[Federal Register: December 29, 2004 (Volume 69, Number 249)]
[Proposed Rules]
[Page 77961-77965]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29de04-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19955; Directorate Identifier 2004-NE-17-AD]
RIN 2120-AA64
Airworthiness Directives; Hartzell Propeller Inc. Propellers
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Hartzell Propeller Inc. propellers. This proposed AD would
require inspecting the propeller blades and other critical propeller
parts for corrosion and mechanical damage. This proposed AD results
from two events where a ``Z-shank'' blade failed and separated and the
results of teardown inspections that detected corrosion in the blade
bore. We are proposing this AD to detect corrosion and mechanical
damage that can cause failure of a propeller, which could result in
loss of control of the airplane.
DATES: We must receive any comments on this proposed AD by February 28,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-001.
Fax: (202) 493-2251.
[[Page 77962]]
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You can get the service information identified in this proposed AD
from Hartzell Propeller Inc. Technical Publications Department, One
Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937)
778-4391.
You may examine the comments on this proposed AD in the AD docket
on the Internet at http://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Tomaso DiPaolo, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate,
2300 East Devon Avenue, Des Plaines, IL 60018-4696; telephone (847)
294-7031; fax (847) 294-7834.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-19955;
Directorate Identifier 2004-NE-17-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of the
DMS Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit http://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the proposal, any comments
received, and any final disposition in person at the DMS Docket Offices
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Office (telephone (800) 647-5227) is located on
the plaza level of the Department of Transportation Nassif Building at
the street address stated in ADDRESSES. Comments will be available in
the AD docket shortly after the DMS receives them.
Discussion
On January 25, 2003, a Beech 95 airplane lost control after takeoff
when a 2.5-foot section of a Hartzell HC-92ZK-2/8447 propeller blade
separated. Examination of the fracture surfaces revealed the blade
failed because of fatigue cracking. The cracking began at corrosion
pits on the internal surface of the blade bore. On July 23, 2001, a
Beech 95A airplane suffered severe engine damage after a Hartzell HC-
92ZK-2B/8447 blade separated. Examination of the fracture surfaces
revealed the blade failed from fatigue cracks that started in an area
that had scratches and a gouge on the internal surface of the blade
bore.
The ``Z'' shank design propellers are often installed on airplanes
that do not have a mandatory periodic propeller maintenance program and
as a result, some propellers have not been maintained as specified in
the manufacturers instructions. Many of the propeller models have been
in service for more than 40 years. If they are not serviced to a recent
maintenance document, like that required by Hartzell Service Bulletin
136, revisions G, H, or I, those propellers are likely to contain
corrosion or mechanical damage in the blade bore.
After the event on January 24, 2003, the National Transportation
Safety Board (NTSB) issued a recommendation to require repetitive
inspections on all ``Z'' shank propellers at the time-between-overhaul
interval recommended by Hartzell Propeller Inc. Because most ``Z''
shank propellers are installed on airplanes that do not have mandatory
periodic maintenance, we are proposing a onetime inspection of ``Z''
shank propellers. We are also proposing a onetime inspection of ``P,''
``R,'' and ``W'' shank propellers because of their similarities to the
``Z'' shank propellers. This condition, if not corrected, could result
in failure and separation of a propeller blade, which could result in
loss of control of the airplane. In addition, while the propeller is
disassembled for the blade bore inspection, we are taking this
significant opportunity to also inspect and remove corrosion and
damaged areas in other critical propeller parts.
We are also proposing requirement to report the inspection
findings. The affected propellers are aging and there is no regulatory
requirement for any type of repetitive safety inspections. We have been
reviewing service difficulty information gathered over the past ten
years and have received reports of ``old'' propellers (some over forty
years of age), which have not had an overhaul, that are corroded,
cracked, or beyond airworthy limits.
Relevant Service Information
We have reviewed and approved the technical contents of Hartzell
Propeller Inc. Service Bulletin (SB) 136, Revision G, dated November
15, 1991; Revision H, dated March 12, 1993; and Revision I, dated April
25, 2003. Those SBs describe procedures for disassembling, cleaning,
inspecting, and reworking the propeller blades. We have also reviewed
the applicable Hartzell overhaul manuals that we reference for the
various additional inspections.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
a onetime inspection of the bore of the propeller blade and other
critical propeller parts, and if necessary, removing any corrosion or
mechanical damage:
Within 12 months after the effective date of the proposed
AD, if the propeller was not overhauled within the past 25 years.
Within 18 months after the effective date of the proposed
AD, if the propeller was not overhauled within the past 20 years.
Within 24 months after the effective date of the proposed
AD, if the propeller was not overhauled within the past 15 years.
Within 36 months after the effective date of the proposed
AD, if the propeller was not overhauled within the past 10 years.
The proposed AD would require you to use the service information
described previously to perform these actions.
Costs of Compliance
There are about 1,700 Hartzell propeller assemblies of the affected
design in the worldwide fleet. We estimate that 1,200 propeller
assemblies installed on airplanes of U.S. registry would be affected by
this proposed AD. We also estimate that it would take about 20 work
hours per propeller assembly to perform the proposed actions, and that
the average labor rate is $65 per work hour. Required parts would cost
about $450 per propeller assembly. Based on these figures, we
[[Page 77963]]
estimate the total cost of the proposed AD to U.S. operators to be
$2,100,000.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this proposal and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
Hartzell Propeller, Inc.: Docket No. FAA-2004-19955; Directorate
Identifier 2004-NE-17-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by February 28,
2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to Hartzell propeller
assemblies with hub model part number (P/N) series specified in
Table 1 of this AD. These propellers are installed on, but not
limited to, the aircraft listed in Table 2 of this AD.
Table 1.--List of Applicable Propeller Assemblies by Hub Model P/N
Series
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HC-92W Series.
BHC-92W Series.
HC-92Z Series.
BHC-92Z Series.
HC-B3P Series.
HC-B3R Series.
HC-B3W Series.
BHC-B3W Series.
HA-B3Z Series.
HC-B3Z Series.
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Table 2.--List of Airplanes That Might Use an Affected Propeller
Assembly
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Aircraft manufacturer Aircraft model
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AERMACCHI (AERONAUTICA MACCHI)... AM-3C
AERO COMMANDER................... 560-F680, 680E, 680F, 680FL, 680FLP,
720
AEROSPATIALE (MORANE SAULNIER)... 733
AEROSTAR AIRCRAFT CORP........... 360
AEROTEK II, INC. (CALLAIR)....... B1A (CALLAIR)
AIR & SPACE...................... 18, 18A
BEECH............................ 18 Series
C45
35 Series
A65, 65, 65-80, 65-A80, 65-B80, 65-88
95, B95, B95A, D95A, E95 70
C18S [(C-45(A, F), UC-45(B, F), AT-7
(A, B, C), JRB-(1, 2, 3, 4), SNB-
2(C)]
C18S, AT-11
C-45G,C-45H; TC-45G,H,J; RC-45J
D18S,E18S, G18S, H18; 3N, 3NM, 3TM
E50, F50, G50, H50, J50
BUSHMASTER AIRCRAFT CORP......... BUSHMASTER 2000
CESSNA........................... 172
175, 175A
190, 195, A, B
421, 421A
A185E, A185F (SEAPLANES ONLY)
CESSNA........................... T50
DE HAVILLAND CANADA.............. DHC-2 MKI
DORNIER.......................... DO28D, DO28D-1
FOUND BROTHERS................... 100
FOUND BROTHERS................... FBA-2C
GOODYEAR (LOCKHEED MARTIN)....... GZ20, GZ20A
GRUMMAN (GULFSTREAM AERO.)....... G44, G44A
GRUMMAN (MCKINNON)............... G21A
[[Page 77964]]
HELIO............................ H-250
H-295, HT-295 (U-10D)
H-395 (L-28A, U-10B)
H-500
ICA (ROMANIA).................... IAR-831
JOBMASTER........................ DGA-15P
KWAD............................. SUPER-V
LAKE (REVO)...................... LA-4
LOCKHEED......................... 12A
MESSERSCHMITT.................... 207
MOONEY........................... M20A
NAVY............................. N3N-3
NORD............................. 3400, 3402
PACIFIC AEROSPACE (FLETCHER)..... FU-24, FU-24A
PIAGGIO.......................... P-166B, C
PILATUS.......................... PC-6/350; PC-6/350-H1, -H2
PIPER............................ PA-23
PA-24
PA-25
PROCAER.......................... F15/B
REVO (COLONIAL).................. C-2
SAAB............................. 91D SAFIR
SCHWEIZER (GRUMMAN).............. G-164
SIMMERING GRAZ PAUKER A.G........ SGP222
SPARTON.......................... 7W
UTVA............................. 66
WDL AVIATION (formerly WDL An Airship
FLUGDIENST).
WEATHERLY........................ 201B, 201C, 620, 620A, 620C
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Unsafe Condition
(d) This AD results from two events where a ``Z-shank'' blade
failed and separated and the results of teardown inspections that
detected corrosion in the blade bore. We are issuing this AD to
detect corrosion and mechanical damage that can cause failure of a
propeller, which could result in loss of control of the airplane.
Compliance: (e) You are responsible for having the actions
required by this AD performed within the compliance times specified
unless the actions have already been done.
Aircraft With Experimental Type Certificates
(f) We recommend that you comply with the inspection
requirements of this AD, if you have an aircraft with an
experimental type certificate, and you have a propeller hub model
listed in this AD installed on that aircraft.
Inspection of the Propeller
(g) If the time-since-overhaul (TSO) of the propeller is 10
years or fewer on the effective date of this AD, no further action
is required.
(h) If the propeller assembly was inspected using Hartzell
Service Bulletin (SB) No. 136, Revision I, dated April 25, 2003;
Revision H, dated March 12, 1993; or Revision G, dated November 15,
1991; no further action is required.
(i) If the TSO of the propeller assembly is more than 10 years
on the effective date of this AD, or if the TSO is unknown, or if
the propeller has not complied with Hartzell SBs HC-SB-61-136,
Revision I, dated April 25, 2003; or Service Bulletin 136, Revision
H, dated March 12, 1993; or Revision G, dated November 15, 1991;
perform the actions specified in Table 3 of this AD. Use the
compliance times specified in Table 3 of this AD. Information on
inspecting the propeller assembly for cracks, corrosion or pits,
nicks, scratches, wear, blade minimum dimensions, and damage in the
blade balance bore can be found in the applicable Hartzell overhaul
manual.
Table 3.--Compliance Times for Onetime Inspection
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If the TSO of the propeller
assembly on the effective Then . . . Perform the
date of this AD is . . . inspection . . .
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(1) More than 25 years or (a) Disassemble and Within 12 months
the TSO is not known. clean the propeller after the effective
assembly.. date of this AD.
(b) Inspect for
cracks, corrosion
or pits, nicks,
scratches, wear,
blade minimum
dimensions, and
damage in the blade
balance hole..
(c) Inspect and
rework the
propeller blade
bore. Use 3.A. of
the Accomplishment
instructions of
Hartzell SB No.
136, Revision I,
dated April 26,
2003.
(d) Repair and
replace with
serviceable parts,
as necessary.
(e) Reassemble and
test.
[[Page 77965]]
(2) Twenty-one to 25 years.. (a) Disassemble and Within 18 months
clean the propeller after the effective
assembly. date of this AD.
(b) Inspect for
cracks, corrosion
or pits, nicks,
scratches, wear,
blade minimum
dimensions, and
damage in the blade
balance hole..
(c) Inspect and
rework the
propeller blade
bore. Use 3.A. of
the Accomplishment
instructions of
Hartzell SB No.
136, Revision I,
dated April 26,
2003.
(d) Repair and
replace with
serviceable parts,
as necessary.
(e) Reassemble and
test.
(3) Sixteen to 20 years..... (a) Disassemble and Within 24 months
clean the propeller after the effective
assembly. date of this AD.
(b) Inspect for
cracks, corrosion
or pits, nicks,
scratches, wear,
blade minimum
dimensions, and
damage in the blade
balance hole..
(c) Inspect and
rework the
propeller blade
bore. Use 3.A. of
the Accomplishment
instructions of
Hartzell SB No.
136, Revision I,
dated April 26,
2003.
(d) Repair and
replace with
serviceable parts,
as necessary.
(e) Reassemble and
test.
(4) Eleven to 15 years...... (a) Disassemble and Within 36 months
clean the propeller after the effective
assembly.. date of this AD.
(b) Inspect for the
following
conditions: cracks,
corrosion or pits,
nicks, scratches,
wear, blade minimum
dimensions, and
damage in the blade
balance hole..
(c) Inspect and
rework the
propeller blade
bore. Use 3.A. of
the Accomplishment
instructions of
Hartzell SB No.
136, Revision I,
dated April 26,
2003.
(d) Repair and
replace with
serviceable parts,
as necessary.
(e) Reassemble and
test.
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Propeller Overhaul
(j) Performing an overhaul of the propeller assembly after the
effective date of this AD constitutes compliance with the
requirements specified in this AD. The latest applicable Overhaul
Manual issued by Hartzell Propeller Inc. contains information on
overhauling a propeller assembly.
(k) The TSO only changes if you overhaul the propeller assembly
while performing the requirements specified in this AD.
Reporting Requirements
(l) Report inspection results to the Manager, Chicago Aircraft
Certification Office, FAA, Small Airplane Directorate, 2300 East
Devon Ave., Des Plaines, IL 60018, within 15 working days of the
inspection. The Office of Management and Budget (OMB) approved the
reporting requirements assigned OMB control number 2120-0056.
Alternative Methods of Compliance (AMOCs)
(m) The Manager, Chicago Aircraft Certification Office has the
authority to approve alternative methods of compliance for this AD
if requested using the procedures found in 14 CFR 39.19.
Related Information
(n) None.
Issued in Burlington, Massachusetts, on December 21, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 04-28492 Filed 12-28-04; 8:45 am]
BILLING CODE 4910-13-P