[Federal Register: January 7, 2008 (Volume 73, Number 4)]
[Rules and Regulations]
[Page 1048-1052]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ja08-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27811; Directorate Identifier 2004-NE-11-AD;
Amendment 39-15321; AD 2007-26-19]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay
611-8, Tay 611-8C, Tay 620-15, 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 existing airworthiness directive
(AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8, Tay 620-
15, Tay 650-15, and Tay 651-54 turbofan engines. That AD currently
requires initial and repetitive visual inspections of all ice-impact
panels and fillers in the low pressure (LP) compressor case for certain
conditions and replacing, as necessary, any or all panels. This AD
requires the same actions, provides terminating action to those
repetitive actions, and adds the Tay 611-8C turbofan engine to the
applicability. This AD results from RRD introducing new LP compressor
case ice-impact panels with additional retention features to these Tay
turbofan engines. We are issuing this AD to prevent release of ice-
impact panels due to improper bonding that can result in loss of thrust
in both engines.
DATES: This AD becomes effective February 11, 2008. The Director of the
Federal Register previously approved the incorporation by reference of
certain publications listed in the regulations as of January 21, 2005
(70 FR 1172, January 6, 2005). The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of February 11, 2008.
ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827
Dahlewitz, Germany; telephone 49 (0) 33-7086-1768; fax 49 (0) 33-7086-
3356.
The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building, Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
Jason.yang@faa.gov; telephone (781) 238-7747; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2004-26-10, Amendment 39-13922 (70 FR 1172, January 6,
2005), with a proposed AD. The proposed AD applies to RRD Tay 611-8,
Tay 620-15, Tay 650-15, and Tay 651-54 turbofan engines. We published
the proposed AD in the Federal Register on July 6, 2007 (72 FR 36916).
That action proposed to require initial and repetitive visual
inspections of all ice-impact panels and fillers in the LP compressor
case for certain conditions and replacing, as necessary, any or all
panels. That action also proposed to provide terminating action to
those repetitive actions, and to add the Tay 611-8C turbofan engine to
the applicability.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.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.
Request for Compliance Time Extension
Two commenters, Rolls-Royce North America Inc. and Gulfstream,
request that we extend the Tay 611-8 and 611-8C engine compliance time
four more years, from December 31, 2011, to
[[Page 1049]]
December 31, 2015, to address new engines having the 6-ice-impact panel
configuration. The commenters state that so far, 12 engines have
incorporated the ice-impact panel retention features, and those engines
displayed strong bonding of the ice-impact panels before the panels
were removed. The commenters are concerned with potential shop capacity
problems, and extra cost if a special in-service repair is necessary.
We do not agree. We coordinated with Rolls-Royce Deutschland Ltd &
Co KG in reviewing the request. Rolls-Royce Deutschland Ltd & Co KG re-
states that the rework of the LP compressor case and installation of
new LP compressor case ice-impact panels with additional retention
features must be done before December 31, 2011 in accordance with Alert
Service Bulletin No. TAY-72-A1650, dated November 2, 2005.
Reference Errors in the Proposed AD
Rolls-Royce Deutschland Ltd & Co KG requests that we correct some
reference errors appearing in the proposed AD, as follows:
In paragraphs (f)(2) and (f)(3), change ``RRD SB No. TAY-
72-1638, Revision 2, dated September 21, 2004'', to ``RRD SB No. TAY-
72-1638, Revision 3, dated February 25, 2005.''
In paragraphs (h)(2) and (i)(2), change ``RRD SB No. TAY-
72-1638, Revision 2, dated September 21, 2004'', to ``RRD SB No. TAY-
72-1639, Revision 2, dated September 21, 2004.''
In paragraph (h)(3), change ``every 1,000 CSLI'' to
``every 1,000 operating hours.''
In paragraph (i)(1), change ``every 3,000 CSLI'' to
``every 3,000 operating hours.''
We agree and made these corrections to the AD.
Corrections Not Carried Forward
Rolls-Royce Deutschland Ltd & Co KG also requests that we review
the proposed AD for missing corrections that were made to AD 2004-26-
10, but not carried forward.
We agree. The corrections were inadvertently left out of the
proposed AD. We have made those corrections to this AD, which
throughout the compliance section changed ``paragraph 3.E.'' to
``paragraphs 3.C. through 3.E.''
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 about 1,085 engines installed
on airplanes of U.S. registry. We also estimate that it will take about
2.5 work-hours per engine to perform an inspection, and about 12 work-
hours to perform a repair. The average labor rate is $80 per work-hour.
Required terminating action parts will cost about $7,500 per engine.
Based on these figures, for the AD, we estimate:
The cost of one inspection to the U.S. fleet to be
$217,000.
The cost of a repair to the U.S fleet to be $1,041,600.
The cost of parts to the U.S. fleet for terminating action
to be $8,137,500.
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 removing Amendment 39-13922 (70 FR
1172, January 6, 2005), and by adding a new airworthiness directive,
Amendment 39-15321, to read as follows:
2007-26-19 Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce
plc): Amendment 39-15321. Docket No. FAA-2007-27811; Directorate
Identifier 2004-NE-11-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective February
11, 2008.
Affected ADs
(b) This AD supersedes AD 2004-26-10, Amendment 39-13922.
Applicability
(c) This AD applies to:
(1) Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8, Tay
620-15, Tay 650-15, and Tay 651-54 turbofan engines that have one or
more ice-impact panels installed in the low pressure (LP) compressor
case that conform to the (RRD) Service Bulletin (SB) No. TAY-72-1326
standard.
(2) RRD Tay 611-8C turbofan engines with serial numbers (SN)
below SN 85078.
(3) The turbofan engines listed in paragraph (c) of this AD are
installed on, but not limited to, Fokker F.28 Mk.0070 and Mk.0100
series airplanes, Gulfstream Aerospace G-IV and G-IV-X series
airplanes, and Boeing Company 727-100 series airplanes modified in
accordance with Supplemental Type Certificate SA8472SW (727-QF).
Unsafe Condition
(d) This AD results from RRD introducing new LP compressor case
ice-impact panels with additional retention features, to these Tay
turbofan engines. We are issuing this AD to prevent release of ice-
impact panels due to improper bonding that can result in loss of
thrust in both engines.
[[Page 1050]]
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.
Inspecting Ice-Impact Panels in Tay 620-15, Tay 650-15, and Tay 651-54
Engines
(f) For airplanes that have any Tay 620-15, Tay 650-15, or Tay
651-54 engines with ice-impact panels incorporated by the RR SB No.
TAY-72-1326 standard, and not all panels were repaired using
polysulfide bonding material by RR repair scheme TV5451R, HRS3491,
HRS3615, HRS3648, or HRS3649, do the following:
(1) Before further flight, rework all six ice-impact panels
using repair scheme HRS3648 or HRS3649 on at least one of the
affected engines.
(2) Before further flight, inspect the ice-impact panels and the
surrounding fillers on the engine not reworked. Use paragraphs 3.C.
through 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1638, Revision 2, dated September 21, 2004, or SB No. TAY-72-
1638, Revision 3, dated February 25, 2005, and the inspection
disposition criteria in Table 1 of this AD.
Table 1.--Inspection Disposition Criteria
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If: Then:
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(i) Any movement or rocking motion of Before further flight, replace
LP compressor ice-impact panel, or any all panels using repair scheme
movement of the front edge of ice- HRS3648 or HRS3649.
impact panel.
(ii) Reappearing signs of moisture on Before further flight, replace
the ice-impact panel or the all panels using repair scheme
surrounding filler. HRS3648 or HRS3649.
(iii) Any dents or impact damage on the Before further flight, replace
ice-impact panel that is greater than the damaged panel using repair
3.1 square inch in total. scheme HRS3648 or HRS3649.
(iv) Any dents or impact damage on the Within 5 flight cycles or 5
ice-impact panel that is between 1.55 flight hours, whichever occurs
square inch and 3.1 square inch in first, replace the damaged
total. panel using repair scheme
HRS3648 or HRS3649.
(v) Any dents or impact damage on the Within 50 flight cycles or 50
ice-impact panel that is less than flight hours, whichever occurs
1.55 square inch in total. first, replace the damaged
panel using repair scheme
HRS3648 or HRS3649.
(vi) Any crack appears on the ice- Within 50 flight cycles or 50
impact panel and there is visible flight hours, whichever occurs
distortion of the airwashed surface. first, replace the damaged
panel using repair scheme
HRS3648 or HRS3649.
(vii) Any crack appears on the ice- Within 150 flight cycles or 150
impact panel and there is no visible flight hours, whichever occurs
distortion of the airwashed surface. first, replace the damaged
panel using repair scheme
HRS3648 or HRS3649.
(viii) Delamination or peeling of the Before further flight, replace
compound layers of the airwashed the damaged panel using repair
surface and the penetrated area is scheme HRS3648 or HRS3649.
greater than 3.1 square inch in total.
(ix) Delamination or peeling of the Within 5 flight cycles or 5
compound layers of the airwashed flight hours, whichever occurs
surface and the penetrated area is first, replace the damaged
between 1.55 square inch and 3.1 panel using repair scheme
square inch in total. HRS3648 or HRS3649.
(x) Delamination or peeling of the Within 50 flight cycles or 50
compound layers of the airwashed flight hours, whichever occurs
surface and the penetrated area is first, replace the damaged
less than 1.55 square inch in total. panel using repair scheme
HRS3648 or HRS3649.
(xi) Delamination or peeling of the Within 150 flight cycles or 150
compound layers but the airwashed flight hours, whichever occurs
surface is not penetrated. first, repair the damaged
panel using repair scheme
HRS3630.
(xii) Missing filler surrounding the LP Before further flight, repair
compressor case. the damaged filler using
repair scheme HRS3630.
(xiii) Damage to the filler surrounding Within 25 flight cycles or 25
the LP compressor case such as flight hours, whichever occurs
chipped, cracked, or missing material. first, repair damaged filler
using repair scheme HRS 3630.
------------------------------------------------------------------------
(3) Re-inspect all ice-impact panels within every 500 cycles-
since-last-inspection (CSLI) or two months since-last-inspection,
whichever occurs first. Use paragraphs 3.C. through 3.E. of the
Accomplishment Instructions of RRD SB No. TAY-72-1638, Revision 2,
dated September 21, 2004, or SB No. TAY-72-1638, Revision 3, dated
February 25, 2005, and the inspection disposition criteria in Table
1 of this AD.
Repetitive Inspections for Tay 620-15, Tay 650-15, and Tay 651-54
Engines With All Ice-Impact Panels Repaired by Polysulfide Bonding
Material
(g) For Tay 620-15, Tay 650-15, and Tay 651-54 engines with ice-
impact panels incorporated by the RRD SB No. TAY-72-1326 standard,
and all panels were repaired using polysulfide bonding material by
RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648 or HRS3649, do
the following:
(1) Re-inspect within every 1,500 CSLI, for the condition of the
ice-impact panels and the surrounding fillers.
(2) Use paragraphs 3.C. through 3.E. of the Accomplishment
Instructions of RRD SB No. TAY-72-1638, Revision 2, dated September
21, 2004 or SB No. TAY-72-1638, Revision 3, dated February 25, 2005,
and the inspection disposition criteria in Table 1 of this AD.
Inspecting Ice-Impact Panels in Tay 611-8 Engines
(h) For airplanes that have any Tay 611-8 engines with ice-
impact panels incorporated by the RR SB No. TAY-72-1326 standard,
and RR repair scheme HRS3491 or HRS3615 was done with two pack epoxy
(Omat 8/52) on one or more of the six ice-impact panels, do the
following:
(1) Before further flight, rework all six ice-impact panels
using repair scheme HRS3648 or HRS3649 on at least one of the
affected engines.
(2) Before further flight, inspect the ice-impact panels and the
surrounding fillers on the engine not reworked. Use paragraphs 3.C.
through 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1639, Revision 2, dated September 21, 2004 and the inspection
disposition criteria in Table 1 of this AD.
(3) Re-inspect the ice-impact panels within every 1,000
operating hours or six months since-last-inspection, whichever
occurs first. Use paragraphs 3.C. through 3.E. of the Accomplishment
Instructions of RRD SB No. TAY-72-1639, Revision 2, dated September
21, 2004, and the inspection disposition criteria in Table 1 of this
AD.
Repetitive Inspections for Tay 611-8 Engines With All Ice-Impact Panels
Repaired by Polysulfide Bonding Material or Introduced Since New
Production
(i) For Tay 611-8 engines with ice-impact panels incorporated by
the RRD SB No. TAY-72-1326 standard and all panels were repaired
using polysulfide bonding material by RR repair scheme TV5451R,
HRS3491, HRS3615, HRS3648 or HRS3649, or panels were introduced
since new production, do the following:
(1) Re-inspect within every 3,000 hours-since-last-inspection,
for the condition of the ice-impact panels and the surrounding
fillers.
(2) Use paragraphs 3.C. through 3.E. of the Accomplishment
Instructions of RRD SB No. TAY-72-1639, Revision 2, dated September
21, 2004, and the inspection disposition criteria in Table 1 of this
AD.
[[Page 1051]]
Installing Tay 620-15, Tay 650-15, or Tay 651-54 Engines That Are Not
Inspected
(j) After the effective date of this AD, do not install any Tay
620-15, Tay 650-15, or Tay 651-54 engines with ice-impact panels if:
(1) Those ice-impact panels incorporate the RR SB No. TAY-72-
1326 standard; and
(2) Ice-impact panels were repaired using RR repair scheme
TV5451R, HRS3491, or HRS3615 and bonding material other than
polysulfide; unless
(3) The panels and the surrounding fillers are inspected for
condition using 3.B. through 3.D.(3) (in-service) or 3.K.(1) through
3.(M)(3) (at overhaul or shop visit) of the Accomplishment
Instructions of RRD SB No. TAY-72-1638, Revision 2, dated September
21, 2004, or SB No. TAY-72-1638, Revision 3, dated February 25,
2005.
(k) Perform repetitive inspections as specified in paragraph (g)
of this AD.
Installing Tay 611-8 Engines That Are Not Inspected
(l) After the effective date of this AD, do not install any Tay
611-8 engine with ice-impact panels if:
(1) Those ice-impact panels incorporate the RR SB No. TAY-72-
1326 standard; and
(2) Ice-impact panels were repaired using RR repair scheme
TV5451R, HRS3491, or HRS3615 and bonding material other than
polysulfide, unless
(3) The panels and the surrounding fillers are inspected for
condition using 3.B. through 3.D.(2) (in-service) or 3.K.(1) through
3.M.(3) (at overhaul or shop visit) of the Accomplishment
Instructions of RRD SB No. TAY-72-1639, Revision 2, dated September
21, 2004.
(m) Perform repetitive inspections as specified in paragraph (i)
of this AD.
Mandatory Terminating Action
(n) No later than December 31, 2011, as mandatory terminating
action to the repetitive visual inspections or rework required by
paragraphs (f), (g), (h), (i), (j), (k), (l), and (m) of this AD, do
the following:
(1) Rework the LP compressor case and install new LP compressor
case ice-impact panels with additional retention features, at the
next shop visit requiring the removal of any module, except when the
work scope requires only the removal of the high speed gearbox
module.
(2) For Tay 620-15, Tay 650-15, and Tay 651-54 turbofan engines,
do the rework and installation using the Accomplishment Instructions
of RRD Alert SB No. TAY-72-A1643, Revision 1, dated November 2,
2005.
(3) For Tay 611-8 turbofan engines, do the rework and
installation using the Accomplishment Instructions of RRD Alert SB
No. TAY-72-A1650, dated November 2, 2005.
Tay 611-8C Turbofan Engines
(o) For Tay 611-8C turbofan engines, no later than December 31,
2011, do the following:
(1) Rework the LP compressor case and install new LP compressor
case ice-impact panels with additional retention features, at the
next shop visit after the effective date of this AD, requiring the
removal of any module, except when the work scope requires only the
removal of the high speed gearbox module.
(2) Do the rework and installation using the Accomplishment
Instructions of RRD Alert SB No. TAY-72-A1650, dated November 2,
2005.
Alternative Methods of Compliance
(p) 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
(q) German AD D2004-313R5, dated November 15, 2005, also
addresses the subject of this AD.
(r) Contact Jason Yang, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: Jason.yang@faa.gov;
telephone (781) 238-7747; fax (781) 238-7199, for more information
about this AD.
Material Incorporated by Reference
(s) You must use the service information specified in Table 2 of
this AD to perform the inspections and rework required by this AD.
Except for Service Bulletin No. TAY-72-1638, Revision 3, Alert
Service Bulletin No. TAY-72-A1643, Revision 1, and Alert Service
Bulletin No. TAY-72-A1650, the Director of the Federal Register
previously approved the incorporation by reference of the Rolls-
Royce Deutschland Ltd & Co KG service information listed in Table 2
of this AD as of January 21, 2005 (70 FR 1172, January 6, 2005). The
Director of the Federal Register approved the incorporation by
reference of Service Bulletin No. TAY-72-1638, Revision 3, dated
February 25, 2005, Alert Service Bulletin No. TAY-72-A1643, Revision
1, dated November 2, 2005, and Alert Service Bulletin No. TAY-72-
A1650, dated November 2, 2005, in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. 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 a copy of this service
information. You may review copies at the FAA, New England Region,
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.
Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service information No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
SB No. TAY-72-1638................ ALL.................. 2................... September 21, 2004.
Total Pages: 35
SB No. TAY-72-1638................ ALL.................. 3................... February 25, 2005.
Total Pages: 35
SB No. TAY-72-1639................ ALL.................. 2................... September 21, 2004.
Total Pages: 28
Alert SB No. TAY-72-A1643......... ALL.................. 1................... November 2, 2005.
Total Pages: 13
Alert SB No. TAY-72-A1643 Appendix ALL.................. 1................... November 2, 2005.
1.
Total Pages: 43
Alert SB No. TAY-72-A1650......... ALL.................. Original............ November 2, 2005.
Total Pages: 11
Alert SB No. TAY-72-A1650 Appendix ALL.................. Original............ November 2, 2005.
1.
Total Pages: 45
Repair Scheme No. HRS3648 Front ALL.................. 2................... January 28, 2004.
Sheet.
Total Pages: 1
Repair Scheme No. HRS3648 History ALL.................. 2................... January 28, 2004.
Sheet.
Total Pages: 3
Repair Scheme No. HRS3648......... ALL.................. 2................... January 27, 2004.
Total Pages: 30
Repair Scheme No. HRS3649 Front ALL.................. 2................... September 1, 2004.
Sheet.
Total Pages: 1
Repair Scheme No. HRS3649 History ALL.................. 2................... September 7, 2004.
Sheet.
[[Page 1052]]
Total Pages: 3
Repair Scheme No. HRS3649......... ALL.................. 2................... June 17, 2004.
Total Pages: 24
----------------------------------------------------------------------------------------------------------------
Issued in Burlington, Massachusetts, on December 21, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-25497 Filed 1-4-08; 8:45 am]
BILLING CODE 4910-13-P