Airworthiness Directives; McCauley Propeller Systems Propeller Assemblies Models 2D34C53/74E-X; D2A34C58/90AT-X; 3AF32C87/82NC-X; D3AF32C87/82NC-X; D3A32C88/82NC-X; D3A32C90/82NC-X; and 3AF34C92/90LF-X., 71753-71756 [05-23430]
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Federal Register / Vol. 70, No. 229 / Wednesday, November 30, 2005 / Rules and Regulations
Frequency
Field strength
(volts per meter)
Peak
700 MHz–1 GHz .......
1 GHz–2 GHz ...........
2 GHz–4 GHz ...........
4 GHz–6 GHz ...........
6 GHz–8 GHz ...........
8 GHz–12 GHz .........
12 GHz–18 GHz .......
18 GHz–40 GHz .......
Average
700
2000
3000
3000
1000
3000
2000
600
100
200
200
200
200
300
200
200
The field strengths are expressed in terms
of peak root-mean-square (rms) values.
or,
(2) The applicant may demonstrate by
a system test and analysis that the
electrical and electronic systems that
perform critical functions can withstand
a minimum threat of 100 volts per
meter, electrical field strength, from 10
kHz to 18 GHz. When using this test to
show compliance with the HIRF
requirements, no credit is given for
signal attenuation due to installation.
A preliminary hazard analysis must
be performed by the applicant for
approval by the FAA to identify either
electrical or electronic systems that
perform critical functions. The term
‘‘critical’’ means those functions, whose
failure would contribute to, or cause, a
failure condition that would prevent the
continued safe flight and landing of the
airplane. The systems identified by the
hazard analysis that perform critical
functions are candidates for the
application of HIRF requirements. A
system may perform both critical and
non-critical functions. Primary
electronic flight display systems, and
their associated components, perform
critical functions such as attitude,
altitude, and airspeed indication. The
HIRF requirements apply only to critical
functions.
Compliance with HIRF requirements
may be demonstrated by tests, analysis,
models, similarity with existing
systems, or any combination of these.
Service experience alone is not
acceptable since normal flight
operations may not include an exposure
to the HIRF environment. Reliance on a
system with similar design features for
redundancy as a means of protection
against the effects of external HIRF is
generally insufficient since all elements
of a redundant system are likely to be
exposed to the fields concurrently.
Applicability
As discussed above, these special
conditions are applicable to the Mooney
M20M and M20R. Should Garmin AT,
Inc. apply at a later date for a
supplemental type certificate to modify
any other model on the same type
VerDate Aug<31>2005
19:03 Nov 29, 2005
Jkt 208001
certificate to incorporate the same novel
or unusual design feature, the special
conditions would apply to that model as
well under the provisions of § 21.101.
Conclusion
This action affects only certain novel
or unusual design features on one model
of airplane. It is not a rule of general
applicability and affects only the
applicant who applied to the FAA for
approval of these features on the
airplane.
The substance of these special
conditions has been subjected to the
notice and comment period in several
prior instances and has been derived
without substantive change from those
previously issued. It is unlikely that
prior public comment would result in a
significant change from the substance
contained herein. For this reason, and
because a delay would significantly
affect the certification of the airplane,
which is imminent, the FAA has
determined that prior public notice and
comment are unnecessary and
impracticable, and good cause exists for
adopting these special conditions upon
issuance. The FAA is requesting
comments to allow interested persons to
submit views that may not have been
submitted in response to the prior
opportunities for comment described
above.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and
symbols.
Citation
The authority citation for these
special conditions is as follows:
I
Authority: 49 U.S.C. 106(g), 40113 and
44701; 14 CFR 21.16 and 21.101; and 14 CFR
11.38 and 11.19.
PART 23—AIRWORTHINESS
STANDARDS: NORMAL, UTILITY,
ACROBATIC, AND COMMUTER
CATEGORY AIRPLANES
The Special Conditions
I Accordingly, pursuant to the authority
delegated to me by the Administrator,
the following special conditions are
issued as part of the type certification
basis for the Mooney M20M and M20R
airplanes modified by Garmin AT, Inc.
to add the G1000 EFIS system.
1. Protection of Electrical and
Electronic Systems from High Intensity
Radiated Fields (HIRF). Each system
that performs critical functions must be
designed and installed to ensure that the
operations, and operational capabilities
of these systems to perform critical
functions, are not adversely affected
when the airplane is exposed to high
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
71753
intensity radiated electromagnetic fields
external to the airplane.
2. For the purpose of these special
conditions, the following definition
applies:
Critical Functions: Functions whose
failure would contribute to, or cause, a
failure condition that would prevent the
continued safe flight and landing of the
airplane.
Issued in Kansas City, Missouri on
November 3, 2005.
William J. Timberlake,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–23481 Filed 11–29–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22731; Directorate
Identifier 2005–NE–36–AD; Amendment 39–
14389; AD 2005–24–09]
RIN 2120–AA64
Airworthiness Directives; McCauley
Propeller Systems Propeller
Assemblies Models 2D34C53/74E–X;
D2A34C58/90AT–X; 3AF32C87/82NC–
X; D3AF32C87/82NC–X; D3A32C88/
82NC–X; D3A32C90/82NC–X; and
3AF34C92/90LF–X.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
McCauley Propeller Systems propeller
assemblies, models 2D34C53/74E–X;
D2A34C58/90AT–X; 3AF32C87/82NC–
X; D3AF32C87/82NC–X; D3A32C88/
82NC–X; D3A32C90/82NC–X; and
3AF34C92/90LF–X. This AD requires,
within 10 flight hours or 10 days after
the effective date of this AD, whichever
occurs first, removing certain serial
number propeller hubs from service.
This AD results from a report by the
manufacturer that they manufactured
and released 40 propeller hubs with
improperly machined socket retention
threads. We are issuing this AD to
prevent cracked propeller hubs, which
could cause failure of the propeller hub,
blade separation, and loss of control of
the airplane.
DATES: This AD becomes effective
December 15, 2005.
We must receive any comments on
this AD by January 30, 2006.
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Federal Register / Vol. 70, No. 229 / Wednesday, November 30, 2005 / Rules and Regulations
Use one of the following
addresses to comment on this AD:
• DOT Docket Web site: Go
to https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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–
0001.
• Fax: (202) 493–2251.
• 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.
Contact McCauley Propeller Systems,
P.O. Box 7704, Wichita, KS 67277–7704,
U.S.A.; telephone (800) 621–7767, for
the service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Jeff
Janusz, Aerospace Engineer, Wichita
Aircraft Certification Office, FAA, Small
Airplane Directorate, 1801 Airport
Road, Wichita, KS 67209, telephone:
(316) 946–4148; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION: In August
of 2005, McCauley Propeller Systems
reported to the FAA that a repair facility
found a single, new, unused propeller
hub with improperly machined socket
retention threads. Further investigation
revealed that McCauley Propeller
Systems improperly machined socket
retention threads on 40 propeller hubs,
manufactured in 2004 and 2005. Using
a propeller hub with improperly
machined socket retention threads
could cause concentrated loading on the
threads, resulting in cracking of the hub
and blade separation. This condition, if
not corrected, could result in failure of
the propeller hub, blade separation, and
loss of control of the airplane.
ADDRESSES:
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other McCauley Propeller Systems
propeller assemblies, models 2D34C53/
74E–X; D2A34C58/90AT–X; 3AF32C87/
82NC–X; D3AF32C87/82NC–X;
D3A32C88/82NC–X; D3A32C90/82NC–
X; and 3AF34C92/90LF–X of the same
type design. For that reason, we are
issuing this AD to prevent cracked hubs,
which could cause failure of the
propeller hub, blade separation, and
loss of control of the airplane. This AD
requires, within 10 flight hours or 10
days after the effective date of this AD,
VerDate Aug<31>2005
19:03 Nov 29, 2005
Jkt 208001
whichever occurs first, removing
affected propeller hubs from service,
and sending those propeller hubs to a
McCauley Service Center. This AD also
requires, before assembly into a
replacement propeller hub, visually
inspecting the retention nut threads
with a 10-power magnifier, and
replacing the nut if necessary.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
issuing this AD are impracticable. Good
cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment. We
invite you however, to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2005–22731; Directorate Identifier
2005–NE–36–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
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 AD. Using the
search function of the DMS web site,
anyone can find and read the comments
in any of our dockets. The dockets
include 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 https://
dms.dot.gov.
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
Facility 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
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Comments will be available
in the AD docket shortly after the DMS
receives them.
ADDRESSES.
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 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 the 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. 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, Safety.
Adoption of the Amendment
Under 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:
I
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Federal Register / Vol. 70, No. 229 / Wednesday, November 30, 2005 / Rules and Regulations
TABLE 1.—AFFECTED PROPELLER
HUBS—Continued
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Hub serial
number
Hub model
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
042529
050071
050073
050866
050934
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2005–24–09 McCauley Propeller Systems:
Amendment 39–14389. Docket No.
FAA–2005–22731; Directorate Identifier
2005–NE–36–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 15, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McCauley Propeller
Systems propeller assemblies, models
2D34C53/74E–X; D2A34C58/90AT–X;
3AF32C87/82NC–X; D3AF32C87/82NC–X;
D3A32C88/82NC–X; D3A32C90/82NC–X;
and 3AF34C92/90LF–X, with the propeller
hubs listed by serial number in the following
Table 1:
C92, C74, C86 ..........................
C87 D index ..............................
(d) Because a propeller hub can be
interchanged and re-identified as a different
model with the installation of different studs
or adapters, any of the affected hubs could
have been re-identified as a different model.
Each propeller hub model listed in Table 1
of this AD is the original hub configuration
when shipped from McCauley.
(e) The propeller hubs listed in Table 1 of
this AD are installed on, but not limited to,
the airplanes listed in the following Table 2:
TABLE 2.—AIRPLANES INSTALLED ON,
BUT NOT LIMITED TO
Airplane
Model
Beagle .......................
Bellanca ....................
B206.
14–19–3A, 17–30,
17–30A.
180 series.
182E thru R.
185, A, B, C, D, E, F.
A185, E, F.
A188, A188A, A188B.
206 series.
P206, A, B, C, D, E.
U206A, B, C, D, E, F,
G.
TP206A, B, C, D, E.
TU206A, B, C, D, E,
F.
U206, A, B, C, D, E,
F, G.
207, A, T207.
210–5, 210–5A, 210,
A, B, C, D, E, F, G,
H, I, J, K, L.
T210F, G, H, J, K, L.
310I, 310P, Q, R,
T310P, Q, R.
320, A, B, C, D, E, F.
335.
340, A.
401, A, B.
402, A, B, C.
411, A.
414, A.
421, A, B.
FA–200–180.
GC–1B.
HA–31.
200B, C, D.
M20C, D, G.
A, B, C, D, E, F, G,
H.
F15/C.
PL12.
AC–7
Cessna ......................
TABLE 1.—AFFECTED PROPELLER
HUBS
Hub model
C58, C34, C49, C78, C98 ........
C53 ...........................................
C79, C90 ..................................
C77, C88 ..................................
C87 blank index, C72, C93 ......
VerDate Aug<31>2005
19:03 Nov 29, 2005
Hub serial
number
030725
030726
030727
030728
030729
030730
030748
030749
030750
030751
030752
030753
030754
030755
030756
030757
030758
030759
030760
050403
050407
050408
050410
050475
050477
050389
042206
042207
042208
042201
042202
042239
042524
042527
042528
Jkt 208001
Fuji ............................
Globe .........................
Hindustan ..................
Meyers ......................
Mooney .....................
Navion .......................
Procaer ......................
Transavia ..................
Windecker .................
Unsafe Condition
(f) This AD results from a report by the
manufacturer that they manufactured and
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Sfmt 4700
71755
released 40 propeller hubs with improperly
machined socket retention threads. We are
issuing this AD to prevent cracked propeller
hubs, which could cause failure of the
propeller hub, blade separation, and loss of
control of the airplane.
Compliance
(g) You are responsible for having the
affected propeller hubs removed from service
within 10 flight hours or 10 days after the
effective date of this AD, whichever occurs
first, unless the actions have already been
done.
Propeller Hub Removal
(h) Remove from service propeller
assemblies with affected propeller hubs,
listed in Table 1 of this AD.
(i) Send propeller assemblies with affected
propeller hubs listed in Table 1 of this AD
to a McCauley Service Center for
disassembly, inspection, and propeller hub
replacement with a serviceable propeller
hub.
(j) Send uninstalled propeller hubs listed
in Table 1 of this AD to a McCauley Service
Center for replacement with a serviceable
propeller hub.
Replacement Propeller Hub Pre-Installation
Requirements
(k) For retention nuts that were removed
from an affected propeller hub, visually
inspect the retention nut threads with a 10power magnifier before assembly into a
replacement propeller hub. Reject the nut for
any signs of galling, heavy localized loading,
thread deformation, or chipped threads that
may have been caused by thread interference
in the propeller hub.
Reporting Requirements
(l) Report within 10 calendar days of
finding affected propeller hubs to:
(1) The FAA, Wichita Aircraft Certification
Office, 1801 Airport Road, Room 100,
Wichita, KS 67209, Attention: Jeff Janusz,
telephone (316) 946–4148; e-mail:
jeff.janusz@faa.gov; and
(2) McCauley Propeller Systems, P.O. Box
7704, Wichita, KS 97277–7704.
(3) Reporting requirements have been
approved by the Office of Management
(OMB) and assigned OMB control number
2120–0056.
McCauley Credit Program
(m) McCauley Alert Service Bulletin No.
ASB251A, dated September 28, 2005
contains information on a credit program for
affected hubs.
Alternative Methods of Compliance
(n) The Manager, Wichita 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.
Special Flight Permits
(o) Under 39.23, we are limiting the special
flight permits for this AD by the following
conditions:
(1) The propeller must have an oil-filled
propeller hub and have no history of hub oil
leakage.
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Federal Register / Vol. 70, No. 229 / Wednesday, November 30, 2005 / Rules and Regulations
(2) You must visually examine the
propeller hub, and it must have no evidence
of existing cracks.
(3) You are allowed a single-occupant
(pilot only), non-revenue flight to a base of
maintenance or FAA-approved propeller
repair facility only.
(4) Your total flight time must not exceed
10 hours.
Related Information
(p) McCauley Propeller Systems Alert
Service Bulletin No. ASB251A, dated
September 28, 2005, pertains to the subject
of this AD.
Issued in Burlington, Massachusetts, on
November 22, 2005.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–23430 Filed 11–29–05; 8:45 am]
BILLING CODE 4910–13–U
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22690; Directorate
Identifier 2005–NE–35–AD; Amendment 39–
14388; AD 2005–24–08]
RIN 2120–AA64
Airworthiness Directives; McCauley
Propeller Systems Five-Blade Propeller
Assemblies
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
McCauley Propeller Systems propeller
assemblies installed on BAE Systems
(Operations) Limited Jetstream model
4100 series airplanes. This AD requires
removing certain propeller hubs from
service at new reduced life limits and
eddy current inspections (ECIs) of the
propeller hub. This AD results from
three reports of cracked propeller hubs.
We are issuing this AD to prevent
cracked propeller hubs, which could
cause failure of the propeller hub, blade
separation, and loss of control of the
airplane.
DATES: This AD becomes effective
December 15, 2005. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of December 15, 2005.
We must receive any comments on
this AD by January 30, 2006.
ADDRESSES: Use one of the following
addresses to comment on this AD:
VerDate Aug<31>2005
19:03 Nov 29, 2005
Jkt 208001
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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–
0001.
• Fax: (202) 493–2251.
• 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.
Contact McCauley Propeller Systems,
P.O. Box 7704, Wichita, KS 97277–7704,
for the service information referenced in
this AD.
FOR FURTHER INFORMATION CONTACT: Jeff
Janusz, Aerospace Engineer, Wichita
Aircraft Certification Office, FAA, Small
Airplane Directorate, 1801 Airport
Road, Wichita, KS 67209, telephone:
(316) 946–4148; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION: In August
2003, we issued AD 2003–17–10 which
requires initial and repetitive
fluorescent penetrant inspection or
ultrasonic inspection of propeller blade
retention areas for cracks, replacement
of high time propeller blades, and a
onetime inspection of propeller hubs.
That AD resulted from four earlier
reports of cracks in propeller blade
shanks. Since we issued AD 2003–17–
10, we received three more reports of
cracked hubs. In November 2004, we
issued AD 2004–23–16 which requires a
onetime ECI of the propeller hub for
cracks, and if necessary, replacing the
propeller assembly. That AD also
captured inspection results for the
propeller hubs installed on the Jetstream
model 4100 fleet.
We received field reports that during
taxi and ground maneuvering, certain
airplane operators might be violating the
published and placarded propeller
ground revolutions-per-minute (rpm)
restrictions. Operating in the restricted
rpm range during ground operation can
excite a natural propeller blade
frequency that creates damaging stress
loadings on the propeller blades and
hub. The stress loadings can cause
cracks, leading to propeller structural
failure.
Additionally, some operators use a
water-methanol assist system to provide
more engine power during certain
operating conditions. The operating
procedures for the water-methanol assist
system define an airplane brakes-locked
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condition. Testing has shown that using
the water-methanol assist system with
airplane brakes locked creates propeller
loadings exceeding structural fatigue
limits of the propeller hub. This
condition, if not corrected, could result
in cracked hubs, which could cause
failure of the propeller hub, blade
separation, and loss of control of the
airplane.
Relevant Service Information
We reviewed and approved the
technical contents of McCauley Alert
Service Bulletin (ASB) No. ASB250,
dated September 12, 2005. This ASB
introduces new lower life limits for the
propeller hubs identified in this AD,
and describes ECI procedures for them.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other McCauley propeller
assemblies, P/Ns B5JFR36C1101/
114GCA–0, C5JFR36C1102/L114GCA–0,
B5JFR36C1103/114HCA–0, and
C5JFR36C1104/L114HCA–0, installed
on BAE Systems (Operations) Limited
Jetstream model 4100 series airplanes.
We are issuing this AD to prevent
cracked hubs, which could cause failure
of the propeller hub, blade separation,
and loss of control of the airplane. This
AD requires:
• Removing any propeller hub from
service that is currently, or ever was,
operated on an engine with a watermethanol assist system, not later than
6,000 hours time-in-service (TIS).
• Removing any other propeller hub
from service not later than 18,000 hours
TIS.
• Removing any propeller hub from
service that exceeds its life limit on the
effective date of this AD, within 50
hours TIS after the effective date of this
AD.
• That any propeller hub removed
from service after exceeding its life limit
must not be returned to service on any
installation.
• For all installed propeller hubs,
performing an ECI within 200 hours TIS
or 60 days after the effective date of this
AD, whichever occurs first.
• Thereafter, for all installed
propeller hubs with 12,000 or more
hours TIS, performing repetitive ECIs
within 1,800 hours TIS or 12 months,
whichever occurs first.
You must use the service information
described previously to perform the
actions required by this AD. This AD
does not require repetitive inspections
for propeller hubs that ever operated on,
or are currently operating on, engines
with a water-methanol assist system,
E:\FR\FM\30NOR1.SGM
30NOR1
]]>Agencies
[Federal Register Volume 70, Number 229 (Wednesday, November 30, 2005)]
[Rules and Regulations]
[Pages 71753-71756]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23430]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22731; Directorate Identifier 2005-NE-36-AD;
Amendment 39-14389; AD 2005-24-09]
RIN 2120-AA64
Airworthiness Directives; McCauley Propeller Systems Propeller
Assemblies Models 2D34C53/74E-X; D2A34C58/90AT-X; 3AF32C87/82NC-X;
D3AF32C87/82NC-X; D3A32C88/82NC-X; D3A32C90/82NC-X; and 3AF34C92/90LF-
X.
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
McCauley Propeller Systems propeller assemblies, models 2D34C53/74E-X;
D2A34C58/90AT-X; 3AF32C87/82NC-X; D3AF32C87/82NC-X; D3A32C88/82NC-X;
D3A32C90/82NC-X; and 3AF34C92/90LF-X. This AD requires, within 10
flight hours or 10 days after the effective date of this AD, whichever
occurs first, removing certain serial number propeller hubs from
service. This AD results from a report by the manufacturer that they
manufactured and released 40 propeller hubs with improperly machined
socket retention threads. We are issuing this AD to prevent cracked
propeller hubs, which could cause failure of the propeller hub, blade
separation, and loss of control of the airplane.
DATES: This AD becomes effective December 15, 2005.
We must receive any comments on this AD by January 30, 2006.
[[Page 71754]]
ADDRESSES: Use one of the following addresses to comment on this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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 20590-0001.
Fax: (202) 493-2251.
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.
Contact McCauley Propeller Systems, P.O. Box 7704, Wichita, KS
67277-7704, U.S.A.; telephone (800) 621-7767, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Jeff Janusz, Aerospace Engineer,
Wichita Aircraft Certification Office, FAA, Small Airplane Directorate,
1801 Airport Road, Wichita, KS 67209, telephone: (316) 946-4148; fax:
(316) 946-4107.
SUPPLEMENTARY INFORMATION: In August of 2005, McCauley Propeller
Systems reported to the FAA that a repair facility found a single, new,
unused propeller hub with improperly machined socket retention threads.
Further investigation revealed that McCauley Propeller Systems
improperly machined socket retention threads on 40 propeller hubs,
manufactured in 2004 and 2005. Using a propeller hub with improperly
machined socket retention threads could cause concentrated loading on
the threads, resulting in cracking of the hub and blade separation.
This condition, if not corrected, could result in failure of the
propeller hub, blade separation, and loss of control of the airplane.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other McCauley Propeller Systems propeller assemblies,
models 2D34C53/74E-X; D2A34C58/90AT-X; 3AF32C87/82NC-X; D3AF32C87/82NC-
X; D3A32C88/82NC-X; D3A32C90/82NC-X; and 3AF34C92/90LF-X of the same
type design. For that reason, we are issuing this AD to prevent cracked
hubs, which could cause failure of the propeller hub, blade separation,
and loss of control of the airplane. This AD requires, within 10 flight
hours or 10 days after the effective date of this AD, whichever occurs
first, removing affected propeller hubs from service, and sending those
propeller hubs to a McCauley Service Center. This AD also requires,
before assembly into a replacement propeller hub, visually inspecting
the retention nut threads with a 10-power magnifier, and replacing the
nut if necessary.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable. Good cause
exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. We invite you however, to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-22731;
Directorate Identifier 2005-NE-36-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
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 AD. Using the search function of the DMS web
site, anyone can find and read the comments in any of our dockets. The
dockets include 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 https://dms.dot.gov.
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
Facility 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.
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 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 the 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. 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, Safety.
Adoption of the Amendment
0
Under 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:
[[Page 71755]]
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:
?>2005-24-09 McCauley Propeller Systems: Amendment 39-14389. Docket
No. FAA-2005-22731; Directorate Identifier 2005-NE-36-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
15, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McCauley Propeller Systems propeller
assemblies, models 2D34C53/74E-X; D2A34C58/90AT-X; 3AF32C87/82NC-X;
D3AF32C87/82NC-X; D3A32C88/82NC-X; D3A32C90/82NC-X; and 3AF34C92/
90LF-X, with the propeller hubs listed by serial number in the
following Table 1:
Table 1.--Affected Propeller Hubs
------------------------------------------------------------------------
Hub serial
Hub model number
------------------------------------------------------------------------
C58, C34, C49, C78, C98.................................... 030725
030726
030727
030728
030729
030730
030748
030749
030750
030751
030752
030753
030754
030755
030756
030757
030758
030759
030760
050403
050407
050408
050410
050475
050477
C53........................................................ 050389
C79, C90................................................... 042206
042207
042208
C77, C88................................................... 042201
042202
C87 blank index, C72, C93.................................. 042239
042524
042527
042528
042529
050071
050073
C92, C74, C86.............................................. 050866
C87 D index................................................ 050934
------------------------------------------------------------------------
(d) Because a propeller hub can be interchanged and re-
identified as a different model with the installation of different
studs or adapters, any of the affected hubs could have been re-
identified as a different model. Each propeller hub model listed in
Table 1 of this AD is the original hub configuration when shipped
from McCauley.
(e) The propeller hubs listed in Table 1 of this AD are
installed on, but not limited to, the airplanes listed in the
following Table 2:
Table 2.--Airplanes Installed On, But Not Limited To
------------------------------------------------------------------------
Airplane Model
------------------------------------------------------------------------
Beagle.................................... B206.
Bellanca.................................. 14-19-3A, 17-30, 17-30A.
Cessna.................................... 180 series.
182E thru R.
185, A, B, C, D, E, F.
A185, E, F.
A188, A188A, A188B.
206 series.
P206, A, B, C, D, E.
U206A, B, C, D, E, F, G.
TP206A, B, C, D, E.
TU206A, B, C, D, E, F.
U206, A, B, C, D, E, F, G.
207, A, T207.
210-5, 210-5A, 210, A, B, C,
D, E, F, G, H, I, J, K, L.
T210F, G, H, J, K, L.
310I, 310P, Q, R, T310P, Q,
R.
320, A, B, C, D, E, F.
335.
340, A.
401, A, B.
402, A, B, C.
411, A.
414, A.
421, A, B.
Fuji...................................... FA-200-180.
Globe..................................... GC-1B.
Hindustan................................. HA-31.
Meyers.................................... 200B, C, D.
Mooney.................................... M20C, D, G.
Navion.................................... A, B, C, D, E, F, G, H.
Procaer................................... F15/C.
Transavia................................. PL12.
Windecker................................. AC-7
------------------------------------------------------------------------
Unsafe Condition
(f) This AD results from a report by the manufacturer that they
manufactured and released 40 propeller hubs with improperly machined
socket retention threads. We are issuing this AD to prevent cracked
propeller hubs, which could cause failure of the propeller hub,
blade separation, and loss of control of the airplane.
Compliance
(g) You are responsible for having the affected propeller hubs
removed from service within 10 flight hours or 10 days after the
effective date of this AD, whichever occurs first, unless the
actions have already been done.
Propeller Hub Removal
(h) Remove from service propeller assemblies with affected
propeller hubs, listed in Table 1 of this AD.
(i) Send propeller assemblies with affected propeller hubs
listed in Table 1 of this AD to a McCauley Service Center for
disassembly, inspection, and propeller hub replacement with a
serviceable propeller hub.
(j) Send uninstalled propeller hubs listed in Table 1 of this AD
to a McCauley Service Center for replacement with a serviceable
propeller hub.
Replacement Propeller Hub Pre-Installation Requirements
(k) For retention nuts that were removed from an affected
propeller hub, visually inspect the retention nut threads with a 10-
power magnifier before assembly into a replacement propeller hub.
Reject the nut for any signs of galling, heavy localized loading,
thread deformation, or chipped threads that may have been caused by
thread interference in the propeller hub.
Reporting Requirements
(l) Report within 10 calendar days of finding affected propeller
hubs to:
(1) The FAA, Wichita Aircraft Certification Office, 1801 Airport
Road, Room 100, Wichita, KS 67209, Attention: Jeff Janusz, telephone
(316) 946-4148; e-mail: jeff.janusz@faa.gov; and
(2) McCauley Propeller Systems, P.O. Box 7704, Wichita, KS
97277-7704.
(3) Reporting requirements have been approved by the Office of
Management (OMB) and assigned OMB control number 2120-0056.
McCauley Credit Program
(m) McCauley Alert Service Bulletin No. ASB251A, dated September
28, 2005 contains information on a credit program for affected hubs.
Alternative Methods of Compliance
(n) The Manager, Wichita 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.
Special Flight Permits
(o) Under 39.23, we are limiting the special flight permits for
this AD by the following conditions:
(1) The propeller must have an oil-filled propeller hub and have
no history of hub oil leakage.
[[Page 71756]]
(2) You must visually examine the propeller hub, and it must
have no evidence of existing cracks.
(3) You are allowed a single-occupant (pilot only), non-revenue
flight to a base of maintenance or FAA-approved propeller repair
facility only.
(4) Your total flight time must not exceed 10 hours.
Related Information
(p) McCauley Propeller Systems Alert Service Bulletin No.
ASB251A, dated September 28, 2005, pertains to the subject of this
AD.
Issued in Burlington, Massachusetts, on November 22, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-23430 Filed 11-29-05; 8:45 am]
BILLING CODE 4910-13-U
