Results
99-18-11: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-SHERPA, SD3-60 SHERPA, SD3-30, and SD3-60 series airplanes, that requires replacement of the existing bolts that secure the elevator control torque tube bearing housing retaining plate with hex head bolts. 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 reduced movement of the elevator controls and consequent reduced controllability of the airplane, as a result of bolts coming loose on the elevator control torque tube bearing housing retaining plate.
2014-01-01: We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arrius 2F turboshaft engines. This AD requires a one- time inspection of the ejector assembly nozzle of an affected lubricating device and, if a discrepancy is found, removal and replacement with a part eligible for installation. This AD was prompted by an in-flight shutdown (IFSD) of an Arriel 1 engine. We are issuing this AD to prevent failure of the ejector assembly nozzle, which could lead to an IFSD of the engine, damage to the engine, and damage to the helicopter.
92-27-16: 92-27-16 SABRELINER: Amendment 39-8451. Docket No. 92-NM-229-AD. Applicability: Model NA265, NA265-20, -30, -40, -50, -60, -65, -70, and -80 series airplanes equipped with or converted to electrical driven hydraulic pump (single or double); as listed in Sabreliner Service Bulletin 92-5, dated December 11, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing, which could lead to fire inside the aft section of the fuselage, accomplish the following: (a) Within 30 days or 10 flight hours after the effective date of this AD, whichever occurs first, install redundant hydraulic pump/motor ground circuitry in accordance with Sabreliner Service Bulletin 92-5, dated December 11, 1992. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office (ACO),FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The installation shall be done in accordance with Sabreliner Service Bulletin 92-5, dated December 11, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Sabreliner Corporation, 18118 Chesterfield Airport Road, Chesterfield, Missouri 63005-1121. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on January 13, 1993.
2013-26-10: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-524G2-19, RB211-524G3-19, RB211-524H-36, and RB211-524H2-19 turbofan engines. This AD requires a one-time reduction in the cyclic life of certain high-pressure (HP) compressor rotor stage 1 and stage 2 discs, and removal of discs that exceed the reduced cycle life. This AD was prompted by a review by RR of the cyclic life of life-limited parts (LLPs) for RB211-524 series engines. We are issuing this AD to prevent the failure of certain LLPs, which could result in uncontained engine damage and damage to the airplane.
99-18-14: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) Model 172R airplanes equipped with a certain modification kit that reduces friction in the elevator control system. This AD requires inspecting the control yoke pivot bolt to assure positive clearance between the pivot bolt s threaded end and aileron direct cable. If positive clearance is not found, this AD requires replacing the control yoke pivot bolt, inspecting the adjacent aileron control cables for damage, and replacing any damaged aileron control cable. This AD is the result of the manufacturer supplying incorrect length control yoke pivot bolts in Cessna Modification Kits MK 172-27-01 that were shipped from September 21, 1998, through April 18, 1999. The actions specified by this AD are intended to prevent failure of an aileron control cable because of an incorrect length control yoke pivot bolt rubbing on one of these cables, which could result in loss of aileron control with loss of directional control of the airplane.
99-18-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires installation of strap assemblies on the ceiling panels and rails that support the video monitors. This amendment is prompted by reports of the video monitor ceiling panels falling into the cabin area due to the failure of certain latch assemblies during turbulence. The actions specified by this AD are intended to prevent ceiling panels from falling into the passenger area in the event of failure of certain latch assemblies on the ceiling panels, which could result in consequent injury to the crew and passengers.
93-15-12: 93-15-12 SAAB-SCANIA: Amendment 39-8657. Docket 93-NM-16-AD. Supersedes AD 92-03-08, Amendment 39-8163, which superseded AD 91-07-02, Amendment 39-6932. Applicability: Model SF340A series airplanes, serial numbers 004 through 159, inclusive; and SAAB 340B series airplanes, serial numbers 160 and subsequent; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To ensure proper operation of the main landing gear (MLG) and the nose landing gear (NLG), accomplish the following: (a) Remove the MLG and NLG components identified in the attachments (listed below) to SAAB Service Bulletin SAAB 340-32-066, Revision 1, dated October 17, 1990, and replace them with serviceable components prior to the accumulation of the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List," or within 60 days after April 15, 1991 (the effective date of AD 91-07-02, Amendment 39-6932), whicheveroccurs later. Thereafter, replace these components with serviceable components at intervals not to exceed the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List. " SAAB SERVICE BULLETIN SAAB 340-32-066 ATTACHMENTS AP PRECISION HYDRAULICS SERVICE BULLETIN NUMBER DATE ISSUED ATTACHMENT NUMBER AIR83530-32-07 January 1990 1 AIR83570-32-04 January 1990 2 AIR83572-32-01 January 1990 3 AIR84306-32-07 January 1990 4 AIR84350-32-01 January 1990 5 AIR83022-32-18 REV 1 August 1990 6 (b) Remove the MLG and NLG components identified in the attachments (listed below) to SAAB Service Bulletin SAAB 340-32-066, Revision 1, dated October 17, 1990, and replace them with serviceable components prior to the accumulation of the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List," or within 60 days after March 16, 1992 (the effective date of AD 92-03-08, Amendment 39-8163), whichever occurs later. Thereafter, replace these components with serviceable components at intervals not to exceed the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List. " SAAB SERVICE BULLETIN SAAB 340-32-066 ATTACHMENTS AP PRECISION HYDRAULICS SERVICE BULLETIN NUMBER DATE ISSUED ATTACHMENT NUMBER AIR83064-32-02 January 1990 7 AIR84310-32-07 January 1990 8 (c) Remove the MLG and NLG components identified in the attachments (listed below) to SAAB Service Bulletin SAAB 340-32-066, Revision 2, dated June 12, 1992, and replace them with serviceable components prior to the accumulation of the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List," or within 60 days after the effective date of this AD, whichever occurs later. Thereafter, replace these components with serviceable components at intervals not to exceed the number of landings listed in the "Fatigue Life Flights" column of the applicable "Life Limited Parts List. " SAAB SERVICE BULLETIN SAAB 340-32-066 ATTACHMENTS AP PRECISION HYDRAULICS SERVICE BULLETIN NUMBER DATE ISSUED ATTACHMENT NUMBER AIR83530-32-07 REV 1 January 1992 1 AIR83570-32-04 REV 1 January 1992 2 AIR83572-32-01 REV 1 January 1992 3 AIR84306-32-07 REV 1 January 1992 4 AIR84350-32-01 REV 1 January 1992 5 AIR83022-32-18 REV 2 January 1992 6 AIR83064-32-02 REV 1 January 1992 7 AIR84310-32-07 REV 1 January 1992 8 AIR83608-32-01 January 1992 9 (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The modifications shall be done in accordance with SAAB Service Bulletin SAAB 340-32-066, Revision 2, dated June 12, 1992, and SAAB Service Bulletin SAAB 340-32-066, Revision 1, dated October 17, 1990. Revision 2 of SAAB Service Bulletin SAAB 340-32-066 contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page Title Page, 1 2 June 12, 1992 ATTACHMENT 1 1 1 January 1992 2-3 Original January 1990 ATTACHMENT 2 1-2 1 January 1992 ATTACHMENT 3 1 1 January 1992 2 Original June 1990 ATTACHMENT 4 1-2 1 January 1992 ATTACHMENT 51-2 1 January 1992 ATTACHMENT 6 1, 3 2 January 1992 2, 4 Original January 1990 ATTACHMENT 7 1, 3 1 January 1992 2 Original January 1990 ATTACHMENT 8 1 1 January 1992 2-3 Original January 1990 ATTACHMENT 9 1-2 Original January 1992 The incorporation by reference of SAAB Service Bulletin SAAB 340-32-066, Revision 2, dated June 12, 1992, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of SAAB Service Bulletin SAAB 340-32-066, Revision 1, dated October 17, 1990, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of March 16, 1992 (57 FR 5376, February 14, 1992). Copies may be obtained from SAAB-SCANIA AB, SAAB Aircraft Product Support, S-581.88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; orat the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on September 17, 1993.
2021-03-15: The FAA is superseding Airworthiness Directive (AD) 2020-13-02 for Leonardo S.p.A. (Leonardo) Model A119 and AW119 MKII helicopters. AD 2020-13-02 required inspecting for movement and the tightening torque of the tail rotor (T/R) plug, the installation of the outboard and inboard faces of the T/R duplex bearing, and the condition of the T/R duplex bearing, T/R plug threads, and nut threads. Depending on the inspection results, AD 2020-13-02 required corrective actions and reporting information. This new AD retains the requirements of AD 2020- 13-02 except the reporting requirement, updates the service information, and requires repeating the inspection. This AD was prompted by Leonardo's update to the service information. The actions of this AD are intended to address an unsafe condition on these products.
99-18-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes. This action requires repetitive inspections and tests of the thrust reverser control and indication system on each engine, and corrective actions, if necessary; installation of a terminating modification; and repetitive operational checks of that installation, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in significant reduction in airplane controllability. The actions specified in this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane.
89-02-05: 89-02-05 BF GOODRICH (SARGENT INDUSTRIES, PICO DIVISION): Amendment 39-6106. Applicability: BF Goodrich (or former company name Sargent Industries, PICO Division) 7-man liferaft, P/N 100102-( ). This liferaft is approved under Technical Standard Order C70. NOTE: These liferafts would most likely be used in helicopters or transport category airplanes. Compliance: Required within 90 days after the effective date of this AD, unless previously accomplished. To eliminate cylinders which may leak due to certain material used in their fabrication, accomplish the following: A. Inspect the liferafts to determine the cylinder part number (P/N). If the liferaft contains a P/N 630104-205 cylinder with a serial number listed in BF Goodrich Alert Bulletin No. 130101-25A-203, dated March 29, 1988, the cylinder must be replaced prior to further flight, in accordance with that service bulletin. NOTE: The BF Goodrich service bulletin lists the raft P/N and S/N on which the cylinders were originally installed. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to BF Goodrich Aircraft Evacuation Systems, 3414 South Fifth Street, Phoenix, Arizona 85040. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. This amendment (39-6106, AD 89-02-05) becomes effective February 13, 1989.
2013-25-04: We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. This AD was prompted by reports of failures of the emergency slide on the forward passenger door, which prevented the door from opening. This AD requires repetitive re-packing of certain forward door escape slides. We are issuing this AD to prevent failure of the emergency slide, which can prevent the forward passenger door from opening, and which could result in impeded emergency evacuation and possible subsequent injury to passengers and flightcrew.
99-18-08: This amendment adopts a new airworthiness directive (AD), applicable to all IAI Model 1124 and 1124A series airplanes, that requires installation of an independent circuit breaker and associated wiring changes for the hydraulic low pressure warning lights. 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 loss of the hydraulic low pressure warning lights. Low pressure in the hydraulic system can result in reduced controllability of the airplane.
87-04-23: 87-04-23 DeHAVILLAND: Amendment 39-5548. Applies to Model DHC-6-1, DHC-6- 100, DHC-6-200, and DHC-6-300 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, after the effective date of this AD, unless already accomplished. To prevent failure of the wing support struts due to corrosion, accomplish the following: (a) Visually inspect each wing support strut for corrosion in accordance with the "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland Service Bulletin (S/B) No. 6/474, dated June 14, 1985, Revision A, dated March 28, 1986, as follows: (1) For aircraft that have accumulated 5,000 or more hours time-in-service (TIS) or are four and one half or more years old on the effective date of this AD, accomplish the inspection within the next 1,000 hours TIS or six months, whichever occurs first, after the effective date of this AD. (2) For aircraft that have accumulated less than 5,000 hours TIS and are less than four andone half years old on the effective date of this AD, accomplish the inspection before the accumulation of 6,000 hours TIS or five years, whichever occurs first. (3) For all airplanes, reinspect at intervals not to exceed 6,000 hours TIS or five years, whichever occurs first, following the previous inspection accomplished in accordance with this AD. (b) If the inspections specified in paragraph (a) of this AD show moderate or severe corrosion anywhere on the wing support struts, or any corrosion within 20 inches from either end of the wing support struts, replace the affected support strut prior to further flight. (c) If the inspections specified in paragraph (a) of this AD show light corrosion in areas other than 20 inches from either end of the struts, remove the corrosion within 30 days. NOTE: Advisory Circular (AC) 43-4, discusses corrosion evaluation, degree of damage, and rework procedures. (d) An alternate method of compliance, which provides an equivalent level of safety, may be used if approved by the Manager, New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York 11581. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) Upon submission of substantiating data by an owner or operator, through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA, New England Region, may adjust the compliance times in this AD. All persons affected by this directive may obtain copies of the document referred to herein upon request to The DeHavilland Aircraft Company of Canada, A Division of Boeing of Canada, Ltd., Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on March 16, 1987.
99-18-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and ATR42-320 series airplanes, that requires a one-time inspection for cracking of a fastener hole located on the lower surface of the outer wing, and repair, if necessary; and cold working of the hole and installation of a new fastener in the hole. 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 fatigue damage on the outer wing and consequent reduced structural integrity of the wing.
96-09-23: 96-09-23 DORNIER: Amendment 39-9599. Docket 96-NM-18-AD. Applicability: All Model Dornier 328-100 series airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions, accomplish the following: (a) Within 30 days after the effective date of this AD, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD. NOTE 2: Operators must initiate action to notify and ensure that flight crewmembers are apprised of this change. (1) Revise the FAA-approved Airplane Flight Manual (AFM) by incorporating the following into the Limitations Section of the AFM. This may be accomplished by inserting a copy of this AD in the AFM. "WARNING Severe icing may result from environmental conditions outside of those for which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protectionsystem, or may result in ice forming aft of the protected surfaces. This ice may not be shed using the ice protection systems, and may seriously degrade the performance and controllability of the airplane. o During flight, severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues. If one or more of these visual cues exists, immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions. - Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice. - Accumulation of ice on the lower surface of the wing aft of the protected area. - Accumulation of ice on the propeller spinner farther aft than normally observed. o Since the autopilot may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when any of the visual cues specified above exist, or when unusual lateral trim requirements or autopilot trim warnings are encountered while the airplane is in icing conditions. o All icing detection lights must be operative prior to flight into icing conditions at night. [NOTE: This supersedes any relief provided by the Master Minimum Equipment List (MMEL).]" (2) Revise the FAA-approved AFM by incorporating the following into the Procedures Section of the AFM. This may be accomplished by inserting a copy of this AD in the AFM. "THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN-FLIGHT ICING: o Visible rain at temperatures below 0 degrees Celsius ambient air temperature. o Droplets that splash or splatter on impact at temperatures below 0 degrees Celsius ambient air temperature. PROCEDURES FOR EXITING THE SEVERE ICING ENVIRONMENT: These procedures are applicable to all flight phases from takeoff to landing. Monitor the ambient air temperature. While severe icing may form at temperatures as cold as -18 degrees Celsius, increased vigilance is warranted at temperatures around freezing with visible moisture present. If the visual cues specified in the Limitations Section of the AFM for identifying severe icing conditions are observed, accomplish the following: o Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the airplane has been certificated. o Avoid abrupt and excessive maneuvering that may exacerbate control difficulties. o Do not engage the autopilot. o If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. o If an unusual roll response or uncommanded roll control movement is observed, reduce the angle-of-attack.o Do not extend flaps during extended operation in icing conditions. Operation with flaps extended can result in a reduced wing angle-of-attack, with the possibility of ice forming on the upper surface further aft on the wing than normal, possibly aft of the protected area. o If the flaps are extended, do not retract them until the airframe is clear of ice. o Report these weather conditions to Air Traffic Control." (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Operations Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtainedfrom the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) This amendment becomes effective on June 11, 1996.
99-18-10: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-SHERPA, SD3-60 SHERPA, SD3-30, and SD3-60 series airplanes, that requires a one-time detailed visual inspection of the emergency brake accumulator mounting structure for evidence of cracking; and corrective action, if necessary. 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 failure of the mounting angle that supports the emergency brake system due to cracking, which could result in loss of the emergency brake system.
76-11-02: 76-11-02 MORANE SAULNIER (SOCATA): Amendment 39-2619. Applies to Model MS880B, MS892A-150 and E-150, MS893A and E, and MS894A and E airplanes, serial numbers 831 and above, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent the possible loss of an engine cowling due to improper latching of locks and cowl lock wear, accomplish the following: (a) For airplanes incorporating Socata-type engine cowl locks, within the next 10 hours time in service after the effective date of this AD, either incorporate the following cowl locking procedures in the Airplane Flight Manual immediately following Section 4.3.1, Step 3; or if an Airplane Flight Manual is not available, install a placard adjacent to one of the engine cowl locks which contains the following cowl locking procedures: Cowl Locking Procedures. (1) Raise latch locking lever to maximum travel to allow cowl upper catch to engage lower cowl catch. (2) Press latch locking lever to full down position until distinct snap is heard indicating completed locking. (3) Check the locking mechanism by pulling the lock latching lever with a force sufficient to overcome the weight of the lever and low friction forces. (b) For airplanes incorporating Socata-type engine cowl locks, within the next 25 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours time in service from the last inspection - (1) Visually inspect the engine lower cowling metal centering tabs and the upper cowling centering pins, for wear of the metal tab receiving holes and wear of the centering pins to assure proper mating of the upper and lower cowling. Replace the metal centering tabs and cowling centering pins, found to be worn; and (2) Inspect the engine cowling locking mechanism and if deterioration in locking push force is evident as demonstrated by a lack of snap action on the latch locking lever, adjustthe Socata type engine cowl lock by removing the cotter pin in the upper catch, threading the latch trunnion into the upper catch a distance of one or more turns, and reinserting the cotter pin in accordance with the procedure described in paragraphs 1.2 and 3.1 of Socata Service Bulletin No. 107 Gr. 71-06, dated November 1972, or an FAA-approved equivalent. (c) For MS880B airplanes, serial numbers 831 through 1604, equipped with Dialatch engine cowl locks - (1) Within the next 50 hours time in service after the effective date of this AD, accomplish the following in accordance with Socata Service Bulletin No. 77/2, Gr. 71-03, dated May 1973, or an FAA-approved equivalent: (i) Replace the Dialatch cowl locks with Socata-type engine cowl locks. (ii) Install reinforcing angle plates on the engine cowl centering pin brackets. (iii) Install engine cowl stops; (2) Within the next 50 hours time in service after the effective date of this AD, revise the Airplane FlightManual, or install a placard, as specified in paragraph (a) of this AD; and (3) Within the next 100 hours time in service after installation of the Socata type engine cowl lock in accordance with paragraph (c)(1)(i) of this AD and thereafter at intervals not to exceed 100 hours time in service from the last inspection, visually inspect the engine lower cowling metal centering tabs and the upper cowling centering pins, for wear of the metal tab receiving holes and wear of the centering pins to assure proper mating of the upper and lower cowling. Replace the metal centering tabs and cowling centering pins found to be worn. This amendment becomes effective on June 7, 1976.
99-01-05 R1: We are revising Airworthiness Directive (AD) 99-01-05 for certain aircraft equipped with wing lift struts. AD 99-01-05 required repetitively inspecting the wing lift struts for corrosion; repetitively inspecting the wing lift strut forks for cracks; replacing any corroded wing lift strut; replacing any cracked wing lift strut fork; and repetitively replacing the wing lift strut forks at a specified time for certain airplanes. AD 99-01-05 also required incorporating a "NO STEP" placard on the wing lift strut. Since we issued AD 99-01-05, we were informed that paragraph (c) had been misinterpreted and caused confusion. This AD clarifies the intent of the language in paragraph (c) of AD 99-01-05 and retains all other requirements of AD 99-01-05. We are issuing this AD to correct the unsafe condition on these products.
99-18-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3-30 series airplanes, that requires modification of electrical wiring associated with heater components. 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 failure of the autofeather system, which could result in reduced controllability of the airplane in the event of engine failure during takeoff.
99-18-05: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires repetitive inspections to detect cracks in the forward flange of the vertical beam of the aft pressure bulkhead at certain buttock lines, and installation of a splice repair, if necessary. The amendment also requires installation of a preventative modification on the vertical beam of the door frame in certain cases. This amendment is prompted by reports of fatigue cracks found in the vertical beam web and forward flange of the aft pressure bulkhead. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in the inability of the subject vertical beam to withstand the fail-safe loads, and consequent loss of cabin pressurization.
2022-15-08: The FAA is superseding Airworthiness Directive (AD) 2019-20- 03, which applied to various transport airplanes. AD 2019-20-03 required modification of certain universal serial bus (USB) receptacles located in the flight deck. Since the FAA issued AD 2019-20-03, it has been determined that additional airplanes are affected by the unsafe condition. This AD continues to require the modification and expands the applicability, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2022-13-02: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of the failure of certain primary ejector fuel feed flexible hoses, which may have a thinner liner than specified by design requirements, and are therefore more susceptible to cracking. This AD requires replacing the hoses. The FAA is issuing this AD to address the unsafe condition on these products.
2013-25-12: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-10, DC-9-30, and DC-9-40 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead web area is subject to widespread fatigue damage (WFD). This AD requires modifying the aft pressure bulkhead. The modification includes inspecting for cracks around the rivet holes, and repair of any cracking. We are issuing this AD to prevent fatigue cracking of the aft pressure bulkhead, which could result in reduced structural integrity of the airplane.
99-18-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-700 and -800 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to prohibit operation of the airplane under certain conditions; repetitive inspections of the tab mast fitting of the elevator tab assemblies to detect cracking; an elevator tab freeplay check; and corrective actions, if necessary. That AD also provides for optional terminating action for certain repetitive inspections, and requires installing an additional fastener on the elevator tab mast fitting, which terminates the AFM revision and extends certain repetitive inspection intervals. This amendment continues to require certain actions, and revises and adds certain other requirements. This amendment is prompted by a report of a severe vibration incident on a Boeing Model 737-800 series airplane; inspection revealed fracturing of the elevator tab mast fitting and excessive freeplay in the elevator tab. The actions specified in this AD are intended to prevent loss of controllability of the airplane due to excessive freeplay in the elevator tab or a free tab.
80-25-06 R1: 80-25-06 R1 TELEDYNE CONTINENTAL MOTORS: Amendment 39-3984 as amended by Amendment 39-4061. Applies to Models GTSIO-520-L, serial numbers 608324 through 608627; GTSIO-520-M, serial numbers 606619 through 606890; and GTSIO-520-N, serial numbers 610001 through 610107, engines with 100 hours or less total time in service on the effective date of this AD, installed on but not limited to certain Cessna Models 404 and 421C airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent engine failure due to loss of engine oil pressure, damage due to contaminated oil, and propeller shaft damage resulting from a malfunctioning thrust washer accomplish the following: (a) Before each flight and immediately after each flight until the accumulation of 100 hours total time in service, perform a special oil pressure check to determine the oil pressure with engine power at the same level as the magneto check. If oil pressure fluctuatesor is less than 30 psi, accomplish paragraphs (b)(1) and (b)(2) before further flight. This oil pressure check may be accomplished by the pilot as provided in FAR 43.3(h). (b) Prior to the next flight and at each oil change until the accumulation of 100 hours total time in service: (1) Remove the oil filter, disassemble the canister, and inspect the paper element between the pleats to determine the quantity of metallic material visually and by using a clean magnet. If total metallic contaminants are in excess of the quantity necessary to cover a 1/4 inch diameter surface, before further flight take the necessary maintenance action to replace those parts that are malfunctioning. NOTE: Exercise caution to prevent contamination of the filter element during disassembly. (2) Inspect to determine the end clearance (shaft end play) of the propeller drive shaft with engine at ambient temperature. If axial movement is in excess of .020 inch, before further flight take necessarymaintenance action to replace those parts that are malfunctioning. (c) Prior to the next flight, inspect the engine and airplane records and change oil if necessary to ensure that SAE No. 50 oil is installed for ambient temperatures above 40 degrees F or SAE No. 30 oil is installed for ambient temperatures below 40 degrees F. (d) Upon or before the accumulation of 25 hours, 50 hours and 100 hours total time in service, change oil and oil filter. Do not use multiviscosity oils within the first 100 hours time in service. (e) Make appropriate maintenance record entry when accomplishing each requirement of this AD. The airplanes equipped with affected engines may be flown in accordance with FAR 21.197 to a location where the AD compliance procedures can be accomplished. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. NOTE: Continental Motors Service Bulletin NO. M80-30, dated December 10, 1980, pertains to this subject. Amendment 39-3984 became effective December 5, 1980. This amendment 39-4061 becomes effective March 23, 1981.