This section of the FEDERAL REGISTER

contains regulatory documents having general

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are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

33159 

Vol. 75, No. 112 

Friday, June 11, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0071; Directorate 

Identifier 2006–SW–27–AD; Amendment 39– 

16291; AD 2010–10–12] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Model 222, 

222B, 222U, 230, and 430 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for the specified Bell Helicopter Textron 

Canada (BHTC) helicopters, that 

currently requires certain checks and 

inspections of the tail rotor blades. If a 

crack is found, the existing AD requires 

replacing the tail rotor blade (blade) 

with an airworthy blade before further 

flight. This amendment requires the 

same checks and inspections of the 

blades until they are required to be 

replaced and removes certain serial 

numbered and specifically coded blades 

from the applicability of the AD. This 

amendment is prompted by the 

approved rework of certain blades and 

two newly redesigned blades, which, if 

installed, constitute terminating action 

for the inspection requirements. The 

actions specified by this AD are 

intended to detect a crack in a blade, 

and to prevent loss of a blade and 

subsequent loss of control of the 

helicopter. 

DATES: Effective July 16, 2010. 

ADDRESSES: 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 this 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or at the Docket 

Operations office, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Sharon 

Miles, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5122, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: On 

February 10, 2005, we issued AD 2005– 

04–09, Amendment 39–13981 (70 FR 

8021, February 17, 2005), that 

superseded AD 2004–26–11, 

Amendment 39–13923 (70 FR 7, January 

3, 2005), to require certain checks and 

inspections of the blades. Both AD 

2004–26–11 and 2005–04–09 also 

require replacing any cracked blade 

before further flight. AD 2004–26–11 

was prompted by reports of cracked 

blades and required certain checks, 

inspections, and replacements, if 

necessary. AD 2005–04–09 required the 

same checks and inspections as AD 

2004–26–11 but also added two serial 

numbers to the applicability and 

corrected some typographical errors. 

Since issuing AD 2005–04–09, the 

manufacturer has introduced a rework 

procedure for the affected blades and 

two newly redesigned blades, which, if 

installed, constitute terminating action 

for the inspection requirements. 

Therefore, a proposal to amend 14 CFR 

part 39 by superseding AD 2005–04–09 

for the specified BHTC model 

helicopters was published as a Notice of 

proposed rulemaking (NPRM) in the 

Federal Register on July 28, 2008 (73 FR 

43648, July 28, 2008). That NPRM 

proposed the same checks, inspections, 

and replacements of the blades. The 

NPRM also proposed to remove certain 

serial numbered and specifically coded 

blades from the applicability of the AD. 

The NPRM was prompted by the 

approved rework of certain blades and 

two newly redesigned blades, which, if 

installed, constitutes terminating action 

for the inspection requirements. 

Transport Canada, the airworthiness 

authority for Canada, notified the FAA 

that an unsafe condition may exist on 

the specified BHTC model helicopters. 

Transport Canada advises of the 

discovery of cracked blades during 

scheduled inspections on three 

occasions. Two cracks originated from 

the outboard feathering bearing bore 

underneath the flanged sleeves. The 

third crack started from the inboard 

feathering bearing bore. Investigation 

found that the cracks originated from 

either a machining burr or a corrosion 

site in the bearing bore underneath the 

flanged sleeves. 

BHTC has issued Alert Service 

Bulletin (ASB) No. 222–04–100, 

Revision B, for Model 222 and 222B 

helicopters; ASB No. 222U–04–71, 

Revision B, for Model 222U helicopters; 

ASB No. 230–04–31, Revision B, for 

Model 230 helicopters; and ASB No. 

430–04–31, Revision C, for Model 430 

helicopters, all dated March 31, 2008. 

The ASBs specify a visual inspection of 

the blade root end around the feathering 

bearings for a crack, not later than at the 

next scheduled inspection, and 

thereafter at every 3 flight hours 

maximum. Further, they describe a 

visual inspection for a crack, to include 

removing the blade from the helicopter 

if a crack is found in the paint, within 

the next 50 flight hours, and thereafter 

at every 50 flight hours. In addition, the 

ASBs state that, on or before December 

31, 2008, each blade should be 

reworked by Rotor Blades, Inc., or 

exchanged if the blade has less than 

4,000 hours TIS or if the blade has 4,000 

or more hours TIS, the blade should 

continue to be repetitively inspected or 

a replacement blade should be ordered. 

Transport Canada classified these 

service bulletins as mandatory and 

issued AD CF–2004–21R3, dated April 

23, 2008, to ensure the continued 

airworthiness of these helicopters in 

Canada. 

This AD differs from the ASB in that 

it requires, on or before 90 days after the 

effective date of the AD, replacing all 

affected blades with airworthy blades 

that are not subject to the inspection 

requirements, without differentiating 

between blades based on hours TIS. 

Additionally, this AD does not require 

operators to send their blades to Rotor 

Blades, Inc. for rework. 

These helicopter models are 

manufactured in Canada and are type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

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33160 Federal Register / Vol. 75, No. 112 / Friday, June 11, 2010 / Rules and Regulations 

agreement. Pursuant to the applicable 

bilateral agreement, Transport Canada 

has kept the FAA informed of the 

situation described above. The FAA has 

examined the findings of Transport 

Canada, reviewed all available 

information, and determined that AD 

action is necessary for products of these 

type designs that are certificated for 

operation in the United States. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. The FAA has 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed. However, we have 

inserted the Joint Aircraft System/ 

Component Code into this AD for 

informational purposes. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of this 

AD. 

We estimate that this AD will affect 

156 helicopters of U.S. registry, and the 

required actions will take: 

• About 0.25 work hour for a pilot 

check, and 2 work hours for a 

maintenance inspection, at an average 

labor rate of $80 per work hour, and 

• About 6 work hours to remove and 

replace the blade. Required parts will 

cost about $13,410 per blade, assuming 

one blade per helicopter is replaced 

each year. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators is $3,090,360, assuming each 

helicopter requires 200 pilot checks and 

12 maintenance inspections prior to 

replacing a blade on or before the 

compliance date for all affected 

helicopters. 

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, 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 

removing Amendment 39–13981 (70 FR 

8021, February 17, 2005), and by adding 

a new airworthiness directive (AD), 

Amendment 39–16291, to read as 

follows: 

2010–10–12 Bell Helicopter Textron 

Canada: Amendment 39–16291. Docket 

No. FAA–2008–0071; Directorate 

Identifier 2006–SW–27–AD. Supersedes 

AD 2005–04–09, Amendment 39–13981, 

Docket No. FAA–2005–20107. 

Applicability: The following 

helicopter models, with a listed 

helicopter serial number (S/N) and a 

listed part-numbered tail rotor blade 

(blade) installed, that does not have an 

excepted S/N or code, certificated in 

any category. 

Helicopter 

model Helicopter S/N Blade Part No. (P/N) 

222 ................... 47006 through 47089 .............. 222–016–001–123, –123M, –127, -127M, –131, –135, –139M, –141M, except those P/Ns 

with S/Ns listed in Exceptions 1 and 2 or the ‘‘R’’ code described in Exception 3. 

222B ................. 47131 through 47156 .............. 222–016–001–123, –123M, –127, -127M, –131, –135, –139M, –141M, except those P/Ns 

with S/Ns listed in Exceptions 1 and 2 or the ‘‘R’’ code described in Exception 3. 

222U ................. 47501 through 47574 .............. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 

2 or the ‘‘R’’ code described in Exception 3. 

230 ................... 23001 through 23038 .............. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 

2 or the ‘‘R’’ code described in Exception 3. 

430 ................... 49001 through 49107 .............. 222–016–001–123, –123M, –131, –139M, except those P/Ns with a S/N listed in Exception 

2 or the ‘‘R’’ code described in Exception 3. 

Exception 1: Blade, P/N 222–016– 

001–135 or –141M, S/N A–1502, A– 

1503, A–1504, A–1505, A–1507, A– 

1508, A–1509, A–1510, A–1556, A– 

1557, A–1558, A–1560, A–1561, A– 

1574, A–1635, A–1636, A–1828, A– 

1829, and S/Ns with a prefix of ‘‘A’’ and 

a number greater than 1829 have the 

intent of this proposal accomplished 

prior to delivery and no further action 

is required by this AD. 

Exception 2: Blade, P/N 222–016– 

001–131 and –139M, S/N A–2049, A– 

2055, A–2060, A–2070, A–2071, A– 

2085, and S/Ns with a prefix of ‘‘A’’ and 

a number greater than 2085 have the 

intent of this proposal accomplished 

prior to delivery and no further action 

is required by this AD. 

Exception 3: Blades identified with an 

‘‘R’’ code in the square block below the 

P/N field of the Data Plate have already 

been modified and no further actions 

are required by this AD. 

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Federal Register / Vol. 75, No. 112 / Friday, June 11, 2010 / Rules and Regulations 33161 

Note 1: New blades, P/N 222–016–001–139 

and –141, with no letter on the Data Plate 

after the P/N, are not subject to the 

requirements of this AD. 

Compliance: Required as indicated. 

To detect a crack in a blade, and to 

prevent loss of the blade and subsequent 

loss of control of the helicopter, 

accomplish the following: 

(a) Within 3 hours time-in-service 

(TIS), unless accomplished previously, 

and thereafter at intervals not to exceed 

3 hours TIS, clean and visually check 

both sides of each blade for a crack in 

the paint in the areas shown in Figure 

1 of this AD. An owner/operator (pilot), 

holding at least a private pilot 

certificate, may perform this visual 

check and must enter compliance with 

this paragraph into the helicopter 

maintenance records by following 14 

CFR 43.11 and 91.417(a)(2)(v). 

Note 2: Bell Helicopter Textron Alert 

Service Bulletin (ASB) No. 222–04–100, 

Revision B, for Model 222 and 222B 

helicopters; ASB No. 222U–04–71, Revision 

B, for Model 222U helicopters; ASB No. 230– 

04–31, Revision B, for Model 230 helicopters; 

and ASB No. 430–04–31, Revision C, for 

Model 430 helicopters, all dated March 31, 

2008, contain guidance on the subject of this 

AD. 

(b) If the visual check required by 

paragraph (a) of this AD reveals a crack 

in the paint, before further flight, 

remove the blade and follow the 

requirements in paragraphs (c)(2) 

through (c)(3)(ii) of this AD. 

(c) Within the next 50 hours TIS, 

unless accomplished previously, and 

thereafter at intervals not to exceed 50 

hours TIS, clean the blade by wiping 

down both surfaces of each blade in the 

inspection area depicted in Figure 1 of 

this AD using aliphatic naphtha (C–305) 

or detergent (C–318) or an equivalent. 

Using a 10X or higher power magnifying 

glass, visually inspect both sides of the 

blade in the areas depicted in Figure 1 

of this AD. 

(1) If a crack is found, even if only in 

the paint, before further flight, remove 

the blade from the helicopter and 

proceed with the following: 

(2) Remove the paint on the blade 

down to the bare metal in the area of the 

suspected crack by using plastic media 

blasting (PMB) or a nylon web abrasive 

pad. Abrade the blade surface in a spanwise direction only. 

Note 3: PMB may cause damage to 

helicopter parts if untrained personnel 

perform the paint removal. BHT–ALL–SPM, 

chapter 3, paragraph 3–24, contains guidance 

on the subject of this AD. 

(3) Using a 10X or higher power 

magnifying glass, inspect the blade for 

a crack. 

(i) If a crack is found, replace the 

blade with an airworthy blade before 

further flight. 

(ii) If no crack is found in the blade 

surface, refinish the blade by applying 

one coat of epoxy polyamide primer, 

MIL–P–23377 or MIL–P–85582, so that 

the primer overlaps the existing coats 

just beyond the abraded area. Let the 

area dry for 30 minutes to 1 hour. Then, 

apply one sealer coat of polyurethane, 

MILC85285 TYI CL2, color number 

27925 (semi-gloss white). Reinstall the 

blade. 

Note 4: BHT–ALL–SPM, chapter 4, 

contains guidance on painting the blade. 

(d) On or before 90 days after the 

effective date of this AD, replace any 

affected serial-numbered blade with an 

airworthy blade that has a S/N that is 

not subject to, or has been excepted 

from, the requirements of this AD. 

Installing an airworthy blade that is not 

subject to the requirements of this AD, 

or has been excepted from the 

requirements of this AD, including 

those blades with an ‘‘R’’ code in the 

square block below the part number 

field of the Data Plate, constitute a 

terminating action for the requirements 

of this AD. 

(e) 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, 

Safety Management Group, FAA, ATTN: 

Sharon Miles, Aviation Safety Engineer, 


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FAA, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone 

(817) 222–5122, fax (817) 222–5961, for 

information about previously approved 

alternative methods of compliance. 

(f) The Joint Aircraft System/ 

Component (JASC) Code is 6410: Tail 

Rotor Blades. 

(g) This amendment becomes effective 

on July 16, 2010. 

Note 5: The subject of this AD is addressed 

in Transport Canada (Canada) AD CF–2004– 

21R3, dated April 23, 2008. 

Issued in Fort Worth, Texas, on April 28, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11071 Filed 6–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0512; Directorate 

Identifier 2010–NE–21–AD; Amendment 39– 

16332; AD 2010–13–01] 

RIN 2120–AA64 

Airworthiness Directives; Microturbo 

Saphir 20 Model 095 Auxiliary Power 

Units (APUs) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by the European Aviation Safety 

Agency (EASA) to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

The turbine wheel, part number (P/N) 095– 

01–015–03, of the SAPHIR 20 Model 095 

APU is a life-limited part. Microturbo had 

determined through ‘‘fleet leader’’ testing and 

inspection that the published life limit of this 

turbine wheel should be reduced to 9,000 

cycles. Use of the turbine wheel beyond 

9,000 cycles could lead to the release of high 

energy debris that could jeopardize aircraft 

safety. 

For the reasons described above, EASA AD 

2008–0084 required the implementation of 

the new life limit on the affected parts and 

the replacement parts that had exceeded the 

new life limit. 

Microturbo has now determined that the 

life limit of the turbine wheel should be 

further reduced to 4,225 cycles. Use of the 

turbine wheel beyond 4,225 cycles could 

lead to the release of high energy debris that 

could jeopardize aircraft safety. 

We are issuing this AD to prevent an 

uncontained burst of the APU turbine 

that could liberate high-energy 

fragments resulting in injury and 

damage to the aircraft. 

DATES: This AD becomes effective July 

16, 2010. 

We must receive comments on this 

AD by July 26, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

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, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

michaelschwetz@faa.gov; telephone 

(781) 238–7761; fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Community, has issued AD 2010–0079, 

dated April 26, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

The turbine wheel, part number (P/N) 095– 

01–015–03, of the SAPHIR 20 Model 095 

APU is a life-limited part. Microturbo had 

determined through ‘‘fleet leader’’ testing and 

inspection that the published life limit of this 

turbine wheel should be reduced to 9,000 

cycles. Use of the turbine wheel beyond 

9,000 cycles could lead to the release of high 

energy debris that could jeopardize aircraft 

safety. 

For the reasons described above, EASA AD 

2008–0084 required the implementation of 

the new life limit on the affected parts and 

the replacement parts that had exceeded the 

new life limit. 

Microturbo has now determined that the 

life limit of the turbine wheel should be 

further reduced to 4,225 cycles. Use of the 

turbine wheel beyond 4,225 cycles could 

lead to the release of high energy debris that 

could jeopardize aircraft safety. 

For the reasons described above, this AD, 

which supersedes EASA AD 2008–0084, 

requires the implementation of the new life 

limit on the affected parts and the 

replacement of parts that had exceeded this 

new limit. This AD also extends the scope to 

include the P/N 095–01–015–20 turbine 

wheel, which is physically identical to the P/ 

N 095–01–015–03 turbine wheel but is 

manufactured using a revised process 

(approved by EASA). 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Microturbo has issued Service 

Bulletin 095–49–17, dated March 16, 

2010. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of EASA and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, they have 

notified us of the unsafe condition 

described in the MCAI and service 

information referenced above. We are 

issuing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

AD requires removal of turbine wheels 

P/N 095–01–015–03 or P/N 095–01– 

015–20, before exceeding the new 

reduced life limit of 4,225 cycles-inservice, and replacement with a new or 

serviceable part. 

FAA’s Determination of the Effective 

Date 

Since no domestic operators use this 

product, notice and opportunity for 

public comment before issuing this AD 

are unnecessary. Therefore, we are 

adopting this regulation immediately. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

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