6838 Federal Register / Vol. 73, No. 25 / Wednesday, February 6, 2008 / Rules and Regulations 

Dated: February 1, 2008. 

Lloyd C. Day, 

Administrator, Agricultural Marketing 

Service. 

[FR Doc. 08–536 Filed 2–4–08; 9:46 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27824; Directorate 

Identifier 2003–NE–12–AD; Amendment 39–

15364; AD 2006–11–05R2] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD) for 

Rolls-Royce plc (RR) RB211–22B series, 

RB211–524B, –524C2, –524D4, –524G2, 

–524G3, and –524H series, and RB211–

535C and –535E series turbofan engines 

with high pressure compressor (HPC) 

stage 3 disc assemblies, part numbers 

(P/Ns) LK46210, LK58278, LK67634, 

LK76036, UL11706, UL15358, UL22577, 

UL22578, and UL24738 installed. That 

AD currently requires removing from 

service certain disc assemblies before 

they reach their full published life if not 

modified with anticorrosion protection. 

This AD requires the same actions but 

relaxes the removal compliance time for 

certain disc assemblies that have a 

record of detailed inspection. This AD 

results from the FAA allowing certain 

affected disc assemblies that have a 

record of a detailed inspection, to 

remain in service for a longer period 

than the previous AD allowed. We are 

issuing this AD to relax the compliance 

time for disc assemblies manufactured 

both ‘‘before and after 1990’’ by 

providing an option to track the disc life 

based on a record of a detailed 

inspection rather than by its entry into 

service date, while continuing to 

prevent corrosion-induced uncontained 

disc assembly failure, resulting in 

damage to the airplane. 

DATES: Effective February 21, 2008. The 

Director of the Federal Register 

previously approved the incorporation 

by reference of certain publications 

listed in the regulations as of February 

24, 2004 (69 FR 2661, January 20, 2004). 

We must receive any comments on 

this AD by April 7, 2008. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Docket Management 

Facility, 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. 

Contact Rolls-Royce plc, PO Box 31, 

Derby, England, DE248BJ; telephone: 

011–44–1332–242424; fax: 011–44–

1332–245–418, for the service 

information identified in this AD. 

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: On May 

15, 2006, the FAA issued AD 2006–11–

05, Amendment 39–14609 (71 FR 

29586, May 23, 2006). We also issued a 

correction to that AD on September 26, 

2006 (71 FR 58254, October 3, 2006) and 

a revision to that AD on April 9, 2007 

(72 FR 18862, April 16, 2007). That AD 

revision requires removing from service 

certain disc assemblies before they 

reach their full published life if not 

modified with anticorrosion protection. 

That AD was the result of the 

manufacturer’s reassessment of the 

corrosion risk on HPC stage 3 disc 

assemblies that have not yet been 

modified with sufficient application of 

anticorrosion protection. That 

condition, if not corrected, could result 

in corrosion-induced uncontained disc 

assembly failure, resulting in damage to 

the airplane. 

Actions Since AD 2006–11–05R1 Was 

Issued 

Since AD 2006–11–05R1 was issued, 

we discovered that the population of 

affected disc assemblies identified in 

that AD was incorrect. That AD allowed 

affected disc assemblies that entered 

into service ‘‘before 1990’’ that have a 

record of a detailed inspection, to 

remain in service for a longer period 

than the previous AD, AD 2006–11–05, 

allowed. This revised AD allows disc 

assemblies manufactured both ‘‘before 

and after 1990’’ that have a record of a 

detailed inspection, to remain in service 

for 17 years from last overhaul 

inspection date. But the discs are not to 

exceed the manufacturer’s published 

cyclic limit in the time limits section of 

the manual. We are issuing this AD to 

relax the compliance time for certain 

disc assemblies by providing an option 

to track the disk life based on a record 

of a detailed inspection rather than by 

its entry into service date, while 

continuing to prevent corrosion-induced 

uncontained disc assembly failure, 

resulting in damage to the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of RR MSB No. 

RB.211–72–9661, Revision 5, dated 

December 22, 2006. That MSB allows 

affected disc assemblies and that have a 

record of detailed inspection: 

• To remain in service for 17 years 

from last overhaul inspection date; but 

• Not to exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. 

We do not incorporate by reference this 

MSB, but we list it in the Related 

Information section. 

Bilateral Airworthiness Agreement 

This engine model is manufactured in 

the United Kingdom (UK), and is type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Under this bilateral 

airworthiness agreement, the Civil 

Aviation Authority (CAA), which is the 

airworthiness authority for the UK, has 

kept the FAA informed of the situation 

described above. We have examined the 

findings of the CAA, reviewed all 

available information, and determined 

that AD action is necessary for products 

of this type design that are certificated 

for operation in the United States. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other RR RB211–22B series, RB211–

524B, –524C2, –524D4, –524G2, 

–524G3, and –524H series, and RB211–

535C and –535E series turbofan engines 

of the same type design. We are issuing 

this AD to relax the compliance time for 

certain disc assemblies by providing an 

option to track the disk life based on a 

record of a detailed inspection rather 

than by its entry into service date, while 

continuing to prevent corrosion-induced 

uncontained disc assembly failure, 

resulting in damage to the airplane. This 

AD requires the following for affected 

HPC stage 3 rotor disc assemblies: 


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Federal Register / Vol. 73, No. 25 / Wednesday, February 6, 2008 / Rules and Regulations 6839 

• Removing affected disc assemblies 

from service; and 

• Re-machining, inspecting, and 

applying anticorrosion protection; and 

• Re-marking, and returning disc 

assemblies into service; and 

• Allowing affected disc assemblies 

that have a record of a detailed 

inspection, to remain in service for 17 

years from last overhaul inspection date 

but not to exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable. Good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2007–27824; Directorate Identifier 

2003–NE–12–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

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 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). 

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. 

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 have 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 that 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration amends part 39 

of the Federal Aviation Regulations (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 

removing Amendment 39–15026 (72 FR 

18862, April 16, 2007) and by adding a 

new airworthiness directive, 

Amendment 39–15364, to read as 

follows: 

2006–11–05R2 Rolls-Royce plc: 

Amendment 39–15364. Docket No. 

FAA–2007–27824; Directorate Identifier 

2003–NE–12–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 21, 2008. 

Affected ADs 

(b) This AD revises AD 2006–11–05R1, 

Amendment 39–15026. 

Applicability 

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

RB211–22B series, RB211–524B, –524C2, 

–524D4, –524G2, –524G3, and –524H series, 

and RB211–535C and –535E series turbofan 

engines with high pressure compressor (HPC) 

stage 3 disc assemblies, part numbers (P/Ns) 

LK46210, LK58278, LK67634, LK76036, 

UL11706, UL15358, UL22577, UL22578, and 

UL24738 installed. These engines are 

installed on, but not limited to, Boeing 747, 

Boeing 757, Boeing 767, Lockheed L–1011, 

and Tupolev Tu204 series airplanes. 

Unsafe Condition 

(d) This AD results from the FAA allowing 

certain affected disc assemblies that have a 

record of a detailed inspection, to remain in 

service for a longer period than the previous 

AD allowed. We are issuing this AD to relax 

the compliance time for disc assemblies 

manufactured both ‘‘ before and after 1990’’

by providing an option to track the disc life 

based on a record of a detailed inspection 

rather than by its entry into service date, 

while continuing to prevent corrosioninduced uncontained disc assembly failure, 

resulting in damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Removal of HPC Stage 3 Disc Assemblies 

(f) Remove from service affected HPC stage 

3 disc assemblies identified in the following 

Table 1, using one of the following criteria: 


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6840 Federal Register / Vol. 73, No. 25 / Wednesday, February 6, 2008 / Rules and Regulations 

TABLE 1.—AFFECTED HPC STAGE 3 DISC ASSEMBLIES

Engine model 

Rework band for 

cyclic life accumulated on disc 

assemblies P/Ns 

LK46210 and 

LK58278 (pre 

RR Service Bulletin (SB) No. 

RB.211–72– 

5420) 

Rework band for 

cyclic life accumulated on disc 

assembly P/N 

LK67634 (pre 

RR SB No. 

RB.211–72– 

5420) 

Rework band for 

cyclic life accumulated on disc 

assemblies P/Ns 

LK76036, 

UL11706, 

UL15358, 

UL22577, 

UL22578, and 

UL24738 (pre 

RR SB No. 

RB.211–72– 

9434) 

–22B series ...................................................................................................................... 4,000–6,200 7,000–10,000 11,500–14,000 

–535E4 series .................................................................................................................. N/A N/A 9,000–15,000 

–524B–02, B–B–02, B3–02, and B4 series, Pre and Post accomplishment of SB No. 

72–7730 ....................................................................................................................... 4,000–6,000 7,000–9,000 11,500–14,000 

–524B2 and C2 series, Pre SB No. 72–7730 ................................................................. 4,000–6,000 7,000–9,000 11,500–14,000 

–524B2–B–19 and C2–B–19 series, SB No. 72–7730 ................................................... 4,000–6,000 7,000–9,000 8,500–11,000 

–524D4 series, Pre SB No. 72–7730 .............................................................................. 4,000–6,000 7,000–9,000 11,500–14,000 

–524D4–B series, SB No. 72–7730 ................................................................................ 4,000–6,000 7,000–9,000 8,500–11,000 

–524G2, G3, H, and H2 series ........................................................................................ 4,000–6,000 7,000–9,000 8,500–11,000 

(1) For disc assemblies that entered into 

service before 1990, remove disc assembly 

and rework as specified in paragraph (g)(2) of 

this AD, on or before January 4, 2007, but not 

to exceed the upper cyclic limit in Table 1 

of this AD before rework. Disc assemblies 

reworked may not exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. 

(2) For disc assemblies that entered into 

service in 1990 or later, remove disc 

assembly within the cyclic life rework bands 

in Table 1 of this AD, or within 17 years after 

the date of the disc assembly entering into 

service, whichever is sooner, but not to 

exceed the upper cyclic limit of Table 1 of 

this AD before rework. Disc assemblies 

reworked may not exceed the manufacturer’s 

published cyclic limit in the time limits 

section of the manual. 

(3) For disc assemblies that when new, 

were modified with an application of 

anticorrosion protection and re-marked to 

P/N LK76036 (not previously machined) as 

specified by part 1 of the original issue of RR 

SB No. RB.211–72–5420, dated April 20, 

1979, remove RB211–22B series disc 

assemblies before accumulating 10,000 

cycles-in-service (CIS), and remove RB211–

524 series disc assemblies before 

accumulating 9,000 CIS. 

(4) If the disc assembly date of entry into 

service cannot be determined, the date of 

disc assembly manufacture may be obtained 

from RR and used instead. 

(5) Disc assemblies in RB211–535C series 

operation are unaffected by the interim 

rework cyclic band limits in Table 1 of this 

AD, but must meet the calendar life 

requirements of either paragraph (f)(1) or 

(f)(2) of this AD, as applicable. 

Optional Rework of HPC Stage 3 Disc 

Assemblies 

(g) Rework HPC stage 3 disc assemblies 

that were removed in paragraph (f) of this AD 

as follows: 

(1) For disc assemblies that when new, 

were modified with an application of 

anticorrosion protection and re-marked to 

P/N LK76036 (not previously machined) as 

specified by Part 1 of the original issue of RR 

SB RB.211–72–5420, dated April 20, 1979, 

rework disc assemblies and re-mark to either 

P/N LK76034 or P/N LK78814 using 

paragraph 2.B. of the Accomplishment 

Instructions of RR SB No. RB.211–72–5420, 

Revision 4, dated February 29, 1980. This 

rework constitutes terminating action to the 

removal requirements in paragraph (f) of this 

AD. 

(2) For all other disc assemblies, rework 

using Paragraph 3.B. of the Accomplishment 

Instructions of RR SB No. RB.211–72–9434, 

Revision 4, dated January 12, 2000. This 

rework constitutes terminating action to the 

removal requirements in paragraph (f) of this 

AD. 

(3) If rework is done on disc assemblies 

that are removed before the disc assembly 

reaches the lower life of the cyclic life rework 

band in Table 1 of this AD, artificial aging 

of the disc assembly to the lower life of the 

rework band, at time of rework, is required. 

(4) Disc assemblies that have a record of 

detailed inspection, regardless of the date of 

entry into service, are allowed to remain in 

service for 17 years from last overhaul 

inspection date but not to exceed the 

manufacturer’s published cyclic limit in the 

time limits section of the manual. 

Alternative Methods of Compliance 

(h) The Manager, Engine Certification 

Office, 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 

(i) Civil Aviation Authority AD 004–01–94, 

dated January 4, 2002, and RR Mandatory 

Service Bulletin No. RB.211–72–9661, 

Revision 5, dated December 22, 2006, pertain 

to the subject of this AD. 

Material Incorporated by Reference 

(j) You must use Rolls-Royce plc Service 

Bulletin No. RB.211–72–5420, Revision 4, 

dated February 29, 1980, and Rolls-Royce plc 

Service Bulletin No. RB.211–72–9434, 

Revision 4, dated January 12, 2000, to 

perform the rework required by this AD. The 

Director of the Federal Register previously 

approved the incorporation by reference of 

these service bulletins in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51, as of 

February 24, 2004 (69 FR 2661, January 20, 

2004). You can get copies from Rolls-Royce 

plc, PO Box 31, Derby, England, DE248BJ; 

telephone: 011–44–1332–242424; fax: 011–

44–1332–245–418. You can 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. 

(k) 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. 

Issued in Burlington, Massachusetts, on 

January 25, 2008. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–2028 Filed 2–5–08; 8:45 am] 

BILLING CODE 4910–13–P 


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