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2015-02-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes; Model DC-10-10, DC-10-10F, DC- 10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40 and DC-10-40F airplanes; Model MD-10-10F and MD-10-30F airplanes; Model DC-9-81 (MD- 81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; Model MD-88 airplanes; and Model MD-90-30 airplanes. This AD was prompted by reports of latent air data transducer degradation. This AD requires revising the maintenance or inspection program, as applicable, to incorporate special compliance items (SCIs). We are issuing this AD to prevent erroneous air data information, which could lead to a mid- air collision within reduced vertical separation minimum (RVSM) airspace.
2000-08-02: This amendment adopts a new airworthiness directive (AD) applicable to Agusta Model A109A, A109AII, and A109C helicopters. This action requires inspecting the main transmission to determine if certain Gleason crowns are installed and replacing any unairworthy Gleason crown with an airworthy Gleason crown. This amendment is prompted by the discovery of a cracked Gleason crown during an unscheduled transmission inspection prompted by abnormal noises coming from the transmission during main rotor deceleration. The actions specified in this AD are intended to prevent failure of the main transmission, loss of rotor drive, and subsequent loss of control of the helicopter.
2015-02-09: We are adopting a new airworthiness directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. 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 cracking found in the engine exhaust pipe. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-07-20: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires electrical resistance measurements of the ground studs of the No. 2 generator in the electrical power center of the center accessory compartment for proper electrical bonding and of the ground studs and circuit breaker terminations in the forward cargo compartment to detect looseness and for proper electrical bonding; and corrective actions, if necessary. This amendment is prompted by an incident of charred insulation blankets in the forward cargo compartment in the area of the external ground power receptacle and the galley external power circuit breakers, and another incident of a No. 2 "generator off" alert while the generator was still on line. The actions specified by this AD are intended to prevent arcing and overheating of terminals and consequent smoke and fire in the forward cargo compartment due to improper bonding of groundstuds in the forward cargo compartment and in the electrical power center and due to improper installation of circuit breaker terminations.
93-19-08: 93-19-08 AEROSPATIALE: Amendment 39-8707. Docket 93-NM-13-AD. Supersedes AD 91-08-10, Amendment 39-6953. Applicability: Model ATR42-200 and -300 series airplanes on which Modification 03226 (as described in Aerospatiale Service Bulletin ATR42-32-0040, dated February 24, 1992, and Revision 1, dated January 18, 1993) has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: Paragraphs (a), (a)(1), and (a)(2) of this AD restate the initial and repetitive inspection requirements of AD 91-08-10, Amendment 39-6953, paragraphs A., A.1., and A.2. As allowed by the phrase, "unless accomplished previously," if the initial and repetitive inspections required by AD 91-08-10 have been accomplished previously, paragraphs (a), (a)(1), and (a)(2) of this AD do not require that those inspections be repeated. To prevent inadvertent retraction of the main landing gear (MLG), accomplish the following:(a) Perform an ultrasonic inspection of the MLG side brace lower arm in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 1, dated February 15, 1991, and Messier-Bugatti Service Bulletin 631-32-070, Revision 1, dated February 12, 1991, at the thresholds given in paragraphs (a)(1) and (a)(2) of this AD. Repeat the ultrasonic inspections thereafter at intervals not to exceed 1,000 landings until the inspection required by paragraph (b) of this AD is accomplished. (1) For airplanes that have accumulated 6,000 or more total landings on either the left or right MLG side brace lower arms as of May 6, 1991 (the effective date of AD 91- 08-10, Amendment 39-6953): Perform the initial inspection prior to the accumulation of 8,000 total landings on either the left or right MLG side brace lower arms, or within 14 days after May 6, 1991 (the effective date of AD 91-08-10, Amendment 39-6953), whichever occurs later. (2) For airplanes that have accumulated less than 6,000 total landings on either the left or right MLG side brace lower arms as of May 6, 1991 (the effective date of AD 91- 08-10, Amendment 39-6953): Perform the initial inspection prior to the accumulation of 6,000 total landings on either the left or right MLG side brace lower arms, or within 90 days after May 6, 1991 (the effective date of AD 91-08-10, Amendment 39-6953), whichever occurs later. (b) For those airplanes that previously have accomplished the ultrasonic inspections in accordance with paragraph (a) of this AD: Within 1,000 landings after the last inspection required by paragraph (a) of this AD, or within 90 days after the effective date of this AD, whichever occurs later, perform the ultrasonic inspection procedure in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 3, dated December 12, 1991. Repeat this inspection thereafter at intervals not to exceed 1,000 landings. Accomplishment of the requirements of this paragraph constitutes terminating action for the repetitive ultrasonic inspections in accordance with Revision 1 of that service bulletin required by paragraph (a) of this AD. (c) For those airplanes that have not previously accomplished the ultrasonic inspections in accordance with paragraph (a) of this AD: Prior to the accumulation of 6,000 total landings on either the left or right MLG side brace lower arms, or within 90 days after the effective date of this AD, whichever occurs later, perform an ultrasonic inspection of the MLG side brace lower arm in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 3, dated December 12, 1991. Repeat this inspection thereafter at intervals not to exceed 1,000 landings. (d) If any ultrasonic inspection result exceeds the acceptance criteria specified in Aerospatiale Service Bulletin ATR42-32-0036, Revision 1, dated February 15, 1991, or Revision 3, dated December 12, 1991, prior to further flight, replace the discrepant MLG side brace lowerarm with a new or serviceable part, in accordance with either service bulletin. Following replacement of discrepant parts, continue to repeat the ultrasonic inspection procedure in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 3, dated December 12, 1991, at intervals not to exceed 1,000 landings. (e) Prior to the accumulation of 15,000 total landings, or within 12 months after the effective date of this AD, whichever occurs later, install Modification 03226, in accordance with Aerospatiale Service Bulletin ATR42-32-0040, dated February 24, 1992, or Revision 1, dated January 18, 1993. Installation of Modification 03226 constitutes terminating action for the repetitive ultrasonic inspections of the MLG side brace lower arm required by this AD. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The actions shall be done in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 1, dated February 15, 1991; Aerospatiale Service Bulletin ATR42-32-0036, Revision 3, dated December 12, 1991; Aerospatiale Service Bulletin ATR42-32-0040, dated February 24, 1992; Aerospatiale Service Bulletin ATR42-32-0040, Revision 1, dated January 18, 1993; and Messier-Bugatti Service Bulletin 631-32-070, Revision 1, dated February 12, 1991. The incorporation by reference of Aerospatiale Service Bulletin ATR42-32-0036, Revision 1, dated February 15, 1991, and Messier-Bugatti Service Bulletin 631-32-070, Revision 1, dated February 12, 1991, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of May 6, 1991 (56 FR 14462, April 10, 1991). The incorporation by reference of the remainder of the service documents listed above 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on December 22, 1993.
2000-06-12: This amendment adopts a new airworthiness directive (AD), applicable to Turbomeca Artouste III series turboshaft engines, that requires smoke emissions checks after every ground engine shutdown. If smoke is detected, this AD would require inspecting for fuel flow. If fuel flow is not detected, the engine may have injection wheel cracks, which would require removing the engine from service for repair. If fuel flow is detected, the engine may have a malfunctioning electric fuel cock, which would require removing the electric fuel cock from service and replacing it with a serviceable part. This action is prompted by reports of cracked injection wheels. The actions specified by this AD are intended to prevent injection wheel cracks, which could result in an in-flight engine shutdown.
85-22-06 R1: 85-22-06 R1 FAIRCHILD AIRCRAFT CORPORATION (formerly Swearingen Aviation Corporation): Amendment 39-5158 as revised by Amendment 39-6675. Docket No. 85-CE-11- AD. Applicability: Models SA226-T (Serial Numbers (S/N) T201 thru T275, T277 thru T291); SA226-AT (S/N AT001 thru AT419, AT003E, AT038E, AT062E, AT064E); SA226-TC (S/N TC201 thru TC419, TC208E, TC211E, TC211EE, TC211EEE, TC211EEEE, TC222E, TC227E, TC228E, TC229E, TC234E, TC237E, TC238E, TC239E, TC331E, TC334E;) SA226- T(B) (S/N T(B)276, T(B)292 thru T(B)417, T(B)303E); SA227-AC (S/N AC406, AC415, AC416, AC420 thru AC601, AC603); SA227-TT (S/N TT421 thru TT535, TT537 thru TT541); SA227-AT (S/N AT423 thru AT526, AT528, AT530 thru AT535, AT537 thru AT585) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD unless previously accomplished in accordance with AD 85-22-06, Amendment 39-5158, and thereafter as indicated below, at thenext scheduled interval. To assure proper operation of the Stall Avoidance System (SAS), accomplish the following: (a) Except as noted in paragraph (b) of this AD, modify and/or inspect the applicable airplanes in accordance with the manufacturer's service bulletins, at the initial and repetitive time- in-service intervals, as specified for the model and serial numbered airplanes, set forth in Table 1 below: Table 1 When performing a functional check of the SAS Servo (Bendix only) allow the servo to run for a minimum of 5 minutes prior to accomplishing the functional check. If the temperature is below 0oC, allow the servo (Bendix only) to run for a minimum of 10 minutes prior to accomplishing the functional check. Model Serial Number Fairchild Service Bulletin Compliance Interval Hrs-Time in Service SA226-T T201 thru T275 226-A27-024 one time only T277 thru T291 226-A27-028 one time only 226-27-038 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 500 Para. 2.D. 800 SA226-AT AT001 thru AT073, 226-A27-024 one time only AT003E, AT038E, AT062E, AT064E 226-27-038 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 500 Para. 2.D. 800 AT074 thru AT419 226-27-038 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 500 Para. 2.D. 800 SA226-TC TC201 thru TC314, 226-A27-024 one time only TC208E, TC211E, TC211EE, TC211EEE, 226-27-038 TC211EEEE, TC222E Para. 2.A 200 TC227E, TC228E Para. 2.B 500 TC229E, TC234E, Para. 2.C. 500 TC237E, TC238E Para. 2.D. 800 TC239E TC315 thru TC419 226-27-038 TC331E, TC334E Para. 2.A 200 Para. 2.B 500 Para. 2.C. 500 Para. 2.D. 800 SA226-T(B) T(B)276, 226-A27-028 one time only T(B)292 thru 226-A27-033 one time only T(B)391 226-27-037 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 T(B)392 thru 226-27-033 one time only T(B)417, 226-27-037 T(B)303E Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 SA227-AC AC420 thru AC551 227-A27-004 one time only 227-27-006 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 AC406, AC415, 227-27-006 AC416, AC552 thru Para. 2.A 200 AC601, AC603 Para. 2.B 500 Para. 2.C. 2000 SA227-TT TT421, thru TT526, 227-A27-004 one time only TT528, TT530 thru 227-27-006 TT535 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 TT527, TT529, 227-27-004 one time only TT536 thru TT541 SA227-AT AT423 thru AT526 227-A27-004 one time only AT528, AT530 thru 227-27-006 AT535, AT537 thru Para. 2.A 200 AT549 Para. 2.B 500 Para. 2.C. 2000 AT550 thru AT585 227-27-006Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 (b) Modify and/or inspect those Model SA226 and SA227 series airplanes which are equipped with the Conrac SAS system (per STC SA4725SW) in accordance with Table 2 as follows: Table 2 When performing a functional check of the SAS Servo (Bendix only) allow the servo to run for a minimum of 5 minutes prior to accomplishing the functional check. If the temperature is below 0oC, allow the servo (Bendix only) to run for a minimum of 10 minutes prior to accomplishing the functional check. Model Serial Number Fairchild Service Bulletin Compliance Interval Hrs-Time in Service 226-27-037 Para. 2.A 200 Para. 2.B 500 Any applicable Model SA226 and SA227 airplanes incorporating STC SA4725SW Para. 2.C 2000 NOTE 1: The current issue date and subject matter of the Service Bulletins specified in Table 1 are as follows: (1) 226-A27-024 - "Flight controls - Elevator," dated 11/13/79. (2) 226-A27-028 - "Flight controls - Rudder and Elevator," dated 12/11/80. (3) 226-A27-033 - "Flight controls - Elevator," dated 12/3/82, revised 1/6/83. (4) 227-A27-004 - "Flight controls - Elevators," dated 12/3/82, revised 1/6/83. (5) 226-27-037 - "Conrac SAS System - Inspection and Recalibration," dated 2/15/85, revised 4/15/88. (6) 226-27-038 - "Rosemount SAS System - Inspection and Recalibration," dated 2/15/85, revised 1/16/90. (7) 227-27-006 - "Conrac SAS System - Inspection and Recalibrations," dated 2/15/85, revised 4/15/88. (c) If the inspections specified in paragraphs (a) and (b) of this AD necessitate replacement of the servo pusher, assure that the replacement unit is either new, overhauled, or meets the limits of the electrical test specified in the above revised service bulletins. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, Fort Worth, Texas 76193-0150; Telephone (817) 624-5150. NOTE 2: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Airplane Certification Office, Fort Worth, Texas. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Fairchild Aircraft Corporation, P.O. Box 790490, San Antonio, Texas 78279- 0490; or may examine these documents at the FAA, Central Region, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 85-22-06 R1 revises AD 85-22-06, Amendment 39-5158. This amendment (39-6675, AD 85-22-06 R1) becomes effective on October 19, 1990.
2000-07-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive inspections to detect cracking of the lower corners of the door frame and cross beam of the forward cargo door, and corrective actions, if necessary. This AD also requires eventual modification of the outboard radius of the lower corners of the door frame and reinforcement of the cross beam of the forward cargo door, which would constitute terminating action for the repetitive inspections. This amendment is prompted by reports indicating that fatigue cracks have been detected in the lower corners of the door frame and cross beam of the forward cargo door. The actions specified by this AD are intended to prevent fatigue cracking of the lower corners of the door frame and cross beam of the forward cargo door, which could result in rapid depressurization of the airplane.
49-07-03: 49-07-03 CONVAIR: Applies to All BT-13 Series Aircraft. Compliance required not later than April 1, 1949. Several accidents have occurred in the above model aircraft from engine stoppage on take-offs and landings when operating on the right tank standpipe outlet with the fuel in the tank down to the level of the standpipe. Such engine stoppages have occurred because pilots not fully familiar with the fuel system have misinterpreted the right tank fuel gage as indicating total available fuel quantity with selector valve on Right Hand Main (standpipe) position, unaware that the change to Reserve or Left Hand Main position must be made before the fuel level in the right tank drops to 17 gallons. To preclude the possibility of pilot error with regard to the foregoing, the following placard shall be installed with each cockpit: "CAUTION: Unless Right Tank is full, use Reserve or Left Tank for Takeoff and Landing."
2000-07-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires repetitive structural inspections of certain aging airplanes, and repair, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design service goal. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the affected airplanes. This AD relates to the recommendations of the Airworthiness Assurance Task Force assigned to review Model 727 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished.
81-18-08 R3: 81-18-08 R3 BEECH: Amendment 39-4196 as amended by Amendments 39-4233 and 39-4235 is further amended by Amendment 39-4273. Applies to Models 99, 99A, A99A and A99 (Serial Numbers U-1 through U-145 and U-147) and Model B99 (Serial Numbers U-146, U-148 and subsequent) airplanes certificated in all categories. COMPLIANCE: Required as indicated, unless previously accomplished. To preclude operations with inoperative systems which are required to be functioning for safe flight, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: A) Make the following revisions to the applicable approved Airplane Flight Manual (AFM) and operate the airplane in accordance with the revised manual. 1. In P/N 99-590012-1D, FAA Approved Airplane Flight Manual for Beechcraft 99 Airliner: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 35" and the entry "Configuration Deviation List...4-44." b) Remove and destroy pages 4-35 through 4-46. 2. In P/N 99-590019-1C, FAA Approved Flight Manual for the Beechcraft 99A Airliner: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 31" and the entry "Configuration Deviation List...4-40." b) Remove and destroy pages 4-31 through 4-42. 3. In P/N 99-590019-13, FAA Approved Flight Manual for the Beechcraft 99 or 99A Airliners which have been modified in accordance with either Beech Kit 99-5014-1 or 99-5014-3, as applicable: a) Delete from page 4-1 the entry "minimum Equipment List...4- 33" and the entry "Configuration Deviation List...4-44." b) Remove and destroy pages 4-33 through 4-44. 4. In P/N 99-590023-1, FAA Approved Flight Manual for the Beechcraft A99A Airliner: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 33" and the entry "Configuration Deviation List...4-42." b) Remove and destroy pages 4-33 through 4-44. 5. In P/N 99-590024-1, FAA Approved Flight Manual for the Beechcraft A99 Airliner: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 29" and the entry "Configuration Deviation List...4-38." b) Remove and destroy pages 4-29 through 4-40. 6. In P/N 99-590026-1, FAA Approved B99 Airliner Airplane Flight Manual: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 33" and the entry "Configuration Deviation List...4-42." b) Remove and destroy pages 4-33 through 4-44. B) In the applicable FAA Approved Airplane Flight Manual identified in paragraph A of this AD: 1. In Section 1, Limitations, delete in its entirety, the paragraph which reads as follows: "This airplane is approved for the following types of operation when required equipment is installed and operational as defined herein. 1. VFR day and night. 2. IFR day and night. 3. Known icing conditions. 4. FAR 135 operations when all pertinent limitations and performance considerations are complied with. 5. FAR 91 operations when all pertinent limitations and considerations are complied with." 2. In Section 1, Limitations, insert the Kinds of Operations Equipment List (KOEL), a copy of which is attached hereto and identified as Appendix I, Revision 1, dated September 25, 1981, for temporary insertion until an identical permanent list is provided by the manufacturer, and operate the airplane in accordance with that Equipment List. C) This AD may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person provided the airplane is not used in air carrier service. An entry must be made in the Aircraft Maintenance Records indicating compliance with this AD. Amendment 39-4196 became effective December 2, 1981. Amendment 39-4233 became effective upon receipt. This Amendment 39-4273 becomes effective upon receipt and extendsthe effective date of Amendment 39-4235 to February 16, 1982. 81-18-08 APPENDIX I KINDS OF OPERATIONS EQUIPMENT LIST (KOEL) This airplane may be operated in day or night VFR, day or night IFR and icing conditions when the appropriate equipment is installed and operable. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated and must be installed and operable for the particular kind of operation indicated. However, certain operations may be authorized with certain listed equipment and/or systems inoperative under certain conditions and under provisions defined by a current Minimum Equipment List (MEL) approved by the FAA which is dated concurrently with or after this AFM revision and authorized under an operating regulation which provides for use of an MEL. VFR Day VFR Night IFR Day IFR Night Icing Electrical Power 1. Battery 1 11 1 1 2. D.C. Generator 2 2 2 2 2 3. D.C. Loadmeter 2 2 2 2 2 4. D.C. Generator Warning Light 2 2 2 2 2 5. Invertor 2 2 2 2 2 6. Invertor Warning Light 1 1 1 1 1 7. Feeder Limiter Warning Light 1 1 1 1 1 8. Battery Monitor System 1 1 1 1 1 9. AC Volt Meter (If installed) 1 1 1 1 1 Equipment/Furnishings 1. Exit Signs - Self-Illuminated 4 4 4 4 4 Fire Protection 1. Engine Fire Detector System 2 2 2 2 2 2. Firewall Fuel Shutoff System 2 2 2 2 2 Icing Flight Controls 1. Flap System 1 1 1 1 1 2. Flap Position Indicator 1 1 1 1 1 3. Horizontal Stabilizer Trim System - Main 1 1 1 1 1 4. Horizontal Stabilizer Trim System - Standby 1 1 1 1 1 5. Stabilizer out-of-trim Aural Warning Indicator 1 1 1 1 1 6. Trim-in-Motion Aural Indicator 1 1 1 1 1 7. Horizontal Stabilizer Position Indicator 1 1 1 1 1 8. Stall Warning Horn 1 1 1 1 1 9. Trim Tab Indicator - Rudder 1 1 1 1 1 10. Trim Tab Indicator Aileron 1 1 1 1 1 Fuel 1. Fuel Boost Pumps (4 are installed) PER AFM Limitations 2. Fuel Quantity Indicator 2 2 2 2 2 3. Fuel Quantity Gauge Selector Switch 1 1 1 1 1 4. Nacelle Not-Full Warning Light 2 2 2 2 2 5. Crossfeed Light 1 1 1 1 1 6. Fuel Boost Pump Low Pressure Warning Light 2 2 2 2 2 7. Fuel Flow Indicator 2 2 2 2 2 8. Jet Transfer Pump 2 2 2 2 2 Ice And Rain Protection 1. Engine Inlet Scoop Deicer Boot 2 2 2 2 2 2. Indicator - Propeller/Inlet Deicer 1 1 1 1 1 3. Engine Inertial Anti-Icing System 2 2 2 2 2 4. Pitot Heat 0 0 2 2 2 5. Alternate Static Air Source 0 0 1 1 1 6. Engine Auto-Ignition System (If Installed) 2 2 2 2 2 7. Propeller Deicer System 0 0 0 0 1 8. Windshield Heat (Left) 0 0 0 0 1 9. Surface Deicer System 0 0 0 0 1 10. Stall Warning Mounting Plate Heater 0 0 0 0 1 11. Wing Ice Light (Left) 0 0 0 0 1 12. Windshield Wiper (Left) 1 1 1 1 1 Landing Gear 1. Landing Gear Position Indicator Lights 3 3 3 3 3 2. Landing Gear Handle Light 1 1 1 1 1 3. Flap-Controlled Landing Gear Aural Warning 1 1 1 1 1 4. Nose Steering Disconnect Actuator 1 1 1 1 1 5. Landing Gear Hydraulic Pump (If Installed) 1 1 1 1 1 Lights 1. Cockpit and Instrument (Required Illumination) 0 1 0 1 0 2. Anti-Collision 0 2 0 2 0 3. Landing Light Bulbs (any 2 of 4 bulbs) 0 2 0 2 0 4. Position Lights 0 3 0 3 0 5. Cabin Door Warning Light (Note) 1 1 1 1 1 6. Baggage Door Warning Light (Note) 1 1 1 1 1 Note: Where combined into one cabin/baggage annunciator - one (1) is required for all conditions. Navigation (Instrument) 1. Altimeter (left) 1 1 1 1 1 2. Airspeed (left) 1 1 1 1 1 3. Magnetic Compass 1 1 1 1 1 4. Outside Air Temperature 1 1 1 1 1 Vacuum System 1. Suction or Pressure Gauge 1 1 1 1 1 2. Instrument Air System 1 1 1 1 1 Propeller 1. Autofeather System 2 2 2 2 2 2. Low Pitch light (PT6A-20 Engine Only) 2 2 2 2 2 3. Do not Reverse Warning Light 1 1 1 1 1 4. Propeller Reversing 2 2 2 2 2 Engine Indicating 1. Tachometer Indicator (Propeller) 2 2 2 2 2 2. Tachometer Indicator (Gas Generator) 2 2 2 2 2 3. ITT Indicator 2 2 2 2 2 4. Torque Indicator 2 2 2 2 2 Engine Oil 1. Oil Temperature Indicator 2 2 2 2 2 2. Oil Pressure Indicator 2 2 2 2 2 3. Low Oil Pressure Light 2 2 2 2 2 4. Engine Chip Detector System 2 2 2 2 2 Note 1: The zeros (0) used in the above list mean that the equipment and/or system was not required for type certification for that kind of operation. Note 2: The above system and equipment list is predicted on a crew of one pilot. Note 3: Equipment and/or systems in addition to those listed above may be required by operating regulations (FAR Part 135) that may specify certain items of equipment for more than one pilot. Note 4: The above system and equipment list does not include specific flight instruments and communications/navigation equipment required by the FAR Part 91 and 135 operating requirements.
2015-01-02: We are adopting a new airworthiness directive (AD) for certain Mitsubishi Heavy Industries, Ltd. Models MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, and MU-2B-60 airplanes. 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 stress corrosion cracking in the flanges of the airframe at stations 4610 and 5605. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-07-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires replacement of the clevis ends on the tie rods for the center stowage bin supports with improved clevis ends. This amendment is prompted by a report that, under ultimate load conditions, the aluminum clevis ends on the tie rods for the center stowage bin supports can break. The actions specified by this AD are intended to prevent broken tie rods, which could result in the center stowage bins dropping onto the passenger seats below, causing possible injury to the occupants.
2000-07-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -200PF series airplanes, that requires repetitive detailed visual inspections to detect loose fuse pins in the outboard beam attachment and forward trunnion support on the main landing gear (MLG) and to detect corrosion on the structure adjacent to the fuse pin; and corrective actions, if necessary. This amendment also requires eventual replacement of the fuse pins with new corrosion resistant steel (CRES) fuse pins, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report of damaged fuse pins caused by corrosion. The actions specified by this AD are intended to prevent corroded fuse pins, which could result in the MLG separating from the wing, and consequent damage to the airplane and possible rupture of the wing fuel tank.
2000-07-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of wing center box angle fittings at frame 47. 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 prevent reduced structural integrity of the wing center box angle fittings at frame 47 due to fatigue cracking.
95-14-05: 95-14-05 MITSUBISHI HEAVY INDUSTRIES, LTD: Amendment 39-9297. Docket 94-NM- 167-AD. Applicability: All Model YS-11 and -11A airplanes, certificated in any category. 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 use the authority provided in paragraph (h) of this AD 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 airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. NOTE 2: This AD references MHI Publication No. YS-MR-301, "YS-11 Corrosion Control Program," dated November 1, 1993 (hereafter referred to as "the Document"), for basic tasks, definitions of corrosion levels, compliance times, and reporting requirements. In addition, this AD specifies inspection and reporting requirements beyond those included in the Document. Where there are differences between the AD and the Document, the AD prevails. NOTE 3: As used throughout this AD, the term "the FAA" is defined differently for different operators, as follows: For those operators complying with paragraph (a) of this AD, "the FAA" is defined as "the Manager of the Los Angeles Aircraft Certification Office (ACO)." For those operators operating under Federal Aviation Regulation (FAR) Part 121 or 129, and complying with paragraph (b) of this AD, "the FAA" is defined as "the cognizant Principal Maintenance Inspector (PMI)." For those operators operating under FAR Part 91 or 125, and complying with paragraph (b) of this AD, "the FAA" is defined as "the cognizant Maintenance Inspector at the appropriate FAA Flight Standards office." To preclude degradation of the structural capabilities of the airplane due to the problems associated with corrosion, accomplish the following: (a) Except as provided in paragraph (b) of this AD, within a date two years after the effective date of this AD, complete each of the basic tasks specified in Section 4.3 of the Document in accordance with the procedures specified in the Document and the schedule specified in Figure 5 of the Document. Thereafter, repeat each basic task at a time interval not to exceed the repeat interval specified in Section 4 of the Document for that task. NOTE 4: A "basic task," as defined in Section 4 of the Document, includes inspections; procedures for a corrective action, including repairs, under identified circumstances; application of sealants or corrosion inhibitors; and other follow-on actions. NOTE 5: Basic tasks completed in accordance with the Document before the effective date of this AD may be credited for compliance with the initial basic task requirements of this paragraph. NOTE 6: Where non-destructive inspection (NDI) methods are employed, in accordance with Section 4 of the Document, the standards and procedures used must be acceptable to the Administrator in accordance with FAR Section 43.13. (b) As an alternative to the requirements of paragraph (a) of this AD: Within one year after the effective date of this AD, revise the FAA-approved maintenance/inspection program to include the corrosion control program specified in the Document; or to include an equivalent program that is approved by the FAA. (1) Any operator complying with paragraph (b) of this AD may use an alternativerecordkeeping method to that otherwise required by FAR Section 91.417 or Section 121.380 for the actions required by this AD, provided it is approved by the FAA and is included in a revision to the FAA-approved maintenance/inspection program. (2) Subsequent to the accomplishment of the initial basic task, any extensions of repeat intervals specified in the Document must be approved by the FAA. (c) To accommodate unanticipated scheduling requirements, it is acceptable for a repeat interval to be increased by up to 10%, but not to exceed 6 months. The FAA must be informed, in writing, of any such extension within 30 days after such adjustment of the schedule. (d) (1) If, as a result of any inspection conducted in accordance with paragraphs (a) or (b) of this AD, Level 3 corrosion is determined to exist in any airplane area, accomplish either paragraph (d)(1)(i) or (d)(1)(ii) within 7 days after such determination: (i) Submit a report of that determination to theFAA and complete the basic task in the affected aircraft zones on all Model YS-11/-11A series airplanes in the operator's fleet; or (ii) Submit to the FAA for approval one of the following: (A) A proposed schedule for performing the basic tasks in the affected aircraft zones on the remaining Model YS-11/-11A series airplanes in the operator's fleet, which is adequate to ensure that any other Level 3 corrosion is detected in a timely manner, along with substantiating data for that schedule; or (B) Data substantiating that the Level 3 corrosion found is an isolated occurrence. NOTE 7: Notwithstanding the provisions of Section 1.3 of the Document, which would permit corrosion that otherwise meets the definition of Level 3 corrosion (i.e., which is determined to be a potentially urgent airworthiness concern requiring expeditious action) to be treated as Level 1 if the operator finds that it "can be attributed to an event not typical of the operator's usage of other airplanes in the same fleet," this paragraph requires that data substantiating any such finding be submitted to the FAA for approval. (2) The FAA may impose schedules other than those proposed, upon finding that such changes are necessary to ensure that any other Level 3 corrosion is detected in a timely manner. (3) Within the time schedule approved under paragraph (d)(1) or (d)(2) of this AD, accomplish the basic tasks in the affected aircraft zones of the remaining Model YS-11/-11A series airplanes in the operator's fleet. (e) If, as a result of any inspection after the initial inspection conducted in accordance with paragraph (a) or (b) of this AD, it is determined that corrosion findings exceed Level 1 in any area, within 60 days after such determination, implement a means, approved by the FAA, to reduce future findings of corrosion in that area to Level 1 or better. (f) Before any operator places into service any airplane subject to the requirements of this AD, a schedule for the accomplishment of basic tasks required by this AD must be established in accordance with paragraph (f)(1) or (f)(2) of this AD, as applicable: (1) For airplanes previously maintained in accordance with this AD, the first basic task in each aircraft zone to be performed by the new operator must be accomplished in accordance with the previous operator's schedule or with the new operator's schedule, whichever would result in the earlier accomplishment date for that task. After each basic task has been performed once, each subsequent task must be performed in accordance with the new operator's schedule. (2) For airplanes that have not been previously maintained in accordance with this AD, the first basic task for each aircraft zone to be performed by the new operator must be accomplished prior to further flight or in accordance with a schedule approved by the FAA. (g) Reports of Level 2 and Level 3 corrosion must be submitted at least every three months to Mitsubishi Heavy Industries, Ltd., in accordance with Section 3 of the Document. NOTE 8: Reporting of Level 2 and Level 3 corrosion found as a result of any opportunity inspections is highly desirable. (h) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. NOTE 9: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (i) 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. (j) Reports of inspection results required by this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (k) The actions shall be done in accordance with MHI Publication No. YS-MR-301, "YS-11 Corrosion Control Program," dated November 1, 1993. This incorporation by reference was 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 Nihon Aeroplane Manufacturing, Toranomon Daiichi, Kotohire-Cho, Shiba, Minato-Ku, Tokyo, Japan. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (l) This amendment becomes effective on August 7, 1995. FOR FURTHER INFORMATION CONTACT: William Roberts, Aerospace Engineer, Airframe Branch, ANM-120L, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (310) 627-5228; fax (310) 627-5210.
2022-19-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A321-251N, A321-251NX, A321-252NX, A321-253N, A321-253NX, and A321-271NX airplanes. This AD was prompted by a determination that the quick release pin that is installed on the upper attachment of certain Smart HS-L41 and Smart HS-L42 lavatories is too short to lock on the bracket. This AD requires replacement of the quick release pin installed on the upper attachment of affected lavatories, as specified in a 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.
2014-26-06: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes, and Model ATR72-212A airplanes. This AD was prompted by a report that, during an inspection of an airplane on the production line, interference was detected between the electrical harness and a bonding lead due to an incorrect installation of the affected bonding lead. This AD requires a detailed inspection for damage or incorrect routing of the bonding lead routing above the 120VU shelf, and if any damage or incorrect routing is found, repairing damage or modifying the bonding lead routing. We are issuing this AD to detect and correct installation of the bonding lead, which could cause arcing and chafing, and could possibly result in an uncontrolled fire.
2000-06-09: This amendment adopts a new airworthiness directive (AD), applicable to Turbomeca Arrius 1A series turboshaft engines, that requires installation of module TU63, which provides a separate supply of fuel for one of the 10 main injectors of the fuel injection system. This action is prompted by reports of unexpected power loss during test flights. The actions specified by this AD are intended to prevent unexpected power loss, which could result in an uncommanded in-flight engine shutdown, autorotation, and forced landing.
81-24-06: 81-24-06 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4260. Applies to Models IO-520, TSIO-520 and GTSIO-520 (except GTSIO-520-F and K) engines equipped with engine driven fuel pumps serial numbers I0178XX through A0280XX, factory new or rebuilt engines which were assembled between September 1, 1978, through July 31, 1980, or fuel pumps which were replaced during that time. The first characters of the fuel pump serial numbers reflect the date of manufacture. The first letter designates the month of manufacture starting with "A" for January, "B" for February, etc. The second and third digits designate the day of build (01 thru 31). The fourth and fifth digits indicate the year of build. Subsequent digits indicate manufacturing sequence number of pump on a given day. Compliance required as indicated unless already accomplished. To prevent possible fuel leakage and potential fire hazard, accomplish the following: (a) Within 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours time in service until (b) is accomplished, visually check the fuel pump for evidence of fuel leaks from between the pump segments. If a leak is detected or fuel stains are present, (b) must be accomplished prior to further flight. (b) Within 50 hours time in service after the effective date of this AD, accomplish the following: (1) Remove safety wire from the four fuel pump through bolts. (2) Torque the through bolts evenly in diagonally opposite pairs to 30 in-lbs. ( 1 in-lb.). (3) Resafety wire through bolts. (4) Upon completion of the above steps, place mixture control in "idle cutoff," pressurize the fuel system with the aircraft boost pump, and inspect for fuel leaks. If a fuel leak still exists, overhaul or replace the pump as appropriate. (c) If fuel leaks were present before retorquing the bolts as required in paragraph (b), then during each of the next five preflights, place the mixture control in "idle cutoff," pressurize the fuel system with the aircraft boost pump and check for fuel leaks or evidence of fuel leaks. If evidence of a fuel leak exists, overhaul or replace the pump as appropriate. This paragraph does not apply if the fuel pump was overhauled or replaced due to compliance with paragraph (b). (d) The checks required by paragraphs (a) and (c) may be accomplished by a certificated pilot as authorized by FAR 43.3(h). (e) Make appropriate maintenance record entries. Upon submission of substantiating data through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch may adjust the inspection intervals. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Teledyne Continental Motors Service Bulletin M-80-26, Revision 1, applies to this subject. This amendment becomes effective November 23, 1981.
91-06-05: 91-06-05 CANADAIR, LTD.: Amendment 39-6852. Docket No. 90-NM-186-AD. Applicability: All Model CL-44D4 and CL-44J series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure the continuing structural integrity of these airplanes, accomplish the following: A. Within six months after the effective date of this AD, incorporate a revision into the FAA-approved maintenance inspection program that provides for supplemental maintenance, inspections, replacement, and overhaul requirements of the significant structural items defined in Canadair Document RBD-44-100, "Supplemental Structural Inspection Program," Revision B, dated February 27, 1990. Inspection results, when a crack is detected, must be reported to Canadair. B. Cracked structure detected during the inspection required by paragraph A. of this AD must be repaired or replaced prior to further flight, in accordance with instructions in Canadair Document RBD-44-100, "Supplemental Structural Inspection Program," Revision B, dated February 27, 1990. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, New England Region. NOTE: The request should be submitted directly to the Manager, New York Aircraft Certification Office, ANE-170, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, New York ACO. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Canadair, Ltd., P.O. Box 6087, Station A, Montreal,Quebec H3C 3G9, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, Northwest Mountain Region, 1601 Lind Avenue S.W., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6852, AD 91-06-05) becomes effective on April 8, 1991.
2014-26-02: We are adopting a new airworthiness directive (AD) for Airbus Helicopters (previously Eurocopter France) Model EC155B1 and AS 365 N3 helicopters with a certain automated flight control system (AFCS) and with a Garmin global positioning system (GPS) installed. This AD requires revising the Rotorcraft Flight Manual (RFM) to prohibit using the autopilot coupled with a Localizer/Instrument Landing System (LOC/ ILS) or Very High Frequency Omnidirectional Range (VOR) approach. This AD is prompted by a report of unpredictable and unexpected roll oscillations during coupled LOC or VOR approaches.This condition, if not corrected, could result in loss of helicopter control.
2014-26-03: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model 340B airplanes. This AD was prompted by a report that the elevator position quoted in an aircraft maintenance manual is incorrect and a report that the trunnion at the lower part of the control column was installed incorrectly. This AD requires an inspection of the stick pusher rigging and an inspection of the installation of the trunnion and the stick pusher rigging, and corrective actions if necessary. We are issuing this AD to correct the rigging of the elevator position of the stick pusher to reduce the probability of a negative effect on the handling quality during stall, which could result in reduced controllability of the airplane.
2000-07-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-200B, -300, -400, -400D, and -400F series airplanes. This action requires repetitive inspections to detect cracking of fire extinguisher discharge tubes in certain engine struts, and corrective action, if necessary. For certain airplanes, this action also provides for a modification of the fire extinguisher discharge tubes, which constitutes terminating action for the repetitive inspections. This amendment is prompted by reports that cracked fire extinguisher discharge tubes have been found in the engine struts on certain airplanes. The actions specified in this AD are intended to detect and correct cracked fire extinguishing tubes in the engine struts. In the event of an engine fire, such cracked tubes could reduce the amount of fire extinguishing agent that can be delivered to the engine, and could result in a fire spreading from the engine to the wing of the airplane.
94-10-01: 94-10-01 Hartzell Propeller Inc.: Amendment 39-8908. Docket 94-ANE-05. Applicability: Hartzell Propeller Inc. Model HC-E4A-3A/E10950() propellers, except propellers with serial numbers HJ199 and greater, installed on but not limited to Beech Model 1900D aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent severe propeller vibration in flight and possible loss of propeller pitch control, accomplish the following: (a) Install new propeller blade pitch change knob twelve point flange head attachment bolts to replace the countersunk screws currently used, new preload plates, and new propeller blade pitch change knob brackets, in accordance with Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. A190, dated January 17, 1994, as follows: (1) For propellers with 800 or more hours time in service (TIS) since new on the effective date of this airworthiness directive (AD), or 800 or more hours TIS since the new pitch change knob screws were last installed in accordance with Hartzell Propeller Inc. ASB No. A184, dated July 19, 1993, or Hartzell Propeller Inc. ASB No. A184(A), dated December 2, 1993, install within 50 hours TIS after the effective date of this AD. (2) For propellers with less than 800 hours TIS since new on the effective date of this AD, or less than 800 hours TIS since the new pitch change knob screws were last installed in accordance with Hartzell Propeller Inc. ASB No. 184, dated July 19, 1993, or Hartzell Propeller Inc. ASB No. A184(A), dated December 2, 1993, install prior to exceeding the later of: (i) 850 hours TIS since new; or (ii) 850 hours TIS since the new pitch change knob screws were last installed in accordance with Hartzell Propeller Inc. ASB No. 184, dated July 19, 1993, or Hartzell Propeller Inc. ASB No. A184(A), dated December 2, 1993; (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Chicago 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, Chicago 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 Chicago Aircraft Certification Office. (c) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) The installation shall be done in accordance with the following service document: Document No. Pages Date Hartzell Propeller Inc. ASB No. A190 Total pages: 3. 1-3 January 17, 1994 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part51. Copies may be obtained from Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2634; telephone (513) 778-4200, fax (513) 778-4391. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on June 22, 1994.