Results
58-02-03: 58-02-03 HILLER: Applies to UH-12 Series Helicopters Equipped With Marvel- Schebler Automatic Altitude Compensating Carburetor Model MA-4-5AA (Aircooled P/N 19588). Compliance required by June 1, 1958. With a Marvel-Schebler Model MA-4-5AA carburetor installed, it is possible to start and run the engine with the carburetor mixture control in the idle cutoff position if the throttle is partially or fully opened. However, as soon as the throttle is fully closed, the idle cutoff will operate and shut off the engine. Therefore, it would be possible to start the engine, take off, and fly with the mixture in idle cutoff, as long as the throttle is never closed. The first time the throttle is closed, however, as in autorotation, an immediate engine stoppage would occur. To prevent inadvertent engine stoppage in flight due to failure to place the carburetor mixture control in the "ALT.COMP" position before takeoff, the following measure is necessary: Delete the carburetor mixture control from the cockpit and secure the carburetor setting at "ALT.COMP" at the carburetor. Hiller will issue a service bulletin covering this subject. Appropriate FAA approved Helicopter Flight Manual revision required.
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.