Results
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.