Document ID: FAA-2009-0994-0010
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce plc RB211-535 Series Turbofan Engine
Posted Date: 2012-01-31T05:00Z

[Federal Register Volume 77, Number 20 (Tuesday, January 31, 2012)]
[Rules and Regulations]
[Pages 4648-4650]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-1954]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0994; Directorate Identifier 2009-NE-39-AD; 
Amendment 39-16934; AD 2012-02-11]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc (RR) RB211-535 Series 
Turbofan Engine

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for

[[Page 4649]]

all RR RB211-535E4-37, -535E4-B-37, -535E4-B-75, and -535E4-C-37 
turbofan engines. That AD currently requires performing initial and 
repetitive visual and fluorescent penetrant inspections (FPI) of the 
low-pressure (LP) turbine stage 1, 2, and 3 discs to detect cracks in 
the discs. This new AD continues to require those inspections and 
changes the definition of a shop visit to be less restrictive. This AD 
was prompted by our finding that the definition of shop visit in the 
existing AD was too restrictive. We are issuing this AD to revise the 
definition of shop visit and to detect cracks in the LP turbine stage 
1, 2, and 3 discs, which could result in an uncontained release of LP 
turbine blades and damage to the airplane.

DATES: This AD is effective March 6, 2012.

ADDRESSES: For service information identified in this AD, contact 
Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; phone: 
011 44 1332 242424, fax: 011 44 1332 249936; or email: http://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 01803. 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 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, 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 notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-11-08, amendment 39-16707 (76 FR 30529, 
May 26, 2011). That AD applies to the specified products. The NPRM was 
published in the Federal Register on October 25, 2011 (76 FR 65997). 
That NPRM proposed to continue to require performing an initial FPI on 
the LP turbine stage 1, 2, and 3 discs at the next engine shop 
inspection after the effective date of that AD. That NPRM also 
continued to require repetitive inspections at each engine shop visit 
after accumulating 1,500 cycles since last inspection of the LP turbine 
stage 1, 2, and 3 discs. That NPRM also proposed to change the 
definition of a shop visit to be less restrictive.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (76 FR 65997, October 25, 
2011) or on the determination of the cost to the public.

Conclusion

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

Costs of Compliance

    We estimate that this AD affects about 588 RB211-535 series 
turbofan engines installed on airplanes of U.S. registry. We also 
estimate that it will take about 30 work-hours per product to comply 
with this AD. The average labor rate is $85 per work-hour. No parts are 
required. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $1,499,400.

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 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) 
2011-11-08, Amendment 39-16707 (76 FR 30529, May 26, 2011, and adding 
the following new AD:

2012-02-11 Rolls-Royce plc: Amendment 39-16934; Docket No. FAA-2009-
0994; Directorate Identifier 2009-NE-39-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective March 6, 2012.

(b) Affected ADs

    This AD supersedes AD 2011-11-08, Amendment 39-16707 (76 FR 
30529, May 26, 2011).

(c) Applicability

    This AD applies to Rolls-Royce plc RB211-535E4-37, -535E4-B-37, 
-535E4-B-75, and -535E4-C-37 turbofan engines.

(d) Unsafe Condition

    This AD was prompted by our determination that the definition of 
``shop visit'' in the existing AD is too restrictive, in

[[Page 4650]]

that it would require operators to inspect more often than required 
to ensure safety. We are issuing this AD to revise the definition of 
shop visit and to detect cracks in the low-pressure (LP) turbine 
stage 1, 2, and 3 discs, which could result in an uncontained 
release of LP turbine blades and damage to the airplane.

(e) Compliance

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

(1) Initial Inspection Requirements

    At the next engine shop visit after the effective date of this 
AD, perform a visual and a fluorescent penetrant inspection of the 
LP turbine stage 1, 2, and 3 discs.

(2) Repeat Inspection Requirements

    At each engine shop visit after accumulating 1,500 cycles since 
the last inspection of the LP turbine stage 1, 2 and 3 discs, repeat 
the inspections specified in paragraph (e)(1) of this AD.

(3) Remove Cracked Discs

    If you find cracks, remove the disc from service.

(f) Definitions

    For the purpose of this AD, an ``engine shop visit'' is 
induction of an engine into the shop for any purpose where:
    (1) All the blades are removed from the high-pressure (HP) 
compressor discs and the HP turbine disc, or
    (2) All the blades are removed from the intermediate pressure 
turbine disc.

(g) Alternative Methods of Compliance (AMOCs)

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

(h) Related Information

    (1) 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, for more information 
about this AD.
    (2) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2009-0244, dated November 9, 2009, and Rolls-Royce plc 
Alert Service Bulletin No. RB.211-72-AG272 for related information. 
Contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United 
Kingdom; phone: 011 44 1332 242424, fax: 011 44 1332 249936; or 
email: http://www.rollsroyce.com/contact/civil_team.jsp, for a copy 
of this service information or download the publication from https://www.aeromanager.com.

(i) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on January 25, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-1954 Filed 1-30-12; 8:45 am]
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