Results
2021-19-16: The FAA is superseding Airworthiness Directive (AD) 2021-16- 02, which applied to certain Airbus Helicopters Model SA330J, AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2021-16-02 required inspecting the locking safety mechanism of the left-hand (LH) side stairway door handle and depending on the results, corrective action. AD 2021-16-02 also required modifying that locking safety mechanism. This AD retains the requirements in AD 2021-16-02, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference, and clarifies a certain exception. This AD was prompted by the need to clarify that exception. The FAA is issuing this AD to address the unsafe condition on these products.
98-12-07: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D series engines, that currently requires a determination of the utilization rate and coating type of the 7th, 8th, 9th, 10th, 11th, and 12th stage high pressure compressor (HPC) disks, and removal, inspection for corrosion, and recoating of those HPC disks based on utilization rate. This amendment shortens the inspection interval for certain low utilization disks. This amendment is prompted by reports of an additional uncontained 9th stage HPC disk failure due to corrosion pitting. The actions specified by this AD are intended to prevent fracture of the HPC disks, which can result in uncontained release of engine fragments, inflight engine shutdown, and airframe damage. The incorporation by reference of Pratt & Whitney Alert Service Bulletin No. 6038, Revision 5, dated August 17, 1994, as listed in the regulations, was approved previously by the Director of the Federal Register as of November 28, 1994 (59 FR 49175, September 27, 1994).
2021-19-05: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by a report of a cracked hoist support assembly having a certain part number. This AD requires a one-time inspection of the hoist support assembly and, depending on the findings, replacement with a serviceable part, as specified in a European Union Aviation Safety Agency (EASA) Emergency AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
72-06-03: 72-06-03 HAWKER SIDDELEY: Amdt. 39-1404. Applies to Hawker Siddeley Model DH-114 "Heron" Airplanes. Compliance is required as indicated. To prevent hazardous internal corrosion of the tubular structure of engine mounting frames, P/N's 14EM11A and 12A, accomplish the following: (a) For airplanes with engine mounting frames with serial numbers DHB/1 and subsequent, or with serial numbers prefixed by "DH/...", that do not incorporate Modification No. 1529, within four years after the effective date of this AD, unless already accomplished within the last four years, and thereafter at intervals not to exceed four years from the last inspection, conduct an x-ray inspection of the tubular structure of the engine mounting frame, P/N's 14EM11A and 12A, for internal corrosion in accordance with Hawker Siddeley Aviation Ltd. Technical News Sheet Series: Heron (114) No. E.3, Issue 1, dated August 24, 1964, or Issue 3, dated September 14, 1970, or later ARB-approved issue or FAA-approved equivalent. (b) For airplanes with engine mounting frames with serial numbers DHB/1 and subsequent, or with serial numbers prefixed by "DH/...", that incorporate Modification No. 1529, within four years after the date of incorporation of the modification, or within one year after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed four years from the last inspection, conduct an x-ray inspection of the tubular structure of the engine mounting frames, P/N's 14EM11A and 12A, for internal corrosion in accordance with Hawker Siddeley Aviation Ltd. Technical Sheet Series: Heron (114) No. E.3, Issue 3, dated September 14, 1970, or later ARB-approved issue or FAA-approved equivalent. (c) For airplanes with engine mounting frames with serial numbers prefixed by "S4/DHB..." or "BGB/DHB..." (manufactured to the standards of Modification No. 1529), within 10 years from the date of manufacture, and thereafter at intervals not to exceedfour years from the last inspection, conduct an x-ray inspection of the tubular structure of the engine mounting frames, P/N's 14EM11A and 12A, for internal corrosion in accordance with Hawker Siddeley Aviation Ltd. Technical News Sheet Series: Heron (114) No. E.3, Issue 3, dated September 14, 1970, or later ARB-approved issue or FAA-approved equivalent. NOTE: See Hawker Siddeley Technical News Sheet Series: Heron (114), No. E.3, Issue 3, dated September 14, 1970, for dates of engine mount manufacture. (d) If internal corrosion is found during an inspection required by paragraph (a), (b), or (c), before further flight replace or repair the engine mounting frame in accordance with Hawker Siddeley factory approved instructions or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, and continue to inspect in accordance with paragraph (a), (b), or (c) whichever is applicable. This supersedes Amendment 39-128 (30 F.R. 11030), AD 65-20-03. This amendment becomes effective April 6, 1972.
2004-09-23: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires repetitive inspections of the control panel of the direct current (DC) generator for discrepancies, and replacement of any discrepant part. This action is necessary to prevent loss of both DC generator systems and loss of several other airplane systems, which could lead to the pilot's inability to maintain controlled flight. This action is intended to address the identified unsafe condition.
2011-25-10: We are adopting a new airworthiness directive (AD) for all PW JT9D-7R4H1 turbofan engines. This AD was prompted by reports of cracks in five high-pressure compressor (HPC) shafts. This AD requires removing certain HPC shafts before their certified life limits and establishes a new, lower life-limit for these parts. We are issuing this AD to correct the unsafe condition on these products.
2011-25-02: We are adopting a new airworthiness directive (AD) for BRP- Powertrain GmbH & Co. KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a production process review, a deviation in the manufacturing process of certain part number (P/N) 888164 crankshafts has been detected, which may have resulted in a latent defect. This condition, if not corrected, could lead to crack formation on the power takeoff side of the crankshaft journal, possibly resulting in failure of the crankshaft support bearing, in- flight engine shutdown and forced landing, damage to the aeroplane and injury to the occupants. We are issuing this AD to prevent in-flight failure of the engine and forced landing.
2021-18-12: The FAA is adopting a new airworthiness directive (AD) for certain PZL Swidnik S.A. Model PZL W-3A helicopters. This AD was prompted by a report of fractured hoist carrying assembly bracket (bracket) bolts. This AD requires repetitively inspecting the sealing compound of certain part-numbered brackets, and depending on the results, removing the hoist or removing the hardware from service and installing new hardware. As an option to replacing the bolts, this AD allows deactivating the hoist, turning the circuit breaker panel switches to the OFF position, installing inoperative placards on the circuit breaker panel switches, and before each flight, inspecting the sealing compound. This AD also establishes a life limit for the bracket bolts, and prohibits installing an affected hoist or an affected bracket and hoist unless the actions required by this AD have been accomplished. The FAA is issuing this AD to address the unsafe condition on these products.
67-29-04: 67-29-04 GRUMMAN: Amdt. 39-497 Part 39 Federal Register October 25, 1967. Applies to Type G-164 aircraft, Serial Numbers 1 through 400. Compliance required as indicated. Gulfstream G-164 type aircraft have experienced loose rivets which attach the rod ends of the elevator forward pushrod assembly. To detect loose rivets on the assembly, P/N A1847-1 (Aircraft Serial Numbers 1 through 100) and P/N A1847-3 (Aircraft Serial Numbers 101 through 400), accomplish the following: (a) For aircraft with 250 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (b) For aircraft with less than 250 hours' total time in service on the effective date of this AD comply with paragraph (c) before the accumulation of 300 hours' total time in service, and thereafter at intervals not to exceed 100 hours' time inservice from the last inspection. (c) Visually inspect the fore and aft ends of the pushrod assemblies to determine if there are loose rivets or elongated holes. (d) If loose rivets or elongated holes are found during the inspection required in paragraphs (a) or (b), before further flight, remove rivets (4 places) and repair as follows: (1) Line ream original rivet holes .190 + .001 inch. (4 places) (2) Install AN3-13A bolt, AN960-10 washer (under nut), and AN365-1032 nut. (4 places) If holes have elongated in excess of .191 inches, repair as follows: (3) Line ream original rivet holes .250 + .001 inch. (4 places) (4) Install AN4-14A bolt, AN960-416 washer (under nut), and AN365-428 nut. (4 places) If holes have been elongated in excess of .251 inch then replace the assembly. (e) The repetitive inspection required by paragraphs (a) and (b) of this AD may be discontinued upon accomplishment of the repair specified in paragraph (d) or equivalent repair approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. (f) Upon request, with substantiating data submitted through an FAA maintenance inspector, compliance time may be increased by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. This amendment effective October 27, 1967.
52-01-01: 52-01-01 BELL: Applies to All Models 47B, 47B3, 47D Helicopters and to Model 47D1 Helicopters Serial Numbers 145 to 164, Inclusive. Compliance required at next 300-hour overhaul, but not later than March 1, 1952. To provide locks of increased tensile strength which will resist shearing should the blade grip adapters tend to loosen, remove the existing lockwire or blade grip adapter locks (P/N 47- 120-154-1), check the torque (3,000-3,300 inch-pounds) of the adapters and install revised locks (P/N 47-120-154-2). (Bell Service Bulletin No. 76 covers this same subject.)
2004-09-17: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 and -300 series airplanes, that requires a one-time inspection for fracture and/or breakage of the hinge bolt of the output rod of the rudder spring tab lever assembly, and corrective action if necessary. This AD also requires modification of the hinge bolt. This action is necessary to prevent fracture and/or breakage of the hinge bolt, which could result in migration of the bolt tail, a loose spring tab, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
98-12-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Models ASW-19 and ASK 21 sailplanes. This AD requires: modifying the rudder surface panels; replacing the airbrake bellcrank; and modifying the rear canopy hinge structure. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent loss of the canopy caused by design deficiency, airbrake failure caused by cracking, and rudder panel flutter caused by high density altitude conditions, all of which could result in reduced sailplane controllability.
2021-20-02: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. (type certificate previously held by Bell Helicopter Textron Inc.) Model 205B helicopters. This AD was prompted by a notification of certain parts needing a life limit. This AD requires determining the total hours time-in-service (TIS) of certain part-numbered main rotor grip assemblies (grip assemblies), establishing a life limit for certain part-numbered grip assemblies, removing from service any grip assembly that has reached or exceeded its retirement life, creating a component history card, and removing any grip assembly from service before reaching its retirement life. This AD also prohibits installing certain grip assemblies unless the life limit was established in accordance with this AD. The FAA is issuing this AD to address the unsafe condition on these products.
96-10-03: This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) PA28, PA32, PA34, and PA44 series airplanes. This action will require inspecting and modifying the flap lever assembly. Reports of worn flap handle attach bolts and elongated holes in the flap lever to cable mounting attach point prompted this AD action. The actions specified by this AD are intended to prevent failure of the flap handle attach bolt and sudden retraction of the flaps, which, if not detected and corrected, could result in loss of control of the airplane.
59-20-02: 59-20-02 LOCKHEED: Applies to All Model 1649A Aircraft. Compliance required on items (1) and (2) by October 15, 1959; compliance required on item (3) by December 1, 1959. As a result of a recent accident involving a suspected explosion of a wing tank, the following shall be accomplished to prevent the possible recurrence of such an explosion: (1) Remove the static wick on the inboard wings adjacent to the tank vents. (2) Install temporary placard at engineer's station reading as follows: "In order to maintain a nonexplosive rich mixture in tanks, do not use fuel out of auxiliary tanks Nos. 5, 6, and 7 below 50 gallons. In operations which involve use of fuel from main tanks only, the 50 gallons of residual fuel in the auxiliary tanks must be replaced with 50 gallons of fresh fuel or mixed with at least 150 gallons of fresh fuel at the end of every 12 flight-hours or 5 flights, whichever occurs first." (3) Install P/N 634014-1 or equivalent flame arrestors in the tank vent outlets. After installation of flame arrestors described in item (3), item (2) may be disregarded.
2004-09-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and Model 328-300 series airplanes, that requires repetitive detailed inspections of all attach caps of the passenger seats for cracks or defects; and replacement of the caps with new caps, if necessary. This action is necessary to prevent failure due to cracking of the seat frame attach caps on the passenger seat assemblies, which could result in separation of the passenger seat from the supporting structure during an emergency landing, hard landing, or turbulence, and consequent injury to the seat occupant. This action is intended to address the identified unsafe condition.
2021-17-14: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream G280 airplanes. This AD was prompted by a report that during full-scale fatigue testing, a crack was found in the area of the attachment of the wing rib 0 to the front spar. This AD requires non-destructive testing on the forward (front) spar vertical stiffener and rib 0 for any cracking, installation of a doubler to the forward (front) spar and rib 0 attachment, and repair if necessary, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
71-17-09: 71-17-09 SCHWEIZER AIRCRAFT: Amdt. 39-1272. Applies to SGS 1-23H. Type Gliders. To prevent severe oscillations and vibrations resulting from excessively loose rudder fittings accomplish the following: (a) Within the next 25 hours time in service unless accomplished within the last 75 hours time in service and thereafter at intervals not to exceed 100 hours time in service, inspect the lower and upper rudder and fin hinges P/N 1A-107-2, P/N 23H704-16 & -17, P/N 1A-105-2 and P/N 23H705-21, to assure that neither the fore and aft nor the sidewards free-play exceeds five-thousandths (0.005) inches. (b) If free-play in excess of the limits set forth in paragraph (a) is found, replace hinges and their connecting bolts with parts of the same part number or with FAA approved equivalent parts; or incorporate a modification described in Schweizer Aircraft Corporation Service Bulletin No. 102-23-2 dated 29 June 1971 or an FAA approved equivalent modification. Equivalent partsor modifications must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region upon receipt of substantiating data submitted through an FAA Maintenance Inspector. This amendment becomes effective August 26, 1971.
98-11-20: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes that incorporate an executive cabin layout. This AD requires modifying the lavatory wall and passenger seat configuration. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent head injuries during an airplane crash because the lavatory wall and passenger seat configuration do not meet current head injury criteria regulations.
2004-09-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 B4-600, B4-600R, C4 605R Variant F, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. This action requires a one-time inspection for damage of the integrated drive generator electrical harness and pyramid arm, and repair if necessary. This action is necessary to prevent electrical arcing within the engine pylon, which could result in loss of the relevant alternating current (AC) bus bar, reduced structural integrity of the engine pylon, and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
98-11-12: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-301, -311, -314, and -315 series airplanes, that requires installation of additional wiring and new electrical connectors for the lights in the forward end of the passenger overhead compartments. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent severe overheating of the electrical connectors for the lights in the forward end of the passenger overhead compartments, which could result in smoke and fire in the passenger cabin.
2021-18-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by a report that an operator found solid rivets with missing heads at the left buttock line 25 on the sloping pressure deck web. This AD requires doing a detailed inspection of the left- and right-side sloping pressure deck at certain stations for any damaged solid rivets, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
69-08-03: 69-08-03 VICKERS: Amdt. 39-747. Applies to Viscount Models 744, 745D, and 810 Series airplanes. Compliance required within the next 1000 hours' time in service after the effective date of this AD, unless already accomplished. To prevent discharge of power plant fire extinguishant into the wrong power plant due to incorrect assembly of power plant fire extinguisher bottles, install interference brackets and retaining cables to the detachable clip assemblies at the fire extinguishing bottle neck at the inner and outer nacelle mountings in accordance with British Aircraft Corporation Modification Bulletin D.3218 dated July 14, 1968 (700 Series) or Modification Bulletin FG.2094 dated July 14, 1968 (800/810 Series) or later ARB-approved issues or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. This amendment becomes effective May 11, 1969.
2021-18-03: The FAA is superseding Airworthiness Directive (AD) 2020-26- 02, which applied to certain Yabora Industria Aeronautica S.A. (type certificate previously held by Embraer S.A.) Model ERJ 190-400 airplanes. AD 2020-26-02 required amending the existing airplane flight manual (AFM) to incorporate a new limitation and revise certain normal procedures. This AD retains those requirements and also requires upgrading the electronic engine control (EEC) software, as specified in an Agencia Nacional de Aviacao Civil (ANAC) AD, which is incorporated by reference. This AD was prompted by a report of an in-flight shutdown (IFSD) due in part to failure in the low-pressure compressor (LPC) rotor 1 during operation in high altitude at high thrust settings, and by the development of updated EEC software, which would \n\n((Page 51598)) \n\nterminate the requirement to amend the existing AFM. The FAA is issuing this AD to address the unsafe condition on these products.
2004-09-03: The FAA adopts a new airworthiness directive (AD) for certain HPH s. r. o. (HPH) Models Glasflugel 304CZ, 304CZ-17, and 304C sailplanes. This AD requires you to inspect to determine the airbrake handle attachment rivet material. This AD also requires you to replace any non-steel rivet with a steel rivet. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. We are issuing this AD to prevent the airbrake handle from becoming loose, which could result in failure of the airbrake control. This failure could lead to loss of control of the sailplane.