[Federal Register Volume 59, Number 78 (Friday, April 22, 1994)]
[Unknown Section]
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From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-9862]
Federal Register / Vol. 59, No. 78 / Friday, April 22, 1994 /
[[Page Unknown]]
[Federal Register: April 22, 1994]
VOL. 59, NO. 78
Friday, April 22, 1994
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-ANE-15; Amendment 39-8894; AD 94-09-06]
Airworthiness Directives; Hamilton Standard 14RF Series, 14SF
Series, and Hamilton Standard/British Aerospace 6/5500/F 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 Hamilton Standard 14RF series, 14SF series, and
Hamilton Standard/British Aerospace 6/5500/F series propellers. This
action requires a one-time inspection for cracks in the propeller blade
taper bore. This amendment is prompted by reports of two incidents
where the incident aircraft lost a portion of a propeller blade
inflight. The actions specified in this AD are intended to prevent loss
of a propeller blade due to cracks initiating in the blade taper bore,
that can result in possible aircraft damage, and possible loss of
aircraft control.
DATES: Effective May 2, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 2, 1994.
Comments for inclusion in the Rules Docket must be received on or
before June 21, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 94-ANE-15, 12 New England
Executive Park, Burlington, MA 01803-5299.
The service information referenced in this AD may be obtained from
Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010,
telephone (203) 654-3610. 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: Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (617) 238-7158, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
has received reports of two incidents where the incident aircraft lost
a portion of a propeller blade inflight. Investigation revealed the
presence of cracks initiating on the inside of the propeller blade
taper bore that led to fracture of the propeller blade. In one
incident, the fractured propeller blade penetrated the aircraft
fuselage, entering a passenger seat and causing decompression. This
condition, if not corrected, could result in loss of the propeller
blade due to cracks initiating in the blade taper bore, that can result
in possible aircraft damage, and possible loss of aircraft control.
The FAA has reviewed and approved the technical contents of
Hamilton Standard Alert Service Bulletin (ASB) No. 14RF-9-61-A66, No.
14RF-19-61-A34, 14RF-21-61-A53, 14SF-61-A73 and 6/5500/F-61-A27, all
dated April 18, 1994, that describe procedures for a ultrasonic shear
wave inspection of the blade taper bore for cracks.
Since an unsafe condition has been identified that is likely to
exist or develop on other propellers of the same type design, this
airworthiness directive (AD) is being issued to prevent loss of the
propeller blade due to cracks initiating in the blade taper bore, that
can result in possible aircraft damage, and possible loss of aircraft
control. This AD requires an ultrasonic shear wave inspection of the
blade taper bore for cracks, and replacement, if necessary, with a
serviceable propeller blade. Operators must perform this inspection
within 45 days after the effective date of this AD. The FAA has
determined that the affected propellers must be inspected in as short a
time period as possible to provide an acceptable level of safety. In
addition, the FAA has determined that 45 days provides that level of
safety considering available logistical support and replacement
propeller blades. The investigation into these failures continues, and
the FAA may consider further rulemaking based on future findings.
Propellers with cracks must be replaced prior to further flight. The
actions are required to be accomplished in accordance with the ASB's
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 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 94-ANE-15.'' 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 14 CFR part
39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
94-09-06 Hamilton Standard: Amendment 39-8894. Docket 94-ANE-15.
Applicability: Hamilton Standard Models 14RF-9, 14RF-19, 14RF-
21, and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19,
and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F
propellers installed on but not limited to Embraer EMB-120 and EMB
120-RT; SAAB-SCANIA SF 340B; Aerospatiale ATR42-100, ATR42-300,
ATR42-320, ATR72; DeHavilland DHC-8-100 series, DHC-8-300 Series;
Construcciones Aeronauticas SA (CASA) CN-235 and CN-235-100;
Canadair CL-215T and CL-415; and British Aerospace ATP airplanes.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of the propeller blade due to cracks initiating
in the blade taper bore, that can result in possible aircraft
damage, and possible loss of aircraft control, accomplish the
following:
(a) Within 45 days after the effective date of this AD, perform
an ultrasonic shear wave inspection for cracks in the blade taper
bore, in accordance with the following Hamilton Standard Service
Bulletins as applicable: 14RF-21-61-A53, dated April 18, 1994; 14SF-
61-A73, dated April 18, 1994; 14RF-19-61-A34, dated April 18, 1994;
14RF-9-61-A66, dated April 18, 1994; 6/5500/F-61-A27, dated April
18, 1994.
(b) Remove cracked propeller blades and replace with a
serviceable blade prior to further flight.
(c) 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, Boston Aircraft Certification
Office. The request should be forwarded through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Boston 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 Boston Aircraft Certification
Office.
(d) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the aircraft to a location where
the requirements of this AD can be accomplished.
(e) The inspection shall be done in accordance with the
following Hamilton Standard service documents:
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Document No. Pages Date
------------------------------------------------------------------------
14RF-21-61-A53................ 19 April 18, 1994.
Total pages: 19
14SF-61-A73................... 19 April 18, 1994.
Total pages: 19
14RF-19-61-A34................ 19 April 18, 1994.
Total pages: 19
14RF-9-61-A66................. 19 April 18, 1994.
Total pages: 19
6/5500/F-61-A27............... 19 April 18, 1994.
Total pages: 19
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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 Hamilton Standard, One Hamilton
Road, Windsor Locks, CT 06096-1010. 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.
(f) This amendment becomes effective on May 2, 1994.
Issued in Burlington, Massachusetts, on April 18, 1994.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 94-9862 Filed 4-20-94; 1:37 pm]
BILLING CODE 4910-13-P
