16114 Federal Register / Vol. 74, No. 67 / Thursday, April 9, 2009 / Rules and Regulations 

ASB No. Revision Date Helicopter model 

222–07–106 ............................. C .............. September 20, 2007 ................................................................. 222 and 222B. 

222U–07–77 ............................. C .............. September 20, 2007 ................................................................. 222U. 

230–07–38 ............................... C .............. September 20, 2007 ................................................................. 230. 

407–07–81 ............................... A .............. September 19, 2007 ................................................................. 407. 

427–07–18 ............................... A .............. September 19, 2007 ................................................................. 427. 

430–07–41 ............................... C .............. September 20, 2007 ................................................................. 430. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

there have been three reports of blade tip 

weights departing from the blade during 

flight. This AD corrects part numbers and 

serial numbers of blades, and adds additional 

blades to the previous AD listing, based on 

revised ASBs issued by Bell Helicopter 

Textron Canada Limited. The actions 

required by this AD are intended to prevent 

loss of a blade tip weight, loss of a blade, and 

subsequent loss of control of the helicopter. 

Actions and Compliance 

(e) Before further flight, unless already 

accomplished, replace any affected blade 

with an airworthy blade. An airworthy blade 

is one that has a part number and a serial 

number that is not listed in the RBI 

document that is attached to each ASB listed 

in the Applicability section of this AD. 

Differences Between This AD and the MCAI 

AD 

(f) The actions required by this AD only 

apply to those blades listed in the RBI 

document that is attached to the ASBs listed 

in paragraph (c). The MCAI allows use of 

those ASBs, or ‘‘later revisions approved by 

Chief, Continuing Airworthiness, Transport 

Canada.’’ 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, FAA, ATTN: Sharon Miles, Aviation 

Safety Engineer, FAA, Rotorcraft Directorate, 

Regulations and Policy Group, 2601 

Meacham Blvd., Fort Worth, Texas 76193– 

0111, telephone (817) 222–5122, fax (817) 

222–5961, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Air Transport Association of America (ATA) 

Tracking Code 

(h) ATA Code 6410: Tail Rotor Blades. 

Material Incorporated by Reference 

(i) You must use the following Bell 

Helicopter Textron Alert Service Bulletin for 

your model helicopter to determine which 

blades are subject to these AD actions: 

ASB No. Revision Date Helicopter model 

206–07–116 ............................. A .............. September 19, 2007 ................................................................. 206A and 206B. 

206L–07–148 ........................... A .............. September 19, 2007 ................................................................. 206L, L–1, L–3, and L–4. 

222–07–106 ............................. C .............. September 20, 2007 ................................................................. 222 and 222B. 

222U–07–77 ............................. C .............. September 20, 2007 ................................................................. 222U. 

230–07–38 ............................... C .............. September 20, 2007 ................................................................. 230. 

407–07–81 ............................... A .............. September 19, 2007 ................................................................. 407. 

427–07–18 ............................... A .............. September 19, 2007 ................................................................. 427. 

430–07–41 ............................... C .............. September 20, 2007 ................................................................. 430. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada, 12,800 Rue de l’Avenir, Mirabel, 

Quebec J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272, or at 

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

(3) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., 76193–0111, or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or e-mail to: 

http://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued in Fort Worth, Texas on March 26, 

2009. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–7783 Filed 4–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0772; Directorate 

Identifier 2008–SW–30–AD; Amendment 39– 

15872; AD 2009–07–13] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc. Model MD900 

(including the MD902 Configuration) 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified MD Helicopters, Inc. (MDHI) 

model helicopters that requires, within 

30 days, reducing the current gross 

weight limit to a maximum gross weight 

limit of 5,400 pounds and inserting a 

copy of this AD into the Limitations 

section of the Rotorcraft Flight Manual 

(RFM) or making certain optional 

modifications that constitute 

terminating actions. This amendment is 

prompted by flight tests that show that 

the information currently listed in the 

Limitations section of the RFM is 

inconsistent with the actual 

performance of the helicopter. The 

actions specified by this AD are 

intended to prevent loss of directional 

control of the helicopter. 

DATES: Effective May 14, 2009. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of May 14, 

2009. 

ADDRESSES: You may get the service 

information identified in this AD from 

MD Helicopters Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615, Mesa, Arizona 

85215–9734, telephone 1–800–388– 

3378, fax 480–346–6813, or on the Web 

at http://www.mdhelicopters.com. 

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 

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Federal Register / Vol. 74, No. 67 / Thursday, April 9, 2009 / Rules and Regulations 16115 

New Jersey Avenue, SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

Chip Adam, Flight Test Pilot, FAA, Los 

Angeles Aircraft Certification Office, 

Flight Test Branch, 3960 Paramount 

Blvd., Lakewood, California 90712– 

4137, telephone (562) 627–5369, fax 

(562) 627–5210. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for the specified model 

helicopters was published in the 

Federal Register on July 28, 2008 (73 FR 

43646). That action proposed to require, 

for helicopters that have not complied 

with MDHI Mandatory SB900–099 R1, 

dated December 27, 2006 (SB), reducing 

the gross weight limit to a maximum 

gross weight limit of 5,400 pounds and 

inserting a copy of the AD into the 

Limitations section of the RFM. These 

actions would be required within 30 

days. The proposed AD also included 

optional terminating actions for the 

weight reduction. Those terminating 

actions would be to: 

• Determine if a NOTAR fan felt seal 

part number (P/N) 900F3441025–103 is 

installed. If a NOTAR fan felt seal, P/N 

900F3441025–103, is not installed, 

replace the installed seal with an 

airworthy NOTAR fan felt seal, P/N 

900F3441025–103, before further flight; 

and 

• Install a thruster extension kit in 

accordance with specified portions of 

SB. 

We have reviewed the SB, which 

describes procedures for adjusting the 

directional control system rigging, 

installing a thruster extension kit, and 

verifying that a NOTAR fan felt seal, 

part number (P/N) 900F3441025–103 is 

installed. The SB specifies that failure to 

comply with the procedures may result 

in reduced anti-torque control during 

certain combinations of high gross 

weight, density altitude, and wind 

critical conditions. The SB also 

indicates that the maximum gross 

weight of the helicopter will be lowered 

if the SB is not complied with. 

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. 

We estimate that this AD affects 31 

helicopters of U.S. registry. The 

estimated lost revenue attributable to 

the gross weight reduction is $1,750,000 

per helicopter over the life of the 

helicopter. It takes approximately c 

work hour per helicopter to insert the 

AD into the Limitations section of the 

RFM; 8 work hours to adjust the 

directional control system rigging; 8 

work hours to install a NOTAR fan felt 

seal; and 24 work hours to install a 

thruster extension kit at an average labor 

rate of $80 per work hour. The NOTAR 

fan felt seal and thruster extension kit 

cost approximately $16,000. However, 

the manufacturer has stated that they 

will provide the fan felt seal and the 

thruster extension kit to all operators at 

no cost to them and that they will also 

provide each affected operator a credit 

for the labor costs for a total of 32 work 

hours for those work hours required to 

perform the directional control rigging 

adjustment (8 work hours) and 

installation of the thruster extension kit 

(24 work hours). Based on these figures, 

the total estimated cost impact of this 

AD on U.S. operators is $1,920, 

assuming (1) The entire fleet chooses to 

modify their affected helicopter in 

accordance with the optional 

terminating action provision of this AD 

and there is no reduction in gross 

weight necessary, (2) the manufacturer 

covers all the costs of the parts and the 

labor costs associated with the rigging 

adjustment and installation of the 

thruster extension kit and (3) only 3 

helicopters need to have a new fan felt 

seal installed. 

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 to read as 

follows: 

2009–07–13 MD Helicopters, Inc.: 

Amendment 39–15872. Docket No. 

FAA–2008–0772; Directorate Identifier 

2008–SW–30–AD. 

Applicability: Model MD900 (including 

MD902 Configuration) helicopters that have 

not complied with MD Helicopters, Inc. 

(MDHI) Mandatory Service Bulletin SB900– 

099 R1, dated December 27, 2006, certificated 

in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent loss of directional control of the 

helicopter, accomplish the following: 

(a) Within 30 days, reduce the gross weight 

limit to a maximum gross weight limit of 

5,400 pounds by inserting a copy of this AD 

into the Limitations section of the Rotorcraft 

Flight Manual. 

(b) As an optional terminating action for 

the weight reduction mandated by paragraph 

(a) of this AD, accomplish the following: 

(1) Determine if a NOTAR fan felt seal part 

number (P/N) 900F3441025–103 is installed. 

If a NOTAR fan felt seal, P/N 900F3441025– 

103, is not installed, replace the installed seal 

with an airworthy NOTAR fan felt seal, P/N 

900F3441025–103, before further flight. 

(2) Install a thruster extension kit in 

accordance with the Accomplishment 

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16116 Federal Register / Vol. 74, No. 67 / Thursday, April 9, 2009 / Rules and Regulations 

Instructions, paragraph B.(3). through (17). of 

MDHI Mandatory SB900–099 R1, dated 

December 27, 2006, before further flight. 

Contacting the manufacturer is not required 

by this AD. 

(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, Los Angeles 

Aircraft Certification Office, ATTN: Chip 

Adam, Flight Test Pilot, FAA, Flight Test 

Branch, 3960 Paramount Blvd., Lakewood, 

California 90712–4137, telephone (562) 627– 

5369, fax (562) 627–5210, for information 

about previously approved alternative 

methods of compliance. 

(d) Special flight permits will not be 

issued. 

(e) The modification shall be done in 

accordance with the specified portions of 

MDHI Mandatory SB900–099 R1, dated 

December 27, 2006. 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 MD Helicopters Inc., Attn: 

Customer Support Division, 4555 E. 

McDowell Rd., Mail Stop M615, Mesa, 

Arizona 85215–9734, telephone 1–800–388– 

3378, fax 480–346–6813, or on the Web at 

http://www.mdhelicopters.com. 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 

May 14, 2009. 

Issued in Fort Worth, Texas, on March 26, 

2009. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–7780 Filed 4–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1240; Directorate 

Identifier 2008–NM–098–AD; Amendment 

39–15877; AD 2009–08–04] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation Model BH.125 

Series 600A Airplanes and Model 

HS.125 Series 700A Airplanes Modified 

in Accordance With Supplemental 

Type Certificate (STC) SA2271SW 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Hawker Beechcraft Corporation Model 

BH.125 series 600A airplanes and 

Model HS.125 series 700A airplanes. 

This AD requires inspecting the wiring 

diagrams containing the cockpit blowers 

and comparing with the current airplane 

configuration, and reworking the wiring 

if necessary. This AD results from a 

report indicating that a blower motor of 

the cockpit ventilation and avionics 

cooling system seized up and gave off 

smoke. We are issuing this AD to 

prevent smoke and fumes in the cockpit 

in the event that a blower motor seizes 

and overheats due to excessive current 

draw. 

DATES: This AD is effective May 14, 

2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 14, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Hawker 

Beechcraft Corporation, Department 62, 

P.O. Box 85, Wichita, Kansas 67201– 

0085; telephone 316–676–8238; fax 

316–676–6706; e-mail 

tmdc@hawkerbeechcraft.com; Internet 

https://www.hawkerbeechcraft.com/ 

service_support/pubs. 

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 (telephone 800–647–5527) 

is the 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: 

Andy Shaw, Aerospace Engineer, 

Special Certification Office, ASW–190, 

FAA Southwest Regional Office, 2601 

Meacham Boulevard, Fort Worth, Texas 

76137; telephone (817) 222–5188; fax 

(817) 222–5785. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Hawker Beechcraft Corporation 

Model BH.125 series 600A airplanes 

and Model HS.125 series 700A 

airplanes. That NPRM was published in 

the Federal Register on November 26, 

2008 (73 FR 71959). That NPRM 

proposed to require inspecting the 

wiring diagrams containing the cockpit 

blowers and comparing with the current 

airplane configuration, and reworking 

the wiring if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Change to Final Rule 

We have changed the product 

identification line to specify the 

airplane type certificate holder. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

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 40 

airplanes of U.S. registry. We also 

estimate that it takes about 1 work-hour 

per product to comply with this AD. 

The average labor rate is $80 per workhour. Based on these figures, we 

estimate the cost of this AD to U.S. 

operators to be $3,200, or $80 per 

product. 

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. 

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