80 FR 34332 - Airworthiness Directives; Bell Helicopter Textron Canada Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 115 (June 16, 2015)

Page Range		34332-34335
FR Document		2015-14278

We are revising an earlier proposed airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 222, 222B, 222U, 230, and 430 helicopters, which proposed to require replacing certain servo actuators before further flight. The NPRM was prompted by a collective servo actuator malfunction. This action revises the NPRM by adding new actions. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes.

Federal Register, Volume 80 Issue 115 (Tuesday, June 16, 2015)

[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)]
[Proposed Rules]
[Pages 34332-34335]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2015-14278]

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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 Canada
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening
of comment period.

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for Bell Helicopter Textron Canada (Bell) Model 222, 222B, 222U,
230, and 430 helicopters, which proposed to require replacing certain
servo actuators before further flight. The NPRM was prompted by a
collective servo actuator malfunction. This action revises the NPRM by
adding new actions. Since these actions impose an additional burden
over that proposed in the NPRM, we are reopening the comment period to
allow the public the chance to comment on these proposed changes.

DATES: We must receive comments on this SNPRM by August 17, 2015.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://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 http://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 Transport Canada
Civil Aviation (TCCA) 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 Woodward HRT and Bell service information identified in this
proposed AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue
de l'Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or (800)
363-8023; fax (450) 433-0272; or at http://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: Matt Wilbanks, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110;
email matt.wilbanks@faa.gov.

[[Page 34333]]

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

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to remove AD 2010-19-51, Amendment 39-16523 (75 FR 71540,
November 24, 2010) and add a new AD. AD 2010-19-51 applies to Bell
Model 222, 222B, 222U, 230, and 430 helicopters and 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 due to a nonconforming grind
relief on a separate piston rod and corrosion cracking at the threaded
end of the output piston rod assembly. 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 helicopter
control.
The NPRM was published in the Federal Register on August 20, 2013
(78 FR 51123). The NPRM proposed inspecting servo actuator, part number
(P/N) 222-382-001-107, for pitting or penetration of the base metal of
the piston rod. If the piston rod has pitting or any penetration of the
base metal, the NPRM proposed replacing the servo actuator with servo
actuator P/N 222-382-001-111 or P/N 222-382-001-111FM, before further
flight. Thereafter, the NPRM proposed requiring 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.

Comments

After our NPRM (78 FR 51123, August 20, 2013) was published, we
received comments from one commenter.

Request

Bell noted that the AD does not mandate replacement of servo
actuator P/N 222-382-001-107 with servo actuator part number P/N 222-
382-001-111 if no pitting or penetration of the base metal is found
during the inspection, and requested that we include the replacement
provisions in Part 1 of Bell Alert Service Bulletin (ASB) 430-11-46,
Revision A, dated June 22, 2012.
We agree. In light of Bell's comment, we have determined that our
AD should retain all of the inspection requirements of AD 2010-19-51
(75 FR 71540, November 24, 2010) and also include compliance times for
replacing servo actuator P/N 222-382-001-107 with servo actuator part
number P/N 222-382-001-111 or -111FM based upon the results of the
inspection, as specified in Revision A of the ASB. We have changed the
Required Actions accordingly and are consequently proposing this SNPRM.

FAA's Determination

We are proposing this SNPRM because we evaluated all known relevant
information and determined that an unsafe condition is likely to exist
or develop on other products of these same type designs. Certain
changes described above expand the scope of the original NPRM. As a
result, we have determined that it is necessary to reopen the comment
period to provide additional opportunity for the public to comment on
this SNPRM.

Related Service Information Under 1 CFR Part 51

We reviewed Woodward HRT Service Bulletin 141600-67-02, dated
August 18, 2010, which provides instructions for disassembling the
servo actuator and for cleaning and inspecting the piston rod and nut.
This service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section of this SNPRM.

Other Related Service Information

We also reviewed Bell 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 results of the inspections required by Woodward HRT
Service Bulletin 141600-67-02, dated August 18, 2010. The Bell ASBs
also provide an alternative inspection procedure for servo actuator P/N
222-382-001-107 that has 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
ensure the continued airworthiness of these helicopters.

Proposed Requirements of the SNPRM

This proposed AD would require before further flight:
Disassembling each servo actuator.
Cleaning the piston rod and nut, and inspecting the grind
relief configuration for the piston rod and nut. If the grind relief is
unacceptable, replacing the piston rod and nut.
Using a 10x or higher magnifying glass, visually
inspecting the nut for any corrosion or any damage to the threads, and
replacing the nut if you find any corrosion or any damage to the
threads.
Using a 10x or higher magnifying glass, visually
inspecting the piston rod for any corrosion, lack of cadmium plate, or
damage.
If there is any corrosion or lack of cadmium plate or
damage in certain critical areas, replacing the servo actuator with P/N
222-382-001-111 or P/N 222-382-001-111FM before further flight.
If there is any corrosion or lack of cadmium plate in
areas that are not critical areas, reworking the piston rod, inspecting
for bare base metal, and reassembling the servo actuator. Replacing the
servo actuator with P/N 222-382-001-111 or P/N 222-382-001-111FM would
be required within 1,200 hours time-in-service (TIS) or 1 year,
whichever occurs first.
If there is any corrosion that is red or orange in color,
magnetic particle inspecting the piston rod for a crack,

[[Page 34334]]

and replacing the servo actuator with P/N 222-382-001-111 or P/N 222-
382-001-111FM before further flight if there is a crack or within 2,400
hours TIS or 2 years, whichever occurs first, if there is no crack.
If there is no corrosion, lack of cadmium plate, or
damage, inspecting for bare base metal, and reassembling the servo
actuator. Replacing the servo actuator with P/N 222-382-001-111 or P/N
222-382-001-111FM would be required within 3,000 hours TIS or 4 years,
whichever occurs first.
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 occurs first.

Differences Between the Proposed AD and the TCCA AD

The TCCA AD requires inspecting each servo actuator to determine
the condition of the piston rod assembly no later than 5 hours upon
receiving the original issue of its AD. This proposed AD would require
inspecting each servo actuator to determine the condition of the piston
rod assembly before further flight.

Costs of Compliance

We estimate that this proposed AD would affect 146 helicopters of
U.S. Registry and that labor costs average $85 a work-hour. Based on
these estimates, we expect the following costs:
Inspecting a servo actuator would require 4 work-hours per
actuator for a labor cost of $340. No parts would be needed for a total
cost of $1,020 per helicopter and $148,920 for the U.S. fleet given 3
actuators per helicopter.
Replacing a servo actuator would require 8 work-hours for
a labor cost of $680. Parts would cost $35,700 for a total cost of
$36,380 per actuator.
Overhauling the servo actuator would require 8 work-hours
for a labor cost of $680. Parts would cost $11,900 for a total cost of
$12,580 per actuator.

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 adding the following new airworthiness
directive (AD):

Bell Helicopter Textron Canada: 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 corrosion or a
nonconforming grind relief on the output piston rod assembly (piston
rod). This condition could lead to failure of the piston rod,
failure of the servo actuator, and subsequent loss of helicopter
control.

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 August 17, 2015.

(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

Before further flight:
(1) Disassemble each servo actuator to gain access to the piston
rod as shown in Figures 1 through 5 and by following the
Accomplishment Instructions, paragraph 3.A., Part I., of Woodward
HRT Alert Service Bulletin No. 141600-67-02, Revision 0, dated
August 18, 2010 (Woodward ASB).
(2) Clean the entire piston rod and nut using acetone and a
nylon bristle brush removing all contaminates to allow for
inspection. Inspect the grind relief configuration for the piston
rod and nut as shown in Figure 6 of the Woodward ASB. If the grind
relief is unacceptable as shown in Figure 6, replace the piston rod
and the nut with airworthy parts.
(3) Using a 10x or higher magnifying glass, visually inspect the
nut for any corrosion or any damage to the threads. If you find any
corrosion or any damage to the threads, replace the nut with an
airworthy nut.
(4) Using a 10x or higher magnifying glass, visually inspect the
piston rod as shown in Figure 7 of the Woodward ASB for any
corrosion, visible lack of cadmium plate (gold or gray color), or
damage to the piston rod. For the purposes of this AD, damage to the
piston rod is defined as pitting, a visible scratch, a crack, or a
visible abrasion.
(i) If there is any corrosion or visible lack of cadmium plate
or any damage to the piston rod in the Critical Areas as shown in
Figure 7 of the Woodward ASB, replace the servo actuator with servo
actuator P/N 222-382-001-111 or P/N 222-382-001-111FM before further
flight.
(ii) If there is any corrosion or visible lack of cadmium plate
on the piston rod in areas that are not considered Critical Areas as
shown in Figure 7 of the Woodward ASB, rework the piston rod by
removing any surface corrosion that has not penetrated into the base
material by lightly buffing. Clean the part using acetone and a
nylon bristle brush to remove any residue. Comply with paragraphs
(f)(5) through (f)(7) of this AD. Within 1,200 hours time-in-service
(TIS) or 1 year, whichever occurs first, replace the

[[Page 34335]]

servo actuator with servo actuator P/N 222-382-001-111 or P/N 222-
382-001-111FM.
(iii) If there is any corrosion that is red or orange in color,
magnetic particle inspect the piston rod for a crack.
(A) If there is a crack, replace the servo actuator with servo
actuator, P/N 222-382-001-111 or P/N 222-382-001-111FM before
further flight.
(B) If there is no crack, comply with paragraphs (f)(5) through
(f)(7) of this AD. Within 2,400 hours TIS or 2 years, whichever
occurs first, replace the servo actuator with servo actuator P/N
222-382-001-111 or P/N 222-382-001-111FM.
(iv) If there is no corrosion, visible lack of cadmium plate, or
damage to the piston rod, comply with paragraphs (f)(5) through and
(f)(7) of this AD. Within 3,000 hours TIS or 4 years, whichever
occurs first, replace the servo actuator with servo actuator P/N
222-382-001-111 or P/N 222-382-001-111FM.
(5) Inspect the portion of the piston rod for any absence of
cadmium plating (bare base metal), as shown in Figure 7 of the
Woodward ASB. If there is any bare base metal on the piston rod in
this area, apply brush cadmium plating to all bare and reworked
areas using SPS5070 or equivalent 0.0002 to 0.0005 inch thick and
rework the piston rod by following the Accomplishment Instructions,
paragraph C., Part III, C.1.1.1. through C.1.1.3., of the Woodward
ASB.
(6) Reassemble the servo actuator by following the
Accomplishment Instructions, paragraph C, Part III, 1.1.4. through
3.3.4. of the Woodward ASB.
(7) 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 occurs first.

(g) Credit for Actions Previously Completed

Compliance with the Woodward ASB or with AD 2010-19-51 (75 FR
71540, November 24, 2010) before the effective date of this AD is
considered acceptable for compliance with the corresponding
inspections specified in paragraph (f) of this AD. If you replaced
the piston rod pursuant to the Woodward ASB or paragraph (d)(1) or
(d)(3) of AD 2010-19-51, apply the requirements of paragraph
(f)(4)(iv) of this AD.

(h) 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, Regulations and Policy Group, 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.

(i) Additional Information

(1) 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, which are not incorporated by reference,
contain additional information about the subject of this AD. For
Woodward HRT and Bell service information identified in this AD,
contact Bell Helicopter Textron Canada Limited, 12,800 Rue de
l'Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or (800)
363-8023; fax (450) 433-0272; or at http://www.bellcustomer.com/files/. You may review a copy of the 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 the Transport Canada
Civil Aviation (TCCA) AD No. CF-2010-29R1, dated July 26, 2012. You
may view the TCCA AD on the Internet at http://www.regulations.gov
in Docket No. FAA-2013-0734.

(j) Subject

Joint Aircraft Service Component (JASC) Code: 6730, Rotorcraft
Servo System.

Issued in Fort Worth, Texas, on May 29, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2015-14278 Filed 6-15-15; 8:45 am]
BILLING CODE 4910-13-P

34332 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules

The Proposed Amendment required in paragraphs (g)(1) and (g)(2) of this for Bell Helicopter Textron Canada
AD, before further flight, replace the PBE (Bell) Model 222, 222B, 222U, 230, and
Accordingly, under the authority with an FAA-approved PBE contained in a
delegated to me by the Administrator, 430 helicopters, which proposed to
vacuum sealed pouch. After the replacement,
the FAA proposes to amend 14 CFR part require replacing certain servo actuators
continue with the inspections required in
39 as follows: paragraphs (g)(1) and (g)(2) of this AD. before further flight. The NPRM was
prompted by a collective servo actuator
PART 39—AIRWORTHINESS (i) Alternative Methods of Compliance malfunction. This action revises the
(AMOCs) NPRM by adding new actions. Since
DIRECTIVES
(1) The Manager, Wichita Aircraft these actions impose an additional
■ 1. The authority citation for part 39 Certification Office (ACO), FAA, has the burden over that proposed in the NPRM,
continues to read as follows: authority to approve AMOCs for this AD, if we are reopening the comment period to
requested using the procedures found in 14
Authority: 49 U.S.C. 106(g), 40113, 44701. allow the public the chance to comment
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector on these proposed changes.
§ 39.13 [Amended] DATES: We must receive comments on
or local Flight Standards District Office, as
■ 2. The FAA amends § 39.13 by adding appropriate. If sending information directly this SNPRM by August 17, 2015.
the following new airworthiness to the manager of the ACO, send it to the ADDRESSES: You may send comments by
directive (AD): attention of the person identified in any of the following methods:
paragraph (j)(1) of this AD. • Federal eRulemaking Docket: Go to
B/E Aerospace: Docket No. FAA–2015–2134;
(2) Before using any approved AMOC,
Directorate Identifier 2015–CE–012–AD. http://www.regulations.gov. Follow the
notify your appropriate principal inspector,
(a) Comments Due Date or lacking a principal inspector, the manager online instructions for sending your
of the local flight standards district office/ comments electronically.
We must receive comments by July 31, • Fax: 202–493–2251.
2015. certificate holding district office.
• Mail: Send comments to the U.S.
(b) Affected ADs (j) Related Information Department of Transportation, Docket
None. (1) For more information about this AD, Operations, M–30, West Building
contact David Enns, Aerospace Engineer, Ground Floor, Room W12–140, 1200
(c) Applicability Wichita ACO, FAA, 1801 S. Airport Road, New Jersey Avenue SE., Washington,
This AD applies to B/E Aerospace Room 100, Wichita, Kansas 67209; phone: DC 20590–0001.
Protective Breathing Equipment (PBE), part (316) 946–4147; fax: (316) 946–4107; email: • Hand Delivery: Deliver to the
number 119003–11, that is installed on david.enns@faa.gov.
‘‘Mail’’ address between 9 a.m. and 5
airplanes. (2) For service information identified in
this AD, contact B/E Aerospace, Inc., 10800 p.m., Monday through Friday, except
(d) Subject Pflumm Road, Commercial Aircraft Products Federal holidays.
Joint Aircraft System Component (JASC)/ Group, Lenexa, Kansas 66215; telephone: Examining the AD Docket
Air Transport Association (ATA) of America (913) 338–9800; fax: (913) 338–8419;
Code 35; Oxygen. Internet: www.beaerospace.com. You may You may examine the AD docket on
review this referenced service information at the Internet at http://
(e) Unsafe Condition www.regulations.gov or in person at the
the FAA, Small Airplane Directorate, 901
This AD was prompted by reports of a Locust, Kansas City, Missouri 64106. For Docket Operations Office between 9
compromise in the vacuum seal of the pouch information on the availability of this a.m. and 5 p.m., Monday through
that contains the PBE. We are issuing this AD material at the FAA, call (816) 329–4148. Friday, except Federal holidays. The AD
to correct the unsafe condition on these
products. Issued in Kansas City, Missouri, on June 5, docket contains this proposed AD, the
2015. Transport Canada Civil Aviation (TCCA)
(f) Compliance Earl Lawrence, AD, the economic evaluation, any
Unless already done, comply with Manager, Small Airplane Directorate, Aircraft comments received, and other
paragraphs (g) through (h) of this AD. Certification Service. information. The street address for the
(g) Inspection [FR Doc. 2015–14286 Filed 6–15–15; 8:45 am] Docket Operations Office (telephone
800–647–5527) is in the ADDRESSES
(1) Within 3 months after the effective date BILLING CODE 4910–13–P
of this AD, while still in the stowage box, section. Comments will be available in
physically inspect the PBE pouch to the AD docket shortly after receipt.
determine if it has an intact vacuum seal. DEPARTMENT OF TRANSPORTATION For Woodward HRT and Bell service
Repetitively thereafter, inspect every 12 information identified in this proposed
months. Do these inspections following Federal Aviation Administration AD, contact Bell Helicopter Textron
paragraph III.A.1. of the Accomplishment Canada Limited, 12,800 Rue de l’Avenir,
Instructions in B/E Aerospace Service 14 CFR Part 39 Mirabel, Quebec J7J1R4; telephone (450)
Bulletin No. 119003–35–011. Rev. 000, dated 437–2862 or (800) 363–8023; fax (450)
February 4, 2015. [Docket No. FAA–2013–0734; Directorate
433–0272; or at http://
(2) Within 36 months after the first Identifier 2012–SW–080–AD]
www.bellcustomer.com/files/. You may
inspection required in paragraph (g)(1) of this
AD, remove the PBE pouch from the stowage
RIN 2120–AA64 review the referenced service
box and physically inspect the PBE pouch to information at the FAA, Office of the
determine if it has an intact vacuum seal. Airworthiness Directives; Bell Regional Counsel, Southwest Region,
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS

Repetitively thereafter, inspect every 36 Helicopter Textron Canada Helicopters 2601 Meacham Blvd., Room 663, Fort
months. Do these inspections following AGENCY: Federal Aviation Worth, Texas 76137.
paragraph III.A.2. of the Accomplishment FOR FURTHER INFORMATION CONTACT: Matt
Administration (FAA), DOT.
Instructions in B/E Aerospace Service Wilbanks, Aviation Safety Engineer,
Bulletin No. 119003–35–011, Rev. 000, dated ACTION: Supplemental notice of
proposed rulemaking (SNPRM); Regulations and Policy Group,
February 4, 2015.
reopening of comment period. Rotorcraft Directorate, FAA, 2601
(h) Replacement Meacham Blvd., Fort Worth, Texas
If a PBE pouch is found that does not have SUMMARY: We are revising an earlier 76137; telephone (817) 222–5110; email
an intact vacuum seal during any inspection proposed airworthiness directive (AD) matt.wilbanks@faa.gov.

VerDate Sep<11>2014 16:44 Jun 15, 2015 Jkt 235001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\16JNP1.SGM 16JNP1

34334 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules

and replacing the servo actuator with P/ for practices, methods, and procedures hydraulic servo actuator (servo actuator) part
N 222–382–001–111 or P/N 222–382– the Administrator finds necessary for number (P/N) 222–382–001–107 installed,
001–111FM before further flight if there safety in air commerce. This regulation certificated in any category.
is a crack or within 2,400 hours TIS or is within the scope of that authority (b) Unsafe Condition
2 years, whichever occurs first, if there because it addresses an unsafe condition This AD defines the unsafe condition as
is no crack. that is likely to exist or develop on corrosion or a nonconforming grind relief on
• If there is no corrosion, lack of products identified in this rulemaking the output piston rod assembly (piston rod).
cadmium plate, or damage, inspecting action. This condition could lead to failure of the
for bare base metal, and reassembling piston rod, failure of the servo actuator, and
the servo actuator. Replacing the servo Regulatory Findings subsequent loss of helicopter control.
actuator with P/N 222–382–001–111 or We determined that this proposed AD (c) Affected ADs
P/N 222–382–001–111FM would be would not have federalism implications
This AD supersedes AD 2010–19–51,
required within 3,000 hours TIS or 4 under Executive Order 13132. This Amendment 39–16523 (75 FR 71540,
years, whichever occurs first. proposed AD would not have a November 24, 2010).
• Overhauling servo actuator P/N substantial direct effect on the States, on
the relationship between the national (d) Comments Due Date
222–382–001–111 or P/N 222–382–001–
111FM at intervals not to exceed 10 Government and the States, or on the We must receive comments by August 17,
years or 10,000 hours TIS, whichever distribution of power and 2015.
occurs first. responsibilities among the various (e) Compliance
levels of government. You are responsible for performing each
Differences Between the Proposed AD For the reasons discussed, I certify
and the TCCA AD action required by this AD within the
this proposed regulation: specified compliance time unless it has
The TCCA AD requires inspecting 1. Is not a ‘‘significant regulatory already been accomplished prior to that time.
each servo actuator to determine the action’’ under Executive Order 12866;
(f) Required Actions
condition of the piston rod assembly no 2. Is not a ‘‘significant rule’’ under the
later than 5 hours upon receiving the DOT Regulatory Policies and Procedures Before further flight:
(44 FR 11034, February 26, 1979); (1) Disassemble each servo actuator to gain
original issue of its AD. This proposed access to the piston rod as shown in Figures
AD would require inspecting each servo 3. Will not affect intrastate aviation in
1 through 5 and by following the
actuator to determine the condition of Alaska to the extent that it justifies Accomplishment Instructions, paragraph
the piston rod assembly before further making a regulatory distinction; and 3.A., Part I., of Woodward HRT Alert Service
flight. 4. Will not have a significant Bulletin No. 141600–67–02, Revision 0,
economic impact, positive or negative, dated August 18, 2010 (Woodward ASB).
Costs of Compliance on a substantial number of small entities (2) Clean the entire piston rod and nut
We estimate that this proposed AD under the criteria of the Regulatory using acetone and a nylon bristle brush
would affect 146 helicopters of U.S. Flexibility Act. removing all contaminates to allow for
We prepared an economic evaluation inspection. Inspect the grind relief
Registry and that labor costs average $85
of the estimated costs to comply with configuration for the piston rod and nut as
a work-hour. Based on these estimates, shown in Figure 6 of the Woodward ASB. If
we expect the following costs: this proposed AD and placed it in the the grind relief is unacceptable as shown in
• Inspecting a servo actuator would AD docket. Figure 6, replace the piston rod and the nut
require 4 work-hours per actuator for a List of Subjects in 14 CFR Part 39 with airworthy parts.
labor cost of $340. No parts would be (3) Using a 10× or higher magnifying glass,
needed for a total cost of $1,020 per Air transportation, Aircraft, Aviation visually inspect the nut for any corrosion or
helicopter and $148,920 for the U.S. safety, Incorporation by reference, any damage to the threads. If you find any
fleet given 3 actuators per helicopter. Safety. corrosion or any damage to the threads,
replace the nut with an airworthy nut.
• Replacing a servo actuator would The Proposed Amendment (4) Using a 10× or higher magnifying glass,
require 8 work-hours for a labor cost of visually inspect the piston rod as shown in
$680. Parts would cost $35,700 for a Accordingly, under the authority
Figure 7 of the Woodward ASB for any
total cost of $36,380 per actuator. delegated to me by the Administrator,
corrosion, visible lack of cadmium plate
• Overhauling the servo actuator the FAA proposes to amend 14 CFR part (gold or gray color), or damage to the piston
would require 8 work-hours for a labor 39 as follows: rod. For the purposes of this AD, damage to
cost of $680. Parts would cost $11,900 the piston rod is defined as pitting, a visible
PART 39—AIRWORTHINESS scratch, a crack, or a visible abrasion.
for a total cost of $12,580 per actuator.
DIRECTIVES (i) If there is any corrosion or visible lack
Authority for This Rulemaking of cadmium plate or any damage to the
■ 1. The authority citation for part 39 piston rod in the Critical Areas as shown in
Title 49 of the United States Code continues to read as follows: Figure 7 of the Woodward ASB, replace the
specifies the FAA’s authority to issue servo actuator with servo actuator P/N 222–
rules on aviation safety. Subtitle I, Authority: 49 U.S.C. 106(g), 40113, 44701.
382–001–111 or P/N 222–382–001–111FM
section 106, describes the authority of § 39.13 [Amended] before further flight.
the FAA Administrator. ‘‘Subtitle VII: (ii) If there is any corrosion or visible lack
■ 2. The FAA amends § 39.13 by adding
Aviation Programs,’’ describes in more of cadmium plate on the piston rod in areas
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS

the following new airworthiness that are not considered Critical Areas as
detail the scope of the Agency’s
directive (AD): shown in Figure 7 of the Woodward ASB,
authority.
We are issuing this rulemaking under Bell Helicopter Textron Canada: Docket No. rework the piston rod by removing any
FAA–2013–0734; Directorate Identifier surface corrosion that has not penetrated into
the authority described in ‘‘Subtitle VII,
2012–SW–080–AD. the base material by lightly buffing. Clean the
Part A, Subpart III, Section 44701: part using acetone and a nylon bristle brush
General requirements.’’ Under that (a) Applicability to remove any residue. Comply with
section, Congress charges the FAA with This AD applies to Bell Helicopter Textron paragraphs (f)(5) through (f)(7) of this AD.
promoting safe flight of civil aircraft in Canada (Bell) Model 222, 222B, 222U, 230, Within 1,200 hours time-in-service (TIS) or 1
air commerce by prescribing regulations and 430 helicopters, with a main rotor year, whichever occurs first, replace the

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Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules 34335

servo actuator with servo actuator P/N 222– (i) Additional Information removing certain engine mount parts
382–001–111 or P/N 222–382–001–111FM. (1) Bell Alert Service Bulletin (ASB) No. from service, measuring the height of
(iii) If there is any corrosion that is red or 222–11–111 for Model 222 and 222B the engine mounting base for certain
orange in color, magnetic particle inspect the helicopters, ASB No. 222U–11–82 for Model helicopters, replacing the engine mount
piston rod for a crack. 222U helicopters, ASB No. 230–11–43 for if a certain height is exceeded,
(A) If there is a crack, replace the servo Model 230 helicopters, and ASB No. 430–11– inspecting the flared coupling on certain
actuator with servo actuator, P/N 222–382– 46 for Model 430 helicopters, all Revision A
001–111 or P/N 222–382–001–111FM before
helicopters for a crack, and replacing
and all dated June 22, 2012, which are not
further flight. incorporated by reference, contain additional
the coupling if it is cracked. Since we
(B) If there is no crack, comply with information about the subject of this AD. For issued AD 2000–05–17 and AD 2001–
paragraphs (f)(5) through (f)(7) of this AD. Woodward HRT and Bell service information 04–12, there have been reports of
Within 2,400 hours TIS or 2 years, whichever identified in this AD, contact Bell Helicopter additional cracks in coupling tubes. The
occurs first, replace the servo actuator with Textron Canada Limited, 12,800 Rue de proposed actions are intended to
servo actuator P/N 222–382–001–111 or P/N l’Avenir, Mirabel, Quebec J7J1R4; telephone prevent coupling tube failure, loss of
222–382–001–111FM. (450) 437–2862 or (800) 363–8023; fax (450) engine drive, and a subsequent forced
(iv) If there is no corrosion, visible lack of 433–0272; or at http:// landing of the helicopter.
cadmium plate, or damage to the piston rod, www.bellcustomer.com/files/. You may
review a copy of the service information at DATES: We must receive comments on
comply with paragraphs (f)(5) through and
the FAA, Office of the Regional Counsel, this proposed AD by August 17, 2015.
(f)(7) of this AD. Within 3,000 hours TIS or
4 years, whichever occurs first, replace the Southwest Region, 2601 Meacham Blvd., ADDRESSES: You may send comments by
servo actuator with servo actuator P/N 222– Room 663, Fort Worth, Texas 76137. any of the following methods:
382–001–111 or P/N 222–382–001–111FM. (2) The subject of this AD is addressed in • Federal eRulemaking Docket: Go to
(5) Inspect the portion of the piston rod for the Transport Canada Civil Aviation (TCCA) http://www.regulations.gov. Follow the
any absence of cadmium plating (bare base AD No. CF–2010–29R1, dated July 26, 2012. online instructions for sending your
You may view the TCCA AD on the Internet
metal), as shown in Figure 7 of the
at http://www.regulations.gov in Docket No.
comments electronically.
Woodward ASB. If there is any bare base
FAA–2013–0734. • Fax: 202–493–2251.
metal on the piston rod in this area, apply • Mail: Send comments to the U.S.
brush cadmium plating to all bare and (j) Subject Department of Transportation, Docket
reworked areas using SPS5070 or equivalent Joint Aircraft Service Component (JASC) Operations, M–30, West Building
0.0002 to 0.0005 inch thick and rework the Code: 6730, Rotorcraft Servo System. Ground Floor, Room W12–140, 1200
piston rod by following the Accomplishment
Issued in Fort Worth, Texas, on May 29, New Jersey Avenue SE., Washington,
Instructions, paragraph C., Part III, C.1.1.1.
2015. DC 20590–0001.
through C.1.1.3., of the Woodward ASB.
(6) Reassemble the servo actuator by Lance T. Gant, • Hand Delivery: Deliver to the
following the Accomplishment Instructions, Acting Directorate Manager, Rotorcraft ‘‘Mail’’ address between 9 a.m. and 5
paragraph C, Part III, 1.1.4. through 3.3.4. of Directorate, Aircraft Certification Service. p.m., Monday through Friday, except
the Woodward ASB. [FR Doc. 2015–14278 Filed 6–15–15; 8:45 am] Federal holidays.
(7) Thereafter, overhaul servo actuator P/N BILLING CODE 4910–13–P Examining the AD Docket
222–382–001–111 or P/N 222–382–001–
111FM at intervals not to exceed 10 years or You may examine the AD docket on
10,000 hours TIS, whichever occurs first. DEPARTMENT OF TRANSPORTATION the Internet at http://
www.regulations.gov or in person at the
(g) Credit for Actions Previously Completed
Federal Aviation Administration Docket Operations Office between 9
Compliance with the Woodward ASB or a.m. and 5 p.m., Monday through
with AD 2010–19–51 (75 FR 71540, Friday, except Federal holidays. The AD
November 24, 2010) before the effective date 14 CFR Part 39
docket contains this proposed AD, the
of this AD is considered acceptable for [Docket No. FAA–2014–0105; Directorate
compliance with the corresponding Direction Generale de L’Aviation Civile
Identifier 2008–SW–58–AD]
inspections specified in paragraph (f) of this (DGAC) AD, the economic evaluation,
AD. If you replaced the piston rod pursuant RIN 2120–AA64 any comments received and other
to the Woodward ASB or paragraph (d)(1) or information. The street address for the
(d)(3) of AD 2010–19–51, apply the Airworthiness Directives; Airbus Docket Operations Office (telephone
requirements of paragraph (f)(4)(iv) of this Helicopters (Previously Eurocopter 800–647–5527) is in the ADDRESSES
AD. France) (Airbus Helicopters) section. Comments will be available in
Helicopters the AD docket shortly after receipt.
(h) Alternative Methods of Compliance
(AMOCs) AGENCY: Federal Aviation For service information identified in
Administration, DOT. this proposed AD, contact Airbus
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this Helicopters, Inc., 2701 N. Forum Drive,
ACTION: Notice of proposed rulemaking
AD. Send your proposal to: Matt Wilbanks, Grand Prairie, Texas 75052; telephone
(NPRM).
Aviation Safety Engineer, Regulations and (972) 641–0000 or (800) 232–0323; fax
Policy Group, Rotorcraft Directorate, FAA, SUMMARY: This document proposes (972) 641–3775; or at http://
2601 Meacham Blvd., Fort Worth, Texas superseding Airworthiness Directives www.airbushelicopters.com/techpub.
76137; telephone (817) 222–5110; email (AD) 2000–05–17 and AD 2001–04–12, You may review the service information
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS

matt.wilbanks@faa.gov. which apply to Eurocopter France (now at the FAA, Office of the Regional
(2) For operations conducted under a 14 Airbus Helicopters) Model EC120B Counsel, Southwest Region, 2601
CFR part 119 operating certificate or under Meacham Blvd., Room 663, Fort Worth,
helicopters. AD 2000–05–17 and AD
14 CFR part 91, subpart K, we suggest that Texas 76137.
you notify your principal inspector, or
2001–04–12 require repetitive visual
lacking a principal inspector, the manager of checks of the engine-to-main gearbox FOR FURTHER INFORMATION CONTACT:
the local flight standards district office or (MGB) coupling tube assembly James Blyn, Aviation Safety Engineer,
certificate holding district office before (coupling tube) for a crack and replacing Regulations and Policy Group,
operating any aircraft complying with this any cracked tube with an airworthy Rotorcraft Directorate, FAA, 2601
AD through an AMOC. tube. This proposed AD would require Meacham Blvd., Fort Worth, Texas

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Document Created: 2018-02-22 10:23:10
Document Modified: 2018-02-22 10:23:10

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period.
Dates		We must receive comments on this SNPRM by August 17, 2015.
Contact		Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected]
FR Citation		80 FR 34332
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 34332 - Airworthiness Directives; Bell Helicopter Textron Canada Helicopters

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 115 (June 16, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration