[Federal Register Volume 59, Number 102 (Friday, May 27, 1994)] [Unknown Section] [Page 0] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 94-13012] [[Page Unknown]] [Federal Register: May 27, 1994] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 94-ANE-26] Airworthiness Directives; Hamilton Standard 14RF, 247F, 14SF, and 6/5500/F Series Propellers AGENCY: Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: This document proposes the supersedure of an existing airworthiness directive (AD), applicable to Hamilton Standard 14RF, 247F, 14SF, and 6/5500/F (formerly Hamilton Standard/British Aerospace 6/5500/F) series propellers, that currently requires initial and repetitive inspections of the propeller control unit (PCU) servo ballscrew internal spline (BIS) teeth for wear, and replacement, if necessary, of PCU servo BIS assemblies. This action would increase the repetitive inspection interval from 500 to 1,500 hours time in service (TIS) since last inspection for propellers that have a ballscrew quill damper installed. This proposal is prompted by the availability of improved hardware that enhances the lubrication of the BIS and significantly reduces BIS wear. The actions specified by the proposed AD are intended to prevent inability to control the propeller blade angle due to tooth wear in the PCU servo BIS assembly. DATES: Comments must be received by June 27, 1994. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), New England Region, Office of the Assistant Chief Counsel, Attention: Rules Docket No. 94-ANE-26, 12 New England Executive Park, Burlington, MA 01803-5299. Comments may be inspected at this location between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. The service information referenced in the proposed rule may be obtained from Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA. FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (617) 238-7158, fax (617) 238-7199. SUPPLEMENTARY INFORMATION: Comments Invited Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this notice may be changed in light of the comments received. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 94-ANE-26.'' The postcard will be date stamped and returned to the commenter. Availability of NPRMs Any person may obtain a copy of this NPRM by submitting a request to the FAA, New England Region, Office of the Assistant Chief Counsel, Attention: Rules Docket No. 94-ANE-26, 12 New England Executive Park, Burlington, MA 01803-5299. Discussion On August 13, 1993, the Federal Aviation Administration (FAA) issued airworthiness directive (AD) 93-16-02, Amendment 39-8659 (58 FR 44441, August 23, 1993), to require initial and repetitive inspections of the propeller control unit (PCU) servo ballscrew internal spline (BIS) teeth for wear, and replacement, if necessary, of PCU servo BIS assemblies. That action was prompted by a report of an incident where the crew experienced difficulties in feathering and controlling the propeller blade angle. Investigation of the PCU servo BIS assembly revealed excessively worn spline teeth. That condition, if not corrected, could result in inability to control the propeller blade angle due to tooth wear in the PCU servo BIS assembly. Since the issuance of that AD, Hamilton Standard has developed a damper to be installed between the end of the ballscrew and the shoulder of the quill shaft. The damper preloads the quill against the retaining ring and eliminates axial motion between the quill and the ballscrew. This reduces vibration, enhances ballscrew lubrication, and results in an extension of the useful life of the BIS assembly. In addition, the manufacturer has issued revisions to the alert service bulletins (ASB) referenced in the current AD. The FAA has reviewed and approved the technical contents of the following Hamilton Standard ASB's, all dated April 7, 1994: No. 14SF-61-A59, Revision 4; No. 14RF-9-61-A53, Revision 5; No. 14RF-19-61-A25, Revision 4; No. 14RF-21-61-A38, Revision 4; No. 247F-61-A3, Revision 3; and No. 6/5500/ F-61-A11, Revision 4. These revisions enable affected propellers with a ballscrew quill damper installed in accordance with the following Hamilton Standard SB's to extend the repetitive inspection interval from 500 to 1,500 hours time in service (TIS) since last inspection: No. 14SF-61-67, Revision 1, dated May 6, 1994; No. 14RF-9-61-61, dated December 9, 1993; No. 14RF-19-61-29, Revision 1, dated May 6, 1994; No. 14RF-21-61-48, Revision 1, dated May 6, 1994; No. 247F-61-6, Revision 1, dated May 6, 1994; and No. 6/5500/F-61-19, Revision 1, dated May 6, 1994. Since an unsafe condition has been identified that is likely to exist or develop on other products of this same type design, the proposed AD would supersede AD 93-16-02 to increase the repetitive inspection interval from 500 to 1,500 hours TIS since last inspection for propellers that have a ballscrew quill damper installed. There are approximately 2,506 propellers of the affected design in the worldwide fleet. The FAA estimates that 1150 propellers installed on aircraft of U.S. registry would be affected by this proposed AD, that it would take approximately 1.5 work hours per engine to accomplish the proposed actions, and that the average labor rate is $55 per work hour. Based on these figures, and on the average utilization rate of 2,000 hours TIS per year equating to 4 inspections, the total cost impact of the proposed AD per inspection on U.S. operators is estimated to be $379,500. However, based on an average utilization rate of 2,000 hours TIS per year, the proposed AD would eliminate 2.7 inspections per year per propeller, resulting in an approximate yearly cost savings to U.S. operators of $256,163. The regulations proposed herein would not have substantial direct effects 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. Therefore, in accordance with Executive Order 12612, it is determined that this proposal would not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this proposed regulation (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) if promulgated, 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. A copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 of the Federal Aviation Regulations as follows: PART 39--AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89. Sec. 39.13 [Amended] 2. Section 39.13 is amended by removing amendment 39-8659 (58 FR 44441, August 23, 1993) and by adding a new airworthiness directive to read as follows: Hamilton Standard: Docket No. 94-ANE-26. Supersedes AD 93-16-02, Amendment 39-8659. Applicability: Hamilton Standard Models 14RF-9, 14RF-19, 14RF- 21, and 14RF-23; 247F-1; 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, 14SF-23; and 6/5500/F propellers installed on but not limited to Embraer EMB-120 and EMB-120RT; SAAB-SCANIA SF340B; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72, ATR72-210; DeHavilland DHC-8-100 series, DHC-8-300; Construcciones Aeronauticas SA (CASA) CN-235 and CN-235-100; Canadair CL215T and CL415; and British Aerospace ATP airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent the inability to control the propeller blade angle due to tooth wear in the propeller control unit (PCU) servo ballscrew internal spline (BIS) assembly, accomplish the following: (a) Inspect the PCU servo BIS assembly for tooth wear in accordance with the Accomplishment Instructions of the following Hamilton Standard Alert Service Bulletins (ASB), all dated April 7, 1994, as applicable: No. 14RF-9-61-A53, Revision 5; No. 14RF-19-61- A25, Revision 4; No. 14RF-21-61-A38, Revision 4; No. 247F-61-A3, Revision 3; No. 14SF-61-A59, Revision 4; and No. 6/5500/F-61-A11, Revision 4; as follows: (1) For a PCU with unknown time in service (TIS), and unknown TIS since the last inspection, on the effective date of this airworthiness directive (AD), and that does not have a ballscrew quill damper installed, inspect within 200 hours TIS after the effective date of this AD. (2) For a PCU with 1,800 or more hours TIS or unknown TIS on the effective date of this AD, and either has not been inspected, or has been inspected more than 500 hours prior to the effective date of this AD, in accordance with the applicable Hamilton Standard ASB listed in paragraph (a) of this AD; and that does not have a ballscrew quill damper installed; inspect within 200 hours TIS after the effective date of this AD. (3) For a PCU with 1,800 or more hours TIS or unknown TIS on the effective date of this AD, and that has been inspected within the previous 500 hours TIS in accordance with the applicable Hamilton Standard ASB listed in paragraph (a) of this AD, and that does not have a ballscrew quill damper installed, inspect within 500 hours TIS since the last inspection in accordance with the applicable Hamilton Standard ASB listed in paragraph (a) of this AD. (4) For a PCU with less than 1,800 hours TIS on the effective date of this AD, and that does not have a ballscrew quill damper installed, inspect prior to accumulating 1,800 hours TIS, or within 300 hours TIS after the effective date of this AD, whichever occurs later. (5) For a PCU that has a ballscrew quill damper installed in accordance with the following applicable Hamilton Standard Service Bulletins (SB), or previous revisions: No. 14SF-61-67, Revision 1, dated May 6, 1994; No. 14RF-9-61-61, dated December 9, 1993; No. 14RF-19-61-29, Revision 1, dated May 6, 1994; No. 14RF-21-61-48, Revision 1, dated May 6, 1994; No. 247F-61-6, Revision 1, dated May 6, 1994; and No. 6/5500/F-61-19, Revision 1, dated May 6, 1994; inspect within 1,500 hours TIS since installation of the ballscrew quill damper. (6) Thereafter, inspect at intervals described as follows: (i) For propellers that have a ballscrew quill damper installed in accordance with the applicable Hamilton Standard SB listed in paragraph (a)(5) of this AD, or previous revisions, inspect at intervals not to exceed 1,500 hours TIS since the last inspection required by this AD. (ii) For propellers that do not have a ballscrew quill damper installed in accordance with the applicable Hamilton Standard SB listed in paragraph (a)(5) of this AD, inspect at intervals not to exceed 500 hours TIS since the last inspection required by this AD. (7) If PCU servo BIS teeth are worn beyond the limits specified in the Accomplishment Instructions of the applicable ASB's listed in paragraph (a) of this AD, prior to further flight, replace the PCU with a serviceable assembly in accordance with the Acccomplishment Instructions of the applicable ASB's listed in paragraph (a) of this AD, and thereafter reinspect in accordance with paragraphs (a)(6) and (a)(7) of this AD. (b) Report the results of the initial and repetitive inspections required by paragraph (a) of this AD by utilizing Appendix 1, ``Ballscrew Inspection Data,'' within 7 days of the inspection to the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, MA 01803-5299; Telex Number 949301 FAAANE BURL; fax (617) 238-7199. The reporting requirements of this AD terminate on December 31, 1994. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provision of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. Appendix 1 Ballscrew Inspection Data The following information must be reported and sent as soon as possible but no later than 7 days after inspection to: Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, MA 01803- 5299, Fax: (617) 238-7199. Operator/Repair Station---------------------------------------------------------------- Date of Inspection------------------------------------------------------------- PCU Part Number----------------------------------------------------------------- PCU Serial Number----------------------------------------------------------------- Date Damper Installed-------------------------------------------------------------- Aircraft Model--------------------------------------------------------- Aircraft Serial Number----------------------------------------------------------------- Position: Left Engine------------------------------------------------------------ Right Engine----------------------------------------------------------- (please check) (please circle): Estimated Time On PCU-------------------------------------------------- Actual Time On PCU----------------------------------------------------- Time Since New (Hours) ________ Time Since Last Ballscrew Inspection/Repair (Hours) ________ Inspection: Accepted--------------------------------------------------------------- *Rejected-------------------------------------------------------------- *Please indicate in comments if unit was rejected as part of the functional check. No. of left side teeth with steps ________ No. of right side teeth with steps ________ Comments:-------------------------------------------------------------- ---------------------------------------------------------------------- (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. Note: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (d) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. Issued in Burlington, Massachusetts, on May 19, 1994. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 94-13012 Filed 5-26-94; 8:45 am] BILLING CODE 4910-13-P