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2021-12-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK 117 D-2 helicopters. This AD was prompted by a short circuit in a yaw trim actuator connector that occurred during production electrical tests. This AD requires replacing certain wire harness trim connector backshells (backshells), as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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73-14-06: 73-14-06 ROCKWELL COMMANDER: Amdt. 39-1670. Applies to Model 112 airplanes Serial Number 3 and up certificated in all categories equipped with Hartzell propeller spinner C-3533 or C-3533P.
Compliance is required within the next 10 hours time in service after the effective date of this AD and every 10 hours time in service thereafter.
Accomplish the following:
(1) Remove the spinner dome.
(2) Visually inspect front bulkhead inside spinner dome for cracks or fractures in the flange or in radius between flange and web.
(3) Visually inspect rear bulkhead and doublers for cracks in the vicinity of the spinner dome attachments, and attachment of the rear bulkhead to propeller hub.
(4) Replace defective, cracked, or broken parts with new or serviceable parts.
(5) Reassemble spinner dome to rear bulkhead. Insure that fiber washers are fitted under the attaching screw heads. Torque screws to 20 - 25 in.lbs.
(6) Record compliance with this airworthiness directive in Aircraft Log Book.
Rockwell International, Albany Aircraft Division, Service Bulletin, SB-112-4 relates to this same subject.
This amendment is effective June 26, 1973, and was effective upon receipt for all recipients of the air mail letter dated June 6, 1973, which contained this amendment.
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68-08-09: 68-08-09 FAIRCHILD-HILLER: Amdt. 39-588. Applies to FH-1100 type Helicopters.
Compliance required as follows:
(a) Remove P/N 19E49-3A -3B coupling shaft serial numbers 20, 21, 22, 23, 24, 25, 75, 77, 87, 90, 93, 98, 104 and 106 from service prior to further flight and replace with the same part number but different serial numbers.
This amendment effective April 23, 1968.
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2021-11-25: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters (Type Certificate previously held by Eurocopter France) Model AS350B3 and EC130T2 helicopters. This AD was prompted by a report of failure of an engine digital electronic control unit (DECU). This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
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65-18-03: 65-18-03 VICKERS: Amdt. 39-114 Part 39 Federal Register August 14, 1965 as amended by Amendment 39-2282. Applies to Viscount Models 744, 745D and 810 Series Airplanes.
Compliance required as indicated.
Cases of severe corrosion on the bore surfaces of the support tubes of the engine mount assemblies, Drawing Nos. 70037 Sht. 3, 80237 Sht. 3, 80237 Sht. 35 and 81037 Sht. 29 have been reported.
To correct this condition accomplish the following:
(a) Within the next 4,000 hours' time in service or at next engine overhaul period, whichever is the sooner, after the effective date of this AD, unless already accomplished, conduct an inspection of the support tubes in accordance with British Aircraft Corporation Preliminary Technical Leaflet No. 252, Issue 2, dated May 22, 1971, for the 700 Series (for 744 and 745D aircraft), and No. 117, Issue 2, dated May 22, 1971, for the 800/810 Series (for 810 Series aircraft), to determine if corrosion exists on the surface of the bore and, if corrosion exits, to determine its depth.
(1) Accomplish the inspection by radiographic or ultrasonic methods as set forth in the appendices of the applicable Preliminary Technical Leaflet or by FAA-approved equivalent method.
(2) If, on inspection, no corrosion exists or the depth of existing corrosion does not exceed 0.030 inch, subject the support tubes to the dewatering and reprotection scheme set forth in paragraphs 5.1 and 5.1.2 of the applicable Preliminary Technical Leaflet.
(3) Where the depth of corrosion is in excess of 0.030 inch in any section of a support tube, the tube in question must be replaced before further flight.
(b) In addition to the inspection and reprotection requirements in paragraph (a), accomplish the dewatering and reprotection scheme in paragraphs 5.1 and 5.1.2 of the applicable Preliminary Technical Leaflet whenever the engine mount assembly is broken down for any reason. Accomplish the dewatering and reprotection after the end fittings have been assembled.
(c) Within seven years from the date of compliance with paragraph (a) or before the accumulation of 500 hours' time in service after the effective date of this amendment, whichever occurs later, repeat the inspection and action specified in paragraph (a). Thereafter, continue to accomplish the inspection and action specified in paragraph (a) at intervals not to exceed seven years from the last inspection.
Amendment 39-114 became effective September 13, 1965.
This amendment becomes effective August 27, 1975.
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2004-05-22: The FAA is adopting a new airworthiness directive (AD) for certain RRD TAY 611-8, TAY 620-15, TAY 650-15, and TAY 651-54 series turbofan engines with ice-impact panels installed in the low pressure (LP) compressor case. This AD requires inspecting all ice-impact panels and fillers in the LP compressor case for certain conditions, and if necessary, replacing any ice-impact panels and fillers that have those conditions. This AD results from two reports of ice-impact panels that released during flight, one of which resulted in reduction of power in both engines. We are issuing this AD to prevent release of ice-impact panels due to improper bonding that can result in loss of thrust in both engines.
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2021-12-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK 117 D-2 helicopters. This AD was prompted by reports of chafing marks on the wiring harness behind the middle side panels in the area of the front passenger (PAX) panels. This AD requires inspecting, modifying, and rerouting the wiring harness, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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2021-13-15: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) (Bell) Model 429 helicopters. This AD was prompted by the identification of certain parts needing life limits and certification maintenance requirement (CMR) tasks. This AD requires establishing life limits and CMR tasks for various parts. Depending on the results of the CMR tasks, this AD requires corrective action. The FAA is issuing this AD to address the unsafe condition on these products.
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47-50-08: 47-50-08 SIKORSKY: Applies to Model S-51 Helicopters.
Compliance required at each 200-hour inspection period.
Disassembly and inspection of the vertical hinge pins and bearings is a mandatory procedure and should be accomplished at each 200-hour inspection period.
The helicopters which utilize Torrington No. 4479 bearings at the vertical hinge pins are subject to replacement of these bearings at each 200-hour inspection period.
The procedure followed is explained on page 4 of Sikorsky Service Bulletin No. 7 dated August 4, 1947.
Helicopters which utilize Smith 14TR-X1 bearings at the vertical hinge pins are subject to inspection at each 200-hour interval and replacement of the bearings is not required unless the installation shows sign of serious wear or damage.
Helicopters which utilize Torrington No. 4479 bearings at the vertical hinge pins can be reworked to incorporate Smith 14TR-X1 bearings at the vertical hinge pins if desired by the owner.
(The procedure to follow for this exchange of bearings is as explained on page 2 of Sikorsky Service Bulletin No. 7 dated August 4, 1947.)
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2004-05-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model DHC-8-401 and -402 airplanes. This action requires a records review to determine the repair/modification status of the airplane, and follow-on and corrective actions as necessary. This action is necessary to prevent cracks in the lower fuselage skin due to fatigue damage in the vicinity of the Number 2 VHF antenna, which could result in rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
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