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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.
2013-16-08: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report of corrosion of the components of the main landing gear (MLG) retraction actuator found in service; the corrosion was found at the interface of the rod end and the piston, and at the bracket and related pins. This AD requires inspection of the MLG retraction actuator components; corrective actions if necessary; and, for certain retraction actuators, installation of a new jam nut. We are issuing this AD to prevent disconnection of the MLG retraction actuator, which could result in extension of the MLG without damping, and consequent structural damage and collapse of the MLG during landing.
2013-16-07: We are adopting a new airworthiness directive (AD) for certain Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters to require inspecting for the presence of blind holes in the tail gearbox (TGB) attachment fittings, and, if they are missing, installing an additional washer under the head of the attachment bolt until the attachment fitting is replaced with an airworthy attachment fitting. This AD was prompted by the discovery of interference between the TGB aft attachment bolt and the structure fitting, caused by a manufacturing anomaly that omitted the blind hole required for proper fit of the attachment bolt. This condition, if not detected and corrected, could result in insufficient tightening of the TGB casing, damage to the TGB attachment, cracking under the attachment bolt, and loss of the TGB, resulting in loss of control of the helicopter.
75-22-18: 75-22-18 SIAI-MARCHETTI: Amendment 39-2408. Applies to Models S.205-18F and -20F airplanes, S/Ns 001 through 003; 102 through 399 (except S/N 109); 4-101 through 4-282 (except S/N 4-245); 4-285, and 5-303, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible failure of the nose landing gear, accomplish the following: (a) Comply with paragraph (b) of this AD - (1) Within the next 10 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection; and (2) Prior to the next takeoff after each hard-landing, except that the airplane may be flown in accordance with FAR Section 21.197 and 21.199 to a base where paragraph (b) can be complied with. (b) Inspect by visual and dye-penetrant methods the nose landing gear drag brace, P/N 205-9-135, and the area around the drag brace attachments, P/Ns 205-1-059-01, in accordance with paragraph a. of the "Instructions" section of SIAI Marchetti Service Bulletin, S.B. No. 205B33, dated January 8, 1972, or an FAA-approved equivalent. (c) Comply with paragraph (d) of this AD as follows: (1) If a crack is found during the inspection required by paragraphs (a) and (b) of this AD, comply with paragraph (d) of this AD before further flight, except that the airplane may be flown in accordance with FAR 21.197 and 21.199 to a base where paragraph (d) can be complied with. (2) If a crack is not found during an inspection required by paragraphs (a) and (b) of this AD, comply with paragraph (d) of this AD within the next 50 hours' time in service after the effective date of this AD or prior to the accumulation of 600 hours' total airplane time in service, whichever occurs later. (d) Replace the nose landing gear dray brace P/N 205-9-135, with a serviceable reinforced drag brace, P/N 205-9-135-03, and replace the two drag brace attachments, P/Ns 205- 1-059-01, with serviceable drag brace attachments, P/Ns 205-1-180-01 and -02, in accordance with paragraph b. of the "Instructions" section of SIAI Marchetti Service Bulletin S.B. No. 205B33 dated January 8, 1972, or an FAA-approved equivalent. (e) The inspections required by paragraphs (a) and (b) of this AD may be discontinued upon accomplishment of the replacements required by paragraphs (c) and (d) of this AD. This amendment becomes effective November 5, 1975.
2013-15-15: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727 airplanes. This AD was prompted by an evaluation by the design approval holder indicating that the frame-to- floor beam attachment is subject to widespread fatigue damage. This AD requires repetitive high frequency eddy current inspections for any crack of the frames at body station (STA) 188 through STA 344, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking at the frame-to-floor beam attachment, on both the left- and right-sides, which could result in reduced structural integrity of the airplane, and decompression of the cabin.
75-17-09: 75-17-09 FLUG-UND FAHRZEUGWERKE AG: Amendment 39-2311. Applies to HBV "Diamant" and Diamant 16.5 gliders, all serial numbers, certificated in all categories. Compliance is required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To prevent structural failure of the lower harness attachments D1.201-0710, reinforce the attachments in accordance with the "REQUIRED ACTION" specified in Flug-und Fahrzeugwerke AG Service Bulletin No. 5, dated February 4, 1974, or an FAA-approved equivalent. This amendment becomes effective August 18, 1975.
70-18-04: 70-18-04 FAIRCHILD HILLER HELICOPTERS: Amdt. 39-1075. Applies to 1100 series helicopters certificated in all categories. Compliance required within the next 25 flight hours of the effective date of this A/D unless already accomplished. To prevent failure of transmission vertical struts and mounts: (1) Strip epoxy paint from weld areas of transmission vertical struts and mounts P/N 24-28030-1 and -2 with commercial paint stripper. (2) With dye penetrant inspect weld areas for cracks. (3) Replace any cracked part prior to further flight. (4) Refinish stripped areas with two coats of zinc chromate. (5) Repeat above procedure at each succeeding 100 flight hours. This amendment is effective September 15, 1970.
76-02-03: 76-02-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2496. Applies to Model SA341G "Gazelle" helicopters, certificated in all categories. Compliance is required as indicated. To prevent abnormal wear of main gear box oil pump hydraulic unit drive gear splines, accomplish the following: (a) Prior to the accumulation of 600 hours' total time in service or within the next 10 hours' time in service after the effective date of this AD, whichever occurs later, unless already accomplished within the last 590 hours' time in service, and thereafter at intervals not to exceed 600 hours' time in service from the last inspection, comply with paragraph (b) of this AD. (b) Inspect the main gear box (MGB) oil pump hydraulic unit drive gear splines in accordance with subparagraphs 1C(1) and 1C(2), and replace the drive gear, oil pump or both, as necessary, or return to service in accordance with the criteria set forth in subparagraph 1C(3), of Gazelle Service Bulletin No. 05.09a, dated March 10, 1975, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667. (c) Prior to the accumulation of 600 hours' time in service or within the next 10 hours' time in service after the effective date of this AD, whichever occurs later, unless already accomplished within the last 190 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last lubrication, comply with paragraph (d) of this AD. (d) Lubricate the splines in accordance with subparagraph 1C(4) of Gazelle Service Bulletin No. 05.09a, dated March 10, 1975, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667. This amendment becomes effective January 30, 1976.