AD Amdt-39-15026

[Federal Register Volume 72, Number 72 (Monday, April 16, 2007)]
[Rules and Regulations]
[Pages 18862-18865]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E7-7032]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27824; Directorate Identifier 2003-NE-12-AD; 
Amendment 39-15026; AD 2006-11-05R1]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is revising an existing airworthiness directive (AD) 
for Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, -524D4, 
-524G2, -524G3, and -524H series, and RB211-535C and -535E series 
turbofan engines with high pressure compressor (HPC) stage 3 disc 
assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, 
UL11706, UL15358, UL22577, UL22578, and UL24738 installed. That AD 
currently requires removing from service certain disc assemblies before 
they reach their full published life if not modified with anticorrosion 
protection. This AD requires the same actions but relaxes the removal 
compliance time for certain disc assemblies that have a record of 
detailed inspection. This AD results from the FAA allowing certain 
affected disc assemblies that entered into service before 1990 that 
have a record of detailed inspections, to remain in service for a 
longer period than the previous AD allowed. We are issuing this AD to 
relax the compliance time for certain disc assemblies and track the 
disc life based on a detailed inspection rather than by its entry into 
service date, while continuing to prevent corrosion-induced uncontained 
disc assembly failure, resulting in damage to the airplane.

[[Page 18863]]


DATES: Effective May 1, 2007. The Director of the Federal Register 
previously approved the incorporation by reference of certain 
publications listed in the regulations as of February 24, 2004 (69 FR 
2661, January 20, 2004).
    We must receive any comments on this AD by June 15, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD.
    <bullet> DOT Docket Web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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 plc, P.O. Box 31, Derby, England, DE248BJ; 
telephone: 011-44-1332-242424; fax: 011-44-1332-245-418, for the 
service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park; Burlington, MA 01803; e-mail: 
<a href="/cdn-cgi/l/email-protection#a2cbc3cc8cc6c3d0c5cbcce2c4c3c38cc5cdd4"><span class="__cf_email__" data-cfemail="ff969e91d19b9e8d989691bf999e9ed1989089">[email&#160;protected]</span></a>; telephone (781) 238-7178; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On May 15, 2006, the FAA issued AD 2006-11-
05, Amendment 39-14609 (71 FR 29586, May 23, 2006). We also issued a 
correction to that AD on September 26, 2006 (71 FR 58254, October 3, 
2006). That AD requires removing from service certain disc assemblies 
before they reach their full published life if not modified with 
anticorrosion protection. That AD was the result of the manufacturer's 
reassessment of the corrosion risk on HPC stage 3 disc assemblies that 
have not yet been modified with sufficient application of anticorrosion 
protection. That condition, if not corrected, could result in 
corrosion-induced uncontained disc assembly failure, resulting in 
damage to the airplane.

Actions Since AD 2006-11-05 Was Issued

    Since AD 2006-11-05 was issued, RR revised an applicable mandatory 
service bulletin (MSB). That MSB allows affected disc assemblies that 
entered into service before 1990 that have a record of detailed 
inspections, to remain in service for 17 years from last overhaul 
inspection date. But the discs are not to exceed the manufacturer's 
published cyclic limit in the time limits section of the manual. We are 
issuing this AD to relax the compliance time for certain disc 
assemblies and track the disk life based on a detailed inspection 
rather than by its entry into service date, while continuing to prevent 
corrosion-induced uncontained disc assembly failure, resulting in 
damage to the airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of RR MSB No. 
RB.211-72-9661, Revision 5, dated December 22, 2006. That MSB allows 
affected disc assemblies that entered into service before 1990; and 
that have a record of detailed inspection:
    <bullet> To remain in service for 17 years from last overhaul 
inspection date; but
    <bullet> Not to exceed the manufacturer's published cyclic limit in 
the time limits section of the manual.
    We do not incorporate by reference this MSB, but we list it under 
related information.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the United Kingdom (UK), 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 CAA, which is the airworthiness 
authority for the UK, 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 (RR) RB211-22B series, RB211-524B, -524C2, -524D4, -
524G2, -524G3, and -524H series, and RB211-535C and -535E series 
turbofan engines of the same type design. We are issuing this AD to 
relax the compliance time for certain disc assemblies and to prevent 
corrosion-induced uncontained disc assembly failure, resulting in 
damage to the airplane. This AD requires the following for affected HPC 
stage 3 rotor disc assemblies:
    <bullet> Removing affected disc assemblies from service; and
    <bullet> Re-machining, inspecting, and applying anticorrosion 
protection; and
    <bullet> Re-marking, and returning disc assemblies into service; 
and
    <bullet> Allowing affected disc assemblies that entered into 
service before 1990 that have a record of detailed inspection, to 
remain in service for 17 years from last overhaul inspection date but 
not to exceed the manufacturer's published cyclic limit in the time 
limits section of the manual.
    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. Good cause 
exists for making this amendment effective in less than 30 days.

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 send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2007-27824; 
Directorate Identifier 2003-NE-12-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to <a href="http://dms.dot.gov">http://dms.dot.gov</a>, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS Web 
site, anyone can find and read the comments in any of our dockets. This 
includes the name of the individual who sent the comment (or signed the 
comment on behalf of an association, business, labor union, etc.). You 
may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78) or you may visit 
<a href="http://dms.dot.gov">http://dms.dot.gov</a>.

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

[[Page 18864]]

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.

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-2007-27824. The old Docket No. became the 
Directorate Identifier, which is 2003-NE-12-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.

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 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 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
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 39-14609 (71 FR 
29586, May 23, 2006) and by adding a new airworthiness directive, 
Amendment 39-15026, to read as follows:

2006-11-05R1 Rolls-Royce plc: Amendment 39-15026. Docket No. FAA-
2007-27824; Directorate Identifier 2003-NE-12-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 1, 
2007.

Affected ADs

    (b) This AD revises AD 2006-11-05, Amendment 39-14609.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211-22B series, 
RB211-524B, -524C2, -524D4, -524G2, -524G3, and -524H series, and 
RB211-535C and -535E series turbofan engines with high pressure 
compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) 
LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, 
UL22578, and UL24738 installed. These engines are installed on, but 
not limited to, Boeing 747, Boeing 757, Boeing 767, Lockheed L-1011, 
and Tupolev Tu204 series airplanes.

Unsafe Condition

    (d) This AD results from the FAA allowing certain affected disc 
assemblies that entered into service before 1990 that have a record 
of detailed inspections, to remain in service for a longer period 
than the previous AD allowed. We are issuing this AD to relax the 
compliance time for certain disc assemblies and track the disc life 
based on a detailed inspection rather than by its entry into service 
date, while continuing to prevent corrosion-induced uncontained disc 
assembly failure, resulting in 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.

Removal of HPC Stage 3 Disc Assemblies

    (f) Remove from service affected HPC stage 3 disc assemblies 
identified in the following Table 1, using one of the following 
criteria:

                                 Table 1.--Affected HPC Stage 3 Disc Assemblies
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                                                                                                Rework band for
                                                          Rework band for                         cyclic life
                                                            cyclic life      Rework band for   accumulated on P/
                                                           accumulated on      cyclic life        Ns LK76036,
                                                         disc assemblies P/   accumulated on   UL11706, UL15358,
                      Engine model                         Ns LK46210 and   disc assembly P/N  UL22577, UL22578,
                                                          LK58278 (Pre RR    LK67634 (pre RR    and UL24738 disc
                                                          Service Bulletin  SB No. RB.211-72-   assemblies (pre
                                                          (SB) No. RB.211-        5420)        RR SB No. RB.211-
                                                              72-5420)                              72-9434)
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-22B series............................................        4,000-6,200       7,000-10,000      11,500-14,000
-535E4 series..........................................                N/A                N/A       9,000-15,000
-524B-02, B-B-02, B3-02, and B4 series, Pre and Post           4,000-6,000        7,000-9,000      11,500-14,000
 accomplishment of SB No. 72-7730......................
-524B2 and C2 series, Pre SB No. 72-7730...............        4,000-6,000        7,000-9,000      11,500-14,000

[[Page 18865]]

 
-524B2-B-19 and C2-B-19, SB No. 72-7730................        4,000-6,000        7,000-9,000       8,500-11,000
-524D4 series, Pre SB No. 72-7730......................        4,000-6,000        7,000-9,000      11,500-14,000
-524D4-B series, SB No. 72-7730........................        4,000-6,000        7,000-9,000       8,500-11,000
-524G2, G3, H, and H2 series...........................        4,000-6,000        7,000-9,000       8,500-11,000
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    (1) For disc assemblies that entered into service before 1990, 
remove disc assembly and rework as specified in paragraph (g)(2) of 
this AD, on or before January 4, 2007, but not to exceed the upper 
cyclic limit in Table 1 of this AD before rework. Disc assemblies 
reworked may not exceed the manufacturer's published cyclic limit in 
the time limits section of the manual.
    (2) For disc assemblies that entered into service in 1990 or 
later, remove disc assembly within the cyclic life rework bands in 
Table 1 of this AD, or within 17 years after the date of the disc 
assembly entering into service, whichever is sooner, but not to 
exceed the upper cyclic limit of Table 1 of this AD before rework. 
Disc assemblies reworked may not exceed the manufacturer's published 
cyclic limit in the time limits section of the manual.
    (3) For disc assemblies that when new, were modified with an 
application of anticorrosion protection and re-marked to P/N LK76036 
(not previously machined) as specified by Part 1 of the original 
issue of RR service bulletin (SB) No. RB.211-72-5420, dated April 
20, 1979, remove RB211-22B disc assemblies before accumulating 
10,000 cycles-in-service (CIS), and remove RB211-524 disc assemblies 
before accumulating 9,000 CIS.
    (4) If the disc assembly date of entry into service cannot be 
determined, the date of disc assembly manufacture may be obtained 
from RR and used instead.
    (5) Disc assemblies in RB211-535C operation are unaffected by 
the interim rework cyclic band limits in Table 1 of this AD, but 
must meet the calendar life requirements of either paragraph (f)(1) 
or (f)(2) of this AD, as applicable.

Optional Rework of HPC Stage 3 Disc Assemblies

    (g) Rework HPC stage 3 disc assemblies that were removed in 
paragraph (f) of this AD as follows:
    (1) For disc assemblies that when new, were modified with an 
application of anticorrosion protection and re-marked to P/N LK76036 
(not previously machined) as specified by Part 1 of the original 
issue of RR SB RB.211-72-5420, dated April 20, 1979, rework disc 
assemblies and re-mark to either LK76034 or LK78814 using paragraph 
2.B. of the Accomplishment Instructions of RR SB No. RB.211-72-5420, 
Revision 4, dated February 29, 1980. This rework constitutes 
terminating action to the removal requirements in paragraph (f) of 
this AD.
    (2) For all other disc assemblies, rework using Paragraph 3.B. 
of the Accomplishment Instructions of RR SB No. RB.211-72-9434, 
Revision 4, dated January 12, 2000. This rework constitutes 
terminating action to the removal requirements in paragraph (f) of 
this AD.
    (3) If rework is done on disc assemblies that are removed before 
the disc assembly reaches the lower life of the cyclic life rework 
band in Table 1 of this AD, artificial aging of the disc assembly to 
the lower life of the rework band, at time of rework, is required.
    (4) Disc assemblies that entered into service before 1990 that 
have a record of detailed inspection are allowed to remain in 
service for 17 years from last overhaul inspection date but not to 
exceed the manufacturer's published cyclic limit in the time limits 
section of the manual.

Alternative Methods of Compliance

    (h) 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

    (i) Civil Aviation Authority airworthiness directive 004-01-94, 
dated January 4, 2002, and RR Mandatory Service Bulletin No. RB.211-
72-9661, Revision 5, dated December 22, 2006, pertain to the subject 
of this AD.

Material Incorporated by Reference

    (j) You must use Rolls-Royce plc Service Bulletin No. RB.211-72-
5420, Revision 4, dated February 29, 1980, and Rolls-Royce plc 
Service Bulletin No. RB.211-72-9434, Revision 4, dated January 12, 
2000, to perform the rework required by this AD. The Director of the 
Federal Register previously approved the incorporation by reference 
of these service bulletins in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51, as of February 24, 2004 (69 FR 2661, January 20, 2004). 
You can get copies from Rolls-Royce plc, P.O. Box 31, Derby, 
England, DE248BJ; telephone: 011-44-1332-242424; fax: 011-44-1332-
245-418. You can 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>.
    (k) Contact Ian Dargin, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: <a href="/cdn-cgi/l/email-protection#432a222d6d272231242a2d032522226d242c35"><span class="__cf_email__" data-cfemail="066f676828626774616f684660676728616970">[email&#160;protected]</span></a>; 
telephone (781) 238-7178; fax (781) 238-7199, for more information 
about this AD.

    Issued in Burlington, Massachusetts, on April 9, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. E7-7032 Filed 4-13-07; 8:45 am]
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