60246 Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Proposed Rules 

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: 

Eurocopter France: Docket No. FAA–2005–

22696; Directorate Identifier 2004–SW–

46–AD. 

Applicability: Model EC 155B and B1 

helicopters, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent interference of the wiring with 

the structure resulting in an electrical short 

circuit, failure of the landing gear to extend, 

and an emergency landing, accomplish the 

following: 

(a) Within 50 hours time-in-service (TIS), 

(1) Inspect the wiring of panel 12 Alpha 

(wiring) electrical cable bundle for wear. If 

wear is present, replace the worn cable 

bundle with an airworthy cable bundle by 

following the Accomplishment Instructions, 

paragraphs 2.A.1, 2.B.1, and 2.B.2 of 

Eurocopter Alert Service Bulletin EC155, 

Revision 1, dated May 14, 2004 (ASB). 

Note 1: Aircraft Maintenance Manual 

(AMM): Tasks 24.00.00.911 and 32–30–00–

721 and Standard Practices Manual (MTC) 

Work Cards 20.02.01.415, 20.06.01.310, 

20.06.01.406, and 20.02.06.409 pertain to the 

subject of this AD. 

(2) Modify the routing of the electrical 

wiring (MOD 0739C28) and replace spreaders 

and spacers by following the 

Accomplishment Instructions, paragraph 

2.B.3. through 2.B.9. of the ASB. 

(b) 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, 

FAA, for information about previously 

approved alternative methods of compliance. 

(c) Special flight permits will not be 

issued. 

Note 2: The subject of this AD is addressed 

in Direction Generale de l’Aviation Civile 

(France) AD F–2004–057 R1, dated July 21, 

2004. 

Issued in Fort Worth, Texas, on October 7, 

2005. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 05–20679 Filed 10–14–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22696; Directorate 

Identifier 2005–SW–22–AD] 

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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

superseding an existing airworthiness 

directive (AD) for the specified Bell 

Helicopter Textron Canada (BHTC) 

model helicopters. That AD currently 

requires an initial inspection and at 

specified intervals checks and 

inspections 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 would contain the 

same actions as the existing AD and 

would also propose adding certain 

serial-numbered blades to the 

applicability that were inadvertently 

omitted from the current AD and would 

require replacing each affected blade, 

which would be terminating action. 

This proposal is prompted by three 

reports of skin cracks originating near 

the blade trailing edge balance weight. 

The actions specified by the proposed 

AD are intended to prevent blade failure 

and subsequent loss of control of the 

helicopter. 

DATES: Comments must be received on 

or before December 16, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically; 

• Government-Wide Rulemaking Web 

Site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically; 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590; 

• Fax: 202–493–2251; or 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

• You may get the service information 

identified in this proposed 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 

• You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http://dms.dot.gov. 

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: 

Comments Invited 

We invite you to submit any written 

data, views, or arguments regarding this 

proposed AD. Send your comments to 

the address listed under the caption 

ADDRESSES. Include the docket number 

‘‘FAA–2005–22696, Directorate 

Identifier 2005–SW–22–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed 

rulemaking. 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 or signed 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), or you may visit 

http://dms.dot.gov. The postcard will be 

date stamped and returned to the 

commenter. 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information in 

person at the Docket Management 

System (DMS) Docket Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Office (telephone 1–800–647–

5227) is located at the plaza level of the 

Department of Transportation NASSIF 

Building in Room PL–401 at 400 

Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Proposed Rules 60247 

Seventh Street, SW., Washington, DC. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Discussion 

On November 22, 2004, the FAA 

issued AD 2004–24–08, Docket No. 

2004–SW–12–AD, Amendment 39–

13884 (69 FR 69810, December 1, 2004). 

That AD requires an initial inspection 

and at intervals not to exceed 12 hours 

time-in-service (TIS), a 10X inspection 

or at intervals not to exceed 24 hours 

TIS a 10X inspection and a 3-hour TIS 

check between each 24 hour TIS 

inspection of the blade for a 

deformation, a crack, and a bent or 

deformed 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. That action 

was prompted by three reports of skin 

cracks originating near the blade trailing 

edge balance weight. The requirements 

of that AD are intended to prevent blade 

failure and subsequent loss of control of 

the helicopter. 

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. 

When we issued AD 2004–24–08, we 

intentionally did not include the longterm 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 in this proposal a long-term 

requirement that the affected blades be 

replaced on or before April 27, 2007, as 

terminating action. This will allow 

public comments before any adoption of 

the long-term proposal. Additionally, in 

AD 2004–24–08, we inadvertently 

omitted blade serial numbers 10102 

through 10114 from the applicability. 

We propose to correct that oversight 

with this action. 

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 were afforded an 

opportunity to participate in the making 

of AD 2004–24–08, Amendment 39–

13884, Docket No. 2004–SW–12–AD, 

which we are proposing to supersede. 

Due consideration has been given to the 

one comment received. 

The commenter expresses concern 

about the 12-hour blade inspection by a 

mechanic and states the inspection will 

make this helicopter unsuitable for its 

intended use. The commenter states the 

alternate pilot check and mechanic 

inspection would require them to shut 

down 4–5 times each day increasing 

engine cycles. The commenter further 

states that since the only difference 

between the pilot check and the 

mechanic inspection is the 10X 

magnifier, pilots need to be certified to 

perform the 12-hour inspection. 

While the FAA agrees the checks and 

inspections could increase engine 

cycles, the primary purpose of issuing 

an AD is to correct an unsafe condition. 

However, the terminating action 

proposed in this AD would eliminate 

the current mandated inspections. We 

do not agree that pilots need to be 

certified to perform inspections. Current 

FAA policy allows pilots holding at 

least a private pilot certificate to 

perform checks that do not require the 

use of tools, precision measuring 

equipment, training, pilot logbook 

endorsements, or reference to technical 

data not contained in the body of the 

AD. Pilots may only perform simple 

maintenance tasks that do not require 

special maintenance training. The 

inspection in the AD requires the use of 

a 10X or higher magnifying glass, which 

is not considered a simple visual check. 

In the interest of safety, the inspection 

must occur at the specified intervals and 

be performed by a qualified mechanic 

until the terminating action is 

accomplished. 

The previously described unsafe 

condition is likely to exist or develop on 

other helicopters of these same type 

designs. Therefore, the proposed AD 

would supersede AD 2004–24–08 to 

require: 

• Before further flight, unless 

accomplished previously, and before 

installing any blade with an affected 

part number and serial number (S/N), 

cleaning the blade. Then, using a 10X or 

higher magnifying glass, inspecting both 

sides of each blade for a deformation, a 

crack, and a bent or deformed weight. 

• Thereafter, cleaning both sides of 

each blade and using a 10X or higher 

magnifying glass, inspecting for a 

deformation, a crack, and a bent or 

deformed weight as follows: 

• At intervals not to exceed 12 hours 

TIS, or 

• At intervals not to exceed 24 hours 

TIS and checking both sides of each 

blade for a deformation, a crack, and a 

bent or deformed weight at intervals not 

to exceed 3 hours TIS between 

inspections. An owner/operator (pilot) 

holding at least a private pilot certificate 

may perform the 3-hour TIS check for 

deformed or cracked blades and for bent 

or deformed weights. Pilots may 

perform these checks because they 

require no tools, can be done by 

observation, and can be done equally 

well by a pilot or a mechanic. However, 

the pilot must enter compliance with 

these requirements into the helicopter 

maintenance records by following 14 

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

• Before further flight, replacing each 

blade with an airworthy blade if you 

find a deformation, a crack, or a bent or 

deformed weight. 

• On or before April 27, 2007, 

replacing each affected blade with an 

airworthy blade that is identified by a 

‘‘V’’ at the end of the blade S/N or an 

airworthy blade with a S/N other than 

one listed in the applicability section of 

this AD. 

Replacing each blade with an 

airworthy blade that is identified by a 

‘‘V’’ at the end of the blade S/N or an 

airworthy blade with a S/N other than 

one listed in the applicability section of 

this AD constitutes terminating action 

for the requirements of this AD. 

The FAA estimates that this proposed 

AD would: 

• Affect 2194 helicopters of U.S. 

registry, 

• Take about 1⁄4 work hour for a blade 

check or inspection, and 

60248 Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Proposed Rules 

• Take 3 work hours to replace a 

blade at an average labor rate of $65 per 

work hour. Required parts would 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 proposed 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 

The regulations proposed herein 

would 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. Therefore, 

it is determined that this proposal 

would not have federalism implications 

under Executive Order 13132. 

For the reasons discussed above, I 

certify that this proposed 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); on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. A copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES. 

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. 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend 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), to read as follows: 

Bell Helicopter Textron Canada: Docket No. 

FAA–2005, 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 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 

Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Proposed Rules 60249 

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 P/N 206–016–201–131, S/N with prefix ‘‘CS’’

and no ‘‘V’’ suffix 

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 

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 

60250 Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Proposed Rules 

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. 

(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, for information 

about previously approved alternative 

methods of compliance. 

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 October 7, 

2005. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 05–20681 Filed 10–14–05; 8:45 am] 

BILLING CODE 4910–13–P 


EP17OC05.002</GPH>