Airworthiness Directives; Rolls-Royce Corporation AE 3007A and AE 3007C Series Turbofan Engines, 67242-67245 [E7-22810]

Download as PDF 67242 Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations 2007–24–07 General Electric Company: Amendment 39–15273. Docket No. FAA–2007–0193; Directorate Identifier 2007–NE–43–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 2, 2008. Affected ADs (b) None. Applicability (c) This AD applies to GE CF6–80C2B1 turbofan engine, serial number 690203, with fan disk, part number (P/N) 1703M78P11, SN RPMDA662, installed. This engine is installed on, but not limited to, a Boeing 747–300 airplane. Unsafe Condition (d) This AD results from a report that a repair shop did not meet the process requirements when applying copper-nickelindium (Cu-Ni-In) thermal coating to certain stage 1 fan disks. We are issuing this AD to prevent possible uncontained release of multiple fan blades, resulting in damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within 3,500 cycles-since-last Cu-Ni-In thermal spray coating of the dovetail slots, but no later than March 31, 2008, unless the actions have already been done. Stripping, Inspecting and Recoating the Stage 1 Fan Disk (f) Strip the Cu-Ni-In thermal coating from the pressure faces and slot bottoms of the stage 1 fan disk, and perform a microstructure evaluation. Use 3.A.(2)(a) through 3.A.(2)(b) of GE Service Bulletin (SB) No. CF6–80C2 S/B 72–1121, dated January 23, 2004, to strip the thermal coating and perform the microstructure evaluation. (g) Ultrasonic inspect, fluorescent penetrant inspect, and eddy current inspect stage 1 fan disk. Use 3.A.(2)(c) of GE SB No. CF6–80C2 S/B 72–1121, dated January 23, 2004, to inspect the disk. (h) Apply Cu-Ni-In thermal coating to the pressure faces and slot bottoms of the stage 1 fan disks, using 3.A.(2)(d) of GE SB No. CF6–80C2 S/B 72–1121, dated January 23, 2004. ebenthall on PRODPC61 with RULES Alternative Methods of Compliance (i) 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 (j) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone: (781) 238–7176, fax: (781) 238–7199, for more information about this AD. Material Incorporated by Reference (k) You must use GE Service Bulletin No. CF6–80C2 S/B 72–1121, dated January 23, VerDate Aug<31>2005 15:16 Nov 27, 2007 Jkt 214001 2004, to perform the actions 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 General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672–8400, fax (513) 672– 8422, for a copy of this service information. You may review copies at the FAA, New England Region, 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. Issued in Burlington, Massachusetts, on November 15, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–22922 Filed 11–27–07; 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; Amendment 39– 15271; AD 2007–24–05] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation AE 3007A and AE 3007C Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding 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 AD also requires those actions and would also require a terminating action. 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 engine accessory gearbox starter pad shaft seal drain and possible loss of the airplane. DATES: This AD becomes effective January 2, 2008. The Director of the Federal Register approved the incorporation by reference of certain PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 publications listed in the regulations as of January 2, 2008. ADDRESSES: You can get the service information identified in this AD from 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. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. 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: The FAA proposed to amend 14 CFR part 39 by superseding AD 99–02–51, Amendment 39–11108 (64 FR 16339, April 5, 1999), with a proposed AD. The proposed AD applies to RRC AE 3007A and AE 3007C series turbofan engines. We published the proposed AD in the Federal Register on March 29, 2007 (72 FR 14724). That action proposed to: • Prohibit before further flight, 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; 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.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 E:\FR\FM\28NOR1.SGM 28NOR1 Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations development of this AD. We have considered the comments received. Request To Continue To Allow Existing Approved AMOCs Four commenters, ExpressJet Inc., RRC, Embraer, and Cessna Aircraft Company state that alternative methods of compliance (AMOCs) currently approved for AD 99–02–51 should be allowed while this AD is not incorporated or until September 30, 2009. Paragraph (l) of the proposed rule states that AMOCs approved for AD 99– 02–51 are not approved for the new rule. Until all engines are modified as required by paragraph (g) of the proposed rule, an aircraft may encounter 32 °F temperature or lower and it seems arbitrary to disallow the use of data that has already been approved and in use for over two years. Operators would have the burden of requesting the same AMOC for the superseding AD. Allowing the currently approved AMOCs would bridge the time gap to the Terminating Action compliance date. We agree. We changed Alternative Methods of Compliance (AMOC), paragraph (l) from ‘‘AMOCs approved for AD 99–02–51 are not approved as AMOCs for this AD.’’ to ‘‘AMOCs currently approved for AD 99–02–51 will remain in effect until the terminating action date for this AD, September 30, 2009. After that date, these AMOCs will expire and not be approved as AMOCs for this AD.’’ This change will avoid confusion in the field and the AMOCs are still appropriate for the period before the mandatory terminating action date. These AMOCs will expire permanently on September 30, 2009, after which the only allowable configuration option is the new seal, a compatible starter and an open seal drain. ebenthall on PRODPC61 with RULES Request To Provide a More Accurate Description of the Original Problem Request to Not Implement the AD Two commenters, RRC and Embraer, ask us to include a more accurate description of the original problem. They state that the nomenclature ‘‘Starter shaft seal’’ may cause confusion with the seal of the pneumatic Air Turbine Starter (ATS). We agree. We changed Unsafe Condition, paragraph (d) from ‘‘* * * due to loss of engine oil from the starter shaft seal’’ to ‘‘* * * due to loss of engine oil from the engine accessory gearbox starter pad shaft seal drain and possible loss of the airplane.’’ Request To Clarify the Regulatory Text Rolls-Royce Corporation asks us to make the following changes for clarity: VerDate Aug<31>2005 17:13 Nov 27, 2007 Jkt 214001 • Prohibited Flights, paragraph (f)(2): Change ‘‘Oil consumption greater than 0.32 quart per hour (303 cc per hour) * * *’’ to ‘‘Oil consumption greater than 0.32 quart per hour, or 300 cc per hour, * * *’’ Although it may not be a completely accurate quart-to-cc conversion, 300 cc is the value listed in all RRC manuals. • Terminating Action, paragraph (g): Change ‘‘* * * do the following, as applicable to your engine model and configuration.’’ to ‘‘* * * do the following, as applicable to your configuration.’’ Engine model applicability is already established so it can be deleted here to make a simpler statement. • Terminating Action, paragraph (g)(1): Change ‘‘Remove seal part number (P/N) * * * ’’ to ‘‘Remove seal and related component part numbers (P/Ns) * * *’’ The P/Ns listed are not only currently approved seals but also adjacent hardware including a wave spring and spacer used in one of the approved configurations. This change accounts for all current hardware, not just the seals. • Terminating Action, paragraph (g)(2): Change ‘‘Install a new seal, P/N AS3209–026 * * *’’ to ‘‘Install a new O-ring, P/N AS3209–026 or M83248/1– 026* * *’’ RRC lists both of these P/Ns as acceptable alternatives in the engine parts list. Also, the correct nomenclature is O-ring, not seal. • Prohibition of Seals, paragraph (i): Change ‘‘Once the terminating action in this AD is performed on an engine, seal P/Ns * * *’’ to ‘‘Once the terminating action in this AD is performed on an engine, seal and related component P/Ns * * *’’ This change accounts for all current hardware, not just the seals. We agree with the suggestions and incorporated them into the applicable regulatory text of the AD. Rolls-Royce North America, Inc., c/o American Eagle Airlines, asks us to not implement the AD, or at least extend the required completion date for the terminating action by at least 6–12 months. They believe that many AE3007A and AE3007C engines are not yet compliant with RRC Service Bulletin AE 3007A–72–321 and or SB AE 3007A–72–330. They state that it would be too much of a burden to modify all of the engines currently out in the field to be compliant with the proposed AD by September 30, 2009. A drastic maintenance campaign such as this would adversely affect the AE3007A and C fleet both in terms of costs and operations to drastic proportions. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 67243 We don’t agree. We have determined that we can better assure long-term continued operational safety by design changes that remove the source of the problem, rather than by repetitive inspections or other special procedures. Based on the availability of the required parts and the support from the vast majority of operators and their ability to comply within the original specified date, we believe this is a reasonable time period and will maintain the final compliance date of September 30, 2009. 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 1,868 RRC AE 3007A and AE 3007C series turbofan engines installed on aircraft of U.S. registry. We also estimate that it will 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 will cost about $2,917 per engine. Based on these figures, if all engines incorporated the terminating action, we estimate the total cost of this 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 AD will not have federalism implications under Executive Order 13132. This AD will E:\FR\FM\28NOR1.SGM 28NOR1 67244 Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations 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 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 removing Amendment 39–11108 64 FR 16339 April 5, 1999, and by adding a new airworthiness directive, Amendment 39–15271, to read as follows: I 2007–24–05 Rolls-Royce Corporation (Formerly Allison Engine Company, Inc.): Amendment 39–15271. Docket No. FAA–2007–26966; Directorate Identifier 99–NE–01–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 2, 2008. 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 and possible loss of 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. 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, or 300 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 RollsRoyce 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 configuration: (1) Remove seal and related component, part numbers (P/Ns) 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 O-ring, P/N AS3209–026, M83248/1–026 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, dated November 12, 2007, 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, dated November 12, 2007 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, dated November 12, 2007 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, dated November 12, 2007 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. Prohibition of Seals (i) Do not install seal and related component P/Ns 42520–71, 42520–196–X, 99004–1–6, 42520–75, and 42520–167, on the air starter mounting pad after the terminating action in this AD is performed. Previous Credit (j) Previous credit is allowed for the terminating action in paragraphs (g)(1) through (g)(7) of this AD, that was done before the effective date of this AD using the Accomplishment Instructions of the SBs listed in the following Table 1: ebenthall on PRODPC61 with RULES 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 VerDate Aug<31>2005 17:13 Nov 27, 2007 Jkt 214001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\28NOR1.SGM 28NOR1 Federal Register / Vol. 72, No. 228 / Wednesday, November 28, 2007 / Rules and Regulations 67245 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 currently approved for AD 99– 02–51 will remain in effect until the terminating action date for this AD, September 30, 2009. After that date, these AMOCs will expire and will not be approved as AMOCs for this AD. 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. Material Incorporated by Reference (n) You must use the service information specified in Table 2 to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact RollsRoyce Corporation, P.O. Box 420, Related Information (m) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago Aircraft Certification Indianapolis, IN 46206; telephone (317) 230– 3774; fax (317) 230–8084; e-mail: indy.pubs.services@rolls-royce.com, for a copy of this service information. You may review copies at the FAA, New England Region, 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. TABLE 2.—INCORPORATION BY REFERENCE Service Bulletin No. Page AE 3007A–72–274 ............................................................................................... Total Pages—6 AE 3007A–72–321, AE 3007C–72–250 .............................................................. Total Pages—13 AE 3007A–72–330 ............................................................................................... Total Pages—6 AE 3007C–72–223 .............................................................................................. Total Pages—7 ALL ............................ 1 November 12, 2007. ALL ............................ 2 November 12, 2007. ALL ............................ 1 November 12, 2007. ALL ............................ 1 November 12, 2007. Issued in Burlington, Massachusetts, on November 14, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–22810 Filed 11–27–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26102; Directorate Identifier 2006–NE–36–AD; Amendment 39– 15272; AD 2007–24–06] RIN 2120–AA64 Airworthiness Directives; Societe de Motorisations Aeronautiques (SMA) SR305–230 and SR305–230–1 Reciprocating Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. ebenthall on PRODPC61 with RULES AGENCY: SUMMARY: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing VerDate Aug<31>2005 17:13 Nov 27, 2007 Jkt 214001 airworthiness information (MCAI) provided by the European Aviation Safety Agency (EASA) to identify and correct an unsafe condition on SMA SR305–230 and SR305–230–1 reciprocating engines. The MCAI states the following: Over a period of time, the alteration of one electronic control unit (ECU) electronic component can cause a rapid uncontrolled power increase. Several occurrences have already been reported during engine start or during engine warm-up. This condition, if not corrected, could result in the loss of control of the aircraft if the pilot fails to react appropriately by switching to the mechanical backup mode. We are issuing this AD to prevent a rapid uncontrolled power increase and possible loss of control of the airplane. DATES: This AD becomes effective December 13, 2007. The Director of the Federal Register approved the incorporation by reference of SMA Service Bulletin (SB) No. SB–01–76– 005, dated December 15, 2006, as of December 13, 2007. We must receive comments on this AD by December 28, 2007. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Revision Date • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.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 the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: Christopher.spinney@faa.gov; telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: E:\FR\FM\28NOR1.SGM 28NOR1

Agencies

[Federal Register Volume 72, Number 228 (Wednesday, November 28, 2007)]
[Rules and Regulations]
[Pages 67242-67245]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22810]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-26966; Directorate Identifier 99-NE-01-AD;
Amendment 39-15271; AD 2007-24-05]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce Corporation AE 3007A and AE
3007C Series Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding 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 AD also requires those actions and would also require a
terminating action. 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 engine accessory gearbox starter pad shaft
seal drain and possible loss of the airplane.

DATES: This AD becomes effective January 2, 2008. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of January 2, 2008.

ADDRESSES: You can get the service information identified in this AD
from 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.
The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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: The FAA proposed to amend 14 CFR part 39 by
superseding AD 99-02-51, Amendment 39-11108 (64 FR 16339, April 5,
1999), with a proposed AD. The proposed AD applies to RRC AE 3007A and
AE 3007C series turbofan engines. We published the proposed AD in the
Federal Register on March 29, 2007 (72 FR 14724). That action proposed
to:
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.

Examining the AD Docket

You may examine the AD docket on the Internet at https://
www.regulations.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

[[Page 67243]]

development of this AD. We have considered the comments received.

Request To Continue To Allow Existing Approved AMOCs

Four commenters, ExpressJet Inc., RRC, Embraer, and Cessna Aircraft
Company state that alternative methods of compliance (AMOCs) currently
approved for AD 99-02-51 should be allowed while this AD is not
incorporated or until September 30, 2009. Paragraph (l) of the proposed
rule states that AMOCs approved for AD 99-02-51 are not approved for
the new rule. Until all engines are modified as required by paragraph
(g) of the proposed rule, an aircraft may encounter 32 [deg]F
temperature or lower and it seems arbitrary to disallow the use of data
that has already been approved and in use for over two years. Operators
would have the burden of requesting the same AMOC for the superseding
AD. Allowing the currently approved AMOCs would bridge the time gap to
the Terminating Action compliance date.
We agree. We changed Alternative Methods of Compliance (AMOC),
paragraph (l) from ``AMOCs approved for AD 99-02-51 are not approved as
AMOCs for this AD.'' to ``AMOCs currently approved for AD 99-02-51 will
remain in effect until the terminating action date for this AD,
September 30, 2009. After that date, these AMOCs will expire and not be
approved as AMOCs for this AD.'' This change will avoid confusion in
the field and the AMOCs are still appropriate for the period before the
mandatory terminating action date. These AMOCs will expire permanently
on September 30, 2009, after which the only allowable configuration
option is the new seal, a compatible starter and an open seal drain.

Request To Provide a More Accurate Description of the Original Problem

Two commenters, RRC and Embraer, ask us to include a more accurate
description of the original problem. They state that the nomenclature
``Starter shaft seal'' may cause confusion with the seal of the
pneumatic Air Turbine Starter (ATS). We agree. We changed Unsafe
Condition, paragraph (d) from ``* * * due to loss of engine oil from
the starter shaft seal'' to ``* * * due to loss of engine oil from the
engine accessory gearbox starter pad shaft seal drain and possible loss
of the airplane.''

Request To Clarify the Regulatory Text

Rolls-Royce Corporation asks us to make the following changes for
clarity:
Prohibited Flights, paragraph (f)(2): Change ``Oil
consumption greater than 0.32 quart per hour (303 cc per hour) * * *''
to ``Oil consumption greater than 0.32 quart per hour, or 300 cc per
hour, * * *'' Although it may not be a completely accurate quart-to-cc
conversion, 300 cc is the value listed in all RRC manuals.
Terminating Action, paragraph (g): Change ``* * * do the
following, as applicable to your engine model and configuration.'' to
``* * * do the following, as applicable to your configuration.'' Engine
model applicability is already established so it can be deleted here to
make a simpler statement.
Terminating Action, paragraph (g)(1): Change ``Remove seal
part number (P/N) * * * '' to ``Remove seal and related component part
numbers (P/Ns) * * *'' The P/Ns listed are not only currently approved
seals but also adjacent hardware including a wave spring and spacer
used in one of the approved configurations. This change accounts for
all current hardware, not just the seals.
Terminating Action, paragraph (g)(2): Change ``Install a
new seal, P/N AS3209-026 * * *'' to ``Install a new O-ring, P/N AS3209-
026 or M83248/1-026* * *'' RRC lists both of these P/Ns as acceptable
alternatives in the engine parts list. Also, the correct nomenclature
is O-ring, not seal.
Prohibition of Seals, paragraph (i): Change ``Once the
terminating action in this AD is performed on an engine, seal P/Ns * *
*'' to ``Once the terminating action in this AD is performed on an
engine, seal and related component P/Ns * * *'' This change accounts
for all current hardware, not just the seals.
We agree with the suggestions and incorporated them into the
applicable regulatory text of the AD.

Request to Not Implement the AD

Rolls-Royce North America, Inc., c/o American Eagle Airlines, asks
us to not implement the AD, or at least extend the required completion
date for the terminating action by at least 6-12 months. They believe
that many AE3007A and AE3007C engines are not yet compliant with RRC
Service Bulletin AE 3007A-72-321 and or SB AE 3007A-72-330. They state
that it would be too much of a burden to modify all of the engines
currently out in the field to be compliant with the proposed AD by
September 30, 2009. A drastic maintenance campaign such as this would
adversely affect the AE3007A and C fleet both in terms of costs and
operations to drastic proportions.
We don't agree. We have determined that we can better assure long-
term continued operational safety by design changes that remove the
source of the problem, rather than by repetitive inspections or other
special procedures. Based on the availability of the required parts and
the support from the vast majority of operators and their ability to
comply within the original specified date, we believe this is a
reasonable time period and will maintain the final compliance date of
September 30, 2009.

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 1,868 RRC AE 3007A and AE
3007C series turbofan engines installed on aircraft of U.S. registry.
We also estimate that it will 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 will cost about $2,917 per
engine. Based on these figures, if all engines incorporated the
terminating action, we estimate the total cost of this 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 AD will not have federalism
implications under Executive Order 13132. This AD will

[[Page 67244]]

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 removing Amendment 39-11108 64 FR
16339 April 5, 1999, and by adding a new airworthiness directive,
Amendment 39-15271, to read as follows:

2007-24-05 Rolls-Royce Corporation (Formerly Allison Engine Company,
Inc.): Amendment 39-15271. Docket No. FAA-2007-26966; Directorate
Identifier 99-NE-01-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective January
2, 2008.

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 and possible loss of 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.

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, or 300 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 configuration:
(1) Remove seal and related component, part numbers (P/Ns)
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 O-ring, P/N AS3209-026, M83248/1-026 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, dated November 12, 2007, 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, dated November 12, 2007 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, dated
November 12, 2007 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, dated
November 12, 2007 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.

Prohibition of Seals

(i) Do not install seal and related component P/Ns 42520-71,
42520-196-X, 99004-1-6, 42520-75, and 42520-167, on the air starter
mounting pad after the terminating action in this AD is performed.

Previous Credit

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

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 67245]]

(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 currently approved for AD 99-02-51 will remain in
effect until the terminating action date for this AD, September 30,
2009. After that date, these AMOCs will expire and will not be
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.

Material Incorporated by Reference

(n) You must use the service information specified in Table 2 to
perform the actions required by this AD. The Director of the Federal
Register approved the incorporation by reference of the documents
listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. 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, for a copy of this
service information. You may review copies at the FAA, New England
Region, 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.

Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
AE 3007A-72-274................. ALL........................... 1 November 12, 2007.
Total Pages--6
AE 3007A-72-321, AE 3007C-72-250 ALL........................... 2 November 12, 2007.
Total Pages--13
AE 3007A-72-330................. ALL........................... 1 November 12, 2007.
Total Pages--6
AE 3007C-72-223................. ALL........................... 1 November 12, 2007.
Total Pages--7
----------------------------------------------------------------------------------------------------------------

Issued in Burlington, Massachusetts, on November 14, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-22810 Filed 11-27-07; 8:45 am]
BILLING CODE 4910-13-P

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