Federal Register / Vol. 67, No. 231 / Monday, December 2, 2002 / Proposed Rules 71493

Citation the occupant 10 seconds after its one or more blade fragments. The The authority citation for these deployment. actions specified by the proposed AD special conditions is as follows: 7. For the purpose of complying with are intended to prevent centrifugal HIRF and lightning requirements, the compressor intake wheel blade cracks, Authority: 49 U.S.C. 106(g), 40113 and inflatable seatbelt system is considered which can result in in-flight engine 44701; 14 CFR 21.16 and 21.101 for STC or a ‘‘critical system’’ if its deployment power loss or shutdown. 21.17 for TC; and 14 CFR 11.38 and 11.19. could have a hazardous effect on the DATES: Comments must be received by The Proposed Special Conditions airplane; otherwise, it is considered an January 31, 2003. The FAA has determined that this ‘‘essential’’ system. ADDRESSES: Submit comments in project will be accomplished on the 8. It must be shown that the inflatable triplicate to the Federal Aviation basis of not lowering the current level seatbelt will not release hazardous Administration (FAA), New England of safety for the Air Tractor Model AT– quantities of gas or particulate matter Region, Office of the Regional Counsel, 401, –402, –502, –602, and –802 series into the cabin. Attention: Rules Docket No. 99–NE–12– 9. The inflatable seatbelt installation occupant restraint design. Accordingly, AD, 12 New England Executive Park, must be protected from the effects of fire the (FAA) proposes the following Burlington, MA 01803–5299. Comments such that no hazard to occupants will special conditions as part of the type may be inspected at this location, by result. certification basis for Air Tractor series appointment, between 8 a.m. and 4:30 10. There must be a means to verify airplanes AT–401, AT–402, AT–502, p.m., Monday through Friday, except the integrity of the inflatable seatbelt AT–602, and AT–802 modified by Federal holidays. Comments may also activation system before each flight or it Goodrich Aircraft Interior Products. be sent via the Internet using the must be demonstrated to reliably following address: 9-ane- 4-Point Inflatable Restraints for operate between inspection intervals. [email protected]. Comments sent 11. A life limit needs to be established Agricultural Airplanes via the Internet must contain the docket for appropriate system designs. 1. It must be shown that the inflatable number in the subject line. 12. Qualification testing of the seatbelt will deploy and provide The service information referenced in internal firing mechanism must be protection under crash conditions the proposed rule may be obtained from accomplished using the vibration levels where it is necessary to prevent serious Turbomeca, 40220 Tarnos, France; appropriate for an agricultural airplane. injury. A dynamic test is required to telephone (33) 05 59 64 40 00; fax (33) verify that the system operates as Michael Gallagher, 05 59 64 60 80. This information may intended when subjected to the 26 G Manager, Small Airplane Directorate, Aircraft be examined, by appointment, at the deceleration pulse described in Certification Service. FAA, New England Region, Office of the § 23.562(b)(2). The dynamic test need [FR Doc. 02–30325 Filed 11–29–02; 8:45 am] Regional Counsel, 12 New England only be performed using a 50 percentile BILLING CODE 4910–13–M Executive Park, Burlington, MA. male ATD. FOR FURTHER INFORMATION CONTACT: 2. The means of protection must take Antonio Cancelliere, Aerospace into consideration a range of stature DEPARTMENT OF TRANSPORTATION Engineer, Engine Certification Office, from a 5 percentile female to a 95 FAA, Engine and Propeller Directorate, percentile male. The inflatable seatbelt Federal Aviation Administration 12 New England Executive Park, must provide a consistent level of Burlington, MA 01803–5299; telephone energy absorption throughout that 14 CFR Part 39 (781) 238–7751; fax (781) 238–7199. range. [Docket No. 99–NE–12–AD] SUPPLEMENTARY INFORMATION: 3. The design must prevent the inflatable seatbelt from either being RIN 2120–AA64 Comments Invited incorrectly buckled or incorrectly Interested persons are invited to Airworthiness Directives; Turbomeca installed, or both, such that the airbag participate in the making of the Turmo IV A and Turmo IV C Series would not properly deploy. proposed rule by submitting such Turboshaft Engines 4. It must be shown that an written data, views, or arguments as inadvertent deployment does not cause AGENCY: Federal Aviation they may desire. Communications an unsafe condition (or hazard to the Administration, DOT. should identify the Rules Docket airplane). Consideration needs to be ACTION: Notice of proposed rulemaking number and be submitted in triplicate to given as a result of wear and tear, or (NPRM). the address specified above. All inertial loads resulting from in-flight or communications received on or before ground maneuvers (including gusts and SUMMARY: The Federal Aviation the closing date for comments, specified hard landings), likely to be experienced Administration (FAA) proposes to adopt above, will be considered before taking in service. The seat belt must have the a new airworthiness directive (AD) that action on the proposed rule. The same strength capability after the is applicable to Turbomeca Turmo IV A proposals contained in this notice may inflatable portion of the restraint has and IV C series turboshaft engines. This be changed in light of the comments been deployed. proposal would require initial and received. 5. It must be shown that deployment repetitive borescope and eddy current or Comments are specifically invited on of the device is not hazardous to the ultrasonic inspections of centrifugal the overall regulatory, economic, occupant. In addition, the seated compressor intake wheel blades for environmental, and energy aspects of occupant must not be injured as cracks and evidence of corrosion pitting, the proposed rule. All comments established by criteria in § 23.562 as a and, if found cracked or if there is submitted will be available, both before result of the inflatable seatbelt evidence of corrosion pitting, and after the closing date for comments, deployment, including keeping the lap replacement with serviceable parts. This in the Rules Docket for examination by belt located on the pelvis. proposal is prompted by reports of interested persons. A report 6. It must be shown that the inflatable cracked centrifugal compressor intake summarizing each FAA-public contact seatbelt will not impede rapid egress of wheel blades, resulting in the release of concerned with the substance of this

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proposal will be filed in the Rules operation in the United States under the For the reasons discussed above, I Docket. provisions of Section 21.29 of the certify that this proposed regulation (1) Commenters wishing the FAA to Federal Aviation Regulations (14 CFR is not a ‘‘significant regulatory action’’ acknowledge receipt of their comments 21.29) and the applicable bilateral under Executive Order 12866; (2) is not submitted in response to this notice airworthiness agreement. Pursuant to a ‘‘significant rule’’ under the DOT must submit a self-addressed, stamped this bilateral airworthiness agreement, Regulatory Policies and Procedures (44 postcard on which the following the DGAC has kept the FAA informed FR 11034, February 26, 1979); and (3) if statement is made: ‘‘Comments to of the situation described above. The promulgated, will not have a significant Docket Number 99–NE–12–AD.’’ The FAA has examined the findings of the economic impact, positive or negative, postcard will be date stamped and DGAC, reviewed all available on a substantial number of small entities returned to the commenter. information, and determined that AD under the criteria of the Regulatory Availability of NPRM’s action is necessary for products of this Flexibility Act. A copy of the draft type design that are certificated for regulatory evaluation prepared for this Any person may obtain a copy of this operation in the United States. action is contained in the Rules Docket. NPRM by submitting a request to the A copy of it may be obtained by Proposed Requirements of This AD FAA, New England Region, Office of the contacting the Rules Docket at the Regional Counsel, Attention: Rules Since an unsafe condition has been location provided under the caption Docket No. 99–NE–12–AD, 12 New identified that is likely to exist or ADDRESSES. England Executive Park, Burlington, MA develop on other products of this same List of Subjects in 14 CFR Part 39 01803–5299. type design, the proposed AD would Discussion require: Air transportation, Aircraft, Aviation • Initial and repetitive borescope and safety, Safety. The Direction Generale de L’Aviation eddy current or ultrasonic inspections Civile (DGAC), which is the The Proposed Amendment of centrifugal compressor intake wheel airworthiness authority for France, blades for cracks and evidence of Accordingly, pursuant to the recently notified the FAA that an unsafe corrosion pitting; and authority delegated to me by the condition may exist on Turbomeca Administrator, the Federal Aviation • Replacement with serviceable parts Turmo IV A and IV C series turboshaft Administration proposes to amend part if found cracked or if there is evidence engines. The DGAC advises that they 39 of the Federal Aviation Regulations of corrosion pitting. have received reports of cracked (14 CFR part 39) as follows: centrifugal compressor intake wheel At this time there is no modification blades. The phenomena of blade available as terminating action; as the PART 39—AIRWORTHINESS cracking occurs in two phases; initiation investigation is ongoing into the cause DIRECTIVES after a single event, such as foreign of crack initiation, future rulemaking 1. The authority citation for part 39 object damage or surge, and crack may be necessary. The actions would be continues to read as follows: propagation due to operating at a gas required to be done in accordance with generator speed, between 80 percent the SB described previously. Authority: 49 U.S.C. 106(g), 40113, 44701. and 83 percent, that appears to set up Economic Analysis § 39.13 [Amended] a vibration. Although the exact cause of 2. Section 39.13 is amended by the initiation of cracks has not yet been There are approximately 1,110 adding the following new airworthiness identified, cracks could initiate at engines of the affected design in the directive: corrosion pits. The investigation is worldwide fleet. The FAA estimates that continuing. This condition, if not there are currently 11 engines installed Turbomeca: Docket No. 99–NE–12–AD. corrected, could result in centrifugal on helicopters of U.S. registry that Applicability: This airworthiness directive compressor intake wheel blade cracks, would be affected by this proposed AD, (AD) is applicable to Turbomeca Turmo IV A which can result in in-flight engine that it would take approximately 41 and IV C series turboshaft engines. These power loss or shutdown. work hours per engine to perform the engines are installed on but not limited to proposed inspections, including Aerospatiale FA 330–PUMA helicopters. Manufacturer’s Service Information disassembling and assembling engines, Note 1: This AD applies to each engine Turbomeca has issued Turmo IV and that the average labor rate is $60 per identified in the preceding applicability Service Bulletin (SB) No. 249 72 0100, work hour. A replacement centrifugal provision, regardless of whether it has been modified, altered, or repaired in the area Update No. 4, dated January 25, 2000, compressor assembly costs approximately $21,651. Based on these subject to the requirements of this AD. For that specifies procedures for the engines that have been modified, altered, or centrifugal compressor intake wheel figures, the cost per inspection is repaired so that the performance of the blade inspections. The DGAC classified estimated to be $265,221. requirements of this AD is affected, the this SB as mandatory and issued Regulatory Analysis owner/operator must request approval for an airworthiness directive (AD) DGAC AD alternative method of compliance in 97–122(A), Revision 3, dated April 5, This proposed rule does not have accordance with paragraph (e) of this AD. 2000, in order to ensure the federalism implications, as defined in The request should include an assessment of airworthiness of these engines in Executive Order 13132, because it the effect of the modification, alteration, or repair on the unsafe condition addressed by France. Turbomeca has also issued would not have a substantial direct effect on the States, on the relationship this AD; and, if the unsafe condition has not Turmo IV SB No. 249 72 0117, dated been eliminated, the request should include March 11, 2000, that specifies between the national government and specific proposed actions to address it. the States, or on the distribution of procedures for installation of Compliance: Compliance is required as modification TU 224. power and responsibilities among the indicated, unless already done various levels of government. Bilateral Agreement Information To prevent centrifugal compressor intake Accordingly, the FAA has not consulted wheel blade cracks, which can result in in- This engine model is manufactured in with state authorities prior to flight engine power loss or shutdown, do the France and is type certificated for publication of this proposed rule. following:

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(a) For engines that have been modified to (iii) If corrosion is not found, perform an Issued in Burlington, Massachusetts, on TU 197 standard, but have not been modified ECI or USI, as applicable, of the blades for November 21, 2002. to TU 191 or TU 224 standard, do the cracks, and, if necessary, replace with Jay J. Pardee, following: serviceable parts, within 250 FH after the Manager, Engine and Propeller Directorate, (1) Remove modification TU 197 and borescope inspection performed in Aircraft Certification Service. install modification TU 224 in accordance accordance with paragraph (b)(2)(i) of this with Turmo IV SB 249 72 0117, dated March [FR Doc. 02–30351 Filed 11–29–02; 8:45 am] 11, 2000, within the next 50 cycles or six AD. BILLING CODE 4910–13–P months after the effective date of the AD, (iv) Thereafter, perform borescope whichever occurs first. inspections and ECI’s or USI’s, as applicable, (2) Within 1,000 flight hours (FH) after the of the blades for cracks and evidence of DEPARTMENT OF TRANSPORTATION installation of modification TU 224 standard, corrosion, alternating at intervals not to do the following: exceed 250 FH since the last inspection. Federal Aviation Administration (i) Perform a visual inspection and an Note 2: Alternating intervals means that if ultrasonic inspection (USI) in accordance the last inspection was an ECI or a USI, the 14 CFR Part 39 with paragraph 2.B.(3) of Turbomeca Turmo IV SB 249 72 0100, Update 4, dated January next inspection will be a borescope [Docket No. 2002–NE–10–AD] 25, 2000. inspection. If the last inspection was a (ii) Thereafter, perform a visual inspection borescope inspection, the next 250 FH and a USI at intervals not to exceed 1,000 FH inspection will be an ECI or a USI as RIN 2120–AA64 in accordance with paragraph 2.B.(3) of applicable. Airworthiness Directives; Rolls-Royce Turbomeca Turmo IV SB 249 72 0100, (v) Remove from service centrifugal Update 4, dated January 25, 2000. plc Model RB211–22B Turbofan compressor intake wheels found cracked and (b) For engines that have not been modified Engines replace with serviceable parts. to TU 191, TU 197, or TU 224 standard, do the following in accordance with Turbomeca (c) For engines not modified to TU 197 but AGENCY: Federal Aviation Turmo IV SB 249 72 0100, Update 4, dated have been modified to TU 191 or TU 224 Administration, DOT. January 25, 2000: standard, that have been operated for more ACTION: Notice of proposed rulemaking (1) For centrifugal compressor intake than 1,000 flight hours since the last (NPRM). wheels that, on the effective date of this AD, inspection of the blades, do the following in have been operated for more than 250 FH accordance with Turbomeca Turmo IV SB SUMMARY: The Federal Aviation since the last inspection of the centrifugal 249 72 0100, Update 4, dated January 25, Administration (FAA) proposes to adopt compressor intake wheel blades, do the 2000: a new airworthiness directive (AD) that following: (1) Perform an initial ECI or USI, as is applicable to Rolls-Royce plc (RR) (i) Perform an initial borescope inspection applicable, of the blades for cracks, in of the blades for evidence of corrosion within model RB211–22B turbofan engines accordance with paragraph 2.B.(3) of the SB, the next 50 FH, or six months after the with intermediate pressure (IP) effective date of this AD, whichever occurs within the next 50 FH, or 6 months after the compressor stage 6 to 7 rotor shaft first, in accordance with paragraph 2.B.(1) of effective date of this AD, whichever occurs assembly part number (P/N) UL37094 the SB. first. installed. This proposal would require (ii) If corrosion is found, perform an ECI or (2) Thereafter, inspect at intervals not to removal from service of IP compressor USI, as applicable, of the blades for cracks exceed 1,000 FH. stage 6 to 7 rotor shaft assemblies P/N within 50 FH after the borescope inspection (3) Remove from service centrifugal UL37094 before reaching newly reduced performed in accordance with paragraph compressor intake wheels found cracked, and life limits. This proposal is prompted by 2.B.(3) of the SB, and if necessary, replace replace with a serviceable part with serviceable parts. the discovery of corrosion during (iii) If corrosion is not found, perform an Alternative Methods of Compliance inspection and analysis of IP compressor stage 6 to 7 rotor shaft ECI or USI, as applicable, of the blades for (e) An alternative method of compliance or assemblies returned from the field. The cracks within 250 FH after the borescope adjustment of the compliance time that inspection performed in accordance with provides an acceptable level of safety may be actions specified by the proposed AD paragraph (b)(1)(i) of this AD, and if used if approved by the Manager, Engine are intended to prevent corrosion- necessary, replace with serviceable parts. induced cracking of the IP compressor (iv) Thereafter, perform borescope Certification Office (ECO). Operators must submit their request through an appropriate stage 6 to 7 rotor shaft assembly, inspections and ECI’s or USI’s, as applicable, resulting in an uncontained engine of the blades for cracks and evidence of FAA Principal Maintenance Inspector, who corrosion, alternating at intervals not to may add comments and then send it to the failure and damage to the airplane. exceed 250 FH since the last inspection. Manager, ECO. DATES: Comments must be received by (v) Remove from service centrifugal Note 3: Information concerning the January 31, 2003. compressor intake wheels found cracked and existence of approved alternative methods of ADDRESSES: Submit comments in replace with serviceable parts. compliance with this airworthiness directive, triplicate to the Federal Aviation (2) For centrifugal compressor intake wheels that, upon the effective date of this if any, may be obtained from the ECO. Administration (FAA), New England AD, have been operated for less than or equal Region, Office of the Regional Counsel, Special Flight Permits to 250 FH since the last inspection of the Attention: Rules Docket No. 2002–NE– blades, do the following: (f) Special flight permits may be issued in 10–AD, 12 New England Executive Park, (i) Perform an initial borescope inspection accordance with §§ 21.197 and 21.199 of the Burlington, MA 01803–5299. Comments of the blades for evidence of corrosion prior Federal Aviation Regulations (14 CFR 21.197 may be inspected at this location, by to accumulating 250 FH since the last and 21.199) to operate the helicopter to a appointment, between 8:00 a.m. and inspection of the blades in accordance with location where the requirements of this AD 4:30 p.m., Monday through Friday, paragraph 2.B.(1) of the SB. can be done. except Federal holidays. Comments may (ii) If corrosion is found, perform an ECI or USI, as applicable, of the blades for cracks, Note 4: The subject of this AD is addressed also be sent via the Internet using the and, if necessary, replace with serviceable in Direction Generale de L’Aviation Civile following address: ‘‘9–ane– parts, within 50 FH after the borescope airworthiness directive AD97–122(B), dated [email protected]’’. Comments sent inspection performed in accordance with May 21, 1997. via the Internet must contain the docket paragraph 2.B.(3) of the SB. number in the subject line.

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