[Federal Register: September 9, 2005 (Volume 70, Number 174)]
[Rules and Regulations]
[Page 53543-53547]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09se05-3]
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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;
Amendment 39-14252; AD 2005-18-12]
RIN 2120-AA64
Airworthiness Directives; Hartzell Propeller Inc. Propellers
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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[[Page 53544]]
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Hartzell Propeller Inc. propellers. This AD requires inspecting
the propeller blades and other critical propeller parts for corrosion
and mechanical damage. 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.
DATES: This AD becomes effective October 14, 2005. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of October 14, 2005.
ADDRESSES: You can get the service information identified in this 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 AD docket on the Internet at http://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tim Smyth, Aerospace Engineer, Chicago
Aircraft Certification Office, FAA, Small Airplane Directorate, 2300
East Devon Avenue, Des Plaines, IL 60018-4696; telephone (847) 294-
7132; fax (847) 294-7834.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to certain Hartzell Propeller Inc. propellers. We published the
proposed AD in the Federal Register on December 29, 2004 (69 FR 77961).
That action proposed to require inspecting the propeller blades and
other critical propeller parts for corrosion and mechanical damage.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
System 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.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Recommendation To Modify the AD To Exclude Certain Propellers
One commenter recommends that this AD be modified to exclude
propellers that have been examined in connection with AD 95-11-08
within the last five years. The commenter feels his propeller has been
adequately inspected and he does not want to remove the propeller at
this time. Doing so could introduce potential oil leaks that are
difficult and expensive to seal.
We do not agree. AD 95-11-08 corrects an unsafe condition in blade
clamp screws and on the outside surface of the blade shank. The
requirements of that AD are not equivalent to the actions mandated by
this AD. This AD mandates inspections of the entire propeller assembly,
especially the inside surface area of the blade balance hole.
Requests To Provide More Clarity in the Compliance Section
One commenter requests that we clarify the compliance section. We
agree, and reworded it. We changed the title for Table 1 to ``List of
Applicable Propeller Assemblies by Hub Model Series''.
The same commenter suggests we should be more specific in detailing
the inspection method in Table 3 if we intend a more thorough
inspection. We agree. We have changed (b) in Table 3 to state ``Perform
visual and nondestructive inspections of propeller components for
cracks, corrosion or pits, nicks, scratches, wear, blade minimum
dimensions, and damage in the blade balance hole.''
The same commenter states that if the FAA intends to detect small
or light cracks in the hub or blade clamps, we should consider adding
the following text to Table 3, under the ``Then:'' column, under (c):
``Perform a magnetic-particle-inspection of the hub and blade clamps
for cracks''. However, if the FAA intends to detect gross corrosion
only, then the added wording in (c) is not needed. The commenter
further states that although they support the need for a blade
dimensional inspection, they suggest the FAA review the justification
for this inspection. The commenter believes the FAA may find this
inspection requirement not supportable by service events.
We do not agree that (c) should be changed. Appropriate clarifying
changes to Table 3, paragraph (b), as noted earlier, achieve the proper
inspection.
The same commenter suggests that the text to Table 3, under the
``Then:'' column, under (d) which reads ``Repair and replace with
serviceable parts, as necessary'' be changed to ``If any of these
conditions are present, perform additional inspections, including
magnetic particle or fluorescent-penetrant inspections as appropriate
to determine the serviceability of the part''. The commenter states
that these inspections be specifically required when corrosion or other
damage has been visually identified since cracks are more likely to
start from these conditions, and the cracks are likely to be small and
only detectable by magnetic particle or fluorescent-penetrant
inspection.
We do not agree that (d) should be changed. Appropriate clarifying
changes to Table 3, paragraph (b), as noted earlier, achieve the proper
inspection.
Request for Repetitive Inspections
One commenter, the National Transportation Safety Board (NTSB),
states that it generally supports the proposed AD. However, the NTSB
notes that the proposed AD only proposes a onetime inspection rather
than a repetitive inspection. The commenter further states that
although the proposed AD also includes a requirement to report
inspection findings and indicates that we will use this information to
determine whether repetitive inspections are in order, the NTSB
continues to believe that repetitive inspections best reflect the
manufacturer's inspection recommendations. These recommendations have
been established in consideration of product design and service
requirements. Therefore, the NTSB again urges us to require that these
propellers be subject to repetitive inspections.
We do not agree. Our review of the service history for the
specified propellers supports the need for a onetime action, especially
in light of the aging of the specified propeller fleet. As stated in
the proposed AD, we will review the need for a repetitive inspection
only if new reports submitted per the AD requirements, document the
need to mandate a repetitive inspection. We encourage the public to
comply with manufacturer's maintenance recommendations, but the public
is only required to maintain their aircraft in accordance with 14 CFR
part 91 requirements.
[[Page 53545]]
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
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 will be affected by
this AD. We also estimate that it will take about 20 work hours per
propeller assembly to perform the actions, and that the average labor
rate is $65 per work hour. Required parts will cost about $450 per
propeller assembly. Based on these figures, we estimate the total cost
of the 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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) 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.
We prepared a summary of the costs to comply with this AD 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2005-18-12 Hartzell Propeller Inc. Propellers: Amendment 39-14252.
Docket No. FAA-2004-19955; Directorate Identifier. 2004-NE-17-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
14, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Hartzell propeller assemblies with hub
model 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 Series
------------------------------------------------------------------------
-------------------------------------------------------------------------
HC-92W Hub Model Series
BHC-92W Hub Model Series
HC-92Z Hub Model Series
BHC-92Z Hub Model Series
HC-B3P Hub Model Series
HC-B3R Hub Model Series
HC-B3W Hub Model Series
BHC-B3W Hub Model Series
HA-B3Z Hub Model Series
HC-B3Z Hub Model Series
------------------------------------------------------------------------
Table 2.--List of Airplanes That Might Use An Affected Propeller
Assembly
------------------------------------------------------------------------
Aircraft manufacturer Aircraft model
------------------------------------------------------------------------
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
[[Page 53546]]
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
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 FLUGDIENST). An Airship
WEATHERLY.............................. 201B, 201C, 620, 620A, 620C
------------------------------------------------------------------------
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. HC-SB-61-136, Revision I, dated April 25,
2003; SB No. 136, Revision H, dated March 12, 1993; or SB No. 136,
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 SB No. HC-SB-61-136,
Revision I, dated April 25, 2003; or SB No. 136, Revision H, dated
March 12, 1993; or SB No. 136, 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
maintenance manuals.
[[Page 53547]]
Table 3.--Compliance Times for Onetime Inspection
------------------------------------------------------------------------
If the TSO of the propeller
assembly on the effective date Then . . . Perform the the
of this AD is . . . inspection . . .
------------------------------------------------------------------------
(1) More 25 years or the TSO (a) Disassemble and Within 12 months
is not known. clean the propeller after the
assembly. effective date
(b) Perform visual and of this AD.
nondestructive
inspections of
propeller components
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. HC-SB-
61-136, Revision I,
dated April 26, 2003.
(d) Repair and replace
with serviceable
parts, as necessary..
(e) Reassemble and
test..
(2) Twenty-one to 25 years.... (a) Disassemble and Within 18 months
clean the propeller after the
assembly. effective date
(b) Perform visual and of this AD.
nondestructive
inspections of
propeller components
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. HC-SB-
61-136, 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
assembly. effective date
(b) Perform visual and of this AD.
nondestructive
inspections of
propeller components
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. HC-SB-
61-136, 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
assembly. effective date
(b) Perform visual and of this AD.
nondestructive
inspections of
propeller components
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. HC-SB-
61-136, Revision I,
dated April 26, 2003.
(d) Repair and replace
with serviceable
parts, as necessary..
(e) Reassemble and
test..
------------------------------------------------------------------------
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 Maintenance
Manuals issued by Hartzell Propeller Inc. contain information on
overhauling a propeller assembly.
(k) The time-since-overhaul 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 and assigned OMB control number 2120-0056.
Alternative Methods of Compliance
(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.
Material Incorporated by Reference
(o) You must use Hartzell Service Bulletin No. HC-SB-61-136,
Revision I, dated April 25, 2003, to perform the inspections and
rework required by this AD. The Director of the Federal Register
approved the incorporation by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Hartzell
Propeller Inc. Technical Publications Department, One Propeller
Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 778-
4391, for a copy of this service information. You may review copies
at the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC 20590-0001, on the internet at http://dms.dot.gov
, or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html
.
Issued in Burlington, Massachusetts, on August 29, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-17667 Filed 9-8-05; 8:45 am]
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