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T95-18-51: T95-18-51 HAMILTON STANDARD: TELEGRAPHIC AD ISSUED ON AUGUST 25, 1995. DOCKET 95-ANE-48. APPLICABILITY: HAMILTON STANDARD MODELS 14RF-9, 14RF-19, 14RF-21, AND 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, AND 14SF-23; AND HAMILTON STANDARD/BRITISH AEROSPACE 6/5500/F PROPELLERS INSTALLED ON BUT NOT LIMITED TO EMBRAER EMB-120 AND EMB 120-RT; SAAB-SCANIA SF 340B; AEROSPATIALE ATR42-100, ATR42-300, ATR42-320, ATR72; DEHAVILLAND DHC-8-100 SERIES, DHC-8-300 SERIES; CONSTRUCCIONES AERONAUTICAS SA (CASA) CN-235 SERIES AND CN-235-100; CANADAIR CL-215T AND CL-415; AND BRITISH AEROSPACE ATP AIRPLANES. NOTE: THIS AD APPLIES TO EACH PROPELLER IDENTIFIED IN THE PRECEDING APPLICABILITY PROVISION, REGARDLESS OF WHETHER IT HAS BEEN MODIFIED, ALTERED, OR REPAIRED IN THE AREA SUBJECT TO THE REQUIREMENTS OF THIS AD. FOR PROPELLERS THAT HAVE BEEN MODIFIED, ALTERED, OR REPAIRED SO THAT THE PERFORMANCE OF THE REQUIREMENTS OF THIS AD IS AFFECTED, THE OWNER/OPERATOR MUST USE THE AUTHORITY PROVIDED IN PARAGRAPH (E) TO REQUEST APPROVAL FROM THE FAA. THIS APPROVAL MAY ADDRESS EITHER NO ACTION, IF THE CURRENT CONFIGURATION ELIMINATES THE UNSAFE CONDITION, OR DIFFERENT ACTIONS NECESSARY TO ADDRESS THE UNSAFE CONDITION DESCRIBED IN THIS AD. SUCH A REQUEST SHOULD INCLUDE AN ASSESSMENT OF THE EFFECT OF THE CHANGED CONFIGURATION ON THE UNSAFE CONDITION ADDRESSED BY THIS AD. IN NO CASE DOES THE PRESENCE OF ANY MODIFICATION, ALTERATION, OR REPAIR REMOVE ANY PROPELLER FROM THE APPLICABILITY OF THIS AD. COMPLIANCE: REQUIRED AS INDICATED, UNLESS ACCOMPLISHED PREVIOUSLY. TO PREVENT SEPARATION OF A PROPELLER BLADE DUE TO CRACKS INITIATING IN THE BLADE TAPER BORE, THAT CAN RESULT IN AIRCRAFT DAMAGE, AND POSSIBLE LOSS OF AIRCRAFT CONTROL, ACCOMPLISH THE FOLLOWING: (A) FOR HAMILTON STANDARD 14RF-9 PROPELLER BLADES, INSTALLED ON EMBRAER EMB-120 SERIES AIRCRAFT, WITHIN THE NEXT 10 FLIGHT CYCLES AFTER THE EFFECTIVE DATE OF THIS AD, REMOVE FROM SERVICE PROPELLER BLADES THAT HAVE BEEN ULTRASONICALLY SHEAR WAVE INSPECTED IN ACCORDANCE WITH AD 94-09-06 OR AD 95-05-03, REMOVED FROM SERVICE DUE TO CRACK INDICATIONS, AND SUBSEQUENTLY REWORKED AND RETURNED TO SERVICE. THESE PROPELLER BLADES INCLUDE, BUT ARE NOT LIMITED TO, THE FOLLOWING SERIAL NUMBERS: 847598, 851646, 852085, 852561, 853151, 854530, 854535, 854838, 855014, 855042, 855196, 855859, 857375, 858696, 859824, 860589, 867590, 876707, 880245 (B) FOR HAMILTON STANDARD MODELS 14RF-19, 14RF-21, AND 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, AND 14SF-23; AND HAMILTON STANDARD/BRITISH AEROSPACE 6/5500/F PROPELLER BLADES, INSTALLED ON AIRCRAFT OTHER THAN EMBRAER EMB-120 AIRCRAFT, WITHIN THE NEXT 10 FLIGHT CYCLES AFTER THE EFFECTIVE DATE OF THIS AD, AND THEREAFTER AT INTERVALS NOT TO EXCEED 1,250 FLIGHT CYCLES SINCE LAST INSPECTION, PERFORM AN ULTRASONIC SHEAR WAVE INSPECTION FOR CRACKS IN THE BLADE TAPER BORE OF PROPELLER BLADES THAT HAVE BEEN ULTRASONICALLY INSPECTED IN ACCORDANCE WITH AD 94-09-06 OR AD 95-05-03, REMOVED FROM SERVICE DUE TO CRACK INDICATIONS, AND SUBSEQUENTLY REWORKED AND RETURNED TO SERVICE. PERFORM THE ULTRASONIC SHEAR WAVE INSPECTION IN ACCORDANCE WITH THE ACCOMPLISHMENT INSTRUCTIONS OF THE FOLLOWING HAMILTON STANDARD ALERT SERVICE BULLETINS (ASB'S), AS APPLICABLE: NO. 14RF-21-61-A68, DATED AUGUST 25, 1995; NO. 14SF-61-A88, DATED AUGUST 25, 1995; NO. 14RF-19-61-A49, DATED AUGUST 25, 1995; NO. 6/5500/F-61-A36, DATED AUGUST 25, 1995. REMOVE CRACKED PROPELLER BLADES FROM SERVICE AND REPLACE WITH SERVICEABLE PARTS. (C) PROPELLER BLADES REMOVED FROM SERVICE IN ACCORDANCE WITH THIS AD MAY NOT BE RETURNED TO SERVICE. (D) FOR THE PURPOSE OF THIS AD, A FLIGHT CYCLE IS DEFINED AS ONE TAKEOFF AND THE NEXT LANDING OF AN AIRCRAFT. (E) AN ALTERNATIVE METHOD OF COMPLIANCE OR ADJUSTMENT OF THE INITIAL COMPLIANCE TIME THAT PROVIDES AN ACCEPTABLE LEVEL OF SAFETY MAY BE USED IF APPROVED BY THE MANAGER, BOSTON AIRCRAFT CERTIFICATION OFFICE. THE REQUEST SHOULD BE FORWARDED THROUGH AN APPROPRIATE FAA PRINCIPAL MAINTENANCE INSPECTOR, WHO MAY ADD COMMENTS AND THEN SEND IT TO THE MANAGER, BOSTON AIRCRAFT CERTIFICATION OFFICE. NOTE: INFORMATION CONCERNING THE EXISTENCE OF APPROVED ALTERNATIVE METHODS OF COMPLIANCE WITH THIS AIRWORTHINESS DIRECTIVE, IF ANY, MAY BE OBTAINED FROM THE BOSTON AIRCRAFT CERTIFICATION OFFICE. (F) SPECIAL FLIGHT PERMITS MAY BE ISSUED IN ACCORDANCE WITH SECTIONS 21.197 AND 21.199 OF THE FEDERAL AVIATION REGULATIONS (14 CFR 21.197 AND 21.199) TO OPERATE THE AIRCRAFT TO A LOCATION WHERE THE REQUIREMENTS OF THIS AD CAN BE ACCOMPLISHED. (G) COPIES OF THE APPLICABLE SERVICE INFORMATION MAY BE OBTAINED FROM HAMILTON STANDARD, ONE HAMILTON ROAD, WINDSOR LOCKS, CT 06096-1010; TELEPHONE (203) 654-3610. THIS INFORMATION MAY BE EXAMINED AT THE FAA, NEW ENGLAND REGION, OFFICE OF THE ASSISTANT CHIEF COUNSEL, 12 NEW ENGLAND EXECUTIVE PARK, BURLINGTON, MA. (H) TELEGRAPHIC AD T95-18-51, ISSUED ONAUGUST 25, 1995, BECOMES EFFECTIVE UPON RECEIPT.
2007-04-26: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines that were reassembled with previously used high pressure compressor (HPC) exit brush seal packs and new or refurbished HPC exit diffuser air seal lands. That AD currently requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. This AD requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, using either original equipment manufactured (OEM) parts, or FAA-approved part manufacturer approval (PMA) parts. This proposed AD also applies to engines reassembled with a PMA HPC exit inner and or outer brush seal packs. This AD results from a request to include PMA HPC exit inner and outer brush seal packs and to include the engines with PMA parts already installed, in the AD. We are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.
2007-04-08: The FAA adopts a new airworthiness directive (AD) for certain EADS SOCATA airplanes. This AD requires you to inspect the pilot door locking stop-fittings for correct length and, if any incorrect length pilot door locking stop-fittings are found, replace them. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are issuing this AD to detect and replace incorrect length pilot door locking stop- fittings. This condition, if not corrected, could result in depressurization of the airplane.
2018-24-01: We are adopting a new airworthiness directive (AD) for certain International Aero Engines (IAE) PW1100G-JM turbofan engine models with certain low-pressure turbine (LPT) 1st- and 3rd-stage disks installed. This AD was prompted by a report of manufacturing defects found on delivered LPT 1st- and 3rd-stage disks. This AD requires removing the LPT 1st- or 3rd-stage disk from service and replacing with a part eligible for installation. We are issuing this AD to address the unsafe condition on these products.
98-19-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600, that requires repetitive visual inspections to detect corrosion on the lower rim area of the fuselage rear pressure bulkhead; and follow-on actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion at the lower rim area of the fuselage rear pressure bulkhead, which could result in reduced structural integrity of the bulkhead, and consequent decompression of the cabin.
2007-04-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (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 cracks found on several main landing gear cylinders. We are issuing this AD to require actions to correct the unsafe condition on these products.
97-07-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings. This amendment is prompted by a report from the manufacturer indicating that full-scale fatigue testing on the test model revealed fatigue cracking in this area. The actions specified by this AD are intended to prevent fatigue cracking in this area, which can reduce the structural integrity of fuselage frame 36 and the wing center section.
2007-04-18: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, 25F, 28, 29, 31, 31A, 35, 35A (C- 21A), 36, 36A, 55, 55B, and 55C airplanes. This AD requires modifying the left- and right-hand standby fuel pump switches. This AD also requires revising the Emergency and Abnormal Procedures sections of the airplane flight manual to advise the flightcrew of the proper procedures to follow in the event of failure of the standby fuel pump to shut off. This AD results from a report of inadvertent operation of a standby fuel pump due to an electrical system malfunction. We are issuing this AD to prevent this inadvertent operation, which could result in inadvertent fuel transfer by the left or right wing fuel system and subsequent over-limit fuel imbalance between the left and right wing fuel loads. This imbalance could affect lateral control of the airplane which could result in reduced controllability.
2021-21-03: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109A, A109A II, A109C, A109E, A109K2, A109S, AW109SP, A119, and AW119 MKII helicopters. This AD was prompted by a report of damage to a rigid connecting link (rod), and loosening of the nut on the upper rod end. This AD requires a visual inspection of the affected rods for damage, cracks, or abnormal play, and corrective actions if necessary, as specified in a European Aviation Safety Agency (now 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.
93-15-02 R2: 93-15-02 R2 FAIRCHILD AIRCRAFT: Amendment 39-9689; Docket No. 93-CE-35-AD. Revises AD 93-15-02 R1, Amendment 39-9180. Applicability: All SA226 and SA227 series airplanes (all models and serial numbers), certificated in any category, that are equipped with a Simmonds-Precision pitch trim actuator, part number (P/N) DL5040M5 or P/N DL5040M6. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition hasnot been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated in the body of this AD, unless already accomplished. To prevent failure of the pitch trim actuator, which could result in the horizontal stabilizer going nose-down or jamming, accomplish the following: NOTE 2: The paragraph structure of this AD is as follows: Level 1: (a), (b), (c), etc. Level 2: (1), (2), (3), etc. Level 3: (i), (ii), (iii), etc. Level 2 and Level 3 structures are designations of the Level 1 paragraph they immediately follow. (a) Accomplish the following at the times specified in the chart in paragraph (b) of this AD: (1) Initial and repetitive inspections: Measure the freeplay (inspection) of the pitch trim actuator and inspect the actuator for rod slippage in accordance with the INSTRUCTIONS section of Fairchild Aircraft SA226 Series Service Letter (SL) 226-SL-005, and Fairchild Aircraft SA227 Series SL227-SL-011, both Issued: April 8, 1993, Revised: May 22, 1996, as applicable. (2) Initial and repetitive replacements: Replace the pitch trim actuator with one of the following in accordance with the instructions in the applicable maintenance manual at the times specified in the Initial Inspection and Repetitive Inspection columns of the chart in paragraph (b) of this AD and, replace the pitch trim actuator prior to further flight if certain freeplay limitations that are specified in the service letters are exceeded or if rod slippage is found. (i) A new Simmonds-Precision actuator, P/N DL5040M5 or DL5040M6. (ii) A pitch trim actuator with an overhauled, zero-timed part of the same design and part number. (iii) A new actuator of improved design, P/N 27-19008-001 or 27- 19008-002. This replacement eliminates the repetitive inspection and replacement requirements of this AD, and may be accomplished at any time to eliminate the inspection requirement of thisAD. (b) The following chart presents the initial and repetitive inspection and replacement compliance times of this AD: Condition Initial Inspection Repetitive Inspection Repetitive Replacement With an original Simmonds-Precision actuator, P/N DL5040M5, installed. Upon accumulating 3,000 hours TIS on a Simmonds-Precision P/N DL5040M5 actuator or within 50 hours TIS after April 17, 1995 (the effective date of AD 93-15-02 R1), whichever occurs later. Every 250 hours TIS after initial inspection until accumulating 5,000 hours TIS on the actuator or 500 hours TIS after the last inspection required by AD 93-15-02 R1, whichever occurs later. Initially upon accumulating 5,000 hours TIS on the actuator or 500 hours TIS after the initial inspection, whichever occurs later, and thereafter as indicated below. With a replacement Simmonds-Precision actuator, P/N DL5040M5, installed. Initially upon accumulating 5,000 hours TIS on the new actuator. Every 300 hours TIS after the initial inspection until accumulating 6,500 hours TIS on the actuator. Upon accumulating 6,500 hours TIS on the actuator. With a replacement Simmonds-Precision actuator, P/N DL5040M6, installed. This part can be new, modified from a P/N DL5040M5 actuator or overhauled and zero-timed. Initially upon accumulating 7,500 hours TIS on the new or modified actuator. Every 300 hours TIS after the initial inspection until accumulating 9,900 hours TIS on the actuator. Upon accumulating 9,900 hours TIS on the actuator. With a replacement P/N DL5040M5 actuator installed that was overhauled and zero-timed where both nut assemblies, P/N AA56142, were replaced with new assemblies during overhaul. Initially upon accumulating 5,000 hours TIS on the overhauled actuator. Every 300 hours TIS after the initial inspection until accumulating 6,500 hours TIS on the actuator. Upon accumulating 6,500 hours TIS on the actuator. With a replacement P/N DL5040M5 actuator installed that was overhauled and zero-timed where both nut assemblies, P/N AA56142, were not replaced with new assemblies during overhaul. Initially upon accumulating 3,000 hours TIS on the overhauled actuator. Every 250 hours TIS after the initial inspection until accumulating 5,000 hours TIS on the actuator. Upon accumulating 5,000 hours TIS on the actuator. With a pitch trim actuator of improved design installed, P/N 27-19008-001 or 27- 19008-002. No action necessary No action necessary No action necessary (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office (ACO), FAA, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth ACO. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth ACO. (e) The inspections and modification required by this AD shall be done in accordance with Fairchild Aircraft SA226 Series Service Letter 226-SL-005, and Fairchild Aircraft SA227 Series Service Letter 227-SL-011, both Issued: April 8, 1993, Revised: May 22, 1996, as applicable. This incorporation by reference is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Field Support Engineering, Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279- 0490. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment (39-9689) revises AD 93-15-02 R1, Amendment 39-9180. (g) This amendment becomes effective on July 25, 1996.