Results
2013-22-20: We are adopting a new airworthiness directive (AD) for Embraer S.A. Model EMB-505 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking in the stator pressure plate of the brake assembly, which may lead to loss of brake parts on the runway and reduced brake capability with possible runway excursion. We are issuing this AD to require actions to address the unsafe condition on these products.
82-16-07: 82-16-07 HILLER AVIATION: Amendment 39-4469. Applies to Hiller Aviation Model UH-12E and L and OH-23F and G Series helicopters certificated in all categories that are equipped with engine drive torsional coupling assemblies, P/N 21047-9 and P/N 21047-11 (S/N 704 through 766) and P/N 21047-15 (all serial numbers), Airworthiness Docket No. 82-ASW-52. Compliance required as indicated unless already accomplished. To detect possible cracks and prevent failure of the engine drive torsional coupling assembly, accomplish the following: 1. Within 10 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 50 hours' time in service: (a) Remove from the helicopter torsional coupling assemblies P/N 21047-9 and -11 (S/N 704 through 766) and P/N 21047-15 (all serial numbers). These have a stamped rubber cure date of December 1980 or later. (b) Clean and inspect the lower housing P/N 21046 in the eight window areas adjacent to the engine attach flange using a fluorescent penetrant inspection method. (c) Replace assemblies with cracked housings before further flight and install a serviceable assembly as prescribed in the appropriate model maintenance manual or FAA approved equivalent. 2. The inspections required by this AD are not applicable to UH-12E, or OH-23F and G series helicopters converted to the turbine engine installation by STC SH178WE. 3. Equivalent means of compliance must be approved by the Manager, Western Aircraft Certification Field Office, P.O. Box 92007, World Way Postal Center, Los Angeles, California 90009. 4. Special flight permits may be issued in accordance with FAR 21.197 and FAR 21.199 to fly aircraft to a base where compliance with this AD can be accomplished. Hiller Aviation Service Bulletin S.B. UH-12-21-3 dated August 4, 1982, contains information regarding this AD. This amendment becomes effective October 15, 1982, to all persons, except those to whomit was made immediately effective by priority mail AD 82-16-07 issued July 23, 1982.
76-09-11: 76-09-11 LOCKHEED: Amendment 39-2601 as amended by Amendment 39-2615. Applies to all Model 382 series airplanes below serial number 4673. Before further flight, unless already accomplished, perform the crank arm inspection for rudder, aileron and elevator in accordance with Lockheed Alert Service Bulletin A 382-27-17. If the crank arms do not pass the inspection requirements, replace the crank arm or servo valve assembly prior to further flight. The Lockheed Alert Service Bulletin stated that acceptable replacement cranks were identified with a "V" index mark. However, some of the replacement cranks are being made from a different material than those identified with a "V" index mark. These new cranks are identified with a straight line index mark and either of the cranks identified with a "V" or a straight line index mark are acceptable. Amendment 39-2601 was effective May 14, 1976 and was effective on receipt for all recipients of the telegram dated April 23, 1976, whichcontained this amendment. This Amendment 39-2615 becomes effective immediately.
2013-22-18: We are adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135ER, - 135KE, -135KL, and -135LR airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires repetitive detailed inspections to detect discrepancies on the attaching parts of the lower eyelet fitting of the cockpit windshield center-post, and, if no discrepancy is found, a check to make sure the bolts are tight, and replacement of the attaching parts if necessary. This AD also provides an option to accomplish the replacement of the attaching parts, which terminates the repetitive inspections. This AD was prompted by reports of failure of the bolts that connect the lower eyelet fitting of the cockpit windshield center-post to the forward fuselage. We are issuing this AD to detect and correct failed bolts and attaching parts of the lower eyelet fitting of the cockpit windshield center-post, which could lead to loss of structural integrity of the airplane.
77-14-02: 77-14-02 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2950. Applies to Puma Model SA 330F and SA 330G helicopters that have not been modified in accordance with Puma Service Bulletin No. 53.13. Compliance is required within the next 50 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time in service since the last inspection, until accomplishment of Puma Service Bulletin No. 53.13, dated May 29, 1974, or an FAA- approved equivalent. To prevent possible failure of the forward engine mount support structure, accomplish the following: (a) Inspect for cracks in beams under attachment fittings for the forward engine mounts located between frames 3245 and 3550 in accordance with subparagraph 1C(1) of Puma Service Bulletin No. 05.35, dated April 9, 1974, or an FAA-approved equivalent. (b) If cracks are found which exceed the criteria for continued service set forth in subparagraph 1C(2) of PumaService Bulletin No. 05.35, before further flight, except that the helicopter may be flown in accordance with FAR Sections 21.197 and 21.199, to a base where the work can be performed, replace the beams in accordance with Puma Service Bulletin No. 53.13, dated May 29, 1974, 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 August 1, 1977.
2013-20-16: We are adopting a new airworthiness directive (AD) for MDHI Model MD900 helicopters with certain main rotor blade (MRB) retention bolts (bolts) installed. This AD requires a daily check of the position of each bolt, a daily check and a repetitive inspection for a gap in each bolt, and, if necessary, removing and inspecting the bolt for a crack and replacing any cracked bolt with an airworthy bolt. This AD was prompted by multiple reports of in-service bolt failures. The actions are intended to prevent failure of a bolt, which could lead to loss of MRB structural integrity and subsequent loss of control of the helicopter.
2013-20-15: We are superseding Airworthiness Directive (AD) 97-19-10 for Sikorsky Aircraft Corporation-manufactured Model S-64E helicopters (type certificate currently held by Erickson Air-Crane Incorporated (Erickson)). AD 97-19-10 required inspecting and reworking the main gearbox (MGB) assembly second stage lower planetary plate (plate). This action establishes or reduces the life limits for certain flight- critical components, removes from service various parts, requires repetitive inspections and other corrective actions, and requires replacing any cracked part discovered during an inspection. This AD is prompted by further analysis performed by the current type certificate holder and the service history of certain parts. The actions specified in this AD are intended to prevent a crack in a flight critical component, failure of a critical part, and subsequent loss of control of the helicopter.
2013-20-10: We are superseding airworthiness directive (AD) 2000-12-11, for certain Model A300 B4-600 and Model A300 B4-600R series airplanes. AD 2000-12-11 required repetitive inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair if necessary. This new AD reduces the initial inspection compliance time and repetitive inspection interval. This AD was prompted by a fleet survey and an updated fatigue and damage tolerance analysis indicating a high risk for fatigue cracking on the front and rear spar bottom booms. We are issuing this AD to detect and correct fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar.
76-07-13: 76-07-13 HAMBURGER FLUGZEUGBAU GmbH: Amendment 39-2579. Applies to Model HFB-320 airplanes, S/N 1021 thru 1023, 1026 thru 1028, 1030 thru 1040, 1045, and 1049 thru 1057, certificated in all categories. Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To detect possible incorrect adjustment of camlocks that could result in cracking of the camlock housing, possible inadvertent opening of the door, and inflight explosive decompression, accomplish the following: (a) Inspect the camlocks for correct adjustment in accordance with the accomplishment instructions contained in Section B, Part 1, of HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent. (b) If a camlock is found out of adjustment beyond the tolerances specified in HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976,or an FAA-approved equivalent, rectify the camlock adjustment in accordance with the accomplishment instructions contained in Section B, Part 2, of Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent. (c) Inspect the door frame camlock housings, which house the camlocks for which adjustment is required in accordance with paragraph (b) of this AD, for cracks, using a dye penetrant method in accordance with the instructions contained in Section B, Part 3, of HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent. (d) If any cracks are found in the door frame camlock housing during the inspection required by paragraph (c) of this AD, before further flight, except that the aircraft may be flown unpressurized in accordance with FAR's 21.197 and 21.199 to a base where the replacement can be accomplished, replace the camlock housing with a new part of the samepart number. This amendment becomes effective, April 26, 1976.
2013-22-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 series airplanes. This AD was prompted by reports of fasteners missing on an airplane undergoing a passenger- to-freighter conversion. This AD requires doing a general visual inspection of the station 1920 splice clip for correct fastener installation, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct missing or incorrect fasteners, which can lead to cracking and loss of load carrying capacity, resulting in a possible decompression event.