[Federal Register Volume 71, Number 123 (Tuesday, June 27, 2006)]
[Proposed Rules]
[Pages 36493-36495]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-10087]


 ========================================================================
 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. 123 / Tuesday, June 27, 2006 / 
Proposed Rules  

[[Page 36493]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24777; Directorate Identifier 2006-NE-19-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay 
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 Series Turbofan Engines

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8, Tay 620-15, 
Tay 650-15, and Tay 651-54 series turbofan engines, with certain low 
pressure (LP) compressor modules installed. This proposed AD would 
require an ultrasonic inspection (UI) of LP compressor fan blades for 
cracks, within 30 days after the effective date of the proposed AD on 
certain serial number (SN) Tay 650-15 engines. This proposed AD would 
also require repetitive UIs of LP compressor fan blades on all engines. 
This proposed AD would also require, for Tay 650-15 and Tay 651-54 
engines, UIs of LP compressor fan blades whenever the blade set is 
removed from one engine and installed on a different engine. This 
proposed AD results from a report that a set of LP compressor fan 
blades failed before reaching the LP compressor fan blade full 
published life limit. We are proposing this AD to prevent LP compressor 
fan blades from failing due to blade root cracks, leading to 
uncontained engine failure and damage to the airplane.

DATES: We must receive any comments on this proposed AD by August 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 20590-001.
     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 Deutschland Ltd & Co KG, Eschenweg 11, D-15827 
Dahlewitz, Germany; telephone 49 (0) 33-7086-1768; fax 49 (0) 33-7086-
3356 for the service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; telephone (781) 238-7747; 
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-2006-24777; 
Directorate Identifier 2006-NE-19-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, including 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 Luftfahrt-Bundesamt (LBA), which is the airworthiness authority 
for Germany, notified us that an unsafe condition may exist on RRD Tay 
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan engines. 
The LBA advises that a Tay 650 LP compressor fan blade set failed 
before reaching the LP compressor fan blade full published life limit. 
The set of fan blades accumulated 14,166 cycles-in-service. An 
investigation revealed that the set of LP compressor fan blades failed 
due to cracking in the blade root. Rolls-Royce initially introduced a 
fluorescent penetrant inspection in the engine manual to detect 
cracking in the blade root. However, further research indicates that 
repetitive UIs are most effective in detecting blade root cracks.

Relevant Service Information

    We reviewed and approved RRD Service Bulletin (SB) No. TAY-72-1591, 
dated May 8, 2003, that describes procedures for UI of LP compressor 
fan blades for cracks on certain SNs of Tay 650-15 engines with certain 
LP compressor modules. These engines may have not yet had UI of LP 
compressor fan blades. We have also reviewed and approved the technical 
contents of RRD SB No. TAY-72-1442, Revision 3, dated November 26, 
2003, that describes procedures for UIs of LP compressor fan blades for 
all RRD Tay

[[Page 36494]]

611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan engines 
with certain LP compressor modules. The LBA classified these SBs as 
mandatory and issued airworthiness directive D-1998-055R3, dated 
December 15, 2003, in order to ensure the airworthiness of these RRD 
Tay 611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan 
engines in Germany. EASA has approved the LBA AD under approval No. 
1869 on December 15, 2003.

FAA's Determination and Requirements of the Proposed AD

    These RRD Tay 611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series 
turbofan engines are manufactured in Germany. 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 LBA kept us informed of the 
situation described above. We have examined the LBA'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:
     UI of LP compressor fan blades for cracks, within 30 days 
after the effective date of the proposed AD on certain serial number 
(SN) Tay 650-15 engines.
     Repetitive UIs of LP compressor fan blades on all engines.
     For Tay 650-15 and Tay 651-54 engines, UIs of LP 
compressor fan blades whenever the blade set is removed from one engine 
and installed on a different engine.
     Removal of the complete LP compressor fan blade set and 
the LP compressor fan disc from service, if any LP compressor fan blade 
is cracked.
    The proposed AD would require you to use the service information 
described previously to perform these actions.

Costs of Compliance

    We estimate that this proposed AD would affect about 1,000 RRD Tay 
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 4 work-hours per engine to perform a proposed inspection, 
and that the average labor rate is $80 per work-hour. Required parts 
would cost about $95,000 per LP compressor fan disk and $140,000 per 
set of LP compressor fan blades. We estimate that 5 percent or 50 
engines would require replacing the LP compressor fan disc and LP 
compressor fan blade set. Based on these figures, we estimate the total 
cost of the proposed AD to U.S. operators to be $11,750,000.

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, ``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 Deutschland Ltd & Co KG (formerly Rolls-Royce plc): 
Docket No. FAA-2006-24777; Directorate Identifier 2006-NE-19-AD.

Comments Due Date

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

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) 
Tay 611-8 and Tay 620-15 turbofan engines with low pressure (LP) 
compressor module part number (P/N) MO1100AA or P/N MO1100AB 
installed, and Tay 650-15 and Tay 651-54 turbofan engines with LP 
compressor module P/N MO1300AA or P/N MO1300AB installed. These 
engines are installed on, but not limited to, Fokker F.28 Mark 0070 
and 0100 airplanes, Supplemental Type Certificate No. SA842SW, 
Boeing 727 airplanes, and Gulfstream G-IV airplanes.

Unsafe Condition

    (d) This AD results from a report that a set of LP compressor 
fan blades failed before reaching the LP compressor fan blade full 
published life limit. We are issuing this AD to prevent LP 
compressor fan blades from failing due to blade root cracks, leading 
to 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.

Ultrasonic Inspection (UI) of LP Compressor Fan Blades for Certain Tay 
650-15 Engines That Have Not Yet Had UI of the LP Compressor Fan Blades

    (f) For Tay 650-15 engines, serial numbers 17201, 17202, 17226, 
17253, 17341, 17356, 17428, 17450, 17457, 17458, 17497, 17530, 
17622, 17643, 17655, 17678, 17709, 17751, 17755, 17805, and 17806 
that have not yet had UI of the LP compressor fan blades:
    (1) Within 30 days after the effective date of this AD, perform 
UI of the LP compressor fan blades for cracks.
    (2) Use Part 1 of RRD Service Bulletin (SB) No. TAY-72-1591, 
dated May 8, 2003, to do the inspection.

[[Page 36495]]

UI of LP Compressor Fan Blades Being Installed in a Different Engine; 
Tay 650-15 and Tay 651-54 Engines

    (g) For Tay 650-15 and Tay 651-54 engines, whenever LP 
compressor fan blades are removed and are being installed in a 
different engine:
    (1) Perform UI of the LP compressor fan blades for cracks.
    (2) Use Part 1 of RRD SB No. TAY-72-1442, Revision 3, dated 
November 26, 2003, to do the inspection.

UI of LP Compressor Fan Blades for All Tay Engines

    (h) Perform UI of the LP compressor fan blades for cracks, using 
Part 2 of RRD SB No. TAY-72-1442, Revision 3, dated November 26, 
2003, at the following:
    (1) For Tay 650-15 and Tay 651-54 engines, at every engine shop 
visit for any reason or before reaching every 4,000 flight hours-
since-last-fan-blade UI, whichever occurs first.
    (2) For Tay 620-15 engines, before reaching every 4,000 flight 
hours but no later than every 10 years since-last-fan-blade UI, 
whichever occurs first.
    (3) For Tay 611-8 engines, before reaching every 8,000 flight 
hours but no later than every 10 years since-last-fan-blade UI, 
whichever occurs first.

LP Compressor Fan Blades That Are Cracked

    (i) If any LP compressor fan blade is cracked, then remove the 
complete LP compressor fan blade set and the LP compressor fan disc 
from service.

Alternative Methods of Compliance

    (j) 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

    (k) Luftfahrt-Bundesamt airworthiness directive D-1998-055R3, 
dated December 15, 2003, which was approved by EASA under approval 
No. 1869 on December 15, 2003, also addresses the subject of this 
AD.

    Issued in Burlington, Massachusetts, on June 21, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E6-10087 Filed 6-26-06; 8:45 am]
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