FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY

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1 FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 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 Oklahoma City, OK FAX

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3 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 Alpha Aviation Design Limited R Turbomeca Engine: Arrius 2B1, 2B1A, and 2B2 turboshaft Raytheon Aircraft Company 390 Biweekly Stemme GMBH & Co. KG Gliders: S10-VT Turbomeca Engine: Artouste III B and III B1 turboshaft Sikorsky Aircraft Corporation Rotorcraft: S-61L, N, R, and NM S Bell Helicopter Textron Canada Rotorcraft: 206A, B, L, L-1, L-3, and L-4 Biweekly SOCATA-Groupe Aerospatiale TB 20 and TB EADS SOCATA TBM S EXTRA Flugzeugproduktionsund EA-300, EA-300L, EA-300S, EA-300/200 Vertriebs-GmbH Reims Aviation F DORNIER LUFTFAHRT Turbomeca Engine: Arriel -1A, -1A1, -1A2, -1B, -1B2, -1C, -1C1, -1C2, -1D, -1D, -1D1, -1K1, -1E, -1E2, -1S, and -1S1 series Pilatus Aircraft Limited PC-12 and PC-12/ Pilatus Aircraft Ltd. PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC- 6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H Turbomeca Engine: Arriel 2B1 Biweekly R1 R Short Brothers SC-7 series 2 and SC-7 series COR Raytheon 65, 90, 99, 100, 200, 1900, 70, and R1 R Turbomeca S.A. Engine: Arrius 2F turboshaft EADS Socata TBM EADS Socata TBM Turbomeca S.A Engine: Makila 1A and 1A1 turboshaft Pacific Aerospace 750XL CTRM Aviation Sdn. Eagle 150B EADS TBM Gippsland Aeronautics Pty. GA EADS TBM E General Electric Aircraft Engine: CF34-3A1/-3B/-3B1 Engines E MD Helicopters Inc. MD600N Biweekly Superior Air Parts, Inc. Appliance: Cast cylinder assemblies Alpha Aviation Design R2160 3

4 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 COR Pacific Aerospace Corporation 750XL Ltd Alpha Aviation Design Limited R Mooney Airplane Company, Inc M20M and M20R SOCATA Groupe M.S. 760, M.S. 760 A, and M.S. 760 B AEROSPATIALE REIMS AVIATION S.A F Cessna Aircraft Company 172R, 172S, 182S, 182T, T182T, 206H, T206H S Teledyne Continental Motors Engine: GTSIO-520 series reciprocating EADS SOCATA TBM Glasflugel Sailplane: H 301 Libelle, H 301B Libelle, Standard Libelle, and Standard Libelle-201B Microturbo Appliance: Auxiliary Power Units (APU) Raytheon Aircraft Company Beech 45 (YT-34), A45 (T34A, B-45), D45 (T-34B) EADS SOCATA TBM B-N Group Ltd BN-2, BN-2A, BN-2B, BN-2T, and BN-2T-4R Series Raytheon Aircraft Company 58 and G PZL-Bielsko Glider: SZD-50-3 ''Puchacz'' EADS SOCATA TBM EADS SOCATA TBM 700 Biweekly FR Eurocopter Deutschland GmbH Rotorcraft: MBB-BK 117 C COR Raytheon Beech 45 (YT-34), A45 (T34A, B-45), D45 (T-34B Eurocopter France Rotorcraft: AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, and AS350D Alpha Aviation Design Limited R2160 Biweekly R1 R Superior Air Parts, Inc Appliance: Cylinder assemblies R1 R Raytheon Beech 45 (YT-34), A45 (T34A, B-45), D45 (T-34B Columbia Aircraft LC40-550FG, LC41-550FG, LC42-550FG Manufacturing Hartzell Propeller Inc. Propeller: HC-E4A-3( )/E10950( ) Cessna 172R, 172S, 182T, T182T, 206H, T206H McCauley Propeller Propeller: 3A32C406/82NDB-X and D3A32C409/82NDB-X British Aerospace Regional HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series Aircraft LATINOAMERICANA DE AVIACIÓN 3101, and Jetstream Model 3201 PA-25, PA , and PA , Biweekly R1 R Turbomeca S.A Engine: Arriel 2B turboshaft MD Helicopters Inc. (MDHI) Rotorcraft: MD600N S Raytheon Aircraft Company See AD Cessna Aircraft Company 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, and 182R REIMS AVIATION S.A F E MD Helicopters Rotorcraft: 369 (Army YOH-6A), 369A (Army OH-6A), 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF 4

5 FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE R1 Turbomeca S.A.: Amendment Docket No. FAA ; Directorate Identifier 2005-NE-17-AD. Effective Date Affected ADs Applicability (a) This airworthiness directive (AD) becomes effective May 22, (b) This AD revises AD , Amendment (c) This AD applies to Turbomeca S.A. Arriel 2B turboshaft engines with Modification TU62A incorporated, but do not have Modification TU132. These engines are installed on, but not limited to, Eurocopter AS350B3 helicopters. Unsafe Condition (d) This AD results from the engine manufacturer releasing a service bulletin to introduce modification TU132. We are issuing this AD to prevent loss of control of engine fuel flow in manual control mode or mixed control mode, which can lead to engine overspeed, and in-flight engine shutdown resulting in a forced autorotation landing or accident. 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. Hydromechanical Units (HMUs) Without Modification TU132 (f) Within 20 operating hours after July 11, 2005, the AD's original effective date, inspect, clean, lubricate, and check for proper operation of the HMU acceleration controller axle. Use paragraph 2 of Instructions to be Incorporated of Turbomeca Alert Mandatory Service Bulletin No. A , Update No. 1, dated January 11, 2005, or Update No. 2, dated December 15, 2006, to do these actions. (g) Thereafter, repeat the actions specified in paragraph (f) of this AD within every 210 operating hours. 5

6 R1 2 Optional Terminating Action (h) Modifying the HMU to Modification TU132, terminates the repetitive inspection requirements specified in paragraph (g) of this AD. Turbomeca Service Bulletin No , dated May 31, 2006, contains information on modifying the HMU to Modification TU132. Alternative Methods of Compliance (i) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR Related Information (j) The EASA airworthiness directive , dated February 1, 2007, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Turbomeca Alert Mandatory Service Bulletin (ASB) No. A , Update No. 1, dated January 11, 2005; or ASB No. A , Update No. 2, dated December 15, 2006, to perform the actions required by this AD. The Director of the Federal Register previously approved the incorporation by reference of ASB No. A , Update No. 1, dated January 11, 2005, on July 11, 2005 (70 FR 36480; June 24, 2005). The Director of the Federal Register approved the incorporation by reference of ASB No. A , Update No. 2, dated December 15, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Turbomeca S.A., Tarnos, France; telephone , fax , for a copy of this service information. 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 , or go to: Issued in Burlington, Massachusetts, on April 9, Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E Filed ; 8:45 am] 6

7 FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE MD Helicopters Inc. (MDHI): Amendment Docket No. FAA ; Directorate Identifier 2007-SW-05-AD. Applicability: Model MD600N helicopters, with a lateral mixer output link assembly (mixer link), part number (P/N) 600N7636-1, -3, -9, or -11 installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect a crack in the mixer link, which could result in failure of the mixer link and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight: (1) Remove each mixer link and visually inspect, with a bright light and a 10x or higher magnifying glass, the shaded areas around the bearing bore for any crack as depicted in the following Figure 1: (2) Perform an eddy current inspection of each mixer link in the bearing end areas. (3) Replace any cracked mixer link with an airworthy mixer link on which an eddy current inspection has been performed. Note: MDHI Service Bulletin No. SB600N-044, dated February 16, 2007, pertains to the subject of this AD. 7

8 (b) Perform an eddy current inspection on each mixer link before installing it on any helicopter. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR Contact the Manager, Los Angeles Aircraft Certification Office, FAA, ATTN: Jon Mowery, Aviation Safety Engineer, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) , fax (562) , for information about previously approved alternative methods of compliance. (d) A one-time special flight permit may be issued in accordance with 14 CFR and to operate the helicopter to a location where the eddy current inspection requirements of this AD can be accomplished provided that no crack is found during the visual inspection required in paragraph (a) of this AD and that the helicopter's airspeed does not exceed 100 knots. (e) This amendment becomes effective on May 7, 2007, to all persons except those persons to whom it was made immediately effective by Emergency AD , issued February 17, 2007, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on April 5, Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E Filed ; 8:45 am] 8

9 FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE Raytheon Aircraft Company (The Beech Aircraft Company and BEECH previously held Type Certificate Nos. 3A15, 3A16, 5A3, and A-777): Amendment ; Docket No. FAA ; Directorate Identifier 2006-CE-55-AD. Effective Date Affected ADs Applicability (a) This AD becomes effective on May 25, (b) This AD supersedes AD , Amendment (c) This AD applies to the following airplane models and serial numbers (SNs) that are certificated in any category: (1) Group 1 (maintains the actions from AD ): Model (i) 35-33, 35-A33, 35-B33, 35-C33, E33, F33, and G33 (ii) 35-C33A, E33A, and F33A (iii) E33C and F33C (iv) 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, and V35B SNs CD-1 through CD-1256 CE-1 through CE-349 CJ-1 through CJ-30 D-1 through D-9287 (v) 36 and A36 E1 through E-283 (vi) A45 (T-34A, B45) and D45 (T-34B) (vii) 95-55, 95-A55, 95-B55, and 95-B55A (viii) 95-C55, 95-C55A, D55, D55A, E55, and E55A (ix) 56TC and A56TC (x) 58 (xi) 95, B95, B95A, D95A, and E95 All TC-1 through TC-1402 TE-1 through TE-846 TG-1 through TG-94 TH-1 through TH-174 TD-2 through TD-721 (2) Group 2: Model 95-B55B (T-42A) airplanes, SNs TF-1 through TF-70. 9

10 Unsafe Condition (d) This AD results from a recent incident involving a Raytheon Aircraft Company (RAC) Model 95-B55B (T-42A) airplane where a seizure of the uplock rollers occurred. We are issuing this AD to decrease the possibility of gear-up landings caused by seizure of the uplock rollers. Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Determine if each uplock roller is of the greasible type (one having a drilled and grooved inner race). (2) Replace any nongreasible uplock roller (one having a solid inner race) with the greasible type. (3) Install hollow zerk-ended mounting bolts on the uplock rollers. (i) For Group 1 airplanes: Within 300 hours time-in-service (TIS) after October 25, 1972 (the effective date of AD ). (ii) For Group 2 airplanes: Within 300 hours TIS after May 25, 2007 (the effective date of this AD). (i) For Group 1 airplanes: Before further flight after the determination required by paragraph (e)(1)(i) of this AD. (ii) For Group 2 airplanes: Before further flight after the determination required by paragraph (e)(1)(ii) of this AD. (i) For Group 1 airplanes: Within 300 hours TIS after October 25, 1972 (the effective date of AD ). (ii) For Group 2 airplanes: Within 300 hours TIS after May 25, 2007 (the effective date of this AD). Follow Beechcraft Service Instructions No , Rev. I, or Beechcraft Service Instructions No Follow Beechcraft Service Instructions No , Rev. I, or Beechcraft Service Instructions No Follow Beechcraft Service Instructions No , Rev. I, or Beechcraft Service Instructions No

11 Actions Compliance Procedures (4) Lubricate the uplock mechanism. (i) For Group 1 airplanes: Initially within 300 hours TIS after October 25, 1972 (the effective date of AD ). Repetitively lubricate thereafter at intervals not to exceed 100 hours TIS. (ii) For Group 2 airplanes: Initially within 300 hours TIS after May 25, 2007 the effective date of this AD. Repetitively lubricate thereafter at intervals not to exceed 100 hours TIS. Alternative Methods of Compliance (AMOCs) Follow Beechcraft Service Instructions No , Rev. I, or Beechcraft Service Instructions No (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Anthony Flores, Aerospace Engineer, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) ; facsimile: (316) , has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR (g) AMOCs approved for AD are approved for this AD. Material Incorporated by Reference (h) You must use Beechcraft Service Instructions No , Rev. I (undated), or Beechcraft Service Instructions No (undated), to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Beechcraft Service Instructions No (undated), and Beechcraft Service Instructions No , Rev. I (undated), under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas ; telephone: (800) or (316) (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call , or go to: Issued in Kansas City, Missouri, on April 6, Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E Filed ; 8:45 am] 11

12 FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE The Government Printing Office (GPO) has made a typo in the table of this AD on page of Federal Register (FR), dated April 20, GPO will issue and print a correction to this AD in the FR. We have corrected this copy and notated it with revision marks Cessna Aircraft Company: Amendment ; Docket No. FAA ; Directorate Identifier 2007-CE-031-AD. Effective Date Affected ADs (a) This AD becomes effective on April 25, (b) None. Applicability (c) This AD applies to Models 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, and 182R airplanes, all serial numbers, that: (i) Have Air Plains Services Corporation Supplemental Type Certificate (STC) SA00152WI installed; (ii) Have a ground power receptacle mounted on the firewall (forward ground power receptacle); and (iii) Are certificated in any category. Unsafe Condition (d) This AD results from a report of an in-flight and post-landing engine compartment fire. We are issuing this AD to detect and correct interference between the ground power electrical cable, the fuel strainer cable, and the fuel line between the auxiliary electric fuel pump and the enginedriven fuel pump. This condition could lead to a fire in the engine compartment. 12

13 Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Remove power to the ground power electrical cable by: (i) Disconnecting the electrical cable at the forward ground power relay and the starter relay, or (ii) Removing the electrical cable between the forward ground power relay and the starter relay. Within 15 days after April 25, 2007 (the effective date of this AD). Follow Air Plains Services Corporation Mandatory Service Bulletin APS , dated March 5, (2) Fabricate and install a placard as close as possible to the forward ground power receptacle that incorporates the following words (using at least 1/8-inch red letters on a white background and a red border): GROUND POWER RECEPTACLE IS INOPERATIVE. (3) Reposition the fuel strainer cable. (4) Visually inspect the fuel line from the auxiliary electric fuel pump to the engine-driven fuel pump for chafing. Before further flight after power to the ground power cable is removed per paragraph (e)(1) of this AD. Within 15 days after April 25, 2007 (the effective date of this AD). Within 15 days after April 25, 2007 (the effective date 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 fabricate and install the placard. 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). Follow Air Plains Services Corporation Mandatory Service Bulletin APS , dated March 5, Follow Air Plains Services Corporation Mandatory Service Bulletin APS , dated March 5,

14 Actions Compliance Procedures (5) If chafing at or beyond the limits defined in the Air Plains Services Corporation Mandatory Service Bulletin APS , dated March 5, 2007, is found in the inspection required by paragraph (e)(4) of this AD, replace the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump with a new hose part number AE G0190 (or FAA-approved equivalent) and remove the ground power electrical cable per (e)(1)(ii) of this AD. (6) Adjust the position of the fuel line fitting at the engine-driven fuel pump. Before further flight after any inspection where evidence of chafing is found. Within 15 days after April 25, 2007 (the effective date of this AD). Alternative Methods of Compliance (AMOCs) Follow Air Plains Services Corporation Mandatory Service Bulletin APS , dated March 5, Follow Air Plains Services Corporation Mandatory Service Bulletin APS , dated March 5, (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Trenton Shepherd, Aerospace Engineer, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) ; fax: (316) , has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (g) You must use Air Plains Services Corporation Mandatory Service Bulletin APS , dated March 5, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Air Plains Services Corporation, P.O. Box 541, Wellington, KS 67152; phone: ; Internet: (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call , or go to: Issued in Kansas City, Missouri, on April 13, Charles L. Smalley,Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E Filed ; 8:45 am] 14

15 FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE REIMS AVIATION S.A.: Amendment ; Docket No. FAA ; Directorate Identifier 2006-CE-088-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective May 31, (b) None. Applicability (c) This AD applies to REIMS AVIATION S.A. Model F406 airplanes, serial numbers F through F and serial number F , certificated in any category. Subject Reason (d) Air Transport Association of America (ATA) Code 57: Wings. (e) The mandatory continuing airworthiness information (MCAI) states: During maintenance, cracks have been discovered about the left and right rib at the connection of the center wing and the fuselage localized at the fuselage station FS Cracks spread in the rib could result in structural failure. Actions and Compliance (f) Unless already done, do the following actions: (1) Within the next 600 hours time-in-service or the next 12 months after the effective date of this AD, whichever occurs first, and thereafter repetitively during a period not to exceed 12 months, inspect the ribs in accordance with REIMS AVIATION INDUSTRIES Service Bulletin No. F REV 1, dated November 9, (2) If cracks are found during any inspection required by this AD, before further flight, do the actions prescribed in chapters 1D and 2E of the REIMS AVIATION INDUSTRIES Service Bulletin No. F REV 1, dated November 9, Note 1: We have established the repetitive inspection times of this AD so that they may coincide with annual inspections. 15

16 FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, ATTN: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) ; fax: (816) , has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number Related Information (h) Refer to MCAI Direction générale de l'aviation civile (DGAC), which is the aviation authority for France, AD No. F R1, dated January 5, 2005; and REIMS AVIATION INDUSTRIES Service Bulletin No. F REV 1, dated November 9, 2004, for related information. Material Incorporated by Reference You must use REIMS AVIATION INDUSTRIES Service Bulletin No. F REV 1, dated November 9, 2004, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact REIMS AVIATION INDUSTRIES, PRUNAY-FRANCE. (3) You may review copies at the 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 , or go to: Issued in Kansas City, Missouri, on April 13, Charles L. Smalley, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E Filed ; 8:45 am] 16

17 DATE: April 27, 2007 AD #: FAA Aircraft Certification Service EMERGENCY AIRWORTHINESS DIRECTIVE This Emergency Airworthiness Directive (AD) is prompted by a report of an accident after the loss of a tail rotor blade. This condition, if not corrected, could result in the failure of a tail rotor blade and subsequent loss of control of the helicopter. The FAA has reviewed MD Helicopters Service Bulletin No. SB369H-247, SB369D-204, SB369E-099, and SB369F-084, dated April 26, 2007 (SB), which describes procedures for inspecting the tail rotor blade assembly. The SB states that reports from the field have shown that there are tail rotor blades in operation with a machining defect. The SB further states that these blades have a sharp transition in the tapered end of the root fitting bore that can cause the tail rotor blade root fitting to fail. This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, this AD requires the following, before further flight: Remove each affected tail rotor blade. Using a bright light, inspect the bore of the tail rotor blade root fitting. Replace each blade assembly that does not have a smooth radius. Identify the airworthy tail rotor blade assembly with the applicable SB No. The actions must be done by following specified portions of the SB described previously. This rule is issued under 49 U.S.C. Section pursuant to the authority delegated to me by the Administrator, and is effective immediately upon receipt of this emergency AD MD HELICOPTERS, INC.: Directorate Identifier 2007-SW-18-AD. Applicability: Model 369 (Army YOH-6A), 369A (Army OH-6A), 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF helicopters, with a tail rotor blade, part number (P/N) 369A1613, 369D21606, 369D21613, 369D21615, or , all dash numbers, installed, certificated in any category. Compliance: Before further flight, unless accomplished previously. To prevent the loss of a tail rotor blade and subsequent loss of control of the helicopter, do the following: (a) Inspect each affected tail rotor blade for a smooth radius as follows: (1) Remove the tail rotor blade assembly by following the Accomplishment Instructions, paragraphs 2.B.(1) through 2.B.(3), Part 2., of MD Helicopters, Inc., Service Bulletin SB369H-247, SB369D-204, SB369E-099, and SB369F-084 dated April 26, 2007 (SB). 17

18 (2) Using a bright light, inspect the bore of the tail rotor blade root fitting by following the Accomplishment Instructions, paragraphs 2.B.(4) and 2.B.(5), Part 2, and Figures 1 and 2 of the SB. (b) Replace each blade assembly that does not have a smooth radius by following the Accomplishment Instructions, paragraphs 2.B.(6) and (7), Part 2, and Figure 2 of the SB. (c) Identify the airworthy tail rotor blade assembly with the applicable model of helicopter by following the Identification, paragraphs 3(1) through 3(4) of the SB. (d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR Contact the Manager, Los Angeles Aircraft Certification Office, FAA; Attn: John Cecil, Aviation Safety Engineer, Airframe Branch, 3960 Paramount Blvd., Lakewood, California , telephone (562) , fax (562) , for information about previously approved alternative methods of compliance. (e) Special flight permits will not be issued. (f) Copies of the applicable service information may be obtained from MD Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona , telephone , fax , or on the web at (g) Emergency AD , issued April 27, 2007, becomes effective upon receipt. FOR FURTHER INFORMATION CONTACT: John Cecil, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California , telephone (562) , fax (562) Issued in Fort Worth, Texas, on April 27, David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. 18

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