Rules and Regulations. Final rule; request for comments

Agency: Federal Aviation Administration (FAA), DOT
Action: Final rule; request for comments
Citation: FR Doc. 04-22812 · RIN 2120-AA64 · Docket No. 86-ANE-7; Amendment 39-13822; AD 2004-21-01 · 14 CFR 39

Summary

The FAA is superseding an existing AD for certain Hartzell Propeller Inc. (formerly Hartzell Propeller Products Division) Model HC-B5MP-3( )/M10282A( )+6 five bladed propellers. That AD currently requires initial and repetitive torque check inspections on the attach bolts on certain model Hartzell HC-B5MP-3 five bladed propellers, and replacement of attach bolts if necessary. This AD requires the same inspections, but reduces compliance time for the initial inspection on certain Short Brothers Ltd. Model SD3-30 airplanes to before further flight and within 100 hours time-in-service for propellers installed on certain Aerospatiale (Nord) Model 262A airplanes. This AD also requires repetitive torque check inspections at reduced intervals on SD3-30 airplanes, and requires additional visual inspections of mounting flanges, and threads in hub bolt holes, and replacement of attach bolts and hubs, if necessary. This AD results from four reports in the last 12 months of eleven cracked or failed propeller attach bolts on Short Brothers Model SD3-30 airplanes. We are issuing this AD to prevent propeller separation from the airplane.

Dates

Effective October 19, 2004. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of October 19, 2004. We must receive any comments on this AD by December 13, 2004.

Supplementary Information

On March 7, 1986, the FAA issued AD 86-06-02, Amendment 39-5259 (51 FR 10613, March 28, 1986). That AD requires initial and repetitive torque check inspections on the attach bolts on certain model Hartzell HC-B5MP-3 five bladed propellers installed on Aerospatiale (Nord) Model 262A airplanes modified by Supplemental Type Certificate (STC) SA2369SW, and Short Brothers Ltd. Model SD3-30 airplanes. Some SD3-30 airplanes are military surplus C23-A Sherpas airplanes. That AD was the result of investigations that revealed fretting wear between the engine and propeller mating flanges. The fretting wear results in loss of attach bolt preload, causing failure of the attach bolts. That condition, if not corrected, could result in propeller separation from the airplane. Actions Since AD 86-06-02 Was Issued Since February 2004, we received four reports of failed propeller attach bolts, part number (P/N) B-3339: • In February 2004, an operator reported a cracked Hartzell propeller attach bolt. The operator discarded the bolt and we could not perform a metallurgical investigation on the bolt. • In June of 2004, another operator reported two broken propeller attach bolts. Both bolts were examined and one was selected for metallurgical investigation. This bolt was found to meet type design. • In September of 2004, the Milwaukee Flight Standards District Office informed us that they received an operator's report of seven cracked or failed propeller attach bolts. All seven bolts were installed on the same propeller, and were found after a pilot reported problems with engine controls. We contacted Hartzell for assistance in investigating the bolt failure. The propeller hub and engine flange are being investigated for fretting, flatness, and thread damage. • In late September of 2004, during the review of the maintenance history of one of the above propellers, we found a fourth event of a cracked propeller attach bolt. Relevant Service Information We have reviewed and approved the technical contents of Hartzell Alert Service Bulletin (ASB) A203A, dated January 5, 1995, that describes procedures for performing initial and repetitive inspections of attach bolts and if necessary, visual inspections of propeller mounting flanges. Differences Between This AD and the Service Information Although Hartzell ASB A203A, dated January 5, 1995, requires an initial torque check inspection within the next 100 hours TIS from the effective date of the original bulletin (dated September 2, 1994) for Short Brothers Ltd. Model SD3-30 airplanes, this AD requires an initial torque check inspection before further flight for SD3-30 airplanes. Also, although that ASB requires an initial torque check inspection within the next 120 hours TIS from the effective date of the original bulletin (September 2, 1994) for Aerospatiale (Nord) Model 262A airplanes, this AD requires an initial torque check inspection within 100 hours TIS for 262A airplanes. FAA's Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other Model HC-B5MP-3( )/M10282A( )+6 five bladed propellers of the same type design installed on Aerospatiale (Nord) Model 262A airplanes modified by STC SA2369SW, and Short Brothers Ltd. Model SD3-30 airplanes. We are issuing this AD to prevent propeller separation from the airplane. This AD requires the following: • Before further flight, performing an initial torque check inspection of the propeller attach bolts on Short Brothers Ltd. Model SD3-30 airplanes unless already done within the last 120 hours TIS before the effective date of this AD; and • Repetitive torque check inspections of the propeller attach bolts within 120 hours TIS from the last inspection. • Within 100 hours TIS after the effective date of this AD, performing an initial torque check inspection of the propeller attach bolts on Aerospatiale (Nord) Model 262A airplanes; and • Repetitive torque check inspections of the propeller attach bolts within 100 hours TIS from the last inspection. • If the bolts fail the torque check, then visually inspect threads in hub bolt holes, and replace attach bolts and hub if necessary. You must use the service information described previously to perform the actions required by this AD. FAA's Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Interim Action These actions are interim actions and we may take further rulemaking actions in the future. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include “AD Docket No. 86-ANE-7” in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will date-stamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us verbally, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments. We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications with you. You may get more information about plain language at http://www.faa.gov/language and http://www.plainlanguage.gov/. Examining the AD Docket You may examine the AD Docket (including any comments and service information), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the 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. 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 by sending a request to us at the address listed under ADDRESSES . Include “AD Docket No. 86-ANE-7” in your request. 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 part 39 of the Federal Aviation Regulations (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 39-5259 (51 FR 10613, March 28, 1986), and by adding a new airworthiness directive, Amendment 39-XXXXX, to read as follows: 2004-21-01 Hartzell Propeller Inc. (formerly Hartzell Propeller Products Division): Amendment 39-13822. Docket No. 86-ANE-7. Supersedes AD 86-06-02, Amendment 39-5259. Effective Date (a) This airworthiness directive (AD) becomes effective October 19, 2004. Affected ADs (b) This AD supersedes AD 86-06-02. Applicability (c) This AD applies to Hartzell Propeller Inc. (formerly Hartzell Propeller Products Division) Model HC-B5MP-3( )/M10282A( )+6 five-bladed propellers installed on, Aerospatiale (Nord) Model 262A airplanes modified by Supplemental Type Certificate (STC) SA2369SW, and Short Brothers Ltd. Model SD3-30 airplanes. Unsafe Condition (d) This AD results from four reports in the last 8 months of eleven cracked or failed Hartzell propeller attach bolts, part number (P/N) B-3339, on Short Brothers Model SD3- 30 airplanes. The actions specified in this AD are intended to prevent propeller separation from the airplane. (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. Torque Check Requirements for Short Brothers Ltd. Model SD3-30 Airplanes (f) Before further flight, for propellers installed on Short Brothers Ltd. Model SD3-30 airplanes, do the following: (1) Perform an initial torque check inspection of the Hartzell propeller attach bolts, P/N B-3339, unless already done within 120 hours time-in-service (TIS) before the effective date of this AD, and thereafter, within 120 hour TIS intervals since the last inspection. Use Procedure #1 “Mounting Bolt Torque Check” of Hartzell Alert Service Bulletin (ASB) A203A, dated January 5, 1995, to do the inspections. (2) If the torque check fails, remove the propeller and go to paragraph (h) of this AD. Torque Check Requirements for Aerospatiale (Nord) Model 262A Airplanes Modified by STC SA2369SW (g) For propellers installed on Aerospatiale (Nord) Model 262A airplanes modified by STC SA2369SW, do the following: (1) Perform an initial torque check inspection of the Hartzell propeller attach bolts, P/N B-3339, within 100 hours TIS after the effective date of this AD, and thereafter, within 100 hour TIS intervals since the last inspection. Use Procedure #1 “Mounting Bolt Torque Check” of Hartzell Alert Service Bulletin (ASB) A203A, dated January 5, 1995, to do the inspections. (2) If the torque check fails, remove the propeller and go to paragraph (h) of this AD. Inspection and Rework of Engine and Propeller Mounting Flange Surfaces and Hub Mounting Bolt Holes (h) When the propeller is removed due to failing the torque check in Procedure #1 of Hartzell ASB A203A, dated January 5, 1995, inspect and rework if necessary, the engine and propeller mounting flange surfaces. Use Procedure #2 “Engine/Propeller Mounting Flanges” of Hartzell ASB A203A, dated January 5, 1995, to do the inspections and rework. Also inspect the hub mounting bolt holes as follows: (1) Clean bolt holes using Stoddard solvent or equivalent and a soft bristle brush. (2) Visually inspect the area around the bolt holes. No deformations, evidence of rework, depressions, or protrusions around bolt holes are permitted, except for an edge chamfer of the bolt hole up to 0.030 inch. (3) Using a 10X magnification, and an appropriate light source, visually inspect threads for chipping, missing material, deformation, and scratches. No damage is permitted. (4) Using a new P/N B-3339 bolt, check threads by threading bolt by hand into the bolt hole. The bolt must thread in easily with no binding. (5) Any hub with a bolt hole showing one or more of the prohibited conditions specified in paragraphs (h)(2) through (h(4) must be removed from service. Preparation of Propeller Attach Bolts (i) Before installing any Hartzell propeller attach bolt P/N B-3339, apply anti-seize compound MIL-PRF-83483, to the threaded surfaces of the attach bolt. Do not use any other anti-seize compound on attach bolts. Preparation of Propeller Mounting and Engine Flanges (j) Before installing a Hartzell HC-B5MP-3( )/M10282A( )+6 propeller, the propeller mounting flange and engine flange must be clean and dry. Do not use anti-fretting compounds on the flanges. You may install an FAA-approved Pratt & Whitney shim between the propeller mount flange and engine flange. Alternative Methods of Compliance (k) The Manager, Chicago Aircraft 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. Special Flight Permits (l) Under 14 CFR part 39.23, special flight permits are prohibited. Material Incorporated by Reference (m) You must use Hartzell Alert Service Bulletin A203A, dated January 5, 1995, to perform the procedures referenced 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. You can get a copy from Hartzell Propeller Inc. Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 778-4391. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Related Information (n) Information on propeller removal and installation procedures can be found in Hartzell Propeller Inc. Service Instruction 140A. Issued in Burlington, Massachusetts, on October 4, 2004. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. FR Doc. 04-22728 Filed 10-13-04; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2003-CE-68-AD; Amendment 39-13823; AD 2004-21-02] RIN 2120-AA64 Airworthiness Directives; Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa “PZL-Bielsko” Model SZD-50-3 “Puchacz” Sailplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA adopts a new airworthiness directive (AD) for all Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa “PZL-Bielsko” (PZL-Bielsko) Model SZD-50-3 “Puchacz” sailplanes. This AD requires you to repetitively inspect the front and back of the fuselage front bulkhead attachment fitting for cracks and replace the attachment fitting if any cracks are found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Poland. We are issuing this AD to detect and correct cracks in the fuselage front bulkhead attachment fitting, which could result in structural failure of the bulkhead. This failure could lead to loss of control of the sailplane. DATES: This AD becomes effective on November 29, 2004. As of November 29, 2004, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: You may get the service information identified in this AD from Przedsiebiorstwo Doświadczalno-Produkcyjne Szybownictwa PZL-Bielsko, ul. Cieszyńska 325, 43-300 Bielsko-Biala: telephone: +48 033 812 50 21; facsimile: +48 033 812 37 39. You may view the AD docket at FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2003-CE-68-AD, 901 Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. to 4 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. SUPPLEMENTARY INFORMATION: Discussion What events have caused this AD? The General Inspectorate of Civil Aviation (GICA), which is the airworthiness authority for Poland, recently notified FAA that an unsafe condition may exist on all PZL-Bielsko Model SZD-50-3 “Puchacz” sailplanes. The GICA reports that cracks were detected in the front bracket console mounted on the fuselage front bulkhead. What is the potential impact if FAA took no action? This condition, if not detected and corrected, could cause the fuselage front bulkhead to fail. Failure of the fuselage front bulkhead could result in loss of control of the sailplane. Has FAA taken any action to this point? We issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all PZL-Bielsko Model SZD-50-3 “Puchacz” sailplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on April 21, 2004 (69 FR 21444). The NPRM proposed to require you to repetitively inspect the front and back of the fuselage front bulkhead attachment fitting for cracks, and replace any cracked attachment fitting found. Is there a modification I can incorporate instead of repetitively inspecting the front and back of the fuselage front bulkhead attachment fitting for cracks? The FAA has determined that long-term continued operational safety would be better assured by design changes that remove the source of the problem rather than by repetitive inspections or other special procedures. With this in mind, FAA will continue to work with PZL-Bielsko in performing further tests to determine the cause of the cracking and to provide a corrective action that would terminate the need for repetitive inspections. What is the difference between this AD and the service information? The manufacturer's service information allows continued flight if cracks are found in the fuselage front bulkhead attachment fitting that do not exceed certain limits. The applicable service bulletin specifies replacement of the fuselage front bulkhead attachment fitting only if cracks are found exceeding this limit. This AD will not allow continued flight if any crack is found. FAA policy is to disallow sailplane operation when known cracks exist in primary structure, unless the ability to sustain ultimate load with these cracks is proven. The fuselage front bulkhead is considered primary structure, and the FAA has not received any analysis to prove that ultimate load can be sustained with cracks in this area. Comments Was the public invited to comment? We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion What is FAA's final determination on this issue? We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: —Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and —Do not add any additional burden upon the public than was already proposed in the NPRM. Changes to 14 CFR Part 39—Effect on the AD How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions. Costs of Compliance How many sailplanes does this AD impact? We estimate that this AD affects 8 sailplanes in the U.S. registry. What is the cost impact of this AD on owners/operators of the affected sailplanes? We estimate the following costs to accomplish the inspection: Labor cost Parts cost Total cost per sailplane Total cost on U.S. operators 2 workhours × $65 per hour = $130 Not applicable $130 $130 × 8 = $1,040. We estimate the following costs to accomplish any necessary replacement that will be required based on the results of this inspection. We have no way of determining the number of sailplanes that may need such a replacement: Labor cost Parts cost Total cost per sailplane 10 workhours × $65 per hour = $650 $680 $650 + $680 = $1,330. Regulatory Findings Will this AD impact various entities? We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Will this AD involve a significant rule or regulatory action? 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 the 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 by sending a request to us at the address listed under ADDRESSES. Include “AD Docket No. 2003-CE-68-AD” in your request. 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 part 39 of the Federal Aviation Regulations (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. FAA amends § 39.13 by adding a new AD to read as follows: 2004-21-02 Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa “PZL-Bielsko”: Amendment 39-13823; Docket No. 2003-CE-68-AD. When Does This AD Become Effective? (a) This AD becomes effective on November 29, 2004. What Other ADs Are Affected by This Action? (b) None. What Sailplanes Are Affected by This AD? (c) This AD affects Model SZD-50-3 “Puchacz” sailplanes, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Poland. We are issuing this AD to detect and correct cracks in the fuselage front bulkhead attachment fitting, which could result in structural failure of the bulkhead. This failure could lead to loss of control of the sailplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Using a flouorescent dye-penetrant or dye-check method, inspect the front and back of the fuselage front bulkhead attachment fitting for cracks Within the next 25 hours time-in-service (TIS) after November 29, 2004 (the effective date of this AD). Repetitively inspect thereafter at intervals not to exceed 12 calendar months Follow Przedsiebiorstwo Doświadczalno-Produkcyjne Szybownictwa PZL-Bielsko (PDPS “PZL-Bielsko”) Mandatory Bulletin No. BE-048/SZD-50-3/2000 “Puchacz”, dated June 6, 2000. (2) If cracks are found during any inspection required in paragraph (e)(1) of this AD, replace the fuselage front bulkhead attachment fitting Prior to further flight after any inspection required in paragraph (e)(1) of this AD in which cracks are found. After replacing the fuselage front bulkhead attachment fitting, continue with the repetitive inspections required in paragraph (e)(1) of this AD Follow Przedsiebiorstwo Doświadczalno-Produkcyjne Szybownictwa PZL-Bielsko (PDPS “PZL-Bielsko”) Mandatory Bulletin No. BE-049/SZD-50-3/2000 Puchacz”, dated September 14, 2000. May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Przedsiebiorstwo Doświadczalno-Produkcyjne Szybownictwa PZL-Bielsko (PDPS “PZL-Bielsko”) Mandatory Bulletin No. BE-048/SZD-50-3/2000 “Puchacz”, dated June 6, 2000; and Przedsiebiorstwo Doświadczalno-Produkcyjne Szybownictwa PZL-Bielsko (PDPS “PZL-Bielsko”) Mandatory Bulletin No. BE-049/SZD-50-3/2000 “Puchacz”, dated September 14, 2000. 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. You may get a copy from Przedsiebiorstwo Doświadczalno-Produkcyjne Szybownictwa PZL-Bielsko, ul. Cieszyńska 325, 43-300 Bielsko-Biala: telephone: +48 033 812 50 21; facsimile: +48 033 812 37 39. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Is There Other Information That Relates to This Subject? (h) Republic of Poland AD Number SP-0059-2000-A, dated June 5, 2000, and AD Number SP-0094-2000-A, dated September 18, 2000, also address the subject of this AD. Issued in Kansas City, Missouri, on October 5, 2004. Dorenda D. Baker, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-22812 Filed 10-13-04; 8:45 am]