12086 Federal Register / Vol. 74, No. 54 / Monday, March 23, 2009 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0224; Directorate 

Identifier 2007–NE–44–AD; Amendment 39– 

15860; AD 2009–07–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG (RRD) 

BR700–715A1–30, BR700–715B1–30, 

and BR700–715C1–30 Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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: 

It is necessary to change the limits of the 

High Pressure (HP) Turbine Stage 1 and Stage 

2 Rotor Discs. The maximum approved life 

of these discs is decreased for all flight 

missions. 

This Emergency Airworthiness Directive 

(EAD) has been raised to instruct mandatory 

decreased maximum approved lives in the 

BR715 Time Limits Manual (TLM) T–715– 

3BR for the HP Turbine Stage 1 Rotor Disc 

for both Part No. BRH20130 and Part No. 

BRH20131 and of the High Pressure (HP) 

Turbine Stage 2 Rotor Disc for both Part No. 

BRH19423 and Part No. BRH19427 for all 

flight missions. The life limits are decreased 

by the same proportion for all flight missions, 

thus back to birth pro-rata calculations due 

to the life limit changes are not necessary. 

We are issuing this AD to prevent 

rotating parts that may have exceeded 

their low-cycle fatigue life limits from 

failing, which could result in 

uncontained engine failure and 

subsequent damage to the airplane. 

DATES: This AD becomes effective April 

27, 2009. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 3, 2008 (73 FR 18220). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that: 

It is necessary to change the limits of the 

High Pressure (HP) Turbine Stage 1 and Stage 

2 Rotor Discs. The maximum approved life 

of these discs is decreased for all flight 

missions. 

This Emergency Airworthiness Directive 

(EAD) has been raised to instruct mandatory 

decreased maximum approved lives in the 

BR715 Time Limits Manual (TLM) T–715– 

3BR for the HP Turbine Stage 1 Rotor Disc 

for both Part No. BRH20130 and Part No. 

BRH20131 and of the High Pressure (HP) 

Turbine Stage 2 Rotor Disc for both Part No. 

BRH19423 and Part No. BRH19427 for all 

flight missions. The life limits are decreased 

by the same proportion for all flight missions, 

thus back to birth pro-rata calculations due 

to the life limit changes are not necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Correction to Table 

One commenter, Rolls-Royce 

Deutschland Ltd & Co KG, states that in 

the 2nd table following paragraph (e)(1), 

in the lower half, fifth column, ‘‘1165’’ 

should be corrected to read ‘‘21165’’. 

We agree and made the correction in 

the AD. 

Change to Table Headings 

Since we issued the proposed AD, we 

determined that the headings in the 

tables following paragraph (e)(1), of 

‘‘Mandatory Decreased Maximum 

Approved Life’’ are not sufficiently 

clear. We changed those headings to 

‘‘Declared Safe Cyclic Life, in Flight 

Cycles’’, in the AD. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Cost of Compliance 

We estimate that this AD will affect 

260 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about one work-hour per 

engine to perform the actions and that 

the average labor rate is $80 per workhour. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $20,800. Our cost 

estimate is exclusive of possible 

warranty coverage. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 AD: 

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 AD and placed it in the AD docket. 

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 AD, the regulatory 

evaluation, any comments received, and 


dwashington3 on PROD1PC60 with RULES
Federal Register / Vol. 74, No. 54 / Monday, March 23, 2009 / Rules and Regulations 12087 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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: 

2009–07–01 Rolls-Royce Deutschland Ltd & 

Co KG (formerly BMW Rolls-Royce 

GmbH, formerly BMW Rolls-Royce Aero 

Engines): Amendment 39–15860. Docket 

No. FAA–2008–0224; Directorate 

Identifier 2007-NE–44-AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 27, 2009. 

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. These engines 

are installed on, but not limited to, 

McDonnell Douglas Model 717–200 

airplanes. 

Reason 

(d) It is necessary to change the limits of 

the High Pressure (HP) Turbine Stage 1 and 

Stage 2 Rotor Discs. The maximum approved 

life of these discs is decreased for all flight 

missions. 

This Emergency Airworthiness Directive 

(EAD) has been raised to instruct mandatory 

decreased maximum approved lives in the 

BR715 Time Limits Manual (TLM) T–715– 

3BR for the HP Turbine Stage 1 Rotor Disc 

for both Part No. BRH20130 and Part No. 

BRH20131 and of the High Pressure (HP) 

Turbine Stage 2 Rotor Disc for both Part No. 

BRH19423 and Part No. BRH19427 for all 

flight missions. The life limits are decreased 

by the same proportion for all flight missions, 

thus back to birth pro-rata calculations due 

to the life limit changes are not necessary. 

We are issuing this AD to prevent rotating 

parts that may have exceeded their low-cycle 

fatigue life limits from failing, which could 

result in uncontained engine failure and 

subsequent damage to the airplane. 

Actions and Compliance 

(e) No later than 30 days after the effective 

date of this AD the following mandatory 

actions need to be completed for each 

individual BR700–715 HP Turbine Stage 1 

Rotor Disc for both Part No. BRH20130 and 

Part No. BRH20131 and High Pressure (HP) 

Turbine Stage 2 Rotor Disc for both Part No. 

BRH19423 and Part No. BRH19427 installed 

in a BR700–715A1–30, B1–30 or C1–30 

engine: 

(1) Identify the mandatory decreased 

maximum approved life for the HP Turbine 

Stage 1 and Stage 2 Rotor Discs listed in the 

tables below: 

High Pressure (HP) Turbine Stage 1 Rotor Disc Declared Safe Cyclic Life, in Flight Cycles 

Part No. 

Engine Thrust Rating Engine Flight Mission 

A1–30 

Design 

B1–30 

Design 

C1–30 

Design 

A1–30 

Hawaiian 

C1–30 

Tropical 

C1–30 

derated 

Tropical 

BRH20130 ................................................................................................ 15971 13324 10500 17647 3794 7941 

BRH20131 ................................................................................................ 15971 13324 10500 17647 3794 7941 

High Pressure (HP) Turbine Stage 2 Rotor Disc Declared Safe Cyclic Life, in Flight Cycles 

Part No. 

Engine Thrust Rating Engine Flight Mission 

A1–30 

Design 

B1–30 

Design 

C1–30 

Design 

A1–30 

Hawaiian 

C1–30 

Tropical 

C1–30 

derated 

Tropical 

BRH19423 ................................................................................................ 21165 17800 13372 21165 10893 13461 

BRH19427 ................................................................................................ 21165 17800 13372 21165 10893 13461 

(2) Record the mandatory maximum 

approved life in the applicable lifing 

documentation. It is mandatory to use the 

values given in the two tables in step (e)(1) 

of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(g) Refer to EASA Emergency 

Airworthiness Directive 2007–0152-E 

(corrected), dated June 1, 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. 

Material Incorporated by Reference 

(i) None. 

Issued in Burlington, Massachusetts, on 

March 17, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–6226 Filed 3–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

National Oceanic and Atmospheric 

Administration 

15 CFR Part 922 

[Docket No. 080311420–9008–02] 

RIN 0648–AT17 

Channel Islands National Marine 

Sanctuary Regulations; Notice of 

Effective Date 

AGENCY: Office of National Marine 

Sanctuaries (ONMS), National Oceanic 

and Atmospheric Administration 

(NOAA), Department of Commerce 

(DOC). 


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