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 


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Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules 6639 

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 based on 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 European Community, has 

issued EASA Airworthiness Directive 

2007–0116–E, dated May 4, 2007 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

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 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. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of Germany, and 

is approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Germany, they have 

notified us of the unsafe condition 

described in the MCAI AD and service 

information referenced above. We are 

proposing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

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, in 

the Time Limits Manual No. T–715–

3BR; 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. 

• Applying the pro rate calculations 

and completing the Life Limited Part 

Tracking Sheet, using the revised 

Hawaiian Flight Mission maximum life 

limit of 25,000 flight cycles and 

checking if their consumed life has 

exceeded maximum approved life of the 

Flight Mission currently installed in; 

and 

• Before further flight, removing LP 

compressor disc assemblies from service 

that do not pass the check. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 240 engines installed 

on aircraft of U.S. registry. This 

proposed LP compressor (fan) disc 

assembly removal does not impose any 

additional labor costs if performed at 

the time of scheduled engine overhaul. 

We also estimate that it will take about 

one work-hour per engine to calculate 

and re-establish the achieved cyclic life 

for an LP compressor (fan) disc 

assembly, and that the average labor rate 

is $80 per work-hour. We estimate that 

the prorate cost of the life reduction per 

engine will be $33,000. Total cost of this 

proposed AD is, therefore, $7,939,200. 

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: 

Rolls-Royce Deutschland Ltd & Co KG 

(formerly BMW Rolls-Royce GmbH, and 

BMW Rolls-Royce Aero Engines): Docket 

No. FAA–2007–0169; Directorate 

Identifier 2007–NE–45–AD. 

Comments Due Date 

(a) We must receive comments by March 6, 

2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG (RRD), BR700–

715A1–30, BR700–715B1–30, and BR700–

715C1–30 turbofan engines, with a low 

pressure (LP) compressor disc assembly, part 

number (P/N) BRH10048 or P/N BRH19253, 

when installed in the BR700–715A1–30 

engine model and operated against the 

Hawaiian Flight Mission. These engines are 

installed on, but not limited to, McDonnell 

Douglas Corporation model 717–200 

airplanes. 

Reason 

(d) The mandatory continuous 

airworthiness information (MCAI) states: 

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 


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6640 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules 

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 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. 

This condition, if not corrected, could 

result in uncontained failure of the LP 

compressor (fan) disc assembly and damage 

to the airplane. 

Actions and Compliance 

(e) No later than 100 flight cycles after the 

effective date of this AD, do the following 

actions, unless already done. 

BR700–715A1–30 Turbofan Engines 

(1) For BR700–715A1–30 turbofan engines, 

amend the Airworthiness Limitations Section 

of the Time Limits Manual SUBTASK 05–10–

01–860–016, (Hawaiian Flight Mission Only) 

by revising the ‘‘GIVEN LIFE A1–30 RATING 

(FLIGHT CYCLES)’’ for both the LP 

compressor (fan) disc assembly P/N 

BRH10048 and LP compressor (fan) disc 

assembly P/N BRH19253 from 33,000 flight 

cycles to 25,000 flight cycles. 

(2) Amend any other Reference, where the 

maximum approved life limit is quoted for 

the LP compressor (fan) disc assembly P/N 

BRH10048 or LP compressor (fan) disc 

assembly P/N BRH19253, when installed in 

the BR700–715A–30 engine model and 

operated under the Hawaiian Flight Mission, 

to the revised maximum approved life limit 

of 25,000 flight cycles. 

BR700–715B1–30 and BR700–715C1–30 

Turbofan Engines 

(3) For BR700–715B1–30 and BR700–

715C1–30 turbofan engines: 

(i) Check to see if the LP compressor (fan) 

disc assembly P/N BRH10048 or LP 

compressor (fan) disc assembly P/N 

BRH19253 is currently, or has previously 

been, installed in the BR700–715A1–30 

engine model and operated under the 

Hawaiian Flight Mission, by checking the 

Life Limited Parts (LLP) Tracking Sheet. 

Information on recording and control of the 

lives of the parts can be found in the 

Airworthiness Limitations Section of the 

Time Limits Manual TASK 05–00–01–800–

001. 

(ii) If the LP compressor (fan) disc 

assembly has not operated, and is not going 

to operate in the Hawaiian Flight Mission, no 

further action is required. 

(iii) If the LP compressor (fan) disc 

assembly has operated in the Hawaiian Flight 

Mission: 

(A) Apply the prorate calculations and 

complete the LLP Tracking Sheet using the 

revised Hawaiian Flight Mission maximum 

approved life limit of 25,000 flight cycles. 

(B) Remove LP compressor (fan) disc 

assemblies from service before reaching 

25,000 flight cycles. 

Other FAA AD Provisions 

(f) Alternative Methods of Compliance: The 

Manager, Engine Certification Office, FAA, 

has the authority to approve alternative 

methods of compliance for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

Related Information 

(g) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2007–

0116–E, dated May 4, 2007, for related 

information. 

(h) 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, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

January 28, 2008. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–2039 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–2008–0115; Directorate 

Identifier 2007–NM–240–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab Model 

SAAB 2000 Airplanes 

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) 

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: 

One LM–219–92 Centre Bracket from an 

LM–219-SA28 Aft Engine Mounting 

assembly was found to be cracked while 

installed on the aircraft. 

This reduces the effectiveness of the 

mounting assembly and could eventually 

cause it to fail. 

* * * * * 

A failed mounting assembly, if not 

corrected, could result in loss of the 

engine. 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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, 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 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 in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM–

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1112; fax (425) 227–1149. 

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–2008–0115; Directorate Identifier 

2007–NM–240–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 based on 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 EASA 


rmajette on PROD1PC64 with PROPOSALS