Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46329 

TABLE 1—AIRPLANES ON WHICH AIRBUS SERVICE BULLETIN A300–57–0205 HAS NOT BEEN DONE

Flight cycles accumulated since first flight as of the effective date of 

this AD Compliance time 

Less than 6,000 flight cycles .................................................................... Prior to accumulating 6,000 flight cycles since first flight or within 90 

days after the effective date of this AD, whichever occurs later. 

6,000 flight cycles or more, but less than 12,000 flight cycles ................ Within 850 flight cycles after the effective date of this AD. 

12,000 flight cycles or more ..................................................................... Within 500 flight cycles after the effective date of this AD. 

TABLE 2—AIRPLANES ON WHICH AIRBUS SERVICE BULLETIN A300–57–0205 HAS BEEN DONE

Flight cycles accumulated since Airbus Service Bulletin A300–57–0205 

modification as of the effective date of this AD Compliance time 

Less than 6,000 flight cycles .................................................................... Prior to accumulating 6,000 flight cycles since Airbus Service Bulletin 

A300–57–0205 modification or within 90 days after the effective date 

of this AD, whichever occurs later. 

6,000 flight cycles or more, but less than 12,000 flight cycles ................ Within 850 flight cycles after the effective date of this AD. 

12,000 flight cycles or more ..................................................................... Within 500 flight cycles after the effective date of this AD. 

(2) If any crack is detected during any 

inspection required by this AD, before further 

flight, replace the center hinge bracket in the 

accordance with Airbus Mandatory Service 

Bulletin A300–57–0250, Revision 01, dated 

September 29, 2008. Within 6,000 flight 

cycles after replacing the center hinge 

bracket, do the inspection required by 

paragraph (f)(1) of this AD, and if no cracking 

is found, repeat the inspection thereafter at 

intervals not to exceed 850 flight cycles. 

(3) Modifying the inboard tab of the center 

flaps in accordance with Airbus Mandatory 

Service Bulletin A300–57–0252, dated 

August 27, 2008, terminates the requirements 

of this AD. 

(4) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Mandatory Service Bulletin A300–57– 

0250, dated November 2, 2007, are 

considered acceptable for compliance with 

the corresponding actions specified in this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although the European Aviation Safety 

Agency AD 2007–0299R2, dated October 28, 

2008 and Airbus Mandatory Service Bulletin 

A300–57–0250, dated November 2, 2007, 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. 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. 

(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. 

Related Information 

(h) Refer to MCAI Airworthiness Directive 

2007–0299R2, dated October 28, 2008; 

Airbus Mandatory Service Bulletin A300–57– 

0250, Revision 01, dated September 29, 2008; 

and Airbus Mandatory Service Bulletin 

A300–57–0252, dated August 27, 2008; for 

related information. 

Material Incorporated by Reference 

(i) You must use Airbus Mandatory Service 

Bulletin A300–57–0250, Revision 01, 

excluding Appendix 1, dated September 29, 

2008, to do the actions required by this AD, 

unless the AD specifies otherwise. If you do 

the optional terminating modification 

specified by this AD, you must use Airbus 

Service Bulletin A300–57–0252, dated 

August 27, 2008, to perform that action, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

31, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21411 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0771; Directorate 

Identifier 2009–NE–14–AD; Amendment 39– 

16009; AD 2009–18–13] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc. (RR) RB211 Trent 900 Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

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: 

Evidence from development testing and 

flight test Trent 900 engines has identified 

cracking on some HP Turbine Nozzle Guide 


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46330 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 

Vane (NGV) Convex Surfaces. Analysis of test 

data and review of the manufacturing process 

has revealed compounding effects that may 

contribute to a shortfall in component life 

and an increased likelihood of premature 

cracking in this region. Excessive cracking on 

the Convex Surface may lead to the release 

of NGV material or the blockage of Turbine 

gas flow. This results in a risk of fracture to 

the HP Turbine Blade. 

We are issuing this AD to prevent the 

release of a high-pressure (HP) turbine 

blade, which could result in an engine 

power loss or in-flight shut down of one 

or more engines, resulting in an 

inability to continue safe flight. 

DATES: This AD becomes effective 

October 14, 2009. 

We must receive comments on this 

AD by October 9, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of RR Alert Service Bulletin (ASB) 

RB.211–72–AF995, Revision 2, dated 

February 9, 2009, listed in the AD as of 

September 24, 2009. 

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: 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 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: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park; Burlington, MA 01803; 

e-mail: ian.dargin@faa.gov; telephone 

(781) 238–7178; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0051, 

dated March 5, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Evidence from development testing and 

flight test Trent 900 engines has identified 

cracking on some HP Turbine Nozzle Guide 

Vane (NGV) Convex Surfaces. Analysis of test 

data and review of the manufacturing process 

has revealed compounding effects that may 

contribute to a shortfall in component life 

and an increased likelihood of premature 

cracking in this region. Excessive cracking on 

the Convex Surface may lead to the release 

of NGV material or the blockage of Turbine 

gas flow. This results in a risk of fracture to 

the HP Turbine Blade. 

Not all NGV assemblies are affected. It is 

believed that the problem, if it exists, will 

manifest itself below 1000 cycles. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Rolls-Royce plc. has issued Alert 

Service Bulletin RB.211–72–AF995, 

Revision 2, dated February 9, 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 This AD 

This product has been approved by 

the aviation authority of the United 

Kingdom, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the United 

Kingdom, they have notified us of the 

unsafe condition described in the MCAI 

and service information referenced 

above. We are issuing 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. 

FAA’s Determination of the Effective 

Date 

Since no domestic operators use this 

product, notice and opportunity for 

public comment before issuing this AD 

are unnecessary. Therefore, we are 

adopting this regulation immediately. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0771; 

Directorate Identifier 2009–NE–14–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 with FAA 

personnel concerning this AD. Using the 

search function of the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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: 


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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46331 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

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: 

2009–18–13 Rolls-Royce plc: Amendment 

39–16009.; Docket No. FAA–2009–0771; 

Directorate Identifier 2009–NE–14–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 14, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce plc (RR) 

model RB211 Trent 970–84, 970B–84, 972– 

84, 972B–84, 977–84, 977B–84, and 980–84 

turbofan engines that do not incorporate RR 

modification Service Bulletin (SB) RB.211– 

72–G025. These engines are installed on, but 

not limited to, Airbus A380 airplanes. 

Reason 

(d) Evidence from development testing and 

flight test Trent 900 engines has identified 

cracking on some HP Turbine Nozzle Guide 

Vane (NGV) Convex Surfaces. Analysis of test 

data and review of the manufacturing process 

has revealed compounding effects that may 

contribute to a shortfall in component life 

and an increased likelihood of premature 

cracking in this region. Excessive cracking on 

the Convex Surface may lead to the release 

of NGV material or the blockage of Turbine 

gas flow. This results in a risk of fracture to 

the HP Turbine Blade. 

We are issuing this AD to prevent the 

release of a high-pressure (HP) turbine blade, 

which could result in an engine power loss 

or in-flight shut down of one or more 

engines, resulting in an inability to continue 

safe flight. 

Actions and Compliance 

First Inspection 

(e) Before accumulating 400 total cycles, 

inspect the HPT NGV Convex Surfaces, in 

accordance with the accomplishment 

instructions in section 3.A of Rolls-Royce 

RB211–Trent 900 Alert Non Modification 

Service Bulletin (NMSB) RB.211–72–AF995 

Revision 2, dated February 9, 2009. 

Reinspection 

(f) If no damage is identified at first 

inspection: 

(1) Repeat the inspection at intervals less 

than 250 Cycles apart. 

(2) If repeat inspections reveal no damage 

at 1000 cycles revert to normal inspection 

maintenance as detailed in the Rolls-Royce 

RB211–Trent 900 Maintenance Planning 

Document (MPD), and sign off this AD as 

complied with; no further inspections are 

required by this AD. 

(g) If any damage is identified, refer to the 

Table 1 and Table 2 in section 3.B. of RollsRoyce RB211–Trent 900 Alert NMSB 

RB.211–72–AF995 Revision 2, dated 

February 9, 2009, for reinspection intervals 

and rejection criteria. 

FAA AD Differences 

(h) None. 

Other FAA AD Provisions 

(i) Alternative Methods of Compliance 

(AMOCs): 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 

(j) Refer to MCAI EASA Airworthiness 

Directive 2009–0051, dated March 5, 2009. 

(k) Contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park; Burlington, MA 01803; 

e-mail: ian.dargin@faa.gov; telephone (781) 

238–7178; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(l) You must use RR Alert Non Mandatory 

Service Bulletin RB.211–72–AF995 Revision 

2, dated February 9, 2009, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Rolls-Royce plc, P.O. Box 

31, DERBY, DE24 8BJ, UK; telephone 44 (0) 

1332 242424; fax 44 (0) 1332 249936. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

August 20, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–20830 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0476; Directorate 

Identifier 2008–NM–188–AD; Amendment 

39–16006; AD 2009–18–10] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 707 Airplanes, and Model 720 

and 720B Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Boeing Model 

707 airplanes, and Model 720 and 720B 

series airplanes. The existing AD 

currently requires repetitive detailed 

inspections to detect cracks and 

corrosion on any existing repairs and at 

certain body stations (STA) of the 

visible surfaces of the wing to body 

terminal fittings including the web, 

flanges, and ribs; and applicable related 

investigative and corrective actions. 

This new AD retains the requirements of 

the existing AD and requires repetitive 

ultrasonic inspections to detect any 

stress corrosion cracks within the 

outboard flange of the left and right 

body terminal fittings at STA 820, and 

related investigative and corrective 

actions if necessary. This AD also 

provides an optional terminating action 

for the repetitive inspections. This AD 

also adds two airplanes to the 

applicability. This AD results from 

reports of cracks found in the wing to 

body terminal fittings during routine 

inspections. We are issuing this AD to 

detect and correct cracks and corrosion 

in the body terminal fittings above and 

below the floor, which could cause loss 

of support for the wing and could 

adversely affect the structural integrity 

of the airplane. 

DATES: This AD becomes effective 

October 14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 14, 2009. 


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