Airworthiness Directives; Rolls-Royce plc RB211-524 and -535 Series Turbofan Engines, 38002-38004 [E7-13410]

Download as PDF 38002 Federal Register / Vol. 72, No. 133 / Thursday, July 12, 2007 / Rules and Regulations Affected ADs (b) None. Applicability (c) This AD applies to Honeywell CAS67A ACAS II systems that are installed on, but not limited to, DORNIER LUFTFAHRT GmbH Models Dornier 228–100, Dornier 228–101, Dornier 228–200, Dornier 228–201, and Dornier 228–212 airplanes that: (1) Had Supplemental Type Certificate No. SA1310 installed prior to January 31, 2005; and (2) are certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 34: Navigation. Reason (e) The mandatory continuing airworthiness information (MCAI) states: It was detected by the STC holder that in earlier installations of the ACASII system there were no isolation diodes installed in the Heading and Attitude Valid lines. The absence of an isolation diode in the valid lines can prevent the valid flag to come up even if a gyro fault exists. The problem has only been detected for Heading Valid lines but could equally affect the Attitude Valid lines. With installation of the ACASII, the heading and attitude valid lines have to be connected to the TPU67A. On valid state, the signals are +28VDC. On invalid, the signals are open. This condition of direct connection (without an isolation diode installed) of the valid lines to the TPU67A, if not corrected, could cause the TPU67A to feed current into the open stated valid lines. This prevents the flag to appear even if the gyro is invalid, providing the flight crew with erroneous navigation information. For the reasons stated above, this Airworthiness Directive (AD) requires the installation of isolation diodes into the signal lines to the TPU67A to prevent reverse feed of the valid lines. Actions and Compliance (f) Unless already done, within the next 100 hours time-in-service (TIS) after August 16, 2007 (the effective date of this AD), modify the Honeywell CAS67A ACASII System Installation following Aerotechnic Vertiebs -u. Service GmbH Service Bulletin No. DO228–119780–0104, Revision 2, dated December 21, 2006. FAA AD Differences cprice-sewell on PROD1PC71 with RULES Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the VerDate Aug<31>2005 14:27 Jul 11, 2007 Jkt 211001 procedures found in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2007–0059, dated March 5, 2007, and Aerotechnic Vertiebs -u. Service GmbH Service Bulletin No. DO228–119780–0104, Revision 2, dated December 21, 2006, for related information. Material Incorporated by Reference (i) You must use Aerotechnic Vertiebs -u. Service GmbH Service Bulletin No. DO228– 119780–0104 Revision 2, dated December 21, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact AEROTECHNIC Vertriebsund Service GmbH, Baden Airpark, Montreal Avenue D425, 77836 Rheinmuenster; telephone: +49 7229 66 2400; facsimile: +49 7229 66 2409. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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. Issued in Kansas City, Missouri, on June 29, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–13249 Filed 7–11–07; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24325; Directorate Identifier 2006–NE–10–AD; Amendment 39– 15129; AD 2007–14–07] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211–524 and –535 Series Turbofan Engines Federal Aviation Administration (FAA), Department ofTransportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211–524 and –535 series turbofan engines. This AD requires initial and repetitive fluorescent penetrant inspections (FPI) of the high pressure (HP) compressor stage 1 and 2 rotor discs for cracks. This AD results from reports of low-cyclefatigue cracks found at overhaul in the interface weld between the HP compressor stage 1 and 2 rotor disc. We are issuing this AD to prevent uncontained engine failure and damage to the airplane. DATES: This AD becomes effective August 16, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of August 16, 2007. ADDRESSES: You can get the service information identified in this AD from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011–44– 1332–242424; fax: 011–44–1332– 249936. The Docket Operations office is located at the U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. 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: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to certain RR RB211–524 and –535 series turbofan engines. We published the proposed AD in the Federal Register on September 25, 2006 (71 FR 57449). That action proposed to require initial and repetitive FPI and E:\FR\FM\12JYR1.SGM 12JYR1 Federal Register / Vol. 72, No. 133 / Thursday, July 12, 2007 / Rules and Regulations borescope inspections of the HP compressor stage 1 and 2 rotor discs for cracks. economic burden on any operator nor increase the scope of the AD. Examining the AD Docket We estimate that this AD will affect 884 RB211–524 and –535 series turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about 2 work-hours per engine to perform the inspections, and that the average labor rate is $80 per work-hour. Based on these figures, we estimate the total cost to U.S. operators of performing one inspection on all of the engines, to be $141,440. You may examine the AD docket on the Internet at https://dms.dot.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Unrealistic Compliance Time Rolls-Royce plc states that the compliance time of 30 days after the effective date of the AD as specified in the proposed AD, is unrealistic and would be an unacceptable burden to operators. We agree. We changed paragraph (f) to read ‘‘At the next shop visit after the effective date of this AD, perform an initial fluorescent penetrant inspection (FPI) and borescope inspection of the HP compressor stage 1 and 2 discs for cracks.’’ Borescope Inspection Requirement Rolls-Royce plc also states that in their Alert Service Bulletin (ASB) No. RB.211–72–AE359, Revision 1, dated November 17, 2005, there is no requirement for performing borescope inspections. We do not agree. That ASB requires borescope inspections per paragraphs 3A(3) through 3A(4)(o)(i). We did not change the AD. Correction to the Applicability Since we issued the proposed AD, we found that we overlooked listing an applicable engine model, model RB211– 524D4–B–19. We investigated and found that no U. S. operators currently operate airplanes with this engine model. We added this model number to this AD to complete the applicability listing. cprice-sewell on PROD1PC71 with RULES Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the VerDate Aug<31>2005 14:27 Jul 11, 2007 Jkt 211001 Costs of Compliance Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 38003 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2007–14–07 Rolls-Royce plc: Amendment 39–15129; Docket No. FAA–2006–24325; Directorate Identifier 2006–NE–10–AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 16, 2007. Affected ADs (b) None. Applicability (c) This AD applies to the following RollsRoyce plc (RR) RB211–524 and –535 series turbofan engines: –524B2–19 –524C2–B–19 –524B–02 –524D4X–19 –524B3–02 –524D4X–B–19 –524C2–19 –524G2–19 –524B4–02 –524G3–19 –524B4–D–02 –524H–36 –524D4–19 –524H2–19 –524D4–39 –535E4–37 –524B–B–02 –535E4–B–37 –524B2–B–19 –535E4–C–37 –524D4–B–19 –535E4–B–75 –524D4–B–39 –535C–37 These engines are installed on, but not limited to, Boeing 747, 757, 767 series, Lockheed L–1011 series, and Tupolev Tu204 airplanes. Unsafe Condition (d) This AD results from reports of lowcycle fatigue cracks found at overhaul in the interface weld between the high pressure (HP) compressor stage 1 and 2 rotor discs. We are issuing this AD to prevent uncontained engine failure and 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. Initial and Repetitive Inspections (f) At the next shop visit after the effective date of this AD, perform an initial fluorescent penetrant inspection (FPI) and borescope inspection of the HP compressor stage 1 and 2 discs for cracks. E:\FR\FM\12JYR1.SGM 12JYR1 38004 Federal Register / Vol. 72, No. 133 / Thursday, July 12, 2007 / Rules and Regulations (g) Thereafter, at every engine shop visit, perform repetitive FPIs and borescope inspections of HP compressor stage 1 and 2 rotor discs for cracks. (h) Use paragraphs 3.A.(1) through 3.A.(4)(o) of the Accomplishment Instructions of RR Alert Service Bulletin (ASB) No. RB.211–72–AE359, Revision 1, dated November 17, 2005, to do the inspections. (i) Accept or reject as necessary, HP compressor stage 1 and 2 rotor discs using inspection criteria paragraphs 3.A.(5)(a) through 3.A.(5)(f) of the Accomplishment Instructions of RR ASB No. RB.211–72– AE359, Revision 1, dated November 17, 2005. Definition (j) For the purpose of this AD, an engine shop visit is defined as anytime the HP compressor stage 1 and 2 rotor discs are removed from the HP compressor stage 3 disc. Reporting Requirements (k) Within 10 days, report inspection findings of cracks to the RR local field service office representative. The Office of Management and Budget has approved the reporting requirements specified in paragraph 3.A.(6)(b) of the Accomplishment Instructions of RR ASB No. RB.211–72– AE359, Revision 1, dated November 17, 2005, and assigned OMB control number 2120– 0056. Alternative Methods of Compliance (l) 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 (m) United Kingdom Civil Aviation Authority airworthiness directive No. G– 2005–0028 R1, dated October 18, 2005, also addresses the subject of this AD. cprice-sewell on PROD1PC71 with RULES Material Incorporated by Reference (n) You must use Rolls-Royce plc Alert Service Bulletin No. RB.211–72–AE359, Revision 1, dated November 17, 2005, to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011–44–1332–242424; fax: 011– 44–1332–249936, for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html. VerDate Aug<31>2005 14:27 Jul 11, 2007 Jkt 211001 Issued in Burlington, Massachusetts, on July 3, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–13410 Filed 7–11–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26353; Directorate Identifier 2006–NM–189–AD; Amendment 39–15124; AD 2007–14–02] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–1A11 (CL–600), CL– 600–2A12 (CL–601), CL–600–2B16 (CL– 601–3A, CL–601–3R, and CL–604) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL–600–1A11 (CL– 600), CL–600–2A12 (CL–601), and CL– 600–2B16 (CL–601–3A, CL–601–3R, and CL–604) airplanes. This AD requires inspecting to identify the part number and serial number of the selector valves of the nose landing gear (NLG) and the nose gear door, and doing related investigative and corrective actions if necessary. This AD results from reports of uncommanded partial retractions of the NLG. We are issuing this AD to prevent internal leakage of the selector valve, which, under certain conditions, could result in an uncommanded retraction of the NLG with consequent damage to the airplane and possible serious injury to ground personnel. DATES: This AD becomes effective August 16, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 16, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service information identified in this AD. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 FOR FURTHER INFORMATION CONTACT: Daniel Parrillo, Aerospace Engineer, Systems and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7305; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located on the ground floor of the West Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Bombardier Model CL–600–1A11 (CL– 600), CL–600–2A12 (CL–601), and CL– 600–2B16 (CL–601–3A, CL–601–3R, and CL–604) airplanes. That supplemental NPRM was published in the Federal Register on April 26, 2007 (72 FR 20777). That supplemental NPRM proposed to require inspecting to identify the part number and serial number of the selector valves of the nose landing gear (NLG) and the nose gear door, and doing related investigative and corrective actions if necessary. That supplemental NPRM also proposed to add airplanes to the applicability. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been received on the supplemental NPRM or on the determination of the cost to the public. Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any E:\FR\FM\12JYR1.SGM 12JYR1

Agencies

[Federal Register Volume 72, Number 133 (Thursday, July 12, 2007)]
[Rules and Regulations]
[Pages 38002-38004]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13410]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24325; Directorate Identifier 2006-NE-10-AD; 
Amendment 39-15129; AD 2007-14-07]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-524 and -535 
Series Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Rolls-Royce plc (RR) RB211-524 and -535 series turbofan 
engines. This AD requires initial and repetitive fluorescent penetrant 
inspections (FPI) of the high pressure (HP) compressor stage 1 and 2 
rotor discs for cracks. This AD results from reports of low-cycle-
fatigue cracks found at overhaul in the interface weld between the HP 
compressor stage 1 and 2 rotor disc. We are issuing this AD to prevent 
uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective August 16, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of August 16, 2007.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 
011-44-1332-242424; fax: 011-44-1332-249936.
    The Docket Operations office is located at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

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: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to certain RR RB211-524 and 
-535 series turbofan engines. We published the proposed AD in the 
Federal Register on September 25, 2006 (71 FR 57449). That action 
proposed to require initial and repetitive FPI and

[[Page 38003]]

borescope inspections of the HP compressor stage 1 and 2 rotor discs 
for cracks.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone (800) 647-5527) is provided in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

Comments

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

Unrealistic Compliance Time

    Rolls-Royce plc states that the compliance time of 30 days after 
the effective date of the AD as specified in the proposed AD, is 
unrealistic and would be an unacceptable burden to operators. We agree. 
We changed paragraph (f) to read ``At the next shop visit after the 
effective date of this AD, perform an initial fluorescent penetrant 
inspection (FPI) and borescope inspection of the HP compressor stage 1 
and 2 discs for cracks.''

Borescope Inspection Requirement

    Rolls-Royce plc also states that in their Alert Service Bulletin 
(ASB) No. RB.211-72-AE359, Revision 1, dated November 17, 2005, there 
is no requirement for performing borescope inspections. We do not 
agree. That ASB requires borescope inspections per paragraphs 3A(3) 
through 3A(4)(o)(i). We did not change the AD.

Correction to the Applicability

    Since we issued the proposed AD, we found that we overlooked 
listing an applicable engine model, model RB211-524D4-B-19. We 
investigated and found that no U. S. operators currently operate 
airplanes with this engine model. We added this model number to this AD 
to complete the applicability listing.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 884 RB211-524 and -535 series 
turbofan engines installed on airplanes of U.S. registry. We also 
estimate that it will take about 2 work-hours per engine to perform the 
inspections, and that the average labor rate is $80 per work-hour. 
Based on these figures, we estimate the total cost to U.S. operators of 
performing one inspection on all of the engines, to be $141,440.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2007-14-07 Rolls-Royce plc: Amendment 39-15129; Docket No. FAA-2006-
24325; Directorate Identifier 2006-NE-10-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
16, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following Rolls-Royce plc (RR) RB211-
524 and -535 series turbofan engines:

-524B2-19                            -524C2-B-19
-524B-02                             -524D4X-19
-524B3-02                            -524D4X-B-19
-524C2-19                            -524G2-19
-524B4-02                            -524G3-19
-524B4-D-02                          -524H-36
-524D4-19                            -524H2-19
-524D4-39                            -535E4-37
-524B-B-02                           -535E4-B-37
-524B2-B-19                          -535E4-C-37
-524D4-B-19                          -535E4-B-75
-524D4-B-39                          -535C-37
 

    These engines are installed on, but not limited to, Boeing 747, 
757, 767 series, Lockheed L-1011 series, and Tupolev Tu204 
airplanes.

Unsafe Condition

    (d) This AD results from reports of low-cycle fatigue cracks 
found at overhaul in the interface weld between the high pressure 
(HP) compressor stage 1 and 2 rotor discs. We are issuing this AD to 
prevent uncontained engine failure and 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.

Initial and Repetitive Inspections

    (f) At the next shop visit after the effective date of this AD, 
perform an initial fluorescent penetrant inspection (FPI) and 
borescope inspection of the HP compressor stage 1 and 2 discs for 
cracks.

[[Page 38004]]

    (g) Thereafter, at every engine shop visit, perform repetitive 
FPIs and borescope inspections of HP compressor stage 1 and 2 rotor 
discs for cracks.
    (h) Use paragraphs 3.A.(1) through 3.A.(4)(o) of the 
Accomplishment Instructions of RR Alert Service Bulletin (ASB) No. 
RB.211-72-AE359, Revision 1, dated November 17, 2005, to do the 
inspections.
    (i) Accept or reject as necessary, HP compressor stage 1 and 2 
rotor discs using inspection criteria paragraphs 3.A.(5)(a) through 
3.A.(5)(f) of the Accomplishment Instructions of RR ASB No. RB.211-
72-AE359, Revision 1, dated November 17, 2005.

Definition

    (j) For the purpose of this AD, an engine shop visit is defined 
as anytime the HP compressor stage 1 and 2 rotor discs are removed 
from the HP compressor stage 3 disc.

Reporting Requirements

    (k) Within 10 days, report inspection findings of cracks to the 
RR local field service office representative. The Office of 
Management and Budget has approved the reporting requirements 
specified in paragraph 3.A.(6)(b) of the Accomplishment Instructions 
of RR ASB No. RB.211-72-AE359, Revision 1, dated November 17, 2005, 
and assigned OMB control number 2120-0056.

Alternative Methods of Compliance

    (l) 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

    (m) United Kingdom Civil Aviation Authority airworthiness 
directive No. G-2005-0028 R1, dated October 18, 2005, also addresses 
the subject of this AD.

Material Incorporated by Reference

    (n) You must use Rolls-Royce plc Alert Service Bulletin No. 
RB.211-72-AE359, Revision 1, dated November 17, 2005, to perform the 
inspections required by this AD. The Director of the Federal 
Register approved the incorporation by reference of this service 
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; 
telephone: 011-44-1332-242424; fax: 011-44-1332-249936, for a copy 
of this service information. You may review copies at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on July 3, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-13410 Filed 7-11-07; 8:45 am]
BILLING CODE 4910-13-P
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