AD 2007-06-10

[Federal Register Volume 72, Number 50 (Thursday, March 15, 2007)]
[Rules and Regulations]
[Pages 12060-12064]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E7-4536]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27267; Directorate Identifier 2002-NE-40-AD; 
Amendment 39-14991; AD 2007-06-10]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-524 Series 
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 plc (RR) RB211-524 series turbofan engines with 
certain part number (P/N) intermediate pressure compressor (IPC) stage 
5 disks installed. That AD currently requires new reduced IPC stage 5 
disk cyclic limits. This AD requires the same reduced IPC stage 5 disk 
cyclic limits, requires removal from service of affected disks that 
already exceed the new reduced cyclic limit, and, removal from service 
of other affected disks before exceeding their cyclic limits using a 
drawdown schedule. This AD also exempts disks reworked to RR Service 
Bulletin (SB) No. RB.211-72-E182, Revision 1, dated July 30, 2004, and 
allows an on-wing eddy current inspection (ECI) on RB211-524G and 
RB211-524H series engines. This AD results from the manufacturer 
issuing a revised Alert Service Bulletin (ASB) to remove certain disks 
from applicability, and to allow an on-wing ECI on RB211-524G and 
RB211-524H series engines. We are issuing this AD to prevent failure of 
the IPC stage 5 disk, which could result in uncontained engine failure 
and possible damage to the airplane.

DATES: This AD becomes effective April 19, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of April 19, 2007.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce plc, P.O. Box 31 Derby, DE248BJ, United Kingdom; 
telephone 011-44-1332-242424; fax 011-44-1332-249936.
    You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; telephone (781) 238-7178; 
fax (781) 238-7199; e-mail: <a href="/cdn-cgi/l/email-protection#c7aea6a9e9a3a6b5a0aea987a1a6a6e9a0a8b1"><span class="__cf_email__" data-cfemail="b9d0d8d797ddd8cbded0d7f9dfd8d897ded6cf">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to RR RB211-524 series 
turbofan engines with certain P/N IPC stage 5 disks installed. We 
published the proposed AD in the Federal Register on July 11, 2006 (71 
FR 39025). That action proposed to require:
    <bullet> Establishing new reduced IPC stage 5 disk cyclic limits.
    <bullet> Removing from service affected disks that already exceed 
the new reduced cyclic limit.
    <bullet> Removing from service other affected disks before 
exceeding their cyclic limits, using a drawdown schedule.
    <bullet> Allowing optional inspections at each shop visit or an on-
wing ECI to extend the disk life beyond the specified life.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The Docket Office (telephone (800) 647-5227) is 
located on the plaza level of the Department of Transportation Nassif 
Building at the street address stated in ADDRESSES. Comments will be 
available in the AD docket shortly after the DMS receives them.

Comments

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

Request To Add a Note

    One commenter, Rolls-Royce plc, requests that we add a note, just 
above compliance paragraph (j)(5), that states: ``To qualify for 
maximum alleviation since last NDT inspection (see Table 5 of this AD) 
it is recommended that discs be ECI inspected using paragraph 3.D. of 
the Accomplishment Instructions of RR

[[Page 12061]]

Alert Service Bulletin No. RB.211-72-AD428, Revision 5, dated March 18, 
2005.'' The commenter feels that this note adds clarification to the AD 
compliance. We do not agree. The note is identified in the service 
bulletin that is incorporated by reference, and need not be included in 
the text of the AD. We did not change the AD.

Request To Add Engine Series

    Rolls-Royce plc requests that we add the RB211-524B/B3 engine 
series to compliance paragraph (k)(1), and add the RB211-524H2 and 
RB211-524H2-T engine series to compliance paragraph (k)(2), as they 
need to be included, the same as they appear in the service bulletin. 
We agree and added those engine series to the paragraphs.

Clarification of Paragraph (g)

    Since we issued the proposed AD, we reviewed the wording in 
paragraph (g) and realized that the compliance times in that paragraph 
were in conflict. We clarified that paragraph. It now states to comply 
with the reduced cyclic life limits in Table 3 of this AD within 30 
days after the effective date of this AD, or conduct optional 
qualifying nondestructive test (NDT) inspections before December 1, 
2008, to extend the IPC stage 5 disk life as specified in paragraph (i) 
of this AD.

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.

Docket Number Change

    We are transferring the docket for this AD to the Docket Management 
System as part of our on-going docket management consolidation efforts. 
The new Docket No. is FAA-2007-27267. The old Docket No. became the 
Directorate Identifier, which is 2002-NE-40-AD. This AD might get 
logged into the DMS docket, ahead of the previously collected documents 
from the old docket file, as we are in the process of sending those 
items to the DMS.

Costs of Compliance

    We estimate this AD will not affect any engines installed on 
airplanes of U.S. registry. Based on this, we estimate this AD will not 
have any cost to U.S. operators.

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 39-14202 (70 FR 
43036, July 26, 2005) and by adding a new airworthiness directive, 
Amendment 39-14991, to read as follows:

2007-06-10 Rolls-Royce plc: Amendment 39-14991. Docket No. FAA-2007-
27267; Directorate Identifier 2002-NE-40-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
19, 2007.

Affected ADs

    (b) This AD supersedes AD 2005-15-13, Amendment 39-14202.

Applicability

    (c) This AD applies to the Rolls-Royce plc (RR) RB211-524 series 
turbofan engines listed in the following Table 1, with intermediate 
pressure compressor (IPC) stage 5 disk part numbers (P/Ns) listed in 
Table 2 of this AD, installed.

                                        Table 1.--Engine Models Affected
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
-524B-02               -524B-B-02             -524B3-02              -524B4-02              -524B4-D-02
-524B2-19              -524B2-B-19            -524C2-19              -524C2-B-19            -524D4-19
-524D4-B-19            -524D4X-19             -524D4X-B-19           -524D4-39              -524D4-B-39
-524G2-19              -524G2-T-19            -524G3-19              -524G3-T-19            -524H2-19
-524H2-T-19            -524H-36               -524H-T-36
----------------------------------------------------------------------------------------------------------------

    These engines are installed on, but not limited to, Boeing 747, 
767, and Lockheed L-1011 series airplanes.

[[Page 12062]]



                                    Table 2.--IPC Stage 5 Disk P/Ns Affected
----------------------------------------------------------------------------------------------------------------
 
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LK60130                LK65932                LK69021                LK81269                LK83282
LK83283                UL12290                UL15743                UL15744                UL15745
UL19132                UL20785                UL20832                UL23291                UL25011
UL36821                UL36977                UL36978                UL36979                UL36980
UL36981                UL36982                UL36983                UL37078                UL37079
UL37080                UL37081                UL37082                UL37083                UL37084
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from the manufacturer issuing a revised 
Alert Service Bulletin (ASB) to remove certain disks from 
applicability and to allow an on-wing eddy current inspection (ECI) 
on RB211-524G and RB211-524H series engines. The actions specified 
in this AD are intended to prevent failure of the IPC stage 5 disk, 
which could result in uncontained engine failure and possible damage 
to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Exempted Disks

    (f) For engines with an IPC stage 5 disk P/N listed in Table 2 
of this AD, reworked to RR SB No. RB.211-72-E182, Revision 1, dated 
July 30, 2004, no further action is necessary.

Cycle Limits

    (g) Comply with the reduced cyclic life limits in Table 3 of 
this AD within 30 days after the effective date of this AD, or 
conduct optional qualifying nondestructive test (NDT) inspections 
before December 1, 2008 to extend the IPC stage 5 disk life, as 
specified in paragraph (i) of this AD.

                         Table 3.--Cyclic Life Limits Without Qualifying NDT Inspection
----------------------------------------------------------------------------------------------------------------
                                                                   Engine models
                                 -------------------------------------------------------------------------------
   Date of reduced life limit      -524G2, G2-T, G3,  -524D4, D4-B, D4-B-                      -524B-02, B-B-02,
                                  G3-T, H2, H2-T, H-  39, D4X, D4X-B, D4-  -524B2, B2-B, C2,  B3-02, B4-02, B4-D-
                                      36, H-T-36              39                 C2-B                 02
----------------------------------------------------------------------------------------------------------------
November 30, 2002...............  13,500 cycles-in-   16,150 CIS........  16,000 CIS........  16,200 CIS.
                                   service (CIS).
April 1, 2003...................  13,500 CIS........  13,500 CIS........  13,500 CIS........  14,000 CIS.
December 1, 2003................  12,000 CIS........  13,500 CIS........  13,500 CIS........  14,000 CIS.
December 1, 2004................  11,000 CIS........  13,500 CIS........  12,000 CIS........  12,000 CIS.
December 1, 2005................  11,000 CIS........  12,000 CIS........  12,000 CIS........  12,000 CIS.
----------------------------------------------------------------------------------------------------------------

    (h) On December 1, 2008, the revised cyclic life limits 
specified in Table 4 of this AD become effective. Incorporate the 
revised cyclic life limits specified in Table 4 of this AD into the 
RR Time Limits Manual, 05-10-01.

                                Table 4.--Cyclic Life Limits on December 1, 2008
----------------------------------------------------------------------------------------------------------------
                                                                   Engine models
                                 -------------------------------------------------------------------------------
   Date of reduced life limit      -524G2, G2-T, G3,  -524D4, D4-B, D4-B-                      -524B-02, B-B-02,
                                  G3-T, H2, H2-T, H-  39, D4X, D4X-B, D4-  -524B2, B2-B, C2,  B3-02, B4-02, B4-D-
                                      36, H-T-36              39                 C2-B                 02
----------------------------------------------------------------------------------------------------------------
December 1, 2008................  7,830 CIS.........  8,700 CIS.........  8,900 CIS.........  9,000 CIS.
----------------------------------------------------------------------------------------------------------------

Optional Inspections

    (i) Before December 1, 2008, you may perform an optional NDT 
inspection on-wing or at each shop visit to extend the disk life. 
Guidance for these inspections is provided in paragraphs (j) or (k) 
of this AD.

Optional Inspections at Shop Visit

    (j) Perform optional inspections at shop visit, as follows:
    (1) Remove corrosion protection from IPC stage 5 disk. 
Information on corrosion protection removal can be found in the 
Engine Maintenance Manual.
    (2) Perform a visual inspection and a binocular inspection of 
the IPC stage 5 disk for corrosion pitting at the cooling air holes 
and defender holes in the disk front spacer arm. Follow paragraph 
3.C. of the Accomplishment Instructions of RR ASB No. RB.211-72-
AD428, Revision 5, dated March 18, 2005. The RR Engine Maintenance 
Manual, Inspection Check-00 (ATA 72-32-31-200-000), contains limits 
for corrosion pitting of the IPC stage 5 disk.
    (3) If the disk has corrosion pitting in excess of limits, 
remove the disk from service.
    (4) If the disk is free from corrosion pitting, perform a 
magnetic penetrant inspection (MPI) of the entire disk as follows:
    (i) For RB211-524G2-T, RB211-524G3-T, and RB211-524H-T series 
engines, the RR Engine Maintenance Manual, Inspection Check 08 (ATA 
72-32-31-200-008), contains limits for corrosion pitting of the IPC 
stage 5 disk.
    (ii) For RB211-524G2, RB211-524G3, and RB211-524H series 
engines, the RR Engine Maintenance Manual, Inspection Check 09 (ATA 
72-32-31-200-009), contains limits for corrosion pitting of the IPC 
stage 5 disk.
    (iii) If the disk passes the MPI and you find no cracks, 
complete all other inspections, re-apply corrosion protection to the 
disk, and return the disk to service using the cyclic limits allowed 
by paragraph (m) of this AD. RR Repair FRS5900 contains information 
on re-applying corrosion protection.
    (5) If the disk has corrosion pitting that is within limits, do 
the following:
    (i) Perform an ECI on all disk cooling air holes, defender 
holes, and inner and outer faces. Use paragraph 3.D. of the 
Accomplishment Instructions of RR ASB No. RB.211-72-AD428, Revision 
5, dated March 18, 2005. The RR Engine Maintenance Manual, 
Inspection Check-00 (ATA 72-32-31-200-000), contains limits for 
corrosion pitting of the IPC stage 5 disk.
    (ii) If the disk passes the ECI and you find no cracks, perform 
an MPI on the entire disk.
    (iii) If the disk passes the MPI and you find no cracks, re-
apply corrosion protection to the disk, and return the disk to 
service using the cyclic limits allowed by paragraph (m) of this AD.

[[Page 12063]]

Optional On-Wing Eddy Current Inspections

    (k) You may perform an optional on-wing ECI of the IPC stage 5 
disk only once between shop visit inspections as follows:
    (1) For RB211-524B2/C2, RB211-524B/B3, and RB211-524B4/D4 series 
engines, use paragraphs 3.A. through 3.F. of the Accomplishment 
Instructions of RR SB No. RB.211-72-E148, dated March 13, 2003, and 
RR SB No. RB.211-72-E150, Revision 1, dated June 4, 2003.
    (2) For RB211-524G2, RB211-524G2-T, RB211-524G3, RB211-524G3-T, 
RB211-524H, RB211-524H-T, RB211-524H2, and RB211-524H2-T series 
engines, use paragraphs 3.A. through 3.M. of the Accomplishment 
Instructions of RR SB No. RB.211-72-E171, Revision 1, dated February 
8, 2005.
    (3) If the disk passes the ECI and you find no cracks, you may 
extend the cycle life as specified in paragraph (m) of this AD.

Definition of Shop Visit

    (l) The manufacturer defines a shop visit as the separation of 
an engine major case flange. This definition excludes shop visits 
when only field maintenance type activities are performed in lieu of 
performing them on-wing (such as to perform an on-wing inspection of 
a tail engine installation on a Lockheed L-1011 series airplane).

Cyclic Life Extension

    (m) Disks that pass an optional inspection may remain in service 
after that inspection for the additional cycles listed in the 
following Table 5, until the next inspection, until the cyclic life 
limit published in the RR Time Limits Manual, 05-10-01, is reached, 
or December 1, 2008, whichever occurs first.

                                         Table 5.--Cyclic Life Extension
----------------------------------------------------------------------------------------------------------------
                                                                           Engine models
                                                 ---------------------------------------------------------------
                                                   -524G2, G2-T,
                Type of extension                  G3, G3-T, H2,   -524D4, D4-B,   -524B2, B2-B,  -524B-02, B-B-
                                                  H2-T, H-36, H-   D4-B-39, D4X,     C2, C2-B     02, B3-02, B4-
                                                  T-36  (cycles)   D4X-B, D4-39      (cycles)       02, B4-D-02
                                                                     (cycles)                        (cycles)
----------------------------------------------------------------------------------------------------------------
Extension After Passing MPI.....................           1,600           2,000           2,000           2,000
Extension After Passing In-Shop ECI.............           3,800           4,500           4,500           4,500
Extension After Passing On-Wing ECI.............           1,000           1,200           1,200           1,200
----------------------------------------------------------------------------------------------------------------

Disks That Have Been Intermixed Between Engine Models

    (n) The RR Time Limits Manual, 05-00-01, contains information on 
intermixing disks between engine models.

Alternative Methods of Compliance

    (o) 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.

Credit for Previous Inspections

    (p) Inspections done using RR SB No. RB.211-72-E150, dated April 
17, 2003, SB No. RB.211-72-E171, dated December 14, 2004, SB No. 
RB.211-72-D428, Revision 3, dated June 30, 2003, and ASB No. RB.211-
72-AD428, Revision 4, dated March 7, 2005, meet the requirements of 
this AD.

Reporting Requirement

    (q) Report findings of all inspections of the IPC stage 5 disk 
using paragraph 3.B.(2) of the Accomplishment Instructions of RR No. 
ASB RB.211-72-AD428, Revision 5, dated March 18, 2005. The Office of 
Management and Budget (OMB) has approved the reporting requirements 
specified in Paragraph 3.B. of the Accomplishment Instructions of RR 
No. ASB RB.211-72-AD428, Revision 5, dated March 18, 2005, and 
assigned OMB control number 2120-0056.

Related Information

    (r) CAA airworthiness directive G-2005-0008, dated March 8, 
2005, also addresses the subject of this AD.
    (s) Contact Ian Dargin, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; telephone (781) 238-7178; fax 
(781) 238-7199; e-mail: <a href="/cdn-cgi/l/email-protection#076e666929636675606e694761666629606871"><span class="__cf_email__" data-cfemail="5a333b34743e3b283d33341a3c3b3b743d352c">[email&#160;protected]</span></a> for more information 
about this AD.

Material Incorporated by Reference

    (t) You must use the service information specified in Table 6 to 
perform the actions required by this AD. The Director of the Federal 
Register approved the incorporation by reference of the documents 
listed in Table 6 of this AD in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. Contact Rolls-Royce plc, P.O. Box 31 Derby, DE248BJ, 
United Kingdom; telephone 011-44-1332-242424; fax 011-44-1332-249936 
for a copy of this service information. 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: 
<a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

                                      Table 6.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
 Rolls-Royce plc Service Bulletin
(SB)/Alert Service Bulletin (ASB)           Page                 Revision                      Date
               No.
----------------------------------------------------------------------------------------------------------------
SB No. RB.211-72-E148............  All..................  Original.............  March 13, 2003.
    Total Pages: 83                                                              ...............................
SB No. RB.211-72-E150............  All..................  1....................  June 4, 2003.
    Total Pages: 72                                                              ...............................
SB No. RB.211-72-E171............  All..................  1....................  February 8, 2005
    Total Pages: 71                                                              ...............................
ASB No. RB.211-72-AD428..........  All..................  5....................  March 18, 2005.
    Total Pages: 27                                                              ...............................
Appendix 1 of ASB No. RB.211-72-   All..................  5....................  March 18, 2005.
 AD428.
    Total Pages: 4                                                               ...............................
Appendix 2 of ASB No. RB.211-72-   All..................  5....................  March 18, 2005.
 AD428.
    Total Pages: 2                                                               ...............................
Appendix 3 of ASB No. RB.211-72-   All..................  5....................  March 18, 2005.
 AD428.
    Total Pages: 5                                                               ...............................
Appendix 4 of ASB No. RB.211-72-   All..................  5....................  March 18, 2005.
 AD428.
    Total Pages: 2                                                               ...............................
----------------------------------------------------------------------------------------------------------------



[[Page 12064]]

    Issued in Burlington, Massachusetts, on March 7, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-4536 Filed 3-14-07; 8:45 am]
BILLING CODE 4910-13-P