Federal Register / Vol. 72, No. 5 / Tuesday, January 9, 2007 / Rules and Regulations 889 

announcing the general course of action 

that the Commission intends to follow. 

This policy statement does not 

constitute an agency regulation 

requiring notice of proposed 

rulemaking, opportunities for public 

participation, prior publication, and 

delay in effective date under 5 U.S.C. 

553 of the Administrative Procedure Act 

(‘‘APA’’). As such, it does not bind the 

Commission or any member of the 

general public. The provisions of the 

Regulatory Flexibility Act, which apply 

when notice and comment are required 

by the APA or another statute, are not 

applicable. 

Dated: December 27, 2006. 

Robert D. Lenhard, 

Vice Chairman, Federal Election Commission. 

[FR Doc. E7–65 Filed 1–8–07; 8:45 am] 

BILLING CODE 6715–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22696; Directorate 

Identifier 2005–SW–22–AD; Amendment 39–

14877; AD 2007–01–06] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Model 

206A, B, L, L–1, L–3, and L–4 

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) model helicopters. The 

existing AD currently requires certain 

inspections and checks of the tail rotor 

blade (blade) for a deformation, a crack, 

and a bent or deformed tail rotor weight 

(weight). Also, that AD requires, before 

further flight, replacing each blade with 

an airworthy blade if a deformation, a 

crack, or a bent or deformed weight is 

found. This action contains the same 

actions as the existing AD and also adds 

to the applicability certain serialnumbered blades inadvertently omitted 

from the current AD. This action also 

requires replacing each affected blade, 

which is a terminating action. This 

amendment is prompted by three 

reports of skin cracks originating near 

the blade trailing edge balance weight. 

The actions specified by this AD are 

intended to prevent blade failure and 

subsequent loss of control of the 

helicopter. 

DATES: Effective February 13, 2007. 

ADDRESSES: You may get the service 

information identified in this AD from 

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. 

Examining the Docket 

You may examine the docket that 

contains this AD, any comments, and 

other information on the Internet at 

http://dms.dot.gov, or at the Docket 

Management System (DMS), U.S. 

Department of Transportation, 400 

Seventh Street, SW., Room PL–401, on 

the plaza level of the Nassif Building, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Guidance Group, Fort Worth, Texas 

76193–0111, telephone (817) 222–5122, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 by 

superseding AD 2004–24–08, 

Amendment 39–13884 (69 FR 69810, 

December 1, 2004), for the specified 

BHTC model helicopters was published 

in the Federal Register on October 17, 

2005 (70 FR 60246). This action 

contains the same actions as the existing 

AD. Also, when we issued AD 2004–24–

08, we intentionally did not include the 

long-term requirement (no later than 

April 27, 2007) for removing and 

sending the affected blades to Rotor 

Blades, Inc. as specified by the 

manufacturer. We are including a longterm requirement in this AD that the 

affected blades be replaced on or before 

April 27, 2007, as terminating action. 

Additionally, in AD 2004–24–08, we 

inadvertently omitted blade serial 

numbers 10102 through 10114 from the 

applicability. We are correcting that 

oversight with this action. 

Since issuing AD 2004–24–08, BHTC 

has issued Alert Service Bulletin 206–

04–100 for Bell Model 206A and B 

helicopters, and 206L–04–127 for Bell 

Model 206L series helicopters, both 

Revision C, both dated March 5, 2005 

(ASB). These ASBs add two warnings in 

the compliance section specifying 

returning the blade for balancing to 

Rotor Blades, Inc., and introduce new 

skin damage limits that supersede the 

previous damage limits. The ASB also 

gives a new address for Rotor Blades 

Inc. 

Transport Canada, the airworthiness 

authority for Canada, notified the FAA 

that an unsafe condition may exist on 

these helicopter models. Transport 

Canada advises of three reports of skin 

cracks originating near the blade trailing 

edge balance weight. Two of the 

occurrences caused a loss of the weight 

and a strip of material along the trailing 

edge leading to an imbalance, which 

caused the fracture of three of the four 

tail rotor gearbox attachments. One of 

these occurrences resulted in the 

gearbox shifting that caused failure of 

the drive shaft and resulting loss of yaw 

control. Transport Canada issued AD 

No. CF–2004–05R1, dated June 28, 

2004, to ensure the continued 

airworthiness of these helicopters in 

Canada. 

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 

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, except for a 

change in paragraph (f) of the AD to add 

additional contact information. This 

change will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

The FAA estimates that this AD will: 

• Affect 2194 helicopters of U.S. 

registry, 

• Take about 1⁄4 work hour for a blade 

check or inspection, and 

• Take 3 work hours to replace a 

blade at an average labor rate of $65 per 

work hour. 

• Cost about $5848 per helicopter. (In 

its ASB, the manufacturer states it will 

give warranty credit based on hour 

usage on the blade with remaining life 

hours and other restrictions.) 

Based on these figures, we estimate 

the total cost impact of the AD on U.S. 

operators to be $19,989,973. Costs 

assume—200 pilot checks, 26 mechanic 

inspections, and one blade replacement 

for 90 percent of the fleet with a 

nonconforming blade. 

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 

bajohnson on PROD1PC69 with RULES

890 Federal Register / Vol. 72, No. 5 / Tuesday, January 9, 2007 / Rules and Regulations 

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 DMS 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 39–13884 (69 FR 

69810, December 1, 2004) and by adding 

a new airworthiness directive (AD), 

Amendment 39–14877, to read as 

follows: 

2007–01–06 Bell Helicopter Textron Canada: 

Amendment 39–14877. Docket No. 

FAA–2005–22696; Directorate Identifier 

2005–SW–22–AD. Supersedes AD 2004–

24–08, Amendment 39–13884, Docket 

No. 2004–SW–12–AD. 

Applicability 

Model 206A, B, L, L–1, L–3, and L–4 

helicopters, with a tail rotor blade (blade) 

with the following part number (P/N) and 

serial number (S/N) installed, certificated in 

any category. 

Model 206A & B; Blade, P/N 206–016–201–

133, S/N with prefix ‘‘CS’’ and no ‘‘V’’ suffix 

Model 206A, B, L, L–1, L–3, & L–4; Blade, P/N 206–016–201–131, S/N with prefix ‘‘CS’’ and no 

‘‘V’’ suffix 

1381 through 1442 7000 through 7018 10174 through 10218 

1492 through 1517 7020 through 7043 10220 

1520 through 1542 7045 through 7050 10232 

1550 7052 through 7132 10235 

1556 7134 through 7246 10237 through 10241 

1560 7248 through 7270 10244 

1562 7272 through 7277 10245 

1564 through 1567 7279 through 7339 10248 

1569 through 1606 7342 through 7368 10250 through 10264 

1609 7784 10266 through 10268 

1611 7786 10270 through 10274 

1612 7788 10276 through 10278 

1614 through 1631 7790 through 7796 10280 through 10282 

1633 through 1675 7798 through 7819 10284 through 10292 

1677 7821 through 7833 10296 

1678 7835 through 7839 10300 through 10330 

1680 through 1682 7841 through 8001 10332 

1684 through 1787 8003 through 8026 10333 

1789 through 1803 8029 through 8061 10335 through 10347 

1810 through 1812 8064 through 8117 10349 

1814 8119 10351 through 10359 

1816 8121 through 8139 10363 through 10365 

1820 8142 through 8176 10367 

1823 through 1831 8178 through 8262 10373 

1834 through 1836 8264 through 8294 10374 

1838 8298 through 8368 10377 through 10385 

1840 through 1844 8370 through 8375 10387 through 10408 

1846 8378 through 8416 10410 

1848 through 1882 8419 10414 through 10417 

1884 through 1887 8421 10419 through 10427 

1889 through 1893 8425 through 8428 10430 

1896 through 1898 8430 through 8438 10432 

1900 8440 10437 

1904 8441 10438 

1909 through 1912 8443 10442 through 10445 

1915 8445 through 8447 10458 through 10466 

1916 8449 through 8606 10469 

1919 through 1921 8608 through 8622 10470 

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Federal Register / Vol. 72, No. 5 / Tuesday, January 9, 2007 / Rules and Regulations 891 

1924 8624 through 8626 10474 

1928 through 1931 8628 through 8632 10476 through 10478 

1933 8635 through 8653 10480 through 10487 

1934 through 1939 8655 through 8686 10489 through 10491 

1943 8690 10493 through 10495 

1945 8692 through 8700 10497 through 10503 

1947 8703 through 8715 10505 through 10588 

1948 8717 through 8722 10591 through 10606 

1952 through 1957 8724 through 8742 10608 through 10610 

1960 8745 through 8828 10612 through 10620 

1962 through 1965 8830 through 8835 10623 

8838 through 8840 10624 

8842 through 8881 10631 through 10655 

8883 through 9032 10657 through 10669 

9034 through 9139 10672 

9141 through 9198 10673 

9200 10676 through 10678 

9202 through 9302 10680 through 10683 

9304 through 9339 10685 

9341 through 9371 10687 

9373 through 9411 10689 through 10702 

9413 10707 

9415 through 9417 10712 

9419 through 9496 10715 

9498 through 9585 10730 

9587 through 9594 10732 through 10734 

9596 through 9618 10736 

9621 through 9629 10738 

9632 through 9642 10739 

9645 through 9651 10746 

9653 through 9673 10750 

9675 through 9707 10756 

9709 through 9724 10760 

9727 through 9731 10761 

9733 through 9735 10765 

9737 through 9739 10770 

9741 through 9748 10774 through 10776 

9751 through 9785 10778 

9787 10781 

9788 10783 through 10785 

9790 through 9792 10792 

9795 through 9847 10794 

9849 through 9928 10798 

9930 through 9937 10799 

9940 through 9942 10806 through 10808 

9944 through 9952 10811 

9955 through 9972 10814 through 10822 

9974 through 9989 10824 

9991 through 9995 10825 

9997 through 10004 10829 

10006 through 10009 10831 

10011 10917 

10013 through 10018 10923 

10021 through 10030 10931 

10034 10936 

10036 through 10057 10937 

10061 through 10082 10940 

10090 through 10092 10943 

10094 through 10100 10945 

10102 through 10114 10947 

10116 10948 

10119 10964 

10121 10965 

10123 through 10134 10973 

10136 through 10140 10982 

10142 through 10144 10985 

10146 through 10172 10986 

Compliance 

Required as indicated. 

To prevent blade failure and subsequent 

loss of control of the helicopter, do the 

following: 

(a) Before further flight, unless 

accomplished previously, and before 

installing any blade with a P/N and S/N 

listed in the applicability section of this AD, 

clean the blade. Using a 10X or higher 

magnifying glass, inspect both sides of each 

blade for a deformation, a crack, and a bent 

or deformed weight in the area shown in 

Figure 1 of this AD. 

Note 1: Paint irregularities on the blade 

may indicate a crack. 

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892 Federal Register / Vol. 72, No. 5 / Tuesday, January 9, 2007 / Rules and Regulations 

(b) After doing paragraph (a) of this AD, at 

the following intervals, clean both sides of 

each blade and do either paragraph (1) or (2) 

as follows: 

(1) At intervals not to exceed 12 hours 

time-in-service (TIS), using a 10X or higher 

magnifying glass, inspect both sides of each 

blade for a deformation, a crack, and a bent 

or deformed weight in the area shown in 

Figure 1 of this AD, or 

(2) Inspect and check both sides of each 

blade for a deformation, a crack, and a bent 

or deformed weight in the area shown in 

Figure 1 of this AD as follows: 

(i) Using a 10X or higher magnifying glass, 

inspect at intervals not to exceed 24 hours 

TIS, and 

(ii) Check at intervals not to exceed 3 hours 

TIS between the inspections required by 

paragraph (b)(2)(i) 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 sections 43.11 

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

(c) Before further flight, replace any blade 

that has a deformation, a crack, or a bent or 

deformed weight with an airworthy blade. 

Note 2: Bell Helicopter Textron Alert 

Service Bulletin No. 206–04–100 for Model 

206A and B and No. 206L–04–127 for Model 

206L series, both Revision C, both dated 

March 5, 2005, pertain to the subject of this 

AD. 

(d) On or before April 27, 2007, for any 

affected part-numbered blade with a S/N 

listed in the applicability section of this AD: 

(1) Replace the blade with a blade that has 

a S/N other than one listed in the 

applicability section of this AD, or 

(2) Replace the blade with a blade that has 

a S/N listed in the applicability section of 

this AD and also has a ‘‘V’’ suffix. 

(e) Replacing each blade with an airworthy 

blade as required by paragraph (d) of this AD 

constitutes terminating action for the 

requirements of this AD. 

(f) 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 Safety Management Group, 

Rotorcraft Directorate, FAA, ATTN: Sharon 

Miles, Aviation Safety Engineer, Regulations 

and Guidance Group, Fort Worth, Texas 

76193–0111, telephone (817) 222–5122, fax 

(817) 222–5961, for information about 

previously approved alternative methods of 

compliance. 

(g) This amendment becomes effective on 

February 13, 2007. 

Note 3: The subject of this AD is addressed 

in Transport Canada (Canada) AD No. CF–

2004–05R1, dated June 28, 2004. 

Issued in Fort Worth, Texas, on December 

26, 2006. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–39 Filed 1–8–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[FAA–2006–26518; Directorate Identifier 

2006–CE–84–AD; Amendment 39–14874; AD 

2007–01–03] 

RIN 2120–AA64 

Airworthiness Directives; Stemme 

GmbH & Co. KG Model S10–VT Gliders 

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) 

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ER09JA07.003