Airworthiness Directives; Bell Helicopter Textron, Inc. (Bell) Helicopters, 56592-56594 [2013-22188]
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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations
(h) Related Information
DEPARTMENT OF TRANSPORTATION
Refer to MCAI European Aviation Safety
Agency (EASA) AD No. 2013–0084, dated
April 5, 2013, which can be found in the AD
docket on the Internet at https://
www.regulations.gov; Messier-Dowty PCS–
2700 Paint Stripping document, dated
January 2011; Messier-Dowty PCS–2622 Cold
Degreasing (Solvent) document, Issue 2,
dated May 12, 2008; and Messier-Dowty Ltd
201034005 and 201034006 Component
Maintenance Manual, page 2, dated May 1,
2004, and page 1020, dated March 17, 2006,
which can be found on the Internet at:
https://www.safranmbd.com, for related
information.
(i) Material Incorporated by Reference
emcdonald on DSK67QTVN1PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80–0345,
dated September 20, 2012.
(ii) PIAGGIO AERO INDUSTRIES S.p.A.
Mandatory Service Bulletin No. 80–0345,
Appendix A, dated September 20, 2012,
which includes Messier-Dowty Service
Bulletin No. P180–32–32, dated September
10, 2012.
(3) For PIAGGIO AERO INDUSTRIES
S.p.A. service information identified in this
AD, contact Piaggio Aero Industries S.p.A—
Airworthiness Office, Via Luigi Cibrario, 4–
16154 Genova-Italy; phone: +39 010 6481353;
fax: +39 010 6481881; email: airworthiness@
piaggioaero.it; Internet: https://
www.piaggioaero.com/#/en/aftersales/
service-support; and Messier-Dowty Limited,
Cheltenham Road, Gloucester, GL2 9QH,
England; phone: +44(0)1452 712424; fax:
+44(0)1452 713821; email: americatassc@
safranmbd.com; Internet:
www.safranmbd.com.
(4) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(5) You may view this service information
that is incorporated by reference 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/cfr/ibrlocations.html.
Issued in Kansas City, Missouri, on August
29, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–22203 Filed 9–12–13; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0379; Directorate
Identifier 2009–SW–26–AD; Amendment 39–
17580; AD 2013–18–07]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron, Inc. (Bell)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding revised
Airworthiness Directive (AD) 76–12–07
for all Bell Model 204B and certain
serial-numbered Model 205A–1
helicopters with a certain tail rotor pitch
control chain (chain) installed. AD 76–
12–07 required visually inspecting the
chain to detect a crack in the link
segments and, for affected Model 205A–
1 helicopters, replacing the chain and
cable control system with a push-pull
control system. This new AD requires,
for Bell Model 204B, inspecting certain
chains at specified intervals, revising
the inspection procedures, installing a
tail rotor cable and chain damper kit
(damper kit), and revising the
maintenance manual or Instructions for
Continued Airworthiness (ICAs) to
include the inspection intervals. This
new AD also requires, for certain Bell
Model 205A–1 helicopters, replacing
the chain and cable control system with
an airworthy tail rotor push-pull control
system kit. This AD was prompted by
the rapid growth of a crack leading to
premature chain failure. The actions are
intended to prevent failure of the chain,
loss of tail rotor blade pitch control, and
subsequent loss of control of the
helicopter.
SUMMARY:
This AD is effective October 18,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 18, 2013.
ADDRESSES: For service information
identified in this 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 a copy of the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas
76137.
DATES:
PO 00000
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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 AD, the foreign
authority’s AD, any incorporated-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (phone: 800–647–5527) is U.S.
Department of Transportation, Docket
Operations Office, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Michael Kohner, Aviation Safety
Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5170; email
7-AVS-ASW-170@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 3, 1976, we issued AD 76–
12–07, Amendment 39–2640 (41 FR
23939, June 14, 1976), Docket No. 76–
SW–19, which required repetitive
inspections at specified intervals for a
certain part-numbered chain installed
on Model 204B and 205A–1 helicopters.
AD 76–12–07 also required, before
further flight, replacing chains with
cracked or broken links or segments.
On September 12, 1979, we revised
AD 76–12–07 by issuing Amendment
39–3569 (44 FR 55555, September 27,
1979). The revised AD 76–12–07 limited
the applicability for the Model 205A–1
helicopter to certain serial numbers;
decreased the inspection interval of the
chain; and required replacing the
existing chain and cable control system
with a push-pull control system.
Both amendments were prompted by
several chain failures occurring in flight
and reports of cracked chain links on
Model 205A–1 helicopters. Those
actions were intended to detect cracks
in the chain link segments to prevent
failure of a chain and subsequent loss of
directional control of the helicopter.
On April 25, 2013, at 78 FR 24368, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 to
include an AD that would supersede
original and revised AD 76–12–07. The
NPRM proposed to expand the
applicability of AD 76–12–07 to a
newly-produced, similarly-designed
chain; reduce the inspection interval for
the Model 204B; and require installing
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a push-pull control system on Model
205A–1 helicopters. Specifically, the
NPRM proposed to apply to Model 204B
helicopters with a chain, part number
(P/N) 204–001–739–003 or –105,
installed, and Model 205A–1
helicopters with a serial number 30001
through 30228. The NPRM proposed to
require, for certain Model 205A–1
helicopters, before further flight,
replacing the chain and cable control
system by installing an improved tail
rotor hub and blade assembly kit and
then installing a certain push/pull antitorque retrofit kit. The NPRM also
proposed, for Model 204B helicopters,
visually inspecting certain partnumbered chains at specified intervals
using a 10-power or higher magnifying
glass and a light; revising the inspection
procedures; installing a damper kit; and
revising the maintenance manual or
ICAs to include the inspection intervals.
The proposed requirements were
intended to prevent failure of the chain,
loss of tail rotor blade pitch control, and
subsequent loss of control of the
helicopter.
057–001 or 205–704–057–101. The tail
rotor push-pull control system is
installed in accordance with Service
Instructions (SI) No. 205–38, ‘‘changed’’
March 28, 1990, for an improved tail
rotor hub and blade assembly kit, P/N
205–704–040–001 and 205–704–040–
003, and SI No. 205–46, revised March
7, 1980, for installing a push/pull antitorque retrofit kit.
FAA’s Determination
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Costs of Compliance
We estimate that this AD will affect
13 Model 204B and 52 Model 205A–1
helicopters of U.S. registry, and
operators may incur the following costs:
• Visual inspection of the link
segments in a chain on a Model 204B
helicopter will require .25 work hour for
each inspection, 60 per year, at an
average labor rate of $85 per work hour
for a cost per helicopter of $1,275 and
fleet cost of $16,575;
• Replacement of a chain having a
cracked or broken link or segment on a
Model 204B helicopter will require .5
work hour and a parts cost of $4,922, for
a cost per helicopter of $4,965 and a
total cost of $9,930 (assuming 2 are
replaced);
• Installation of a damper kit on a
Model 204B helicopter will require 3
work hours and a parts cost of $14,925,
for a cost per helicopter of $15,180 and
a total cost of $30,360 (assuming 2 are
installed); and
• Installation of a tail rotor push-pull
control system on an affected Model
205A–1 helicopter will require 225
work hours and a parts cost of $152,214,
for a cost per helicopter of $171,339.
Therefore, we estimate the total cost
impact of this AD on U.S. operators to
be $228,204.
Related Service Information
The FAA has reviewed Bell Alert
Service Bulletin (ASB) No. 204–75–4,
dated December 16, 1975, for the Model
204B helicopter, which specifies
visually inspecting the chain using a 10power magnifying glass every 10 flight
hours. The inspection intervals for a
chain were reduced because of several
field reports of cracked and broken
links. We have also reviewed Bell ASB
204–79–7, dated August 21, 1979,
which specifies installing a damper kit.
A field evaluation has shown
considerable improvement in the
reliability of the chain when a damper
kit is installed.
Further, we have reviewed Bell ASB
No. 205–78–5, dated May 16, 1978, for
Model 205A–1 helicopters, serial
number 30001 through 30228, which
specifies removing the chain and cable
control system and installing a pushpull control system kit, P/N 205–704–
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.
emcdonald on DSK67QTVN1PROD with RULES
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (78 FR 24368, April 25, 2013).
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Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(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 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
76–12–07 Amendment 39–3569 (44 FR
55555, September 27, 1979), which
amended Amendment 39–2640 (41 FR
23939; June 14, 1976), and by adding
the following new AD:
■
2013–18–07 BELL HELICOPTER TEXTRON
(BELL): Amendment 39–17580; Docket
No. FAA–2013–0379; Directorate
Identifier 2009–SW–26–AD.
(a) Applicability
This AD applies to Model 204B helicopters
with a tail rotor pitch control chain (chain),
part number (P/N) 204–001–739–003 or –105,
installed, and Model 205A–1 helicopters
with a serial number (S/N) 30001 through
30228, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in a chain, which can grow quickly
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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations
because of oscillatory loads and lead to
premature failure of the chain, loss of the tail
rotor blade pitch control, and subsequent loss
of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 76–12–07,
Amendment 39–2640 (41 FR 23939, June 14,
1976) as revised by Amendment 39–3569 (44
FR 55555, September 27, 1979).
(d) Effective Date
This AD becomes effective October 18,
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.
emcdonald on DSK67QTVN1PROD with RULES
(f) Required Actions
(1) For Model 205A–1 helicopters, before
further flight, replace the tail rotor chain and
cable control system with an airworthy tail
rotor push-pull control system by installing
an improved tail rotor hub and blade
assembly kit, P/N 205–704–040–001 or 205–
704–040–103, and then installing a push/pull
anti-torque retrofit kit, P/N 205–704–057–001
or 205–704–057–101.
(2) For Model 204B helicopters:
(i) Within 10 hours time-in-service (TIS)
and thereafter at intervals not to exceed 10
hours TIS, using a 10-power or higher
magnifying glass and a light, visually inspect
each of the link segments in the chain for a
crack. Also, slowly operate the cockpit antitorque control pedals during the inspection
so that the entire surface area of the chain in
contact with the control quill sprocket
(sprocket) is visibly accessible and can be
inspected. Pay particular attention to the
portion of the chain that travels over the
sprocket and extends 6 inches to each side
of the sprocket.
(A) If there is no cracked or broken link
segment, lubricate the chain with a light
preservative oil (C–125) or wipe with a cloth
dampened in lubricating oil (C–010).
(B) If there is a cracked or broken link
segment, before further flight, replace the
chain with an airworthy chain.
(ii) Within 50 hours TIS, install a tail rotor
cable and chain damper kit, P/N 204–706–
130–101, as depicted in Figures 1 through 3,
and by following the Accomplishment
Instructions, paragraphs 2. through 9., of Bell
Alert Service Bulletin (ASB) No. 204–79–7,
dated August 21, 1979.
(g) Alternative Methods of Compliance
(AMOC)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to Michael Kohner,
ASW–170, Aviation Safety Engineer,
Rotorcraft Directorate, 2601 Meacham Blvd.,
Fort Worth, Texas 76137, telephone (817)
222–5170, fax (817) 222–5783, email
mike.kohner @faa.gov.
(2) For operations conducted under 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
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holding district office before operating any
aircraft complying with this AD through an
AMOC.
(h) Additional Information
(1) Bell ASB No. 204–75–4, dated
December 16, 1975; Bell ASB No. 205–78–5,
dated May 16, 1978; Service Instructions (SI)
No. 205–38, ‘‘changed’’ March 28, 1990; and
SI No. 205–46, revised March 7, 1980, which
are not incorporated by reference, contain
additional information about the subject of
this AD. For this service information, 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 a copy of the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(2) The subject of this AD is addressed in
Transport Canada Civil Aviation (TCCA) AD
CF–1990–06R1, issued January 7, 2008. You
may view the TCAA AD in the AD docket on
the Internet at https://www.regulations.gov.
(i) Subject
The Joint Aircraft System Component Code
is 6720: Tail Rotor Control System.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Bell Alert Service Bulletin No. 204–79–
7, dated August 21, 1979.
(ii) Reserved.
(3) For Bell Helicopter Textron, Inc. service
information identified in this 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/.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference 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/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on August 27,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–22188 Filed 9–12–13; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0186; Directorate
Identifier 2013–NE–11–AD; Amendment 39–
17571; AD 2013–17–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
General Electric Company (GE) GE90–
76B, –85B, –90B, –94B, –110B1, and
–115B turbofan engines. This AD was
prompted by multiple reports of distress
of certain stage 1 high-pressure turbine
(HPT) stator shrouds due to accelerated
corrosion and oxidation, including one
engine in-flight shutdown (IFSD) caused
by failure of the HPT stator shrouds.
This AD requires initial and repetitive
on-wing 360-degree borescope
inspections (BSIs) for corrosion and
oxidation of stage 1 HPT stator shrouds.
If a shroud is found to be distressed, this
AD requires reinspection at a reduced
interval or removal from service before
further flight. We are issuing this AD to
prevent failure of stage 1 HPT stator
shrouds, resulting in an IFSD of one or
more engines, loss of thrust control, and
damage to the airplane.
DATES: This AD is effective October 18,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 18, 2013.
ADDRESSES: For service information
identified in this AD, contact General
Electric Company, One Neumann Way,
MD Y–75, Cincinnati, OH; phone: 513–
552–2913; email: geae.aoc@ge.com; Web
site: www.GE.com. You may view this
service information at the FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
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]]>Agencies
[Federal Register Volume 78, Number 178 (Friday, September 13, 2013)]
[Rules and Regulations]
[Pages 56592-56594]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-22188]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0379; Directorate Identifier 2009-SW-26-AD;
Amendment 39-17580; AD 2013-18-07]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. (Bell)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding revised Airworthiness Directive (AD) 76-12-
07 for all Bell Model 204B and certain serial-numbered Model 205A-1
helicopters with a certain tail rotor pitch control chain (chain)
installed. AD 76-12-07 required visually inspecting the chain to detect
a crack in the link segments and, for affected Model 205A-1
helicopters, replacing the chain and cable control system with a push-
pull control system. This new AD requires, for Bell Model 204B,
inspecting certain chains at specified intervals, revising the
inspection procedures, installing a tail rotor cable and chain damper
kit (damper kit), and revising the maintenance manual or Instructions
for Continued Airworthiness (ICAs) to include the inspection intervals.
This new AD also requires, for certain Bell Model 205A-1 helicopters,
replacing the chain and cable control system with an airworthy tail
rotor push-pull control system kit. This AD was prompted by the rapid
growth of a crack leading to premature chain failure. The actions are
intended to prevent failure of the chain, loss of tail rotor blade
pitch control, and subsequent loss of control of the helicopter.
DATES: This AD is effective October 18, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 18,
2013.
ADDRESSES: For service information identified in this 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 a copy of the referenced service information at the
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
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 AD, the foreign authority's AD,
any incorporated-by-reference service information, the economic
evaluation, any comments received, and other information. The street
address for the Docket Operations Office (phone: 800-647-5527) is U.S.
Department of Transportation, Docket Operations Office, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170;
email 7-AVS-ASW-170@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 3, 1976, we issued AD 76-12-07, Amendment 39-2640 (41 FR
23939, June 14, 1976), Docket No. 76-SW-19, which required repetitive
inspections at specified intervals for a certain part-numbered chain
installed on Model 204B and 205A-1 helicopters. AD 76-12-07 also
required, before further flight, replacing chains with cracked or
broken links or segments.
On September 12, 1979, we revised AD 76-12-07 by issuing Amendment
39-3569 (44 FR 55555, September 27, 1979). The revised AD 76-12-07
limited the applicability for the Model 205A-1 helicopter to certain
serial numbers; decreased the inspection interval of the chain; and
required replacing the existing chain and cable control system with a
push-pull control system.
Both amendments were prompted by several chain failures occurring
in flight and reports of cracked chain links on Model 205A-1
helicopters. Those actions were intended to detect cracks in the chain
link segments to prevent failure of a chain and subsequent loss of
directional control of the helicopter.
On April 25, 2013, at 78 FR 24368, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to include an AD that would supersede original and revised
AD 76-12-07. The NPRM proposed to expand the applicability of AD 76-12-
07 to a newly-produced, similarly-designed chain; reduce the inspection
interval for the Model 204B; and require installing
[[Page 56593]]
a push-pull control system on Model 205A-1 helicopters. Specifically,
the NPRM proposed to apply to Model 204B helicopters with a chain, part
number (P/N) 204-001-739-003 or -105, installed, and Model 205A-1
helicopters with a serial number 30001 through 30228. The NPRM proposed
to require, for certain Model 205A-1 helicopters, before further
flight, replacing the chain and cable control system by installing an
improved tail rotor hub and blade assembly kit and then installing a
certain push/pull anti-torque retrofit kit. The NPRM also proposed, for
Model 204B helicopters, visually inspecting certain part-numbered
chains at specified intervals using a 10-power or higher magnifying
glass and a light; revising the inspection procedures; installing a
damper kit; and revising the maintenance manual or ICAs to include the
inspection intervals. The proposed requirements were intended to
prevent failure of the chain, loss of tail rotor blade pitch control,
and subsequent loss of control of the helicopter.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 24368,
April 25, 2013).
FAA's Determination
We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
helicopters of these same type designs and that air safety and the
public interest require adopting the AD requirements as proposed.
Related Service Information
The FAA has reviewed Bell Alert Service Bulletin (ASB) No. 204-75-
4, dated December 16, 1975, for the Model 204B helicopter, which
specifies visually inspecting the chain using a 10-power magnifying
glass every 10 flight hours. The inspection intervals for a chain were
reduced because of several field reports of cracked and broken links.
We have also reviewed Bell ASB 204-79-7, dated August 21, 1979, which
specifies installing a damper kit. A field evaluation has shown
considerable improvement in the reliability of the chain when a damper
kit is installed.
Further, we have reviewed Bell ASB No. 205-78-5, dated May 16,
1978, for Model 205A-1 helicopters, serial number 30001 through 30228,
which specifies removing the chain and cable control system and
installing a push-pull control system kit, P/N 205-704-057-001 or 205-
704-057-101. The tail rotor push-pull control system is installed in
accordance with Service Instructions (SI) No. 205-38, ``changed'' March
28, 1990, for an improved tail rotor hub and blade assembly kit, P/N
205-704-040-001 and 205-704-040-003, and SI No. 205-46, revised March
7, 1980, for installing a push/pull anti-torque retrofit kit.
Costs of Compliance
We estimate that this AD will affect 13 Model 204B and 52 Model
205A-1 helicopters of U.S. registry, and operators may incur the
following costs:
Visual inspection of the link segments in a chain on a
Model 204B helicopter will require .25 work hour for each inspection,
60 per year, at an average labor rate of $85 per work hour for a cost
per helicopter of $1,275 and fleet cost of $16,575;
Replacement of a chain having a cracked or broken link or
segment on a Model 204B helicopter will require .5 work hour and a
parts cost of $4,922, for a cost per helicopter of $4,965 and a total
cost of $9,930 (assuming 2 are replaced);
Installation of a damper kit on a Model 204B helicopter
will require 3 work hours and a parts cost of $14,925, for a cost per
helicopter of $15,180 and a total cost of $30,360 (assuming 2 are
installed); and
Installation of a tail rotor push-pull control system on
an affected Model 205A-1 helicopter will require 225 work hours and a
parts cost of $152,214, for a cost per helicopter of $171,339.
Therefore, we estimate the total cost impact of this AD on U.S.
operators to be $228,204.
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(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 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
76-12-07 Amendment 39-3569 (44 FR 55555, September 27, 1979), which
amended Amendment 39-2640 (41 FR 23939; June 14, 1976), and by adding
the following new AD:
2013-18-07 BELL HELICOPTER TEXTRON (BELL): Amendment 39-17580;
Docket No. FAA-2013-0379; Directorate Identifier 2009-SW-26-AD.
(a) Applicability
This AD applies to Model 204B helicopters with a tail rotor
pitch control chain (chain), part number (P/N) 204-001-739-003 or -
105, installed, and Model 205A-1 helicopters with a serial number
(S/N) 30001 through 30228, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a chain,
which can grow quickly
[[Page 56594]]
because of oscillatory loads and lead to premature failure of the
chain, loss of the tail rotor blade pitch control, and subsequent
loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 76-12-07, Amendment 39-2640 (41 FR 23939,
June 14, 1976) as revised by Amendment 39-3569 (44 FR 55555,
September 27, 1979).
(d) Effective Date
This AD becomes effective October 18, 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) For Model 205A-1 helicopters, before further flight, replace
the tail rotor chain and cable control system with an airworthy tail
rotor push-pull control system by installing an improved tail rotor
hub and blade assembly kit, P/N 205-704-040-001 or 205-704-040-103,
and then installing a push/pull anti-torque retrofit kit, P/N 205-
704-057-001 or 205-704-057-101.
(2) For Model 204B helicopters:
(i) Within 10 hours time-in-service (TIS) and thereafter at
intervals not to exceed 10 hours TIS, using a 10-power or higher
magnifying glass and a light, visually inspect each of the link
segments in the chain for a crack. Also, slowly operate the cockpit
anti-torque control pedals during the inspection so that the entire
surface area of the chain in contact with the control quill sprocket
(sprocket) is visibly accessible and can be inspected. Pay
particular attention to the portion of the chain that travels over
the sprocket and extends 6 inches to each side of the sprocket.
(A) If there is no cracked or broken link segment, lubricate the
chain with a light preservative oil (C-125) or wipe with a cloth
dampened in lubricating oil (C-010).
(B) If there is a cracked or broken link segment, before further
flight, replace the chain with an airworthy chain.
(ii) Within 50 hours TIS, install a tail rotor cable and chain
damper kit, P/N 204-706-130-101, as depicted in Figures 1 through 3,
and by following the Accomplishment Instructions, paragraphs 2.
through 9., of Bell Alert Service Bulletin (ASB) No. 204-79-7, dated
August 21, 1979.
(g) Alternative Methods of Compliance (AMOC)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to Michael Kohner,
ASW-170, Aviation Safety Engineer, Rotorcraft Directorate, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5170,
fax (817) 222-5783, email mike.kohner @faa.gov.
(2) For operations conducted under 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.
(h) Additional Information
(1) Bell ASB No. 204-75-4, dated December 16, 1975; Bell ASB No.
205-78-5, dated May 16, 1978; Service Instructions (SI) No. 205-38,
``changed'' March 28, 1990; and SI No. 205-46, revised March 7,
1980, which are not incorporated by reference, contain additional
information about the subject of this AD. For this service
information, 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 a copy of
the referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in Transport Canada
Civil Aviation (TCCA) AD CF-1990-06R1, issued January 7, 2008. You
may view the TCAA AD in the AD docket on the Internet at https://www.regulations.gov.
(i) Subject
The Joint Aircraft System Component Code is 6720: Tail Rotor
Control System.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Bell Alert Service Bulletin No. 204-79-7, dated August 21,
1979.
(ii) Reserved.
(3) For Bell Helicopter Textron, Inc. service information
identified in this 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/.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference 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/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on August 27, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-22188 Filed 9-12-13; 8:45 am]
BILLING CODE 4910-13-P
