Document ID: FAA-2007-27811-0025
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Rolls-Royce Deutschland Ltd and Co KG Tay 611-8, Tay 611-8C, Tay 620-15, Tay 650-15, and Tay 651-54 Turbofan Engines
Posted Date: 2008-01-07T05:00Z

[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]                         

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

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.

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

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
------------------------------------------------------------------------
                  If:                                 Then:
------------------------------------------------------------------------
(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