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.