Results
98-12-24: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 series airplanes. This action requires a one-time inspection to detect cracked or broken links of the aft engine mounts, and replacement of any cracked or broken link with a serviceable link. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking of the links of the aft engine mounts, which could result in failure of the aft engine attachment and consequent separation of the engine from the airplane.
2023-06-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-202, -203, -223, and -243 airplanes; Model A330- 200 Freighter series airplanes; Model A330-300 series airplanes; Model A340-200 series airplanes; and Model A340-300 series airplanes. This AD was prompted by a report that damage was found to the firewall and fuselage skin in the auxiliary power unit (APU) compartment area on Model A330 airplanes. This AD requires replacing affected tee ducts with serviceable parts, 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.
2025-09-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes, Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by cracks being found during full-scale fatigue testing of the keel beam bottom panel between the edge profile and stringer run-out at a certain frame and stringer. This AD requires repetitive special detailed inspections (SDI) of the affected area, and corrective actions, if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
96-08-07: 96-08-07 AIRBUS INDUSTRIE: Amendment 39-9573. Docket 95-NM-137-AD. Supersedes AD 94-21-07, Amendment 39-9049. Applicability: All Model A310 and A300-600 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 (d) 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 prevent an out-of-trim condition between the trimmable horizontal stabilizer and the elevator, which may severely reduce controllability of the airplane, accomplish the following: (a) Within 10 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the information contained in paragraph (a)(1) or (a)(2) of this AD, as applicable. This may be accomplished by inserting a copy of this AD in the AFM. The AFM limitation required by AD 94-21-07, amendment 39- 9049, may be removed following accomplishment of the requirements of this paragraph. (1) For airplanes on which the flight control computers (FCC) have not been modified in accordance with the requirements of paragraph (b) of this AD: "Overriding the autopilot (AP) in pitch axis does not cancel the AP autotrim when LAND TRACK mode [green LAND on both Flight Mode Annunciators (FMA)] or GO-AROUND mode is engaged.In these modes, if the pilot counteracts the AP, the autotrim will trim against pilot input. This could lead to a severe out-of- trim situation in a critical phase of flight." (2) For airplanes on which the FCC's have been modified in accordance with requirements of paragraph (b) of this AD. "Overriding the autopilot (AP) in pitch axis does not cancel the AP autotrim when LAND TRACK mode (green LAND on both FMA's) is engaged, or GO- AROUND mode is engaged below 400 feet radio altitude (RA). In these modes, if the pilot counteracts the AP, the autotrim will trim against pilot input. This could lead to a severe out-of-trim situation in a critical phase of flight." (b) For airplanes equipped with FCC's having either part number (P/N) B470ABM1 (for Model A310 series airplanes) or B470AAM1 (for Model A300-600 series airplanes): Within 60 days after November 2, 1994 (the effective date of AD 94-21-07, amendment 39-9049), modify the FCC's in accordance with Airbus Service Bulletin A310-22-2036, dated December 14, 1993 (for Model A310 series airplanes), or Airbus Service Bulletin A300-22-6021, Revision 1, dated December 24, 1993 (for Model A300-600 series airplanes), as applicable. NOTE 2: Paragraph (b) of this AD merely restates the requirements of paragraph (b) of AD 94-21-07, amendment 39-9049. As allowed by the phrase, "unless accomplished previously," specified in the compliance statement of this AD, if those requirements of AD 94- 21-07 have already been accomplished, this AD does not require that those actions be repeated. (c) As of November 2, 1994 (the effective date of AD 94-21-07, amendment 39-9049), no person shall install an FCC having either P/N B470ABM1 or B470AAM1 on any airplane. (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 3: 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 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. (f) The modification shall be done in accordance with Airbus Service Bulletin A310-22-2036, dated December 14, 1993, or Airbus Service Bulletin A300-22-6021, Revision 1, dated December 24, 1993, as applicable. The incorporation by reference of these documents 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 November 2,1994 (59 FR 52414, October 18, 1994). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 23, 1996.
2002-07-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) P206, TP206, TU206, U206, 207, T207, 210, P210, and T210 series airplanes. This AD requires you to visually inspect certain horizontal stabilizer attachment reinforcement brackets for the existence of seam welds and replace any reinforcement bracket found without seam welds. This AD authorizes the pilot to check the logbooks to determine whether one of the affected horizontal stabilizer attachment reinforcement brackets is installed. This AD is the result of a report that certain parts were manufactured without seam welds. The actions specified by this AD are intended to detect and replace structurally deficient horizontal stabilizer attachment brackets. Continued use of such brackets could result in structural failure of the horizontal stabilizer with reduced or loss of control of the airplane.
2023-06-01: The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. This AD was prompted by in-service experience that has shown that the lateral flight guidance of the flight director/ auto pilot may not limit HI BANK turns in severe icing conditions. This AD requires the replacement of the affected new avionics suite (NAS), as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of the affected NAS on any airplane. The FAA is issuing this AD to address the unsafe condition on these products.
2025-08-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A321-251NX, -252NX, -253NX, -271NX, and -272NX airplanes. This AD was prompted by discovery of two bushes that had migrated on the latch shaft of an emergency overwing exit door (OWED) during accomplishment of an inspection on an in-service airplane. This AD requires repetitive detailed inspections (DETs) of the affected parts and, in case of discrepancies, modification of the affected parts, and prohibits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
74-10-01: 74-10-01 PIPER: Amendment 39-1830 as amended by Amendment 39-2480. Applies to model PA-23-250, Aircraft Serial Numbers 27-3050, 27-3154 to 27-7405330, certificated in all categories. Unless already accomplished within the last 75 hours in service, to prevent possible asymmetric flap conditions attributed to cracks developing in the outboard flap hinge, the following must be performed within the next 25 hours in service after the effective date of this airworthiness directive, and every 100 hours thereafter: 1. Using the hydraulic hand pump, lower the flaps to full-down position. 2. Clean outboard hinges, part numbers 17103-04 (left) and 17103-05 (right). Using a 10-power magnifying glass, inspect these parts (outboard flap hinges) for cracks. An equivalent inspection method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may be used. 3. If cracks are found, replace, before further flight, any cracked part with unused hinges,part number 17103-04 (left) and/or 17103-05 (right) or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Compliance with this AD is not required upon incorporation of Piper Kits 760 861 (right flap) and 760 817 (left flap) or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Service Bulletin 408B pertains to the same subject. Amendment 39-1830 was effective May 7, 1974. This amendment 39-2480 is effective December 31, 1975.
79-01-02 R2: 79-01-02 R2 BEECH: Amendment 39-3385 as amended by Amendment 39-3491 is further amended by Amendment 39-3914. Applies to: (1) Models E50, F50, G50, H50, J50, 65, A65, A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, and 70 airplanes except those airplanes modified in accordance with STC SA444SW or STC SA587SW, and (2) those Models C50, D50, D50A, D50B, D50C and D50E airplanes modified per STC SA76SW. COMPLIANCE: Required as indicated unless already accomplished. To prevent or reduce the possibility of in-flight fires in the engine compartment, wing, nacelle and main landing gear wheel well accomplish the following: A. MODIFICATIONS OR PARTS REPLACEMENT. Within 100 hours time-in-service after December 12, 1977, or the last inspection per AD 77-25-01, on all applicable airplanes except those exempted below: 1. Unless previously accomplished per AD 72-18-07 on Models 65 (S/Ns L-1, L-2, L-6, LF-7, LF-8 and LC-1 thru LC-239) A65 and A65-8200 (S/Ns LC-240 thru LC-335); 70 (S/Ns LB-1 thru LB-35) 65-80, 65-A80, 65-A80-8800, and 65-B80 (S/Ns LD-1 thru LD-456) and 65-88 (S/Ns LP-1 thru LP-47) airplanes. a. Install Beech Part No. 131072 Flight Manual Supplement in the Airplane Flight Manual. b. Install Beech P/N 50-910615-3 decal or a locally fabricated placard using 3/32" high letters on the overhead or instrument panel which reads as follows: EMERGENCY ENGINE SHUTDOWN PROCEDURES 1. MIXTURE CONT-IDLE CUT-OFF 2. FUEL SELECTOR-OFF 3. OIL SHUT-OFF HDL-UP AND LKD 4. PROP CONTROL-FEATHERED 5. THROTTLE-FULLY OPEN 6. BOTH BOOST PUMPS-OFF 7. MAGNETO SWITCH-OFF 8. ALTNTR/GEN SWITCH OFF 2. Unless previously accomplished per AD 73-23-04 on Models 65 (S/Ns L-1, L-2, L6, LF-7 and up and LC-1 thru LC-239), A65 and A65-8200 (S/Ns LC240 through LC-335) 65-80 (S/Ns LD-1 thru LD-150 (except LD-34 and LD-46)); 65A80 and 65-A80-8800 (S/Ns LD-34, LD-46, LD-151thru LD-269); 65-B80 (S/Ns LD-270 thru LD-475); 70 (S/Ns LB-1 and up) E50 (S/Ns EH-1 thru EH-70); F50 (S/Ns FH-71 thru FH-96 (except FH-94)) G50 (S/Ns GH-94, GH-97 thru GH-119); H50 (S/Ns HH-120 thru HH-149); J50 (S/Ns JH-150 and up) airplanes, except those modified per STCs SA444SW, SA76SW or SA587SW install Beech Nacelle Interior Fire Seal Kit No. 65-9008-1. 3. Unless previously accomplished per AD 73-23-04 on Models 65-88 (S/Ns LP-1 and up (except LP-27 and LP-29)) airplanes, except those modified per STCs SA444SW, SA76SW or SA587SW install Beech Nacelle Interior Fire Seal Kit No. 65-9008-3. 4. Unless previously accomplished per AD 75-25-04 on Model 65-B80 (S/Ns LD-476 thru 502 and LD-504) airplanes, visually inspect the nacelle interior fire shield installation for the proper installation of the P/N 50-980109-5 and -7 shields in accordance with Beechcraft Service Instruction No. 0771-065 or later revision and correct as necessary in accordance with the above service instruction. 5. Unless previously accomplished per AD 76-13-03 on Model 65-88 (S/Ns LP-1 thru LP-26, LP-28 and LP-30 thru LP-47) airplanes, visually inspect the LH and RH nacelle fire shield installation in accordance with Beechcraft Service Instructions 0809-065 or later approved revision for installation of the small P/N 50-980109-5 shield above the second stage augmenter tube on the inboard side of both nacelles. If not present install this part in accordance with the above Instruction. B. INSPECTIONS 1. Within 25 hours time-in-service after December 12, 1977, or 100 hours time-in-service after the last inspection per AD 77-25-01 and each 100 hours time-in-service thereafter, except as noted in paragraph B.2., accomplish the following: a. Engine Compartment Inspection Open the cowl doors and visually inspect engine and powerplant components forward of the firewall as indicated. i) Drain plugs, filters and strainers for security, leakage and dirt accumulation. ii) Engine cylinders for cracks, abnormal leakage and security of hold down nuts. NOTE: Minor oil seepage stains at engine parting lines, rocker box covers, and push rod housings are acceptable. iii) Engine carburetion and induction system for security of attachment, evidence of leakage, deterioration and damage such as stains, chafing, cuts, bulges and cracks. iv) Fuel and oil lines and their fittings for security as evidenced by torque paint or putty, and evidence of deterioration such as stiffness, stains, cracks, chafing, and leakage. NOTE: Fire sleeves need not be removed for this inspection. v) Exhaust system stacks and primary augmenters for security of attachment, integrity of supports, cracks, bulges and alignment. vi) Drains for deterioration and blockage. vii) Cowl and firewall for fuel and oil stains and indications of source of these stains. viii) Firewall for missing or deteriorated grommets and open holes. b. Nacelle and wheel well inspection: Remove augmenter covers, open or remove access doors and inspection covers, canvas covers over fuel selectors (if installed), invertor access covers (if installed), and cover over the hydraulic driven cabin pressurization compressor (Model 65-88) and visually inspect the following components in the engine nacelles as indicated: i) All flammable fluid lines and drain lines for deterioration, chafing against other components, other damage and fitting security. ii) Oil tank installation including supply, return and vent lines for evidence of deterioration, leakage or damage. iii) Fuel selector valve and hydraulic cabin pressurization system reservoir for evidence of damage, leakage and security of line fittings and mounting. c. Fuel System Leakage Inspection: On airplanes having engines with Bendix fuel injection system disconnect and cap the hose at the fuel injectionnozzle at the top of the induction housing, select main tanks, turn main boost pump ON, place mixture control in rich position and check all fuel carrying lines and fittings in the engine compartment and wheel well for leakage. Correct leaks detected and recheck prior to installing hose on nozzle fitting. On other airplanes, with mixture control in "cut off" select main tanks, turn main boost pump ON and check all fuel carrying lines and fittings in the engine compartment and wheel well for leakage. Correct leaks detected and recheck. d. Wing Inspection: i) Visually inspect the wings for fuel stains or wetness of the lower wing skin from fuel cell leakage. ii) Remove leading edge between nacelle and fuselage and visually inspect flexible and solid flammable fluid line and electrical bundles for adequate separation. 2. Within 100 hours time-in-service since last inspection per AD 77-25-01 and each 500 hours time-in-service thereafter, on Models 65 (SerialNumber LC-163 thru LC-324); 65-80 (Serial Numbers LD-1 thru LD-150) and 65-A80 (Serial Numbers LD-151 thru LD-269, except LD-263) a. Remove the inboard secondary augmenter and visually inspect fuel flow indicator hoses on aft side of firewall above augmenters for evidence of deterioration or chafing, tightness of fittings and line security. 3. After completion of above inspections, correct all unsatisfactory or unairworthy conditions noted and reinstall or close all door panels or access plates removed for the inspections. C. ENGINE RUN UP AND FUEL SYSTEM FUNCTIONAL CHECK. 1. After completion of inspections required by Section B, start and warm up engines using normal procedures. Check functioning of fuel injector or carburetor idle cutoff by moving mixture controls to "idle cutoff" position and observing RPM and fuel pressure, or flow indications as appropriate, for drop. When drop is observed move mixture control back to full rich position and check for proper fuel tank selector valve operation by placing selector in "OFF" position and observe engine RPM and fuel pressure or flow indications, as appropriate, for drop. After stopping engines, open cowls and visually inspect engine compartments and nacelles for fuel or oil leakage and correct as necessary before returning airplane to service. D. The interval for the repetitive inspection and checks set forth in Paragraphs A, B and C of this AD may be extended by 10 hours up to a maximum of 110 hours time-in-service to allow compliance at previously scheduled maintenance periods. E. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beech Service Bulletins No. 66-24 or later revisions, Beech Service Bulletin No. 67-8 or later revisions, Beechcraft Service Instruction 0509-016 or later revision, Beechcraft Service Instruction No. 0771-065 or later revision, and Beechcraft Service Instructions 0809-065 or later revision pertain to this subject. This AD supersedes the following: AD 72-18-07, Amendment 39-1512 (37 FR 18030); AD 72-18-08, Amendment 39-1513 (37 FR 18030 and 18031) as amended by Amendment 39-3152 (43 FR 9593 and 9594); AD 73-23-04, Amendment 39-1740 (38 FR 30867), as amended by Amendment 39-1771 (39 FR 2469) and 39-1813 (39 FR 13072 and 13073); AD 75-25-04, Amendment 39-2449 (40 FR 56883); AD 76-13-03, Amendment 39-2690 (41 FR 25997); and 77-25-01, Amendment 39-3092 (42 FR 61993-61995). Amendment 39-3385 became effective January 8, 1979. Amendment 39-3491 became effective on June 4, 1979. This Amendment 39-3914 becomes effective on September 22, 1980.
2002-06-11: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires replacement of the existing strake feed-thru and internal electrical connectors with new, moisture-resistant connectors. This action is necessary to prevent moisture from entering the strake feed-thru and internal electrical connectors, which could lead to electrical arcing and a consequent fire in the electrical and electronic (E/E) compartment of the airplane. This action is intended to address the identified unsafe condition.
2023-05-15: The FAA is superseding Airworthiness Directive (AD) 2017-09-03 and AD 2018-20-07, which applied to all Dassault Aviation Model MYSTERE-FALCON 50 airplanes. AD 2017-09-03 and AD 2018-20-07 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2018-20-07 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2017-25-16: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 \n\n((Page 58719)) \n\nFreighter, and A330-300 series airplanes; and Airbus Model A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD requires repetitive inspections of certain fuel pumps for cavitation erosion, corrective action if necessary, and revision of the minimum equipment list (MEL). This AD was prompted by a report indicating that a fuel pump showing cavitation erosion breached the fuel pump housing and exposed the fuel pump power supply wires. We are issuing this AD to address the unsafe condition on these products.
2025-10-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a determination that certain master minimum equipment list (MMEL) items do not comply with MMEL certification requirements. This AD requires revising the operator's existing FAA-approved minimum equipment list (MEL), as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
75-16-04: 75-16-04 PIPER AIRCRAFT CORPORATION: Amendment 39-2272. Applies to PA-28-151 airplanes serial numbers 28-7415001 through 28-7515425; certificated in all categories. Compliance required within the next 50 hours' time in service or at the next scheduled inspection, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent over-travel of the carburetor air box valve, accomplish the following or accomplish an alternate modification method approved by the Chief, Engineering and Manufacturing Branch, Southern Region. (1) Remove lower nose cowl and metal bottom panel for access to the carburetor air box. (2) Loosen clamps attaching carburetor heat and induction air hoses to air box. Remove hoses from air box. (3) Remove control cable from bracket and lever on air box. Retain all hardware except cotter pin for reinstallation. (4) Remove air box bottom and valve by removing (12) #6 screws, nuts, and washers around the bottom of the air box. Retain the air box bottom and valve and attaching hardware for reinstallation. (5) Remove safety wire securing (4) MS20074-04-04 bolts which mount air box to carburetor. Remove the bolts and AN936A416 washers. Remove air box from carburetor. Remove and discard old 73451-07 gasket, but retain mounting hardware for reinstallation. (6) Install (2) plates, Piper Part Number 35646002, to top stiffener, secured with 8 (4 each plate) MS28470AL3-4 (Piper P/N 420-201) rivets. Installation must prevent valve over- travel. (7) Install new gasket Piper P/N 73451-07, and reworked air box on carburetor using (4) MS20874-04-04 bolts and AN936A416 washers. Safety wire bolts. (8) Reinstall bottom and valve assembly to air box using (12) #6 screws, nuts, and washers previously removed. Insure lever on valve is on the same side of box as control cable bracket. (9) Reinstall control cable. Tighten the swivel fitting nut to draw the core wire into the recess 1/2 its diameter. (10) Reinstall carburetor heat and induction air hoses on air box and secure with clamps. (11) Replace cowling and metal bottom panel. Piper Service Bulletin 474 also pertains to this same subject. This amendment becomes effective July 30, 1975.
2002-06-14: This amendment adopts a new airworthiness directive (AD) applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10-10F and MD-10-30F series airplanes. This action requires an inspection of the parallel power feeder cables of the number 2 generator for chafing or structure damage; repositioning of the cables; and repair, if necessary. This action is necessary to prevent wire chafing of the parallel power feeder cables of the number 2 generator, which, if not corrected, could result in electrical arcing and damage to adjacent structure, and consequent smoke and/or fire in the aft door panel area. This action is intended to address the identified unsafe condition.
75-11-05: 75-11-05 PIPER: Amendment 39-2205. Applies to model PA-23-250 Airplane Serial Numbers 27-7554001 through 27-7554060, certificated in all categories. Unless already accomplished, within the next 50 hours in service after the effective date of this AD, accomplish the following: Replace the existing instrument glare shield panel in accordance with the installation instructions in Piper Kit No. 760 932 or with equivalent parts which must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Service Bulletin No. 452 pertains to the same subject. This amendment is effective May 20, 1975.
2023-05-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report that in case of a flap, slat, or slat- flap failure in flight, resetting the slat flap control unit (SFCU) to clear the error using the airplane flight manual (AFM) could result in the stall protection computer (SPC) setting the low-speed cue to the most conservative stall advance mode. This AD requires revising the non-normal procedures section of the existing AFM to provide the flightcrew with procedures for addressing failure warnings in the slat and flap control systems. The FAA is issuing this AD to address the unsafe condition on these products.
75-09-18:
2002-06-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and -300 series airplanes. This action requires replacement of the switch guard on the switch used to control the passenger and/or therapeutic oxygen system with a new, improved switch guard. This action is necessary to prevent displacement of the passenger/therapeutic oxygen switch, which could result in the unavailability of supplemental/therapeutic oxygen and possible incapacitation of passengers during flight. This action is intended to address the identified unsafe condition.
75-12-10: 75-12-10 COLLINS: Amendment 39-2232. Applies to Collins AP106 Autopilots which may be installed on Aero Commander Models 500S and 690A; Beech Models 60, A60, B60, 95-C55, 95-C55A, D55, D55A, E55, E55A and A36; DeHavilland Model DHC-6; Piper Models PA 31-350 and PA 31-325; and Swearingen Models SA 226-AT and SA 226-TC, airplanes. Compliance: Required as indicated, unless already accomplished. To prevent failure in multiple servos, accomplish the following: A. Within the next 10 hours" time in service after the effective date of this AD, check the modification information plate on the 161H-1 programmer (P/N 622-1036-001), which is part of the AP106 Autopilot, to determine if the unit has been modified in accordance with Collins Service Bulletin No. 6, or approved revisions. If so modified, make an appropriate entry in the aircraft records indicating compliance with this AD. B. If the 161H-1 programmer has not been modified in accordance with Collins Service Bulletin No. 6, or approved revisions, prior to further flight, disable the roll and pitch servo axes by placing a collar over the circuit breakers, if installed, or remove and tie back the connector from the roll and pitch servos, and in either case install a placard in plain view of the pilot which reads: "DO NOT ENGAGE AUTOPILOT" and operate the aircraft in accordance with this limitation. C. On or before December 1, 1975, modify all the 161H-1 programmers in accordance with Collins Service Bulletin No. 6. D. Any alternate means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective June 11, 1975, to all persons except those to whom it was made effective earlier by air mail letter issued May 15, 1975.
2023-05-14: The FAA is superseding Airworthiness Directive (AD) 2022-06- 02, which applied to all Airbus SAS Model A318-111, and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2022-06-02 required new repetitive inspections of the 80 view unit (80VU) rack lower lateral fittings, lower central support, upper fittings, central post, and shelves attachments for discrepancies, and corrective actions if necessary. This AD was prompted by a determination that the compliances times must be revised to address the unsafe condition. This AD continues to require the actions in AD 2022- 06-02 with revised compliance times, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2025-10-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320 series airplanes; Model A321-211, -212, -213, - 231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -272N, and -272NX airplanes; Airbus SAS Model A330-200 series airplanes; Model A330-300 series airplanes; Model A330-800 series airplanes; Model A330-900 series airplanes; Model A350-941 and -1041 airplanes; and Model A380-800 series airplanes. This AD was prompted by a report of corrosion and cracks on the broadband antenna adapter plate during an inspection. This AD requires repetitive general visual inspections of the broadband antenna adapter plate, skirt, vents, and attachment fittings, and applicable corrective actions, and limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
75-05-02: 75-05-02 BEECH, CESSNA, NAVION AND PIPER: Amendment 39-2095. Applies to Beech Models 35, A35, B35, C35, D35, E35, F35, G35, 35R, 35-33, 35-A33, 35-B33, 35-C33, 35-C33A, E33, E33A, E33C, F33, F33A, F33C, G33, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36 series airplanes; Piper Models PA24, PA24-250, PA24-260 series airplanes; Navion Model Navion A series airplanes; Cessna Models 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P series airplanes certificated in all categories which have been modified in accordance with STC SA2653WE. Compliance required as indicated unless already accomplished. To prevent loss of engine oil, improper engine lubrication or engine oil contamination, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 25 hours' time in service, unless (b) has been accomplished, remove the Beryl Aviation airoil separator Filtrator Assembly and inspect in accordance with the following procedure. (1) Add one quart of clear gasoline to the assembly can and plug or cap the ends of all tubes. (2) Hold the assembly can upright and shake vigorously for about two minutes. (3) Completely drain the gasoline from the 1/8 inch oil return tube through a paint strainer or similar fine mesh strainer and check for the presence of polyester urethane particles that have broken off of the internal screen material. (4) If screen particles are present, accomplish (b). (5) If screen particles are not present, install a 1/8 inch rivet in the top center of the assembly can to fasten the inside center cone to the outside can. Seal the rivet with an oil and fuel resistant type sealant if required. After assuring that cleaning agent has evaporated, reinstall the filtrator assembly. (b) Within the next 100 hours' time in service after the effective date of this AD, unless alreadyaccomplished, accomplish (1), (2), or (3). (1) (i) For Beech Models 35, A35, B35, C35, D35, E35, F35, G35 and 35R Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1119-1 and install either P/N B-1119-M or P/N B-1119-RM. (ii) For Beech Models S35, V35, V35A, V35B, 35C-33A, E33A, E33C, F33A, F33C, 36 and A36 Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1116-1 and install either P/N B-1116-M or P/N B-1116-RM. (iii) For Beech Models H35, J35, K35, M35, N35, P35, 35-33, 35-A33, 35-B33, 35-C33, E33, F33 and G33 Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1114-1 and install either P/N B-1114-M or P/N B-1114-RM. (iv) For Piper Models PA24, PA24-250, and PA24-260 Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1113-1 and install either P/N B-1113-M or P/N B-1113-RM. (v) For Navion Model A Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1112-1 and install either P/N B-1112-M or P/N B-1112-RM. (vi) For Cessna Models 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N and 182P Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1114-1 and install either P/N B-1114-M or P/N B-1114-RM. (2) Remove the modification incorporated by STC SA2653WE and return airplane to the standard unmodified configuration. (3) Provide compliance with an equivalent method approved by Chief, Engineering and Manufacturing Branch, Southern Region. Beryl Aviation Specialties, Route 1, Box 127D, Leesburg, Florida 32748, Service Bulletin B-1-1-75-1 also pertains to this subject. This amendment becomes effective February 21, 1975.
2002-06-13: This amendment adopts a new airworthiness directive (AD) applicable to certain McDonnell Douglas MD-90-30 airplanes. This action requires inspection of the power feeder cables on the left and right side of the aft cargo compartment between certain stations for minimum clearance from the adjacent structure and for the presence of a grommet in the lightening hole through the floor cusp, and corrective actions, if necessary. The actions specified by this AD are intended to detect and correct inadequate clearance of the power feeder cables on the left and right side of the aft cargo compartment, the lack of a grommet in the lightening hole through the floor cusp, and improper installation of the cabin sidewall grill during production. These conditions could lead to chafing of the power feeder cables, resulting in electrical arcing and possibly in a fire in the cargo compartment of the airplane. This action is intended to address the identified unsafe condition.
75-02-03: 75-02-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2066. Applies to Piper Models PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-32-260 and PA-32-300 airplanes, modified by installing a large nose wheel fork (Tibbetts-Herre Airmotive P/N PA-32-1) and an 8.00-6 nose wheel tire in accordance with Supplemental Type Certificate SA281AL, certificated in all categories. Compliance is required prior to the accumulation of 25 landings after the effective date of this AD, unless already accomplished. To prevent possible failure of the nose wheel fork assembly, accomplish the following: (a) Visually inspect the nose wheel fork for bends in the legs which are not part of the STC design. (b) Straighten any bends found in the inspection required by paragraph (a) of this AD, prior to the inspection required by paragraph (c) of this AD. (c) Inspect those nose wheel forks that have at any time been straightened in the past for cracks in the vicinity of the nosewheel axle holes, using a standard dye or fluorescent penetrant inspection procedure. To determine whether a nose wheel fork has been straightened in the past - (1) Check the aircraft maintenance records; and (2) Visually inspect the fork for any evidence of it having been straightened. (d) If no cracks are found in the inspection required by paragraph (c) of this AD, or the nose wheel fork is a fork excepted from the inspection required by paragraph (c) of this AD, chamfer and heat treat the nose wheel fork before further flight in accordance with paragraphs (f) and (g) of this AD. (e) If cracks are found in the inspection required by paragraph (c) of this AD, before further flight, replace the nose wheel fork with a serviceable nose wheel fork of the same part number which has been chamfered and heat treated in accordance with paragraphs (f) and (g) of this AD. (f) Chamfer the outside edge of each nose wheel fork axle hole at 45 degrees to a minimum depthof 1/32-inch prior to heat treating. (g) Heat treat the nose wheel fork to Ftu of 180,000 PSI in accordance with MIL-H- 6875 or an FAA approved equivalent. (h) Permanently stamp the letter "H" on each nose wheel fork heat treated in accordance with paragraph (g) of this AD, adjacent to the serial and part number stamps. (i) Replace each Piper P/N 20825-00 cap assembly with a Tibbetts-Herre P/N PA- 32-5 cap assembly or an equivalent approved by the Chief, Engineering and Manufacturing Field Office, FAA, Alaskan Region. (j) Replace the Tibbetts-Herre P/N PA-32-4 axle rod with a Tibbetts-Herre P/N PA- 32-6 axle rod or equivalent approved by the Chief, Engineering and Manufacturing Field Office, FAA, Alaskan Region, using AN365-624 nuts and AN960-616 washers. Note: For the purpose of complying with this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours' time in service bythe operator's fleet average time from takeoff to landing for the airplane type. This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made effective upon receipt of the airmail letter dated November 26, 1974, that contained this amendment.