Results
2024-16-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by the discovery of a single-point failure within the left- hand and right-hand heater current monitor (HCM) units. This AD requires installing a monitor circuit comprising relays external to the HCM units. This AD also requires revising the normal and non-normal procedure sections of the existing airplane flight manual (AFM) to add new procedures associated with revised crew alerting system (CAS) messages. The FAA is issuing this AD to address the unsafe condition on these products.
2017-10-02: We are superseding airworthiness directive (AD) 2015-11-01 for Slingsby Aviation Ltd. Models T67M260 and T67M260-T3A airplanes. This AD results from mandatory continuing airworthiness information [[Page 24046]] (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of a brake master cylinder pivot pin, which could cause the rudder pedal mechanism to detach from the brake cylinder. We are issuing this AD to require actions to address the unsafe condition on these products.
2017-11-02: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model MD-90-30 airplanes. This AD was prompted by a report of cracking in a horizontal stabilizer rear spar cap. This AD requires repetitive inspections for any crack in the left and right side horizontal stabilizer rear spar upper caps, and repair or replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
75-22-08: 75-22-08 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2402. Applies to SA330F and SA330G helicopters certificated in all categories, equipped with external hoists AE-76 360-100 or AE-76 360-110-01. Compliance is required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To ensure proper functioning of the pyrotechnic shears, accomplish the following: (a) Inspect electrical connections ME 24F and ME 25F on mobile connector 52 Ma of the pyrotechnic shears control for proper connections. (b) Electrical connections which are improperly connected must be disassembled, reconnected and checked in accordance with paragraph 2.B of Aerospatiale Service Bulletin No. 45.06, dated April 2, 1975, or an FAA-approved equivalent. This amendment becomes effective November 3, 1975.
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.