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2013-18-05: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters with certain fire extinguishing systems installed. This AD requires modifying the fire extinguishing system injection tubes. This AD is prompted by a report that the injection tubes are deforming due to heat. The actions required by this AD are intended to prevent deformation of the fire extinguishing system injection tubes during a fire, which could result in impaired distribution of the fire extinguishing agent, failure of the fire extinguishing system to contain an engine fire, and subsequent loss of control of the helicopter.
77-17-03: 77-17-03 BELL: Amendment 39-3009. Applies to Model 212 helicopters, S/N 30502 through 30804, 30806 through 30810, 30812, 30814, 30815, 30817, 30818, 30820 through 30825, 30827, 30828, 30829, and to Model 205A-1 helicopters, S/N 30001 through 30247, equipped with tail rotor blades, P/N 212-010-750, certificated in all categories. Compliance required within 25 hours' time in service after the effective date of this AD unless already accomplished and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. To detect possible cracks in each tail rotor blade pitch change horn, P/N 212-010-716-5 and -9, accomplish the following: (a) Remove the bolt and barrel nut of the control rod and clean the external surfaces of the pitch change horns. (b) Inspect the horns for cracks, particularly in the barrel nut and bushing area using a dye penetrant or equivalent inspection method. (c) If a crack is found, replace the affected pitch change horn before further flight in accordance with the Model 212 Overhaul Manual, paragraphs 65-58 and 65-63, or Models 205A/205A-1 Maintenance and Overhaul Instructions, paragraphs 3-41 and 3-43, as appropriate. (d) Install the blade's control rod bolt and barrel nut as specified in the instructions in paragraphs 65-57 Model 212 Maintenance Manual or 3-40 Models 205/205A-1 Maintenance and Overhaul Instructions, as appropriate. (e) After installation of pitch change horns, P/N 212-010-716-11, this AD is no longer applicable. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (g) The manufacturer's instructions identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Textron, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. (Bell Helicopter Textron Service Bulletin Nos. 212-77-7 and 205-77-5 dated March 11, 1977, pertain to this subject.) This amendment becomes effective August 19, 1977.
76-13-06: 76-13-06 DEHAVILLAND: Amendment 39-2654. Applies to DeHavilland Model DHC- 6 series Twin Otter aircraft serial nos. 1 thru 430 incorporating wing tip strobe lighting. Compliance required as indicated: To restore the aircraft lightning strike protection to its original status, as a result of excessive removal of lightning strike protection bonding strap material, during the installation of the wing tip strobe lights, accomplish the following: (a) Within the next 100 hours in service after the effective date of this AD, accomplish the alteration to the aircraft wing tips in accordance with "Accomplishment Instructions" in DeHavilland DHC-6 Service Bulletin No. 6/318, dated January 3, 1975, or later revision, or equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective July 6, 1976.
2013-16-24: We are superseding airworthiness directive (AD) 90-23-14 for certain The Boeing Company Model 747 series airplanes. AD 90-23-14 required inspections of the fuselage skin lap splice between body station (BS) 340 and BS 400 at stringers (S)-6L and S-6R, and repair if necessary. This new AD adds new repetitive inspections for cracking in the S-6 skin lap splice, which terminates the inspections required by AD 90-23-14; eventual modification of the lap splice, which terminates the repetitive inspections; post-modification inspections; and corrective actions if necessary. This AD also adds airplanes to the applicability. This AD was prompted by a report of cracks up to 18.5 inches that were found at S-6L and S-6R on several airplanes, and subsequent analysis results that indicated that the protruding head fastener modification and related post-modification inspections required by AD 90-23-14 are not adequate to prevent cracking at the upper row of fasteners in the S-6 lap joint before the cracks reach a critical length. We are issuing this AD to detect and correct cracking at the upper row of fasteners in the S-6 lap joint, which could result in a sudden loss of cabin pressurization and the inability of the fuselage to withstand failsafe loads.
77-15-15: 77-15-15 BRITISH AIRCRAFT CORPORATION: Amendment 39-2986. Applies to BAC 1- 11 200 and 400 series airplanes, certificated in all categories. Compliance is required within the next 200 hours time in service after the effective date of this AD, unless already accomplished. To prevent the inadvertent loss of cabin pressure due to failure of the light alloy stop on the cabin pressure discharge valve manual control, replace the light alloy stop, P/N AB55-2301, on the gear wheel and drum assembly of the air conditioning discharge valve manual control (P/N AB55A-2425 or ED55A779) with an improved strength stop, P/N AB55-3433, or an FAA-approved equivalent. (British Aircraft Corporation Service Bulletin No. 21-PM 5139, Revision 2, dated September 5, 1973, applies to this same subject.) This amendment becomes effective August 29, 1977.
51-03-01: 51-03-01 MOONEY: Applies to Model M-18 Series Aircraft, Serial Numbers 1 Through 82 and 201 Through 236. Compliance required not later than March 15, 1951. There have been reported failures of the fuel line due to vibration and relative motion between the fuel tank and the fuel shutoff valve. To preclude the possibility of recurrence of this type failure, cut the fuel line at a point approximately 4 inches from the fuel tank outlet and install a 4-inch length of 3/8-inch ID approved aromatic resistant flexible hose and hose clamps at this point. (Mooney Service Bulletin No. 6 covers this same subject.)
77-10-10: 77-10-10 ROCKWELL INTERNATIONAL: Amendment 39-2902. Applies to NA- 265-80 airplanes, serial numbers 380-1 through 380-4, 380-6 through 380-9, 380-11 through 380-13, 380-15, 380-17, 380-19, 380-21, 380-23, 380-25, 380-27, 380-30, 380-32, 380-34, 380- 36 and 380-38 through 380-54, with Relay K1066 installed (Cutler-Hammer P/N 6141H126), certificated in all categories. Compliance required on or before June 7, 1977, unless already accomplished. To provide electrical protection for the Instrument Inverter power input cable, and improve thermal isolation of the Instrument Inverter Remote Reset Circuit Breaker Relay (K1066), accomplish the following: (a) Modification specified in Rockwell International Sabreliner Service Bulletin No. 28, dated April 8, 1977, or later FAA approved revisions. (b) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. (c) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to a base for accomplishment of the modification required by this AD. This amendment becomes effective May 23, 1977.
2013-16-25: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of advance pneumatic detectors (APDs) for engine fire/ overheat detector assemblies failing to reset after activation due to permanent deformation of the detector switch diaphragm after being exposed to high temperatures. This AD requires replacing all three APDs with new detector assemblies. We are issuing this AD to prevent a continued engine fire indication in the cockpit after the actual fire has been extinguished, which is misleading and might influence the pilot to conduct a potentially hazardous ``off-airport'' landing.
90-06-03 R1: 90-06-03 R1 CESSNA: Amendment 39-6528 as revised by Amendment 39-6927, Docket No. 90-CE-10-AD. Applicability: Model 172 airplanes (serial numbers 36216 through 36769) that have not been modified with Cessna Service Kit SK-172-10 or SK-172-10A, certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent cracking of the exhaust heater/muffler that could result in dangerous carbon monoxide levels, accomplish the following: (a) Inspect the exhaust heater/muffler assembly for cracks in accordance with the procedures as outlined in the applicable Cessna Service Manuals, or the following: (1) Remove and disassemble the exhaust heater/muffler assembly by removing the shroud assembly. (2) Visually inspect the exhaust heater/muffler, Cessna Part Number 0550157-32, for cracks, or submerge the muffler in water and pressure test at 5 pounds p.s.i.NOTE 1: Particular attention should be given to the cylindrical surface that contains the heat transfer pins. (3) If cracks, breaks, or any leakage is found in the exhaust heater/muffler area, prior to further flight, replace the exhaust heater/muffler with an airworthy part. (b) Modify the airplane by the installation of Cessna Service Kit SK-172-10A. NOTE 2: Cessna Service Letter (SL) 170/172-11, dated February 3, 1958, and Cessna SL 170/172-13, dated April 7, 1958, contain information that pertains to the subject of this AD. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished provided that the cabin air control remains in the "OFF" position. (d) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, Mid-Continent Airport, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. (e) All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Cessna Aircraft Corporation, P.O. Box 7704, Wichita, Kansas 67277; or may examine the service letters at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 90-06-03 R1 revises AD 90-06-03, Amendment 39-6528. {{Amendment 39-6528 supersedes AD 58-08-02.}} This amendment (39-6927, AD 90-06-03 R1) becomes effective on March 27, 1991.
71-09-01: 71-09-01 CESSNA: Amdt. 39-1193. Applies to all Model 320 series Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent nacelle electrical failures and inflight electrical fires, accomplish the following: A) Within the next 50 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the date of the last inspection, visually inspect the following: 1) The insulating material of the electrical wiring, grommet and clamps located in the engine nacelles between the canted bulkhead and the firewall for charred, burnt or heat hardened conditions; 2) The heat shields located in the engine nacelles between the canted bulkhead and the forewall for deterioration or improper installation and attachment that could contribute to excessive heat in this area. B) If any of the conditions described in Paragraph A are found during the required inspections, prior tofurther flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can be performed, replace any defective parts with airworthy parts. The replacement of defective parts does not relieve the requirement for the repeated inspections specified in Paragraph A. C) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Central Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. D) On or before January 1, 1972 modify the engine nacelles in accordance with Cessna Service Letter ME71-6, dated April 9, 1971, and Cessna Service Kit SK320-53, dated March 5, 1971, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. E) When the engine nacelles are modified in accordance with Cessna Service Letter ME71-6, dated April 9, 1971, and Cessna Service Kit SK320-53, dated March 5, 1971, the inspections required by Paragraph A will no longer be required. This amendment becomes effective April 23, 1971.