish the following:
(1) Within 10 hours TIS after the effective date of this AD,
disassemble the propeller and perform a one-time fluorescent dye
penetrant inspection of a twelve-inch long area on both the face and
camber sides of propeller blade shanks for forging flaws or cracks,
in accordance with Hartzell Propeller Inc. ASB No. HC-ASB-61-220,
dated July 8, 1996.
(2) Prior to further flight, remove from service propeller
blades exhibiting forging flaws or cracks and replace with
serviceable parts.
(b) For all other propellers, regardless of aircraft
installation, accomplish the following:
(1) Within 60 hours TIS after the effective date of this AD,
disassemble the propeller and perform a one-time fluorescent dye
penetrant inspection of a twelve-inch long area on both the face and
camber sides of propeller blade shanks for forging flaws or cracks
in accordance with Hartzell Propeller Inc. ASB No. HC-ASB-61-220,
dated July 8, 1996.
(2) Prior to further flight, remove from service propeller
blades exhibiting forging flaws or cracks and replace with
serviceable parts.
(c) For propellers that have not been inspected in accordance
with this AD, which experience a sudden or unusual vibration,
accomplish the following:
(1) Prior to further flight, disassemble the propeller and
perform a one-time fluorescent dye penetrant inspection of a twelve-
inch long area on both the face and camber sides of propeller blade
shanks for forging flaws or cracks in accordance with Hartzell
Propeller Inc. ASB No. HC-ASB-61-220, dated July 8, 1996.
(2) Prior to further flight, remove from service propeller
blades exhibiting forging flaws or cracks and replace with
serviceable parts.
(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, Chicago 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, Chicago 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 Chicago Aircraft Certification
Office.
(e) Except for propellers subject to paragraph (c) of this AD,
special flight
[[Page 39311]]
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.
(f) The actions required by this AD shall be done in accordance
with the following Hartzell Propeller Inc. service document:
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Document No. Pages Date
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ASB No. HC-ASB-61-220.............. 1-24 July 8, 1996.
Total pages: 24.
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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 Hartzell Propeller Inc., One
Propeller Place, Piqua, OH 45356-2634; telephone (513) 778-4388, fax
(513) 778-4321. 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 July 29, 1996.
Issued in Burlington, Massachusetts, on July 17, 1996.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 96-18765 Filed 7-24-96; 4:53 pm]
BILLING CODE 4910-13-P