Airworthiness Directives; Sikorsky Aircraft Corporation Model S-76A, B, and C Helicopters, 25783-25785 [E6-6586]
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Federal Register / Vol. 71, No. 84 / Tuesday, May 2, 2006 / Proposed Rules
is proposing to adopt the following
amendments to 10 CFR part 72.
PART 72—LICENSING
REQUIREMENTS FOR THE
INDEPENDENT STORAGE OF SPENT
NUCLEAR FUEL, HIGH-LEVEL
RADIOACTIVE WASTE, AND
REACTOR-RELATED GREATER THAN
CLASS C WASTE
1. The authority citation for part 72 is
revised to read as follows:
Authority: Secs. 51, 53, 57, 62, 63, 65, 69,
81, 161, 182, 183, 184, 186, 187, 189, 68 Stat.
929, 930, 932, 933, 934, 935, 948, 953, 954,
955, as amended, sec. 234, 83 Stat. 444, as
amended (42 U.S.C. 2071, 2073, 2077, 2092,
2093, 2095, 2099, 2111, 2201, 2232, 2233,
2234, 2236, 2237, 2238, 2282); sec. 274, Pub.
L. 86–373, 73 Stat. 688, as amended (42
U.S.C. 2021); sec. 201, as amended, 202, 206,
88 Stat. 1242, as amended, 1244, 1246 (42
U.S.C. 5841, 5842, 5846); Pub. L. 95–601, sec.
10, 92 Stat. 2951 as amended by Pub. L. 102–
486, sec. 7902, 106 Stat. 3123 (42 U.S.C.
5851); sec. 102, Pub. L. 91–190, 83 Stat. 853
(42 U.S.C. 4332); secs. 131, 132, 133, 135,
137, 141, Pub. L. 97–425, 96 Stat. 2229, 2230,
2232, 2241, sec. 148, Pub. L. 100–203, 101
Stat. 1330–235 (42 U.S.C. 10151, 10152,
10153, 10155, 10157, 10161, 10168); sec.
1704, 112 Stat. 2750 (44 U.S.C. 3504 note);
sec. 651(e), Pub. L. 109–58, 119 Stat. 806–10
(42 U.S.C. 2014, 2021, 2021b, 2111).
Section 72.44(g) also issued under secs.
142(b) and 148(c), (d), Pub. L. 100–203, 101
Stat. 1330–232, 1330–236 (42 U.S.C.
10162(b), 10168(c), (d)). Section 72.46 also
issued under sec. 189, 68 Stat. 955 (42 U.S.C.
2239); sec. 134, Pub. L. 97–425, 96 Stat. 2230
(42 U.S.C. 10154). Section 72.96(d) also
issued under sec. 145(g), Pub. L. 100–203,
101 Stat. 1330–235 (42 U.S.C. 10165(g)).
Subpart J also issued under secs. 2(2), 2(15),
2(19), 117(a), 141(h), Pub. L. 97–425, 96 Stat.
2202, 2203, 2204, 2222, 2224 (42 U.S.C.
10101, 10137(a), 10161(h)). Subparts K and L
are also issued under sec. 133, 98 Stat. 2230
(42 U.S.C. 10153) and sec. 218(a), 96 Stat.
2252 (42 U.S.C. 10198).
2. In § 72.214, Certificate of
Compliance 1030 is added to read as
follows:
§ 72.214 List of approved spent fuel
storage casks.
rmajette on PROD1PC67 with PROPOSALS
*
*
*
*
*
Certificate Number: 1030.
Initial Certificate Effective Date:
(insert effective date of final rule).
SAR Submitted by: Transnuclear, Inc.
SAR Title: Final Safety Analysis
Report for the NUHOMS HD
Horizontal Modular Storage System for
Irradiated Nuclear Fuel.
Docket Number: 72–1030.
Certificate Expiration Date: [insert 20
years from the effective date of the final
rule].
Model Number: NUHOMS HD–
32PTH.
*
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*
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VerDate Aug<31>2005
14:31 May 01, 2006
Jkt 208001
Dated at Rockville, Maryland, this 13th day
of April, 2006.
For the Nuclear Regulatory Commission.
William F. Kane,
Acting Executive Director for Operations.
[FR Doc. 06–4116 Filed 5–1–06; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24587; Directorate
Identifier 2006–SW–05–AD]
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation Model S–76A, B,
and C Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
adopting a new airworthiness directive
(AD) for Sikorsky Aircraft Corporation
(Sikorsky) Model S–76A, B, and C
helicopters. The AD would require
inspecting all installed HR Textron
main rotor servo actuators (servo
actuators) for a high rate of leakage and
also inspecting for contaminated
hydraulic fluid. The AD would also
require reducing the time-in-service
(TIS) interval for overhauling the servo
actuators. This proposal is prompted by
a National Transportation Safety Board
(NTSB) Safety Recommendation written
in response to an accident involving a
Model S–76 helicopter in which the
performance of an HR Textron servo
actuator was questioned as a result of
piston head seal leakage and piston
head plasma spray flaking. The actions
specified by the proposed AD are
intended to detect a high rate of leaking
from a servo actuator and contamination
of the hydraulic fluid, which could lead
to degraded ability to maneuver the
cyclic and collective controls and could
result in subsequent loss of control of
the helicopter.
DATES: Comments must be received on
or before July 3, 2006.
ADDRESSES: Use one of the following
addresses to submit comments 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
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
25783
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; or
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT:
Terry Fahr, Aviation Safety Engineer,
Boston Aircraft Certification Office, 12
New England Executive Park,
Burlington, MA 01803, telephone (781)
238–7155, fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
data, views, or arguments regarding this
proposed AD. Send your comments to
the address listed under the caption
ADDRESSES. Include the docket number
‘‘FAA–2006–24587, Directorate
Identifier 2006–SW–05–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to 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 proposed
rulemaking. Using the search function
of our docket Web site, you can find and
read the comments to any of our
dockets, including the name of the
individual who sent or signed the
comment. 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 Docket
You may examine the docket that
contains the proposed AD, any
comments, and other information in
person at the Docket Management
System (DMS) Docket Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5227) is located at the plaza level of the
Department of Transportation Nassif
E:\FR\FM\02MYP1.SGM
02MYP1
25784
Federal Register / Vol. 71, No. 84 / Tuesday, May 2, 2006 / Proposed Rules
rmajette on PROD1PC67 with PROPOSALS
Building in Room PL–401 at 400
Seventh Street, SW., Washington, DC.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Discussion
This document proposes adopting a
new AD for Sikorsky Model S–76A, B,
and C helicopters with an HR Textron
servo actuator, part number (P/N)
76650–09805, installed. The AD would
require inspecting all installed HR
Textron servo actuators for leakage that
exceeds 700 cc per minute by installing
a test line in the servo actuator return
port, and inspecting the hydraulic fluid
for contamination using a patch test kit
or an independent laboratory analysis
method. If leakage in excess of 700 cc
per minute is detected in any servo
actuator, the proposed AD would
require replacing that servo actuator
with an airworthy servo actuator. If the
hydraulic fluid is found to be
contaminated, the proposed AD would
require flushing the hydraulic system.
The AD would also require reducing the
TIS interval for overhauling an affected
servo actuator from 3,000 to 2,000 hours
TIS. This proposal is prompted by an
NTSB Safety Recommendation written
in response to an accident involving a
Model S–76 helicopter in which the
performance of an HR Textron servo
actuator was questioned as a result of
piston head seal leakage and piston
head plasma spray flaking. The actions
specified by the proposed AD are
intended to detect a high rate of leaking
from a servo actuator and contamination
of the hydraulic fluid, which could lead
to degraded ability to maneuver the
cyclic and collective controls and could
result in subsequent loss of control of
the helicopter.
This unsafe condition is likely to exist
or develop on other helicopters of the
same type design. Therefore, the
proposed AD would require, within 25
hours TIS and thereafter at intervals not
to exceed 600 hours TIS, determining
the leakage rate for the three servo
actuators by installing a test line in each
servo actuator return port and turning
on the hydraulic power. If the leakage
rate exceeds 700 cc per minute in any
servo actuator, the proposed AD would
require replacing that servo actuator
with an airworthy servo actuator before
further flight. The proposed AD would
also require inspecting the hydraulic
fluid for contamination using a patch
test kit or an independent laboratory
analysis method. If the hydraulic fluid
is found to be contaminated, the
proposed AD would require flushing the
hydraulic system before further flight.
The proposed AD would also require
VerDate Aug<31>2005
14:31 May 01, 2006
Jkt 208001
reducing the TIS interval for
overhauling the servo actuator from
3,000 to 2,000 hours TIS.
We estimate that this proposed AD
would affect 300 helicopters of U.S.
registry, and that
• Determining the servo actuator
leakage rate would take approximately 8
work hours,
• Inspecting the hydraulic fluid for
contamination would take
approximately 3 work hours,
• Replacing the servo actuator, if
necessary, would take approximately 12
work hours, and
• Flushing the hydraulic system, if
necessary, would take approximately 6
work hours per helicopter to accomplish
at an average labor rate of $80 per work
hour. Required parts would cost
approximately $13,000 per helicopter
for a servo actuator. Based on these
figures, the total cost impact of the
proposed AD on U.S. operators would
be $4,596,000 ($15,320 per helicopter),
assuming one leakage inspection and
one hydraulic fluid inspection on each
helicopter, and replacing one servo
actuator and flushing the hydraulic
system on each helicopter.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. Additionally, this proposed AD
would not have a substantial direct
effect on the States, on the relationship
between the national Government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. 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 draft economic
evaluation of the estimated costs to
comply with this proposed AD. See the
DMS to examine the draft economic
evaluation.
1. The authority citation for part 39
continues to read as follows:
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.
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend part
39 of the Federal Aviation Regulations
(14 CFR part 39) as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by
adding a new airworthiness directive to
read as follows:
Sikorsky Aircraft Corporation: Docket No.
FAA–2006–24587; Directorate Identifier
2006–SW–05–AD.
Applicability: Model S–76A, B, and C
helicopters, with HR Textron main rotor
servo actuator (servo actuator), part number
(P/N) 76650–09805, installed, certificated in
any category.
Compliance: Required as indicated, unless
accomplished previously.
To detect leaking in a servo actuator and
contamination of the hydraulic fluid, which
could lead to degraded ability to maneuver
the cyclic and collective controls and could
result in subsequent loss of control of the
helicopter, accomplish the following:
(a) Within 25 hours time-in-service (TIS),
and thereafter at intervals not to exceed 600
hours TIS:
(1) Determine the leakage rate of each of
the three servo actuators by installing a test
line in each servo actuator return port and
turning on the hydraulic power.
(2) If the leakage rate exceeds 700 cc per
minute in a servo actuator, before further
flight, remove that servo actuator and replace
it with an airworthy servo actuator.
(3) Inspect the hydraulic fluid for
contamination using either a patch test kit or
an independent laboratory analysis method.
(4) If contamination is found, before further
flight, flush the hydraulic system and refill
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02MYP1
Federal Register / Vol. 71, No. 84 / Tuesday, May 2, 2006 / Proposed Rules
the system with uncontaminated hydraulic
fluid.
(b) On or before reaching 2,000 hours TIS
since the last overhaul, and thereafter at
intervals not to exceed 2,000 hours TIS,
overhaul each servo actuator, P/N part
number 76650–09805, or replace it with an
airworthy servo actuator.
(c) This AD revises the Airworthiness
Limitations and Inspection Requirements
manual by reducing the overhaul interval for
the servo actuator, P/N 76650–09805, from
3,000 hours TIS to 2,000 hours TIS.
(d) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the FAA, ATTN: Terry Fahr,
Aviation Safety Engineer, Boston Aircraft
Certification Office, 12 New England
Executive Park, Burlington, MA 01803,
telephone (781) 238–7155, fax (781) 238–
7199, for information about previously
approved alternative methods of compliance.
14 CFR Part 39
this AD to prevent the crew seats from
folding forward during emergency
landing dynamic loads with consequent
occupant injury.
DATES: We must receive comments on
this proposed AD by June 15, 2006.
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.
For service information identified in
this proposed AD, contact Cirrus Design
Corporation, 4515 Taylor Circle, Duluth,
Minnesota 55811; telephone: (218) 727–
2737; Internet address: https://
www.cirrusdesign.com.
[Docket No. FAA–2006–24254; Directorate
Identifier 2006–CE–24–AD]
FOR FURTHER INFORMATION CONTACT ONE
OF THE FOLLOWING:
Issued in Fort Worth, Texas, on April 21,
2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E6–6586 Filed 5–1–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; Cirrus
Design Corporation Models SR20 and
SR22 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
rmajette on PROD1PC67 with PROPOSALS
AGENCY:
SUMMARY: We propose to supersede
Airworthiness Directive (AD) 2005–17–
19, which applies to certain Cirrus
Design Corporation (CDC) Models SR20
and SR22 airplanes. AD 2005–17–19
currently requires you to measure and
adjust the crew seat break-over bolts and
to replace the crew seat recline locks on
both crew seats. Since we issued AD
2005–17–19, CDC developed new crew
seat break-over pins to replace the old
crew seat break-over bolts.
Consequently, this proposed AD would
retain the action from AD 2005–17–19
of replacing the crew seat recline locks
on both seats and would add the action
of replacing the crew seat break-over
bolts with the new crew seat break-over
pins on both seats. We are proposing
VerDate Aug<31>2005
14:31 May 01, 2006
Jkt 208001
• Wess Rouse, Small Airplane Project
Manager, ACE–117C, Chicago Aircraft
Certification Office, 2300 East Devon
Avenue, Room 107, Des Plaines, Illinois
60018; telephone: (847) 294–8113;
facsimile: (847) 294–7834; e-mail:
wess.rouse@faa.gov; or
• Angie Kostopoulos, Composite
Technical Specialist, ACE–116C,
Chicago Aircraft Certification Office,
2300 East Devon Avenue, Room 107,
Des Plaines, Illinois 60018; telephone:
(847) 294–7426; facsimile: (847) 294–
7834; e-mail:
evangelia.kostopoulos@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number, ‘‘FAA–2006–24254; Directorate
Identifier 2006–CE–24–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
25785
and may amend the proposed AD in
light of those comments.
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 we receive
concerning this proposed AD.
Discussion
CDC performed dynamic seat testing
on Models SR20 and SR22 airplanes.
CDC found that, under emergency
landing dynamic loads, the crew seats
may fold forward at less than the 26 g
required by 14 CFR 23.562(b)(2). This
condition, if not corrected, could result
in the crew seats folding forward during
emergency landing dynamic loads with
consequent occupant injury.
This condition caused us to issue AD
2005–17–19, Amendment 39–14240 (70
FR 51999, September 1, 2005). AD
2005–17–19 currently requires the
following on CDC Models SR20 and
SR22 airplanes:
• Measuring and adjusting the crew
seat break-over bolts; and
• Replacing the crew seat recline
locks on both crew seats.
Since AD 2005–17–19, CDC
performed more dynamic seat testing on
Models SR20 and SR22 airplanes and
found that the crew seats may still fold
forward at less than the 26 g required by
14 CFR 23.562(b)(2). CDC developed
new crew seat break-over pins to replace
the crew seat break-over bolts.
Relevant Service Information
We have reviewed CDC Service
Bulletins SB 2X–25–06 R4, Issued
August 13, 2004, Revised May 5, 2005;
and SB 2X–25–17 R1, Issued December
15, 2005, Revised January 20, 2006.
The service information describes
procedures for:
• Replacing the crew seat break-over
bolts with the new crew seat break-over
pins;
• Inspecting crew seats;
• Determining number of bolts used
to secure recline locks to the seat frame;
• Performing recline lock
replacement; and
• Checking the crew seat break-over
pin alignment.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This proposed AD would
supersede AD 2005–17–19 with a new
AD that would retain the action of
E:\FR\FM\02MYP1.SGM
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Agencies
[Federal Register Volume 71, Number 84 (Tuesday, May 2, 2006)]
[Proposed Rules]
[Pages 25783-25785]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-6586]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24587; Directorate Identifier 2006-SW-05-AD]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation Model S-
76A, B, and C Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, B, and C
helicopters. The AD would require inspecting all installed HR Textron
main rotor servo actuators (servo actuators) for a high rate of leakage
and also inspecting for contaminated hydraulic fluid. The AD would also
require reducing the time-in-service (TIS) interval for overhauling the
servo actuators. This proposal is prompted by a National Transportation
Safety Board (NTSB) Safety Recommendation written in response to an
accident involving a Model S-76 helicopter in which the performance of
an HR Textron servo actuator was questioned as a result of piston head
seal leakage and piston head plasma spray flaking. The actions
specified by the proposed AD are intended to detect a high rate of
leaking from a servo actuator and contamination of the hydraulic fluid,
which could lead to degraded ability to maneuver the cyclic and
collective controls and could result in subsequent loss of control of
the helicopter.
DATES: Comments must be received on or before July 3, 2006.
ADDRESSES: Use one of the following addresses to submit comments 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;
Fax: 202-493-2251; or
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You may examine the comments to this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Terry Fahr, Aviation Safety Engineer,
Boston Aircraft Certification Office, 12 New England Executive Park,
Burlington, MA 01803, telephone (781) 238-7155, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2006-
24587, Directorate Identifier 2006-SW-05-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to 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 proposed rulemaking. Using the search
function of our docket Web site, you can find and read the comments to
any of our dockets, including the name of the individual who sent or
signed the comment. 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 Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Management
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of
Transportation Nassif
[[Page 25784]]
Building in Room PL-401 at 400 Seventh Street, SW., Washington, DC.
Comments will be available in the AD docket shortly after the DMS
receives them.
Discussion
This document proposes adopting a new AD for Sikorsky Model S-76A,
B, and C helicopters with an HR Textron servo actuator, part number (P/
N) 76650-09805, installed. The AD would require inspecting all
installed HR Textron servo actuators for leakage that exceeds 700 cc
per minute by installing a test line in the servo actuator return port,
and inspecting the hydraulic fluid for contamination using a patch test
kit or an independent laboratory analysis method. If leakage in excess
of 700 cc per minute is detected in any servo actuator, the proposed AD
would require replacing that servo actuator with an airworthy servo
actuator. If the hydraulic fluid is found to be contaminated, the
proposed AD would require flushing the hydraulic system. The AD would
also require reducing the TIS interval for overhauling an affected
servo actuator from 3,000 to 2,000 hours TIS. This proposal is prompted
by an NTSB Safety Recommendation written in response to an accident
involving a Model S-76 helicopter in which the performance of an HR
Textron servo actuator was questioned as a result of piston head seal
leakage and piston head plasma spray flaking. The actions specified by
the proposed AD are intended to detect a high rate of leaking from a
servo actuator and contamination of the hydraulic fluid, which could
lead to degraded ability to maneuver the cyclic and collective controls
and could result in subsequent loss of control of the helicopter.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design. Therefore, the proposed AD would
require, within 25 hours TIS and thereafter at intervals not to exceed
600 hours TIS, determining the leakage rate for the three servo
actuators by installing a test line in each servo actuator return port
and turning on the hydraulic power. If the leakage rate exceeds 700 cc
per minute in any servo actuator, the proposed AD would require
replacing that servo actuator with an airworthy servo actuator before
further flight. The proposed AD would also require inspecting the
hydraulic fluid for contamination using a patch test kit or an
independent laboratory analysis method. If the hydraulic fluid is found
to be contaminated, the proposed AD would require flushing the
hydraulic system before further flight. The proposed AD would also
require reducing the TIS interval for overhauling the servo actuator
from 3,000 to 2,000 hours TIS.
We estimate that this proposed AD would affect 300 helicopters of
U.S. registry, and that
Determining the servo actuator leakage rate would take
approximately 8 work hours,
Inspecting the hydraulic fluid for contamination would
take approximately 3 work hours,
Replacing the servo actuator, if necessary, would take
approximately 12 work hours, and
Flushing the hydraulic system, if necessary, would take
approximately 6 work hours per helicopter to accomplish at an average
labor rate of $80 per work hour. Required parts would cost
approximately $13,000 per helicopter for a servo actuator. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators would be $4,596,000 ($15,320 per helicopter), assuming one
leakage inspection and one hydraulic fluid inspection on each
helicopter, and replacing one servo actuator and flushing the hydraulic
system on each helicopter.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD would not have a substantial direct effect on the States, on the
relationship between the national Government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. 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 draft economic evaluation of the estimated costs to
comply with this proposed AD. See the DMS to examine the draft economic
evaluation.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Sikorsky Aircraft Corporation: Docket No. FAA-2006-24587;
Directorate Identifier 2006-SW-05-AD.
Applicability: Model S-76A, B, and C helicopters, with HR
Textron main rotor servo actuator (servo actuator), part number (P/
N) 76650-09805, installed, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect leaking in a servo actuator and contamination of the
hydraulic fluid, which could lead to degraded ability to maneuver
the cyclic and collective controls and could result in subsequent
loss of control of the helicopter, accomplish the following:
(a) Within 25 hours time-in-service (TIS), and thereafter at
intervals not to exceed 600 hours TIS:
(1) Determine the leakage rate of each of the three servo
actuators by installing a test line in each servo actuator return
port and turning on the hydraulic power.
(2) If the leakage rate exceeds 700 cc per minute in a servo
actuator, before further flight, remove that servo actuator and
replace it with an airworthy servo actuator.
(3) Inspect the hydraulic fluid for contamination using either a
patch test kit or an independent laboratory analysis method.
(4) If contamination is found, before further flight, flush the
hydraulic system and refill
[[Page 25785]]
the system with uncontaminated hydraulic fluid.
(b) On or before reaching 2,000 hours TIS since the last
overhaul, and thereafter at intervals not to exceed 2,000 hours TIS,
overhaul each servo actuator, P/N part number 76650-09805, or
replace it with an airworthy servo actuator.
(c) This AD revises the Airworthiness Limitations and Inspection
Requirements manual by reducing the overhaul interval for the servo
actuator, P/N 76650-09805, from 3,000 hours TIS to 2,000 hours TIS.
(d) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the FAA, ATTN: Terry Fahr, Aviation Safety Engineer, Boston
Aircraft Certification Office, 12 New England Executive Park,
Burlington, MA 01803, telephone (781) 238-7155, fax (781) 238-7199,
for information about previously approved alternative methods of
compliance.
Issued in Fort Worth, Texas, on April 21, 2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E6-6586 Filed 5-1-06; 8:45 am]
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