[Federal Register Volume 68, Number 5 (Wednesday, January 8, 2003)]
[Rules and Regulations]
[Pages 1001-1003]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-226]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-25-AD; Amendment 39-13014; AD 2003-01-03]
RIN 2120-AA64


Airworthiness Directives; Hartzell Propeller Inc. Model ( )HC-( 
)2Y( )-( ) 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 Hartzell Propeller Inc. model ( )HC-( )2Y( )-( ) 
propellers, with certain serial numbers (SN's) of two-bladed aluminum 
propeller hubs part numbers (P/N's) D-6522-1, D-6522-2, D-6529-1, and 
D-6559-3 installed. This action requires removal from service of those 
certain SN's of two-bladed aluminum propeller hubs and replacement with 
serviceable hubs. This amendment is prompted by a two-bladed aluminum 
propeller hub manufacturing quality control problem. The actions 
specified in this AD are intended to prevent in-flight propeller blade 
separation resulting in airframe and engine damage, and possible loss 
of the airplane.

DATES: Effective January 23, 2003. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of January 23, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before March 10, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-NE-25-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in this AD may be obtained from 
Hartzell Propeller Inc. Technical Publications Department, One 
Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 
778-4391. This information may be examined, by appointment, at the FAA, 
New England Region, Office of the Regional 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, Des Plaines, IL 60018; telephone (847) 294-
7031; fax (847) 294-7834.

SUPPLEMENTARY INFORMATION: On August 19, 2002, the FAA was notified by 
Hartzell Propeller Inc. that certain two-bladed aluminum propeller hub 
SN's installed in 2-bladed propellers were found to have subsurface 
discontinuities in the aluminum. Some of these hubs have been installed 
in propellers and some have been shipped as spares. The discontinuities 
were not removed during the propeller hub forging process, and could 
initiate fatigue cracking in the propeller hub arms. This final rule; 
request for comments, replaces affected hubs determined to be under 
higher stresses based on specific airplane installation, within 50 
hours time-since-new (TSN) or 12 months from the effective date of the 
AD, whichever occurs first, and affected hubs determined to be under 
lower stresses based on specific airplane installation, within 100 
hours TSN or 12 months from the effective date of this AD, whichever 
occurs first. This condition, if not corrected, could result in in-
flight propeller blade separation, airframe and engine damage, and 
possible loss of the airplane.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of 
Hartzell Propeller Inc. Alert Service Bulletin

[[Page 1002]]

(ASB) HC-ASB-61-259, dated September 4, 2002, that provides a SN list 
of 123 affected propeller hubs and describes procedures for hub 
replacement. This AD action has denoted the remaining 52 serial 
numbered propeller hubs that need to be replaced.

FAA's Determination of an Unsafe Condition and Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other propeller hubs of the same type design, this 
AD is being issued to prevent in-flight propeller blade separation 
resulting in airframe and engine damage, and possible loss of airplane 
control. This AD requires removal from service of certain two-bladed 
aluminum propeller hubs identified by SN and replacement with 
serviceable two-bladed aluminum propeller hubs. This action lists the 
remaining 52 serial numbered propeller hubs that need to be replaced. 
The actions are required to be done in accordance with the alert 
service bulletin described previously.

Immediate Adoption of This AD

    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NE-25-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would not have a substantial 
direct effect 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

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

2003-01-03 Hartzell Propeller Inc.: Amendment 39-13014. Docket No. 
2002-NE-25-AD.

Applicability

    This airworthiness directive (AD) is applicable to Hartzell 
Propeller Inc. model ( )HC-( )2Y( )-( ) propellers, with propeller 
hub part numbers (P/N's) D-6522-1, D-6522-2, D-6529-1, and D-6559-3, 
with the serial numbers (SN's) listed in the following Table 1:

                Table 1.--Applicable Propellers and Hubs
------------------------------------------------------------------------
           Propeller SN                  Hub SN             Hub P/N
------------------------------------------------------------------------
AU11115B..........................  A61365B           D-6522-1
AU11116B..........................  A61366B           D-6522-1
AU11117B..........................  A61367B           D-6522-1
AU11119B..........................  A61369B           D-6522-1
AU11125B..........................  A61375B           D-6522-1
AU11131B..........................  A61381B           D-6522-1
AU11134B..........................  A61384B           D-6522-1
AU11135B..........................  A61385B           D-6522-1
AY515B............................  A61397B           D-6522-2
AY516B............................  A61398B           D-6522-2
CH36140B..........................  A61409B           D-6529-1
CH36141B..........................  A61410B           D-6529-1
CH36151B..........................  A61420B           D-6529-1
CH36152B..........................  A61421B           D-6529-1
CH36153B..........................  A61422B           D-6529-1
CH36157B..........................  A61427B           D-6529-1
EU376B............................  A61443B           D-6559-3
CH36172B..........................  A61547B           D-6529-1
CH36159B..........................  A61553B           D-6529-1
CH36160B..........................  A61554B           D-6529-1
CH36162B..........................  A61556B           D-6529-1
CH36163B..........................  A61557B           D-6529-1
CH36165B..........................  A61560B           D-6529-1
CH36188B..........................  A61563B           D-6529-1
CH36193B..........................  A61568B           D-6529-1
CH36194B..........................  A61569B           D-6529-1

[[Page 1003]]

 
CH36195B..........................  A61570B           D-6529-1
CH36196B..........................  A61571B           D-6529-1
CH36178B..........................  A61573B           D-6529-1
CH36179B..........................  A61574B           D-6529-1
CH36181B..........................  A61576B           D-6529-1
CH36182B..........................  A61577B           D-6529-1
CH36183B..........................  A61578B           D-6529-1
CH36198B..........................  A61583B           D-6529-1
CH36199B..........................  A61584B           D-6529-1
CH36200B..........................  A61585B           D-6529-1
CH36201B..........................  A61586B           D-6529-1
CH36202B..........................  A61587B           D-6529-1
CH36203B..........................  A61588B           D-6529-1
CH36204B..........................  A61589B           D-6529-1
CH36205B..........................  A61590B           D-6529-1
CH36209B..........................  A61594B           D-6529-1
CH36211B..........................  A61596B           D-6529-1
CH36212B..........................  A61597B           D-6529-1
CH36213B..........................  A61598B           D-6529-1
CH36215B..........................  A61601B           D-6529-1
CH36216B..........................  A61602B           D-6529-1
AU11145B..........................  A61603B           D-6522-1
AU11147B..........................  A61605B           D-6522-1
AU11155B..........................  A61613B           D-6522-1
AY520B............................  A61743B           D-6522-2
AU11175B..........................  A61893B           D-6522-1
------------------------------------------------------------------------

    These propellers are installed on, but not limited to the 
following:

AMERICAN CHAMPION 8GCBC, 8KCAB
AERMACCHI S.p.A. S.208, S.208A
BEECH 95 series
BELLANCA 14-19-3, 14-19-3A
CESSNA 170 series, 172 series, 175 series, 177, A188A, A188B, T188C, 
310 series
DIAMOND AIRCRAFT DA-40
LAKE (REVO) LA-4, LA-4-200
MAULE Aerospace Technology, Inc. M(T)-7-235( ), M-5-235C, M-6-235, 
M(X)-7-235
MOONEY M20 series
Pilatus BRITTEN-NORMAN LTD BN-2 series, MK III, MK III-2, MK III-3
PIPER PA-23, PA-23-160, PA-24, PA-24-260, PA-25-260,
PA-28-140, PA-32-300, PA-32S-300, PA-34-200, PA-44-180T
SOCATA--Groupe AEROSPATIALE MS-200, MS 894A, MS 894E, TB-20, TB-21
Sky International Inc (Husky) A-1, S-1T, S-2A, S-2S (previous owners 
were Christian Industries; Aviat, Inc.; White International, LTD.)
Univair Aircraft Corporation 108 series (previous owner was Stinson)
Vulcanair S.p.A. P68 series (previous owner was Partenavia 
Construzioni Aeronautiche S.p.A)


    Note 1: The parentheses 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 is applicable regardless of whether these letters are 
present or absent on the propeller hub model designation.


    Note 2: 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 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

    Compliance with this AD is required as indicated, unless already 
done.
    To prevent in-flight propeller blade separation resulting in 
airframe and engine damage, and possible loss of the airplane, do 
the following:
    (a) For Piper PA-32( ) series airplanes with Lycoming 540 series 
engines rated at 300 horse power or higher, Britten Norman BN-2 
series airplanes with Lycoming 540 series engines, acrobatic 
airplanes including certificated acrobatic airplanes, military 
trainers, any airplanes routinely exposed to acrobatics usage, and 
airplanes used for agricultural purposes, remove affected hubs 
listed by SN in Table 1 of this AD within 50 hours time-since-new 
(TSN) or 12 months from the effective date of this AD, whichever 
occurs first, and replace with serviceable hubs, in accordance with 
paragraphs 3.A. through 3.B.(3) of ASB HC-ASB-61-259, dated 
September 4, 2002.
    (b) For airplanes other than those listed in paragraph (a) of 
this AD, remove affected hubs listed by SN in Table 1 of this AD 
within 100 hours TSN or 12 months from the effective date of this 
AD, whichever occurs first, and replace with serviceable hubs, in 
accordance with paragraphs 3.A. through 3.B.(3) of ASB HC-ASB-61-
259, dated September 4, 2002.
    (c) After the effective date of this AD, do not install any 
propeller assembly that has a hub with a P/N D-6522-1, D-6522-2, D-
6529-1, or D-6559-3, with a SN listed in Table 1 of this AD.

Alternative Methods of Compliance

    (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 (ACO). Operators must submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Chicago ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Chicago ACO.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
Sec. Sec.  21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (f) The propeller hub replacements must be done in accordance 
with Alert Service Bulletin Hartzell Propeller Inc. HC-ASB-61-259, 
dated September 4, 2002. 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. Technical Publications Department, One 
Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax 
(937) 778-4391. Copies may be inspected at the FAA, New England 
Region, Office of the Regional 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.

Effective Date

    (g) This amendment becomes effective on January 23, 2003.

    Issued in Burlington, Massachusetts, on December 31, 2002.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-226 Filed 1-7-03; 8:45 am]
BILLING CODE 4910-13-P