Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines, 18862-18865 [E7-7032]

Download as PDF 18862 Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations system, there is not a direct mechanical link between the airplane flight control surface and the pilot’s cockpit control device as there is on more conventional airplanes. Instead, a flight control computer commands the airplane flight control surfaces, based on input received from the cockpit control device. The pilot input is modified by the flight control computer—based on the current airplane flight parameters— before the command is given to the flight control surface. Discussion The formulation of airplane design load conditions in 14 CFR part 25 is based on the assumption that the airplane is equipped with a control system in which there is a direct mechanical linkage between the pilot’s cockpit control and the control surface. Thus, for roll maneuvers, the regulation specifies a displacement for the aileron itself and does not envision any modification of the pilot’s control input. Since such a system will affect the airplane flight loads and thus the structural strength of the airplane, special conditions appropriate for this type of control system are needed. In particular, the special condition adjusts the design roll maneuver requirements specified in § 25.349(a), so that they take into account the effect of the Falcon 7X’s electronic flight control computer on the control surface deflection. The special condition requires that the roll maneuver be performed by deflection of the cockpit roll control, as opposed to specifying a deflection of the aileron itself as the current regulation does. The deflection of the control surface would then be determined from the cockpit input, based on the computer’s flight control laws and the current airplane flight parameters. cprice-sewell on PROD1PC66 with RULES Applicability As discussed above, these special conditions are applicable to the Dassault Aviation Model Falcon 7X. Should Dassault Aviation apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features of the Dassault Aviation Model Falcon 7X of airplane. It is not a rule of general applicability. The substance of these special conditions has been subjected to the notice and comment period in several VerDate Aug<31>2005 15:00 Apr 13, 2007 Jkt 211001 prior instances and has been derived without substantive change from those previously issued. It is unlikely that public comment would result in a significant change from the substance contained herein. Therefore, because a delay would significantly affect the certification of the airplane, which is imminent, the FAA has determined that prior public notice and comment are unnecessary and impracticable and that good cause exists for adopting these special conditions upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. I The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions I Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Dassault Aviation Model Falcon 7X airplanes. Design Roll Maneuvering Conditions In lieu of compliance with 14 CFR 25.349(a), the following special conditions apply: Maneuvering: The following conditions, speeds and cockpit roll control motions (except as the motions may be limited by pilot effort) must be considered in combination with an airplane load factor of zero and the twothirds of limit positive maneuvering load factor. In determining the resulting control surface deflections, the torsional flexibility of the wing must be considered in accordance with 14 CFR 25.301(b): (1) Conditions corresponding to maximum steady rolling velocities and conditions corresponding to maximum angular accelerations must be investigated. For the angular acceleration conditions, zero rolling velocity may be assumed in the absence of a rational time history investigation of the maneuver. (2) At VA, movement of the cockpit roll control up to the limit is assumed. The position of the cockpit roll control must be maintained until a steady roll rate is achieved and then must be returned suddenly to the neutral position. (3) At VC, the cockpit roll control must be moved suddenly and PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 maintained so as to achieve a roll rate not less than that obtained in subparagraph (2) of this paragraph. (4) At VD, the cockpit roll control must be moved suddenly and maintained so as to achieve a roll rate not less than one third of that obtained in sub-paragraph (2) of this paragraph. Issued in Renton, Washington, on April 4, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 07–1809 Filed 4–13–07; 8:45 am] BILLING CODE 4910–13–M 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: 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 corrosioninduced uncontained disc assembly failure, resulting in damage to the airplane. E:\FR\FM\16APR1.SGM 16APR1 Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations 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. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Rolls-Royce 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: ian.dargin@faa.gov; 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. cprice-sewell on PROD1PC66 with RULES DATES: 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 VerDate Aug<31>2005 15:00 Apr 13, 2007 Jkt 211001 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 corrosioninduced 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: • 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. 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: PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 18863 • Removing affected disc assemblies from service; and • Re-machining, inspecting, and applying anticorrosion protection; and • Re-marking, and returning disc assemblies into service; and • 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 https:// dms.dot.gov, 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 https://dms.dot.gov. 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 E:\FR\FM\16APR1.SGM 16APR1 18864 Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations 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 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: I PART 39—AIRWORTHINESS DIRECTIVES 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 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 new airworthiness directive, Amendment 39–15026, to read as follows: [Amended] (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 2. The FAA amends § 39.13 by removing Amendment 39–14609 (71 FR 29586, May 23, 2006) and by adding a I (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 Rework band for cyclic life accumulated on disc assemblies P/Ns LK46210 and LK58278 (Pre RR Service Bulletin (SB) No. RB.211– 72–5420) cprice-sewell on PROD1PC66 with RULES Engine model –22B series ................................................................................................................ –535E4 series ............................................................................................................ –524B–02, B–B–02, B3–02, and B4 series, Pre and Post accomplishment of SB No. 72–7730 ........................................................................................................... –524B2 and C2 series, Pre SB No. 72–7730 ........................................................... VerDate Aug<31>2005 15:00 Apr 13, 2007 Jkt 211001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Rework band for cyclic life accumulated on disc assembly P/N LK67634 (pre RR SB No. RB.211– 72–5420) Rework band for cyclic life accumulated on P/Ns LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 disc assemblies (pre RR SB No. RB.211– 72–9434) 4,000–6,200 N/A 7,000–10,000 N/A 11,500–14,000 9,000–15,000 4,000–6,000 4,000–6,000 7,000–9,000 7,000–9,000 11,500–14,000 11,500–14,000 E:\FR\FM\16APR1.SGM 16APR1 18865 Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Rules and Regulations TABLE 1.—AFFECTED HPC STAGE 3 DISC ASSEMBLIES—Continued Rework band for cyclic life accumulated on disc assemblies P/Ns LK46210 and LK58278 (Pre RR Service Bulletin (SB) No. RB.211– 72–5420) Engine model –524B2–B–19 and C2–B–19, SB No. 72–7730 ........................................................ –524D4 series, Pre SB No. 72–7730 ........................................................................ –524D4–B series, SB No. 72–7730 .......................................................................... –524G2, G3, H, and H2 series .................................................................................. cprice-sewell on PROD1PC66 with RULES (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 VerDate Aug<31>2005 15:00 Apr 13, 2007 Jkt 211001 Rework band for cyclic life accumulated on disc assembly P/N LK67634 (pre RR SB No. RB.211– 72–5420) Rework band for cyclic life accumulated on P/Ns LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 disc assemblies (pre RR SB No. RB.211– 72–9434) 4,000–6,000 4,000–6,000 4,000–6,000 4,000–6,000 7,000–9,000 7,000–9,000 7,000–9,000 7,000–9,000 8,500–11,000 11,500–14,000 8,500–11,000 8,500–11,000 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 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 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: https://www.archives.gov/federalregister/cfr/ibr-locations.html. (k) Contact Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: ian.dargin@faa.gov; 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] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30545; Amdt. No. 3214] Standard Instrument Approach Procedures, Weather Takeoff Minimums; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: This amendment establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and/or Weather Takeoff Minimums for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, addition of new obstacles, or changes in air traffic E:\FR\FM\16APR1.SGM 16APR1

Agencies

[Federal Register Volume 72, Number 72 (Monday, April 16, 2007)]
[Rules and Regulations]
[Pages 18862-18865]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[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.

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

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.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Rolls-Royce 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:
ian.dargin@faa.gov; 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:
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.
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:
Removing affected disc assemblies from service; and
Re-machining, inspecting, and applying anticorrosion
protection; and
Re-marking, and returning disc assemblies into service;
and
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 https://
dms.dot.gov, 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
https://dms.dot.gov.

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
----------------------------------------------------------------------------------------------------------------
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)
----------------------------------------------------------------------------------------------------------------
-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
----------------------------------------------------------------------------------------------------------------

(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: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
(k) Contact Ian Dargin, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: ian.dargin@faa.gov;
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]
BILLING CODE 4910-13-P

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