Airworthiness Directives; [Hoffmann Propeller GmbH & Co KG Models HO-V343 and HO-V343K Propellers], 36008-36011 [05-12172]
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36008
Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations
Actions
Compliance
Procedures
(2) Repetitively replace any eyebolts that attach
the front and rear spar of the horizontal stabilizer to the respective stabilizer strut.
Initially replace upon accumulating the applicable number of hours TIS referenced in
Snow Engineering Co. Service Letter #129,
revised October 21, 2004, or within 50
hours TIS after August 5, 2005 (the effective date of this AD), whichever occurs
later. Replace repetitively thereafter at the
intervals referenced in Snow Engineering
Co. Service Letter #129, revised October
21, 2004.
Follow Snow Engineering Co. Service Letter
#129, Issued September 26, 1994, Revised
October 21, 2004.
(3) For Model AT–602 airplanes through serial
number 602–0695 and AT–802, and 802A
airplanes through serial number 802A–0188:
As an alternative in order to use the increased replacement compliance times in
paragraph (e)(2) of this AD, you may replace
the steel brace assembly inside the stabilizer
with a new steel brace assembly with larger
bushings, and
(i) For the Model AT–602 airplane: replace any
7/16-inch eyebolt with the 9/16-inch eyebolt
(P/N 30774–1)
(ii) For the Model AT–802 and AT–802A airplanes: replace any 7/16-inch eyebolt with
the 9/16-inch eyebolt (P/N 30775–1)
At any time after August 5, 2005 (the effective
of this AD). Use the applicable time in
Snow Engineering Co. Service Letter
#129A, dated August 7, 2004. The repetitive replacement of paragraph (e)(2) of this
AD is still required.
Follow Snow Engineering Co. Service Letter
#129A, Dated August 7, 2004.
(4) Do not install any 5/16-inch eyebolt (P/N
AN44–17A or AN44–21A), 7/16-inch eyebolt
(AN47–22A or AN47–30A), or 9/16-inch eyebolt (P/N 30774–1 or 30775–1) that exceeds
the corresponding cumulative hours TIS
specified in paragraphs (e)(2) or (e)(3) of this
AD.
As of August 5, 2005 (the effective date of
this AD).
Not Applicable.
May I Request an Alternative Method of
Compliance?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, Fort Worth Airplane Certification
Office (ACO), FAA. For information on any
already approved alternative methods of
compliance, contact Andrew D. McAnaul,
Aerospace Engineer, FAA, Fort Worth ACO,
ASW–150, 2601 Meacham Boulevard, Fort
Worth, Texas 76193–0150. Current duty
station: San Antonio Manufacturing
Inspection District Office (MIDO–43), 10100
Reunion Place, Suite 650, San Antonio,
Texas 78216; telephone: (210) 308–3365;
facsimile: (210) 308–3370.
Does This AD Incorporate Any Material by
Reference?
(g) You must do the actions required by
this AD following the instructions in Snow
Engineering Co. Service Letter #129, Issued
September 26, 1994, Revised October 21,
2004, and Snow Engineering Co. Service
Letter #129A, dated August 7, 2004. 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. To get a copy of this
service information, contact Air Tractor,
Incorporated, P.O. Box 485, Olney, Texas
76374. To review copies of this service
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15:52 Jun 21, 2005
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information, go to the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2004–19837; Directorate Identifier 2004–CE–
43–AD.
Issued in Kansas City, Missouri, on June
14, 2005.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–12177 Filed 6–21–05; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–18958; Directorate
Identifier 2004–NE–32–AD; Amendment 39–
14137; AD 2005–13–01]
RIN 2120–AA64
Airworthiness Directives; [Hoffmann
Propeller GmbH & Co KG Models HO–
V343 and HO–V343K Propellers]
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
Hoffmann Propeller GmbH & Co KG
Models HO–V343 and HO–V343K
propellers. That AD currently requires
initial and repetitive visual inspections
of propeller blades for blade shake and
blade nut preload. That AD also requires
initial and repetitive eddy current
inspections of blade hubs for damage
and cracks. This AD requires an
ultrasonic inspection of the propeller
hub and an eddy current inspection of
the propeller hub if any cracks are
discovered during ultrasonic inspection.
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Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations
Additionally, this AD requires sending
a hub inspection report to the
manufacturer. This AD also requires
replacement of the propeller if any signs
of blade shake, cracks, or other damage
to the propeller hub outside serviceable
limits are detected during the
inspections. This AD results from the
discovery of a propeller blade
separation due to a possible hub failure.
We are issuing this AD to prevent
propeller hub failure and blade
separation due to an unknown root
cause, leading to damage and possible
loss of control of the airplane.
DATES: Effective July 7, 2005. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of July 7, 2005.
We must receive any comments on
this AD by August 22, 2005.
ADDRESSES: Use one of the following
addresses to comment on this proposed
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 Hoffmann Propeller GmbH &
¨
Co KG, Kupferlingstrabe 9, D–83022
Rosenheim, Germany, telephone ++49–
(0)8031–1878–0; fax ++49–(0)8031–
1878–78 for the service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office,
FAA, Engine & Propeller Directorate, 12
New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7158; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: On August
24, 2004, the FAA issued AD 2004–18–
01, Amendment 39–13778 (69 FR
53603, September 2, 2004). That AD
requires initial and repetitive visual
inspections of propeller blades for blade
shake and blade nut preload. That AD
also requires initial and repetitive eddy
current inspections of blade hubs for
damage and cracks. That AD resulted
from a report of a blade separating from
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15:52 Jun 21, 2005
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either a model HO–V343 or HO–V343K
propeller. That condition, if not
corrected, could result in propeller hub
failure and blade separation due to an
unknown root cause, leading to damage
and possible loss of control of the
airplane.
Actions Since AD 2004–18–01 Was
Issued
Since that AD was issued, the
Luftfahrt-Bundesamt (LBA), which is
the aviation authority for Germany,
notified us that an unsafe condition
might still exist on Hoffmann propeller
models HO–V343 and HO–V343K
propellers. The LBA advises that
another instance of a propeller blade
separation due to possible hub failure
has been reported. The root cause of the
failure is not known and is still under
investigation. This AD requires an
ultrasonic inspection of the propeller
hub and eddy current inspection of the
propeller hub if any cracks are
discovered during ultrasonic inspection.
Additionally, this AD requires sending
a hub inspection report to the
manufacturer. This AD also requires
replacement of the propeller if any signs
of blade shake, cracks, or other damage
to the propeller hub outside serviceable
limits are detected during the
inspections. We certificated these
propellers for use in the U.S. in 1997
and it is possible that some U.S.
airplanes have acquired sufficient
service hours for the propellers to be
subject to the failure mode. We are
issuing this AD to prevent propeller hub
failure and blade separation due to an
unknown root cause, leading to damage
and possible loss of control of the
airplane.
Relevant Service Information
We have reviewed and approved the
technical contents of Hoffmann
Propeller GmbH & Co KG Service
Instruction (SI) No. 61–10–05 SI E 4D,
dated March 16, 2005. This SI describes
procedures for initial and repetitive
visual inspections of propeller blades
for blade shake, blade nut preload, and
inspection of blade retaining threads for
cracks. This service instruction also
describes procedures for initial and
repetitive ultrasonic and eddy current
inspections of blade hubs for damage or
cracks. The LBA classified this service
instruction as mandatory and issued AD
D–2004–352R4 in order to ensure the
airworthiness of these Hoffmann
Propeller GmbH & Co KG propellers in
Germany.
Bilateral Airworthiness Agreement
This propeller model is manufactured
in Germany and is type certificated for
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36009
operation in the United States under the
provisions of § 21.29 of the Federal
Aviation Regulations (14 CFR 21.29)
and the applicable bilateral
airworthiness agreement. Under this
bilateral airworthiness agreement, the
LBA has kept the FAA informed of the
situation described above. We have
examined the findings of the LBA,
reviewed all available information, and
determined that AD action is necessary
for products of this type design that are
certificated for operation in the United
States.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other Hoffmann Propeller GmbH &
Co KG Models HO–V343 and HO–
V343K propellers of the same type
design. We are issuing this AD to
prevent propeller hub failure and blade
separation due to an unknown root
cause, leading to damage and possible
loss of control of the airplane.
This AD requires initial and repetitive
visual inspections of propeller blades
for blade shake and blade nut preload.
This AD also requires an ultrasonic
inspection of the propeller hub and an
eddy current inspection of the propeller
hub if any cracks are discovered during
ultrasonic inspection. Additionally, this
AD requires sending a hub inspection
report to the manufacturer. This AD also
requires replacement of the propeller if
any signs of blade shake, cracks, or
other damage to the propeller hub
outside serviceable limits are detected
during the inspections. You must use
the service information described
previously to perform the actions
required by this AD.
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, and
that good cause exists for making this
amendment effective in less than 30
days.
Interim Action
These actions are interim actions and
we may take further rulemaking actions
in the future.
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;
however, we invite you to send us any
written relevant data, views, or
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Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2004–18958; Directorate Identifier
2004–NE–32–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, 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
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 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.
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.
15:52 Jun 21, 2005
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Applicability
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 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 by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘AD Docket No. 2004–NE–32–
AD’’ in your request.
(c) This AD applies to Hoffmann Propeller
GmbH & Co KG (Hoffmann Propeller) models
HO–V343 and HO–V343K propellers. These
propellers are installed on, but not limited to,
general aviation airplanes possibly having an
FAA-approved Supplemental Type
Certificate.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
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
PART 39—AIRWORTHINESS
DIRECTIVES
Authority for This Rulemaking
VerDate jul<14>2003
Regulatory Findings
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–13778 (69 FR
53603, September 2, 2004), and by
adding a new airworthiness directive,
Amendment 39–14137, to read as
follows:
I
2005–13–01 Hoffmann Propeller GmbH &
Co KG: Amendment 39–14137. Docket
No. FAA–2004–18958; Directorate
Identifier 2004–E–32–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 7, 2005.
Affected ADs
(b) This AD supersedes AD 2004–18–01,
Amendment 39–13778.
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Unsafe Condition
(d) This AD results from a report of a blade
separating from either a model HO–V343 or
HO–V343K propeller. We are issuing this AD
to prevent propeller hub failure and blade
separation due to an unknown root cause,
leading to damage and possible 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.
Propeller Blade Shake Inspection During
Preflight Inspection
(f) For all propellers, perform an inspection
for propeller blade shake at each preflight
inspection. If you have any blade shake,
replace the propeller assembly.
Propeller Blade Nut Preload Inspection
(g) For all propellers, use paragraph 2.1 of
the Accomplishment Instructions of
Hoffmann Propeller Service Instruction (SI)
No. 61–10–05 SI E 4D, dated March 16, 2005,
to inspect blade nut preload at the following
intervals:
(1) Before further flight after the effective
date of this AD.
(2) Inspect within 50 flight hours (FH)
time-since-initial inspection.
(3) Thereafter, inspect within 100 FH timesince-last inspection (TSLI).
(h) If the blade nut preload inspection
shows a loss of the blade nut preload, before
further flight perform an ultrasonic
inspection (UI) as specified in paragraph (i)
of this AD.
Ultrasonic Inspection
(i) If the propeller meets any of the
conditions detailed in subparagraphs (1) and
(2) below, before further flight, calibrate the
ultrasonic probe and conduct an ultrasonic
inspection of the propeller hub blade
retaining threads for cracks inserting the
probe in each hub arm bore. Use paragraph
2.2 of the Accomplishment Instructions of
Hoffmann Propeller Service Instruction (SI)
No. 61–10–05 SI E 4D, dated March 16, 2005,
to perform the inspection.
(1) The propeller hub has accumulated 500
or more FH time-since-new (TSN), and has
not been inspected using an ultrasonic or
eddy current method, or
(2) The blade nut preload and final
retorque force inspection called for in
paragraph (g) of this AD indicates a loss of
blade retention nut preload torque below
allowable limits.
(j) For propellers with hubs that have
accumulated 500 or more FH TSN repeat the
ultrasonic inspection within intervals of 100
FH TSLI.
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Eddy Current Inspection
DEPARTMENT OF TRANSPORTATION
(k) If the ultrasonic inspection shows any
signs of cracks or damage, conduct an eddy
current inspection of the threads in the hub
bore before further flight. Use paragraph 2.3
of the Accomplishment Instructions of
Hoffmann Propeller Service Instruction (SI)
No. 61–10–05 SI E 4D, dated March 16, 2005,
to perform this inspection.
(l) If you find any signs of cracks or damage
to the propeller hub outside serviceable
limits during the eddy current inspection,
repair or replace the propeller before further
flight.
Credit for Previous Inspections
(m) Previous credit is allowed for propeller
hub inspections performed under the
requirements of AD 2004–18–01.
Hub Inspection Report
(n) Complete Hoffmann Hub Inspection
Report HO–V343 detailing any blade shake,
blade nut preload history and final blade nut
retorque force and forward report to
Hoffmann Propeller GmbH & Co KG,
¨
Kupferlingstra+e 9, D–83022 Rosenheim,
Germany, telephone ++49–(0)8031–1878–0;
fax ++49–(0)8031–1878–78.
Alternative Methods of Compliance
(AMOCs)
(o) The Manager, Boston 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.
Material Incorporated by Reference
(p) You must use Hoffmann Propeller
Service Instruction No. 61–10–05 SI E 4D,
dated March 16, 2005, to perform the checks
and inspections 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. You can get a copy from
Hoffmann Propeller GmbH & Co KG,
¨
Kupferlingstra+e 9, D–83022 Rosenheim,
Germany, telephone ++49–(0)8031–1878–0;
fax ++49–(0)8031–1878–78; 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: https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Related Information
(q) LBA airworthiness directive D–2004–
352R4, dated April 10, 2005, which holds
EASA Approval No. 2005–2514, also
addresses the subject of this AD.
Issued in Burlington, Massachusetts, on
June 13, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–12172 Filed 6–21–05; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21598; Directorate
Identifier 2005–NM–121–AD; Amendment
39–14159; AD 2005–13–22]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135 Airplanes
and Model EMB–145, –145ER, –145MR,
–145LR, –145XR, –145MP, and –145EP
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to all EMBRAER Model
EMB–135 and –145 airplanes. The
existing AD currently requires repetitive
inspections of the electrical connectors
of the electric fuel pumps to detect
discrepancies, application of anticorrosion spray, replacement of all fuel
pumps with improved fuel pumps,
repetitive inspections after all six fuel
pumps are replaced, and applicable
corrective actions. This new AD retains
those requirements but revises the
initial compliance time for an
inspection for certain airplanes. This
new AD is prompted by the need to
correct a compliance time in the
existing AD. We are issuing this AD to
prevent an ignition source in the fuel
tank or adjacent dry bay, which could
result in fire or explosion.
DATES: Effective July 7, 2005.
On May 19, 2005 (70 FR 19685, April
14, 2005), the Director of the Federal
Register approved the incorporation by
reference of EMBRAER Service Bulletin
145–28–0013, dated April 25, 2001.
On October 3, 2000 (65 FR 56233,
September 18, 2000), the Director of the
Federal Register approved the
incorporation by reference of EMBRAER
Alert Service Bulletin S.B. 145–28–
A013, dated August 16, 2000.
We must receive any comments on
this AD by August 22, 2005.
ADDRESSES: Use one of the following
addresses to submit comments 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
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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.
• 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.
For service information identified in
this AD, contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
21598; the directorate identifier for this
docket is 2005–NM–121–AD.
Examining the Docket
You can examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System (DMS) receives
them.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: On April
1, 2005, the FAA issued AD 2005–08–
02, amendment 39–14054 (70 FR 19685,
April 14, 2005). That AD applies to all
EMBRAER Model EMB–135 and –145
series airplanes. That AD requires
repetitive inspections of the electrical
connectors of the electric fuel pumps to
detect discrepancies, follow-on
corrective actions, replacement of
discrepant fuel pumps under certain
conditions, application of anti-corrosion
spray, eventual replacement of all fuel
pumps with improved fuel pumps; and
repetitive inspections after all six fuel
pumps are replaced. That AD was
prompted by the manufacturer’s
development of a new modification that
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]]>Agencies
[Federal Register Volume 70, Number 119 (Wednesday, June 22, 2005)]
[Rules and Regulations]
[Pages 36008-36011]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12172]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18958; Directorate Identifier 2004-NE-32-AD;
Amendment 39-14137; AD 2005-13-01]
RIN 2120-AA64
Airworthiness Directives; [Hoffmann Propeller GmbH & Co KG Models
HO-V343 and HO-V343K Propellers]
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Hoffmann Propeller GmbH & Co KG Models HO-V343 and HO-V343K
propellers. That AD currently requires initial and repetitive visual
inspections of propeller blades for blade shake and blade nut preload.
That AD also requires initial and repetitive eddy current inspections
of blade hubs for damage and cracks. This AD requires an ultrasonic
inspection of the propeller hub and an eddy current inspection of the
propeller hub if any cracks are discovered during ultrasonic
inspection.
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Additionally, this AD requires sending a hub inspection report to the
manufacturer. This AD also requires replacement of the propeller if any
signs of blade shake, cracks, or other damage to the propeller hub
outside serviceable limits are detected during the inspections. This AD
results from the discovery of a propeller blade separation due to a
possible hub failure. We are issuing this AD to prevent propeller hub
failure and blade separation due to an unknown root cause, leading to
damage and possible loss of control of the airplane.
DATES: Effective July 7, 2005. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of July 7, 2005.
We must receive any comments on this AD by August 22, 2005.
ADDRESSES: Use one of the following addresses to comment on this
proposed 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 Hoffmann Propeller GmbH & Co KG, K[uuml]pferlingstra[beta]e
9, D-83022 Rosenheim, Germany, telephone ++49-(0)8031-1878-0; fax ++49-
(0)8031-1878-78 for the service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office, FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7158; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: On August 24, 2004, the FAA issued AD 2004-
18-01, Amendment 39-13778 (69 FR 53603, September 2, 2004). That AD
requires initial and repetitive visual inspections of propeller blades
for blade shake and blade nut preload. That AD also requires initial
and repetitive eddy current inspections of blade hubs for damage and
cracks. That AD resulted from a report of a blade separating from
either a model HO-V343 or HO-V343K propeller. That condition, if not
corrected, could result in propeller hub failure and blade separation
due to an unknown root cause, leading to damage and possible loss of
control of the airplane.
Actions Since AD 2004-18-01 Was Issued
Since that AD was issued, the Luftfahrt-Bundesamt (LBA), which is
the aviation authority for Germany, notified us that an unsafe
condition might still exist on Hoffmann propeller models HO-V343 and
HO-V343K propellers. The LBA advises that another instance of a
propeller blade separation due to possible hub failure has been
reported. The root cause of the failure is not known and is still under
investigation. This AD requires an ultrasonic inspection of the
propeller hub and eddy current inspection of the propeller hub if any
cracks are discovered during ultrasonic inspection. Additionally, this
AD requires sending a hub inspection report to the manufacturer. This
AD also requires replacement of the propeller if any signs of blade
shake, cracks, or other damage to the propeller hub outside serviceable
limits are detected during the inspections. We certificated these
propellers for use in the U.S. in 1997 and it is possible that some
U.S. airplanes have acquired sufficient service hours for the
propellers to be subject to the failure mode. We are issuing this AD to
prevent propeller hub failure and blade separation due to an unknown
root cause, leading to damage and possible loss of control of the
airplane.
Relevant Service Information
We have reviewed and approved the technical contents of Hoffmann
Propeller GmbH & Co KG Service Instruction (SI) No. 61-10-05 SI E 4D,
dated March 16, 2005. This SI describes procedures for initial and
repetitive visual inspections of propeller blades for blade shake,
blade nut preload, and inspection of blade retaining threads for
cracks. This service instruction also describes procedures for initial
and repetitive ultrasonic and eddy current inspections of blade hubs
for damage or cracks. The LBA classified this service instruction as
mandatory and issued AD D-2004-352R4 in order to ensure the
airworthiness of these Hoffmann Propeller GmbH & Co KG propellers in
Germany.
Bilateral Airworthiness Agreement
This propeller model is manufactured in Germany and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Under this bilateral
airworthiness agreement, the LBA has kept the FAA informed of the
situation described above. We have examined the findings of the LBA,
reviewed all available information, and determined that AD action is
necessary for products of this type design that are certificated for
operation in the United States.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other Hoffmann Propeller GmbH & Co KG Models HO-V343 and HO-
V343K propellers of the same type design. We are issuing this AD to
prevent propeller hub failure and blade separation due to an unknown
root cause, leading to damage and possible loss of control of the
airplane.
This AD requires initial and repetitive visual inspections of
propeller blades for blade shake and blade nut preload. This AD also
requires an ultrasonic inspection of the propeller hub and an eddy
current inspection of the propeller hub if any cracks are discovered
during ultrasonic inspection. Additionally, this AD requires sending a
hub inspection report to the manufacturer. This AD also requires
replacement of the propeller if any signs of blade shake, cracks, or
other damage to the propeller hub outside serviceable limits are
detected during the inspections. You must use the service information
described previously to perform the actions required by this AD.
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, and that good
cause exists for making this amendment effective in less than 30 days.
Interim Action
These actions are interim actions and we may take further
rulemaking actions in the future.
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; however, we invite you to send us any written relevant data,
views, or
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arguments regarding this AD. Send your comments to an address listed
under ADDRESSES. Include ``AD Docket No. FAA-2004-18958; Directorate
Identifier 2004-NE-32-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,
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
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 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.
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 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 by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2004-NE-32-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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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:
PART 39--AIRWORTHINESS DIRECTIVES
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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]
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2. The FAA amends Sec. 39.13 by removing Amendment 39-13778 (69 FR
53603, September 2, 2004), and by adding a new airworthiness directive,
Amendment 39-14137, to read as follows:
2005-13-01 Hoffmann Propeller GmbH & Co KG: Amendment 39-14137.
Docket No. FAA-2004-18958; Directorate Identifier 2004-E-32-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 7,
2005.
Affected ADs
(b) This AD supersedes AD 2004-18-01, Amendment 39-13778.
Applicability
(c) This AD applies to Hoffmann Propeller GmbH & Co KG (Hoffmann
Propeller) models HO-V343 and HO-V343K propellers. These propellers
are installed on, but not limited to, general aviation airplanes
possibly having an FAA-approved Supplemental Type Certificate.
Unsafe Condition
(d) This AD results from a report of a blade separating from
either a model HO-V343 or HO-V343K propeller. We are issuing this AD
to prevent propeller hub failure and blade separation due to an
unknown root cause, leading to damage and possible 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.
Propeller Blade Shake Inspection During Preflight Inspection
(f) For all propellers, perform an inspection for propeller
blade shake at each preflight inspection. If you have any blade
shake, replace the propeller assembly.
Propeller Blade Nut Preload Inspection
(g) For all propellers, use paragraph 2.1 of the Accomplishment
Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-
10-05 SI E 4D, dated March 16, 2005, to inspect blade nut preload at
the following intervals:
(1) Before further flight after the effective date of this AD.
(2) Inspect within 50 flight hours (FH) time-since-initial
inspection.
(3) Thereafter, inspect within 100 FH time-since-last inspection
(TSLI).
(h) If the blade nut preload inspection shows a loss of the
blade nut preload, before further flight perform an ultrasonic
inspection (UI) as specified in paragraph (i) of this AD.
Ultrasonic Inspection
(i) If the propeller meets any of the conditions detailed in
subparagraphs (1) and (2) below, before further flight, calibrate
the ultrasonic probe and conduct an ultrasonic inspection of the
propeller hub blade retaining threads for cracks inserting the probe
in each hub arm bore. Use paragraph 2.2 of the Accomplishment
Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-
10-05 SI E 4D, dated March 16, 2005, to perform the inspection.
(1) The propeller hub has accumulated 500 or more FH time-since-
new (TSN), and has not been inspected using an ultrasonic or eddy
current method, or
(2) The blade nut preload and final retorque force inspection
called for in paragraph (g) of this AD indicates a loss of blade
retention nut preload torque below allowable limits.
(j) For propellers with hubs that have accumulated 500 or more
FH TSN repeat the ultrasonic inspection within intervals of 100 FH
TSLI.
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Eddy Current Inspection
(k) If the ultrasonic inspection shows any signs of cracks or
damage, conduct an eddy current inspection of the threads in the hub
bore before further flight. Use paragraph 2.3 of the Accomplishment
Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-
10-05 SI E 4D, dated March 16, 2005, to perform this inspection.
(l) If you find any signs of cracks or damage to the propeller
hub outside serviceable limits during the eddy current inspection,
repair or replace the propeller before further flight.
Credit for Previous Inspections
(m) Previous credit is allowed for propeller hub inspections
performed under the requirements of AD 2004-18-01.
Hub Inspection Report
(n) Complete Hoffmann Hub Inspection Report HO-V343 detailing
any blade shake, blade nut preload history and final blade nut
retorque force and forward report to Hoffmann Propeller GmbH & Co
KG, K[uuml]pferlingstra[szlig]e 9, D-83022 Rosenheim, Germany,
telephone ++49-(0)8031-1878-0; fax ++49-(0)8031-1878-78.
Alternative Methods of Compliance (AMOCs)
(o) The Manager, Boston 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.
Material Incorporated by Reference
(p) You must use Hoffmann Propeller Service Instruction No. 61-
10-05 SI E 4D, dated March 16, 2005, to perform the checks and
inspections 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. You
can get a copy from Hoffmann Propeller GmbH & Co KG,
K[uuml]pferlingstra[szlig]e 9, D-83022 Rosenheim, Germany, telephone
++49-(0)8031-1878-0; fax ++49-(0)8031-1878-78; 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:
https://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.
Related Information
(q) LBA airworthiness directive D-2004-352R4, dated April 10,
2005, which holds EASA Approval No. 2005-2514, also addresses the
subject of this AD.
Issued in Burlington, Massachusetts, on June 13, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-12172 Filed 6-21-05; 8:45 am]
BILLING CODE 4910-13-P
