Airworthiness Directives; Rolls-Royce plc RB211-524 Series Turbofan Engines, 39025-39028 [E6-10771]

Download as PDF Federal Register / Vol. 71, No. 132 / Tuesday, July 11, 2006 / Proposed Rules Related Information (h) LBA airworthiness directive D–2005– 197, dated June 30, 2005, also addresses the subject of this AD. Issued in Burlington, Massachusetts, on July 5, 2006. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–10772 Filed 7–10–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2002–NE–40–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211–524 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede 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 proposed AD would require the same reduced IPC stage 5 disk cyclic limits, the requirement to remove from service affected disks that already exceed the new reduced cyclic limit, and to remove from service other affected disks before exceeding their cyclic limits using a drawdown schedule. This proposed AD also would exempt disks reworked to RR Service Bulletin (SB) RB.211–72–E182, Revision 1, dated July 30, 2004, and would allow an on-wing eddy current inspection (ECI) on RB211–524G and RB211–524H series engines. This proposed 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 proposing 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: We must receive any comments on this proposed AD by September 11, 2006. ADDRESSES: Use one of the following addresses to comment on this proposed AD: jlentini on PROD1PC65 with PROPOSAL SUMMARY: VerDate Aug<31>2005 16:39 Jul 10, 2006 Jkt 208001 • By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2002–NE– 40–AD, 12 New England Executive Park, Burlington, MA 01803. • By fax: (781) 238–7055. • By e-mail: 9-aneadcomment@faa.gov. You can get the service information identified in this proposed 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, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. 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. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. 2002–NE–40–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 datestamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. If a person contacts us verbally, and that contact relates to a substantive part of this proposed 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 proposed 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. Discussion On July 18, 2005, the FAA issued AD 2005–15–13, Amendment 39–14202 (70 FR 43036, July 26, 2005). That AD requires: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 39025 • Establishing new reduced IPC stage 5 disk cyclic limits. • Removing from service affected disks that already exceed the new reduced cyclic limit. • Removing from service other affected disks before exceeding their cyclic limits, using a drawdown schedule. • Allowing optional inspections at each shop visit or an on-wing ECI to extend the disk life beyond the specified life. Actions Since We Issued AD 2005–15– 13 Since we issued that AD, the manufacturer issued a new revision to ASB RB.211–72–AD428 to reference AD G–2005–0008. Relevant Service Information We have reviewed and approved the technical contents of RR ASB No. RB.211–72–AD428, Revision 5, dated March 18, 2005, that specifies a drawdown schedule for removing from service affected IPC stage 5 disks, using new RR Time Limits Manual (TLM), 05– 10–01 cyclic limits. The ASB also describes procedures for optional inspections at each shop visit to extend the disk life beyond the lives specified. The Civil Aviation Authority (CAA), the airworthiness authority of the United Kingdom (U.K.), has classified this service bulletin as mandatory and issued AD G–2005–0008 to ensure the airworthiness of these RR turbofan engines in the U.K. We have also reviewed and approved the technical contents of the following SBs: • SB No. RB.211–72–E148, dated March 13, 2003, • SB No. RB.211–72E150, Revision 1, dated June 4, 2003, and • SB No. RB.211–72–E171, Revision 1, dated February 8, 2005. These SBs provide an optional onwing ECI of the affected disks, to extend the disk life beyond the lives specified. Differences Between the Proposed AD and the Service Information This proposed AD adds a requirement to comply with the reduced cyclic life limits not later than 30 days after the effective date of this AD. Bilateral Agreement Information This engine model is manufactured in the 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 CAA has kept us informed of the situation described above. E:\FR\FM\11JYP1.SGM 11JYP1 39026 Federal Register / Vol. 71, No. 132 / Tuesday, July 11, 2006 / Proposed Rules FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. We are proposing this AD, which would require: • Establishing new reduced IPC stage 5 disk cyclic limits. • Removing from service affected disks that already exceed the new reduced cyclic limit. • Removing from service other affected disks before exceeding their cyclic limits, using a drawdown schedule. • Allowing optional inspections at each shop visit or an on-wing ECI to extend the disk life beyond the specified life. The proposed AD would require you to use the service information described previously to perform these actions. Changes to 14 CFR Part 39—Effect on the Proposed AD On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 47998, July 22, 2002), which governs the FAA’s AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions. Costs of Compliance We estimate this proposed AD would not affect any engines installed on airplanes of U.S. registry. Based on this, we estimate this proposed 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed 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. Would 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 proposal 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 Include ‘‘AD Docket No. 2002–NE–40–AD’’ in your request. ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–14202 (70 FR 43036, July 26, 2005) and by adding a new airworthiness directive, to read as follows: Rolls-Royce plc: Docket No. 2002–NE–40– AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by September 11, 2006. 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 –524B2–19 –524D4–B–19 –524G2–19 –524H2–T–19 –524B–B–02 –524B2–B–19 –524D4X–19 –524G2–T–19 –524H–36 –524B3–02 –524C2–19 –524D4X–B–19 –524G3–19 –524H–T–36 –524B4–02 –524C2–B–19 –524D4–39 –524G3–T–19 –524B4–D–02 –524D4–19 –524D4–B–39 –524H2–19 These engines are installed on, but not limited to, Boeing 747, 767, and Lockheed L– 1011 airplanes. jlentini on PROD1PC65 with PROPOSAL TABLE 2.—IPC STAGE 5 DISK P/NS AFFECTED LK60130 LK83283 UL19132 UL36821 UL36981 VerDate Aug<31>2005 LK65932 UL12290 UL20785 UL36977 UL36982 16:39 Jul 10, 2006 Jkt 208001 LK69021 UL15743 UL20832 UL36978 UL36983 PO 00000 Frm 00010 Fmt 4702 LK81269 UL15744 UL23291 UL36979 UL37078 Sfmt 4702 E:\FR\FM\11JYP1.SGM LK83282 UL15745 UL25011 UL36980 UL37079 11JYP1 39027 Federal Register / Vol. 71, No. 132 / Tuesday, July 11, 2006 / Proposed Rules TABLE 2.—IPC STAGE 5 DISK P/NS AFFECTED—Continued UL37080 UL37081 UL37082 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. UL37083 UL37084 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. dated July 30, 2004, no further action is necessary. Cycle Limits 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, (g) Comply with the reduced cyclic life limits in Table 3 of this AD or conduct qualifying nondestructive test (NDT) inspections to extend the IPC stage 5 disk life within 30 days after the effective date of this AD, but before December 1, 2008. TABLE 3.—CYCLIC LIFE LIMITS WITHOUT QUALIFYING NDT INSPECTION Engine models –524G2, G2– T, G3, G3–T, H2, H2–T, H– 36, H–T–36 Date of reduced life limit November 30, 2002 ......................................................................................... April 1, 2003 December 1, December 1, December 1, .................................................................................................... 2003 ........................................................................................... 2004 ........................................................................................... 2005 ........................................................................................... (h) On December 1, 2008, the revised cyclic life limits specified in Table 4 of this AD –524D4, D4– B, D4–B–39, D4X, D4X–B, D4–39 13,500 cyclesin-service (CIS) 13,500 CIS 12,000 CIS 11,000 CIS 11,000 CIS 16,150 CIS 16,000 CIS 16,200 CIS 13,500 13,500 13,500 12,000 13,500 13,500 12,000 12,000 14,000 14,000 12,000 12,000 become effective. Incorporate the revised cyclic life limits specified in Table 4 of this CIS CIS CIS CIS –524B2, B2– B, C2, C2–B CIS CIS CIS CIS –524B–02, B– B–02, B3–02, B4–02, B4–D– 02 CIS CIS CIS CIS AD into the RR Time Limits Manual, 05–10– 01. TABLE 4.—CYCLIC LIFE LIMITS ON DECEMBER 1, 2008 Engine models –524G2, G2– T, G3, G3–T, H2, H2–T, H– 36, H–T–36 Date of reduced life limit –524D4, D4– B, D4–B–39, D4X, D4X–B, D4–39 7,830 CIS 8,700 CIS December 1, 2008 ........................................................................................... jlentini on PROD1PC65 with PROPOSAL 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. VerDate Aug<31>2005 16:39 Jul 10, 2006 Jkt 208001 (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, reapply 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. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 –524B2, B2– B, C2, C2–B 8,900 CIS –524B–02, B– B–02, B3–02, B4–02, B4–D– 02 9,000 CIS (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. 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 and RB211– 524B4/D4 series engines, use paragraphs 3.A. E:\FR\FM\11JYP1.SGM 11JYP1 39028 Federal Register / Vol. 71, No. 132 / Tuesday, July 11, 2006 / Proposed Rules 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, and RB211–524H–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. inspection of a tail engine installation on a Lockheed L–1011 airplane). Definition of Shop Visit (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. (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 onwing (such as to perform an on-wing Cyclic Life Extension TABLE 5.—CYCLIC LIFE EXTENSION Engine models –524G2, G2– T, G3, G3–T, H2, H2–T, H– 36, H–T–36 Type of extension Extension After Passing MPI ........................................................................... Extension After Passing In-Shop ECI ............................................................. Extension After Passing On-Wing ECI ............................................................ –524D4, D4– B, D4–B–39, D4X, D4X–B, D4–39 1,600 cycles 3,800 cycles 1,000 cycles 2,000 cycles 4,500 cycles 1,200 cycles Disks That Have Been Intermixed Between Engine Models DEPARTMENT OF HOMELAND SECURITY (n) The RR Time Limits Manual, 05–00–01, contains information on intermixing disks between engine models. Coast Guard Alternative Methods of Compliance 33 CFR Part 117 (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. [CGD01–06–051] 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 jlentini on PROD1PC65 with PROPOSAL (r) CAA airworthiness directive G–2005– 0008, dated March 8, 2005, also addresses the subject of this AD. Issued in Burlington, Massachusetts, on June 30, 2006. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–10771 Filed 7–10–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 16:39 Jul 10, 2006 Jkt 208001 RIN 1625–AA09 Drawbridge Operation Regulations; Saugus River, Lynn and Revere, MA Coast Guard, DHS. Notice of proposed rulemaking. AGENCY: ACTION: The Coast Guard proposes to temporarily change the drawbridge operating regulations governing the operation of the General Edwards SR1A Bridge, at mile 1.7, across the Saugus River between Lynn and Revere, Massachusetts. This change to the drawbridge operation regulations would allow the bridge to remain in the closed position from November 1, 2006 through April 30, 2007. This action is necessary to facilitate structural maintenance at the bridge. DATES: Comments and related material must reach the Coast Guard on or before August 10, 2006. ADDRESSES: You may mail comments and related material to Commander (dpb), First Coast Guard District Bridge Branch, 408 Atlantic Avenue, Boston, Massachusetts 02110, or deliver them to the same address between 7 a.m. and 3 p.m., Monday through Friday, except, Federal holidays. The telephone number is (617) 223–8364. The First Coast Guard District, Bridge Branch, maintains the public docket for this rulemaking. Comments and material received from the public, as well as SUMMARY: PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 –524B2, B2– B, C2, C2–B 2,000 cycles 4,500 cycles 1,200 cycles –524B–02, B– B–02, B3–02, B4–02, B4–D– 02 2,000 cycles 4,500 cycles 1,200 cycles documents indicated in this preamble as being available in the docket, will become part of this docket and will be available for inspection or copying at the First Coast Guard District, Bridge Branch, between 7 a.m. and 3 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: Mr. John McDonald, Project Officer, First Coast Guard District, (617) 223–8364. SUPPLEMENTARY INFORMATION: Request or Comments We encourage you to participate in this rulemaking by submitting comments and related material. If you do so, please include your name and address, identify the docket number for this rulemaking (CGD01–06–051), indicate the specific section of this document to which each comment applies, and give the reason for each comment. Please submit all comments and related material in an unbound format, no larger than 81⁄2 by 11 inches, suitable for copying. If you would like to know if they reached us, please enclose a stamped, self-addressed postcard or envelope. We will consider all comments and material received during the comment period. We may change this proposed rule in view of them. Public Meeting We do not now plan to hold a public meeting; however, you may submit a request for a meeting by writing to the First Coast Guard District, Bridge Branch, at the address under ADDRESSES explaining why one would be beneficial. If we determine that one would aid this rulemaking, we will hold E:\FR\FM\11JYP1.SGM 11JYP1

Agencies

[Federal Register Volume 71, Number 132 (Tuesday, July 11, 2006)]
[Proposed Rules]
[Pages 39025-39028]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-10771]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-40-AD]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc RB211-524 Series
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede 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 proposed AD would require the same
reduced IPC stage 5 disk cyclic limits, the requirement to remove from
service affected disks that already exceed the new reduced cyclic
limit, and to remove from service other affected disks before exceeding
their cyclic limits using a drawdown schedule. This proposed AD also
would exempt disks reworked to RR Service Bulletin (SB) RB.211-72-E182,
Revision 1, dated July 30, 2004, and would allow an on-wing eddy
current inspection (ECI) on RB211-524G and RB211-524H series engines.
This proposed 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 proposing 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: We must receive any comments on this proposed AD by September
11, 2006.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2002-NE-40-AD, 12 New England Executive Park, Burlington, MA 01803.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information identified in this proposed 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, by appointment, at the FAA, New
England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA.

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.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2002-NE-40-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 proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed 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 proposed 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.

Discussion

On July 18, 2005, the FAA issued AD 2005-15-13, Amendment 39-14202
(70 FR 43036, July 26, 2005). That AD requires:
Establishing new reduced IPC stage 5 disk cyclic limits.
Removing from service affected disks that already exceed
the new reduced cyclic limit.
Removing from service other affected disks before
exceeding their cyclic limits, using a drawdown schedule.
Allowing optional inspections at each shop visit or an on-
wing ECI to extend the disk life beyond the specified life.

Actions Since We Issued AD 2005-15-13

Since we issued that AD, the manufacturer issued a new revision to
ASB RB.211-72-AD428 to reference AD G-2005-0008.

Relevant Service Information

We have reviewed and approved the technical contents of RR ASB No.
RB.211-72-AD428, Revision 5, dated March 18, 2005, that specifies a
drawdown schedule for removing from service affected IPC stage 5 disks,
using new RR Time Limits Manual (TLM), 05-10-01 cyclic limits. The ASB
also describes procedures for optional inspections at each shop visit
to extend the disk life beyond the lives specified. The Civil Aviation
Authority (CAA), the airworthiness authority of the United Kingdom
(U.K.), has classified this service bulletin as mandatory and issued AD
G-2005-0008 to ensure the airworthiness of these RR turbofan engines in
the U.K. We have also reviewed and approved the technical contents of
the following SBs:
SB No. RB.211-72-E148, dated March 13, 2003,
SB No. RB.211-72E150, Revision 1, dated June 4, 2003, and
SB No. RB.211-72-E171, Revision 1, dated February 8, 2005.
These SBs provide an optional on-wing ECI of the affected disks, to
extend the disk life beyond the lives specified.

Differences Between the Proposed AD and the Service Information

This proposed AD adds a requirement to comply with the reduced
cyclic life limits not later than 30 days after the effective date of
this AD.

Bilateral Agreement Information

This engine model is manufactured in the 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 CAA has kept us informed of the situation
described above.

[[Page 39026]]

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would
require:
Establishing new reduced IPC stage 5 disk cyclic limits.
Removing from service affected disks that already exceed
the new reduced cyclic limit.
Removing from service other affected disks before
exceeding their cyclic limits, using a drawdown schedule.
Allowing optional inspections at each shop visit or an on-
wing ECI to extend the disk life beyond the specified life.
The proposed AD would require you to use the service information
described previously to perform these actions.

Changes to 14 CFR Part 39--Effect on the Proposed AD

On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR
47998, July 22, 2002), which governs the FAA's AD system. This
regulation now includes material that relates to altered products,
special flight permits, and alternative methods of compliance. This
material previously was included in each individual AD. Since this
material is included in 14 CFR part 39, we will not include it in
future AD actions.

Costs of Compliance

We estimate this proposed AD would not affect any engines installed
on airplanes of U.S. registry. Based on this, we estimate this proposed
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
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. Would 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 proposal 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. 2002-NE-40-AD'' in your request.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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]

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, to
read as follows:

Rolls-Royce plc: Docket No. 2002-NE-40-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by September
11, 2006.

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 airplanes.

Table 2.--IPC Stage 5 Disk P/Ns Affected
----------------------------------------------------------------------------------------------------------------

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

[[Page 39027]]

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 or conduct qualifying nondestructive test (NDT) inspections
to extend the IPC stage 5 disk life within 30 days after the
effective date of this AD, but before December 1, 2008.

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

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 and RB211-524B4/D4 series engines, use
paragraphs 3.A.

[[Page 39028]]

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, and RB211-524H-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 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,
G3, G3-T, H2, -524D4, D4-B, -524B2, B2-B, -524B-02, B-B-
Type of extension H2-T, H-36, H- D4-B-39, D4X, C2, C2-B 02, B3-02, B4-
T-36 D4X-B, D4-39 02, B4-D-02
----------------------------------------------------------------------------------------------------------------
Extension After Passing MPI..................... 1,600 cycles 2,000 cycles 2,000 cycles 2,000 cycles
Extension After Passing In-Shop ECI............. 3,800 cycles 4,500 cycles 4,500 cycles 4,500 cycles
Extension After Passing On-Wing ECI............. 1,000 cycles 1,200 cycles 1,200 cycles 1,200 cycles
----------------------------------------------------------------------------------------------------------------

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.

Issued in Burlington, Massachusetts, on June 30, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-10771 Filed 7-10-06; 8:45 am]
BILLING CODE 4910-13-P

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