FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2007-09 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 2007-01 2006-26-03 2006-26-07 2006-26-08
Alpha Aviation Design Limited Turbomeca Raytheon Aircraft Company
R2160 Engine: Arrius 2B1, 2B1A, and 2B2 turboshaft 390
Stemme GMBH & Co. KG Turbomeca Sikorsky Aircraft Corporation Bell Helicopter Textron Canada
Gliders: S10-VT Engine: Artouste III B and III B1 turboshaft Rotorcraft: S-61L, N, R, and NM Rotorcraft: 206A, B, L, L-1, L-3, and L-4
TB 20 and TB 21 TBM 700 EA-300, EA-300L, EA-300S, EA-300/200
2007-02-12 2007-02-13 2007-02-17
SOCATA-Groupe Aerospatiale EADS SOCATA EXTRA Flugzeugproduktionsund Vertriebs-GmbH Reims Aviation DORNIER LUFTFAHRT Turbomeca
2007-03-06 2007-03-08
Pilatus Aircraft Limited Pilatus Aircraft Ltd.
2007-03-14
Turbomeca
Biweekly 2007-02 2007-01-03 2007-01-04 2007-01-05 2007-01-06
S 2004-24-08
Biweekly 2007-03 2007-02-04 2007-02-08 2007-02-11
S 2002-21-11
F406 228-212 Engine: Arriel -1A, -1A1, -1A2, -1B, -1B2, -1C, -1C1, -1C2, -1D, -1D, -1D1, -1K1, -1E, -1E2, -1S, and -1S1 series PC-12 and PC-12/45 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, PC6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Engine: Arriel 2B1
Biweekly 2007-04 2003-17-05R1 2004-23-02 2005-17-17 R1 2007-03-16 2007-03-17 2007-03-20 2007-04-01 2007-04-02 2007-04-08 2007-04-12 2007-04-13 2007-04-51
R 2003-17-05 COR R 2005-17-17
E
2007-05-51
E
Short Brothers Raytheon Turbomeca S.A. EADS Socata EADS Socata Turbomeca S.A Pacific Aerospace CTRM Aviation Sdn. EADS Gippsland Aeronautics Pty. EADS General Electric Aircraft Engines MD Helicopters Inc.
SC-7 series 2 and SC-7 series 3 65, 90, 99, 100, 200, 1900, 70, and 300 Engine: Arrius 2F turboshaft TBM 700 TBM 700 Engine: Makila 1A and 1A1 turboshaft 750XL Eagle 150B TBM 700 GA8 TBM 700 Engine: CF34-3A1/-3B/-3B1 MD600N
Superior Air Parts, Inc. Alpha Aviation Design
Appliance: Cast cylinder assemblies R2160
Biweekly 2007-05 2007-04-19 2007-04-25
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 2007-06 2007-04-01
COR
2007-05-03 2007-05-04 2007-05-05 2007-05-09 2007-05-10 2007-05-15 2007-05-18 2007-05-19
S 2005-20-04
2007-05-20 2007-06-01 2007-06-04 2007-06-06 2007-06-07 2007-06-08 2007-06-11 2007-06-14
Pacific Aerospace Corporation Ltd Alpha Aviation Design Limited Mooney Airplane Company, Inc SOCATA–Groupe AEROSPATIALE REIMS AVIATION S.A Cessna Aircraft Company Teledyne Continental Motors EADS SOCATA Glasflugel Microturbo Raytheon Aircraft Company EADS SOCATA B-N Group Ltd Raytheon Aircraft Company PZL-Bielsko EADS SOCATA EADS SOCATA
750XL R2160 M20M and M20R M.S. 760, M.S. 760 A, and M.S. 760 B F406 172R, 172S, 182S, 182T, T182T, 206H, T206H Engine: GTSIO-520 series reciprocating TBM 700 Sailplane: H 301 “Libelle,” H 301B “Libelle,” Standard “Libelle,” and Standard Libelle-201B Appliance: Auxiliary Power Units (APU) Beech 45 (YT-34), A45 (T34A, B-45), D45 (T-34B) TBM 700 BN-2, BN-2A, BN-2B, BN-2T, and BN-2T-4R Series 58 and G58 Glider: SZD-50-3 ''Puchacz'' TBM 700 TBM 700
Biweekly 2007-07 2006-26-51 2007-06-01 2007-06-15
FR COR
2007-06-16
Eurocopter Deutschland GmbH Raytheon Eurocopter France Alpha Aviation Design Limited
Rotorcraft: MBB-BK 117 C-2 Beech 45 (YT-34), A45 (T34A, B-45), D45 (T-34B Rotorcraft: AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, and AS350D1 R2160
Biweekly 2007-08 2007-04-19 R1 2007-06-01 R1 2007-07-06
R 2007-04-19 R 2007-06-01
2007-08-02 2007-08-03 2007-08-04 2007-08-06 2007-08-07
Superior Air Parts, Inc Raytheon Columbia Aircraft Manufacturing Hartzell Propeller Inc. Cessna McCauley Propeller British Aerospace Regional Aircraft LATINOAMERICANA DE AVIACIÓN
Appliance: Cylinder assemblies Beech 45 (YT-34), A45 (T34A, B-45), D45 (T-34B LC40-550FG, LC41-550FG, LC42-550FG
Turbomeca S.A MD Helicopters Inc. (MDHI) Raytheon Aircraft Company Cessna Aircraft Company REIMS AVIATION S.A MD Helicopters
Engine: Arriel 2B turboshaft Rotorcraft: MD600N See AD 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, and 182R F406 Rotorcraft: 369 (Army YOH-6A), 369A (Army OH-6A), 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF
Propeller: HC-E4A-3( )/E10950( ) 172R, 172S, 182T, T182T, 206H, T206H Propeller: 3A32C406/82NDB-X and D3A32C409/82NDB-X HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 PA-25, PA-25-235, and PA-25-260,
Biweekly 2007-09 2005-13-25R1 2007-05-51 2007-08-08 2007-09-01 2007-09-02 2007-09-51
R 2005-13-25 S 72-22-01
E
4
AIRWORTHINESS DIRECTIVE
FAA Aircraft Certification Service
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
2005-13-25R1 Turbomeca S.A.: Amendment 39-15028. Docket No. FAA-2005-21624; Directorate Identifier 2005-NE-17-AD. Effective Date (a) This airworthiness directive (AD) becomes effective May 22, 2007. Affected ADs (b) This AD revises AD 2005-13-25, Amendment 39-14162. Applicability (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. A292 73 2814, 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
2005-13-25R1 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. 292 73 2132, 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 39.19. Related Information (j) The EASA airworthiness directive 2007-0026, 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. A292 73 2814, Update No. 1, dated January 11, 2005; or ASB No. A292 73 2814, 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. A292 73 2814, 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. A292 73 2814, 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., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, 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 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Burlington, Massachusetts, on April 9, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7-7115 Filed 4-16-07; 8:45 am]
6
AIRWORTHINESS DIRECTIVE
FAA Aircraft Certification Service
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
2007-05-51 MD Helicopters Inc. (MDHI): Amendment 39-15030. Docket No. FAA-2007-27343; 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
2007-05-51 2
(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 39.19. 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) 627-5322, fax (562) 627-5210, for information about previously approved alternative methods of compliance. (d) A one-time special flight permit may be issued in accordance with 14 CFR 21.197 and 21.199 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 2007-05-51, issued February 17, 2007, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on April 5, 2007. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7-7438 Filed 4-19-07; 8:45 am]
8
AIRWORTHINESS DIRECTIVE
FAA Aircraft Certification Service
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
2007-08-08 Raytheon Aircraft Company (The Beech Aircraft Company and BEECH previously held Type Certificate Nos. 3A15, 3A16, 5A3, and A-777): Amendment 39-15025; Docket No. FAA-2006-26075; Directorate Identifier 2006-CE-55-AD. Effective Date (a) This AD becomes effective on May 25, 2007. Affected ADs (b) This AD supersedes AD 72-22-01, Amendment 39-1544. Applicability (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 72-22-01): Model
SNs
(i) 35-33, 35-A33, 35-B33, 35-C33, E33, F33, and G33
CD-1 through CD-1256
(ii) 35-C33A, E33A, and F33A
CE-1 through CE-349
(iii) E33C and F33C
CJ-1 through CJ-30
(iv) 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, and V35B
D-1 through D-9287
(v) 36 and A36
E1 through E-283
(vi) A45 (T-34A, B45) and D45 (T-34B)
All
(vii) 95-55, 95-A55, 95-B55, and 95-B55A
TC-1 through TC-1402
(viii) 95-C55, 95-C55A, D55, D55A, E55, and E55A
TE-1 through TE-846
(ix) 56TC and A56TC
TG-1 through TG-94
(x) 58
TH-1 through TH-174
(xi) 95, B95, B95A, D95A, and E95
TD-2 through TD-721
(2) Group 2: Model 95-B55B (T-42A) airplanes, SNs TF-1 through TF-70.
9
2007-08-08 2
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).
(i) For Group 1 airplanes: Within 300 hours time-in-service (TIS) after October 25, 1972 (the effective date of AD 72-22-01). (ii) For Group 2 airplanes: Within 300 hours TIS after May 25, 2007 (the effective date of this AD).
Follow Beechcraft Service Instructions No. 0448-211, Rev. I, or Beechcraft Service Instructions No. 0448-211.
(2) Replace any nongreasible uplock roller (one having a solid inner race) with the greasible type.
(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.
Follow Beechcraft Service Instructions No. 0448-211, Rev. I, or Beechcraft Service Instructions No. 0448-211.
(3) Install hollow zerk-ended mounting bolts on the uplock rollers.
(i) For Group 1 airplanes: Within 300 hours TIS after October 25, 1972 (the effective date of AD 72-22-01). (ii) For Group 2 airplanes: Within 300 hours TIS after May 25, 2007 (the effective date of this AD).
Follow Beechcraft Service Instructions No. 0448-211, Rev. I, or Beechcraft Service Instructions No. 0448-211.
10
2007-08-08 3
Actions (4) Lubricate the uplock mechanism.
Compliance
Procedures
(i) For Group 1 airplanes: Initially within 300 hours TIS after October 25, 1972 (the effective date of AD 72-22-01). 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.
Follow Beechcraft Service Instructions No. 0448-211, Rev. I, or Beechcraft Service Instructions No. 0448-211.
Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Anthony Flores, Aerospace Engineer, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4174; facsimile: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 72-22-01 are approved for this AD. Material Incorporated by Reference (h) You must use Beechcraft Service Instructions No. 0448-211, Rev. I (undated), or Beechcraft Service Instructions No. 0448-211 (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. 0448-211 (undated), and Beechcraft Service Instructions No. 0448-211, 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 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. (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 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on April 6, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-7048 Filed 4-19-07; 8:45 am]
11
AIRWORTHINESS DIRECTIVE
FAA Aircraft Certification Service
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
The Government Printing Office (GPO) has made a typo in the table of this AD on page 19792 of Federal Register (FR), dated April 20, 2007. GPO will issue and print a correction to this AD in the FR. We have corrected this copy and notated it with “revision marks”. 2007-09-01 Cessna Aircraft Company: Amendment 39-15031; Docket No. FAA-2007-27786; Directorate Identifier 2007-CE-031-AD. Effective Date (a) This AD becomes effective on April 25, 2007. Affected ADs (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
2007-09-01 2
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-07-01-01, dated March 5, 2007.
(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.”
Before further flight after power to the ground power cable is removed per 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 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).
(3) Reposition the fuel strainer Within 15 days after April cable. 25, 2007 (the effective date of this AD).
Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007.
(4) Visually inspect the fuel line from the auxiliary electric fuel pump to the engine-driven fuel pump for chafing.
Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007.
Within 15 days after April 25, 2007 (the effective date of this AD).
13
2007-09-01 3
Actions
Compliance
Procedures
(5) If chafing at or beyond the limits defined in the Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, 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 AE3663161G0190 (or FAA-approved equivalent) and remove the ground power electrical cable per (e)(1)(ii) of this AD.
Before further flight after any inspection where evidence of chafing is found.
Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007.
(6) Adjust the position of the fuel line fitting at the engine-driven fuel pump.
Within 15 days after April 25, 2007 (the effective date of this AD).
Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007.
Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Trenton Shepherd, Aerospace Engineer, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4143; fax: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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-07-01-01, 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: 620-326-8904; Internet: http://www.airplains.com. (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 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on April 13, 2007. Charles L. Smalley,Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-7519 Filed 4-19-07; 8:45 am] 14
AIRWORTHINESS DIRECTIVE
FAA Aircraft Certification Service
www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html
2007-09-02 REIMS AVIATION S.A.: Amendment 39-15032; Docket No. FAA-2006-26690; Directorate Identifier 2006-CE-088-AD. Effective Date (a) This airworthiness directive (AD) becomes effective May 31, 2007. Affected ADs (b) None. Applicability (c) This AD applies to REIMS AVIATION S.A. Model F406 airplanes, serial numbers F4060001 through F406-0089 and serial number F406-0091, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 57: Wings. Reason (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 FS160.80. 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. F406-54 REV 1, dated November 9, 2004. (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. F406-54 REV 1, dated November 9, 2004. Note 1: We have established the repetitive inspection times of this AD so that they may coincide with annual inspections.
15
2007-09-02 2
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) 329-4144; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (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. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (h) Refer to MCAI Direction générale de l'aviation civile (DGAC), which is the aviation authority for France, AD No. F-2004-114 R1, dated January 5, 2005; and REIMS AVIATION INDUSTRIES Service Bulletin No. F406-54 REV 1, dated November 9, 2004, for related information. Material Incorporated by Reference You must use REIMS AVIATION INDUSTRIES Service Bulletin No. F406-54 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, 51360 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 202-7416030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on April 13, 2007. Charles L. Smalley, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-7641 Filed 4-25-07; 8:45 am]
16
EMERGENCY AIRWORTHINESS DIRECTIVE
FAA Aircraft Certification Service
www.faa.gov/aircraft/safety/alerts/
DATE: April 27, 2007 AD #: 2007-09-51 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 44701 pursuant to the authority delegated to me by the Administrator, and is effective immediately upon receipt of this emergency AD. 2007-09-51 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 421-088, 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
2007-09-51 2
(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 39.19. Contact the Manager, Los Angeles Aircraft Certification Office, FAA; Attn: John Cecil, Aviation Safety Engineer, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-5228, fax (562) 627-5210, 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 852159734, telephone 1-800-388-3378, fax 480-346-6813, or on the web at www.mdhelicopters.com. (g) Emergency AD 2007-09-51, 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 90712-4137, telephone (562) 627-5228, fax (562) 627-5210. Issued in Fort Worth, Texas, on April 27, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service.
18
