Results
2017-10-09: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Models 402C and 414A airplanes (type certificate previously held by Cessna Aircraft Company). This AD requires inspecting the nacelle fittings for cracks, replacing if necessary, and reporting the results of the inspection to the FAA. This AD was prompted by reports of cracks found on certain nacelle fittings. We are issuing this AD to correct the unsafe condition on these products.
2017-09-10: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-400, 747-400D, and 747-400F airplanes. This AD was prompted by a report of a crack in the left wing front spar web, found following a fuel leak. This AD requires repetitive inspections for cracking of the front spar web, and repairs if necessary. We are issuing this AD to address the unsafe condition on these products.
2024-16-10: The FAA is superseding Airworthiness Directive (AD) 2019-25- 17, which applied to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2019-25-17 required revising the existing airplane flight manual (AFM) to prohibit selection of certain runways for airplanes equipped with certain software. Since the FAA issued AD 2019-25-17, Boeing has developed new software to address the unsafe condition. This AD was prompted by reports of display electronic unit (DEU) software errors on airplanes with a selected instrument approach to a specific runway. This AD retains the requirements of AD 2019-25-17. This AD also requires installing the new software and performing a software configuration check, which terminates the AFM revision. The FAA is issuing this AD to address the unsafe condition on these products.
74-12-03: 74-12-03 MCDONNELL DOUGLAS: Amendment 39-1858. Applies to DC-8-61F, -62F, -63F convertible freighter airplanes, certificated in all categories. \n\n\t(1)\tFor all aircraft in the passenger configuration, within twenty-four (24) hours of receipt of this telegram, or prior to further flight, whichever occurs later, unless already accomplished within the last 50 hours, perform the passenger oxygen system leak check per paragraph 1(a) DACO Alert Service Bulletin A35-25 Revision A dated May 10, 1974, or later FAA-approved revisions. If the oxygen system does not pass the leak check, inspect, repair and replace worn piping as required, and replace broken and missing supports prior to next flight; repeat leak test per DACO A.S.B. A35-25 Revision A, paragraph 1(a). At intervals not to exceed 50 flight hours visually inspect for worn oxygen piping, replace as necessary, and conduct the leak test per DACO A.S.B. A35-25 Revision A, paragraph 1(a) until the modifications described by DACO A.S.B. A35-25 Revision A, paragraph 1(b) have been accomplished. Within 300 hours time in service after initial leak check, secure all oxygen piping, per DACO A.S.B. A35-25 Revision A, paragraph 1(b). \n\n\t(2)\tFor aircraft in the full freighter configuration, prior to further flight after receipt of this telegram, close the oxygen hand shutoff valve on the passenger system and placard system inoperative until (1), above, is accomplished. Prior to conversion to passenger configuration, perform checks, repair, and modifications of (1) above. Paragraph 2, DACO A.S.B. A35-25 Revision A covers this subject. \n\n\tThis amendment becomes effective June 6, 1974, for all persons except those to whom it was made effective immediately by telegram dated May 11, 1974.
70-13-03: 70-13-03 CONTINENTAL: Amendment 39-1017. Applies to Continental Model TSIO-520-C (Serial Numbers 140001 through 140678) engines installed in Cessna Model TU206, TP206 and T210 airplanes. Compliance: Unless already accomplished, within the next 12 months after the effective date of this AD, accomplish the following: To prevent hydraulic lock and resulting engine damage and power loss: Replace the presently installed Teledyne Continental Motors Part Number 633125 balance tube assembly with new Teledyne Continental Motors Part Number 635645 balance tube assembly and install associated aircraft installation drainage provisions in accordance with Cessna Service Kit SK206-10, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. Teledyne Continental Motors Service Bulletin M70-5 dated May 6, 1970, also pertains to this subject. This amendment becomes effective July 2, 1970.
74-10-11: 74-10-11\tAIRESEARCH: Amendment 39-1837 as amended by Amendment 39-1869. Applies to Model TSCP 700-4B Auxiliary Power Units (APU) installed in McDonnell Douglas Model DC-10 aircraft. \n\n\t"Pursuant to the authority of the Federal Aviation Act of 1958, delegated to me by the Administrator the following airworthiness directive applicable to AiResearch Model TSCP 700- 4B Auxiliary Power Units (APU) (installed in McDonnell-Douglas Model DC-10 Series Aircraft) is effective immediately upon receipt of this telegram because of numerous reports of fatigue cracks in the fuel control differential pressure regulator body. The presence of crack(s) can allow fuel to leak into the APU compartment. Compliance required as indicated, unless already accomplished. \n\n\t(a)\tWithin 25 hours additional time in service after the effective date of this AD, as amended, unless already accomplished, install a placard in view of the flight crew to prohibit all in-flight operation of the APU. Thereafter the APU may not be used in flight but may be used in ground operations." \n\n\t(b)\tThe operating restriction prescribed in (a), above, may be removed when the inspections and modifications described in paragraph 2.B. and C. of AiResearch Service Bulletin 969900-49-3635, Revision 1, dated May 14, 1974, or later FAA-approved revisions, are accomplished. Differential pressure regulator body assembly P/N 977320-1 or -2 which does not meet the wall thickness and fillet radius requirements specified in the referenced Service Bulletin must be rendered unserviceable. Those found satisfactory or that can be reworked per the instructions contained in paragraph 2.B.(4) of the referenced Service Bulletin must be re- identified as P/N 977320-4 and may be continued in service. Re-identify the fuel control assembly per paragraph 2.D. of the referenced service bulletin." \n\n\t(c)\tWithin 3000 APU operating cycles in service after accomplishment of paragraph (b), above, and at intervals not to exceed 3000 APU operating cycles in service thereafter, inspect the fuel control differential pressure regulator body, P/N 977320-4, for cracks in accordance with paragraph 2.B.(2) of AiResearch Service Bulletin 969900-49-3635. If cracks are found, replace the housing with a serviceable housing conforming to P/N 977320-4, prior to further in-flight operation. \n\n\tNote: For the purpose of this AD, an APU operating cycle is any operation consisting of a start and shut-down. The number of cycles may be determined by actual count, or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing the fuel control assembly time in service by the operator's fleet average APU operating time per APU operating cycle. \n\n\t(d)\tThe inspections prescribed in (c) above may be discontinued when the fuel control differential pressure regulator body assembly P/N 977320-4 is replaced with a new part conforming to P/N 977656-1. \n\n\t(e)\tEquivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. \n\n\tAmendment 39-1837 was effective May 13, 1974, for all persons except those to whom it was made effective immediately by telegram dated April 17, 1974. \n\n\tThis Amendment 39-1869 becomes effective June 14, 1974.
2017-09-12: We are adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes and Model ATR72-102, -202, -212, and -212A airplanes. This AD was prompted by reports of failure of emergency power supply units (EPSUs) in production and in service. This AD requires an inspection to determine the part number and serial number of each EPSU, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
2024-19-07: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) Model LEAP-1A32 engines. This AD was prompted by a report of multiple events of loss of thrust control during go-around. This AD requires replacement of the full set of fuel nozzles. The FAA is issuing this AD to address the unsafe condition on these products.
2017-10-01: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FAN JET FALCON airplanes; all Model FAN JET FALCON SERIES C, D, E, F, and G airplanes; and all Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. This AD was prompted by a determination that inspections for discrepancies of the fuselage bulkhead are necessary. This AD requires repetitive inspections for discrepancies of the fuselage bulkhead, and repair if [[Page 21470]] necessary. We are issuing this AD to address the unsafe condition on these products.
74-04-03: 74-04-03 HILLER AVIATION: Amendment 39-1785. Applies to Hiller Models UH- 12D (H-23D) and UH-12E (3 and 4 place), (OH-23G, H-23F) helicopters certificated in all categories. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To detect main rotor drag struts P/N 52120 with unacceptably low heat-treat condition and prevent premature fatigue failure of this strut accomplish the following: (a) Remove and prepare for inspection the two main rotor drag struts, P/N 52120, in accordance with the instructions contained in Hiller Aviation Service Bulletin No. 51-2, dated January 21, 1974, or later FAA-approved revisions, or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) Check the Rockwell hardness of struts P/N 52120 using the "C" scale in accordance with the instructions contained in Hiller Aviation Service Bulletin No. 51-2, dated January 21,1974, or later FAA-approved revisions, or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (1) Struts with Rockwell "C" from 31.5 to 36 may be returned to service for the remainder of the 2500 hour service life. These struts should be identified by etching an "H" before the serial number. (2) Struts with Rockwell "C" less than 23 must be replaced within the next 50 hours' time in service or a total of 2500 hours' time in service whichever comes first. (3) Struts with Rockwell "C" from 23 to 31 must be replaced within the next 50 hours' time in service or a total of 1200 hours' time in service whichever comes later, but must not exceed in any case, a total of 2500 hours' time in service. (c) Repaint the drag struts and reinstall or replace them on the helicopter observing the proper rotor blade alignment (Refer to UH-12E Service Manual). (d) In lieu of performing the above inspections, the struts, P/N 52120 maybe removed and replaced with struts P/N 52120-5. Struts P/N 52120-5 also have a service life limit of 2500 hours' time in service. (e) Aircraft may be flown to a base where the maintenance required by this AD may be performed per FARs 21.197 and 21.199. This amendment becomes effective February 18, 1974.
2017-09-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707 airplanes and Model 720 and 720B series airplanes. This AD was prompted by a determination that undetected web fatigue cracking caused by oil canning may exist in the aft pressure bulkhead web. This AD requires repetitive detailed inspections for any oil canning or cracking of the aft pressure bulkhead web, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2024-16-07: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by incidents related to erroneous autothrottle (A/ T) behavior during a balked landing with the A/T engaged, potential erroneous readings from the low range radio altimeter (LRRA), and possible deficiencies in low airspeed protections and crew alerting systems. This AD requires updating the thrust management (TM) and displays and crew alerting (DCA) operational program software (OPS). The FAA is issuing this AD to address the unsafe condition on these products.
2017-08-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a report indicating that during inspections to detect corrosion of the bulk cargo doors, several cracks were discovered. This AD requires inspections of the bulk cargo door frame to identify any structural repairs and cracking, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
75-08-15: 75-08-15 SIKORSKY: Amendment 39-2163. Applies to S-61N helicopters certificated in all categories. Compliance required within 5 hours time in service after the effective date of this AD. (1) Prior to each flight, a flight crewmember or ground service personnel shall check the baggage door, P/N S6120-72601-1, to ensure that it is closed and the locking mechanism and pins are in the locked position. (2) If the baggage door opens in flight as indicated by warning light in the instrument panel and the door cannot be closed and locked, the aircraft speed must be reduced to 45 knots and a landing made as soon as practicable. This amendment becomes effective upon publication in the FEDERAL REGISTER.
75-22-15: 75-22-15 MORANE SAULNIER (SOCATA) RALLYE: Amendment 39-2405. Applies to MS880B and MS885 airplanes, certificated in all categories, except serial numbers 1962 and subsequent; and MS892A150, MS893A, and MS894A airplanes, certificated in all categories, except serial numbers 11993 and subsequent. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible interference between the control stick and floor hat section, accomplish the following: Modify the floor adjacent to the control stick by increasing the clearance between the floor and control stick in accordance with the "Description" paragraph in Socata Service Bulletin No. 104 GR-27-09, dated September, 1972, or an FAA-approved equivalent. This amendment becomes effective November 4, 1975.
2017-08-10: We are superseding airworthiness directive (AD) 2017-01-01 for all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211- Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2017-01-01 required inspections of the low-pressure turbine (LPT) exhaust case and support assembly or tail bearing housing (TBH) to detect cracks or damage. This AD corrects references to certain service bulletins in the compliance section of AD 2017-01-01. This AD was prompted by reports that references to service bulletins in AD 2017-01-01 are incorrect. We are issuing this AD to correct the unsafe condition on these products.
2017-06-11: We are superseding Emergency Airworthiness Directive (Emergency AD) 2015-24-51 for Airbus Helicopters Model EC120B. Emergency AD 2015-24-51 required inspections of the air conditioning system. This supersedure revises the applicability, some of the terminology, and the [[Page 18691]] inspection requirements. This AD was prompted by a report of an abnormal noise during flight of a Model EC120B helicopter that resulted in a precautionary landing. We are issuing this AD to prevent an unsafe condition on these products.
2024-15-13: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB-545 and EMB-550 airplanes. This AD was prompted by occurrences of premature cracks in the outer layer of certain flight deck side windows caused by interference due to manufacturing tolerances. This AD requires initial and repetitive inspections of the flight deck side windows and applicable corrective actions, and prohibits the installation of affected flight deck side windows, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
75-03-05: 75-03-05 HAMILTON STANDARD: Amendment 39-2025. Applies to propeller Models 54H60-63, -81, -91, -111, -117, and -125. Compliance required as indicated, unless already accomplished. To prevent inflight separation of the extension sleeve, P/N 541850, Change B or earlier revision, from the pitch lock regulator assembly resulting in propeller pitchlocking, accomplish the following: A. Propellers with a total of 2500 or more hours in service as of the effective date of this AD or whose total time in service is unknown, accomplish the requirements of Paragraph (C) below within the next 100 hours time in service. B. Propellers with less than 2500 hours total time in service as of the effective date of this AD, accomplish the requirements of Paragraph (C) below prior to the accumulation of 2600 hours total time in service. C. 1. Replace the fluid transfer housing extension sleeve, P/N 541850B or earlier revision, with an extension sleeve, P/N 541850C or later revision,or with a modified extension sleeve in accordance with Hamilton Standard Service Bulletin HS Code 54H60, No. 59, Revision No. 1, dated August 1, 1972, or later FAA approved revision, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 2. Replace the surge valve housing, P/N 543734B or earlier revision, with housing P/N 543734C or later revision, or replace surge valve housing, P/N 535299E or earlier revision with housing P/N 535299F or later revision. The Manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Hamilton Standard, Division of United Aircraft Corporation, Windsor Locks, Connecticut 06096. These documents may also be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on February 5, 1975.
2017-08-07: We are adopting a new airworthiness directive (AD) for certain Learjet, Inc., Model 60 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper fuselage skin under the aft oxygen line fairing is subject to multi-site damage (MSD). This AD requires a one-time inspection of the fuselage skin for corrosion, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
76-01-09: 76-01-09 PILATUS AIRCRAFT LTD: Amendment 39-2490. Applies to Pilatus Model PC-6 airplanes (all variants) manufactured by Pilatus Aircraft Ltd. serial numbers 667 and subsequent and serial numbers 2001 through 2047 inclusive manufactured by Fairchild Hiller. Compliance is required as indicated. To prevent a possible fatigue failure of the elevator attachment brackets on the inboard ends of the right and left elevator surfaces, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD unless already accomplished within the last 25 hours' time in service and thereafter at intervals not to exceed 50 hours time in service since the last inspection, visually inspect both the left and right brackets, P/N 6300.0011.00, of the welded attachment assembly for cracks in the flanges using a glass of at least 10 power in accordance with paragraph 2.1 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (b) If cracks are found, before further flight, repair in accordance with paragraph 2.1 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (c) Within the next 200 hours' time in service after the effective date of this AD, install reinforcement plates, P/Ns 6002.6993.51 and 6002.6993.52, unless already accomplished, in accordance with paragraph 2.2 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued after all cracks have been repaired and reinforcement plates have been installed in accordance with paragraph (c) of the AD. (Fairchild Hiller Service Bulletin PC-6-55-3 pertains to this same subject.) This amendment becomes effective on February 6, 1976.
2024-16-04: The FAA is superseding Airworthiness Directive (AD) 2009-25- 13, which applied to certain Bombardier, Inc., Model BD-100-1A10 (Challenger 300) airplanes. AD 2009-25-13 required the deactivation of the left-hand (LH) baggage bay heater mat. Since the FAA issued AD 2009-25-13, Bombardier developed a new design solution for the potential uncontrolled heating of the baggage bay sidewall heater mat. This AD retains the requirements of AD 2009-25-13 and requires modifying the baggage bay sidewall interior panel, heater mat, and water tank heater installation, and doing functional testing. Upon the completion of the new actions, the retained requirements of AD 2009-25- 13 will terminate. This AD also revises the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
2024-15-12: The FAA is superseding Airworthiness Directive (AD) 2021-26- 05, which applied to all Saab AB Model SAAB 2000 airplanes. AD 2021-26- 05 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 certain actions in AD 2021-26-05 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.
2024-15-14: The FAA is superseding Airworthiness Directive (AD) 2021-17- 02, which applied to all ATR-GIE Avions de Transport R[eacute]gional Model ATR42-200, -300, and -320 airplanes. AD 2021-17-02 required a one-time inspection for discrepancies of the wire bundles between the left- and right-hand angle of attack (AOA) probes and the crew alerting computer, and, depending on findings, applicable corrective actions. AD 2021-17-02 also required, for certain airplanes, modifying the captain stick shaker wiring, and for all airplanes, revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to incorporate procedures for the stick pusher/shaker. Since the FAA issued AD 2021-17-02, additional modification of the affected wiring for certain airplanes was developed. This AD retains all of the requirements of AD 2021-17-02 and requires installing a new AOA power supply unit and removing the AFM amendment; 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.
2017-08-03: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320-211, -212, -214, -231, -232, and -233 airplanes, and A321 series airplanes. This AD was prompted by the discovery of corroded circlips in fuel vent protectors (FVP) having a certain part number. This AD requires an inspection to determine the part number and serial number of the FVP, and replacement if necessary; and application of sealant on certain nuts and bolts of the National Advisory Committee for Aeronautics (NACA) duct assembly. We are issuing this AD to address the unsafe condition on these products.