[Federal Register Volume 71, Number 174 (Friday, September 8, 2006)]
[Rules and Regulations]
[Pages 52988-52990]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-14685]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25513; Directorate Identifier 99-NE-61-AD; 
Amendment 39-14753; AD 2006-18-14]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay 
650-15 and Tay 651-54 Turbofan Engines

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an airworthiness directive (AD) for 
Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 650-15 and Tay 651-54 
turbofan engines. That AD currently establishes cyclic life limits for 
certain part number (P/N) stage 1 high pressure turbine (HPT) discs and 
stage 1 low pressure turbine (LPT) discs operating under certain flight 
plan profiles. This AD requires calculating and re-establishing the 
achieved cyclic life of stage 1 HPT discs, P/N JR32013 or P/N JR33838, 
and stage 1 LPT discs, P/N JR32318A, that have been exposed to 
different flight plan profiles. This AD also requires removing from 
service those stage 1 HPT discs and stage 1 LPT discs operated under 
Tay 650-15 engine flight plan profiles A, B, C, and D, and operated 
under Tay 651-54 engine datum flight profile, at reduced cyclic life 
limits, using a drawdown schedule. This AD results from RRD updating 
their low-cycle-fatigue analysis for stage 1 HPT discs and stage 1 LPT 
discs and reducing their cyclic life limits. We are issuing this AD to 
prevent cracks leading to turbine disc failure, which could result in 
an uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective October 13, 2006. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of October 13, 2006.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, 15872 
Blankenfelde-Mahlow, Germany, telephone 49-0-33-7086-1768; fax 49-0-33-
7086-3356.
    You may examine the AD docket on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

[[Page 52989]]


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: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to RRD Tay 650-15 and Tay 
651-54 turbofan engines. We published the proposed AD in the Federal 
Register on May 4, 2006 (71 FR 26282). That action proposed to require 
calculating and re-establishing the achieved cyclic life of stage 1 HPT 
discs, P/N JR32013 or P/N JR33838, and stage 1 LPT discs, P/N JR32318A, 
that have been exposed to different flight plan profiles. That action 
also proposed to require removing those stage 1 HPT discs and stage 1 
LPT discs at reduced cyclic life limits, using a drawdown schedule.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located 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.

Comments

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

Request for Clarification of Flight Plan Profiles

    RRD requests we clarify that engine flight plan profiles A, B, C, 
and D, apply to Tay 650-15 engines, and that an engine datum flight 
profile applies to Tay 651-54 engines. We agree and clarified the 
profiles in the Summary paragraph of this AD. It now reads ``This AD 
requires calculating and re-establishing the achieved cyclic life of 
stage 1 HPT discs, P/N JR32013 or P/N JR33838, and stage 1 LPT discs, 
P/N JR32318A, that have been exposed to different engine flight plan 
profiles. This AD also requires removing from service those stage 1 HPT 
discs and stage 1 LPT discs operated under Tay 650-15 engine flight 
plan profiles A, B, C, and D, and operated under Tay 651-54 engine 
datum flight profile, at reduced cyclic life limits, using a drawdown 
schedule''. We also clarified the references to the flight plan 
profiles and engine datum flight profile in the compliance section.

Change in Compliance Time

    In the Notice of Proposed Rulemaking, we required initial 
compliance with the proposed rule on or before August 31, 2006. Because 
that date has past, we have changed the initial compliance date 
requirement to start after the effective date of this AD.

Docket Number Change

    We are transferring the docket for this AD to the Docket Management 
System as part of our on-going docket management consolidation efforts. 
The new Docket No. is FAA-2006-25513. The old Docket No. became the 
Directorate Identifier, which is 99-NE-61-AD. This final rule might get 
logged into the DMS docket, ahead of the proposed AD and comments 
received, as we are in the process of sending those items to the DMS.

Conclusion

    We have carefully reviewed the available data, including the 
comment 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 50 Tay 650-15 and Tay 651-54 
turbofan engines installed on airplanes of U.S. registry. We also 
estimate that it will take about one work-hour per engine to calculate 
and re-establish the achieved cyclic life for a disc, and that the 
average labor rate is $80 per work-hour. We estimate that the prorated 
cost of the life reduction per engine will be $15,000. Based on these 
figures, we estimate that if all of the engines required calculating 
and re-establishing achieved cyclic life, the total cost of the AD to 
U.S. operators will be $752,000.

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 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:

 2006-18-14 Rolls-Royce Deutschland Ltd & Co KG (formerly 
Rolls-Royce plc): Amendment 39-14753. Docket No. FAA-2006-25513; 
Directorate Identifier 99-NE-61-AD.

[[Page 52990]]

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
13, 2006.

Affected ADs

    (b) This AD supersedes AD 2000-08-01, Amendment 39-11687.

Applicability

    (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) 
Tay 650-15 and Tay 651-54 turbofan engines with stage 1 high 
pressure turbine (HPT) discs, part number (P/N) JR32013 or P/N 
JR33838, and stage 1 low pressure turbine (LPT) discs, P/N JR32318A, 
installed. These engines are installed on, but not limited to, 
Fokker Model F.28 Mark 0100, and Boeing 727-100 series airplanes 
modified in accordance with Supplemental Type Certificate (STC) 
SA8472SW (727-QF).

Unsafe Condition

    (d) This AD results from RRD updating their low-cycle-fatigue 
analysis for stage 1 HPT discs and stage 1 LPT discs and reducing 
their cyclic life limits. We are issuing this AD to prevent cracks 
leading to turbine disc failure, which could result in an 
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.
    (f) Information on the referenced Tay 650-15 engine flight plan 
profiles A, B, C, and D and Tay 651-54 engine datum flight profile, 
can be found in RRD Tay Engine Manual, Section 70-01-10.

Calculating and Re-Establishing Within 30 Days, the Achieved Cyclic 
Life of a Stage 1 HPT Disc or Stage 1 LPT Disc Previously Exposed to 
Different Flight Plan Profiles

    (g) If a stage 1 HPT disc or stage 1 LPT disc was previously 
exposed to flight plan profile(s) different than the currently 
operated flight plan:
    (1) You must calculate and re-establish the achieved cyclic life 
for that disc, within 30 days after the effective date of this AD.
    (2) Use paragraphs 3.A. through 3.D.(2)(c) of Accomplishment 
Instructions of RRD Alert Service Bulletin (ASB) No. Tay-72-A1676, 
Revision 1, dated August 16, 2005, to calculate and re-establish the 
achieved cyclic life.

After an Engine Flight Plan Profile Changeover, Calculating and Re-
Establishing Within 30 Days, the Achieved Cyclic Life of Stage 1 HPT 
Discs and Stage 1 LPT Discs

    (h) After an engine has a flight plan profile changeover:
    (1) You must calculate and re-establish the achieved cyclic life 
for the stage 1 HPT disc and stage 1 LPT disc, within 30 days after 
the flight plan changeover.
    (2) Use paragraphs 3.A. through 3.D.(2)(c) of Accomplishment 
Instructions of RRD ASB No. Tay-72-A1676, Revision 1, dated August 
16, 2005, to calculate and re-establish the achieved cyclic life.

Removal of Stage 1 HPT Discs and Stage 1 LPT Discs From Service Tay 
650-15 Engine Flight Plan Profile A

    (i) Remove from service Tay 650-15 stage 1 HPT discs and stage 1 
LPT discs operated under flight plan profile A, before accumulating 
23,000 cycles-since-new (CSN), and replace with serviceable parts.

Tay 650-15 Engine Flight Plan Profile B

    (j) Remove from service Tay 650-15 stage 1 HPT discs operated 
under flight plan profile B and replace with serviceable parts:
    (1) On or before July 31, 2007, before accumulating 21,000 CSN; 
and
    (2) After July 31, 2007, before accumulating 20,000 CSN.
    (k) Remove from service Tay 650-15 stage 1 LPT discs operated 
under flight plan profile B, before accumulating 21,000 CSN, and 
replace with serviceable parts.

Tay 650-15 Engine Flight Plan Profile C

    (l) Remove from service Tay 650-15 stage 1 HPT discs operated 
under flight plan profile C and replace with serviceable parts:
    (1) After the effective date of this AD, before accumulating 
15,800 CSN; and
    (2) After July 31, 2007, before accumulating 14,700 CSN.
    (m) Remove from service Tay 650-15 stage 1 LPT discs operated 
under flight plan profile C, before accumulating 18,000 CSN, and 
replace with serviceable parts.

Tay 650-15 Engine Flight Plan Profile D

    (n) Remove from service Tay 650-15 stage 1 HPT discs operated 
under flight plan profile D and replace with serviceable parts after 
the effective date of this AD, before accumulating 11,000 CSN.
    (o) Remove from service Tay 650-15 stage 1 LPT discs operated 
under flight plan profile D, before accumulating 14,250 CSN, and 
replace with serviceable parts.

Tay 651-54 Engine Datum Flight Profile

    (p) Remove from service Tay 651-54 stage 1 HPT discs operated 
under the engine datum flight profile, and replace with serviceable 
parts after the effective date of this AD, before accumulating 
12,600 CSN.
    (q) Remove from service Tay 651-54 stage 1 LPT discs before 
accumulating 20,000 CSN and replace with serviceable parts.

Alternative Methods of Compliance

    (r) The Manager, Engine Certification Office, FAA, 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

    (s) Luftfahrt-Bundesamt airworthiness directive No. D-2005-
252R1, dated August 31, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (t) You must use Rolls-Royce Deutschland Ltd & Co KG Alert 
Service Bulletin No. Tay-72-A1676, Revision 1, dated August 16, 
2005, to perform the actions 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. You can get a copy from Rolls-Royce Deutschland Ltd & Co KG, 
Eschenweg 11, 15872 Blankenfelde-Mahlow, Germany, telephone 49-0-33-
7086-1768; fax 49-0-33-7086-3356. 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 August 30, 2006.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-14685 Filed 9-7-06; 8:45 am]
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