[Federal Register: January 6, 2005 (Volume 70, Number 4)]
[Rules and Regulations]
[Page 1172-1176]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06ja05-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004-NE-11-AD; Amendment 39-13922; AD 2004-26-10]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland (RRD) (Formerly
Rolls-Royce, plc) Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15, Tay
650-15/10, and Tay 651-54 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for certain RRD Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15,
Tay 650-15/10, and Tay 651-54 turbofan engines with ice-impact panels
installed in the low pressure (LP) compressor case. That AD currently
requires visually inspecting all ice-impact panels and fillers in the
LP compressor case for certain conditions, and if necessary, replacing
any ice-impact panels and fillers that have those conditions. This AD
requires 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. This AD also introduces a
new compliance date of no later than March 1, 2005, to have all but one
engine on each airplane in compliance with the polysulfide bonding of
panels. This AD results from RRD issuing two service bulletins since AD
2004-05-22 was published, that required repetitive visual inspections
of panels, and defines a minimum configuration and repair standard. 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: Effective January 21, 2005. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of January 21, 2005.
We must receive any comments on this AD by March 7, 2005.
[[Page 1173]]
ADDRESSES: Use one of the following addresses to comment on this 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 referenced in this AD. You may
examine the comments on this AD in the AD docket on the Internet at
http://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7747; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: On March 3, 2004, the FAA issued AD 2004-05-
22, Amendment 39-13517 (69 FR 11305, March 10, 2004). That AD requires
visually inspecting all LP compressor case ice-impact panels and
fillers that conform to the RR Service Bulletin (SB) No. TAY-72-1326
standard or were repaired using RR repair scheme TV5451R or HRS3491,
for certain conditions. That AD also requires replacing any ice-impact
panels and fillers that have those conditions, if necessary. That AD
was the result of two reported events of ice-impact panels that
released during flight, one of which resulted in reduction of power in
both engines. That condition, if not corrected, could result in release
of ice-impact panels due to improper bonding that can result in loss of
thrust in both engines.
Actions Since AD 2004-05-22 Was Issued
Since AD 2004-5-22 was issued, RRD issued two SBs that supersede
the existing SBs used in that AD. The new SBs require initial and
repetitive visual inspections of all LP compressor case ice-impact
panels and fillers that conform to RR SB No. TAY-72-1326, or were
repaired using RR repair scheme TV5451R or HRS3491, for certain
conditions. The new SBs also require bonding of replacement ice-impact
panels using polysulfide bonding. Also, the new SBs introduce a new
compliance date of no later than March 1, 2005, to have all but one
engine on each airplane in compliance with the polysulfide bonding of
panels.
Relevant Service Information
We have reviewed and approved the technical contents of RRD SB No.
TAY-72-1638, Revision 2, dated September 21, 2004, and RRD SB No. TAY-
72-1639, Revision 2, dated September 21, 2004, that are described in
the previous paragraph. The Luftfahrt-Bundesamt (LBA), which is the
airworthiness authority for Germany, classified these SBs as mandatory
and issued AD D2004-313R2, dated September 21, 2004, in order to ensure
the airworthiness of these RRD engines in Germany.
Bilateral Airworthiness Agreement
This engine model is manufactured in the United Kingdom (U.K). and
is 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. Under this
bilateral airworthiness agreement, the Civil Aviation Authority (CAA),
which is the airworthiness authority for the U.K., has kept the FAA
informed of the situation described above. We have examined the
findings of the CAA, 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.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other RRD Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15,
Tay 650-15/10, and Tay 651-54 turbofan engines of the same type design.
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.
This AD requires the following:
Initial and repetitive visual inspections of all ice-
impact panels and fillers in the LP compressor case for certain
conditions and replacing any or all panels, based on condition.
Bonding of replacement ice-impact panels using polysulfide
bonding.
Introduction of a new compliance date of no later than
March 1, 2005, to have all but one engine on each airplane in
compliance with the polysulfide bonding of panels.
You must use the service information described previously to perform
the actions required by this AD.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Interim Action
These actions are interim actions and we may take further
rulemaking actions in the future.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2004-NE-11-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the rule
that might suggest a need to modify it. If a person contacts us
verbally, and that contact relates to a substantive part of this AD, we
will summarize the contact and place the summary in the docket. We will
consider all comments received by the closing date and may amend the AD
in light of those comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
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
[[Page 1174]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify that the 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. 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 by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2004-NE-11-AD'' in your request.
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 part 39 of the Federal
Aviation Regulations (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 39-13517 (69 FR
11305, March 10, 2004), and by adding a new airworthiness directive,
Amendment 39-13922, to read as follows:
2004-26-10 Rolls-Royce Deutschland (RRD) (Formerly Rolls-Royce,
plc): Amendment 39-13922. Docket No. 2004-NE-11-AD. Supersedes AD
2004-05-22, Amendment 39-13517.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
21, 2005.
Affected ADs
(b) This AD supersedes AD 2004-05-22, Amendment 39-13517.
Applicability
(c) This AD applies to RRD Tay 611-8, Tay 620-15, Tay 620-15/20,
Tay 650-15, Tay 650-15/10, 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 Rolls-Royce, plc (RR) Service
Bulletin (SB) No. TAY-72-1326 standard. These engines are installed
on, but not limited to, Fokker F.28 Mk.0070 and Mk.0100 series
airplanes, Gulfstream Aerospace G-IV 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 issuing two SBs since AD 2004-05-22
was published, that require repetitive visual inspections of ice-
impact panels and defines a minimum configuration and repair
standard. 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.
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 620-15/20, Tay 650-15,
and Tay 650-15/10 Engines
(f) For airplanes that have one Tay 620-15, Tay 620-15/20, Tay
650-15, or Tay 650-15/10 engine 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) Within 500 cycles-in-service (CIS) after the effective date
of this AD, but no later than February 15, 2005, inspect the ice-
impact panels and the surrounding fillers. Use paragraph 3.E. of the
Accomplishment Instructions of RRD SB No. TAY-72-1638, Revision 2,
dated September 21, 2004, and the inspection disposition criteria in
Table 1 of this AD.
Table 1.--Inspection Disposition Criteria
------------------------------------------------------------------------
If: Then:
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(a) 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.
(b) 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.
(c) 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.
(d) 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.
(e) 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.
(f) Any crack appears on the ice-impact Within 50 flight cycles or 50
panel and there is visible distortion flight hours, whichever occurs
of the airwashed surface. first, replace the damaged
panel using repair scheme
HRS3648 or HRS3649.
(g) Any crack appears on the ice-impact Within 150 flight cycles or 150
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.
(h) 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.
(i) Delamination or peeling of the Within 5 cycles or 5 flight
compound layers of the airwashed hours, whichever occurs first,
surface and the penetrated area is replace the damaged panel
between 1.55 square inch and 3.1 using repair scheme HRS3648 or
square inch in total. HRS3649.
(j) Delamination or peeling of the Within 50 cycles or 50 flight
compound layers of the airwashed hours, whichever occurs first,
surface and the penetrated area is replace the damaged panel
less than 1.55 square inch in total. using repair scheme HRS3648 or
HRS3649.
(k) 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.
(l) Missing filler surrounding the LP Before further flight, repair
compressor case. the damaged filler using
repair scheme HRS3630.
(m) 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.
------------------------------------------------------------------------
[[Page 1175]]
(2) Re-inspect within every 500 cycles-since-last-inspection
(CSLI) or two months since-last-inspection, whichever occurs first.
Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No.
TAY-72-1638, Revision 2, dated September 21, 2004, and the
inspection disposition criteria in Table 1 of this AD.
(g) For airplanes that have two Tay 620-15, Tay 620-15/20, Tay
650-15, or Tay 650-15/10 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, inspect the ice-impact panels and the
surrounding fillers on at least one of the affected engines. Use
paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1638, Revision 2, dated September 21, 2004, and the inspection
disposition criteria in Table 1 of this AD.
(2) Within 60 CIS after the effective date of this AD, but no
later than January 15, 2005, inspect the remaining engine ice-impact
panels and the surrounding fillers. Use paragraph 3.E. of the
Accomplishment Instructions of RRD SB No. TAY-72-1638, Revision 2,
dated September 21, 2004, and the inspection disposition criteria in
Table 1 of this AD.
(3) Re-inspect one of the affected engines on the airplane,
within every 250 CSLI or one month since-last-inspection, whichever
occurs first. Thereafter, alternate the repetitive inspections
between the two engines. Use paragraph 3.E. of the Accomplishment
Instructions of RRD SB No. TAY-72-1638, Revision 2, dated September
21, 2004, and the inspection disposition criteria in Table 1 of this
AD.
(h) Before March 1, 2005, rework all six ice-impact panels using
repair scheme HRS3648 or HRS3649 on at least one of the affected
engines.
(i) After complying with paragraph (h) of this AD, re-inspect
the engine not reworked, using the intervals in paragraph (f)(2) of
this AD.
Inspecting Ice-Impact Panels in Tay 651-54 Engines
(j) For airplanes that have one Tay 651-54 engine 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) Within 30 CIS after the effective date of this AD, inspect
the ice-impact panels and the surrounding fillers on the affected
engine. Use paragraph 3.E. of the Accomplishment Instructions of RRD
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the
inspection disposition criteria in Table 1 of this AD.
(2) Re-inspect the affected engine within every 500 CSLI or six
months since-last-inspection, whichever occurs first. Use paragraph
3.E. of the Accomplishment Instructions of RRD SB No. TAY-72-1638,
Revision 2, dated September 21, 2004, and the inspection disposition
criteria in Table 1 of this AD.
(k) For airplanes that have more than one Tay 651-54 engine 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, inspect the ice-impact panels and the
surrounding fillers on at least one of the engines affected. Use
paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1638, Revision 2, dated September 21, 2004, and the inspection
disposition criteria in Table 1 of this AD.
(2) Within 30 CIS after the effective date of this AD, inspect
the ice-impact panels and the surrounding fillers on the remaining
engine. Use paragraph 3.E. of the Accomplishment Instructions of RRD
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the
inspection disposition criteria in Table 1 of this AD.
(3) Re-inspect at least one of the affected engines within every
250 CSLI or three months since-last inspection, whichever occurs
first. Use paragraph 3.E of the Accomplishment Instructions of RRD
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the
inspection disposition criteria in Table 1 of this AD.
(l) Before March 1, 2005, rework all six ice-impact panels using
RR repair scheme HRS3648 or HRS3649 on at least one of the affected
engines.
(m) After complying with paragraph (l) of this AD, re-inspect
the engine not reworked, using the intervals in paragraph (j)(2) of
this AD.
Repetitive Inspections for Tay 620-15, Tay 620-15/20, Tay 650-15, Tay
650-15/10, and Tay 651-54 Engines With All Ice-impact Panels Repaired
by Polysulfide Bonding Material
(n) For Tay 620-15, Tay 620-15/20, Tay 650-15, Tay 650-15/10,
and Tay 651-54 engines with ice-impact panels incorporated by the
RRD SB No. SB 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 paragraph 3.E. of the Accomplishment Instructions of RRD
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the
inspection disposition criteria in Table 1 of this AD.
Inspecting Ice-Impact Panels in Tay 611-8 Engines
(o) For airplanes that have one Tay 611-8 engine 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) Within 450 flight hours after the effective date of this AD,
inspect the ice-impact panels on the affected engine. Use paragraph
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.
(2) Re-inspect the ice impact panels within every 1,000 CSLI or
six months since-last-inspection, whichever occurs first, Use
paragraph 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.
(p) For airplanes with both Tay 611-8 engines with ice-impact
panels incorporated with 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 on the affected
engines, do the following:
(1) Within 150 flight hours after the effective date of this AD,
inspect the ice-impact panels on one of the affected engines. Use
paragraph 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.
(2) Within 450 flight hours after the effective date of this AD,
inspect the ice-impact panels on the remaining engine. Use paragraph
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 500 CSLI or
three months since-last-inspection, whichever occurs first, Use
paragraph 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, on at least one of the
affected engines.
(q) Before March 1, 2005, rework all six ice-impact panels using
RR repair scheme HRS3648, or HRS3649 on at least one of the affected
engines.
(r) After complying with paragraph (q) of this AD, re-inspect
the engine not reworked, using the intervals in paragraph (o)(2) 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
(s) For Tay 611-8 engines with ice-impact panels incorporated by
the RRD SB No. SB 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 CSLI, for the condition of the
ice-impact panels and the surrounding fillers.
(2) Use paragraph 3.E. of the Accomplishment Instructions of RRD
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the
inspection disposition criteria in Table 1 of this AD.
Installing Engines That Are Not Inspected
(t) After the effective date of this AD, do not install any Tay
620-15, Tay 620-15/20,
[[Page 1176]]
Tay 650-15, Tay 650-15/10, and 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.
(u) Perform repetitive inspections as specified in paragraph (n)
of this AD.
(v) 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.
(w) Perform repetitive inspections as specified in paragraph (s)
of this AD.
Alternative Methods of Compliance
(x) 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.
Material Incorporated by Reference
(y) You must use the Rolls-Royce service information specified
in Table 2 to perform the inspections required by this AD. The
Director of the Federal Register approved the incorporation by
reference of the documents listed in Table 2 of this AD 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, D-15827
Dahlewitz, 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/code_of_federal_regulations/ibr_locations.html.
Table 2 follows:
Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service information No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
SB No. TAY-72-1638..................... ALL....................... 2 Sept. 21, 2004.
Total Pages: 35
SB No. TAY-72-1639..................... ALL....................... 2 Sept. 21, 2004.
Total Pages: 28
Repair Scheme No. HRS3648 Front Sheet.. ALL....................... 2 Jan. 28, 2004.
Total Pages: 1
Repair Scheme No. HRS3648 History Sheet ALL....................... 2 Jan. 28, 2004.
Total Pages: 3
Repair Scheme No. HRS3648.............. ALL....................... 2 Jan. 27, 2004.
Total Pages: 30
Repair Scheme No. HRS3649 Front Sheet.. ALL....................... 2 Sept. 1, 2004.
Total Pages: 1
Repair Scheme No. HRS3649 History Sheet ALL....................... 2 Sept. 7, 2004.
Total Pages: 3
Repair Scheme No. HRS3649.............. ALL....................... 2 June 17, 2004.
Total Pages: 24
----------------------------------------------------------------------------------------------------------------
Related Information
(z) LBA AD D2004-313R2, dated September 21, 2004, also addresses
the subject of this AD.
Issued in Burlington, Massachusetts, on December 22, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-40 Filed 1-5-05; 8:45 am]
BILLING CODE 4910-13-P