Airworthiness Directives; Rolls-Royce plc (RR) RB211-Trent 800 Series Turbofan Engines, 10355-10356 [2012-3863]

Download as PDF Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Rules and Regulations 39–1917 (39 FR 28229, August 6, 1974)), and thereafter at intervals not to exceed 1,000 hours’ time-in-service from the last inspections, accomplish the following: (1) Inspect all lavatory paper and linen waste receptacle enclosure access doors and disposal doors for proper operation, fit, sealing, and latching for the containment of possible trash fires. (2) Correct all defects found during the inspections required by paragraph (k)(1) of this AD. (l) Restatement of Requirements of AD 74– 08–09 R2, Amendment 39–9680 (61 FR 32318, June 24, 1996): Adjustments to Inspection Intervals Upon the request of an operator, the FAA Principal Maintenance Inspector (PMI) may adjust the 1,000-hour repetitive inspection interval specified in paragraph (k) of this AD to permit compliance at an established inspection period of the operator if the request contains data to justify the requested change in the inspection interval. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Airframe/Cabin Safety Branch, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (n) Related Information For more information about this AD, contact Alan Sinclair, Aerospace Engineer, Airframe/Cabin Safety Branch, ANM–115, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–227–2195; fax: 425– 227–1232; email: alan.sinclair@faa.gov. (o) Material Incorporated by Reference Issued in Renton, Washington, on January 27, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. wreier-aviles on DSK5TPTVN1PROD with RULES Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0755; Directorate Identifier 2010–NE–12–AD; Amendment 39– 16956; AD 2012–04–01] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc (RR) RB211–Trent 800 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for all RR RB211–Trent 800 series turbofan engines. That AD currently requires removal from service of certain critical engine parts based on reduced life limits. This new AD reduces the life limits of additional critical engine parts. This AD was prompted by RR reducing the life limits of additional critical engine parts. We are issuing this AD to prevent the failure of critical rotating parts, which could result in uncontained failure of the engine and damage to the airplane. DATES: This AD is effective March 28, 2012. SUMMARY: For service information identified in this AD, contact RollsRoyce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332–242424; fax: 011– 44–1332–245418 or email from https:// www.rolls-royce.com/contact/ civil_team.jsp, or download the publication from https:// www.aeromanager.com. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. ADDRESSES: Examining the AD Docket None. [FR Doc. 2012–3973 Filed 2–21–12; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 DEPARTMENT OF TRANSPORTATION 14:56 Feb 21, 2012 Jkt 226001 You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility 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 address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 10355 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7143; fax: 781–238– 7199; email: alan.strom@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede airworthiness directive (AD) 2003–16– 18, amendment 39–13271 (68 FR 49344, August 18, 2003). That AD applies to the specified products. That SNPRM published in the Federal Register on November 7, 2011 (76 FR 68663). The original NPRM (75 FR 45560, August 3, 2010) proposed to revise the Trent 800 Time limits Manual (TLM) of the Trent 800 engine maintenance manuals (EMMs). The SNPRM proposed to prohibit installation of one certain critical part and to increase the life of another critical part whose lives were previously reduced by that existing AD. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM (76 FR 68663, November 7, 2011). Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance Based on the service information, we estimate that this AD affects about 16 RB211–Trent 800 series turbofan engines of U.S. registry. The average labor rate is $85 per work-hour, but no labor cost is associated with this AD because discs are replaced at scheduled maintenance intervals. Prorated cost of parts cost about $45,000 per engine. Based on these figures, we estimate the cost of the AD on U.S. operators to be $720,000. 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: E:\FR\FM\22FER1.SGM 22FER1 10356 Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Rules and Regulations ‘‘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. (3) Will not affect intrastate aviation in Alaska, and (4) 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. 2012–04–01 Rolls-Royce plc: Amendment 39–16956; Docket No. FAA–2010–0755; Directorate Identifier 2010–NE–12–AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. This AD supersedes AD 2003–16–18, Amendment 39–13271 (68 FR 49344, August 18, 2003). Regulatory Findings Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: This AD applies to Rolls-Royce plc (RR) RB211–Trent 895–17, 892–17, 892B–17, 884– 17, 884B–17, 877–17, and 875–17 turbofan engines. 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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), This AD is effective March 28, 2012. (b) Affected ADs (c) Applicability (d) Unsafe Condition This AD was prompted by RR reporting changes to the lives of certain life-limited rotating parts. We are issuing this AD to prevent the failure of critical rotating parts, which could result in uncontained failure of the engine and damage to the airplane. 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 (a) Effective Date (e) Actions and Compliance Compliance is required within 30 days after the effective date of this AD, unless already done. (1) After the effective date of this AD, remove from service the parts listed in Table 1 of this AD before exceeding the new life limit indicated: [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2003–16–18, Amendment 39–13271 (68 FR 49344, August 18, 2003) and adding the following new AD: ■ TABLE 1—REDUCED PART LIVES Part No. (P/N) Part nomenclature (i) Intermediate-pressure (IP) Compressor Rotor Shaft ........................................................ (ii) IP Compressor Rotor Shaft .............................................................................................. (iii) High-pressure (HP) Compressor Stage 1 to 4 Rotor Discs Shaft .................................. (iv) HP Compressor Stage 1 to 4 Rotor Discs Shaft ............................................................ (v) HP Compressor Stage 1 to 4 Rotor Discs Shaft ............................................................. (vi) HP Compressor Stage 1 to 4 Rotor Discs Shaft ............................................................ (vii) HP Compressor Stage 1 to 4 Rotor Discs Shaft ........................................................... (viii) HP Compressor Stage 5 and 6 Discs and Cone .......................................................... (ix) HP Compressor Stage 5 and 6 Discs and Cone ............................................................ (x) IP Turbine Rotor Disc ....................................................................................................... (xi) IP Turbine Rotor Disc ...................................................................................................... (f) Installation Prohibition After the effective date of this AD, do not install any IP turbine rotor discs, P/N FK33083, into any engine. wreier-aviles on DSK5TPTVN1PROD with RULES (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. (h) Related Information (1) You may find additional information on calculating Standard Duty Cycles and/or using HEAVY Profile Cycles, in RR Time Limits Manual 05–00–01–800–801, Recording and Control of the Lives of Parts. (2) For more information about this AD, contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine & VerDate Mar<15>2010 14:56 Feb 21, 2012 Jkt 226001 Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7143; fax: 781–238–7199; email: alan.strom@faa.gov. (3) Refer to European Aviation Safety Agency Airworthiness Directive 2007– 0003R1, dated January 15, 2009, and RR Alert Service Bulletin No. RB.211–72–AE935, Revision 7, dated January 19, 2009, for related information. (4) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; phone: 011–44–1332– 242424; fax: 011–44–1332–249936; email from https://www.rolls-royce.com/contact/ civil_team.jsp; or Web: https://www. aeromanager.com. Life in standard duty cycles FK24100 FK24496 FK24009 FK26167 FK32580 FW11590 FW61622 FK25230 FK27899 FK21117 FK33083 Frm 00006 Fmt 4700 Sfmt 9990 8,140 8,180 4,460 6,000 6,850 6,850 6,850 5,000 5,000 10,400 0 Issued in Burlington, Massachusetts, on February 10, 2012. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–3863 Filed 2–21–12; 8:45 am] BILLING CODE 4910–13–P (i) Material Incorporated by Reference None. PO 00000 8,140 8,860 4,560 6,340 8,550 8,550 8,550 5,000 5,000 11,610 0 Life in cycles using the HEAVY profile E:\FR\FM\22FER1.SGM 22FER1

Agencies

[Federal Register Volume 77, Number 35 (Wednesday, February 22, 2012)]
[Rules and Regulations]
[Pages 10355-10356]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-3863]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0755; Directorate Identifier 2010-NE-12-AD; 
Amendment 39-16956; AD 2012-04-01]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc (RR) RB211-Trent 800 
Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for all RR RB211-Trent 800 series turbofan engines. That AD currently 
requires removal from service of certain critical engine parts based on 
reduced life limits. This new AD reduces the life limits of additional 
critical engine parts. This AD was prompted by RR reducing the life 
limits of additional critical engine parts. We are issuing this AD to 
prevent the failure of critical rotating parts, which could result in 
uncontained failure of the engine and damage to the airplane.

DATES: This AD is effective March 28, 2012.

ADDRESSES: For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, 
DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-245418 or email 
from https://www.rolls-royce.com/contact/civil_team.jsp, or download 
the publication from https://www.aeromanager.com. You may review copies 
of the referenced service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
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 address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7143; fax: 
781-238-7199; email: alan.strom@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede airworthiness directive (AD) 2003-16-
18, amendment 39-13271 (68 FR 49344, August 18, 2003). That AD applies 
to the specified products. That SNPRM published in the Federal Register 
on November 7, 2011 (76 FR 68663). The original NPRM (75 FR 45560, 
August 3, 2010) proposed to revise the Trent 800 Time limits Manual 
(TLM) of the Trent 800 engine maintenance manuals (EMMs). The SNPRM 
proposed to prohibit installation of one certain critical part and to 
increase the life of another critical part whose lives were previously 
reduced by that existing AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM (76 FR 68663, November 7, 
2011).

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    Based on the service information, we estimate that this AD affects 
about 16 RB211-Trent 800 series turbofan engines of U.S. registry. The 
average labor rate is $85 per work-hour, but no labor cost is 
associated with this AD because discs are replaced at scheduled 
maintenance intervals. Prorated cost of parts cost about $45,000 per 
engine. Based on these figures, we estimate the cost of the AD on U.S. 
operators to be $720,000.

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:

[[Page 10356]]

``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

    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 DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2003-16-18, Amendment 39-13271 (68 FR 49344, August 18, 2003) and 
adding the following new AD:

2012-04-01 Rolls-Royce plc: Amendment 39-16956; Docket No. FAA-2010-
0755; Directorate Identifier 2010-NE-12-AD.

(a) Effective Date

    This AD is effective March 28, 2012.

(b) Affected ADs

    This AD supersedes AD 2003-16-18, Amendment 39-13271 (68 FR 
49344, August 18, 2003).

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-Trent 895-17, 892-
17, 892B-17, 884-17, 884B-17, 877-17, and 875-17 turbofan engines.

(d) Unsafe Condition

    This AD was prompted by RR reporting changes to the lives of 
certain life-limited rotating parts. We are issuing this AD to 
prevent the failure of critical rotating parts, which could result 
in uncontained failure of the engine and damage to the airplane.

(e) Actions and Compliance

    Compliance is required within 30 days after the effective date 
of this AD, unless already done.
    (1) After the effective date of this AD, remove from service the 
parts listed in Table 1 of this AD before exceeding the new life 
limit indicated:

                                           Table 1--Reduced Part Lives
----------------------------------------------------------------------------------------------------------------
                                                                                    Life in       Life in cycles
                      Part nomenclature                         Part No. (P/N)   standard duty   using the HEAVY
                                                                                     cycles          profile
----------------------------------------------------------------------------------------------------------------
(i) Intermediate-pressure (IP) Compressor Rotor Shaft........          FK24100            8,140            8,140
(ii) IP Compressor Rotor Shaft...............................          FK24496            8,860            8,180
(iii) High-pressure (HP) Compressor Stage 1 to 4 Rotor Discs           FK24009            4,560            4,460
 Shaft.......................................................
(iv) HP Compressor Stage 1 to 4 Rotor Discs Shaft............          FK26167            6,340            6,000
(v) HP Compressor Stage 1 to 4 Rotor Discs Shaft.............          FK32580            8,550            6,850
(vi) HP Compressor Stage 1 to 4 Rotor Discs Shaft............          FW11590            8,550            6,850
(vii) HP Compressor Stage 1 to 4 Rotor Discs Shaft...........          FW61622            8,550            6,850
(viii) HP Compressor Stage 5 and 6 Discs and Cone............          FK25230            5,000            5,000
(ix) HP Compressor Stage 5 and 6 Discs and Cone..............          FK27899            5,000            5,000
(x) IP Turbine Rotor Disc....................................          FK21117           11,610           10,400
(xi) IP Turbine Rotor Disc...................................          FK33083                0                0
----------------------------------------------------------------------------------------------------------------

(f) Installation Prohibition

    After the effective date of this AD, do not install any IP 
turbine rotor discs, P/N FK33083, into any engine.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(h) Related Information

    (1) You may find additional information on calculating Standard 
Duty Cycles and/or using HEAVY Profile Cycles, in RR Time Limits 
Manual 05-00-01-800-801, Recording and Control of the Lives of 
Parts.
    (2) For more information about this AD, contact Alan Strom, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7143; fax: 781-238-7199; email: 
alan.strom@faa.gov.
    (3) Refer to European Aviation Safety Agency Airworthiness 
Directive 2007-0003R1, dated January 15, 2009, and RR Alert Service 
Bulletin No. RB.211-72-AE935, Revision 7, dated January 19, 2009, 
for related information.
    (4) For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, DE24 
8BJ, United Kingdom; phone: 011-44-1332-242424; fax: 011-44-1332-
249936; email from https://www.rolls-royce.com/contact/civil_team.jsp; or Web: https://www.aeromanager.com.

(i) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on February 10, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-3863 Filed 2-21-12; 8:45 am]
BILLING CODE 4910-13-P
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