[Federal Register Volume 70, Number 4 (Thursday, January 6, 2005)]
[Rules and Regulations]
[Pages 1172-1176]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-40]


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

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.

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

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:
------------------------------------------------------------------------
(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