52912 Federal Register / Vol. 75, No. 167 / Monday, August 30, 2010 / Proposed Rules 

Actions Accomplished According to 

Previous Issues of Service Bulletin 

(k) For airplanes that have been inspected 

before the effective date of this AD in 

accordance with the service information 

specified in Table 1 of this AD: At the 

applicable times specified in Tables 22 

through 24 and Tables 26 through 29 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–53A2563, Revision 4, 

dated May 6, 2010, except as provided in 

paragraph (h) of this AD, do detailed 

inspections for scribe lines of affected lap 

splices, butt splices and cargo door lap 

splices; and do detailed and surface high 

frequency eddy current or ultrasonic 

inspections of scribe lines, and do all 

applicable related investigative and 

corrective actions, by accomplishing all the 

applicable actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2563, Revision 4, 

dated May 6, 2010, except as provided by 

paragraph (i) of this AD. 

TABLE 1—CREDIT SERVICE BULLETINS

Document Revision Date 

Boeing Alert Service Bulletin 747–53A2563 ................................................................................................................ Original March 29, 2007. 

Boeing Service Bulletin 747–53A2563 ......................................................................................................................... 2 January 3, 2008. 

Boeing Service Bulletin 747–53A2563 ......................................................................................................................... 3 June 11, 2009. 

Note 2: Boeing Alert Service Bulletin 747– 

53A2563, Revision 1, dated November 8, 

2007, was published with omitted 

information. Actions accomplished according 

to Boeing Alert Service Bulletin 747– 

53A2563, Revision 1, dated November 8, 

2007, are not considered acceptable for 

compliance with this AD. 

(l) Actions accomplished before the 

effective date of this AD according to the 

service information identified in Table 1 of 

this AD are considered acceptable for 

compliance with the corresponding actions 

specified in paragraph (g) of this AD, except 

as required by paragraph (k) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Nicholas Han, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6449; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authority (ODA) that has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Issued in Renton, Washington, on August 

13, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–21523 Filed 8–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0866; Directorate 

Identifier 2010–SW–065–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Model 427 Helicopters 

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) 

originated 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: 

Tail rotor driveshaft hanger bearing bracket 

part number (P/N) 427–044–223–101 has 

been found cracked due to fatigue. It has 

been determined that the fatigue cracking 

was initiated by a tooling mark left during 

manufacture. 

The existence of tooling marks on the 

bracket could lead to bracket failure, loss of 

tail rotor drive and, consequently, loss of 

control of the helicopter. 

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 October 14, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aerospace Engineer, 

FAA, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5122; fax: 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

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–2010–0866; Directorate Identifier 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 167 / Monday, August 30, 2010 / Proposed Rules 52913 

2010–SW–065–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:// 

www.regulations.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 

Transport Canada, which is the 

aviation authority for Canada, has 

issued AD No. CF–2010–17, dated June 

2, 2010 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Tail rotor driveshaft hanger bearing bracket 

part number (P/N) 427–044–223–101 has 

been found cracked due to fatigue. It has 

been determined that the fatigue cracking 

was initiated by a tooling mark left during 

manufacture. 

The existence of tooling marks on the 

bracket could lead to bracket failure, loss of 

tail rotor drive and, consequently, loss of 

control of the helicopter. 

The MCAI requires you to rework the 

tail rotor driveshaft hanger bearing 

bracket. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Bell Helicopter has issued Alert 

Service Bulletin No. 427–09–29, REV A, 

dated November 17, 2009. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 30 products of U.S. registry. 

We also estimate that it would take 

about 4 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $10,200, or $340 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would 

require parts costing $5,034, for a cost 

of $5,034 per product. We have no way 

of determining the number of products 

that may need these actions. 

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 determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. 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 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); 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 regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 adding 

the following new AD: 

Bell Helicopter Textron Canada Limited: 

Docket No. FAA–2010–0866; Directorate 

Identifier 2010–SW–065–AD. 

Comments Due Date 

(a) We must receive comments by October 

14, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model 427 

helicopters, all serial numbers (SNs), 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 65: Tail Rotor Drive. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Tail rotor driveshaft hanger bearing bracket 

part number (P/N) 427–044–223–101 has 

been found cracked due to fatigue. It has 

been determined that the fatigue cracking 

was initiated by a tooling mark left during 

manufacture. 

The existence of tooling marks on the 

bracket could lead to bracket failure, loss of 

tail rotor drive and, consequently, loss of 

control of the helicopter. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
52914 Federal Register / Vol. 75, No. 167 / Monday, August 30, 2010 / Proposed Rules 

The MCAI requires you to rework the tail 

rotor driveshaft hanger bearing bracket. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Applicable to SNs 56001 through 

56073, and 56077: Within 30 days after the 

effective date of this AD, inspect both sides 

of the hanger bracket, P/N 427–044–223–101, 

for cracks following Bell Helicopter Alert 

Service Bulletin No. 427–09–29, REV A, 

dated November 17, 2009. 

(i) If no cracks are found during the 

inspection required by paragraph (f)(1) of this 

AD, before further flight rework both sides of 

the hanger bracket, P/N 427–044–223–101, 

following Bell Helicopter Alert Service 

Bulletin No. 427–09–29, REV A, dated 

November 17, 2009. 

(ii) If cracks are found during the 

inspection required by paragraph (f)(1) of this 

AD, before further flight replace the hanger 

bracket, P/N 427–044–223–101, with a new 

hanger bracket, P/N 427–044–223–101, that 

has been reworked following Bell Helicopter 

Alert Service Bulletin No. 427–09–29, REV 

A, dated November 17, 2009. 

(2) Applicable to all SNs: As of the 

effective date of this AD, you may not install 

replacement tail rotor driveshaft hanger 

bracket, P/N 427–044–223–101, unless the 

bracket has been inspected and found free of 

cracks and has been reworked following Bell 

Helicopter Alert Service Bulletin No. 427– 

09–29, REV A, dated November 17, 2009. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Sharon Miles, Aerospace Engineer, 

FAA, Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone: 

(817) 222–5122; fax: (817) 222–5961. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Transport Canada AD 

No. CF–2010–17, dated June 2, 2010; and 

Bell Helicopter Alert Service Bulletin No. 

427–09–29, REV A, dated November 17, 

2009, for related information. 

Issued in Fort Worth, Texas, on August 19, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–21582 Filed 8–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0865; Directorate 

Identifier 2010–SW–061–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Models 206A, 206B, 206L, 206L–1, 

206L–3, and 206L–4 Helicopters 

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) 

originated 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: 

It has been determined that new tail rotor 

disc assembly Part Number (P/N) 101584–1 

or –2, sold through Bell Helicopter Spares 

beginning March 2009, as an alternate to 

P/N 32721–1, does not conform to the 

approved configuration. Operating a 

helicopter with disk assembly P/N 101584– 

1 or –2 installed may result in loss of control 

of the helicopter. 

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 October 14, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aerospace Engineer, 

FAA, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5122; fax: 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

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–2010–0865; Directorate Identifier 

2010–SW–061–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:// 

www.regulations.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 

Transport Canada, which is the 

aviation authority for Canada, has 

issued AD No. CF–2010–07, dated 

February 24, 2010 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

It has been determined that new tail rotor 

disc assembly Part Number (P/N) 101584–1 

or –2, sold through Bell Helicopter Spares 


jlentini on DSKJ8SOYB1PROD with PROPOSALS