[Federal Register Volume 59, Number 78 (Friday, April 22, 1994)]
[Unknown Section]
[Page 0]
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: 

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

    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]
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