35334 Federal Register / Vol. 76, No. 117 / Friday, June 17, 2011 / Rules and Regulations 

Issued in Fort Worth, Texas, on June 2, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–14246 Filed 6–16–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0561; Directorate 

Identifier 2010–SW–001–AD; Amendment 

39–16715; AD 2011–12–08] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. Model 205A, 

205A–1, 205B, 212, 412, 412CF, and 

412EP Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Bell Helicopter Textron, Inc. 

(BHT) model helicopters with tail rotor 

(T/R) blades with certain serial numbers 

installed. This action requires a onetime inspection of the T/R blade for 

corrosion or pitting, and repairing or 

replacing the T/R blade, if that 

condition is found during the 

inspection. This amendment is 

prompted by a report from the 

manufacturer that T/R blades with 

certain serial numbers may have 

manufacturing anomalies in the spar 

area. These actions are intended to 

detect corrosion or pitting in the 

forward spar area of a T/R blade to 

prevent a crack in the T/R blade, loss of 

the T/R blade, and subsequent loss of 

control of the helicopter. 

DATES: Effective July 5, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of July 5, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

August 16, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this AD from Bell 

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

Fort Worth, TX 76101, telephone (817) 

280–3391, fax (817) 280–6466, or at 

http://www.bellcustomer.com/files/. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Michael 

Kohner, ASW–170, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5447, fax 

(817) 222–5783. 

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD for the 

specified BHT model helicopters with 

an installed T/R blade, part number 

212–010–750 (all dash numbers), all 

serial numbers except those with a 

prefix of ‘‘A’’ and the number 17061 or 

larger. This action requires a one-time 

inspection of the T/R blade for corrosion 

or pitting after sanding the paint from 

the spar area between blade stations 

22.5 and 40.0, and repairing or replacing 

the T/R blade if corrosion, pitting, or 

damage is discovered. This amendment 

is prompted by a report from the 

manufacturer that T/R blades with 

certain serial numbers may have 

manufacturing anomalies in the spar 

area as a result of the chemical milling 

process. The anomalies may be 

identified as pits or corrosion on the 

spar. This corrosion or pitting condition 

in the forward spar of a T/R blade, if not 

corrected, could lead to a crack in the 

T/R blade, loss of the T/R blade, and 

subsequent loss of control of the 

helicopter. 

We have reviewed the following BHT 

Alert Service Bulletins, all Revision A, 

and all dated December 8, 2009, which 

specify a one-time inspection of the T/R 

blades for corrosion or pitting, and 

repairing or replacing the T/R blade if 

corrosion, pitting, or other damage is 

discovered: 

• Alert Service Bulletin (ASB) No. 

205–09–102, for Model 205A and 

205A–1 helicopters; 

• ASB No. 205B–09–54, for Model 

205B helicopters; 

• ASB No. 212–09–134, for Model 

212 helicopters; 

• ASB No. 412CF–09–38, for Model 

412CF helicopters; and 

• ASB No. 412–09–136, for Model 

412 and 412EP helicopters. 

This unsafe condition is likely to exist 

or develop on other helicopters of these 

same type designs. Therefore, this AD is 

being issued to require inspecting the 

T/R blades to detect corrosion or pitting 

in the forward spar area that could 

result in a crack, loss of a T/R blade, and 

subsequent loss of control of the 

helicopter. Accomplish the actions by 

following specified portions of the ASBs 

described previously. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the structural integrity 

and controllability of the helicopter. 

Therefore, inspecting the T/R blade for 

corrosion or pitting is required within 

25 hours time-in-service (TIS) or 30 

days, whichever occurs first. This is a 

very short compliance time, and this AD 

must be issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

We estimate that this AD will affect 

263 helicopters. Removing, inspecting, 

refinishing, and re-installing the T/R 

blade will take about 10 work hours at 

an average labor rate of $85 per work 

hour and an approximate labor cost of 

$850 per helicopter. Replacing the T/R 

blade with an airworthy blade will take 

about 6 work hours at an average labor 

rate of $85 per work hour for an 

approximate labor cost of $510 per 

helicopter. Required parts will cost 

about $17,495 for each T/R blade 

assembly. Based on these figures, we 

estimate the total cost impact of the AD 

on U.S. operators to be $277,565, 

assuming all affected helicopters are 

inspected and three T/R blades are 

replaced. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

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Federal Register / Vol. 76, No. 117 / Friday, June 17, 2011 / Rules and Regulations 35335 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2011–0561; 

Directorate Identifier 2011–SW–001– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Regulatory Findings 

We have determined that 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 the 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); and 

3. 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. See the AD docket to examine 

the economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends Part 39 of the 

Federal Aviation Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive (AD) to 

read as follows: 

2011–12–08 Bell Helicopter Textron, Inc. 

(BHT): Amendment 39–16715. Docket 

No. FAA–2011–0561; Directorate 

Identifier 2010–SW–001–AD. 

Applicability: Model 205A, 205A–1, 205B, 

212, 412, 412CF, and 412EP helicopters with 

a tail rotor (T/R) blade, part number 212– 

010–750 (all dash numbers), all serial 

numbers (S/Ns) except those S/Ns with a 

prefix of ‘‘A’’ and a number 17061 or larger, 

installed, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect corrosion or pitting in the 

forward spar area of a T/R blade to prevent 

a crack in the T/R blade, loss of the T/R 

blade, and subsequent loss of control of the 

helicopter, do the following: 

(a) Within 25 hours time-in-service (TIS) or 

30 days, whichever occurs first: 

(1) Remove the T/R hub and blade 

assembly from the helicopter and remove the 

T/R blade from the hub. Remove the paint 

from the spar area on both sides of the T/R 

blade by following the Accomplishment 

Instructions, paragraphs 3. through 5., of the 

following BHT Alert Service Bulletins, all 

Revision A, and all dated December 8, 2009: 

Alert Service Bulletin (ASB) No. 205–09–102 

for the Model 205A and 205A–1 helicopters; 

ASB No. 205B–09–54 for the Model 205B 

helicopters; ASB No. 212–09–134 for the 

Model 212 helicopters; ASB No. 412CF–09– 

38 for the Model 412CF helicopters; and ASB 

No. 412–09–136 for the Model 412 and 

412EP helicopters. 

(2) Using a 3-power or higher magnifying 

glass, visually inspect both sides of the T/R 

blade for any corrosion or pitting in the spar 

inspection areas as depicted in Figure 1 of 

the ASB for your model helicopter. 

(b) Before further flight: 

(1) If you find any corrosion or pitting that 

is 0.003 inch deep or less, either replace the 

unairworthy T/R blade with an airworthy T/ 

R blade or repair the T/R blade. 

Note: The maintenance and repair 

procedures along with the maximum repair 

damage limitations as referenced in 

paragraphs (b)(1) and (b)(3) of this AD are 

contained in the applicable maintenance 

manual and component repair and overhaul 

manuals. 

(2) If you find any corrosion or pitting that 

is greater than 0.003 inch deep, replace the 

T/R blade with an airworthy T/R blade. 

(3) If any parent material is removed 

during the sanding operation required by 

paragraph (a)(1) of this AD, either replace the 

T/R blade with an airworthy T/R blade, or 

repair the T/R blade if the parent material 

removed is within the maximum repair 

damage limits. 

(4) If there is no corrosion or pitting and 

no damage greater than 0.003 inch deep, 

refinish the inspection areas and reinstall 

each T/R blade onto the T/R hub, install the 

T/R assembly on the helicopter and track and 

balance the T/R in accordance with the 

Accomplishment Instructions, paragraphs 8. 

through 10., of the ASB for your model 

helicopter. 

(c) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Rotorcraft 

Certification Office, FAA, Attn: Michael 

Kohner, ASW–170, Aviation Safety Engineer, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax (817) 

222–5783, for information about previously 

approved alternative methods of compliance. 

(d) Joint Aircraft System/Component 

(JASC) Code 6410: Tail rotor blades. 

(e) Accomplish the instructions in this AD 

by following the specified portions of the 

following Bell Helicopter Textron, Inc. Alert 

Service Bulletin, as applicable to your model 

helicopter: No. 205–09–102; No. 205B–09– 

54; No. 212–09–134; No. 412CF–09–38, or 

No. 412–09–136. Each Alert Service Bulletin 

is Revision A, and each is dated December 

8, 2009. The Director of the Federal Register 

approved this incorporation by reference in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

Part 51. Copies may be obtained from Bell 

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

Worth, TX 76101, telephone (817) 280–3391, 

fax (817) 280–6466, or at http:// 

www.bellcustomer.com/files. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas or 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/code_of_federal_

regulations/ibr_locations.html. 

(f) This amendment becomes effective on 

July 5, 2011. 

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35336 Federal Register / Vol. 76, No. 117 / Friday, June 17, 2011 / Rules and Regulations 

Issued in Fort Worth, Texas, on May 17, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–14247 Filed 6–16–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0957; Directorate 

Identifier 2010–NM–062–AD; Amendment 

39–16718; AD 2011–12–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires, for certain airplanes, 

reworking the bonding jumper 

assemblies on the drain tube assemblies 

of the slat track housing of the wings. 

For certain other airplanes, the existing 

AD requires repetitive inspections of the 

drain tube assemblies of the slat track 

housing of the wings to find 

discrepancies, corrective actions if 

necessary, and terminating action for 

the repetitive inspections. This new AD 

also requires replacing the drain tube 

assemblies. For certain airplanes, this 

new AD also requires installing an 

additional electrostatic bond path for 

the number 5 and 8 inboard slat track 

drain tube assemblies. For certain other 

airplanes, this new AD also requires 

reworking the bonding jumper 

assembly. This new AD also revises the 

applicability to include additional 

airplanes. This AD was prompted by (1) 

reports of fuel leaks from certain drain 

locations of the slat track housing near 

the engine exhaust nozzle, which could 

result in a fire when the airplane is 

stationary, or taxiing at low speed; (2) 

reports of a bonding jumper assembly of 

certain drain tubes that did not meet 

bonding specifications and could result 

in electrostatic discharge and an in-tank 

ignition source; and (3) reports of fuel 

leaks onto the main landing gear (MLG) 

as a result of a cracked drain tube at the 

number 5 or 8 slat track housing, which 

could let fuel drain from the main fuel 

tanks into the dry bay area of the wings 

and onto hot MLG brakes and result in 

a fire. 

DATES: This AD is effective July 22, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 27, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 28, 2001 (66 FR 

38350, July 24, 2001). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6509; fax: 425–917–6590; e-mail: 

rebel.nichols@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2001–14–19, 

amendment 39–12330 (66 FR 38350, 

July 24, 2001). That AD applies to the 

specified products. The NPRM was 

published in the Federal Register on 

October 7, 2010 (75 FR 61999). That 

NPRM proposed to continue to require, 

for certain airplanes, reworking the 

bonding jumper assemblies on the drain 

tube assemblies of the slat track housing 

of the wings. That NPRM also proposed 

to continue to require, for certain other 

airplanes, repetitive inspections of the 

drain tube assemblies of the slat track 

housing of the wings to find 

discrepancies, corrective actions if 

necessary, and terminating action for 

the repetitive inspections. That NPRM 

also proposed to require replacing the 

drain tube assemblies, and, for certain 

airplanes, installing an additional 

electrostatic bond path for the number 

5 and 8 inboard slat track drain tube 

assemblies. For certain other airplanes, 

that NPRM also proposed to require 

reworking the bonding jumper 

assembly. That NPRM also proposed to 

revise the applicability to include 

additional airplanes. 

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. 

Support for the NPRM 

Boeing concurs with the contents of 

the NPRM. 

Request To Clarify Service Information 

Continental Airlines requested that 

we revise the NPRM to correct 

discrepancies in Boeing Service Bulletin 

767–57A0094, Revision 2, dated 

December 17, 2009. (That service 

bulletin was cited in the NPRM as the 

appropriate source of service 

information for the drain tube 

replacement on Model 767–200, –300, 

and –300F series airplanes.) In Figure 13 

(Sheet 2 of 5) on page 104, and Figure 

14 (Sheet 2 of 5) on page 109, the view 

identified as ‘‘C’’ should be identified as 

‘‘A.’’ These discrepancies were 

communicated to Boeing and confirmed 

as discrepancies. 

We agree and have revised paragraph 

(j) in this final rule to specify these 

corrections. 

Request To Clarify Requirements 

American Airlines stated that the 

Relevant Service Information section of 

the NPRM provides the current 

requirements (for AD 2001–14–19) but 

does not provide in detail the new 

additional requirements for the NPRM. 

That paragraph, according to the 

commenter, merely provides 

information regarding the service 

bulletins, not the specific proposed 

requirements. The commenter added 

that the Relevant Service Information 

section does not explain whether the 

new actions are to be done in 

accordance with the original or revised 

service information. The commenter 

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