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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.