[Federal Register Volume 72, Number 133 (Thursday, July 12, 2007)]
[Rules and Regulations]
[Pages 38002-38004]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-13410]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24325; Directorate Identifier 2006-NE-10-AD; 
Amendment 39-15129; AD 2007-14-07]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-524 and -535 
Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department 
ofTransportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Rolls-Royce plc (RR) RB211-524 and -535 series turbofan 
engines. This AD requires initial and repetitive fluorescent penetrant 
inspections (FPI) of the high pressure (HP) compressor stage 1 and 2 
rotor discs for cracks. This AD results from reports of low-cycle-
fatigue cracks found at overhaul in the interface weld between the HP 
compressor stage 1 and 2 rotor disc. We are issuing this AD to prevent 
uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective August 16, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of August 16, 2007.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 
011-44-1332-242424; fax: 011-44-1332-249936.
    The Docket Operations office is located 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 20590.

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine And Propeller Directorate, 12 New 
England Executive Park; Burlington, MA 01803; telephone (781) 238-7178; 
fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to certain RR RB211-524 and 
-535 series turbofan engines. We published the proposed AD in the 
Federal Register on September 25, 2006 (71 FR 57449). That action 
proposed to require initial and repetitive FPI and

[[Page 38003]]

borescope inspections of the HP compressor stage 1 and 2 rotor discs 
for cracks.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.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 provided in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Unrealistic Compliance Time

    Rolls-Royce plc states that the compliance time of 30 days after 
the effective date of the AD as specified in the proposed AD, is 
unrealistic and would be an unacceptable burden to operators. We agree. 
We changed paragraph (f) to read ``At the next shop visit after the 
effective date of this AD, perform an initial fluorescent penetrant 
inspection (FPI) and borescope inspection of the HP compressor stage 1 
and 2 discs for cracks.''

Borescope Inspection Requirement

    Rolls-Royce plc also states that in their Alert Service Bulletin 
(ASB) No. RB.211-72-AE359, Revision 1, dated November 17, 2005, there 
is no requirement for performing borescope inspections. We do not 
agree. That ASB requires borescope inspections per paragraphs 3A(3) 
through 3A(4)(o)(i). We did not change the AD.

Correction to the Applicability

    Since we issued the proposed AD, we found that we overlooked 
listing an applicable engine model, model RB211-524D4-B-19. We 
investigated and found that no U. S. operators currently operate 
airplanes with this engine model. We added this model number to this AD 
to complete the applicability listing.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 884 RB211-524 and -535 series 
turbofan engines installed on airplanes of U.S. registry. We also 
estimate that it will take about 2 work-hours per engine to perform the 
inspections, and that the average labor rate is $80 per work-hour. 
Based on these figures, we estimate the total cost to U.S. operators of 
performing one inspection on all of the engines, to be $141,440.

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); 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

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration 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 adding the following new airworthiness 
directive:

2007-14-07 Rolls-Royce plc: Amendment 39-15129; Docket No. FAA-2006-
24325; Directorate Identifier 2006-NE-10-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
16, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following Rolls-Royce plc (RR) RB211-
524 and -535 series turbofan engines:

-524B2-19                            -524C2-B-19
-524B-02                             -524D4X-19
-524B3-02                            -524D4X-B-19
-524C2-19                            -524G2-19
-524B4-02                            -524G3-19
-524B4-D-02                          -524H-36
-524D4-19                            -524H2-19
-524D4-39                            -535E4-37
-524B-B-02                           -535E4-B-37
-524B2-B-19                          -535E4-C-37
-524D4-B-19                          -535E4-B-75
-524D4-B-39                          -535C-37
 

    These engines are installed on, but not limited to, Boeing 747, 
757, 767 series, Lockheed L-1011 series, and Tupolev Tu204 
airplanes.

Unsafe Condition

    (d) This AD results from reports of low-cycle fatigue cracks 
found at overhaul in the interface weld between the high pressure 
(HP) compressor stage 1 and 2 rotor discs. We are issuing this AD to 
prevent uncontained engine failure and 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.

Initial and Repetitive Inspections

    (f) At the next shop visit after the effective date of this AD, 
perform an initial fluorescent penetrant inspection (FPI) and 
borescope inspection of the HP compressor stage 1 and 2 discs for 
cracks.

[[Page 38004]]

    (g) Thereafter, at every engine shop visit, perform repetitive 
FPIs and borescope inspections of HP compressor stage 1 and 2 rotor 
discs for cracks.
    (h) Use paragraphs 3.A.(1) through 3.A.(4)(o) of the 
Accomplishment Instructions of RR Alert Service Bulletin (ASB) No. 
RB.211-72-AE359, Revision 1, dated November 17, 2005, to do the 
inspections.
    (i) Accept or reject as necessary, HP compressor stage 1 and 2 
rotor discs using inspection criteria paragraphs 3.A.(5)(a) through 
3.A.(5)(f) of the Accomplishment Instructions of RR ASB No. RB.211-
72-AE359, Revision 1, dated November 17, 2005.

Definition

    (j) For the purpose of this AD, an engine shop visit is defined 
as anytime the HP compressor stage 1 and 2 rotor discs are removed 
from the HP compressor stage 3 disc.

Reporting Requirements

    (k) Within 10 days, report inspection findings of cracks to the 
RR local field service office representative. The Office of 
Management and Budget has approved the reporting requirements 
specified in paragraph 3.A.(6)(b) of the Accomplishment Instructions 
of RR ASB No. RB.211-72-AE359, Revision 1, dated November 17, 2005, 
and assigned OMB control number 2120-0056.

Alternative Methods of Compliance

    (l) 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

    (m) United Kingdom Civil Aviation Authority airworthiness 
directive No. G-2005-0028 R1, dated October 18, 2005, also addresses 
the subject of this AD.

Material Incorporated by Reference

    (n) You must use Rolls-Royce plc Alert Service Bulletin No. 
RB.211-72-AE359, Revision 1, dated November 17, 2005, to perform the 
inspections required by this AD. The Director of the Federal 
Register approved the incorporation by reference of this service 
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; 
telephone: 011-44-1332-242424; fax: 011-44-1332-249936, for a copy 
of this service information. You may review copies at the FAA, New 
England Region, Office of the Regional Counsel, 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/ibr-locations.html.

    Issued in Burlington, Massachusetts, on July 3, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-13410 Filed 7-11-07; 8:45 am]
BILLING CODE 4910-13-P