[Federal Register Volume 71, Number 189 (Friday, September 29, 2006)]
[Proposed Rules]
[Pages 57449-57451]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-16047]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 71, No. 189 / Friday, September 29, 2006 / 
Proposed Rules  

[[Page 57449]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24325; Directorate Identifier 2006-NE-10-AD]
RIN 2120-AA64


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

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Rolls-Royce plc (RR) RB211-524 and -535 series turbofan 
engines. This proposed AD would require initial and repetitive 
fluorescent penetrant inspections (FPI) and borescope inspections of 
the high pressure (HP) compressor stage 1 and 2 rotor discs for cracks. 
This proposed 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 proposing this AD to prevent uncontained engine 
failure and damage to the airplane.

DATES: We must receive any comments on this proposed AD by November 28, 
2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; 
telephone: 011-44-1332-242424; fax: 011-44-1332-249936 for the service 
information identified in this proposed 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; telephone (781) 238-7178; 
fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-24325; 
Directorate Identifier 2006-NE-10-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of the 
DMS Web site, anyone can find and read the comments in any of our 
dockets. This includes 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) or 
you may visit http://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, any comments 
received, and any final disposition in person at the DMS Docket Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is on the plaza 
level of the Department of Transportation Nassif Building at the street 
address stated in ADDRESSES. Comments will be available in the AD 
docket shortly after the DMS receives them.

Discussion

    The Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom, recently notified us that an unsafe 
condition might exist on certain RR RB211-524 and -535 series turbofan 
engines. The CAA advises that during overhaul inspections of HP 
compressor stage 1 and 2 rotors, low-cycle-fatigue cracks were 
identified. The cracks ran in an axial direction in the region of the 
interface weld between the HP compressor stage 1 and 2 rotor discs. If 
allowed to spread, the cracks could result in uncontained engine 
failure and damage to the airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of RR Alert 
Service Bulletin (ASB) No. RB.211-72-AE359, dated November 17, 2005. 
That ASB describes FPI and borescope inspections for cracks in HP 
compressor stage 1 and 2 rotor discs. The CAA classified this ASB as 
mandatory and issued airworthiness directive G-2005-0028 R1, dated 
October 18, 2005, in order to ensure the airworthiness of these engines 
in the United Kingdom.

FAA's Determination and Requirements of the Proposed AD

    These RR RB211-524 and -535 series turbofan engines are 
manufactured in the United Kingdom. They are 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. In keeping with this bilateral 
airworthiness agreement, the CAA kept us informed of the situation 
described above. We have examined the CAA's findings, 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. For this reason, we are proposing this AD, which would 
require starting at the next engine shop visit, initial and repetitive 
FPI and borescope inspections of the HP

[[Page 57450]]

compressor stage 1 and 2 rotor discs for cracks. The proposed AD would 
require you to use the service information described previously to 
perform these actions.

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Costs of Compliance

    We estimate that this proposed AD would affect 884 RB211-524 and -
535 series turbofan engines installed on airplanes of U.S. registry. We 
also estimate that it would take about 2 work-hours per engine to 
perform the proposed 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 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); and
    3. Would 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:


Rolls-Royce plc: Docket No. FAA-2006-24325; Directorate Identifier 
2006-NE-10-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by November 28, 
2006.

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

    These engines are installed on, but not limited to, Boeing 747, 
757, 767, Lockheed L-1011, 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 engine shop visit, but no later than 30 days 
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 rotor discs for cracks.
    (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.

[[Page 57451]]

Related Information

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

    Issued in Burlington, Massachusetts, on September 25, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E6-16047 Filed 9-28-06; 8:45 am]
BILLING CODE 4910-13-P