Document ID: FAA-2013-0734-0004
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bell Helicopter Textron Canada Helicopters
Posted Date: 2015-06-16T04:00Z

[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)]
[Proposed Rules]
[Pages 34332-34335]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[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.

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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.

(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 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