FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2006-02 This electronic copy may be printed and used in lieu of the FAA biweekly paper copy.

U.S. Department of Transportation Federal Aviation Administration Regulatory Support Division Delegation and Airworthiness Programs Branch, AIR-140 P. O. Box 26460 Oklahoma City, OK 73125-0460 FAX 405-954-4104

2

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.

Information

Manufacturer

Applicability

Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2006-01 2005-26-10 2005-26-11 2005-26-12

S 2004-08-13

2005-26-13 2005-26-14

S 2002-22-11

2005-26-53

E

Engine Components Inc. DG Flugzeugbau GmbH Burkhardt Grob Luft-Und Raumfahrt Gmbh & Co Kg Turbomeca Burkhardt Grob Luft-Und Raumfahrt Gmbh & Co Kg Pacific Aerospace Corporation

See AD Sailplane: DG-800B and DG-500MB Sailplane: G103 Twin Astir, G103 Twin II, G103A Twin 11 Acro, G103C Twin III Acro, and G 103 Twin III SL Engine: Artouste III B, B1, and D turboshaft Sailplane: G103 Twin Astir

Turbomeca S.A. American Champion Aircraft Corp.

Engine: Arrius Models 2B, 2B1, and 2F 7ECA, 7GCAA, 7GCBC, 8KCAB, and 8GCBC, 7AC, 7ACA, S7AC, 7BCM, 7CCM, S7CCM, 7DC, S7DC, 7EC, S7EC, 7ECA, 7FC, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBA, 7GCBC, 7HC, 7JC, 7KC, 7KCAB, 8KCAB, and 8GCBC 750XL

750XL

Biweekly 2006-02 2001-08-14R1 2005-24-10

R 2001-08-14

2005-26-53 2006-01-05

S 87-12-05

Pacific Aerospace Corporation Ltd. Honeywell International Inc.

2006-01-11 2006-02-51

E

Cessna Raytheon

3

Engine: T5309, T5311, T5313B, T5317A, T5317A-1, and T5317B series turboshaft, T53-L-9, T53-L-11, T53-L-13B, T53-L-13BA, T53-L-13B S/SA, T53-L-13B S/SB, T53-L-13B/D, and T53-L-703 series turboshaft 208 and 208B 390

BW 2006-02 TURBOMECA S.A. AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2001-08-14R1 Turbomeca S.A.: Amendment 39-14423. Docket No. 2000-NE-12-AD. Revises AD 2001-08-14, Amendment 39-12218. Applicability This AD applies to Arrius Models 2B, 2B1, and 2F engines. These engines are installed on but not limited to Eurocopter France Model EC120B and Eurocopter Deutschland EC135 T1 rotorcraft. Note 1: This AD applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. To prevent engine flameout and the inability to maintain the 2.5 minutes one engine inoperative (OEI) rating due to blockage of the fuel injection manifolds, do the following: Initial Replacement (a) If not already done in accordance with Turbomeca Alert Service Bulletin (ASB) No. A319 73 2012, Revision 2, dated May 25, 1999, or Revision 3, dated July 21, 2000, or ASB No. A319 73 4001, Revision 3, dated May 25, 1999, or Revision 4, dated October 20, 2000, replace injector manifolds and borescope-inspect the flame tube and the high pressure turbine area within 30 days after the effective date of this AD, or prior to exceeding 200 hours time-in-service (TIS), whichever is later. Do these in accordance with Instructions 2.A. through 2.C. of Turbomeca ASB No. A319 73 2012, Revision 6, dated August 14, 2004, for Arrius 2B and 2B1 turboshaft engines, and ASB No. A319 73 4001, Revision 7, dated August 14, 2004, for Arrius 2F turboshaft engines, except that replacement may be done at any appropriately rated repair shop.

4

2008-08-14R1 2

Repetitive Replacements (b) Thereafter, replace injector manifolds, in accordance with Instructions 2.A. through 2.C. of Turbomeca ASB No. A319 73 2012, Revision 6, dated August 14, 2004, for Arrius 2B and 2B1 turboshaft engines, and ASB No. A319 73 4001, Revision 7, dated August 14, 2004, for Arrius 2F turboshaft engines, except that replacement may be done at any appropriately rated repair shop, as follows: (1) For Arrius 2B and 2B1 engines, replace within 200 hours TIS since last injector manifolds replacement. (2) For Arrius 2F engines, replace within 400 hours TIS since last injector manifolds replacement. (3) For all engines, replace injector manifolds before further flight after performing the applicable flight manual or overhaul manual power check if that check shows a negative turbine outlet temperature (TOT) margin or negative T4 margin. Definition (c) For the purposes of this AD, time-in-service (TIS) is defined as the number of engine operating hours on the manifolds since the manifolds were new or since the manifolds were refurbished. Alternative Methods of Compliance (d) 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, Engine Certification Office. Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. Special Flight Permits (e) Special flight permits may be issued in accordance with §§ 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. Documents That Have Been Incorporated by Reference (f) The inspections and replacements must be done in accordance with the following Turbomeca S.A. mandatory alert service bulletins (ASBs): Document No. ASB No. A319 73 2012, Total pages: 8 ASB No. A319 73 4001, Total pages: 8

Pages 8 8

Revision 6 7

Date August 14, 2004. August 14, 2004.

The Director of the Federal Register approved the incorporation by reference of these service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Turbomeca S.A., 40220 Tarnos, France; telephone: (33) 05 59 64 40 00; fax: (33) 05 59 64 60 80. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New 5

2008-08-14R1 3

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/cfr/ibr-locations.html. Note 3: The subject of this AD was addressed by the Direction Generale de L'Aviation Civile (DGAC), which is the airworthiness authority for France, in airworthiness directives AD 1999217(A) and AD 1999-233(A). Effective Date (g) This airworthiness directive (AD) becomes effective February 23, 2006. Issued in Burlington, Massachusetts, on January 9, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06-366 Filed 1-18-06; 8:45 am] BILLING CODE 4910-13-P

6

BW 2006-02 AMERICAN CHAMPION AIRCRAFT CORP. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-24-10 American Champion Aircraft Corp.: Amendment 39-14390; Docket No. FAA-200523025; Directorate Identifier 2005-CE-50-AD. When Does This AD Become Effective? (a) This AD becomes effective on January 17, 2006. Are Any Other ADs Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models, all serial numbers, that are certificated in any category: MODELS (1) 7ECA, 7GCAA, 7GCBC, 8KCAB, and 8GCBC that: (i) were manufactured before August 12, 2005; and (ii) have less than 250 hours time-in-service (TIS). (2) 7AC, 7ACA, S7AC, 7BCM, 7CCM, S7CCM, 7DC, S7DC, 7EC, S7EC, 7ECA, 7FC, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBA, 7GCBC, 7HC, 7JC, 7KC, 7KCAB, 8KCAB, and 8GCBC that: (i) have installed a flight control cable (or flight control cable included in a wing retrofit kit) that was purchased from American Champion Aircraft Corp. (ACAC) before August 12, 2005; and (ii) have less than 250 hours TIS since the above installation. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of partial loss of aileron control because an incorrectly swaged cable sleeve allowed the cable to slip. We are issuing this AD to detect and correct incorrect swaging width of the flight control cable Nicopress sleeves, which could result in failure of the elevator, rudder, aileron, and flap controls. This failure could lead to loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

7

2005-24-10 2

Actions (1) If you operate the airplane before the inspection required in paragraph (e)(2) of this AD, do one of the following: (i) Fabricate (using letters at least 1⁄8-inch in height) a warning placard with the following language and install this placard in the cockpit in full view of the pilot: "Acrobatic flight prohibited!"; or (ii) Add the following statement to the Limitations Section of the Pilots Operating Handbook (POH): "Acrobatic flight prohibited until the inspection and replacement requirements of AD 2005– 24–10 are done." To do this, you may insert a copy of this AD into the Limitations Section of the POH. (2) Inspect the Nicopress sleeves on the following flight control cables for the correct width. Each sleeve has three swages or crimps and must not exceed a maximum width of 0.354 inches: (i) Elevator cables in 6 locations; (ii) Rudder cables in 4 locations; (iii) Aileron cables in 12 locations; and (iv) Flap cables in 6 locations. (3) If you find any flight control cable Nicopress swages of incorrect width during the inspection required in paragraph (e)(2) of this AD, replace the affected cables. (4) If you performed the actions in paragraph (e)(1) of this AD, remove the temporary placard or POH limitation after completing the actions required in paragraphs (e)(2) and (e)(3) of this AD.

Compliance Before further flight after January 17, 2006 (the effective date of this AD).

Procedures No specific procedures are necessary for this action. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the placard or POH requirements. Make an entry into the aircraft records showing compliance with these portions of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

Within 25 hours TIS Follow ACAC Service Letter after January 17, #427, Revision B, dated 2006 (the effective November 29, 2005. date of this AD).

Within 25 hours TIS Follow ACAC Service Letter after January 17, #427, Revision B, dated 2006 (the effective November 29, 2005. date of this AD). After completing the actions required in paragraphs (e)(2) and (e)(3) of this AD.

8

No specific procedures are necessary for this action. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the placard or POH requirements. Make an entry into the aircraft records showing compliance with these portions of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

2005-24-10 3

(5) If you find any flight control cable Nicopress swages of incorrect width during the inspection required in paragraph (e)(2) of this AD, report the findings to FAA. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 and those following sections) and assigned OMB Control Number 2120– 0056.

Within 10 days after the incorrect swage widths are found or within 10 days after January 17, 2006 (the effective date of this AD), whichever occurs later.

Include in your report the aircraft model, TIS of the flight control cable Nicopress swage, which cable swage was affected and its location, corrective action taken, and a point of contact name and phone number. Send your report to Wess Rouse, Small Airplane Project Manager, ACE–117C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; facsimile: (847) 294– 7834; e-mail: [email protected].

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, Chicago Aircraft Certification Office, FAA. For information on any already approved alternative methods of compliance, contact Wess Rouse, Small Airplane Project Manager, ACE-117C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; telephone: 847-294-8113; facsimile: (847) 294-7834; e-mail: [email protected]. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in ACAC Service Letter 427, Revision B, dated November 29, 2005. 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. To get a copy of this service information, contact American Champion Aircraft Corporation, P.O. Box 37, 32032 Washington Avenue, Rochester, WI 53167; telephone: (262) 534-6315; Internet address: http://www.amerchampionaircraft.com. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-23025; Directorate Identifier 2005-CE-50-AD. Issued in Kansas City, Missouri, on December 23, 2005. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-49 Filed 1-6-06; 8:45 am] BILLING CODE 4910-13-P

9

BW 2006-02 PACIFIC AEROSPACE CORPORATION LTD. AIRWORTHINESS DIRECTIVE FINAL RULE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-26-53 Pacific Aerospace Corporation Ltd.: Amendment 39-14451; Docket No. FAA-200523473; Directorate Identifier 2005-CE-54-AD. When Does This AD Become Effective? (a) This AD becomes effective on January 16, 2006, to all affected persons who did not receive emergency AD 2005-26-53, issued December 22, 2005. Emergency AD 2005-26-53 contained the requirements of this amendment and became effective immediately upon receipt. Are Any Other ADs Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model 750XL airplanes, 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 New Zealand. We are issuing this AD to reduce the maximum takeoff weight that will allow wing ultimate load requirements to be met. If wing ultimate load requirements are not met, wing failure could result and subsequent loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

10

2005-26-53 2

Actions Insert the following information into the Limitations Section of the Airplane Flight Manual (AFM). You may do this by inserting a copy of this AD into the Limitations Section of the AFM. "The maximum takeoff weight is reduced from 7,500 pounds to 7,125 pounds."

Compliance Prior to further flight after January 16, 2006 (the effective date of this AD), except for those who received emergency AD 2005–26–53, issued December 22, 2005, unless already done. Emergency AD 2005–26–53 contained the requirements of this amendment and became effective immediately upon receipt.

Procedures The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the flight manual changes requirement of this AD. Make an entry in the aircraft records showing compliance with this portion of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

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 Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? (g) Civil Aviation Authority airworthiness directive DCA/750XL/7, dated December 22, 2005, also addresses the subject of this AD. Issued in Kansas City, Missouri, on January 5, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-260 Filed 1-13-06; 8:45 am] BILLING CODE 4910-13-P

11

BW 2006-02 HONEYWELL INTERNATIONAL INC. AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2006-01-05 Honeywell International Inc. (formerly AlliedSignal, Inc., formerly Textron Lycoming, formerly Avco Lycoming): Amendment 39-14444. Docket No. FAA-2004-18038; Directorate Identifier 2004-NE-01-AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 16, 2006. Affected ADs (b) This AD supersedes AD 87-12-05, Amendment 39-5640. Applicability (c) This AD applies to Honeywell International Inc., (formerly AlliedSignal, Inc., formerly Textron Lycoming, formerly Avco Lycoming) T5309, T5311, T5313B, T5317A, T5317A-1, and T5317B series turboshaft engines, installed on Bell 204, Bell 205, and Kaman K-1200 series helicopters, and T53-L-9, T53-L-11, T53-L-13B, T53-L-13BA, T53-L-13B S/SA, T53-L-13B S/SB, T53-L-13B/D, and T53-L-703 series turboshaft engines, installed on Bell AH-1 and UH-1 helicopters, certified under § 21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 or 14 CFR 21.27). Unsafe Condition (d) This AD results from the manufacturer informing us of test and analysis showing lower calculated service life limits for certain parts, than originally determined. We are issuing this AD to prevent failure of certain compressor, gas producer, and power turbine rotating components, which could result in failure of the engine and possible damage to the helicopter. 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. T5309, T5311, T53-L-9, and T53-L-11 Series Turboshaft Engines (f) For T5309, T5311, T53-L-9, and T53-L-11 series turboshaft engines, within 100 operating hours or 90 days after the effective date of this AD, whichever occurs first, compute the total

12

2006-01-05 2

operating hours and cycles and replace rotating components before they exceed the new service life limits. Use 2.a. through 2.f. and Component Service Life Limits Table 1 of Accomplishment Instructions of Lycoming Service Bulletin (SB) No. 0002, Revision 2, dated March 6, 1989. T5313B, T5317A, T5317A-1, and T5317B Turboshaft Engines (g) For T5313B, T5317A, T5317A-1, and T5317B turboshaft engines, within 100 operating hours or 90 days after the effective date of this AD, whichever occurs first, compute the total operating hours and cycles and replace the rotating components before they exceed the new service life limits. Use 2.A. through 2.K. and Component Service Life Limits Table 1 of Accomplishment Instructions of Honeywell International Inc. SB No. T5313B/17-0020, Revision 7, dated November 21, 2002. (h) For T5313B, T5317A, T5317A-1, and T5317B turboshaft engines that have one or more rotating components that exceed the limits specified in Component Service Life Limits Table 1 of Honeywell International Inc. SB No. T5313B/17-0020, Revision 7, dated November 21, 2002, replace the components using the applicable draw-down schedule in Table 1 of Honeywell International Inc. SB No. T5313B-0125, dated March 15, 2001 or Honeywell International Inc. SB No. T5317-0125, dated March 15, 2001. T53-L-13B, T53-L-13BA, T53-L-13B S/SA, and T53-L-13B S/SB Turboshaft Engines (i) For T53-L-13B, T53-L-13BA, T53-L-13B S/SA, and T53-L-13B S/SB turboshaft engines, within 100 operating hours or 90 days after the effective date of this AD, whichever occurs first, compute the total operating hours and cycles and replace the rotating components before they exceed the new service life limits. Use 2.A. through 2.J. and Component Service Life Limits Table 1 of Accomplishment Instructions of Honeywell International Inc. SB No. T53-L-13B-0020, Revision 3, dated October 25, 2001. (j) For T53-L-13B, T53-L-13BA, T53-L-13B S/SA, and T53-L-13B S/SB turboshaft engines that have one or more rotating components that exceed the limits in Component Service Life Limits Table 1 of Honeywell SB No. T53-L-13B-0020, Revision 3, dated October 25, 2001, replace the components using the applicable draw-down schedule in Table 1 of Honeywell International Inc. SB No. T53-L-13B-0125, dated April 5, 2001. T53-L-13B/D Turboshaft Engines (k) For T53-L-13B/D turboshaft engines, within 100 operating hours or 90 days after the effective date of this AD, whichever occurs first, compute the total operating hours and cycles and replace the rotating components before they exceed the new service life limits. Use 2.A. through 2.J. and Component Service Life Limits Table 1 of Accomplishment Instructions of Honeywell International Inc. SB No. T53-L-13B/D-0020, Revision 2, dated November 25, 2002. (l) For T53-L-13B/D turboshaft engines that have one or more rotating components that exceed the limits in Component Service Life Limits Table 1 of Honeywell International Inc. SB No. T53-L-13B/D-0020, Revision 2, dated November 25, 2002, replace the components using the applicable draw-down schedule in Table 1 of Honeywell International Inc. SB No. T53-L-13B/D0125, dated April 5, 2001.

13

2006-01-05 3

T53-L-703 Turboshaft Engines (m) For T53-L-703 turboshaft engines, within 100 operating hours or 90 days after the effective date of this AD, whichever occurs first, compute the total operating hours and cycles and replace the rotating components, before they exceed the new service life limits. Use 2.A. through 2.K. and Component Service Life Limits Table 1 of Accomplishment Instructions of Honeywell International Inc. SB No. T53-L-703-0020, Revision 2, dated November 25, 2002. (n) For T53-L-703 turboshaft engines that have one or more rotating components that have exceeded the limits in Component Service Life Limits Table 1 of Honeywell International Inc. SB No. T53-L-703-0020, Revision 2, dated November 25, 2002, replace the components using the applicable draw-down schedule in Table 1 of Honeywell International Inc. SB No. T53-L-703-0125, dated April 5, 2001. Action for Engines With Unknown Accumulated Hour or Cycle Information (o) For any engines operating with parts affected by this AD for which accumulated operating hour or cycle information is unknown, those parts must be removed from service within 250 cycles after the effective date of this AD. Computing Compliance Intervals (p) For the purposes of this AD, use the effective date of this AD for computing compliance intervals whenever the SBs refer to the release date of the SB. Prohibition of Removed Rotating Components (q) Do not reinstall any rotating component that is replaced as specified in paragraphs (f) through (n) of this AD, into any engine. Alternative Methods of Compliance (r) The Manager, Los Angeles 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. Related Information (s) None. Material Incorporated by Reference (t) You must use the service information specified in Table 1 of this AD to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of Honeywell International Inc. Service Bulletin No. T53-L-13B-0020, Revision 3, dated October 25, 2001, listed in Table 1 of this AD as of June 13, 2002 (67 FR 31111, May 9, 2002). The Director of the Federal Register approved the incorporation by reference of the other documents listed in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Honeywell International Inc., Attn: Data Distribution, M/S 64-3/2101-201, P.O. Box 29003, Phoenix,

14

2006-01-05 4

AZ 85038-9003; telephone: (602) 365-2493; fax: (602) 365-5577 for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 205900001, on the Internet at http://dms.dot.gov, 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/cfr/ibr-locations.html TABLE 1.–INCORPORATION BY REFERENCE Service Bulletin No. Page Revision Textron Lycoming Service Bulletin (SB) No. 0002 Total Pages: 4 Honeywell International Inc. SB No. T5313B/17–0020 Total Pages: 14 Honeywell International Inc. SB No. T5313B–0125 Total Pages: 6 Honeywell International Inc. SB No. T5317–0125 Total Pages: 5 Honeywell International Inc. SB No. T53–L–13B–0020 Total Pages: 13 Honeywell International Inc. SB No. T53–L–13B–0125 Total Pages: 6 Honeywell International Inc. SB No. T53–L–13B/D–0020 Total Pages: 13 Honeywell International Inc. SB No. T53–L–13B/D–0125 Total Pages: 6 Honeywell International Inc. SB No. T53–L–703–0020 Total Pages: 13 Honeywell International Inc. SB No. T53–L–703–0125 Total Pages: 6

Date

ALL

2

March 6, 1989.

ALL

7

November 21, 2002.

ALL

Original

March 15, 2001.

ALL

Original

March 15, 2001.

ALL

3

October 25, 2001.

ALL

Original

April 5, 2001.

ALL

2

November 25, 2002.

ALL

Original

April 5, 2001.

ALL

2

November 25, 2002.

ALL

Original

April 5, 2001.

Issued in Burlington, Massachusetts, on December 28, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06-63 Filed 1-11-06; 8:45 am]

15

BW 2006-02 CESSNA AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2006-01-11 The Cessna Aircraft Company: Amendment 39-14450; Docket No. FAA-2005-21275; Directorate Identifier 2005-CE-28-AD. When Does This AD Become Effective? (a) This AD becomes effective on February 22, 2006. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Models 208 and 208B, 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 reports of several accidents involving the affected airplanes during operations in-flight and in ground icing conditions. We are issuing this AD to provide a safe method to detect ice, snow, frost, or slush adhering to the upper wing (a critical surface) prior to takeoff; and to reduce drag in-flight by shedding ice on the cargo pod and landing gear fairings. Ice adhering to the upper wing surface, cargo pod, or landing gear fairings could result in a reduction in airplane performance with the consequences that the airplane cannot perform a safe takeoff or climb or maintain altitude. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

16

2006-01-11 2

Actions (1) Install the pilot assist handle SK208–146–2 subkit (part number (P/N) SK208–146–2( (or FAAapproved equivalent part number if the airplane will be operated in the ground icing conditions defined under ‘Visual/Tactile Check’in the LIMITATIONS section of the AFM after the compliance time). (2) 14 CFR 21.303 allows for replacement parts through parts manufacturer approval (PMA). The phrase ‘‘or FAA-approved equivalent part number’’in this AD is intended to signify those parts that are PMA parts approved through identicality to the design of the part under the type certificate and parts to correct the unsafe condition under PMA (other than identicality). Equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD. (3) Insert the text in Appendix 1 of this AD after the ‘‘OTHER LIMITATIONS’’in the LIMITATIONS section of the Cessna Models 208 or 208B Pilot’s Operating Handbook (POH) and FAA-approved Airplane Flight Manual (AFM).

Compliance Within the next 125 days after February 22, 2006 (the effective date of this AD), unless already done.

Procedures Install the pilot assist handle SK208–146–2 subkit (part number (P/N) SK208–146–2 (or FAA-approved equivalent part number) following step 4 of the Accomplishment Instructions of Cessna Caravan Service Kit No. SK208–146, dated October 4, 2004.

Not Applicable

Not Applicable.

Before further flight after compliance to paragraph (e)(1) of this AD.

The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may insert the information into the POH as specified in paragraph (e)(3) of this AD. You may insert a copy of this AD into the appropriate sections of the POH to comply with this action. Make an entry into the aircraft records showing compliance with portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

17

2006-01-11 3

Actions (4) For Cessna Model 208B with Pratt & Whitney of Canada Ltd., PT6A–114 Turbo Prop engine installed (600 SHP) or equivalent, and equipped with pneumatic deicing boots, do one of the following:. (i) Install Cessna Accessory Kit AK208–6C per Cessna Service Bulletin CAB95–19; or. (ii) Install a placard in view of the pilot which states ‘‘This airplane is prohibited from flight in known or forecast icing’’.

(5) For all Cessna Model 208 and 208B airplanes equipped with pneumatic deicing boots and not included in paragraph (e)(4) of this AD, do one of the following:. (i) Install Cessna Accessory Kit AK208–6C per Cessna Service Bulletin CAB93–20 Revision 1; or. (ii) Install a placard in view of the pilot with the following words: ‘‘This airplane is prohibited from flight in known or forecast icing’’.

(6) Insert the text in Appendix 2 of this AD in the ‘‘KINDS OF OPERATION LIMITS’’in the LIMITATIONS section of the Cessna Models 208 or 208B Pilot’s Operating Handbook (POH) and FAA-approved Airplane Flight Manual (AFM).

Compliance Within the next 125 days after February 22, 2006 (the effective date of this AD), unless already done.

Procedures Install the cargo pod and landing gear fairing deice kit (part number (P/N) AK208–6C2) (or FAA-approved equivalent part number) following the Installation Instructions of Cessna Caravan Service Bulletin No. CAB95–19, dated October 13, 1995, and Cessna Caravan Accessory Kit No. AK208–6C, Revision C, dated August 27, 1993. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may install the placard as specified in paragraph (e)(4) of this AD. You may insert a copy of this AD into the appropriate sections of the POH to comply with this action. Make an entry into the aircraft records showing compliance with portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Within the Do the installation following the next 125 days Installation Instructions of Cessna Caravan after February Service Bulletin No. CAB93–20, Revision 22, 2006 (the 1, dated October 13, 1995, and Cessna effective date Caravan Accessory Kit No. AK208–6C, of this AD), Revision C, issued August 27, 1993. The unless already owner/operator holding at least a private done. pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may install the placard as specified in paragraph (e)(5)(ii) of this AD. Make an entry into the aircraft records showing compliance with portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Before further The owner/operator holding at least a flight after private pilot certificate as authorized by compliance to section 43.7 of the Federal Aviation paragraph Regulations (14 CFR 43.7) may insert the (e)(4)(i) or information into the POH as specified in (e)(5)(i) of this paragraph (e)(3) of this AD. You may AD. insert a copy of this AD into the appropriate sections of the POH to comply with this action. Make an entry into the aircraft records showing compliance with portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). 18

2006-01-11 4

Actions (7) Delete the text in Appendix 3 of this AD from the ‘‘REQUIRED EQUIPMENT’’in the LIMITATIONS section of the Cessna Models 208 or 208B Pilot’s Operating Handbook (POH) and FAA-approved Airplane Flight Manual (AFM) Supplement S1 ‘‘Known Icing Equipment’’.

Compliance Before further flight after compliance to paragraph (e)(4)(i) or (e)(5)(i) of this AD.

Procedures The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may insert the information into the POH as specified in paragraph (e)(3) of this AD. You may insert a copy of this AD into the appropriate sections of the POH to comply with this action. Make an entry into the aircraft records showing compliance with portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

Note: Cessna Caravan Service Bulletin No. CAB04-9, dated October 4, 2004, also addresses the installation of the pilot assist handle. May I Request an Alternative Method of Compliance? (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 39.19. For information on any already approved alternative methods of compliance, contact Paul Pellicano, Aerospace Engineer (Icing), FAA, Small Airplane Directorate, c/o Atlanta ACO, One Crown Center, 1985 Phoenix Boulevard, Suite 450, Atlanta, GA 30349; telephone: (770) 703-6064; facsimile: (770) 703-6097; or Robert P. Busto, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4157; facsimile: (316) 946-4107. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Cessna Caravan Service Kit No. SK208-146, dated October 4, 2004 and Cessna Caravan Accessory Kit No. AK2086C, Revision C, dated August 27, 1993. 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. To get a copy of this service information, contact The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277-7706; telephone: (316) 517-5800; facsimile: (316) 942-9006. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-21275; Directorate Identifier 2005-CE-28-AD. Appendix 1 to AD 2006-01-11 Changes to the Cessna Models 208 or 208B Pilot's Operating Handbook (POH) and FAA-Approved Airplane Flight Manual

19

2006-01-11 5

Affected Cessna Models 208 or 208B Pilot's Operating Handbook (POH) and FAA-Approved Airplane Flight Manual (AFM) Insert the following text after the ''OTHER LIMITATIONS'' in the LIMITATIONS section of the Cessna Models 208 or 208B Pilot's Operating Handbook (POH) and FAA-approved Airplane Flight Manual (AFM): COLD WEATHER OPERATIONS The airplane must be equipped with the following equipment when operating at an airport in the ground icing conditions defined under `Visual/Tactile Check' in the LIMITATIONS section: 1. Pilot assist handle, Cessna P/N SK208-146-2 (or FAA-approved equivalent part number) Appendix 2 to AD 2006-01-11 Changes to the Cessna Models 208 or 208B Pilot's Operating Handbook (POH) and FAA-Approved Airplane Flight Manual Affected Cessna Models 208 or 208B Pilot's Operating Handbook (POH) and FAA-Approved Airplane Flight Manual (AFM) Add the following to the equipment listed under ''FLIGHT INTO KNOWN ICING'' in the ''KINDS OF OPERATION LIMITS'' in the LIMITATIONS section of the FAA approved Airplane Flight Manual: Lower main landing gear leading edge deice boots Cargo pod nosecap deice boot Appendix 3 to AD 2006-01-11 Changes to the Cessna Models 208 or 208B Pilot's Operating Handbook (POH) and FAA-Approved Airplane Flight Manual Supplement S1 Affected Cessna Models 208 or 208B Pilot's Operating Handbook (POH) and FAA-Approved Airplane Flight Manual (AFM) Supplement S1 Remove the paragraph under ''REQUIRED EQUIPMENT'' in the Limitations section of the FAA Approved Flight Manual Supplement S1 ''Known Icing Equipment'', that currently reads as follows: The following additional equipment is not required for flight into icing conditions as defined by FAR 25, but may be installed on early serial airplanes by using optional accessory Kit AK208-6. On later serial airplanes, this equipment may be included with the flight into known icing package. If installed, this equipment must be fully operational: Issued in Kansas City, Missouri, on January 5, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-225 Filed 1-11-06; 8:45 am]

20

BW 2006-02 RAYTHEON AIRWORTHINESS DIRECTIVE EMERGENCY SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2006-02-51 RAYTHEON AIRCRAFT COMPANY: Directorate ID 2005-CE-51-AD. When Does This AD Become Effective? (a) This emergency AD becomes effective upon receipt. Are Any Other ADs Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following Model 390 airplanes that are certificated in any category: (1) serial numbers RB-1 through RB-49 that are equipped with Kit 390-9100 that incorporates part number (P/N) 390-580035-0001 (or FAA-approved equivalent part number); (2) serial numbers RB-50 through RB-141; and (3) serial numbers RB-143 through RB-148

21

2006-02-51 2

What is the Unsafe Condition Presented in This AD? (d) This AD is the result of failure of the hydraulic tube assembly, which caused in-flight loss of hydraulic fluid. We are issuing this AD to prevent failure of the hydraulic tube assembly and the clamp and consequent leaking of hydraulic fluid. This failure could result in loss of hydraulic system functions and risk of fire because of flammable fluid leakage in the engine nacelle and lead to loss of control of the airplane. What Must I do to Address This Problem? (e) To address this problem, you must do the following: Actions

Compliance

Procedures

(1) Perform a one-time visual inspection of the hydraulic tube assembly and clamp using Raytheon Safety Communique No. 267, dated January 2006. Perform repetitive detailed inspections thereafter per Raytheon Mandatory Service Bulletin No. SB 29-3771, dated January, 2006. (i) The tube assembly part number is P/N 390-5800350001 or P/N 390-5800350005). (ii) The clamp part number is P/N MS21919WCJ6 or P/N MS21919WCJ7.

Visually inspect before further flight after receipt of this emergency AD. Perform the detailed inspection within 10 hours time-in-service (TIS) after receipt of this emergency AD, and thereafter at intervals not to exceed 50 hours TIS. You may perform the detailed inspection before further flight instead of the visual inspection.

For the visual inspection, use Raytheon Safety Communique No. 267, dated January 2006. For the detailed inspections, use the procedures in Raytheon Mandatory Service Bulletin No. SB 293771, dated January, 2006.

(2) Replace the hydraulic tube assembly (P/N 390580035-0001 or P/N 390580035-0005) and the clamp (P/N MS21919WCJ6 or P/N MS21919WCJ7) (or FAAapproved equivalent part numbers) with new P/N 390580035-0001 or P/N 390580035-0005 and P/N MS21919WCJ7 (or FAAapproved equivalent part numbers) or used parts.

Replace the clamp at each inspection. Replace the tube assembly prior to further flight after any inspection where evidence of chafing, excessive vibration, wear, deterioration, or hydraulic fluid leakage is found. Refer to SB 29-3771, dated January, 2006 for acceptance / rejection information for the tube assembly.

Follow the procedures in Raytheon Mandatory Service Bulletin No. SB 29-3771, dated January, 2006.

22

2006-02-51 3

(3) Report the results to FAA of each inspection or replacement required in paragraphs (e)(1) and (e)(2) of this AD. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 and those following sections) and assigned OMB Control Number 2120-0056.

Within 10 days after the inspection or replacement or within 10 days after receipt of this AD, whichever occurs later.

Include in your report the airplane serial number, the TIS of the airplane, and the TIS of the hydraulic tube assembly (P/N 390580035-0001 or P/N 390-580035-0005) (or FAA-approved equivalent part number). Email/send your report to James P. Galstad, Propulsion Aerospace Engineer, ACE 116W, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; email: [email protected]; telephone: 316-9464135; facsimile: 316946-4107.

(4) Repositioning and Special Flight Permits: You may operate the airplane to return/position the airplane to a home base, hangar, maintenance facility, etc., for the purpose of doing only the visual inspection required by this AD. (i) Operation of up to 10 hours time-in-service (TIS) is allowed for visual inspection repositioning flight(s) provided the flight(s) occur(s) no later than 30 days after January 19, 2006. This is a one-time provision. (ii) Special flight permits are also allowed for the visual inspection required for this AD. Use the procedures in 14 CFR part 39. (iii) Special flight permits are prohibited for the detailed inspections and possible replacements required by this AD. (iv) For any repositioning flight or special flight permit for the visual inspection, you must operate with only the PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE OPERATION. (5) Disposal of Parts: Return replaced hydraulic tube assembly (P/N 390-580035-0001 or P/N 390-580035-0005) to Raytheon Aircraft Company per SB 29-3771 and dispose of the P/N MS21919WCJ6 or P/N MS21919WCJ6 clamp (or FAA-approved equivalent part numbers) following 14 CFR 43.10. Ship any replaced hydraulic tube and dispose of the clamp prior to returning the aircraft to service.

23

2006-02-51 4

(6) Parts Manufacturer Approval (PMA): 14 CFR 21.303 allows for replacement parts through PMA. The phrase "or FAA-approved equivalent part number(s)" in this AD is intended to signify those parts that are PMA approved through identicality to the design of the part under the type certificate and replacement parts to correct the unsafe condition under PMA (other than identicality). If parts are installed that are identical to the unsafe parts, then the corrective actions of the AD affect these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD. 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, Wichita Aircraft Certification Office, FAA. For information on any already approved alternative methods of compliance, contact James P. Galstad, Propulsion Aerospace Engineer, ACE 116W, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: 316-946-4135; facsimile: 316-946-4107. Issued in Kansas City, Missouri, on January 19, 2006.

John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

24