[Federal Register Volume 61, Number 82 (Friday, April 26, 1996)]
[Proposed Rules]
[Pages 18520-18524]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-10060]



 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 61, No. 82 / Friday, April 26, 1996 / 
Proposed Rules  

[[Page 18520]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-ANE-30]


Airworthiness Directives; Hartzell Propeller Inc. HC-A3V, HC-B3M, 
HC-B3T, HC-B4M, HC-B4T, and HC-B5M Series Propellers

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to Hartzell Propeller Inc. (Hartzell) 
HC-A3V, HC-B3M, HC-B3T, HC-B4M, HC- B4T, and HC-B5M series propellers. 
This proposal would require hub replacement over a 10-year time period 
with a concurrent blade and blade clamp inspection. This proposal is 
prompted by reports of two propeller hub failures and one crack 
indication that occurred on Mitsubishi MU-2B-60 aircraft, the 
similarity of construction and load transfer paths between the Hartzell 
propeller models installed on the Mitsubishi MU-2 aircraft and 
Hartzell's 3-, 4-, and 5-bladed steel hub propeller models, several 
blade shank failures, and reports of cracks in blade clamps. The 
actions specified by the proposed AD are intended to prevent propeller 
hub, blade, or blade clamp failure, which can result in loss of 
aircraft control.

DATES: Comments must be received by June 25, 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. 95-ANE-30, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location between 8:00 a.m. and 4:30 p.m., Monday through Friday, 
except Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Hartzell Propeller Inc., One Propeller Place, Piqua, OH 
45356-2634. This information may be examined at the FAA, New England 
Region, Office of the Assistant Chief Counsel, 12 New England Executive 
Park, Burlington, MA.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal 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-30.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Assistant Chief Counsel, 
Attention: Rules Docket No. 95-ANE-30, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion

    The Federal Aviation Administration (FAA) has received reports of 
two hub failures and one crack indication that occurred on Hartzell 
Propeller Inc. (Hartzell) 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-2B-60 aircraft. This airworthiness directive (AD) action is prompted 
by those reports and the similarity of construction and load transfer 
paths between the Hartzell propeller models installed on the Mitsubishi 
MU- 2B-60 aircraft and other Hartzell 3-, 4-, and 5-bladed steel hub 
propeller model installations. This condition, if not corrected, could 
result in hub failure, which can result in loss of aircraft control.
    The FAA has determined that the most effective way to address all 
hub strength concerns is to require propeller hub replacement. The 
following are some of the benefits of a replacement program:
    1. Improved propeller hub metallurgy;
    2. Elimination of any surface decarburization in the pilot tube 
bore;
    3. Introduction of compressive residual stress in the pilot tube 
bore;
    4. Improved corrosion protection in the pilot tube bore;
    5. Improved surface finish in the pilot tube bore.
    Additionally, the referenced propeller models have been involved in 
several incidents of blade shank failures and have been reported to 
have cracks in the blade clamps. These conditions, if not corrected, 
could result in blade or blade clamp failure, which can result in loss 
of aircraft control. Therefore, the FAA has determined that a 
concurrent inspection of the blades and blade clamps at the time of hub 
replacement is necessary to detect cracks in either component.
    The FAA has issued previous AD's to address a similar condition for 
specific propeller models and aircraft combinations. This AD, however, 
addresses a broader population. Airworthiness directive 95-01-02 is 
applicable to Hartzell propeller models HC-B4TN-5(D,G,J)L/LT10282(B,K)- 
5.3R, HC-B4TN-5(D,G,J)L/

[[Page 18521]]

LT10282N(B,K)-5.3R, and HC-B4TN- 5(D,G,J)L/LT10282NS(B,K)-5.3R 
installed on Mitsubishi MU-2B- 26A, -36A, -40, -60; MU-2B-30 modified 
by Supplemental Type Certificate (STC) SA336GL-D & SA339GL-D; MU-2B-36 
Modified by STC SA2413SW and any other MU-2 Series aircraft which have 
the referenced propeller models installed. Airworthiness directive 95-
03-03 is applicable to Hartzell propeller models HC-B4TN-3/
T10173F(N)(B,K)-12.5 and HC-B4TN- 3A/T10173F(N)(B,K)-12.5 installed on 
Beech A100 and A100A aircraft. Operators of the referenced propellers 
and aircraft combinations must refer to the previous AD's for required 
actions.
    The FAA has reviewed and approved the technical contents of 
Hartzell Propeller Inc. Manual 118F, Revision 2, dated May 1992, pages 
15 to 19 and 57 through 96, for 3- and 4-bladed hub models, and Manual 
132A, Revision 2, dated June 1992, pages IV-5 to IV-11 and VII-1 to 
VII-46, for 5-bladed hub models, that describe procedures for 
disassembling and reassembling the propeller with a new hub; Hartzell 
Propeller Inc. Service Manual 202A, Revision 3, dated June 1995, pages 
201 through 215, that describes the magnetic particle inspection 
procedure for the propeller blade clamps; and Hartzell Propeller Inc. 
Service Bulletin No. 136H, dated March 12, 1993, that describes 
inspection procedures for the propeller blade bearing bores.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require, over a 10-year time period, propeller hub 
replacement with a concurrent blade and blade clamp inspection for 
Hartzell Propeller Inc. Models HC-A3VF-7 ( ), HC-B3TF-7( ), HC-B3MN-3( 
), HC-B3TN-2( ), HC-B3TN-3( ), HC-B3TN-5 ( ), HC-B4MN-5( ), HC-B4MP-3( 
), HC-B4TN-3( ), HC-B4TN-5( ), HC-B5MA-3( ), HC-B5MP-3( ), HC-B5MP-5( 
), HC-B3MN-5( ), HC- B3TN-4( ), HC-B4MP-4( ), and HC-B5MN-3( ) 
propellers. This propeller hub replacement program has been scheduled 
to require replacement of the most aged propeller hubs first. 
Additionally, the replacement program will accelerate the replacement 
of the 4 and 5 blade propeller hubs, while still replacing the 3 blade 
propeller hubs, with completion of the program in 10 years. Hartzell 
Propeller Inc. has advised the FAA that they will provide new hubs at 
special prices for the duration of this AD program. The actions would 
be required to be accomplished in accordance with the service documents 
described previously.
    There are approximately 24,320 propellers of the affected design in 
the worldwide fleet. The FAA estimates that 50% of the subject 
propellers are installed on aircraft of U.S. registry and that 75% will 
have the work done during normally scheduled propeller maintenance. For 
those who accomplish the AD action during normal propeller maintenance, 
the parts cost will average $1,955 with no additional labor. For those 
who accomplish the AD action by itself, the parts cost will average 
$2,174, plus approximately 27 work hours per propeller at an average 
labor rate of $60 per work hour. Based on these figures, the total cost 
impact on U.S. operators is estimated to be $29,363,360. The cost will 
vary between the 3-, 4-, and 5-bladed propeller configurations and the 
above data represents an average cost.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Hartzell Propeller Inc.: Docket No. 95-ANE-30.

    Applicability: Hartzell Propeller Inc. (Hartzell) Models HC-
A3VF-7( ), HC-B3TF-7( ), HC-B3MN-3( ), HC-B3TN-2( ), HC-B3TN-3( ), 
HC-B3TN-5 ( ), HC-B4MN-5( ), HC-B4MP-3( ), HC-B4TN-3( ), HC-B4TN-5( 
), HC-B5MA-3( ), HC-B5MP-3( ), HC-B5MP-5( ), HC-B3MN-5( ), HC-B3TN-
4( ), HC-B4MP-4( ), and HC-B5MN-3( ) propellers. These propellers 
are installed on but not limited to the following aircraft:

Aerospace Technologies of Australia PTY LTD N22B, N24A, N22S; Air 
Tractor, Inc. AT-301, AT-302, AT-400, AT-400A, AT-401, AT-402, AT-
502, AT-503, AT-802;
Agusta S.p.A. SF600, F.260;
Ayres Corporation S-2R, S2R-T11, S2R-T15, S2R-T34, S2R-T56, S2RHG-
T65;
Beech A36, 65-90, 65-90A, C90, B90, E90, C90A, F90, 100, 200, 200C, 
A200C, B200, B200C, 200T, 200CT, A200CT, B200T, B200CT, 65-80, 65-
A90-1, 65-A90-2, 65-A90-4, 99, 99A, A99A, B99, A200, C99, H90, 300, 
300LW, B300, B300C, 1900, 1900C, T34C, T34C-1;
Cessna 208, 208A, 208B, 421, 425, 441, 402, P210N;
Construcciones Aeronauticas, S.A. (CASA) C-212-CB, -CC, -CE, -CF;
deHavilland Aircraft Co., Ltd. D.H.114;
deHavilland Inc. DHC-2, DHC-3, DHC-4; DHC-6, 1, 100, 200, 300;
Empresa Brasileira de Aeronautica S/A Embraer EMB-110P1, EMB-110P2;
Fairchild Aircraft, Inc. SA26-AT, -T; SA226-AT, -TB;
Frakes Aviation (Gulfstream American ) G-73;
Great Lakes Aircraft Co. 2T-1A;
Helio HST-550, HST-550A;
Industrie Aeronautiche e Meccaniche Piaggio P.166DL3;
Israel Aircraft Industries, Ltd. Arava 101, 101B;
McDonnell Douglas DC-3 series;
McKinnon Enterprises, Inc. (Grumman) G-21E, G21-G;
Mitsubishi MU-2B series;
Pacific Aerospace Corporation, Ltd. FU24-954, FU2A-954;
Partenavia Costruzioni Aeronautiche S.p.A. AP68TP 300, AP68TP 600;
Pilatus Aircraft Ltd. PC-6/A-H2, /B1-H2, /B-H2, /B2-H2, /B2-H4, PC-
7;
Piper Aircraft Corporation PA31-T1, -T2, -T3; PA31P; PA42, -42-720, 
-42-720R;
Prop-Jets, Inc., Interceptor (Aero Commander) (Meyers) 400;
Schweizer Aircraft Corp. (Grumman) G-164A, G-164B, G-164B-34T, -15T; 
G-164D;
Short Bros. Limited & Harland Ltd. SC-7 series, SD3 series;

[[Page 18522]]

Twin Commander Aircraft Corp. 680T, V, 681, 690A, 690B, 690C, 695, 
695A;
Weatherly Aviation Company 620TP.

    Note 1: The parenthesis that appear in the propeller models 
indicate the presence or absence of additional letter(s) which vary 
the basic propeller hub model designation. This airworthiness 
directive (AD) is applicable regardless of whether these letters are 
present or absent on the propeller hub model designation.
    Note 2: The above is not a complete list of aircraft which may 
contain the affected Hartzell Propeller Inc. Models HC-A3VF-7  ( ), 
HC-B3TF-7( ), HC-B3MN-3( ), HC-B3TN-2( ), HC-B3TN-3( ), HC-3TN-5( ), 
HC-B4MN-5( ), HC-B4MP-3( ), HC-B4TN-3( ), HC-B4TN-5( ), HC-B5MA-3( 
), HC-B5MP-3( ), HC-B5MP-5( ), HC-B3MN-5( ), HC-B3TN-4( ), HC-B4MP-
4( ), and HC-B5MN-3( ) 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 3: This 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 use the authority 
provided in paragraph (h) to request approval from the Federal 
Aviation Administration (FAA). This approval may address either no 
action, if the current configuration eliminates the unsafe 
condition, or different actions necessary to address the unsafe 
condition described in this AD. Such a request should include an 
assessment of the effect of the changed configuration on the unsafe 
condition addressed by this AD. In no case does the presence of any 
modification, alteration, or repair remove any propeller from the 
applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent propeller hub, blade, or blade clamp failure, which 
can result in loss of aircraft control, accomplish the following:
    (a) This AD requires no action for operators with Hartzell 
propeller models HC-B4TN-5(D,G,J)L/LT10282(B,K)-5.3R, HC-B4TN-
5(D,G,J)L/LT10282N(B,K)-5.3R, and HC-B4TN-5(D,G,J)L/LT10282NS(B,K)-
5.3R installed on Mitsubishi MU-2B- 26A, -36A, -40, -60; MU-2B-30 
modified by Supplemental Type Certificate (STC) SA336GL-D & SA339GL-
D; MU-2B-36 Modified by STC SA2413SW and any other MU-2 Series 
aircraft which have the referenced propeller models installed. These 
operators must, however, comply with AD 95-01-02.
    (b) This AD requires no action for operators with Hartzell 
propeller models HC-B4TN-3/T10173F(N)(B,K)-12.5 and HC-B4TN-3A/
T10173F(N)(B,K)-12.5 installed on Beech A100 and A100A aircraft. 
These operators must, however, comply with AD 95-03-03.
    (c) Disassemble the propeller in accordance with Hartzell 
Propeller Inc. Service Manual 118F, Revision 2, dated May 1992, 
pages 15 to 19, for 3- and 4-bladed hub models, and Service Manual 
132A, Revision 2, dated June 1992, pages IV-5 to IV-11, for 5-bladed 
hub models, remove the hub from service, and replace the hub with a 
serviceable hub in accordance with the compliance schedule in Table 
1 of this AD.
    (1) Utilize Table 1 of this AD in accordance with the following 
example: Model HC-B3TN-3( ) series propellers, starting with serial 
numbers (S/N's) BU1 through BU377, require replacement before the 
end of December of calendar year 1996. Serial numbers BU378 through 
BU754 require hub replacement before the end of June of calendar 
year 1997, and so forth.
    (2) The affected hubs can only be replaced with serviceable hubs 
having a S/N not listed in Table 1 of this AD for that propeller 
model, or serviceable hubs having a S/N for which replacement is not 
yet required in accordance with Table 1 of this AD.
    (3) Some existing propeller hub S/N's include a suffix letter, 
such as an ``A.'' The presence or absence of this letter has no 
significance in determining compliance.
    (4) Since a hub may be used in various propeller models, the S/N 
and the model number shown in Table 1 of this AD may not coincide. 
Precedence is given to the hub S/N in determining compliance 
requirements. The hub model is only given as a reference.
    (5) Hub replacement must be accomplished by the end of the 
calendar month indicated at the top of the appropriate column in 
Table 1 of this AD. The S/N ranges in this table identify the 
propeller hubs that require replacement by the end of that month.

BILLING CODE 4190-13-P

[[Page 18523]]

Table 1
[GRAPHIC] [TIFF OMITTED] TP26AP96.000


BILLING CODE 4910-13-C

[[Page 18524]]

    (d) Perform a fluorescent penetrant inspection of blades for 
cracks in accordance with Hartzell Propeller Inc. Service Bulletin 
136H, dated March 12, 1993, prior to installing a serviceable hub.
    (e) Perform magnetic particle inspection of blade clamps for 
cracks in accordance with Hartzell Service Manual 202A, Revision 3, 
dated June 1995, pages 201 to 215, prior to installing a serviceable 
hub.
    (f) If cracks are found in either the blade or the blade clamps, 
prior to further flight replace with serviceable blade or blade 
clamps.
    (g) Reassemble the propeller in accordance with Hartzell 
Propeller Inc. Service Manual 118F, Revision 2, dated May 1992, 
pages 57 through 96, for 3- and 4-bladed hub models, and Service 
Manual 132A, Revision 2, dated June 1992, pages VII-1 to -46, for 5-
blade hub models.
    (h) 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 
Principal 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.

    (i) 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.

    Issued in Burlington, Massachusetts, on April 16, 1996.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 96-10060 Filed 4-25-96; 8:45 am]
BILLING CODE 4910-13-P