7642 Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 

instrument panel of each helicopter at 

an average labor rate of $85 per work 

hour, or $7,714 for the fleet. 

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 

helicopters 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): 

2013–01–05 Eurocopter France: 

Amendment 39–17319; Docket No. 

FAA–2012–0794; Directorate Identifier 

2006–SW–04–AD. 

(a) Applicability 

This AD applies to Model AS350B3 and 

EC130B4 helicopters with an Aircraft Parts 

Corporation 200-ampere (amp) starter 

generator, part number 200SGL130Q, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

excessive power consumption of the starter 

generator, which reduces the engine surge 

margin. This condition could result in engine 

failure 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 

Within the next 100 hours time-in-service: 

(1) Revise Paragraph 2, Limitations, of the 

Rotorcraft Flight Manual Supplement 29 to 

reduce the maximum current of the starter 

generator to 180 amps Max. continuous. 

(2) Install a placard, 125 millimeters long 

by 10 millimeters wide, on the instrument 

panel below the vehicle engine multifunction 

display indicating the starter generator 

reduced limitation: ‘‘MAXIMUM 

CONTINUOUS GENERATOR LOAD = 

180A.’’ 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Safety Management 

Group, Rotorcraft Directorate, FAA, may 

approve AMOCs for this AD. Send your 

proposal to: Chinh Vuong, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, Safety 

Management Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone (817) 

222–5110, fax (817) 222–5961, email 

chinh.vuong@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. 

(g) Additional Information 

(1) Eurocopter Alert Service Bulletins No. 

01.00.57 and No. 04A002, both Revision 1, 

and both dated September 14, 2006, which 

are not incorporated by reference, contain 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. You may review copies 

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 

European Aviation Safety Agency AD No. 

2006–0337, dated November 7, 2006. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: Starter-Generator 2435. 

Issued in Fort Worth, Texas, on January 9, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02236 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–2012–0731; Directorate 

Identifier 2012–CE–020–AD; Amendment 

39–17334; AD 2013–02–13] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Piper Aircraft, Inc. (type certificate 

previously held by The New Piper 

Aircraft Inc.) PA–28, PA–32, PA–34, 

and PA–44 airplanes. This AD was 

prompted by reports of control cable 

assembly failures that may lead to 

failure of the horizontal stabilator 

control system and could result in loss 

of pitch control. This AD requires 

inspections of the stabilator control 

system and replacement of parts as 

necessary. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD is effective March 11, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 11, 2013. 

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Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 7643 

ADDRESSES: For 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. 

You may review copies of the 

referenced service information at the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

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 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Hector Hernandez, Aerospace Engineer, 

FAA, Atlanta Aircraft Certification 

Office, 1701 Columbia Avenue, College 

Park, Georgia 30337; telephone: (404) 

474–5587; fax: (404) 474–5606; email: 

hector.hernandez@faa.gov. 

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 published in the Federal 

Register on August 2, 2012 (77 FR 

45979). That NPRM proposed to require 

inspections of the stabilator control 

system and replacement of parts as 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Rescind the AD 

Gregory E. Sniegowski, Carl 

Poplawsky, and Eric Stendahl stated 

that since inspections of the control 

systems and pulleys are already part of 

the annual inspection, the requirements 

of this AD would seem to be redundant 

and that the NPRM should be 

withdrawn. 

We do not agree. The service 

difficulty report (SDR) database shows 

that certain Piper models have multiple 

reports of cracks, corrosion, failure of 

the turnbuckle, control cable fraying, or 

cable swage end breaks. This AD was 

prompted by reports concerning an 

accident on a Piper Model PA–32R– 

301T and an incident on a Piper Model 

PA–32R–300 airplane. 

NTSB Support 

Deborah A.P. Hersman, Chairman, 

National Transportation Safety Board 

(NTSB), stated that two special 

airworthiness information bulletins 

(SAIBs) have been issued that 

recommend inspecting the entire 

surface of each cable terminal, 

turnbuckle, or other cable fittings for 

corrosion or cracking. Within the past 2 

years, the NTSB has investigated two 

accidents and one incident involving 

Piper airplanes where control cable 

assembly failures due to stress corrosion 

cracking led to failures of the horizontal 

stabilator control system. She stated that 

the fact these events continue to occur 

more than 10 years after the SAIBs were 

issued shows that the SAIBs were not 

effective. The NTSB supports the need 

for this AD. 

We concur with the findings by the 

NTSB. 

Removal of Surface Corrosion 

Joseph Boenzi stated that we should 

revise the AD to allow an individual to 

remove the surface corrosion on a 

turnbuckle by using a cleaning agent 

and then making a determination if the 

part is airworthy. There have been 

reports that surface corrosion on 

turnbuckles could be easily removed 

with scotch-brite. 

We agree because Piper investigated 

the possibility of using scotch-brite to 

remove surface corrosion and found it to 

be acceptable. We will change this AD 

to reference the revised Piper Aircraft, 

Inc. Mandatory Service Bulletin No. 

1245A, dated November 28, 2012, 

which incorporated cleaning agents and 

scotch-brite. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

45979, August 2, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 45979, 

August 2, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 

34,013 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection of the horizontal stabilator control 

system.

5 work-hours × $85 per hour = $425 ............ Not applicable .. $425 $14,455,525 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

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7644 Federal Register / Vol. 78, No. 23 / Monday, February 4, 2013 / Rules and Regulations 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of all stabilator control cable system— 

per set of cables.

10 work-hours × $85 per hour = $850 ......................... $608 $1,458 

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, 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. 

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): 

2013–02–13 Piper Aircraft, Inc.: 

Amendment 39–17334; Docket No. 

FAA–2012–0731; Directorate Identifier 

2012–CE–020–AD. 

(a) Effective Date 

This AD is effective March 11, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Models PA–28–236, 

PA–28–140, PA–28–150, PA–28–151, PA– 

28–160, PA–28–161, PA–28–180, PA–28– 

181, PA–28–201T, PA–28R–201, PA–28–235, 

PA–28R–201T, PA–28S–160, PA–28S–180, 

PA–28R–180, PA–28R–200, PA–28RT–201, 

PA–28RT–201T, PA–32–260, PA–32–301, 

PA–32–301T, PA–32–300, PA–32R–300, PA– 

32R–301T, PA–32R–301 (SP), PA–32R–301 

(HP), PA–32RT–300, PA–32RT–300T, PA– 

32S–300, PA–32–301FT, PA–32–301XTC, 

PA–34–200, PA–34–200T, PA–34–220T, PA– 

44–180, and PA–44–180T airplanes, all serial 

numbers, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2740, Stabilizer Control System. 

(e) Unsafe Condition 

This AD was prompted by reports of 

control cable assembly failures that may lead 

to failure of the horizontal stabilator control 

system and could result in loss of pitch 

control. This AD requires inspections of the 

stabilator control system and replacement of 

parts as necessary. We are issuing this AD to 

correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

(1) Initially inspect the stabilator control 

system following instructions 1 through 10 of 

Piper Aircraft, Inc. Mandatory Service 

Bulletin No. 1245A, dated November 28, 

2012, as follows: 

(i) If the age of the airplane is at or exceeds 

15 years as of March 11, 2013 (the effective 

date of this AD): At the next annual 

inspection or within the next 12 months after 

March 11, 2013 (the effective date of this 

AD). 

(ii) If the age of the airplane is less than 

15 years as of March 11, 2013 (the effective 

date of this AD): When the age of the airplane 

reaches 15 years, then at the next annual 

inspection or within 12 months after the 

airplane reaches 15 years of age. 

(iii) If the age of the airplane cannot be 

determined as of March 11, 2013 (the 

effective date of this AD): At the next annual 

inspection or within the next 12 months after 

March 11, 2013 (the effective date of this 

AD). 

Note for paragraph (g)(1)(i), (g)(1)(ii), and 

(g)(1)(iii) of this AD: To assist in determining 

the age of the airplane, you may contact Piper 

Aircraft, Inc., 2926 Piper Drive, Vero Beach, 

Florida 32960; telephone: (772) 567–4361; 

Internet: www.piper.com; or access the FAA 

airplane registry database at: http://registry.

faa.gov/aircraftinquiry/Serial_Inquiry.aspx. 

(2) After the applicable initial inspection 

required in paragraph (g)(1) of this AD, 

repetitively thereafter at intervals not to 

exceed 2,000 hours time-in-service or 7 years, 

whichever occurs first, inspect the stabilator 

control system following instructions 1 

through 10 of Piper Aircraft, Inc. Mandatory 

Service Bulletin No. 1245A, dated November 

28, 2012. 

(h) Repair 

If any cracks, corrosion, or cable fraying are 

found during any inspection required in 

paragraphs (g)(1) or (g)(2) of this AD, before 

further flight, replace the damaged part with 

an airworthy part. 

(i) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

This AD provides credit for the actions 

required in this AD if already done before 

March 11, 2013 (the effective date of this AD) 

following Piper Aircraft, Inc. Mandatory 

Service Bulletin No. 1245, dated May 3, 

2012. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

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(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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