Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 7645 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(k) Related Information 

For more information about this AD, 

contact Hector Hernandez, Aerospace 

Engineer, FAA, Atlanta ACO, 1701 Columbia 

Avenue, College Park, Georgia 30337; 

telephone: (404) 474–5587; fax: (404) 474– 

5606; email: hector.hernandez@faa.gov. 

(l) 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) Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 1245A dated November 28, 

2012. 

(ii) Reserved. 

(3) For Piper Aircraft, Inc. service 

information identified in this AD, contact 

Piper Aircraft, Inc., 2926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 567– 

4361; Internet: http://www.piper.com/pages/ 

publications.cfm. 

(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: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on January 

22, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–02075 Filed 2–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0082; Directorate 

Identifier 2010–SW–036–AD; Amendment 

39–17318; AD 2013–01–04] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc., Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron, Inc. (Bell), Model 

412 and 412EP helicopters. This AD 

requires creating a component history 

card or equivalent record and begin 

counting and recording the number of 

accumulated landings for each high aft 

crosstube assembly (crosstube). Also, 

this AD requires installing ‘‘caution’’ 

decals regarding towing of a helicopter 

at or above 8,900 pounds. This AD also 

requires confirming the crosstube is 

within the horizontal deflection limits 

and replacing it if it is not. This AD also 

requires a recurring fluorescent 

penetrant inspection (FPI) of each 

crosstube and upper center support for 

a crack, any corrosion, nick, scratch, 

dent, or any other damage. This AD 

requires repairing damaged crosstubes 

and upper center supports that are 

within acceptable limits, reworking 

crosstubes by bonding on abrasion 

strips, and replacing each unairworthy 

crosstube with an airworthy crosstube. 

This AD was prompted by analysis of 

the crosstubes conducted as a result of 

recent field failures and corrosion 

problems of the affected crosstubes. The 

actions are intended to prevent failure 

of a crosstube, collapse of the landing 

gear, and subsequent loss of control of 

the helicopter. 

DATES: This AD is effective March 11, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of March 11, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, Texas 76101; telephone 

(817) 280–3391; fax (817) 280–6466; 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. 

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 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 February 3, 2012, at 77 FR 5427, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 to include an AD that would apply 

to Bell Model 412 and 412EP 

helicopters. That NPRM proposed to 

require counting and recording the 

number of accumulated landings for 

each crosstube on a component history 

card or equivalent record and installing 

CAUTION decals regarding towing a 

helicopter that weighs at or above 8,900 

pounds. The NPRM also proposed to 

require confirming that the crosstube is 

within the horizontal deflection limits 

and replacing it if it is not. Also, the 

NPRM proposed to require a recurring 

FPI of each crosstube and upper center 

support for a crack, any corrosion, a 

nick, scratch, dent, or other damage, 

repairing each damaged crosstube and 

upper center support if there is damage 

within acceptable limits, reworking 

each crosstube by bonding abrasion 

strips, and replacing each unairworthy 

crosstube. 

The affected crosstubes are the older 

non-anodized configuration and have 

had a service history of corrosion 

problems. In response to reports of field 

failures, Bell has completed a load level 

survey, material coupon testing, and 

additional analysis of the crosstubes. 

The results indicate that fatigue damage 

can occur during towing and landing. 

The proposed requirements were 

intended to prevent failure of a 

crosstube, collapse of the landing gear, 

and subsequent loss of control of the 

helicopter. 

Comments 

After our NPRM (77 FR 5427, 

February 3, 2012) was published, we 

received comments from one 

commenter. 

Request 

One commenter objected to the 

proposal because of ‘‘continual noise, 

pollution and aggravation as a result of 

low flying planes.’’ The commenter 

expressed concern about additional 

airplanes operating at lower altitudes for 

longer periods of time over her home 

near Peachtree-Dekalb Airport, Georgia. 

We find that this comment does not 

pertain to the NPRM (77 FR 5427, 

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7646 Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 

February 3, 2012) regarding Bell Model 

412 and 412EP helicopters, and believe 

the comment was attached to the NPRM 

in error. We find the comment does not 

warrant extending the comment period 

or withdrawing the proposed action. 

FAA’s Determination 

We have reviewed the relevant 

information, considered the comment 

received, 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 

We have reviewed Bell Helicopter 

Alert Service Bulletin No. 412–09–135, 

dated August 25, 2009 (ASB). The ASB 

specifies, within 6 months after 

receiving the ASB, for each affected 

crosstube, a recurring 12 month/2500 

landing FPI, a recurring 12 month/2500 

landing deflection check, and use of a 

towing retention kit per BHT–412–SI–58 

Gross Weight Towing Kit Provisions and 

Puller Equipment for helicopters that 

weigh 8900 pounds or higher. 

Costs of Compliance 

We estimate that this AD will affect 

115 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. It will take about 1 work-hour 

to create a component history card or 

equivalent record and begin to 

determine and record the number of 

accumulated landings; 0.5 work-hour to 

install caution decals on the pilot and 

co-pilot side of each helicopter; 0.5 

work-hour to measure the horizontal 

deflection of each crosstube; 3 workhours to inspect and prepare the area 

and do an FPI on each crosstube; 4 

work-hours to rework a crosstube, 

assuming 5 will need to be reworked; 

and 2 work-hours to replace a crosstube, 

assuming 3 will need to be replaced. 

The average labor rate is $85 per workhour and required parts for a 

replacement crosstube will cost about 

$9,315 per helicopter. Based on these 

figures, we estimate the total cost 

impact of this AD on U.S. operators to 

be $79,030. 

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 

■ 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 adding 

the following new airworthiness 

directive (AD): 

2013–01–04 Bell Helicopter Textron, Inc.: 

Amendment 39–17318; Docket No. 

FAA–2012–0082; Directorate Identifier 

2010–SW–036–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron, 

Inc. (Bell), Model 412 and 412EP helicopters 

with a high aft crosstube assembly 

(crosstube), part number (P/N) 412–050–011– 

101, –103, –105, –107; or 412–050–045–105, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure and corrosion of the affected 

crosstubes. This condition could result in 

collapse of the landing gear and subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective March 11, 2013. 

(d) 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. 

(e) Required Actions 

(1) Within 50 hours time-in-service (TIS): 

(i) For each crosstube, create a component 

history card or equivalent record. Begin to 

count and record the number of accumulated 

landings for each crosstube. For the purposes 

of this AD, a landing would be counted 

anytime the helicopter lifts off into the air 

and then lands again with any further 

reduction of the collective after the landing 

gear touches the ground. 

(ii) Install CAUTION decals, P/N 212–070– 

600–143, on the pilot and co-pilot sides of 

each helicopter as depicted in Figure 3 of 

Bell Helicopter Alert Service Bulletin No. 

412–09–135, dated August 25, 2009 (ASB), 

and by following the Accomplishment 

Instructions, Part III—Towing, paragraph 1., 

of the ASB. 

(2) Within 6 months and thereafter at 

intervals not to exceed 12 months or 2,500 

landings, whichever occurs first, determine 

the horizontal deflection of each crosstube 

from the centerline of the helicopter (BL 0.0) 

to the outside edge of each skid tube. Before 

further flight, replace any crosstube that 

exceeds any maximum allowable deflection 

limit contained in the maintenance manual. 

(3) Within 6 months and thereafter at 

intervals not to exceed 12 months or 2,500 

landings, whichever occurs first: 

(i) Remove and disassemble the landing 

gear assembly to prepare each crosstube for 

a fluorescent penetrant inspection (FPI) by 

following the Accomplishment Instructions, 

Part I, paragraphs 1. through 9., of the ASB. 

Note 1 to paragraph (e)(3)(i) of this AD: 

Abrasion strip, P/N 206–050–301–111; lower 

center support, P/N 412–050–007–101, with 

the incorporated Larson L101 abrasion strip; 

and lower center support, P/N 604–026–003, 

if installed on any crosstube, P/N 412–050– 

045–105, or reworked crosstubes, P/N 412– 

050–011–101, –103, –105, or –107, are only 

removed if required by following the 

instructions in the ASB (see items 2, 5, and 

6 in Figure 1 of the ASB). 

(ii) Clean and prepare the crosstube for the 

FPI by removing the sealant and paint in the 

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Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 7647 

area depicted in Figure 2 of the ASB by 

following the Accomplishment Instructions, 

Part I, ‘‘Cleaning and Preparation,’’ 

paragraphs 1. through 5., of the ASB. 

(iii) Perform an FPI of each crosstube and 

upper center support, P/N 412–050–006–101, 

for a crack, any corrosion, a nick, scratch, 

dent, or any other damage by following the 

Accomplishment Instructions, Part I, 

‘‘Inspection,’’ paragraphs 1. through 3. of the 

ASB. Use Table 2 in the ASB to determine 

the appropriate Inspection Criteria Table to 

use in the maintenance manual, which list 

the maximum repair damage limits for each 

crosstube P/N applicable to this AD. 

(iv) Repair the crosstube or upper center 

support if there is any corrosion, a nick, 

scratch, dent, or any other damage that is 

within the maximum repair damage limits, 

before further flight, or replace the crosstube 

with an airworthy crosstube. 

Note 2 to paragraph (e)(3)(iv) of this AD: 

The repair procedures are specified in the 

Component Repair and Overhaul Manual. 

(v) If there is a crack or other damage 

beyond any of the maximum repair damage 

limits, before further flight, replace the 

crosstube with an airworthy crosstube. 

(4) Before further flight, after completing 

paragraph (e)(3) of this AD, rework each 

crosstube P/N 412–050–011–101, –103, –105, 

or –107 by applying the bonding procedures 

and abrasion strips on the under side of the 

crosstubes at BL 0.0 and BL 14 by following 

the Accomplishment Instructions, Part I, 

‘‘Rework of Crosstubes,’’ paragraphs 1. 

through 10. of the ASB. Record on the 

component history card or equivalent record 

an ‘‘FM’’ to the end of the part number 

sequence of each crosstube that has been 

reworked (for example, 412–050–011– 

107FM). Omit the Larson L101 abrasion strip 

at BL 0.0 on each crosstube when installing 

lower center support, P/N 604–026–003 (see 

item 6 in Figure 1 of the ASB). 

(f) Special Flight Permits 

Special flight permits for inspections only 

may be issued under 14 CFR 21.197 and 

21.199 to operate the helicopter to a location 

where the requirements of this AD can be 

accomplished. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: 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. 

(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. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 3210, Main Landing Gear. 

(i) 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 Helicopter Alert Service Bulletin 

No. 412–09–135, dated August 25, 2009. 

(ii) Reserved. 

(3) For Bell Helicopter service information 

identified in this AD, contact Bell Helicopter 

Textron, Inc., P.O. Box 482, Fort Worth, 

Texas 76101; telephone (817) 280–3391; fax 

(817) 280–6466; or at http:// 

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: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on January 9, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02238 Filed 2–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0639; Directorate 

Identifier 2012–NM–005–AD; Amendment 

39–17329; AD 2013–02–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by a 

report that the safe life limit and 

inspection requirements for the 

horizontal stabilizer trim actuator 

(HSTA) attachment pins and trunnions 

were not listed in the Airworthiness 

Limitations Section of the maintenance 

program. This AD requires inspecting 

the trunnions and upper and lower pins 

for gouges, scratches, and corrosion, and 

replacing the trunnions if necessary; 

and adding serial numbers and new part 

numbers to certain trunnions, and upper 

and lower pins. This AD also requires 

revising the maintenance program to 

incorporate the information specified in 

certain temporary revisions of the 

limitations section. We are issuing this 

AD to detect and correct cracking, 

gouges, scratches, and corrosion of the 

HSTA attachment pins and trunnions, 

which could result in failure of these 

pins and trunnions and consequent 

disconnection of the horizontal 

stabilizer and subsequent loss of 

controllability of the airplane. 

DATES: This AD becomes effective 

March 11, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 11, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 20, 2012 (77 FR 36948). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

During a review of the Horizontal 

Stabilizer Trim Actuator (HSTA) system, it 

was discovered that the safe life limits and 

the inspection requirements for the HSTA 

attachment pins and trunnions were not 

listed in the Airworthiness Limitations 

Section of the Instructions for Continued 

Airworthiness. Also, the HSTA attachment 

pins and trunnions were not serialized 

making it impossible to keep accurate records 

of the life of these parts. Failure of these pins 

and trunnions will lead to a disconnect of the 

horizontal stabilizer and subsequent loss of 

the aeroplane. 

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