59170 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Proposed Rules 

specified in paragraphs (h)(1) and (h)(2) of 

this AD, as applicable. 

(1) For Model 737–600, -700, and -800 

series airplanes identified in Boeing Service 

Bulletin 737–78–1063, Revision 2, dated 

October 7, 1999: Replace the inner wall 

blanket insulation, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–78–1063, Revision 2, 

dated October 7, 1999. 

(2) For airplanes equipped with engines 

identified in CFM CFM56–7B Service 

Bulletin 73–0135, dated March 30, 2007: 

Install updated full-authority digital 

electronic control (FADEC) software, in 

accordance with the Accomplishment 

Instructions of CFM CFM56–7B Service 

Bulletin 73–0135, dated March 30, 2007. 

Inspection/Measurement 

(i) At the applicable time specified in 

paragraph (j) of this AD: Do the actions 

specified in paragraphs (i)(1), (i)(2), and (i)(3) 

of this AD, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–78–1088, dated May 12, 

2010. If any damage or discrepancy is found, 

before further flight, do all applicable 

corrective actions, in accordance with 

Accomplishment Instructions of Boeing 

Service Bulletin 737–78–1088, dated May 12, 

2010; except as required by paragraph (k) of 

this AD; and except where the service 

bulletin refers to ‘‘unsatisfactory’’ findings, 

this AD assumes those parts or locations are 

‘‘unserviceable.’’ 

(1) Do a detailed inspection for damage of 

the engine side and inner wall side of the 

upper and lower insulation blankets. 

(2) Measure the electrical conductivity on 

the aluminum upper compression pads 2 and 

3, as applicable. 

(3) Inspect for discrepancies of the thrust 

reverser inner wall (including an ultrasonic 

inspection for interplay delamination and 

skin-to-core disbond, a detailed inspection 

for signs of heat damage as applicable, and 

a detailed inspection for loose fasteners 

where the inner wall attaches to the hinge 

beam and at the fasteners for the compression 

pads). 

Compliance Times for Paragraph (i) 

(j) Do the actions specified in paragraph (i) 

of this AD at the applicable time specified in 

paragraph (j)(1), (j)(2), (j)(3), (j)(4), or (j)(5) of 

this AD. 

(1) For airplanes with thrust reverser part 

number (P/N) 315A2295–003 through 

315A2295–154 inclusive: Do the actions 

within 30 months after the effective date of 

this AD. 

(2) For airplanes with thrust reverser P/N 

315A2295–155 through 315A2295–174 

inclusive: Do the actions within 60 months 

after the effective date of this AD. 

(3) For airplanes with thrust reverser P/N 

315A2295–175 through 315A2295–190 

inclusive: Do the actions within 72 months 

after the effective date of this AD. 

(4) For airplanes with thrust reverser P/N 

315A2295–191 through 315A2295–198 

inclusive: Do the actions within 84 months 

after the effective date of this AD. 

(5) For airplanes with thrust reverser P/N 

315A2295–199 through 315A2295–202 

inclusive: Do the actions within 96 months 

after the effective date of this AD. 

Exception to Boeing Service Bulletin 737–78– 

1088 Procedures 

(k) Where Boeing Service Bulletin 737–78– 

1088, dated May 12, 2010, specifies to 

contact Boeing for appropriate action, repair 

before further flight in accordance with a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA. 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. 

Actions Concurrent With Paragraph (i) 

(l) For airplanes identified in Boeing 

Service Bulletin 737–78–1069, Revision 4, 

dated June 16, 2005: Before or concurrently 

with the accomplishment of the requirements 

of paragraph (i) of this AD, modify the thrust 

reverser inner wall and insulation blankets, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

78–1069, Revision 4, dated June 16, 2005. A 

modification done before the effective date of 

this AD is also acceptable if done in 

accordance with Boeing Service Bulletin 

737–78–1069, Revision 1, dated June 13, 

2002; Revision 2, dated February 6, 2003; or 

Revision 3, dated August 5, 2004. 

(m) If the actions required by paragraph (i) 

of this AD are done before the compliance 

time specified in paragraph (g) of this AD: 

Before or concurrently with the 

accomplishment of the actions required by 

paragraph (i) of this AD, the modification 

required by paragraph (g) of this AD must be 

done. 

Option to Requirements of Paragraphs (g) 

and (i) 

(n) Accomplishment of all of the actions 

(including inspections and modification) 

specified in Boeing Service Bulletin 737–78– 

1079, Revision 2, dated June 7, 2010, within 

24 months after the effective date of this AD, 

is acceptable for compliance with the 

requirements of paragraphs (g) and (i) of this 

AD and is acceptable for compliance with the 

requirements of this AD, provided applicable 

repairs are done before further flight, and 

provided the applicable actions specified in 

paragraphs (h)(1), (h)(2), and (l) of this AD 

have been done. Actions done before the 

effective date of this AD in accordance with 

Boeing Service Bulletin 737–78–1079, dated 

August 6, 2007; or Revision 1, dated 

December 17, 2007; are also acceptable for 

compliance with the corresponding actions 

specified in this paragraph. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: Chris 

Parker, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone 425–917–6496; fax 425–917– 

6590. Information may be e-mailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@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 refer to this AD. 

Issued in Renton, Washington on 

September 15, 2010. 

Robert D. Breneman, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–24175 Filed 9–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0942; Directorate 

Identifier 2010–CE–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Regional Aircraft Models 

Jetstream Series 3101 and 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) 

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: 

As a result of the fatigue-testing 

programme on the Jetstream fatigue test 

specimen, it has been identified that failure 

of the undercarriage jack mounting shaft 

assembly can occur. 

This condition, if not corrected, could lead 

to a Main Landing Gear (MLG) collapse on 

the ground or during landing and 

consequently damage to the aeroplane or 

injury to the occupants. 

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 November 12, 

2010. 

ADDRESSES: You may send comments by 

any of the following methods: 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Proposed Rules 59171 

• 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: 

Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4138; fax: (816) 329–4090; e-mail: 

taylor.martin@faa.gov. 

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–2010–0942; Directorate Identifier 

2010–CE–049–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2010– 

0162, dated August 4, 2010 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

As a result of the fatigue-testing 

programme on the Jetstream fatigue test 

specimen, it has been identified that failure 

of the undercarriage jack mounting shaft 

assembly can occur. 

This condition, if not corrected, could lead 

to a Main Landing Gear (MLG) collapse on 

the ground or during landing and 

consequently damage to the aeroplane or 

injury to the occupants. 

BAE SYSTEMS have now defined safe life 

limits for these components. 

For the reasons described above, this AD 

requires the application of safe life limits to 

these components. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

BAE Systems has issued British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 05–JA090143, dated 

April 30, 2009; and British Aerospace 

Regional Aircraft has issued British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–JA990142, dated 

March 26,1999. 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 80 products of U.S. registry. 

We also estimate that it would take 

about 15 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $10,000 per 

product. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $902,000, or $11,275 per 

product. 

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 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
59172 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Proposed Rules 

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: 

British Aerospace Regional Aircraft: Docket 

No. FAA–2010–0942; Directorate 

Identifier 2010–CE–049–AD. 

Comments Due Date 

(a) We must receive comments by 

November 12, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to British Aerospace 

Regional Aircraft Models Jetstream Series 

3101 and Jetstream Model 3201 airplanes, all 

serial numbers, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

As a result of the fatigue-testing 

programme on the Jetstream fatigue test 

specimen, it has been identified that failure 

of the undercarriage jack mounting shaft 

assembly can occur. 

This condition, if not corrected, could lead 

to a Main Landing Gear (MLG) collapse on 

the ground or during landing and 

consequently damage to the aeroplane or 

injury to the occupants. 

BAE SYSTEMS have now defined safe life 

limits for these components. 

For the reasons described above, this AD 

requires the application of safe life limits to 

these components. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 30 days after the effective date 

of this AD, establish the number of landings 

accumulated since installation of each left 

and right main landing gear radius rod 

mounting shaft assemblies following 

paragraph 2.(A) of BAE Systems British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 05–JA090143, dated April 

30, 2009. 

(2) Replace the left and right main landing 

gear radius rod mounting shaft assembly with 

an airworthy assembly following British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–JA990142, dated March 

26, 1999, within the following: 

(i) For Model Jetstream Series 3101: Within 

38,220 total landings accumulated on each 

main landing gear radius rod mounting shaft 

assembly or within 1,000 landings after the 

effective date of this AD, whichever occurs 

later; and 

(ii) For Model Jetstream Model 3201: 

Within 31,038 total landings accumulated on 

each main landing gear radius rod mounting 

shaft assembly or within 1,000 landings after 

the effective date of this AD, whichever 

occurs later. 

(3) After replacing each main landing gear 

radius rod mounting shaft assembly as 

required by paragraph (f)(2) of this AD, 

repetitively thereafter replace each assembly 

with an airworthy assembly at intervals not 

to exceed the following life limits: 

(i) For Model Jetstream Series 3101: Within 

38,220 total landings; and 

(ii) For Model Jetstream Model 3201: 

Within 31,038 total landings. 

(4) For operators that do not have landing 

records, determine the number of landings by 

multiplying the number of hours time-inservice (TIS) accumulated on each main 

landing gear radius rod mounting shaft 

assembly by 0.75. For the purpose of this AD: 

(i) 1,000 landings equals 1,333 hours TIS; 

(ii) 31,038 landings equals 41,384 hours 

TIS; and 

(ii) 38,220 landings equals 50,960 hours 

TIS. 

(5) Compliance with the life limits set in 

paragraph (f)(3) of this AD may be done by 

incorporating these limits into the limitations 

section of the aircraft maintenance manual. 

You may do this by inserting a copy of this 

AD into the limitations section of aircraft 

maintenance manual. 

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: Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4138; fax: (816) 329– 

4090; e-mail: taylor.martin@faa.gov. 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 European Aviation 

Safety Agency (EASA) AD No.: 2010–0162, 

dated August 4, 2010; BAE Systems British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 05–JA090143, dated April 

30, 2009; and British Aerospace Regional 

Aircraft British Aerospace Jetstream Series 

3100 & 3200 Service Bulletin 32–JA990142, 

dated March 26, 1999, for related 

information. 

Issued in Kansas City, Missouri, on 

September 21, 2010. 

Patrick R. Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–24180 Filed 9–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Parts 1, 31, 40, and 301 

[REG–153340–09] 

RIN 1545–BJ13 

Electronic Funds Transfer of 

Depository Taxes; Hearing 

Cancellation 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Cancellation of notice of public 

hearing on proposed rulemaking. 

SUMMARY: This document cancels a 

public hearing on proposed regulation 

relating to Federal tax deposits (FTDs) 

by Electronic Funds Transfer (EFT). The 

proposed regulations affect all taxpayers 

that currently use FTD coupons. 

DATES: The public hearing, originally 

scheduled for September 27, 2010 at 10 

a.m. is cancelled. 

FOR FURTHER INFORMATION CONTACT: 

Regina Johnson of the Publications and 

Regulations Branch, Legal Processing 

Division, Associate Chief Counsel 

(Procedure and Administration) at (202) 

622–7180 (not a toll-free number). 

SUPPLEMENTARY INFORMATION: A notice 

of proposed rulemaking and notice of 

public hearing that appeared in the 

Federal Register on Thursday, August 


emcdonald on DSK2BSOYB1PROD with PROPOSALS