[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:

------------------------------------------------------------------------
            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