Document ID: FAA-2007-28059-0021
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Rolls-Royce plc Turbofan Engines
Posted Date: 2013-03-21T04:00Z

[Federal Register Volume 78, Number 55 (Thursday, March 21, 2013)]
[Proposed Rules]
[Pages 17300-17303]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-06498]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28059; Directorate Identifier 2007-NE-13-AD]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) for all Rolls-Royce plc (RR) RB211-Trent 553-61, 553A2-61, 556-61, 
556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61, 768-60, 772-60, 772B-60, 
875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan 
engines. The existing AD currently requires inspection of the 
intermediate-pressure (IP) compressor rotor shaft rear balance land for 
cracks. Since we issued that AD, a crack was detected in a Trent 500 IP 
compressor rotor shaft rear balance land during a shop visit, and 
further engineering evaluation done by RR concluded that the cracking 
may also exist in Trent 900 engines. This proposed AD would require 
inspections of the IP compressor rotor shaft as required by the 
existing AD while adding on-wing inspections for the Trent 500 engines, 
and on-wing and in-shop inspections for the Trent 900 engines. We are 
proposing this AD to detect cracking on the IP compressor rotor shaft 
rear balance land, which could lead to uncontained engine failure and 
damage to the airplane.

DATES: We must receive comments on this proposed AD by May 20, 2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    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; email: http://www.rolls-royce.com/contacts/civil_team.jsp. You may view this 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 http://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 proposed AD, the regulatory 
evaluation, any comments received and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Frederick Zink, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7779; 
fax: 781-238-7199; email: frederick.zink@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28059; Directorate Identifier 2007-NE-13-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy

[[Page 17301]]

aspects of this proposed AD. We will consider all comments received by 
the closing date and may amend this proposed 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 we 
receive about this proposed AD.

Discussion

    On May 15, 2012, we issued AD 2012-10-12, Amendment 39-17061 (77 FR 
31176, May 25, 2012), for all RR RB211-Trent 553-61, 553A2-61, 556-61, 
556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61, 768-60, 772-60, 772B-60, 
875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan 
engines. That AD requires continuing initial inspections, adding 
additional inspections, and a mandatory terminating action. That AD 
resulted from reports of additional cracking on RB211-Trent 700 and 
RB211-Trent 800 IP compressor rotor shafts. We issued that AD to detect 
cracking on the IP compressor rotor shaft rear balance land, which 
could lead to uncontained engine failure and damage to the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2012-10-12, Amendment 39-17061 (77 FR 31176, May 
25, 2012), a crack in a Trent 500 IP compressor rotor shaft rear 
balance land was detected during a shop visit. Further engineering 
evaluation, done by RR, concluded that the cracking may also exist in 
Trent 900 engines.

Relevant Service Information

    We reviewed RR Non-Modification Alert Service Bulletin (NMASB) No. 
RB.211-72-AH058, dated December 13, 2012, and RR NMASB No. RB.211-72-
AH059, dated December 11, 2012. NMASB No. RB.211-72-AH058 describes 
procedures for inspection of RB211-Trent 553-61, 553A2-61, 556-61, 
556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 engines. NMASB No. 
RB.211-72-AH059 describes procedures for inspection of RB211-Trent 970-
84, 970B-84, 972-84, 972B-84, 977-84, 977B-84, and 980-84 engines.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all the requirements of AD 2012-10-
12, Amendment 39-17061 (77 FR 31176, May 25, 2012). This proposed AD 
would add requirements to perform on-wing inspections for the Trent 500 
and on-wing and in-shop inspections for the Trent 900 engines.

Costs of Compliance

    We estimate that this proposed AD would affect about 136 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 14 hours per engine to perform required inspections. The 
average labor rate is $85 per hour. Replacement parts are estimated to 
cost about $2,271 per engine. Based on these figures, we estimate the 
cost of the proposed AD on U.S. operators to be $470,696.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    (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),
    (3) Will not affect intrastate aviation in Alaska, to the extent 
that it justifies making a regulatory distinction, 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2012-10-12, Amendment 39-17061 (77 FR 31176, May 25, 2012), and adding 
the following new AD:

Rolls-Royce plc: Docket No. FAA-2007-28059; Directorate Identifier 
2007-NE-13-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by May 20, 2013.

(b) Affected ADs

    This AD supersedes AD 2012-10-12, Amendment 39-17061 (77 FR 
31176, May 25, 2012).

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-Trent 553-61, 
553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61, 
768-60, 772-60, 772B-60, 875-17, 877-17, 884-17, 884B-17, 892-17, 
892B-17, 895-17, 970-84, 970B-84, 972-84, 972B-84, 977-84, 977B-84, 
and 980-84 turbofan engines.

(d) Unsafe Condition

    This AD was prompted by detection of a crack in a Trent 500 
intermediate-pressure (IP) compressor rotor shaft rear balance land 
with follow-on RR engineering evaluation concluding that cracking 
may also exist in Trent 900 engines. We are issuing this AD to 
detect cracking on the IP compressor rotor shaft rear balance land, 
which could lead to uncontained engine failure and damage to the 
airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

[[Page 17302]]

(f) RB211-Trent 700 Series Engines--Rear Balance Land Inspections

    (1) Within 625 cycles-in-service (CIS) after June 29, 2012, or 
before the next flight after the effective date of this AD, 
whichever occurs later, borescope inspect the IP compressor rotor 
shaft rear balance land. Use RB211 Trent 700 Series Propulsion 
System Non-Modification Alert Service Bulletin (NMASB) No. RB.211-
72-AG270, Revision 4, dated March 21, 2011, sections 3.A.(2)(a) 
through 3.A.(2)(c) and 3.A.(3)(a) through 3.A.(3)(c) for in-shop 
procedures, or 3.B.(2)(a) through 3.B.(2)(c) and 3.B.(4)(a) through 
3.B.(4)(c) for on-wing procedures, to do the inspection.
    (2) Thereafter, repeat the inspection within every 625 cycles-
since-last inspection (CSLI). You may count CSLI from the last 
borescope inspection or the last eddy current inspection (ECI), 
whichever occurred last.
    (3) At each shop visit after the effective date of this AD, 
perform an ECI and visually inspect the IP compressor rotor shaft 
rear balance land, and visually inspect the balance weights. Use 
RB211 Trent 700 and Trent 800 Series Propulsion Systems NMASB No. 
RB.211-72-AG085, Revision 2, dated July 7, 2011, sections 3.A. 
through 3.C., to do the inspections.

(g) RB211-Trent 800 Series Engines--Rear Balance Land Inspections

    (1) Within 475 CIS after June 29, 2012, or before the next 
flight after the effective date of this AD, whichever occurs later, 
borescope inspect the IP compressor rotor shaft rear balance land. 
Use RB211 Trent 800 Series Propulsion System NMASB No. RB.211-72-
AG264, Revision 5, dated March 21, 2011, sections 3.A.(2)(b) through 
3.A.(2)(c) and 3.A.(3)(a) through 3.A.(3)(c) for in-shop procedures, 
or 3.B.(2)(a) through 3.B.(2)(c) and 3.B.(4)(a) through 3.B.(4)(c) 
for on-wing procedures, to do the inspection.
    (2) Thereafter, repeat the inspection within every 475 CSLI. You 
may count CSLI from the last borescope inspection or the last ECI, 
whichever occurred last.
    (3) At each shop visit, perform an ECI and visually inspect the 
IP compressor rotor shaft rear balance land, and visually inspect 
the balance weights. Use RB211 Trent 700 and Trent 800 Series 
Propulsion Systems NMASB No. RB.211-72-AG085, Revision 2, dated July 
7, 2011, sections 3.A. through 3.C., to do the inspections.

(h) RB211-Trent 500 Series Engines--Rear Balance Land Inspections

    (1) Within 340 CIS after the effective date of this AD, 
borescope inspect the IP compressor rotor shaft rear balance land. 
Use RB211 Trent 500 Series Propulsion Systems NMASB No. RB.211-72-
AH058, dated December 13, 2012, sections 3.A.(2)(a) through 
3.A.(2)(c), 3.A.(3)(a) through 3.A.(3)(d), and 3.A.(5)(a) through 
3.A.(5)(c) for on-wing procedures, to do the inspection.
    (2) Thereafter, repeat the inspection within every 340 CSLI. You 
may count CSLI from the last borescope inspection or the last ECI, 
whichever occurred last.
    (3) At each shop visit, perform an ECI and visually inspect the 
IP compressor rotor shaft rear balance land, and visually inspect 
the balance weights. Use RB211 Trent 500 and Trent 900 Series 
Propulsion Systems Non-Modification Service Bulletin (NMSB) No. 
RB.211-72-G448, Revision 3, dated July 7, 2011, sections 3.D.(4) 
through 3.D.(5), 3.D.(6)(f) through 3.D.(7)(w), 3.D.(8)(f) through 
3.D.(8)(w), 3.D.(11), and 3.D.(12), to do the inspections.

(i) RB211-Trent 900 Series Engines--Rear Balance Land Inspections

    (1) Within 280 flight cycles after the effective date of this 
AD, borescope inspect the IP compressor rotor shaft rear balance 
land. Use RB211 Trent 900 Series Propulsion Systems NMASB No. 
RB.211-72-AH059, dated December 11, 2012, sections 3.A.(2)(a) 
through 3.A.(2)(c), 3.A.(3)(a) through 3.A.(3)(d), and 3.A.(5)(a) 
through 3.A.(5)(c), to do the inspection.
    (2) Thereafter, repeat the inspection within every 280 CSLI. You 
may count from the last borescope inspection or the last ECI, 
whichever occurred last.
    (3) At each shop visit after the effective date of this AD, 
perform an ECI and visually inspect the IP compressor rotor shaft 
rear balance land, and visually inspect the balance weights. Use 
RB211 Trent 500 and Trent 900 Series Propulsion Systems NMSB No. 
RB.211-72-G448, Revision 3, dated July 7, 2011, sections 3.D.(4) 
through 3.D.(5), 3.D.(6)(f) through 3.D.(7)(w), 3.D.(8)(f) through 
3.D.(8)(w), 3.D.(11), and 3.D.(12), to do the inspection.

(j) Mandatory Termination Action for RB211-Trent 700 and RB211-Trent 
800 Engines

    (1) For RB211-Trent 700 engines. At the next shop visit in which 
any level of inspection or strip is scheduled to be carried out on 
the IP compressor, remove the existing IP compressor balance 
weights.
    (2) For RB211-Trent 800 engines. At the next shop visit in which 
any level of inspection or strip is scheduled to be carried out on 
the IP compressor, remove the existing IP compressor balance 
weights.
    (3) Once you have removed the balance weights, do not re-install 
them on any IP compressor shaft rear balance land.

(k) Credit for Previous Actions

    (1) For RB211-Trent 700 series engines:
    (i) If you borescope inspected your RB211-Trent 700 series 
engine using RB211 Trent 700 Series Propulsion System NMASB No. 
RB.211-72-AG270, Revision 1, dated December 14, 2009, or Revision 2, 
dated December 21, 2010, or Revision 3, dated February 25, 2011, 
before the effective date of this AD, you have satisfied the 
requirements of paragraph (f)(1) of this AD.
    (ii) If you performed the ECI and visual inspection of your 
RB211-Trent 700 series engines using RB211 Trent 700 and Trent 800 
Series Propulsion Systems NMASB No. RB.211-72-AG085, Revision 1, 
dated September 27, 2010, before the effective date of this AD, you 
have satisfied the ECI and visual inspections required by paragraph 
(f)(3) of this AD.
    (2) For RB211-Trent 800 series engines:
    (i) If you borescope inspected your RB211-Trent 800 series 
engine using RB211 Trent 800 Series Propulsion System NMASB No. 
RB.211-72-AG264, Revision 3, dated December 21, 2010, or Revision 4, 
dated February 25, 2011, before the effective date of this AD, you 
have satisfied the requirements of paragraph (g)(1) of this AD.
    (ii) If you performed the ECI and in-shop visual inspection of 
your RB211-Trent 800 series engines using RB211 Trent 700 and Trent 
800 Series Propulsion Systems NMASB No. RB.211-72-AG085, Revision 1, 
dated September 27, 2010, before the effective date of this AD, you 
have satisfied the ECI and visual inspections required by paragraph 
(g)(3) of this AD.
    (3) For RB211-Trent 500 and 900 series engines:
    (i) If you performed the ECI of your RB211-Trent 500 series 
engines using RB211 Trent 500, 700 and 800 Series Propulsion Systems 
NMASB No. RB.211-72-AF260, Revision 4, dated July 28, 2009, and 
RB211 Trent 500 and Trent 900 Series Propulsion Systems NMSB No. 
RB.211-72-G448, Revision 2, dated December 23, 2010 before the 
effective date of this AD, you have satisfied the ECIs required by 
paragraph (h)(3) of this AD.
    (ii) If you performed the in-shop visual inspection of your 
RB211-Trent 500 series engines using RB211 Trent 500 and Trent 900 
Series Propulsion Systems NMSB No. RB.211-72-G448, Revision 2, dated 
December 23, 2010, before the effective date of this AD, you have 
satisfied the in-shop visual inspections required by paragraph 
(h)(3) of this AD.

(l) Definitions

    For the purpose of this AD, a shop visit is defined as 
introduction of an engine into a shop and disassembly sufficient to 
expose the IP compressor module rear face.

(m) Alternative Methods of Compliance (AMOCs)

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

(n) Related Information

    (1) For more information about this AD, contact Frederick Zink, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7779; fax: 781-238-7199; email: 
frederick.zink@faa.gov.
    (2) European Aviation Safety Agency AD 2013-0002, dated January 
4, 2013 also pertains to the subject of this AD.
    (3) 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; Internet: http://www.rolls-royce.com/contact/civil_team.jsp.
    (4) You may view the referenced service information at the FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call 781-238-7125.

[[Page 17303]]

    Issued in Burlington, Massachusetts, on March 13, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-06498 Filed 3-20-13; 8:45 am]
BILLING CODE 4910-13-P