Federal Register / Vol. 72, No. 48 / Tuesday, March 13, 2007 / Proposed Rules 11297 

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 39–12737 (67 FR 

22349, May 3, 2002), and by adding a 

new airworthiness directive (AD), to 

read as follows: 

Bell Helicopter Textron, Inc.: Docket No. 

FAA–2007–27496; Directorate Identifier 

2005–SW–37–AD. Supersedes AD 2002–

09–04, Amendment 39–12737, Docket 

No. 2001–SW–37–AD. 

Applicability 

Model 205A, 205A–1, 205B, 212, 412, 

412CF, and 412EP helicopters with a tail 

rotor blade (blade), part number 212–010–

750–009 through –129, all serial numbers 

except serial numbers with a prefix of ‘‘A’’

or ‘‘AFS’’ and the number 11926, 13351, 

13367, 13393, 13400, 13402, 13515, 13540, 

13568, 13595 through 13602, 13619, and 

subsequent assigned numbers, installed, 

certificated in any category. 

Compliance 

Within 100 hours time-in-service, unless 

accomplished previously. 

To prevent loss of the forward tip weight 

retention block (tip block) or aft tip closure 

(tip closure), loss of the blade, and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Inspect the tip block and tip closure for 

voids. Remove from service any blade with 

a void in excess of that allowed by the 

Component Repair and Overhaul Manual 

limitations. 

(b) Inspect the tip block attachment 

countersink screws in four locations to 

determine if the head of each countersunk 

screw is flush with the surface of the 

abrasion strip. The locations of these four 

screws are depicted on Figure 1 of Bell 

Helicopter Textron, Inc. Alert Service 

Bulletins 205–00–80, 205B–00–34, 212–00–

111, 412–00–106, and 412CF–00–13, all 

Revision D, all dated March 18, 2005 (ASB). 

If any of these screws are set below the 

surface of the abrasion strip or are covered 

with filler material, install shear pins by 

following the Accomplishment Instructions, 

Part A, Shear Pin Installation paragraphs, of 

the ASB appropriate for your model 

helicopter. 

(c) Install the aft tip closure rivets, reidentify the modified blade by adding an 

‘‘FM,’’ and dynamically balance the tail rotor 

hub assembly by following the 

Accomplishment Instructions, Part B, Aft Tip 

Closure Rivet Installation paragraphs, of the 

ASB appropriate for your model helicopter. 

(d) 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, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, ATTN: Michael Kohner, Aviation 

Safety Engineer, Fort Worth, Texas 76193–

0170, telephone (817) 222–5447, fax (817) 

222–5783, for information about previously 

approved alternative methods of compliance. 

Issued in Fort Worth, Texas, on February 

28, 2007. 

S. Frances Cox, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4525 Filed 3–12–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27495; Directorate 

Identifier 2005–SW–14–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model AS350B, BA, B1, B2, B3, 

C, D, and D1; EC–130B4; and AS355E, 

F, F1, F2, and N Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

adopting a new airworthiness directive 

(AD) for the specified Eurocopter France 

(ECF) model helicopters. This proposal 

would require, within the next 30 days, 

modifying the collective hold-down 

strap (strap) and thereafter inspecting it 

at specified intervals to ensure the 

rubber grommet is resting against the 

console or replacing the strap with an 

ECF designed strap that has a torsional 

spring at the lower end of the strap. This 

proposal is prompted by reports of two 

accidents occurring while the pilots 

were performing an autorotation. The 

pilots were unable to arrest the descent 

of the helicopter using collective blade 

pitch due to the collective stick locking 

in the down position when the 

collective was lowered during the 

maneuver. The actions specified by this 

proposed AD are intended to prevent 

inadvertent locking of a collective stick 

in flight and the flight crew not being 

aware of the locked condition leading to 

a subsequent loss of control of the 

helicopter. 

DATES: Comments must be received on 

or before May 14, 2007. 

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 examine the comments to 

this proposed AD in the AD docket on 

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

FOR FURTHER INFORMATION CONTACT: 

Vince Massey, Aerospace Engineer, 

FAA, Seattle Aircraft Certification 

Office, Systems and Equipment Branch, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056, telephone 

(425) 917–6475, fax (425) 917–6590. 

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–2007–27495, Directorate 

Identifier 2005–SW–14AD’’ 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. 


cprice-sewell on PROD1PC66 with PROPOSALS
11298 Federal Register / Vol. 72, No. 48 / Tuesday, March 13, 2007 / Proposed Rules 

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 

Seventh Street, SW., Washington, DC. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Discussion 

This document proposes adopting a 

new AD for the specified ECF model 

helicopters. This proposal would 

require, within the next 30 days, 

modifying the strap and thereafter 

inspecting it at specified intervals to 

ensure the rubber grommet is resting 

against the console or replacing the 

strap with an ECF strap designed with 

the torsional spring at the lower end of 

the strap. This proposal is prompted by 

reports of two accidents occurring while 

the pilots were performing an 

autorotation. The pilots were unable to 

arrest the descent of the helicopter using 

collective blade pitch due to the 

collective control locking in the down 

position when the collective was 

lowered during the maneuver. The 

positive locking feature and the 

structural integrity of the hold-down 

strap prevent the pilot from overriding 

the collective stick control lock by 

simply pulling up on the collective 

control stick. Before the collective stick 

can be raised, it must be held in a 

position where the button on the end of 

the collective stick is centered in the 

hole in the hold-down strap and then 

pushed forward to disengage the holddown strap from the button on the end 

of the collective stick. The actions 

specified by this proposed AD are 

intended to prevent inadvertent locking 

of a collective stick in flight and the 

flight crew not being aware of the 

locked condition leading to a 

subsequent loss of control of the 

helicopter. 

This unsafe condition is likely to exist 

or develop on other helicopters of these 

same type designs. Therefore, the 

proposed AD would require you to do 

the following within the next 30 days: 

• Modify the strap by forming the 

strap as depicted in Figure 1 of this AD. 

Install the modified strap so that the 

rubber grommet rests against the 

console. Thereafter, at intervals not to 

exceed 100 hours time-in-service, 

inspect the strap to ensure the rubber 

grommet is resting against the console. 

• An alternative approach for 

complying with this AD is to replace the 

affected strap with an ECF designed 

strap that has a torsional spring at the 

lower end of the strap. 

Replacing the strap with an ECF 

designed strap that has a torsional 

spring at the lower end of the strap 

would constitute terminating action for 

the requirements of this AD. 

We estimate that this proposed AD 

would affect 475 helicopters of U.S. 

registry. The proposed actions would 

take about 10 minutes to inspect a strap, 

20 minutes to modify it, and 30 minutes 

to replace a strap at an average labor rate 

of $80 per work hour. Required parts 

would cost about $194.70 per helicopter 

for the ECF strap designed with the 

torsional spring at the end of the strap. 

Based on these figures, we estimate the 

total cost impact of the AD on U.S. 

operators would be $111,483 if the ECF 

strap designed with the torsional spring 

at the end is installed in the entire fleet. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, this proposed AD 

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. 

For the reasons discussed above, I 

certify that the 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); 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 a draft economic 

evaluation of the estimated costs to 

comply with this proposed AD. See the 

DMS to examine the draft 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. 

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 

adding a new airworthiness directive to 

read as follows: 

Eurocopter France: Docket No. FAA–2007–

27495; Directorate Identifier 2005–SW–

14–AD. 

Applicability 

Model AS350B, BA, B1, B2, B3, C, D, and 

D1; EC–130B4; and AS355E, F, F1, F2, and 

N helicopters, with a collective hold-down 

strap (strap), part number (P/N) 

350A273107126, installed, certificated in any 

category. 

Compliance 

Required as indicated. 

To prevent inadvertent locking of a 

collective stick in the lowered position 

during flight and the flight crew not being 

aware of the locked condition leading to a 

subsequent loss of control of the helicopter, 

do the following: 

(a) Within the next 30 days, unless 

accomplished previously, modify the strap 

by forming the strap as depicted in Figure 1 

of this AD. Install the modified strap so that 

the rubber grommet rests against the console. 

Thereafter, at intervals not to exceed 100 

hours time-in-service, inspect the strap to 

ensure that the rubber grommet is resting 

against the console. 

Note: Vertical adjustment of the strap is 

described in the applicable Eurocopter 

France maintenance manual. 


cprice-sewell on PROD1PC66 with PROPOSALS
Federal Register / Vol. 72, No. 48 / Tuesday, March 13, 2007 / Proposed Rules 11299 

BILLING CODE 4910–13–C 


cprice-sewell on PROD1PC66 with PROPOSALSEP13MR07.030</GPH>
11300 Federal Register / Vol. 72, No. 48 / Tuesday, March 13, 2007 / Proposed Rules 

(b) An alternative approach for complying 

with paragraph (a) of this AD this AD is to 

replace the affected strap with an ECF 

designed strap kit, P/N 350A27–0350–

0071,that has a torsional spring at the lower 

end of the strap. The following Parts List 

constitutes the required parts of the ECF 

strap kit designed with the torsional spring 

at the lower end of the strap: 

Item Part No. Quantity 

(1) Leaf Assy 350A27–1426–03 1 

(2) Spring ..... 350A27–1423–21 1 

(3) Leaf Support.350A27–1421–20 1 

(4) Cotter Pin 23310CA015012 ... 1 

(5) Shear Pin 22719BC050068L 1 

(6) Screw ...... 22208CM050010 .. 2 

(7) Washer ... 23111AG050LE .... 3 

(8) Support ... 350A27–1377–01 1 

(c) Replacing the strap with an ECF 

designed strap kit as described in paragraph 

(b) of this AD constitutes terminating action 

for the requirements of this AD. 

(d) 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 Seattle Aircraft 

Certification Office, FAA, ATTN: Vince 

Massey, Aerospace Engineer, FAA, Systems 

and Equipment Branch, 1601 Lind Avenue 

SW., Renton, Washington 98057, telephone 

(425) 917–6475, fax (425) 917–6590, for 

information about previously approved 

alternative methods of compliance. 

Issued in Fort Worth, Texas, on February 

26, 2007. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 07–1167 Filed 3–12–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26284; Directorate 

Identifier 2006–CE–68–AD] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Regional Aircraft Jetstream 

Model 3201 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

The Airworthiness Limitations Section of 

the Aircraft Maintenance Manual (AMM) 

applicable to the British Aerospace Jetstream 

3200 has been revised. Some lives have been 

amended and new lives introduced. 

Compliance with these requirements is 

necessary to maintain airworthiness. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by April 12, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

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

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• 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. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 

proposed AD, the regulatory evaluation, 

any comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Taylor Martin, Aerospace Safety 

Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, 

Kansas City, Missouri 64106; telephone: 

(816) 329–4138; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This proposed AD references the 

MCAI and related service information 

that we considered in forming the 

engineering basis to correct the unsafe 

condition. The proposed AD contains 

text copied from the MCAI and for this 

reason might not follow our plain 

language principles. 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2006–26284; Directorate Identifier 

2006–CE–68–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because 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 we receive 

about this proposed AD. 

Discussion 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, has issued AD No. 

G–2004–0024, Issue Date: September 22, 

2004, European Aviation Safety Agency 

(EASA) approved on September 16, 

2004, under approval number 2004–

9648 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The Airworthiness Limitations Section of 

the Aircraft Maintenance Manual (AMM) 

applicable to the British Aerospace Jetstream 

3200 has been revised. Some lives have been 

amended and new lives introduced. 

Compliance with these requirements is 

necessary to maintain airworthiness. 

The MCAI requires: 

From the effective date of this 

Airworthiness Directive (AD), comply with 

the requirements of BAE Jetstream Series 

3200 Aircraft Maintenance Manual, Chapter 

05–10–05, Airworthiness Limitations 

Description and Operation Section,* 

Revision 14 or later EASA approved revision. 

* Only the structural fatigue tasks are 

mandated by this AD, the following tasks are 

not addressed by this AD: All the tasks 

recorded in Tables 2, 4, 5 and 8. Together 


cprice-sewell on PROD1PC66 with PROPOSALS