49368 Federal Register / Vol. 75, No. 156 / Friday, August 13, 2010 / Rules and Regulations 

Page No. Revision level 

shown on page 

Date 

shown on page 

1, 3–4, 7, 15–16, 19 .................................................................................................................................. 4 June 15, 1990. 

2 ................................................................................................................................................................. 3 August 1, 1989. 

5, 8–12, 17–18, 20 .................................................................................................................................... 1 August 10, 1988. 

6, 13–14 .................................................................................................................................................... 2 June 27, 1989. 

(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 BAE Systems (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; e-mail 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(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. 

(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 July 28, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19329 Filed 8–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0748; Directorate 

Identifier 2010–NE–13–AD; Amendment 39– 

16384; AD 2010–16–07] 

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: 

Wear, beyond Engine Manual limits, has 

been identified on the abutment faces of the 

splines on the Trent 900 Intermediate 

Pressure (IP) shaft rigid coupling on several 

engines during strip. The shaft to coupling 

spline interface provides the means of 

controlling the turbine axial setting and wear 

through of the splines would permit the IP 

turbine to move rearwards. 

Rearward movement of the IP turbine 

would enable contact with static turbine 

components and would result in loss of 

engine performance with potential for inflight shut down, oil migration and oil fire 

below the LP turbine discs prior to sufficient 

indication resulting in loss of LP turbine disc 

integrity. 

We are issuing this AD to detect 

rearward movement of the IP turbine, 

which could result in loss of disc 

integrity, an uncontained failure of the 

engine, and damage to the airplane. 

DATES: This AD becomes effective 

September 17, 2010. 

We must receive comments on this 

AD by September 13, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of Rolls-Royce Trent 900 Series 

Propulsion Systems Alert NonModification Service Bulletin (NMSB) 

RB.211–72–AG329, Revision 1, dated 

January 13, 2010, listed in the AD as of 

September 17, 2010. 

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 2010–0008, 

dated January 15, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Wear, beyond Engine Manual limits, has 

been identified on the abutment faces of the 

splines on the Trent 900 Intermediate 

Pressure (IP) shaft rigid coupling on several 

engines during strip. The shaft to coupling 

spline interface provides the means of 

controlling the turbine axial setting and wear 

through of the splines would permit the IP 

turbine to move rearwards. 

Rearward movement of the IP turbine 

would enable contact with static turbine 

components and would result in loss of 

engine performance with potential for inflight shut down, oil migration and oil fire 

below the LP turbine discs prior to sufficient 

indication resulting in loss of LP turbine disc 

integrity. 

This AD requires inspection of the IP shaft 

coupling splines and, depending on the 

results, requires further repetitive inspections 

or corrective actions. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Rolls-Royce plc has issued RB211 

Trent 900 Series Propulsion Systems 

Alert NMSB RB.211–72–AG329, 

Revision 1, dated January 13, 2010. The 

actions described in this service 

information are intended to correct the 


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Federal Register / Vol. 75, No. 156 / Friday, August 13, 2010 / Rules and Regulations 49369 

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 the United Kingdom, 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–2010–0748; 

Directorate Identifier 2010–NE–13–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: 

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: 

2010–16–07 Rolls-Royce plc (RR): 

Amendment 39–16384.; Docket No. 

FAA–2010–0748; Directorate Identifier 

2010–NE–13–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 17, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to RR model RB211– 

Trent 970–84, 970B–84, 972–84, 972B–84, 

977–84, 977B–84, and 980–84 turbofan 

engines. These engines are installed on, but 

not limited to, Airbus A380 series airplanes. 

Reason 

(d) European Aviation Safety Agency 

(EASA) AD No. 2010–0008, dated January 15, 

2010, states: 

Wear, beyond Engine Manual limits, has 

been identified on the abutment faces of the 

splines on the Trent 900 Intermediate 

Pressure (IP) shaft rigid coupling on several 

engines during strip. The shaft to coupling 

spline interface provides the means of 

controlling the turbine axial setting and wear 

through of the splines would permit the IP 

turbine to move rearwards. 

Rearward movement of the IP turbine 

would enable contact with static turbine 

components and would result in loss of 

engine performance with potential for inflight shut down, oil migration and oil fire 

below the LP turbine discs prior to sufficient 

indication resulting in loss of LP turbine disc 

integrity. 

We are issuing this AD to detect rearward 

movement of the IP turbine, which could 

result in loss of disc integrity, an 

uncontained failure of the engine, and 

damage to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

On-Wing Borescope Inspection 

(1) Inspect the IP shaft coupling splines 

using section 3.A of RR RB211 Trent 900 

Series Propulsion Systems Alert NonModification Service Bulletin (NMSB) 

RB.211–72–AG329, Revision 1, dated January 

13, 2010, before accumulating 400 cyclessince-new or within 150 cycles-in-service 

(CIS) after the effective date of this AD, 

whichever occurs later. 

(2) If the coupling, P/N FW33264, was 

replaced with a new coupling, P/N FW33264, 

during any shop visit, then you may use the 

life since that shop visit in place of engine 

time since new to establish the inspection 

threshold. 

(3) Use the inspection results and actions 

compliance times or specified in Table 1 of 

this AD to disposition the engine or to 

determine the interval for the repetitive 

inspections. 


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49370 Federal Register / Vol. 75, No. 156 / Friday, August 13, 2010 / Rules and Regulations 

TABLE 1—ON-WING BORESCOPE INSPECTION—FURTHER ACTION AND REPETITIVE INSPECTION INTERVALS

Condition measured spline crest in accordance 

with section 3.A of Rolls-Royce alert NMSB 

RB.211–72–AG329, Revision 1, dated January 

13, 2010, is: 

Action Compliance time/repetitive interval (not to exceed) flight cycles since last inspection 

(i) Less than 0.5 mm with no material remaining Remove the engine .......................................... Before next flight. 

(ii) Less than 0.5 mm with some material remaining.Remove the engine .......................................... Within 10 flight cycles. 

(iii) Equal to or more than 0.5 mm but less than 

1 mm.

Repeat inspection ............................................ Within 50 flight cycles. 

(iv) Equal to or more than 1 mm but less than 

1.5 mm.

Repeat inspection ............................................ Within 100 flight cycles. 

(v) Equal to or more than 1.5 mm but less than 

2 mm.

Repeat inspection ............................................ Within 200 flight cycles. 

(vi) Equal to or more than 2 mm but less than 

2.4 mm.

Repeat inspection ............................................ Within 300 flight cycles. 

(vii) Equal to or more than 2.4 mm .................... Repeat inspection ............................................ Within 400 flight cycles. 

Note 1: The nominal unworn dimension of 

the spline crest is 2.65 mm. 

In-Shop Replacement and Inspection 

(4) At the next shop visit after the effective 

date of this AD perform the following: 

(i) Replace any IP shaft coupling that was 

previously borescope inspected in 

accordance with paragraph (e)(1) of this AD 

and put on a reduced re-inspection interval 

in accordance with paragraphs (e)(3)(i) 

through (e)(3)(vii) of this AD. 

(ii) Inspect all other IP shaft coupling 

splines using paragraphs 3.B.(2) or 3.B.(3) of 

RR RB211 Trent 900 Series Propulsion 

Systems Alert NMSB RB.211–72–AG329, 

Revision 1, dated January 13, 2010. 

Definitions 

(5) For the purposes of this AD, a shop visit 

is the induction of an engine into the shop 

for maintenance involving the separation of 

pairs of major mating engine flanges, except 

that the separation of engine flanges solely 

for the purposes of transportation without 

subsequent engine maintenance does not 

constitute an engine shop visit. 

FAA AD Differences 

(f) None. 

Other FAA AD Provisions 

(g) 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 

(h) Refer to MCAI EASA Airworthiness 

Directive 2010–0008, dated January 15, 2010, 

for related information. 

(i) Contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; email: ian.dargin@faa.gov; telephone (781) 

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

information about this AD. 

Material Incorporated by Reference 

(j) You must use Rolls-Royce RB211 Trent 

900 Series Propulsion Systems Alert NonModification Service Bulletin RB.211–72– 

AG329 Revision 1, dated January 13, 2010 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, United Kingdom; 

telephone 044 1332 242424; fax 044 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 

July 26, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–18730 Filed 8–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0281; Directorate 

Identifier 2009–NM–184–AD; Amendment 

39–16390; AD 2010–16–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F airplanes (Collectively Called 

A300–600 series airplanes); and A310 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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) 

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: 

Surface defects were visually detected on 

the rudder of an [Airbus] A319 and an A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A310 and A300–600 

aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 17, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

September 17, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 


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