Results
97-12-03: This amendment supersedes two existing airworthiness directives (AD) that are applicable to certain Boeing Model 747 series airplanes. One of those AD's currently requires inspections for cracking, corrosion, and fracturing of the lower horizontal clevis of the strut midspar fittings, and replacement of discrepant parts with new or serviceable parts, or repair, if necessary. That AD also requires inspection for removal of broken sealant of the clevis and the fasteners, and various follow-on actions. It also provides for optional terminating actions for the inspections. The other AD currently requires inspection for cracking of certain fastener holes of the upper and lower horizontal clevis legs. This amendment continues to require inspections to detect cracking, corrosion, and fracturing of the lower horizontal clevis; and adds corresponding inspections of the upper horizontal clevis, and replacement of discrepant parts with new parts, or rework, if necessary. This amendment also removes certain optional terminating actions. This amendment is prompted by reports of cracking of the lower and upper leg of the horizontal clevis of the midspar fitting. The actions specified in this AD are intended to detect and correct cracking and fracturing of the clevis, which could result in drooping of the strut at the strut-to-wing interface, and consequent separation of the engine and strut from the airplane.
94-22-04: This amendment supersedes an existing airworthiness directive (AD), applicable to Costruzioni Aeronautiche Giovanni Agusta S.p.A. Model A109A and A109AII series helicopters, that currently imposes a calendar life limit of 10 years and 6 months on the main rotor retention strap assemblies (strap assemblies). This amendment requires reducing the calendar life limit to 8 years. This amendment is prompted by additional service experience and analyses, that show the current life limit needs to be reduced from 10 years and 6 months to 8 years to prevent deterioration and subsequent failure of the strap assemblies. The actions specified by this AD are intended to prevent failure of the strap assemblies, loss of a main rotor blade, and subsequent loss of control of the helicopter.
2011-27-05: We are superseding an existing airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model 340A (SAAB/SF340A) and SAAB 340B airplanes. That AD currently requires an inspection of the main landing gear (MLG) separation bolt harness for broken wires and corroded connectors, and corrective actions if necessary; and for certain airplanes, a modification of the MLG separation bolt's electrical harness. This new AD requires replacement of the separation bolt harness. This AD was prompted by reports of broken wires and corroded connectors in the SAAB 340 MLG emergency release system. We are issuing this AD to prevent improper release of the MLG during an emergency situation, possibly resulting in damage to the airplane during landing and injury to the occupants.
97-11-12: This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N22S, and N24A airplanes. This action requires repetitively inspecting the stub wing upper front spar cap flanges for cracks, and repairing any cracked part. This AD results from fatigue tests that show that the stub wing upper front spar cap flanges could fail over time because of fatigue. The actions specified by this AD are intended to prevent structural failure of the front spar caused by cracks in the stub wing upper front spar cap flanges, which could result in loss of control of the airplane.
84-02-08: 84-02-08 SCOTT AVIATION: Amendment 39-4801. Applies to all aircraft equipped with Scott Aviation oxygen cylinders delivered between May 16, 1983, and September 22, 1983, listed in Scott Airworthiness Alert dated September 27, 1983, revised December 12, 1983. Compliance required as indicated below. To prevent possible use of improperly charged oxygen cylinders, bleed down (discharge) the cylinders, and recharge with aviator's breathing oxygen, per the above Scott Airworthiness Alert. 1. For unpressurized airplanes, compliance required before flight at operating altitudes above 14,000 feet, unless already accomplished. 2. For pressurized airplanes, compliance required within 500 hours in service, unless already accomplished. 3. For pressurized and unpressurized airplanes, compliance with this AD is required no later than May 1, 1984. After accomplishment of this AD, mark each oxygen cylinder with a white paint dot approximately 1/2 inch in diameter after the serial number, as evidence of compliance with this AD. Cylinders previously recharged in accordance with this AD, for which records of such action are available, may be marked with the paint dot without repeating the recharging. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the compliance time of this AD may be adjusted and/or an equivalent method of compliance may be approved, upon request to the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, telephone (516) 791-6680. The Airworthiness Alert identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Scott Aviation, 235 Eric Street, Lancaster, New York 14086, telephone (716) 683-5100. These documentsalso may be examined at the Office of the Regional Counsel, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective February 9, 1984.
73-19-10: 73-19-10 GRUMMAN AIRCRAFT: Amendment 39-1719 as amended by Amendments 39-1757 and 39-1828 is further amended by Amendment 39-3544. Applies to G-164A S/N's 1 through 1659A and G-164B S/N's 1B through 56B certificated in all categories and all G-164A and G-164B aircraft in which the elevator control horn assembly and torque tube end fittings have not been modified per Gulfstream American Service Note No. 23 or FAA-approved equivalent. Compliance required as indicated. 1. Within the next 25 hours in service or two weeks, whichever occurs first, unless already accomplished within the last 75 hours in service, inspect the bolts attaching the Elevator Control Horn, P/N A 1841-3, to the left and right side elevator, P/N A1201-5A and A1201-4A respectively, for a standard (ref. AC 43.13-1 Chg. 7) torque rating and for corrosion and thereafter at intervals not to exceed 100 hours in service or 60 days, whichever occurs first. 2. If any looseness is detected, the bolts must be removed and inspected for wear. 3. Replace any worn or corroded bolts with bolts of the same part number or NAS 1304-12 bolts or an equivalent as approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, except that the aircraft may be flown in accordance with FAR 21.197. 4. The bolts referenced in paragraph 3, must be replaced at intervals not exceeding 1000 hours in service or one year, whichever occurs first. 5. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the inspection intervals specified in this AD. 6. The repetitive inspection intervals required by paragraph 1 may be discontinued upon accomplishment of the modification in Grumman Gulfstream Service Note No. 23 dated 8/1/76, or an FAA-approved equivalent. 7. Any equivalent parts or alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Grumman American Aviation Corporation AgCat Service Bulletin No. 51 pertains to this subject.) Amendment 39-1719 was effective September 21, 1973. Amendment 39-1757 was effective December 20, 1973. Amendment 39-1828 was effective May 6, 1974. This Amendment 39-3544 is effective August 29, 1979.
2011-27-02: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3 airplanes. This AD was prompted by results from a damage tolerance analysis conducted by the manufacturer indicating that fatigue cracking could occur in wing rear spar and upper surface zones. This AD requires repetitive inspections for cracking of the wing rear spar and upper surface zones, and repair if necessary. We are issuing this AD to detect and correct such fatigue cracking, which could result in cracking that grows large enough to reduce the wing strength below certificated requirements and possibly cause fracture of the rear spar, resulting in extensive damage to the wing and possible fuel leaks.
2011-26-07: We are superseding an existing airworthiness directive (AD) for certain TCM and R-RM series reciprocating engines. That AD currently requires replacement of certain magnetos if they fall within the specified serial number (S/N) range, inspection of the removed magneto to verify that the stop pin is still in place, and, if the stop pin is not in place, inspection of the engine gear train, crankcase, and accessory case. This new AD corrects the range of S/Ns affected, requires the same replacement and inspections, and adds R-RM C-125, C- 145, O-300, IO-360, TSIO-360, and LTSIO-520-AE series reciprocating engines to the applicability. This AD was prompted by our awareness of an error in the previous AD applicability in the range of magneto S/Ns affected and of the need to include certain engines made by R-RM, under license of TCM. We are issuing this AD to prevent engine failure and loss of control of the airplane due to migration of the magneto impulse coupling stop pin out of the magneto frame and into the gear train of the engine.
2006-11-18: We are adopting a new airworthiness directive (AD) for certain Pacific Aerospace Corporation Ltd. Model 750XL airplanes. This AD requires you to inspect the condition of the insulation of the wiring adjacent to the electrical plugs mounted in the left-hand (LH) and right-hand (RH) sides of the forward end of the cockpit center console for signs of abrasion and arcing. If you find any evidence of abrasion or arcing, this AD requires you to replace the affected wire(s) and secure the wires away from the back shells of the electrical plugs. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. We are issuing this AD to detect and correct damaged wires on the LH and RH sides of the forward end of the cockpit center console, which could result in short-circuiting of the related wiring. This could lead to electrical failure of affected systems and potential fire in the cockpit.
94-15-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company Model R22 helicopters. This action requires an initial inspection and repetitive checks and visual inspections for corrosion and cracks on certain main rotor blades. This amendment is prompted by reports of chordwise cracks found in the main rotor blades. The actions specified in this AD are intended to prevent abnormal in-flight vibrations, failure of the main rotor blade, and subsequent loss of control of the helicopter.