54926 Federal Register / Vol. 76, No. 172 / Tuesday, September 6, 2011 / Rules and Regulations 

determined from Figure 3. Flutter 

clearance speeds V′ and V′′ may be 

based on the speed limitation specified 

for the remainder of the flight using the 

margins defined by § 25.629(b). 

V′ = Clearance speed as defined by 

Sec. 25.629(b)(2). 

V′′ = Clearance speed as defined by 

Sec. 25.629(b)(1). 

Qj = (Tj)(Pj) 

Where: 

Tj = Average time spent in failure condition 

j (in hours) 

Pj = Probability of occurrence of failure mode 

j (per hour) 

Note: If Pj is greater than 10¥3 per flight 

hour, then the flutter clearance speed must 

not be less than V′′. 

(v) Freedom from aeroelastic 

instability must also be shown up to V′ 

in Figure 3, above, for any probable 

system-failure condition combined with 

any damage required or selected for 

investigation by § 25.571(b). 

Consideration of certain failure 

conditions may be required by other 

sections of part 25 regardless of 

calculated system reliability. Where 

analysis shows the probability of these 

failure conditions to be less than 10¥9, 

criteria other than those specified in this 

paragraph may be used for structural 

substantiation to show continued safe 

flight and landing. 

4. Failure indications. For systemfailure detection and indication, the 

following apply: 

a. The system must be checked for 

failure conditions, not extremely 

improbable, that degrade the structural 

capability below the level required by 

part 25 or that significantly reduce the 

reliability of the remaining system. As 

far as reasonably practicable, the 

flightcrew must be made aware of these 

failures before flight. Certain elements 

of the control system, such as 

mechanical and hydraulic components, 

may use special periodic inspections, 

and electronic components may use 

daily checks, in lieu of detection-andindication systems to achieve the 

objective of this requirement. These 

certification-maintenance requirements 

must be limited to components that are 

not readily detectable by normal 

detection-and-indication systems and 

where service history shows that 

inspections provide an adequate level of 

safety. 

b. The existence of any failure 

condition, not extremely improbable, 

during flight that could significantly 

affect the structural capability of the 

airplane, and for which the associated 

reduction in airworthiness can be 

minimized by suitable flight limitations, 

must be signaled to the flightcrew. For 

example, failure conditions that result 

in an FS between the airplane strength 

and the loads of part 25 subpart C below 

1.25, or flutter margins below V′′, must 

be signaled to the flightcrew during 

flight. 

5. Dispatch with known failure 

conditions. If the airplane is to be 

dispatched in a known system-failure 

condition that affects structural 

performance, or affects the reliability of 

the remaining system to maintain 

structural performance, then the 

provisions of this special condition 

must be met, including the provisions of 

paragraph 2 in these special conditions 

for the dispatched condition, and 

paragraph 3 for subsequent failures. 

Expected operational limitations may be 

taken into account in establishing Pj as 

the probability of failure occurrence for 

determining the safety margin in Figure 

1. Flight limitations and expected 

operational limitations may be taken 

into account in establishing Qj as the 

combined probability of being in the 

dispatched failure condition, and the 

subsequent failure condition for the 

safety margins in Figures 2 and 3. These 

limitations must be such that the 

probability of being in this combined 

failure state, and then subsequently 

encountering limit-load conditions, is 

extremely improbable. No reduction in 

these safety margins is allowed if the 

subsequent system-failure rate is greater 

than 1E¥3 per hour. 

Issued in Renton, Washington, on August 

29, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22631 Filed 9–2–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1270; Directorate 

Identifier 2001–NE–50–AD; Amendment 39– 

16788; AD 2005–25–10R1] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers Type R321/4–82–F/8, R324/ 

4–82–F/9, R333/4–82–F/12, and R334/4– 

82–F/13 Propeller Assemblies 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. That AD 

currently requires initial and repetitive 

ultrasonic inspections of propeller hubs, 

part number (P/N) 660709201. This new 

AD requires introducing a new hub 

assembly P/N as an optional terminating 

action to the repetitive hub inspections. 

This AD was prompted by the need to 


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Federal Register / Vol. 76, No. 172 / Tuesday, September 6, 2011 / Rules and Regulations 54927 

introduce an optional terminating action 

for the repetitive inspections. We are 

issuing this AD to prevent propeller hub 

failure due to cracks in the hub, which 

could result in loss of control of the 

airplane. 

DATES: This AD is effective October 11, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 11, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Dowty 

Propellers, Anson Business Park, 

Cheltenham Road East, Gloucester GL 

29QN, UK; phone: 44 (0) 1452 716000; 

fax: 44 (0) 1452 716001. You may 

review copies of the referenced service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, 12 New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7761; fax: 781–238–7170; e-mail: 

michael.schwetz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2005–25–10, 

Amendment 39–14403 (70 FR 73364, 

December 12, 2005). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

April 18, 2011 (76 FR 21675). That 

NPRM proposed to continue to require 

initial and repetitive ultrasonic 

inspections of propeller hubs, P/N 

660709201. That NPRM also proposed 

to introduce as an optional terminating 

action for the initial and repetitive 

ultrasonic inspections of that AD, 

replacement of propeller hub P/N 

660709201 with a new propeller hub, P/ 

N 660717226. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 21675, April 18, 2011) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

132 propellers installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 0.5 work-hour per 

propeller to perform the inspection and 

about 1 hour to replace a propeller hub. 

The average labor rate is $85 per workhour. Required parts will cost about 

$19,500 per engine. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $2,590,830. 

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 

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 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 

removing airworthiness directive (AD) 

2005–25–10, Amendment 39–14403 (70 

FR 73364, December 12, 2005), and 

adding the following new AD: 

2005–25–10R1 Dowty Propellers (formerly 

Dowty Aerospace; Dowty Rotol Limited; 

and Dowty Rotol): Amendment 39– 

16788 ; Docket No. FAA–2010–1270; 

Directorate Identifier 2001–NE–50–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective October 11, 2011. 

Affected ADs 

(b) This AD revises AD 2005–25–10, 

Amendment 39–14403 (70 FR 73364, 

December 12, 2005). 

Applicability 

(c) This AD applies to Dowty Propellers 

Type R321/4–82–F/8, R324/4–82–F/9, R333/ 

4–82–F/12, and R334/4–82–F/13 propeller 

assemblies with propeller hubs, part number 

(P/N) 660709201. 

Unsafe Condition 

(d) This AD was prompted by the need to 

introduce an optional terminating action for 

the repetitive inspections. We are issuing this 

AD to prevent propeller hub failure due to 

cracks in the hub, which could result in loss 

of control of the airplane. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Initial Ultrasonic Inspections 

(f) Perform an initial ultrasonic inspection 

of the rear wall of the rear half of the 

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54928 Federal Register / Vol. 76, No. 172 / Tuesday, September 6, 2011 / Rules and Regulations 

propeller hub for cracks within the 

compliance time specified in Table 1 of this 

AD. Use Appendix A or Appendix D of the 

applicable Dowty Alert Service Bulletin (SB) 

listed in Table 1 of this AD to do the 

inspection. 

TABLE 1—APPLICABLE ALERT SB FOR PROPELLER TYPE

Propeller assembly 

type Initial inspection within . . . Repeat inspection within . . . Applicable SB 

(1) R334/4–82–F/13 10 flight hours (FH) time-in-service 

(TIS) after the effective date of this 

AD.

300 FH time-since-last-inspection 

(TSLI) or 300 flight cycles-since-last 

inspection, whichever occurs sooner.

Alert SB No. 61–1119, Revision 5, 

dated July 1, 2009. 

(2) R321/4–82–F/8 .. 50 FH TIS after the effective date of 

this AD.

1,000 FH TSLI ...................................... Alert SB No. 61–A1125, Revision 2, 

dated August 25, 2010. 

(3) R324/4–82–F/9 .. 50 FH TIS after the effective date of 

this AD.

1,000 FH TSLI ...................................... Alert SB No. 61–A1126, Revision 2, 

dated August 25, 2010. 

(4) R333/4–82–F/12 50 FH TIS after the effective date of 

this AD.

1,000 FH TSLI ...................................... Alert SB No. 61–A1124, Revision 2, 

dated August 25, 2010. 

(g) For hubs and propellers in storage, 

perform an initial ultrasonic inspection of the 

rear wall of the rear half of the propeller hub 

for cracks, before placing in service. Use 

Appendix A or Appendix D of the applicable 

Dowty Alert SB listed in Table 1 of this AD 

to do the inspection. 

Initial Inspection—Previous Credit 

(h) Propeller hubs, P/N 660709201, that 

previously passed inspection using Dowty 

Alert SBs listed in Table 1 of this AD or an 

earlier issue of those SBs, have satisfied the 

initial inspection requirements of this AD. 

However, you must comply with the 

repetitive inspection requirements found in 

this AD. 

Repetitive Ultrasonic Inspections 

(i) Thereafter, perform a repetitive 

ultrasonic inspection of the rear wall of the 

rear half of the propeller hub for cracks 

within the compliance time specified in 

Table 1 of this AD. Use Appendix A or 

Appendix D of the applicable Dowty Alert SB 

listed in Table 1 of this AD to do the 

inspection. 

Optional Terminating Action 

(j) As optional terminating action for the 

repetitive inspections required by this AD, 

replace propeller hub, P/N 660709201, with 

a new propeller hub, P/N 660717226. 

Alternative Methods of Compliance 

(AMOCs) 

(k) The Manager, Boston Certification 

Office, has the authority to approve AMOCs 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(l) For more information about this AD, 

contact Michael Schwetz, Aerospace 

Engineer, Boston Aircraft Certification Office, 

FAA, 12 New England Executive Park, 

Burlington, MA 01803; phone: 781–238– 

7761; fax: 781–238–7170; e-mail: 

michael.schwetz@faa.gov. 

(m) European Aviation Safety Agency 

2010–0196R1, dated November 12, 2010, 

pertains to the subject of this AD. 

Material Incorporated by Reference (IBR) 

(n) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(1) Dowty Propellers Alert SB No. 61–1119, 

Revision 5, dated July 1, 2009, approved for 

IBR as of October 11, 2011. 

(2) Dowty Propellers Alert SB No. 61– 

A1124, Revision 2, dated August 25, 2010, 

approved for IBR as of October 11, 2011. 

(3) Dowty Propellers Alert SB No. 61– 

A1125, Revision 2, dated August 25, 2010, 

approved for IBR as of October 11, 2011. 

(4) Dowty Propellers Alert SB No. 61– 

A1126, Revision 2, dated August 25, 2010, 

approved for IBR as of October 11, 2011. 

(5) For service information identified in 

this AD, contact Dowty Propellers, Anson 

Business Park, Cheltenham Road East, 

Gloucester GL 29QN, UK; phone: 44 (0) 1452 

716000; fax: 44 (0) 1452 716001. 

(6) You may review copies of the service 

information at the FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

(7) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

August 15, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22566 Filed 9–2–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Parts 738, 740, 745, and 748 

[Docket No. 110802457–1467–01] 

RIN 0694–AF18 

Export Administration Regulations: 

Netherlands Antilles, Curac ̧ao, Sint 

Maarten and Timor-Leste 

AGENCY: Bureau of Industry and 

Security, Commerce. 

ACTION: Final rule. 

SUMMARY: The Netherlands Antilles 

dissolved on October 10, 2010. This rule 

removes the Netherlands Antilles from 

all places where it is mentioned in the 

Export Administration Regulations 

(EAR), e.g., the Commerce Country 

Chart, the Country Groups, and License 

Exception APP. Curac ̧ao and Sint 

Maarten (the Dutch two-fifths of the 

island of Saint Martin) became semiautonomous entities within the 

Kingdom of the Netherlands. Therefore, 

Curac ̧ao and Sint Maarten are added to 

the Commerce Country Chart. 

The territories and dependencies of a 

country are treated as the parent country 

under the EAR. Bonaire, Saba, and Sint 

Eustatius now fall under the direct 

administration of the Netherlands. 

Therefore, these dependencies are 

treated like the Netherlands and will not 

be listed on the Commerce Country 

Chart. 

This rule also revises the name ‘‘East 

Timor’’ to read ‘‘Timor-Leste’’ 

throughout the EAR, because this is the 

proper name of the country. 

DATES: Effective Date: This rule is 

effective: September 6, 2011. 

FOR FURTHER INFORMATION CONTACT: For 

questions contact Sharron Cook, Office 

of Exporter Services, Bureau of Industry 

and Security, U.S. Department of 

Commerce at 202–482–2440 or by 

e-mail: Sharron.Cook@bis.doc.gov. 

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