Airworthiness Directives; Bell Helicopter Textron, 51123-51126 [2013-20309]
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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules
39–1312 (36 FR 19572, October 8, 1971). We
are issuing this AD to detect and correct
defective fuel valve covers, which could
result in fuel selector handle binding leading
to fuel flow interruption resulting in engine
stoppage.
date of this AD or within the next 12 months
after the effective date of this AD, whichever
occurs first, do the following actions as
applicable in paragraphs (g) through (h) of
this AD, including all subparagraphs.
(f) Compliance
Inspect to verify if the appropriate kit,
Piper part number (P/N) 760–545V or P/N
760–546V, has been installed on the
Unless already done, within the next 100
hours time-in-service (TIS) after the effective
(g) Inspection
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applicable airplanes, using one of two
methods defined in paragraphs (g)(1), (g)(2),
or (g)(3) of this AD:
(1) Review the prior logbook entries of the
airplanes identified in table 2 to paragraph
(g) of this AD for documentation of Piper
Mandatory Service Bulletin (MSB) 840, dated
June 19, 1986, or Piper Service Letter (SL)
588, dated September 3, 1971, compliance; or
kit, Piper P/N 760–545V installation.
TABLE 2 TO PARAGRAPH (G) OF THIS AD—KIT, PIPER P/N 760–545V, APPLICABILITY
Model
Serial Nos.
PA–28–140 .........................
PA–28–180 .........................
PA–28R–180 ......................
PA–28R–200 ......................
28–7125001 through 28–7125666.
28–7105001 through 28–7105259.
28R–7130001 through 28R–7130038.
28R–7135001 through 28R–7135254.
(2) Review the prior logbook entries of the
airplanes identified in table 3 to paragraph
(g) of this AD for documentation of Piper
Mandatory Service Bulletin (MSB) 840, dated
June 19, 1986, or Piper Service Letter (SL)
588, dated September 3, 1971 compliance; or
kit, Piper P/N 760–546V installation.
TABLE 3 TO PARAGRAPH (G) OF THIS AD—KIT, PIPER P/N 760–546V, APPLICABILITY
Model
PA–28–140 .........................
PA–28–150/160/180 ...........
PA–28R–180 ......................
PA–28R–200 ......................
Serial Nos.
28–20000 through 28–26946.
28–01 through 28–5859.
28R–30000 through 28R–31270.
28R–35001 through 28R–35820.
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(3) Visually examine the fuel selector cover
installed on the applicable airplanes
referenced in table 1 to paragraph (c) of this
AD. Airplanes that have installed the kit,
Piper P/N 760–545V or 760–546V, will
have a fuel selector cover with a silver-gray,
spring loaded, metal stop located at the 5
o’clock position, approximately 1.75 inches
from the center of the fuel selector cover.
(h) Replacement
If after doing the inspections required in
paragraph (g)(1), (g)(2), and (g)(3) of this AD
you do not find fuel selector valve kit, Piper
P/N 760–545V or P/N 760–546V, installed on
the airplane, replace the fuel selector valve
as specified in paragraphs (h)(1) and (h)(2) of
this AD:
(1) For Model PA–28–140 airplanes, serial
numbers (S/Ns) 28–7125001 through 28–
7125666; Model PA–28–180 airplanes, S/Ns
28–7105001 through 28–7105259; Model PA–
28R–180 airplanes, S/Ns 28R–7130001
through 28R–7130038; and Model PA–28R–
200 airplanes, S/Ns 28R–7135001 through
28R–7135254: Replace with FuelSelector
Valve Cover Replacement Kit, Piper P/N 760–
545V; and Air Vent Flange Kit, Piper P/N
65735–219. Do the replacement following the
instructions referenced in Piper MSB No.
840, dated June 19, 1986.
(2) For Model PA–28–140 airplanes, S/Ns
28–20000 through 28–26946; Model PA–28–
150/160/180 airplanes, S/Ns 28–01 through
28–5859; Model PA–28R–180 airplanes, S/Ns
28R–30000 through 28R–31270; and Model
PA–28R–200 airplanes, S/Ns 28R–35001
through 28R–35820: Replace with Fuel
Selector Valve Cover Replacement Kit, Piper
P/N 760–546V. Do the replacement following
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the instructions referenced in Piper MSB No.
840, dated June 19, 1986.
availability of this material at the FAA, call
(816) 329–4148.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Issued in Kansas City, Missouri, on August
14, 2013.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
(j) Related Information
(1) For more information about this AD,
contact Gary Wechsler, Aerospace Engineer,
Atlanta Aircraft Certification Office, FAA,
1701 Columbia Avenue, College Park,
Georgia 30337; telephone: (404) 474–5575;
fax: (404) 474–5606; email: gary.wechsler@
faa.gov.
(2) For service information identified in
this AD, contact Piper Aircraft, Inc., 2926
Piper Drive, Vero Beach, Florida 32960;
telephone: (772) 567–4361; fax: (772) 978–
6573; email: customer.service@piper.com;
Internet: www.piper.com/home/pages/
Publications.cfm. You may view this service
information at FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
RIN 2120–AA64
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[FR Doc. 2013–20328 Filed 8–19–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0734; Directorate
Identifier 2012–SW–080–AD]
Airworthiness Directives; Bell
Helicopter Textron
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD) for
Bell Helicopter Textron (Bell) Model
222, 222B, 222U, 230, and 430
helicopters. The existing AD currently
requires inspecting parts of the main
rotor hydraulic servo actuator (servo
actuator) for certain conditions and
SUMMARY:
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replacing any unairworthy parts before
further flight. Since we issued the AD,
a new stainless steel piston rod has been
manufactured. We propose requiring the
installation of a servo actuator assembly
with this piston rod and setting an
interval for the next overhaul at 10,000
hours time-in-service (TIS) or 10 years,
whichever comes first. The proposed
actions are intended to detect pitting or
penetration of the base metal of the
piston rod that could lead to the piston
rod’s failure, the servo actuator’s failure,
and the loss of helicopter control.
DATES: We must receive comments on
this proposed AD by October 21, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
foreign authority’s AD, the economic
evaluation, any comments received and
other information. The street address for
the Docket Operations Office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
For service information identified in
this proposed AD, contact Bell
Helicopter Textron, 12,800 Rue de
l’Avenir, Mirabel, Quebec J7J1R4;
telephone (450) 437–2862 or (800) 363–
8023; fax (450) 433–0272; or at https://
www.bellcustomer.com/files/. You may
review service information at the FAA,
Office of the Regional Counsel,
Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas
76137.
Matt
Wilbanks, Aviation Safety Engineer,
Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
matt.wilbanks@faa.gov.
FOR FURTHER INFORMATION CONTACT:
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SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
Discussion
On November 24, 2010, we published
AD 2010–19–51, Amendment 39–16523
(75 FR 71540), for Bell Model 222, 222B,
222U, 230, and 430 helicopters. AD
2010–19–51 requires inspecting parts of
the servo actuator for certain conditions
and replacing any unairworthy parts
before further flight. AD 2010–19–51
was prompted by a collective servo
actuator malfunction. A subsequent
investigation revealed that the output
piston rod assembly had fractured at the
threaded end because of corrosion
cracking. The investigation also showed
a nonconforming grind relief on a
separate piston rod. The actions of AD
2010–19–51 were intended to detect
corrosion or a nonconforming piston rod
that, if not corrected, could result in the
failure of the piston rod, failure of the
servo actuator, and subsequent loss of
the helicopter.
Actions Since Existing AD Was Issued
Since we issued AD 2010–19–51 (75
FR 71540, November 24, 2010),
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, issued Canadian AD No.
CF–2010–29R1, dated July 26, 2012, to
correct an unsafe condition for Bell
Model 222, 222B, 222U, 230, and 430
helicopters with servo actuator part
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number (P/N) 222–382–001–107. TCCA
AD No. CF–2010–29R1 supersedes AD
No. CF–2010–29, dated August 26,
2010. The original TCCA AD required a
one-time inspection of the servo
actuator for corrosion or a crack, and if
needed, repair of the servo actuator. AD
No. CF–2010–29 also set intervals for a
required overhaul of the servo actuator,
depending on the primer or plating on
the piston rod.
TCCA’s subsequent AD No. CF–2010–
29R1 requires an inspection of the servo
actuator and either overhauling or
replacing the piston rod with a stainless
steel piston rod. Replacement of the
piston rod extends the overhaul interval
of the servo actuator to 10,000 hours TIS
or 10 years, whichever comes first. AD
No. CF–2010–29R1 allows different
compliance times for overhaul or
replacement of the piston rod,
depending on the condition of the
piston rod when inspected.
FAA’s Determination
These helicopters have been approved
by the aviation authority of Canada and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with Canada, TCCA, its
technical representative, has notified us
of the unsafe condition described in its
AD. We are proposing this AD because
we evaluated all known relevant
information and determined that an
unsafe condition is likely to exist or
develop on other products of the same
type design.
Related Service Information
We reviewed Bell Alert Service
Bulletin (ASB) 222–11–111 for Model
222 and 222B helicopters, ASB 222U–
11–82 for Model 222U helicopters, ASB
230–11–43 for Model 230 helicopters,
and ASB 430–11–46 for Model 430
helicopters, all Revision A and all dated
June 22, 2012. The ASBs contain, and
require compliance with, Woodward
HRT Service Bulletin 141600–67–03,
dated February 14, 2012, to upgrade the
servo actuator by replacing the piston
rod and then re-identifying the servo
actuator dash number with ‘‘–111FM.’’
The compliance time for upgrading the
servo actuator varies depending on the
color and amount of corrosion found
and type of plating on the piston rod.
The Bell ASBs also provide an
alternative inspection and procedure for
servo actuator P/N 222–382–001–107
which have not reached certain hours
TIS and where the servo actuator cannot
be upgraded.
TCCA classified these ASBs as
mandatory and issued AD No. CF–
2010–29R1, dated July 26, 2012, to
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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules
ensure the continued airworthiness of
these helicopters.
Proposed AD Requirements
This proposed AD would supersede
AD 2010–19–51, Amendment 39–16523
(75 FR 71540, November 24, 2010) and
would require within 5 hours time-inservice (TIS), inspecting servo actuator,
P/N 222–382–001–107, using a 10X or
higher power magnifying glass to
determine whether the piston rod has
any pitting or penetration of the base
metal.
If the piston rod has pitting or
penetration of the base metal, the
proposed AD would require, before
further flight, replacing the servo
actuator with servo actuator P/N 222–
382–001–111 or P/N 222–382–001–
111FM. Thereafter, the proposed AD
would require overhauling servo
actuator P/N 222–382–001–111 or P/N
222–382–001–111FM at intervals not to
exceed 10 years or 10,000 hours TIS,
whichever comes first.
Differences Between the Proposed AD
and the TCCA AD
This proposed AD differs from the
TCCA AD as follows:
The TCCA AD sets three different
timelines or time-in-service
requirements for the overhaul or
upgrade of the applicable servo
actuators, depending on the damage and
type of material applied to protect the
piston rod.
We would require replacing, before
further flight, the piston rod if it has
pitting or any penetration of the base
metal.
The TCCA AD requires returning
parts to the manufacturer, and this
proposed AD would not.
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Costs of Compliance
We estimate that this proposed AD
would affect 146 helicopters of U.S.
Registry and that labor costs average $85
an hour. Based on these estimates, we
expect the following costs:
• Inspecting the servo actuators
would require 4 work-hours for a labor
cost of $340 per helicopter, and $49,640
for the U.S. fleet.
• Overhauling the servo actuators
would require 8 work-hours for a labor
cost of $680. Parts would cost $11,900
for a total cost of $12,580 per helicopter.
• Replacing the servo actuators would
require 8 hours work-hours for a labor
cost of $680. Parts would cost $35,700
for a total cost of $36,380 per helicopter.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed, I certify
this 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);
3. Will not affect intrastate aviation in
Alaska to the extent that it justifies
making a regulatory distinction; and
4. 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 an economic evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
§ 39.13
51125
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–16523, 75 FR
71540, and adding the following new
airworthiness directive (AD):
■
Bell Helicopter Textron: Docket No. FAA–
2013–0734; Directorate Identifier 2012–SW–
080–AD.
(a) Applicability
This AD applies to Bell Helicopter Textron
Canada (Bell) Model 222, 222B, 222U, 230,
and 430 helicopters, with a main rotor
hydraulic servo actuator (servo actuator), part
number (P/N) 222–382–001–107, installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
pitting or any other penetration of the base
metal on the output piston rod assembly.
This condition could lead to failure of the
piston rod, failure of the servo actuator, and
subsequent loss of helicopter control.
(c) Affected ADs
This AD supersedes AD 2010–19–51,
Amendment 39–16523 (75 FR 71540,
November 24, 2010).
(d) Comments Due Date
We must receive comments by October 21,
2013.
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) Within 5 hours time-in-service (TIS),
inspect servo actuator, P/N 222–382–001–
107, using a 10X or higher power magnifying
glass to determine whether the piston rod has
any pitting or penetration of the base metal.
(2) If the piston rod has pitting or any
penetration of the base metal, replace with
servo actuator P/N 222–382–001–111 or P/N
222–382–001–111FM, before further flight.
Thereafter, overhaul servo actuator P/N 222–
382–001–111 or P/N 222–382–001–111FM at
intervals not to exceed 10 years or 10,000
hours TIS, whichever comes first.
List of Subjects in 14 CFR Part 39
(g) Alternative Methods of Compliance
(AMOCs)
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Wilbanks,
Aviation Safety Engineer, Rotorcraft
Certification Office, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5110;
email matt.wilbanks@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules
(h) Additional Information
(1) The subject of this AD is addressed in
Transport Canada Civil Aviation AD No. CF–
2010–29R1, dated July 26, 2012. A copy of
this document is available for review in
Docket No. FAA–2013–0734 on the Internet
at https://www.regulations.gov.
(2) Bell Alert Service Bulletin (ASB) No.
222–11–111 for Model 222 and 222B
helicopters, ASB No. 222U–11–82 for Model
222U helicopters, ASB No. 230–11–43 for
Model 230 helicopters, and ASB No. 430–11–
46 for Model 430 helicopters, all Revision A
and all dated June 22, 2012, contain
information to replace and overhaul the servo
actuator. You may review service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6730, Rotorcraft Servo System.
Issued in Fort Worth, Texas, on August 12,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–20309 Filed 8–19–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0735; Directorate
Identifier 2013–SW–014–AD]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron, Inc. (Bell)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for Bell
Model 204B helicopters. This proposed
AD would require inspecting the tail
rotor (T/R) cable assembly for an
incorrectly machined body. This
proposed AD is prompted by a report
from Bell that a defective body on the
cable prevents the barrel assembly from
fully engaging in the body cavity. The
proposed actions are intended to
prevent disengagement of the cable from
the barrel, failure of the T/R pitch
control, and subsequent loss of control
of the helicopter.
DATES: We must receive comments on
this proposed AD by October 21, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
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SUMMARY:
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online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
For service information identified in
this proposed AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482,
Fort Worth, TX 76101; telephone (817)
280–3391; fax (817) 280–6466; or at
https://www.bellcustomer.com/files/.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT:
Helene Gandy, Aviation Safety
Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5413; email
7-AVS-ASW-170@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
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We received a report from Bell that a
number of cable assemblies, part
number (P/N) 205–001–720–001, were
manufactured with a defective body, P/
N 205–001–742–001. Bell states the
bodies were incorrectly machined with
a ‘‘false cut,’’ preventing the barrel
assembly, P/N 0301245, from fully
engaging with the body cavity. This
condition, combined with a failure of
the lockwire securing the barrel and the
cable, could result in disengagement of
the cable, T/R pitch control failure in a
fixed position, and subsequent loss of
control of the helicopter.
FAA’s Determination
We are proposing this AD because we
evaluated all known relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other helicopters of
the same type design.
Related Service Information
We reviewed Bell Alert Service
Bulletin (ASB) No. 204B–12–68, dated
October 10, 2012, which describes
procedures for inspecting the barrel
assembly to determine if an incorrectly
machined body is installed. If an
incorrectly machined body is installed,
the ASB specifies replacing the cable
assembly. The ASB further specifies
inspecting the barrel assembly and cable
connection daily until the cable
assembly is replaced.
Proposed AD Requirements
This proposed AD would require
inspecting each cable assembly, within
25 hours time-in-service (TIS), to
determine if an incorrectly machined
body is installed. If an incorrectly
machined body is installed, the
proposed AD would require replacing
the cable assembly within 100 hours
TIS. Until the cable assembly is
replaced, this proposed AD would
require inspecting the assembly for
separation daily.
E:\FR\FM\20AUP1.SGM
20AUP1
]]>Agencies
[Federal Register Volume 78, Number 161 (Tuesday, August 20, 2013)]
[Proposed Rules]
[Pages 51123-51126]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-20309]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0734; Directorate Identifier 2012-SW-080-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive
(AD) for Bell Helicopter Textron (Bell) Model 222, 222B, 222U, 230, and
430 helicopters. The existing AD currently requires inspecting parts of
the main rotor hydraulic servo actuator (servo actuator) for certain
conditions and
[[Page 51124]]
replacing any unairworthy parts before further flight. Since we issued
the AD, a new stainless steel piston rod has been manufactured. We
propose requiring the installation of a servo actuator assembly with
this piston rod and setting an interval for the next overhaul at 10,000
hours time-in-service (TIS) or 10 years, whichever comes first. The
proposed actions are intended to detect pitting or penetration of the
base metal of the piston rod that could lead to the piston rod's
failure, the servo actuator's failure, and the loss of helicopter
control.
DATES: We must receive comments on this proposed AD by October 21,
2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the foreign
authority's AD, the economic evaluation, any comments received and
other information. The street address for the Docket Operations Office
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
For service information identified in this proposed AD, contact
Bell Helicopter Textron, 12,800 Rue de l'Avenir, Mirabel, Quebec
J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 433-0272;
or at https://www.bellcustomer.com/files/. You may review service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110;
email matt.wilbanks@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
On November 24, 2010, we published AD 2010-19-51, Amendment 39-
16523 (75 FR 71540), for Bell Model 222, 222B, 222U, 230, and 430
helicopters. AD 2010-19-51 requires inspecting parts of the servo
actuator for certain conditions and replacing any unairworthy parts
before further flight. AD 2010-19-51 was prompted by a collective servo
actuator malfunction. A subsequent investigation revealed that the
output piston rod assembly had fractured at the threaded end because of
corrosion cracking. The investigation also showed a nonconforming grind
relief on a separate piston rod. The actions of AD 2010-19-51 were
intended to detect corrosion or a nonconforming piston rod that, if not
corrected, could result in the failure of the piston rod, failure of
the servo actuator, and subsequent loss of the helicopter.
Actions Since Existing AD Was Issued
Since we issued AD 2010-19-51 (75 FR 71540, November 24, 2010),
Transport Canada Civil Aviation (TCCA), which is the aviation authority
for Canada, issued Canadian AD No. CF-2010-29R1, dated July 26, 2012,
to correct an unsafe condition for Bell Model 222, 222B, 222U, 230, and
430 helicopters with servo actuator part number (P/N) 222-382-001-107.
TCCA AD No. CF-2010-29R1 supersedes AD No. CF-2010-29, dated August 26,
2010. The original TCCA AD required a one-time inspection of the servo
actuator for corrosion or a crack, and if needed, repair of the servo
actuator. AD No. CF-2010-29 also set intervals for a required overhaul
of the servo actuator, depending on the primer or plating on the piston
rod.
TCCA's subsequent AD No. CF-2010-29R1 requires an inspection of the
servo actuator and either overhauling or replacing the piston rod with
a stainless steel piston rod. Replacement of the piston rod extends the
overhaul interval of the servo actuator to 10,000 hours TIS or 10
years, whichever comes first. AD No. CF-2010-29R1 allows different
compliance times for overhaul or replacement of the piston rod,
depending on the condition of the piston rod when inspected.
FAA's Determination
These helicopters have been approved by the aviation authority of
Canada and are approved for operation in the United States. Pursuant to
our bilateral agreement with Canada, TCCA, its technical
representative, has notified us of the unsafe condition described in
its AD. We are proposing this AD because we evaluated all known
relevant information and determined that an unsafe condition is likely
to exist or develop on other products of the same type design.
Related Service Information
We reviewed Bell Alert Service Bulletin (ASB) 222-11-111 for Model
222 and 222B helicopters, ASB 222U-11-82 for Model 222U helicopters,
ASB 230-11-43 for Model 230 helicopters, and ASB 430-11-46 for Model
430 helicopters, all Revision A and all dated June 22, 2012. The ASBs
contain, and require compliance with, Woodward HRT Service Bulletin
141600-67-03, dated February 14, 2012, to upgrade the servo actuator by
replacing the piston rod and then re-identifying the servo actuator
dash number with ``-111FM.'' The compliance time for upgrading the
servo actuator varies depending on the color and amount of corrosion
found and type of plating on the piston rod. The Bell ASBs also provide
an alternative inspection and procedure for servo actuator P/N 222-382-
001-107 which have not reached certain hours TIS and where the servo
actuator cannot be upgraded.
TCCA classified these ASBs as mandatory and issued AD No. CF-2010-
29R1, dated July 26, 2012, to
[[Page 51125]]
ensure the continued airworthiness of these helicopters.
Proposed AD Requirements
This proposed AD would supersede AD 2010-19-51, Amendment 39-16523
(75 FR 71540, November 24, 2010) and would require within 5 hours time-
in-service (TIS), inspecting servo actuator, P/N 222-382-001-107, using
a 10X or higher power magnifying glass to determine whether the piston
rod has any pitting or penetration of the base metal.
If the piston rod has pitting or penetration of the base metal, the
proposed AD would require, before further flight, replacing the servo
actuator with servo actuator P/N 222-382-001-111 or P/N 222-382-001-
111FM. Thereafter, the proposed AD would require overhauling servo
actuator P/N 222-382-001-111 or P/N 222-382-001-111FM at intervals not
to exceed 10 years or 10,000 hours TIS, whichever comes first.
Differences Between the Proposed AD and the TCCA AD
This proposed AD differs from the TCCA AD as follows:
The TCCA AD sets three different timelines or time-in-service
requirements for the overhaul or upgrade of the applicable servo
actuators, depending on the damage and type of material applied to
protect the piston rod.
We would require replacing, before further flight, the piston rod
if it has pitting or any penetration of the base metal.
The TCCA AD requires returning parts to the manufacturer, and this
proposed AD would not.
Costs of Compliance
We estimate that this proposed AD would affect 146 helicopters of
U.S. Registry and that labor costs average $85 an hour. Based on these
estimates, we expect the following costs:
Inspecting the servo actuators would require 4 work-hours
for a labor cost of $340 per helicopter, and $49,640 for the U.S.
fleet.
Overhauling the servo actuators would require 8 work-hours
for a labor cost of $680. Parts would cost $11,900 for a total cost of
$12,580 per helicopter.
Replacing the servo actuators would require 8 hours work-
hours for a labor cost of $680. Parts would cost $35,700 for a total
cost of $36,380 per helicopter.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed, I certify this 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);
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
4. 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 an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-16523, 75 FR
71540, and adding the following new airworthiness directive (AD):
Bell Helicopter Textron: Docket No. FAA-2013-0734; Directorate
Identifier 2012-SW-080-AD.
(a) Applicability
This AD applies to Bell Helicopter Textron Canada (Bell) Model
222, 222B, 222U, 230, and 430 helicopters, with a main rotor
hydraulic servo actuator (servo actuator), part number (P/N) 222-
382-001-107, installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as pitting or any other
penetration of the base metal on the output piston rod assembly.
This condition could lead to failure of the piston rod, failure of
the servo actuator, and subsequent loss of helicopter control.
(c) Affected ADs
This AD supersedes AD 2010-19-51, Amendment 39-16523 (75 FR
71540, November 24, 2010).
(d) Comments Due Date
We must receive comments by October 21, 2013.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Within 5 hours time-in-service (TIS), inspect servo
actuator, P/N 222-382-001-107, using a 10X or higher power
magnifying glass to determine whether the piston rod has any pitting
or penetration of the base metal.
(2) If the piston rod has pitting or any penetration of the base
metal, replace with servo actuator P/N 222-382-001-111 or P/N 222-
382-001-111FM, before further flight. Thereafter, overhaul servo
actuator P/N 222-382-001-111 or P/N 222-382-001-111FM at intervals
not to exceed 10 years or 10,000 hours TIS, whichever comes first.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817)
222-5110; email matt.wilbanks@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
[[Page 51126]]
(h) Additional Information
(1) The subject of this AD is addressed in Transport Canada
Civil Aviation AD No. CF-2010-29R1, dated July 26, 2012. A copy of
this document is available for review in Docket No. FAA-2013-0734 on
the Internet at https://www.regulations.gov.
(2) Bell Alert Service Bulletin (ASB) No. 222-11-111 for Model
222 and 222B helicopters, ASB No. 222U-11-82 for Model 222U
helicopters, ASB No. 230-11-43 for Model 230 helicopters, and ASB
No. 430-11-46 for Model 430 helicopters, all Revision A and all
dated June 22, 2012, contain information to replace and overhaul the
servo actuator. You may review service information at the FAA,
Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6730, Rotorcraft
Servo System.
Issued in Fort Worth, Texas, on August 12, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-20309 Filed 8-19-13; 8:45 am]
BILLING CODE 4910-13-P
