[Federal Register Volume 60, Number 41 (Thursday, March 2, 1995)]
[Rules and Regulations]
[Pages 11615-11617]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-4248]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-ANE-06; Amendment 39-9140; AD 95-03-03]


Airworthiness Directives; Hartzell Propeller Inc. Model HC-B4TN-
3/T10173F(N)(B,K)-12.5 and HC-B4TN-3A/T10173F(N)(B,K)-12.5 Propellers 
Installed on Beech A100 and A100A Aircraft

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. Model HC-B4TN-3/
T10173F(N)(B,K)-12.5 and HC-B4TN-3A/T10173F(N)(B,K)-12.5 propellers 
installed on Beech A100 and A100A aircraft. This action requires an 
initial and repetitive inspections, and specified rework or retirement, 
as necessary, of the propeller hub assemblies and propeller blades. 
This amendment is prompted by a determination that the current hub 
design and blade repair limits do not adequately protect against 
initiation of fatigue cracks in the propeller hub arm bore and do not 
prevent the resonant speed of the propeller from shifting into the 
permitted ground idle operating range. The actions specified in this AD 
are intended to prevent initiation of fatigue cracks in the propeller 
hub arm bore and subsequent progression to failure, with departure of 
the hub arm and blade, that may result in loss of aircraft control.

DATES: Effective March 17, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 17, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before May 1, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 95-ANE-06, 12 New England 
Executive Park, Burlington, MA 01803-5299.
    The service information referenced in this AD may be obtained from 
Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2634; 
telephone (513) 778-4200, fax (513) 778-4391. 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 Avenue, Room 232, Des Plaines, IL 60018; telephone 
(708) 294-7031, fax (708) 294-7834.

SUPPLEMENTARY INFORMATION: On December 22, 1994, the Federal Aviation 
Administration (FAA) issued airworthiness directive (AD) 95-01-02, 
applicable to Hartzell Model HC-B4TN-5(D,G,J)L/LT10282(B,K)-5.3R and 
HC-B4TN-5(D,G,J)L/LT10282N(B,K)-5.3R propellers installed on Mitsubishi 
MU-2 series aircraft. That AD requires new propeller blade repair 
limits and requires replacement of propeller hubs with new improved 
fatigue strength steel hubs which require inspection, and specified 
rework as necessary, at a repetitive interval of 3,000 hours time in 
service (TIS). That AD was prompted by a determination that the 
previous hub design and blade repair limits did not adequately protect 
against initiation of fatigue cracks in the propeller hub arm bore and 
did not prevent the resonant speed of the propeller from shifting into 
the permitted ground idle operating range when installed in Mitsubishi 
MU-2 Series aircraft. That condition, if not corrected, can result in 
fatigue cracks in the propeller hub arm bore and subsequent progression 
to failure, with departure of the hub arm and blade, that may result in 
loss of aircraft control.
    The FAA has determined, based on operating stresses and similarity 
of propeller type design, that similar fatigue cracks could occur in 
Hartzell Propeller Inc. Model HC-B4TN-3/T10173F(N)(B,K)-12.5 and HC-
B4TN-3A/T10173F(N)(B,K)-12.5 propellers installed on Beech A100 and 
A100A aircraft.
    The FAA has reviewed and approved the technical contents of 
Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. A196A, dated 
December 27, 1994, that describes procedures for initial and repetitive 
inspections, and specified rework or retirement, as necessary, of the 
propeller hub assemblies and propeller blades. [[Page 11616]] 
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Hartzell Propeller Inc. Model HC-B4TN-3/
T10173F(N)(B,K)-12.5 and HC-B4TN-3A/T10173F(N)(B,K)-12.5 propellers of 
the same type design, this AD is being issued to require initial and 
repetitive inspections, and specified rework or retirement, as 
necessary, of the propeller hub assemblies and propeller blades. 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 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 95 ANE-06.'' 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. 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:

95-03-03  Hartzell Propeller Inc.: Amendment 39-9140. Docket 95-ANE-
06.

    Applicability: Hartzell Propeller Inc. Model HC-B4TN-3/
T10173F(N) (B,K)-12.5 and HC-B4TN-3A/T10173F(N) (B,K)-12.5 
propellers installed on Beech A100 and A100A aircraft.

    Note: The parentheses indicate the presence or absence of an 
additional letter(s) which vary the basic propeller blade model 
designation. This airworthiness directive (AD) still applies 
regardless of whether these letters are present or absent on the 
propeller blade model designation.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent initiation of fatigue cracks in the propeller hub arm 
bore and subsequent progression to failure, with departure of the 
hub arm and blade, that may result in loss of aircraft control, 
accomplish the following:
    (a) For affected propellers with Time-Since-New (TSN) greater 
than or equal to 3,000 hours or TSN unknown on the effective date of 
this AD, within the next 150 hours Time-In-Service (TIS) or the next 
12 calendar months after the effective date of this AD, whichever 
occurs first, accomplish paragraphs (a)(1), (a)(2), and either 
(a)(3) or (a)(4) of this AD:
    (1) Remove affected propeller hub and blade assemblies from the 
aircraft for inspection, and accomplish specified rework or 
retirement, if necessary, in accordance with Hartzell Propeller Inc. 
Alert Service Bulletin (ASB) No. A196A, dated December 27, 1994.
    (2) Replace propeller blade assemblies that have been rejected 
or retired per paragraph (a)(1) of this AD with propeller blade 
assemblies inspected and reworked, if necessary, per paragraph 
(a)(1) of this AD or new blade assemblies. Thereafter, at intervals 
of 3,000 hours TIS or 60 calendar months, whichever occurs first, 
inspect, and rework or retire, if necessary, the blade assemblies in 
accordance with Hartzell Propeller Inc. ASB No. A196A, dated 
December 27, 1994.
    (3) Replace propeller hub assemblies that have been rejected or 
retired per paragraph (a)(1) of this AD with propeller hub 
assemblies that have had the hub arm bores inspected (and reworked 
as necessary), pilot tubes replaced, and have a metal impression 
stamp at the end of the hub serial number with suffix letter ``M'', 
followed by a number (1, 2, 3, etc.) to indicate the number of 
repetitive inspections performed in accordance with Hartzell ASB No. 
A196A, dated December 27, 1994. Thereafter, at intervals of 600 
hours TIS or 60 calendar months, whichever occurs first, inspect, 
and rework or retire, as necessary, the hub assemblies in accordance 
with Hartzell Propeller Inc. ASB No. A196A, dated December 27, 1994.
    (4) Replace propeller hub unit Part Number (P/N) 840-139 or P/N 
840-89, unless already accomplished, with a hub that has compressive 
rolled internal bearing bores, which is identified with the addition 
of a third letter ``A'' in the hub serial number prefix (e.g. 
``CDA1234''). Thereafter, at intervals of 3,000 hours TIS or 60 
calendar months, whichever occurs first, inspect, and rework or 
retire, as necessary, the hub assemblies in accordance with Hartzell 
Propeller Inc. ASB No. A196A, dated December 27, 1994.
    (b) For affected propellers with less than 3,000 hours TSN on 
the effective date of this AD, within the next 300 hours TIS, or 
prior to the accumulation of 3,150 hours TSN, or within the next 12 
calendar months after the effective date of this AD, whichever 
occurs first, accomplish paragraphs (a)(1), (a)(2), and either 
(a)(3) or (a)(4) of this AD. [[Page 11617]] 
    (c) Any blade repairs made after the effective date of this AD 
shall be accomplished in accordance with the procedures specified in 
Hartzell ASB No. A196A, dated December 27, 1994.
    (d) For propellers that experience a blade strike, as defined in 
paragraph (f) of this AD, after the effective date of this AD, prior 
to further flight, accomplish paragraphs (a)(1), (a)(2), and either 
(a)(3) or (a)(4) of this AD.
    (e) For propellers that have experienced a blade strike, as 
defined in paragraph (f) of this AD, prior to the effective date of 
this AD, within the next 100 hours TIS after the effective date of 
this AD, accomplish paragraphs (a)(1), (a)(2), and either (a)(3) or 
(a)(4) of this AD.
    (f) A blade strike is defined as a propeller having any blade(s) 
bent beyond the repair limits specified in Hartzell Propeller Inc. 
Standard Practices Manual 61-01-02, Revision 1, Pages 1104-1105, 
dated June 1994.
    (g) 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.

    (h) Except when propellers have experienced a blade strike, 
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.
    (i) The inspections and rework shall be accomplished in 
accordance with the following service documents:

------------------------------------------------------------------------
           Document No.                  Pages              Date        
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Hartzell Propeller Inc., ASB No.               1-5  Dec. 27, 1994.      
 A196A.                                                                 
    Total pages: 5.                                                     
Hartzell Propeller Inc., Standard        1104-1105  June 1994.          
 Practices Manual, 61-01-02,                                            
 Revision 1.                                                            
    Total pages: 2.                                                     
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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) 778-4200, fax 
(513) 778-4391. 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.
    (j) This amendment becomes effective on March 17, 1995.

    Issued in Burlington, Massachusetts, on February 7, 1995.
Donald F. Perrault,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 95-4248 Filed 3-1-95; 8:45 am]
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