Results
2017-10-06: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD requires fluorescent penetrant inspection (FPI) of the compressor intermediate case (CIC) for cracking. This AD was prompted by CICs that were weld repaired and have a higher probability of cracking as a result of the weld repair process. We are issuing this AD to correct the unsafe condition on these products.
2024-16-18: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a determination that a revised restrictive airworthiness limitation is necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate a revised restrictive airworthiness limitation for the aft engine mount attachment bolts. The FAA is issuing this AD to address the unsafe condition on these products.
71-19-06: 71-19-06 HAWKER SIDDELEY: Amdt. 39-1294. Applies to Model DH-104 "Dove" airplanes. Compliance is required as indicated. To ensure that the emergency escape hatches (P/N's 4FS.835A/I and 4FS.835A/2) can be opened from outside the airplane accomplish the following: (a) Before further flight check the operation of each escape hatch lock mechanism by turning the external handle with the internal handle in the stowed position. The check required by this paragraph may be performed by the pilot. (b) If an escape hatch lock mechanism is found to be inoperable during the check required by paragraph (a), before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repairs can be performed, secure the inoperable lock mechanism to the escape hatch in accordance with Hawker Siddeley Technical News sheet Series: CT(104) No. 222, Issue 1, dated March 15, 1971, or an FAA approved equivalent. (c) Within the next 100 hourstime in service after the effective date of this AD, unless already accomplished, secure the lock mechanism to each escape hatch in accordance with Hawker Siddeley Aviation, Ltd., Technical News Sheet Series: CT(104) No. 222, Issue 1, dated March 15, 1971, or an FAA-approved equivalent. This amendment becomes effective September 21, 1971.
71-24-03: 71-24-03 PRATT & WHITNEY ENGINES: Amdt. 39-1335 as amended by Amendment 39-1365 and 39- 1401 is further amended by Amendment 39-1447. Applies to all Pratt & Whitney Aircraft JT9D-3A turbofan engines which incorporate Part Number 669647 diffuser case assembly. Compliance required as indicated. To preclude rupture of the part number 669647 diffuser case assembly as the result of borescope boss weld cracks, accomplish the following: 1. For wet operating JT9D-3A engines with diffuser cases having in excess of 2500 hours or 600 cycles time in service, inspect all borescope positions in accordance with paragraph 4 within 25 cycles after the effective date of this AD and every 25 cycles thereafter. 2. For dry operating JT9D-3A engines with diffuser cases having in excess of 2500 hours or 600 cycles in service, inspect all borescope positions in accordance with paragraph 4 within 100 cycles after the effective date of this AD or 250 cycles since the last inspection, whichever occurs later, and every 250 cycles thereafter. NOTE: For the purposes of this paragraph, JT9D-3A engines operating both wet and dry may be considered as dry operation provided each wet cycle is counted as equivalent to 10 dry cycles. 3. Inspect all borescope positions which have been weld repaired as specified in Pratt & Whitney Aircraft Alert Service Bulletin No. 2901 in accordance with paragraph 4 within the next 5 to 15 cycles after weld repair or 15 cycles after the effective date of this AD, whichever occurs later, and every 25 cycles wet operation or 250 cycles dry operation thereafter. 4. Inspect borescope boss weld areas of the Part Number 669647 diffuser case assembly using one of the techniques specified in Pratt & Whitney Aircraft Alert Service Bulletin No. 2901 or any equivalent inspection procedure approved by the FAA, Chief, Engineering and Manufacturing Branch, Eastern Region. If any crack is found, remove the diffuser case from service, and replaceor repair in accordance with Pratt & Whitney Aircraft Alert Service Bulletin No. 2901. 5. For JT9D-3A engines with diffuser cases incorporating reinforcement straps in accordance with Pratt & Whitney Aircraft Special Instruction No. 29F-71, or equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, inspect all borescope positions in accordance with paragraph 4 within 250 cycles after installation of the reinforcement straps and every 250 cycles thereafter. 6. Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive inspection times specified in this airworthiness directive. 7. For JT9D-3A engines incorporating fuel nozzle and support assemblies reworked in accordance with Pratt & Whitney Aircraft Turbine Engine Service Bulletin No. 3627 or equivalent method approved by the Chief, Engineering and ManufacturingBranch, Eastern Region, inspect all borescope positions in accordance with paragraph 4 within 75 cycles after installation of the reworked fuel nozzle and support assemblies and every 75 cycles thereafter. NOTE: Turbine Engine Service Bulletin No. 3627 does not apply to engines which incorporate Turbine Engine Service Bulletin No. 3223 or 3628. Amendment 39-1335 was effective November 24, 1971, and was effective upon receipt for all recipients of the telegram dated October 8, 1971 which contained this amendment. Amendment 39-1365 was effective December 31, 1971. Amendment 39-1401 was effective March 14, 1972. This Amendment 39-1447 is effective May 19, 1972.
2017-10-24: We are superseding Airworthiness Directive (AD) 2011-17- [[Page 24036]] 09 for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and AD 2012-25-12 for all Airbus Model A330-200 and -300 series airplanes. AD 2011-17-09 required revisions to certain operator maintenance documents to include new inspections. AD 2012-25-12 required replacing certain main landing gear (MLG) bogie beams before reaching new reduced life limits. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new, more restrictive, or revised instructions and/or airworthiness limitation requirements. This AD was prompted by revisions to certain airworthiness limitation item (ALI) documents, which specify more restrictive instructions and/or airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2017-10-04: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes. This AD was prompted by changes to the airworthiness limitations, which add life-limited landing gear parts not previously identified. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new airworthiness limitations that add life limits for previously unidentified landing gear parts. We are issuing this AD to address the unsafe condition on these products.
72-08-02: 72-08-02 HAWKER SIDDELEY AVIATION: Amdt. 39-1424. Applies to Model DH- 114 "Heron" Series 2 airplanes. Compliance is required as indicated. To prevent failures of the main undercarriage main and damper jack attachment bolts, P/N 14-2U.229 and P/N 14-2U.631, accomplish the following: (a) For airplanes with main undercarriage units that have any P/N 14-2U.229 main and damper jack attachment bolts installed, within the next 150 hours' time in service after the effective date of this AD, unless already accomplished within the last 150 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service from the last inspection, remove and visually inspect the attachment bolts for cracks. (b) For airplanes with main undercarriage units that have only P/N 14-2U.631 (Modification 1536) main and damper jack attachment bolts installed, within the next 1,200 hours' time in service after the effective date of this AD, unless already accomplished within the last 1,200 hours' time in service, and thereafter at intervals not to exceed 2,400 hours' time in service from the last inspection, remove and visually inspect the attachment bolts for cracks. (c) If any bolt is found to be cracked during an inspection required by paragraph (a) or (b), before further flight replace the cracked bolt in accordance with subparagraph (1) or (2): (1) Replace a cracked bolt, P/N 14-2U.229 with either a serviceable bolt of the same part number or replace with a serviceable bolt, P/N 14-2U.631 (Modification 1536), and continue to inspect in accordance with paragraphs (a) or (b) as applicable. (2) Replace a cracked bolt, P/N 14-2U-631 (Modification 1536), with a serviceable bolt of the same part number and continue to inspect in accordance with paragraphs (a) or (b) as applicable. This amendment becomes effective May 1, 1972.
2024-19-10: The FAA is adopting a new airworthiness directive (AD) for certain Austro Engine GmbH (Austro) Model E4 and E4P engines. This AD was prompted by reports of engine failures and an investigation where cracks were discovered on the pistons. This AD requires repetitive borescope inspections (BSIs) for cracks on the pistons, and, if necessary, removal from service and replacement of the piston, and a fuel sample analysis for water contamination and, if contamination is found, replacement of the high-pressure pump (HPP), injectors, and fuel rails. The FAA is issuing this AD to address the unsafe condition on these products.
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.
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.