6636 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules 

Applicability 

(c) This AD applies to Model R2160 

airplanes, serial numbers 001 through 378, 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code: 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

To prevent failure of the wing structure 

and assembly components due to undetected 

fatigue and corrosion * * * 

The MCAI requires that you inspect the wing 

structure and fuselage attachment and repair 

any defects that you find. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Disassemble the wings from the 

fuselage and inspect the wing structure and 

assembly components using instruction No. 1 

in Robin Aviation Service Bulletin No. 123, 

revision 3, dated December 23, 1999. If any 

defects are found, repair following Robin 

Aviation Service Bulletin No. 123, revision 3, 

dated December 23, 1999. Use the following 

compliance times for the inspection: 

(i) For airplanes with less than 4,000 hours 

time-in-service (TIS): When the airplane 

reaches a total of 3,500 hours TIS or within 

the next 100 hours TIS after the effective date 

of this AD, whichever occurs later, and 

thereafter at intervals not to exceed 750 hours 

TIS. 

(ii) For airplanes with 4,000 hours TIS or 

more that have not complied with the special 

instruction in paragraph E of Avions Pierre 

Robin Service Bulletin No. 123, revision 2, 

dated November 14, 1995: Within the next 

100 hours TIS after the effective date of this 

AD and thereafter at intervals not to exceed 

750 hours TIS. 

(iii) For airplanes with 4,000 hours TIS or 

more that have complied with the special 

instruction in paragraph E of Avions Pierre 

Robin Service Bulletin No. 123, revision 2, 

dated November 14, 1995: Within the next 

750 hours TIS after the effective date of this 

AD and thereafter at intervals not to exceed 

750 hours TIS. 

(2) When the airplane reaches a total of 

3,500 hours TIS with original wing-tofuselage bolts installed or 3,500 hours TIS of 

an airplane since new bolts have been 

installed or within the next 100 hours TIS 

after the effective date of this AD, whichever 

occurs later, do a non-destructive inspection 

of the wing-to-fuselage retaining bolts and 

replace any bolts that do not pass this 

inspection following instruction No. 2 in 

Robin Aviation Service Bulletin No. 123, 

revision 3, dated December 23, 1999. 

Thereafter, repetitively inspect wing-tofuselage retaining bolts and replace any bolts 

that do not pass this inspection every 750 

hours TIS following instruction No. 2 in 

Robin Aviation Service Bulletin No. 123, 

revision 3, dated December 23, 1999. 

Note 1: The requirement for a 3,500-hour 

inspection is a time since new or time since 

installation (that is, the TIS of new bolts). 

(3) Within the next 50 hours TIS after reassembling the wing and thereafter at 

intervals not to exceed 100 hours TIS, inspect 

the wing-to-fuselage retaining bolts for 

correct torque settings following instruction 

No. 3 in Robin Aviation Service Bulletin No. 

123, revision 3, dated December 23, 1999. 

The required torque value is 22 ft-lb with nut 

part number 95.24.39.010. Tighten to 16 ftlb (pre-loading) and then torque from 16 to 

22 ft-lb. 

FAA AD Differences 

Note 2: 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: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090. 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 Civil Aviation Authority 

AD DCA/R2000/28, dated September 28, 

2006, and Robin Aviation Mandatory Service 

Bulletin No. 123, revision 3, dated December 

23, 1999, for related information. 

Issued in Kansas City, Missouri, on January 

30, 2008. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–2047 Filed 2–4–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0136; Directorate 

Identifier 2007–CE–104–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Limited Model 750XL 

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 1⁄8-inch rivets installed in 

place of the correct 5⁄32-inch rivets that 

secure the horizontal tail surface load 

transfer angles to the rearmost fuselage 

frame at Station 384.62 (Corrected from 

369.62 per notification from the Civil 

Aviation Authority of New Zealand). 

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 March 6, 2008. 

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 


rmajette on PROD1PC64 with PROPOSALS
Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules 6637 

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: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; fax: (816) 

329–4090. 

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–2008–0136; Directorate Identifier 

2007–CE–104–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 Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

New Zealand, has issued AD DCA/ 

750XL/4, effective date: September 30, 

2004 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

describes the unsafe condition as 

1⁄8-inch rivets installed in place of the 

correct 5⁄32-inch rivets that secure the 

horizontal tail surface load transfer 

angles to the rearmost fuselage frame at 

Station 384.62 (Corrected from 369.62 

per notification from the Civil Aviation 

Authority of New Zealand). The MCAI 

requires you to inspect for the correct 

size rivets and if the wrong size rivets 

are installed, replace the rivets with the 

correct size rivets. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Pacific Aerospace Corporation 

Limited has issued Mandatory Service 

Bulletin No. PACSB/XL/010, dated: July 

23, 2004. 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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 7 products of U.S. registry. 

We also estimate that it would take 

about .5 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $280, or $40 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 2 work-hours and require parts 

costing $10, for a cost of $170 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, 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: 

Pacific Aerospace Limited: Docket No. FAA–

2008–0136; Directorate Identifier 2007–

CE–104–AD. 

Comments Due Date 

(a) We must receive comments by March 6, 

2008. 

Affected ADs 

(b) None. 


rmajette on PROD1PC64 with PROPOSALS
6638 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules 

Applicability 

(c) This AD applies to 750XL airplanes, 

serial numbers 101 through 108, certificated 

in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 51: Structures. 

Reason 

(e) The MCAI describes the unsafe 

condition as 1⁄8-inch rivets installed in place 

of the correct 5⁄32-inch rivets that secure the 

horizontal tail surface load transfer angles to 

the rearmost fuselage frame at Station 384.62 

(Corrected from 369.62 per notification from 

the Civil Aviation Authority of New 

Zealand). The MCAI requires you to inspect 

for the correct size rivets and if the wrong 

size rivets are installed, replace the rivets 

with the correct size rivets. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 100 hours time-in-service (TIS) 

after the effective date of this AD, inspect to 

ensure that 1⁄8-inch rivets are not installed in 

place of the correct 5⁄32-inch rivets that secure 

the horizontal tail surface load transfer angles 

to the rearmost fuselage frame at Station 

384.62 following Pacific Aerospace 

Corporation Limited Mandatory Service 

Bulletin No. PACSB/XL/010, dated: July 23, 

2004. 

(2) Before further flight, if you find 

undersized rivets are installed as a result of 

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

this AD, replace the undersized rivets with 

the correct 5⁄32-inch rivets following Pacific 

Aerospace Corporation Limited Service 

Mandatory Bulletin No. PACSB/XL/010, 

dated: July 23, 2004. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: An official 

of The New Zealand Civil Aviation Authority 

confirms that the MCAI should reference 

Station 384.62. 

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: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090. 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 Civil Aviation Authority 

of New Zealand AD DCA/750XL/4, effective 

date: September 30, 2004; and Pacific 

Aerospace Corporation Limited Mandatory 

Service Bulletin No. PACSB/XL/010, dated: 

July 23, 2004, for related information. 

Issued in Kansas City, Missouri, on January 

29, 2008. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–2046 Filed 2–4–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0169; Directorate 

Identifier 2007–NE–45–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG, BR700–

715A1–30, BR700–715B1–30, and 

BR700–715C1–30 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), 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 another country to identify 

and correct an unsafe condition on 

Rolls-Royce Deutschland Ltd & Co KG, 

BR700–715A1–30, BR700–715B1–30, 

and BR700–715C1–30 turbofan engines. 

The MCAI states the following: 

The application of most recent 3D FEM 

modeling has resulted in the need to 

reconsider the disc lives as currently shown 

in the Time Limits Manual. The current Post 

Certification Life Statement for the low 

pressure (LP) compressor (fan) disc assembly 

revises the Declared Safe Cyclic Life (DSCL) 

from 33,000 flight cycles to 25,000 flight 

cycles for both the BR715 LP (fan) disc 

assembly Part No. (P/N) BRH10048 and 

BR715 LP compressor (fan) disc assembly P/ 

N BRH19253, when installed in the BR700–

715A1–30 engine model and operated against 

the Hawaiian Flight Mission. 

The proposed AD would require 

revising the maximum approved life 

limit for both the BR715 LP compressor 

(fan) disc assembly P/N BRH10048 and 

BR715 LP compressor (fan) disc 

assembly P/N BRH19253, from 33,000 

flight cycles to 25,000 flight cycles, if 

ever operated against the Hawaiian 

Flight Mission and removing LP 

compressor (fan) disc assemblies from 

service that exceed the maximum 

approved life limit before further flight. 

This condition, if not corrected, could 

result in uncontained failure of the LP 

compressor (fan) disc assembly and 

damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by March 6, 2008. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Jason Yang, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: Jason.yang@faa.gov; telephone 

(781) 238–7747; fax (781) 238–7199. 

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–2007–0169; Directorate Identifier 

2007–NE–45–AD’’ at the beginning of 


rmajette on PROD1PC64 with PROPOSALS