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53-13-01: 53-13-01 De HAVILLAND GYPSY QUEEN: Applies to All Model 70-4 Engines and to Those 70, 70-2, and 70-3 Engines Incorporating Modification G.1493.
Compliance required not later than September 1, 1953.
In order to prevent the loss of propeller control because of failure of the oil transfer mechanism, Modification G.1920, as described in de Havilland Engine Service Modification News Sheet GQ. 70 dated May 8, 1953, must be accomplished. Should Modification G.1728 not be incorporated, it is strongly recommended that it be embodied concurrently with Modification G.1920.
The FAA concurs in this mandatory action.
(de Havilland Modification News Sheet GQ. 70 dated May 8, 1953, available from de Havilland Aircraft Co., representative at Linden Airport, Linden, N.J., covers the same subject and describes method of repair.)
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2021-22-14: The FAA is superseding Airworthiness Directive (AD) 2021-05-16 for certain Pratt & Whitney Division (PW) PW4164, PW4164-1D, PW4168, PW4168-1D, PW4168A, PW4168A-1D, and PW4170 model turbofan engines. AD 2021-05-16 required initial and repetitive replacements of the low- pressure turbine (LPT) 4th-stage air sealing ring segment assemblies with parts eligible for installation. AD 2021-05-16 also required initial and repetitive dimensional inspections of the LPT case for bulging and, depending on the results of the dimensional inspections, repair or replacement of the LPT case. This AD was prompted by notification to the FAA of an inadvertent omission in the LPT 4th-stage air sealing ring segment assembly part numbers. This AD requires initial and repetitive replacements of the LPT 4th-stage air sealing ring segment assemblies with parts eligible for installation. This AD also requires initial and repetitive dimensional inspections of the LPT case for bulging and, depending on the results of the dimensional inspections, repair or replacement of the LPT case. The FAA is issuing this AD to address the unsafe condition on these products.
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2012-05-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes. This AD requires a general visual inspection for chamfer of the upper edge of each leaf spring, and rework if necessary. This AD also requires installing a new friction brake nut. This AD was prompted by reports that it was possible to inadvertently move the power levers through the flight idle gate into the beta range due to an un-chamfered leaf spring in the friction brake that may contact the power lever latch when the friction adjusting knob is fully loosened. We are issuing this AD to detect and correct an unsafe condition where both engines can inadvertently be operated in beta mode during flight and consequently reduce controllability of the airplane.
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72-12-03: 72-12-03 HAWKER SIDDELEY AVIATION, LTD.: Amdt. 39-1457 as amended by Amendment 39-1542 is further amended by Amendment 39-1555. Applies to Hawker Siddeley de Havilland Model DH-104 "Dove" airplanes.
Compliance is required on or before February 1, 1973.
To prevent possible failure of the air bottles, P/N B.2994, used in the two main air reservoir assemblies, P/N C.51450, of the pneumatic system, replace the main air reservoir assemblies, P/N C.51450, located in the fuselage nose with serviceable assemblies, P/N SAS.388- 002, or SAS.388-003, containing air bottles P/N BAT.205-001.
(Hawker Siddeley Technical News Sheet, Series: CT(104) No. 223, Issues 1 and 2 dated June 21, 1971, and September 28, 1971, respectively, cover this same subject.)
Amendment 39-1457 became effective July 3, 1972.
Amendment 39-1542 was effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by telegram datedAugust 31, 1972, which contained this amendment.
This Amendment 39-1555 becomes effective November 13, 1972.
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2004-10-01: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, -20, and -20J turbofan engines. This AD clarifies a life limit for certain part numbers of 6th stage low pressure turbine (LPT) air seals, and requires their removal from service before accumulating 15,000 cycles-since-new (CSN). This AD results from reports of certain 6th stage LPT air seals possibly not being life tracked due to confusion from updates to the engine manuals. We are issuing this AD to prevent failure of the 6th stage LPT air seal, which could cause LPT damage resulting in an uncontained engine failure.
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98-18-23: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive high frequency eddy current (HFEC) inspections to detect cracking on all surfaces of the upper recesses in certain latch support fittings of the cargo doorway, and replacement of cracked fittings with new fittings. The existing AD also provides for optional terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by reports indicating that the repetitive inspections required by the existing AD may not detect cracked fittings in a timely manner. The actions specified by this AD are intended to prevent the cargo door from opening while the airplane is in flight, which could result in rapid decompression of the airplane.
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2021-21-12: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A2-20 model turbofan engines. This AD was prompted by flight data obtained from airplanes equipped with certain Rockwell Collins avionics and auto- throttle systems that demonstrated significant oscillation of the engine rotor revolution speed during flight. This AD requires initial and repetitive recalculation of the consumed and remaining service life of certain life-limited parts (LLPs). This AD also requires removal of an LLP prior to its approved life limit or within 90 days after the effective date of this AD, whichever occurs later. The FAA is issuing this AD to address the unsafe condition on these products.
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2021-23-05: The FAA is superseding Airworthiness Directive (AD) 2021-18- 08, which applied to all Airbus SAS Model A319-171N airplanes; Model A320-271N, -272N, and -273N airplanes; and Model A321-271N, -272N, - 271NX, and -272NX airplanes. AD 2021-18-08 required repetitive inspections of the pylon/engine interface rods for damage, and applicable corrective actions, as specified in European Union Aviation Safety Agency (EASA) AD 2021-0177. AD 2021-18-08 also provided for limited installation of affected parts under certain conditions. Since the FAA issued AD 2021-18-08, operators reported that the requirements of EASA AD 2021-0177 were unclear. This AD retains the requirements of AD 2021-18-08, with clarified instructions, as specified in an EASA AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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96-10-09: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, and 500N helicopters. This action requires initial and repetitive inspections of each main rotor blade (blade) root for either cracks or paint and sealant cracking or separation between the lower surface root end fitting and the doubler. This amendment is prompted by one accident in which a blade separated from the helicopter, as well as eight other reports of cracked blades. The actions specified in this AD are intended to prevent failure of a blade resulting in separation of the blade and subsequent loss of control of the helicopter.
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59-25-04: 59-25-04 LOCKHEED: Applies to All Model 188 Series Aircraft - Serial Numbers 1002 Through 1072.
Compliance required as indicated.
Insufficient clearance between the generator feeder wires and the leading edge rib at wing Station 221 together with deflection of the leading edge has resulted in abrasion of the insulation on the generator feeder wires and grounding of the generator feeder.
(a) Inspect for evidence of abrasion not later than the next 8 hours' time in service with a light and mirror through fillet access doors N125 and N126 left and right without lowering the leading edge section. If the inspection shows evidence of abrasion, additional spacers must be installed prior to the next flight to obtain a minimum 0.38-inch clearance with the flange of the leading edge rib. If no evidence of abrasion is present, the inspection must be repeated at intervals of 60 hours' time in service but not to exceed 250 hours' time in service when additional spacers must be installed to provide at least 0.38-inch clearance.
Functionally test the generator differential protection system in accordance with Lockheed Maintenance Manual, Section 24-1-0, page 201.
(b) Within the next 250 hours' time in service inspect all wiring in the leading edge and power plant sections for actual or incipient abrasion of wires. If abrasion of wires or insufficient clearance is found, the conditions are to be corrected prior to the next flight.
(Lockheed Electra Alert Service Bulletin 376 covers this same subject.)
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