Airworthiness Directives; Rolls-Royce Corporation AE 3007A and AE 3007C Series Turbofan Engines, 14724-14727 [E7-5775]

Download as PDF 14724 Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules maintenance program manual, the general revisions may be inserted in the applicable maintenance program manual and the copy of the task may be removed from the maintenance program manual. TABLE 1.—TASKS To the program support manual (PSM)— Task— Dated— Dash 8 Series 100 Maintenance Task Card 3210/15. Dash 8 Series 200 Maintenance Task Card 3210/15. Dash 8 Series 300 Maintenance Task Card 3210/15. June 22, 2005 ........................................ 1–8–7 DHC–8–100 Series Airplanes. June 22, 2005 ........................................ 1–82–7 DHC–8–200 Series Airplanes. November 29, 2005 ............................... 1–83–7 DHC–8–300 Series Airplanes. Parts Installation (h) After the effective date of this AD, no person may install a part identified in paragraphs (h)(1) and (h)(2) of this AD, as a replacement during the repair or overhaul of any shock strut assembly, on any airplane. (1) Upper bearing, part number 10130–3 or 10130–551. (2) Damper ring, part number 10129–3 or 10129–551. (i) After the effective date of this AD, only the parts identified in paragraphs (i)(1) and (i)(2) of this AD may be installed on any airplane as replacement upper bearings and damper rings during the repair or overhaul of any shock strut assembly, except as provided by paragraph (j) of this AD. (1) Upper bearing, part number 10130–5. (2) Damper ring, part number 10129–5 or 10129–533. (j) After the effective date of this AD, only MLGs with a reworked, oversize cylinder bore (part number identified in the applicable component maintenance manual (CMM)) that have parts identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD used in accordance with the applicable CMM may be installed on any airplane. (1) Upper bearing, part number CRS85– 167–11. (2) Damper ring, part number CRS85–167– 31 or CRS85–167–33. (3) Seal carrier, part number CRS85–167– 21. pwalker on PROD1PC71 with PROPOSALS Credit for Actions Done Using Previous Service Information (k) Modifications accomplished before the effective date of this AD in accordance with Bombardier Service Bulletin 8–32–144, dated August 10, 1998, including Messier-Dowty Service Bulletin M–DT SBDCH8–32–82, dated March 9, 1998, are considered acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA VerDate Aug<31>2005 18:15 Mar 28, 2007 Jkt 211001 Flight Standards Certificate Holding District Office. Related Information (m) Canadian airworthiness directive CF– 2006–14, effective July 21, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on March 20, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–5668 Filed 3–28–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–26966; Directorate Identifier 99–NE–01–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation AE 3007A and AE 3007C Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for Rolls-Royce Corporation (RRC) AE 3007A and AE 3007C series turbofan engines. That AD currently prohibits any flight following a ground engine start where the engine oil temperature is below 32 °F (0 °C), unless certain preflight operational procedures are followed. This proposed AD would also require those actions, and would also require a terminating action. This proposed AD would supersede the compliance requirements of AD 99–02–51 and all related alternative methods of compliance (AMOCs). This proposed AD results from design improvements to PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 For model— components in the accessory gearbox air turbine starter mounting pad. We are proposing this AD to prevent an inflight engine shutdown due to loss of engine oil from the starter shaft seal. DATES: We must receive any comments on this proposed AD by May 29, 2007. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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 Corporation, P.O. Box 420, Indianapolis, IN 46206; telephone (317) 230–3774; fax (317) 230–8084; e-mail: indy.pubs.services@rolls-royce.com, to get the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer, Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; telephone (847) 294–7836; fax (847) 294–7834. 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 ‘‘Docket No. FAA– E:\FR\FM\29MRP1.SGM 29MRP1 Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules 2007–26966; Directorate Identifier 99– NE–01–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// 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 proposed AD. Using the search function of the DMS Web site, anyone can find and read the comments in any of our dockets, including 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 http:// dms.dot.gov. Examining the AD Docket You may examine the docket that contains the proposal, any comments received and any final disposition in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. pwalker on PROD1PC71 with PROPOSALS Docket Number Change We are transferring the docket for this proposed AD to the Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA–2007–26966. The old Docket No. became the Directorate Identifier, which is 99–NE– 01–AD. Discussion On March 29, 1999, we issued AD 99– 02–51, Amendment 39–11108 (64 FR 16339, April 5, 1999), applicable to RRC AE 3007A and AE 3007C series turbofan engines. That AD prohibits any flight following a ground engine start where the engine oil temperature is below 32 °F (0 °C), unless certain preflight operational procedures are followed to ensure that there is no excessive loss of oil from leakage at the air turbine starter shaft. That action resulted from reports VerDate Aug<31>2005 18:15 Mar 28, 2007 Jkt 211001 14725 of in-flight engine shutdowns attributed to loss of engine oil from the starter shaft seal. Since we issued AD 99–02–51, RRC, Cessna Aircraft Company, and Empresa Brasileira de Aeronautica S.A. (EMBRAER) issued Service Bulletins (SBs) that describe a procedure to install a cap on the accessory gearbox starter pad drain fitting to prevent rapid engine oil loss during flight. These SBs were approved in 1999 as AMOCs to the requirements of AD 99–02–51. In September 2001, RRC developed singleand multi-orifice restrictors that were approved for use also as an AMOC that replaced the drain fitting cap in the previous AMOCs. RRC has since improved the design for the multiorifice restrictor which is also approved as an AMOC. Since we approved these AMOCs, RRC released an improved seal for the accessory gearbox air turbine starter mounting pad. On January 19, 2006, we approved a terminating action AMOC incorporating the improved seal. That AMOC requires no cap or restrictor on the starter drain, but does not require removal of those components either. This proposed AD would mandate the removal of the AMOC configurations incorporating caps or restrictors and the installation of an open drain adapter. preflight operational procedures are followed to ensure that there is no excessive loss of oil from leakage at the air turbine starter shaft; and • Require terminating action to the prohibition requirements of the existing AD, by removing from service certain seal P/Ns from the accessory gearbox air turbine starter mounting pad and installing an improved seal; and • Require removing certain P/N drain caps, drain adapters, and orifice inserts, and installing an open adapter on the starter pad drain. The proposed AD would require that you do these actions using the service information described previously. Relevant Service Information We have reviewed and approved the technical contents of the following RRC SBs: • SB No. AE 3007A–72–321 AE 3007C–72–250, Revision 2, which describes procedures for installing an improved starter shaft seal. • SB No. AE 3007C–72–223, Revision 1, and SB No. AE 3007A–72–330, Revision 1, which describe procedures for installing an open starter drain adapter. • SB No. AE 3007A–72–274, Revision 1, which describes procedures for removing the drain cap or starter drain adapter on AE 3007A series engines. The SB issue dates do not appear in this proposed AD because we agreed to allow RRC to assign the final rule AD issue date to them, as they want to reference the AD number in the SBs. Authority for This Rulemaking 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: • Prohibit before further flight, any flight following a ground engine start where the engine oil temperature is below 32 °F (0 °C), unless certain PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 Costs of Compliance We estimate that this proposed AD would affect 1,868 RRC AE 3007A and AE 3007C series turbofan engines installed on aircraft of U.S. registry. We also estimate that it would take about 4 work-hours per engine to perform the proposed terminating action, and that the average labor rate is $80 per workhour. Required parts would cost about $2,917 per engine. Based on these figures, if all engines incorporated the terminating action, we estimate the total cost of the proposed AD to U.S. operators to be $6,046,100. 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 E:\FR\FM\29MRP1.SGM 29MRP1 14726 Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed 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. 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 regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. Affected ADs (b) This AD supersedes AD 99–02–51, Amendment 39–11108. List of Subjects in 14 CFR Part 39 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. 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 39–11108 (64 FR 16339, April 5, 1999) and by adding a new airworthiness directive to read as follows: Rolls-Royce Corporation (formerly Allison Engine Company, Inc.): Docket No. FAA–2007–26966; Directorate Identifier 99–NE–01–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by May 29, 2007. Applicability (c) This AD applies to Rolls-Royce Corporation (RRC) (formerly Allison Engine Company, Inc.) AE 3007A and AE 3007C series turbofan engines. These engines are installed on, but not limited to, Cessna Aircraft Company 750 series, and Empresa Brasileira de Aeronautica S. A. (EMBRAER) EMB–135 and EMB–145 series airplanes. Unsafe Condition (d) This AD results from design improvements to components in the accessory gearbox air turbine starter mounting pad. We are issuing this AD to prevent an in-flight engine shutdown due to loss of engine oil from the starter shaft seal. Prohibited Flights (f) All flights after ground engine starts at engine oil temperatures below 32 °F (0 °C), are prohibited except as follows: (1) If the engine oil temperature has dropped below 32 °F (0 °C), before flight, perform a high-power leak check on each engine (at least three minutes at takeoff power). (2) Oil consumption greater than 0.32 quart per hour (303 cc per hour) is not permitted. Instructions for performing the high-power leak check for the AE 3007A series engines can be found in the Rolls-Royce AE 3007A Series Maintenance Manual, TASK 72–00– 00–700–801, SUBTASK 72–00–00–790–002. Leak check limits for the AE 3007A series engines can be found in the Rolls-Royce AE 3007A Series Maintenance Manual, TASK 71–00–00–200–801. (3) Instructions for performing the highpower leak check for the AE 3007C series engines (including leak check limits) can be found in the Rolls-Royce AE 3007C Series Maintenance Manual, TASK 72–00–00–700– 801, SUBTASK 72–00–00–790–002. Terminating Action (g) No later than September 30, 2009, as terminating action to the requirements in paragraph (f) through (f)(3) of this AD, do the following, as applicable to your engine model and configuration: (1) Remove seal part number (P/N) 42520– 71, 42520–196–X, 99004–1–6, 42520–75, or 42520–167, from the accessory gearbox (AGB) air turbine starter mounting pad. (2) Install a new seal, P/N AS3209–026, or other serviceable part, to the shaft of the starter mounting pad. (3) Install a new bearing locknut, P/N 42520–170, or other serviceable part, and an AGB air turbine starter mounting pad mechanical seal, P/N 42520–192, or other serviceable part. (4) Use paragraphs 2. through 2.G. of the Accomplishment Instructions of RRC Service Bulletin (SB) No. AE 3007A–72–321 / AE 3007C–72–250, Revision 2, to do the removals and installations. (5) For AE 3007A series engines, remove the drain cap or starter drain adapter. Use paragraphs 2. through 2.C.(4)(c) of the Accomplishment Instructions of RRC SB No. AE 3007A–72–274, Revision 1, to do the removal. (6) For AE 3007A series engines, install an open starter drain adapter. Use paragraphs 2. through 2.C.(2) of the Accomplishment Instructions of RRC SB No. AE 3007A–72– 330, Revision 1, to do the installation. (7) For AE 3007C series engines, install an open starter drain adapter. Use paragraphs 2. through 2.E.(2) of the Accomplishment Instructions of RRC SB No. AE 3007C–72– 223, Revision 1, to do the installation. Definition (h) A serviceable part is any FAA-approved part not being removed from service, or not otherwise specifically addressed by this AD action. Serviceable parts may be available from the original equipment manufacturer or through Part Manufacturer Approval sources. Prohibition of Seals (i) Once the terminating action in this AD is performed on an engine, seal P/Ns 42520– 71, 42520–196–X, 99004–1–6, 42520–75, and 42520–167, are prohibited from being installed on the air starter mounting pad. Previous Credit (j) Previous credit is allowed for the terminating action in paragraphs (g)(1) through (g)(7) of this AD, that was done using the Accomplishment Instructions of the SBs listed in the following Table 1, before the effective date of this AD: TABLE 1.—SBS ALLOWING PREVIOUS CREDIT pwalker on PROD1PC71 with PROPOSALS For AE 3007A Series Engines (1) Engine—Accessory Drive Gearbox Assembly—New Starter Shaft Seal; RRC SB No. AE 3007A–72–321/AE 3007C–72–250, Revision 1, dated November 7, 2005; and (2) Engine—Accessory Gearbox Starter Pad Drain—Remove The Drain Cap or Starter Drain Adapter; RRC SB No. AE 3007A–72–274, dated January 19, 2006; and (3) Engine—Accessory Gearbox Starter Pad Drain—Install the Open Starter Drain Adapter (23083402 or 23077526); RRC SB No. AE 3007A– 72–330, dated January 19, 2006. For AE 3007C Series Engines (4) Engine—Accessory Drive Gearbox Assembly—New Starter Shaft Seal; RRC SB No. AE 3007A–72–321/AE 3007C–72–250, Revision 1, dated November 7, 2005; and VerDate Aug<31>2005 18:15 Mar 28, 2007 Jkt 211001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1 Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules 14727 TABLE 1.—SBS ALLOWING PREVIOUS CREDIT—Continued (5) Engine—Accessory Gearbox Starter Pad Drain—Install the Open Starter Drain Adapter (23077526 or 23083403); RRC SB No. AE 3007C– 72–223, dated January 19, 2006. Alternative Methods of Compliance (AMOC) (k) The Manager, Chicago Aircraft Certification Office, has the authority to approve AMOCs for this AD if requested using the procedures found in 14 CFR 39.19. (l) AMOCs approved for AD 99–02–51 are not approved as AMOCs for this AD. Related Information (m) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; e-mail: kyri.zaroyiannis@faa.gov; telephone (847) 294–7836; fax (847) 294–7834, for more information about this AD. Issued in Burlington, Massachusetts, on March 23, 2007. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–5775 Filed 3–28–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF LABOR Occupational Safety and Health Administration 29 CFR Part 1926 [New Docket No. OSHA—2007–0012, Old Docket No. S–204A] RIN 1218–AC02 Notice of Availability of the Regulatory Flexibility Act Review of the Occupational Safety Standard for Excavations Occupational Safety and Health Administration, Department of Labor. ACTION: Notice of availability. pwalker on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: The Occupational Safety and Health Administration (OSHA) has completed a review of its Excavations Standard pursuant to section 610 of the Regulatory Flexibility Act and section 5 of Executive Order 12866 on Regulatory Planning and Review. In 1989, OSHA issued a final, revised Excavations Standard to reduce deaths and injuries from excavation and trenching activities in the construction industry. This regulatory review concludes that the 1989 Excavations Standard has reduced deaths from approximately 90 to 70 per year while real construction activity has increased by 20%. The review also concludes that the Standard has not had a negative impact on small business, that the cost of control technology has VerDate Aug<31>2005 18:15 Mar 28, 2007 Jkt 211001 been reduced, that the Standard is understandable and does not conflict with other rules, and that commenters agree that the Standard should be retained. Based on this review, OSHA concludes that the Excavations Standard should remain in effect, but OSHA will issue some improved guidance and training materials, based on commenters suggestions. ADDRESSES: Copies of the entire report may be obtained from the OSHA Publication Office, Room N–3101, 200 Constitution Avenue, NW., Washington, DC 20210; telephone (202) 693–1888; Fax (202) 693–2498. The full report, comments, and referenced documents are available for review at the OSHA Docket Office, New Docket No. OSHA– 2007–0012, Old Docket No. S–204A, Room N–2625, 200 Constitution Avenue, NW., Washington, DC 20210; telephone (202) 693–2350 (OSHA’s TTY number is (877) 889–5627). OSHA’s Docket Office hours of operation are 8:15 a.m. to 4:45 p.m., e.t. The main text of the report, this Federal Register Notice and any news releases will become available at the OSHA Webpage at http://www.OSHA.gov. Electronic copies of this Federal Register Document, the full text of the report, comments and referenced documents are or will become available at http:// www.regulations.gov FOR FURTHER INFORMATION CONTACT: General information: Joanna Dizikes Friedrich, OSHA Directorate of Evaluation and Analysis, Room N–3641, U.S. Department of Labor, 200 Constitution Avenue, NW., Washington, DC 20210; telephone (202) 693–1939. Technical inquiries about the Excavations Standard: Garvin Branch, OSHA, Directorate of Construction, Room N–3468, U.S. Department of Labor, 200 Constitution Avenue, NW., Washington, DC 20210; telephone (202) 693–2020. Press inquiries: Elaine Fraser, OSHA Office of Communications, N– 3637, 200 Constitution Avenue, NW., Washington DC 20210; telephone (202) 693–1999. SUPPLEMENTARY INFORMATION: The Occupational Safety and Health Administration (OSHA) has completed a ‘‘lookback’’ review of its Excavations Standard, 29 CFR part 1926, Subpart P, §§ 1926.650 to 1926.652 and Appendices A to F, titled ‘‘Regulatory Review of 29 CFR part 1926, Subpart P: Excavations, March 2007’’ (‘‘Regulatory PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 Review’’). This Federal Register document announces the availability of the Regulatory Review and briefly summarizes it. The Regulatory Review was undertaken pursuant to and meets the requirements of section 610 of the Regulatory Flexibility Act (5 U.S.C. 601 et seq.) and section 5 of Executive Order 12866 (59 FR 51739, Oct 4, 1993). The purpose of a review under section 610 of the Regulatory Flexibility Act is to determine whether a rule should be continued without change, or should be amended or rescinded, consistent with the stated objectives of applicable statutes to minimize any significant impact of the rule on a substantial number of small entities. In making this determination, the Agency considers the following factors: (1) The continued need for the rule; (2) The nature of complaints or comments received concerning the rule from the public; (3) The complexity of the rule; (4) The extent to which the rule overlaps, duplicates or conflicts with other Federal rules; and to the extent feasible, with state and local governmental rules; and (5) The length of time since the rule has been evaluated and the degree to which technology, economic conditions, or other factors have changed in the areas affected by the rule. Under section 5 of Executive Order 12866, agencies examine whether rules have become unjustified or unnecessary as a result of changed circumstances, whether they are both compatible with other rules and not duplicative or inappropriately burdensome in the aggregate, whether they are consistent with the President’s priorities and the principles set forth in the Executive Order, within applicable law, and whether their effectiveness can be improved. On October 31, 1989, OSHA issued a final, revised Standard for excavation and trenching, at 54 FR 45894. The revision updated the previous standard by simplifying many of the existing provisions, adding and clarifying definitions, eliminating duplicate provisions and ambiguous language, and giving employers added flexibility in providing protection for employees. In addition, the Standard provided several new appendices. One appendix provided a consistent method of soil classification. Others provided sloping E:\FR\FM\29MRP1.SGM 29MRP1

Agencies

[Federal Register Volume 72, Number 60 (Thursday, March 29, 2007)]
[Proposed Rules]
[Pages 14724-14727]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-5775]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-26966; Directorate Identifier 99-NE-01-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation AE 3007A and AE 
3007C 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 Corporation (RRC) AE 3007A and AE 3007C 
series turbofan engines. That AD currently prohibits any flight 
following a ground engine start where the engine oil temperature is 
below 32 [deg]F (0 [deg]C), unless certain preflight operational 
procedures are followed. This proposed AD would also require those 
actions, and would also require a terminating action. This proposed AD 
would supersede the compliance requirements of AD 99-02-51 and all 
related alternative methods of compliance (AMOCs). This proposed AD 
results from design improvements to components in the accessory gearbox 
air turbine starter mounting pad. We are proposing this AD to prevent 
an in-flight engine shutdown due to loss of engine oil from the starter 
shaft seal.

DATES: We must receive any comments on this proposed AD by May 29, 
2007.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
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 Corporation, P.O. Box 420, Indianapolis, IN 
46206; telephone (317) 230-3774; fax (317) 230-8084; e-mail: 
indy.pubs.services@rolls-royce.com, to get the service information 
identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer, 
Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 
2300 E. Devon Ave., Des Plaines, IL 60018; telephone (847) 294-7836; 
fax (847) 294-7834.

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 ``Docket No. FAA-

[[Page 14725]]

2007-26966; Directorate Identifier 99-NE-01-AD'' in the subject line of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
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 proposed AD. Using the search function of the 
DMS Web site, anyone can find and read the comments in any of our 
dockets, including 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 http://dms.dot.gov.

Examining the AD Docket

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

Docket Number Change

    We are transferring the docket for this proposed AD to the Docket 
Management System as part of our on-going docket management 
consolidation efforts. The new Docket No. is FAA-2007-26966. The old 
Docket No. became the Directorate Identifier, which is 99-NE-01-AD.

Discussion

    On March 29, 1999, we issued AD 99-02-51, Amendment 39-11108 (64 FR 
16339, April 5, 1999), applicable to RRC AE 3007A and AE 3007C series 
turbofan engines. That AD prohibits any flight following a ground 
engine start where the engine oil temperature is below 32 [deg]F (0 
[deg]C), unless certain preflight operational procedures are followed 
to ensure that there is no excessive loss of oil from leakage at the 
air turbine starter shaft. That action resulted from reports of in-
flight engine shutdowns attributed to loss of engine oil from the 
starter shaft seal.
    Since we issued AD 99-02-51, RRC, Cessna Aircraft Company, and 
Empresa Brasileira de Aeronautica S.A. (EMBRAER) issued Service 
Bulletins (SBs) that describe a procedure to install a cap on the 
accessory gearbox starter pad drain fitting to prevent rapid engine oil 
loss during flight. These SBs were approved in 1999 as AMOCs to the 
requirements of AD 99-02-51. In September 2001, RRC developed single- 
and multi-orifice restrictors that were approved for use also as an 
AMOC that replaced the drain fitting cap in the previous AMOCs. RRC has 
since improved the design for the multi-orifice restrictor which is 
also approved as an AMOC. Since we approved these AMOCs, RRC released 
an improved seal for the accessory gearbox air turbine starter mounting 
pad. On January 19, 2006, we approved a terminating action AMOC 
incorporating the improved seal. That AMOC requires no cap or 
restrictor on the starter drain, but does not require removal of those 
components either. This proposed AD would mandate the removal of the 
AMOC configurations incorporating caps or restrictors and the 
installation of an open drain adapter.

Relevant Service Information

    We have reviewed and approved the technical contents of the 
following RRC SBs:
     SB No. AE 3007A-72-321 AE 3007C-72-250, Revision 2, which 
describes procedures for installing an improved starter shaft seal.
     SB No. AE 3007C-72-223, Revision 1, and SB No. AE 3007A-
72-330, Revision 1, which describe procedures for installing an open 
starter drain adapter.
     SB No. AE 3007A-72-274, Revision 1, which describes 
procedures for removing the drain cap or starter drain adapter on AE 
3007A series engines.
    The SB issue dates do not appear in this proposed AD because we 
agreed to allow RRC to assign the final rule AD issue date to them, as 
they want to reference the AD number in the SBs.

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:
     Prohibit before further flight, any flight following a 
ground engine start where the engine oil temperature is below 32 [deg]F 
(0 [deg]C), unless certain preflight operational procedures are 
followed to ensure that there is no excessive loss of oil from leakage 
at the air turbine starter shaft; and
     Require terminating action to the prohibition requirements 
of the existing AD, by removing from service certain seal P/Ns from the 
accessory gearbox air turbine starter mounting pad and installing an 
improved seal; and
     Require removing certain P/N drain caps, drain adapters, 
and orifice inserts, and installing an open adapter on the starter pad 
drain.
    The proposed AD would require that you do these actions using the 
service information described previously.

Costs of Compliance

    We estimate that this proposed AD would affect 1,868 RRC AE 3007A 
and AE 3007C series turbofan engines installed on aircraft of U.S. 
registry. We also estimate that it would take about 4 work-hours per 
engine to perform the proposed terminating action, and that the average 
labor rate is $80 per work-hour. Required parts would cost about $2,917 
per engine. Based on these figures, if all engines incorporated the 
terminating action, we estimate the total cost of the proposed AD to 
U.S. operators to be $6,046,100.

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

[[Page 14726]]

responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 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. 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

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 39-11108 (64 FR 
16339, April 5, 1999) and by adding a new airworthiness directive to 
read as follows:

Rolls-Royce Corporation (formerly Allison Engine Company, Inc.): 
Docket No. FAA-2007-26966; Directorate Identifier 99-NE-01-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by May 29, 
2007.

Affected ADs

    (b) This AD supersedes AD 99-02-51, Amendment 39-11108.

Applicability

    (c) This AD applies to Rolls-Royce Corporation (RRC) (formerly 
Allison Engine Company, Inc.) AE 3007A and AE 3007C series turbofan 
engines. These engines are installed on, but not limited to, Cessna 
Aircraft Company 750 series, and Empresa Brasileira de Aeronautica 
S. A. (EMBRAER) EMB-135 and EMB-145 series airplanes.

Unsafe Condition

    (d) This AD results from design improvements to components in 
the accessory gearbox air turbine starter mounting pad. We are 
issuing this AD to prevent an in-flight engine shutdown due to loss 
of engine oil from the starter shaft seal.

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.

Prohibited Flights

    (f) All flights after ground engine starts at engine oil 
temperatures below 32 [deg]F (0 [deg]C), are prohibited except as 
follows:
    (1) If the engine oil temperature has dropped below 32 [deg]F (0 
[deg]C), before flight, perform a high-power leak check on each 
engine (at least three minutes at takeoff power).
    (2) Oil consumption greater than 0.32 quart per hour (303 cc per 
hour) is not permitted. Instructions for performing the high-power 
leak check for the AE 3007A series engines can be found in the 
Rolls-Royce AE 3007A Series Maintenance Manual, TASK 72-00-00-700-
801, SUBTASK 72-00-00-790-002. Leak check limits for the AE 3007A 
series engines can be found in the Rolls-Royce AE 3007A Series 
Maintenance Manual, TASK 71-00-00-200-801.
    (3) Instructions for performing the high-power leak check for 
the AE 3007C series engines (including leak check limits) can be 
found in the Rolls-Royce AE 3007C Series Maintenance Manual, TASK 
72-00-00-700-801, SUBTASK 72-00-00-790-002.

Terminating Action

    (g) No later than September 30, 2009, as terminating action to 
the requirements in paragraph (f) through (f)(3) of this AD, do the 
following, as applicable to your engine model and configuration:
    (1) Remove seal part number (P/N) 42520-71, 42520-196-X, 99004-
1-6, 42520-75, or 42520-167, from the accessory gearbox (AGB) air 
turbine starter mounting pad.
    (2) Install a new seal, P/N AS3209-026, or other serviceable 
part, to the shaft of the starter mounting pad.
    (3) Install a new bearing locknut, P/N 42520-170, or other 
serviceable part, and an AGB air turbine starter mounting pad 
mechanical seal, P/N 42520-192, or other serviceable part.
    (4) Use paragraphs 2. through 2.G. of the Accomplishment 
Instructions of RRC Service Bulletin (SB) No. AE 3007A-72-321 / AE 
3007C-72-250, Revision 2, to do the removals and installations.
    (5) For AE 3007A series engines, remove the drain cap or starter 
drain adapter. Use paragraphs 2. through 2.C.(4)(c) of the 
Accomplishment Instructions of RRC SB No. AE 3007A-72-274, Revision 
1, to do the removal.
    (6) For AE 3007A series engines, install an open starter drain 
adapter. Use paragraphs 2. through 2.C.(2) of the Accomplishment 
Instructions of RRC SB No. AE 3007A-72-330, Revision 1, to do the 
installation.
    (7) For AE 3007C series engines, install an open starter drain 
adapter. Use paragraphs 2. through 2.E.(2) of the Accomplishment 
Instructions of RRC SB No. AE 3007C-72-223, Revision 1, to do the 
installation.

Definition

    (h) A serviceable part is any FAA-approved part not being 
removed from service, or not otherwise specifically addressed by 
this AD action. Serviceable parts may be available from the original 
equipment manufacturer or through Part Manufacturer Approval 
sources.

Prohibition of Seals

    (i) Once the terminating action in this AD is performed on an 
engine, seal P/Ns 42520-71, 42520-196-X, 99004-1-6, 42520-75, and 
42520-167, are prohibited from being installed on the air starter 
mounting pad.

Previous Credit

    (j) Previous credit is allowed for the terminating action in 
paragraphs (g)(1) through (g)(7) of this AD, that was done using the 
Accomplishment Instructions of the SBs listed in the following Table 
1, before the effective date of this AD:

                 Table 1.--SBs Allowing Previous Credit
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
                       For AE 3007A Series Engines
------------------------------------------------------------------------
(1) Engine--Accessory Drive Gearbox Assembly--New Starter Shaft Seal;
 RRC SB No. AE 3007A-72-321/AE 3007C-72-250, Revision 1, dated November
 7, 2005; and
(2) Engine--Accessory Gearbox Starter Pad Drain--Remove The Drain Cap or
 Starter Drain Adapter; RRC SB No. AE 3007A-72-274, dated January 19,
 2006; and
(3) Engine--Accessory Gearbox Starter Pad Drain--Install the Open
 Starter Drain Adapter (23083402 or 23077526); RRC SB No. AE 3007A-72-
 330, dated January 19, 2006.
------------------------------------------------------------------------
                       For AE 3007C Series Engines
------------------------------------------------------------------------
(4) Engine--Accessory Drive Gearbox Assembly--New Starter Shaft Seal;
 RRC SB No. AE 3007A-72-321/AE 3007C-72-250, Revision 1, dated November
 7, 2005; and

[[Page 14727]]

 
(5) Engine--Accessory Gearbox Starter Pad Drain--Install the Open
 Starter Drain Adapter (23077526 or 23083403); RRC SB No. AE 3007C-72-
 223, dated January 19, 2006.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOC)

    (k) The Manager, Chicago Aircraft Certification Office, has the 
authority to approve AMOCs for this AD if requested using the 
procedures found in 14 CFR 39.19.
    (l) AMOCs approved for AD 99-02-51 are not approved as AMOCs for 
this AD.

Related Information

    (m) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago 
Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 
E. Devon Ave., Des Plaines, IL 60018; e-mail: 
kyri.zaroyiannis@faa.gov; telephone (847) 294-7836; fax (847) 294-
7834, for more information about this AD.

    Issued in Burlington, Massachusetts, on March 23, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-5775 Filed 3-28-07; 8:45 am]
BILLING CODE 4910-13-P