Results
2000-07-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time detailed visual inspection of the electrical connections to detect corrosion; repair, if necessary; and installation of new circuit breakers and associated wiring. This amendment is prompted by a report that the ratings of certain circuit breakers of a certain video entertainment system exceed the ratings of their associated electrical connector contacts. The actions specified by this AD are intended to prevent a disparity between the ratings of certain circuit breakers and their associated electrical connector contacts, which could damage the electrical connector contacts and cause possible arcing and heat damage to the electrical connector.
91-07-03: 91-07-03 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-6944. Docket No. 91-NM-17-AD. Applicability: All Model L-1011 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent structural failure of the aft pressure bulkhead, accomplish the following: A. Except as provided in paragraph B. of this AD, within 30 days after the effective date of this AD, unless previously accomplished within the last 60 days, inspect the gore panels of the aft pressure bulkhead around the entire perimeter of the 1503618-145 (LH) and 1503618-143 (RH) reinforcing doublers, in accordance with Section 2. of the Accomplishment Instructions of Lockheed Service Bulletin 093-53-263, dated February 27, 1991. B. For airplanes on which inspections of the aft pressure bulkhead have been accomplished in accordance with Lockheed Service Wire PSC/90-531176-OW, dated December 21, 1990, prior to the effective date of this AD: The remaining inspections required by paragraph A. of this AD may be deferred for a period not to exceed 3,000 landings following the effective date of this AD. C. If cracks are found, prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. D. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles ACO, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. E. 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 information from the manufacturer may obtain copies upon request to Lockheed Aeronautical Systems Company, 86 South Cobb Drive, Marietta, Georgia 30063, Attention: Commercial Order Administration, Dept 65-11, Building B-95, Zone 0577. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This amendment (39-6944, AD 91-07-03) becomes effective on April 3, 1991.
2025-05-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model SA330J helicopters. This AD was prompted by the determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance records by incorporating new or more restrictive airworthiness limitations, 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.
2013-09-05: We are adopting a new airworthiness directive (AD) for certain Twin Commander Aircraft LLC Models 690, 690A, and 690B airplanes. This AD requires inspection for cracking of the outer fuselage attachments, the lower wing main spar, the vertical channels, the upper picture window channels, aft cabin pressure web, external wing to fuselage fillets, and fasteners; repair or replacement of damaged parts as necessary; and modification of the structure with reinforced parts. This AD [[Page 28126]] was prompted by cracks found in the upper picture window frame channels, left- and right-hand wing main spar frame support channels, and aft pressure bulkhead web. This condition, if not corrected, could result in structural failure of the airplane. We are issuing this AD to correct the unsafe condition on these products.
75-17-16: 75-17-16 BELLANCA: Amendment 39-2309. Applies to the Bellanca Models 7ECA, 7GCAA, 7GCBC, 7KCAB, 8KCAB, and 8GCBC airplanes as set forth below. Compliance required as indicated, unless previously accomplished. A special flight permit pursuant to FAR 21.197 may be issued to allow ferrying of the aircraft to a facility where the required maintenance can be performed. To prevent possible engine power loss due to fatigue failure of the carburetor alternate air valves, accomplish the following: A). Within the next 10 hours time in service after the effective date of this AD on Models 7ECA (S/N 985-74 thru 1108-75), 7GCAA (S/N 280-74 thru 319-75), 7GCBC (S/N 604- 74 thru 859-75), 7KCAB (S/N 405-74 thru 532-75), 8KCAB (S/N 12074 thru 204-75), 8GCBC (S/N 1-74 thru 181-75), install Bellanca service Kit No. 248A. Bellanca Service Letter No. 118A pertains to this subject. B). Within the next 10 hours time in service after June 25, 1975, on the Models 7ECA (S/N 723-70 thru 984-73), 7GCAA (S/N 205-70 thru 279-73), 7GCBC (S/N 202-70 thru 603-73), 7KCAB (S/N 209-70 thru 404-73), 8KCAB (S/N 4-71 thru 119-73), install Bellanca Service Kit No. 251. Bellanca Service Letter No. 120 applies to this subject. C). At each annual, progressive, or 100-hour inspection as required by Federal Aviation Regulation 91.169, on the Models covered by paragraphs A and B and all subsequent serials of those same models, inspect the alternate air valve for cracks. If any cracks are noted, replace the alternate air valve by installing Bellanca Service Kit 251 on Models 7ECA (S/N 723- 70 thru 984-73), 7GCAA (S/N 205-70 thru 279-73), 7GCBC (S/N 202-70 thru 603-73) 7KCAB (S/N 209-70 thru 404-73), 8KCAB (S/N 4-71 thru 119- 73); Bellanca Service Kit #248A on Models 7ECA (S/N 985-74 and up), 7GCAA (S/N 280-74 and up), 7GCBC (604-74 and up), 7KCAB (405-74 and up), 8KCAB (S/N 120-74 and up), 8GCBC (S/N 1-74 and up). Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region, 2300 E. Devon Avenue, Des Plaines, Illinois, 60018. This Amendment supersedes Amendment 39-2173, 40 F. R. 17138, AD 75-09-02 as amended by Amendment 39-2243, and Amendment 39-2261. This amendment becomes effective August 12, 1975.
2013-09-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of two in-service incidents where the left main landing gear (MLG) failed to extend. This AD requires installing stopper plates on the aft uplock frames in the MLG bay adjacent to the right and left MLG uplock assemblies. We are issuing this AD to prevent incorrect installation of the upper bolt in the MLG uplock assembly, which could prevent the MLG from extending and could adversely affect the safe landing of the airplane.
96-16-06: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-16-06, which was sent previously to all known U.S. owners and operators of certain Weatherly Aviation Company, Inc., (Weatherly) Models 620A and 620B airplanes. This AD requires inspecting all wing hinge pins, part number (P/N) 40852-001, at the main wing-to-center section attachment (four per airplane) for depth of the threaded ends, length of the pin, and position of the pin; and replacing or repositioning any pin, as necessary. A report received by the Federal Aviation Administration of manufacturing deficiencies at the area of the main wing center section attachment prompted the AD. The actions specified by this AD are intended to prevent failure of the wing hinge pin, which could result in the wing separating from the fuselage.
2025-05-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332L1 and EC225LP helicopters. This AD was prompted by a determination of a possible interference of the hoist operator's helmet cord with the toggle switch of the hoist cable cut control. This AD requires replacing, or modifying and re- identifying, certain hoist shear toggle switch supports, and prohibits installing certain hoist shear toggle switch supports, 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.
2013-08-14: We are superseding an existing airworthiness directive (AD) for certain Revo, Incorporated Models COLONIAL C-1, COLONIAL C-2, LAKE LA-4, LAKE LA-4A, LAKE LA-4P, and LAKE LA-4-200 airplanes. That AD currently requires a one-time, dye-penetrant inspection of the horizontal stabilizer attachment fitting and repetitive visual inspections of the fitting for any evidence of fretting, cracking, or corrosion (with necessary replacement and modification); replacement of the fitting upon reaching the 850-hours time-in-service (TIS) safe life; and reporting to the FAA the results of the initial inspection and any cracks found on repetitive inspections. This new AD requires the same actions of AD 2005-12-02 except using revised service documents and procedures, adds Model COLONIAL C-1 airplanes to the Applicability, and adds an optional terminating action for the requirements. This AD was prompted by a report from Revo, Incorporated that, while the drawing numbers are different, the attachment fittings on the Model COLONIAL C-1 airplanes are identical in every other respect to those installed on the airplanes referenced in AD 2005-12- 02. We are issuing this AD to correct the unsafe condition on these products.
68-20-02: 68-20-02 AVIONS MARCEL DASSAULT: Amendment 39-659. Applies to Dassault Fan Jet Falcon Airplanes, Serial Numbers 1 thru 72. Compliance required not later than December 31, 1968. To prevent the ingress of moisture causing internal corrosion in the landing gear switch assembly, replace the existing microswitch with a modified switch, in accordance with Dassault AMD Service Bulletin No. 333, dated June 21, 1968, or later SGAC-approved issue, or FAA- approved equivalent, as follows: LOCATION Nose Landing Gear, EXISTING SWITCH P/N A1-23802 Telescopic Bar MODIFIED SWITCH P/N A1-23802 - V1 - V2 Nose Landing gear, EXISTING SWITCH P/N A1-23801 Door Actuating Cylinder MODIFIED SWITCH P/N A1-23801 - V1 - V2 Main Landing Gear, EXISTING SWITCH P/N A2-23802 Drag Strut Actuator Cylinder MODIFIED SWITCH P/N A2-23802 - V1 - V2 Main Landing Gear, EXISTING SWITCH P/N A2-23801 Door Actuating Cylinder MODIFIED SWITCH P/N A2-23801 - V1 - V2 This amendment becomes effective October 25, 1968.
96-15-01: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-15-01, which was sent previously to all known U.S. owners and operators of Raytheon Aircraft Corporation (formerly Beech) Model 1900D airplanes. This AD requires immediately pulling and banding the circuit breakers leading to the windshield heat control on both the pilot and co-pilot sides, inserting a copy of the priority letter AD into the Limitations section of the Airplane Flight Manual (AFM), and fabricating and installing a placard instructing the pilot to avoid flight into known icing conditions. Reports of smoke and fire in the cockpit on two Beech Model 1900D airplanes caused by a high resistance short circuit condition in the heated windshield wiring prompted the action. The actions specified by this AD are intended to prevent smoke and fire around the forward edge of the glare shield in the cockpit, which could result in loss of control of the airplane. Comments for inclusion in the Rules Docket must be received on or before October 21, 1996.
2021-06-05: The FAA is superseding Airworthiness Directive (AD) 2017-07-08 for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB- BK 117 D-2 helicopters. AD 2017-07-08 required repetitively inspecting each engine mount elastomeric bushing (elastomeric bushing). Since the FAA issued AD 2017-07-08, Airbus Helicopters has designed an improved engine mount metal bushing (metal bushing). This new AD retains the inspection requirements of AD 2017-07-08 and requires replacing each affected engine mount bushing with an improved engine mount bushing, while also requiring repetitive inspections of the improved engine mount bushing. This AD also prohibits installing an elastomeric bushing on any helicopter. The actions of this AD are intended to address an unsafe condition on these products.
2000-07-03: This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters, that requires inspecting the wire harness for contact with the fuel line assembly, removing and replacing the fuel line assembly if chafing has occurred, and installing spiral wrap tubing on the fuel line assembly. This amendment is prompted by four incidents of contact between the wire harness and the fuel line assembly. The actions specified by this AD are intended to prevent contact between the wire harness and the fuel line, which could result in chafing of the wire harness and a potential fire hazard.
2000-06-10: This amendment adopts a new airworthiness directive (AD) applicable to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. This action requires preflight checking and repetitively inspecting the tail boom for a crack and replacing the tail boom if a crack is found. This amendment is prompted by four reports of cracks on the tail boom in the area of the horizontal stabilizer. The actions specified in this AD are intended to prevent separation of the tail boom and subsequent loss of control of the helicopter.
2003-10-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes, that currently requires repetitive inspections to find discrepancies of the barrel nuts that attach the vertical fin to body section 48, and follow-on actions. For certain airplanes, the existing AD requires replacement of certain bolts with new bolts. The existing AD also provides for optional terminating actions for the repetitive inspections. This amendment reduces the compliance time for the inspections; changes the torque specification; and mandates eventual replacement of all H-11 steel alloy barrel nuts and bolts with Inconel nuts and bolts, which ends the repetitive inspections. The actions specified by this AD are intended to find and fix corroded, cracked, or broken barrel nuts that attach the vertical fin to body section 48, which could result in reduced structural integrity of the vertical fin attachment joint, loss of the vertical fin, and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2018-06-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by reports of in-flight uncommanded rudder movements on airplanes with an installation similar to the installation on certain Model CL-600-2B16 (CL-604 Variant) airplanes. This AD requires modification of the wiring harness for the yaw damper control system. We are issuing this AD to address the unsafe condition on these products.
2013-08-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of damaged fire seals on the forward edge of the thrust reverser. This AD requires inspecting to detect damage to the upper fire seals on the forward edge of the thrust reverser, where the fire seal contacts the 12-o'clock engine strut, and for correct stiffness and vent holes, and doing corrective actions if necessary; and installing a bracket for the fire seal. We are issuing this AD to detect and correct damage to the fire seals, which could allow airflow into the engine fire zone and could degrade the ability to extinguish an engine fire.
2003-10-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model 717-200 airplanes, that requires modification of the longeron-to-frame installation of the upper center fuselage. This action is necessary to prevent fatigue cracking of the longerons of the upper center fuselage, which could result in reduced structural integrity of the fuselage. This action is intended to address the identified unsafe condition.
93-16-03: 93-16-03 BRITISH AEROSPACE: Amendment 39-8660. Docket 93-NM-23-AD. Applicability: Model BAe 146 airplanes, as listed in British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-135, dated April 23, 1992, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent adverse airplane flight characteristics during autopilot operation, accomplish the following: (a) Within 60 days after the effective date of this AD, perform a visual inspection of the autopilot pitch servomotor mounting to identify the part number on the dataplate in accordance with British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-135, dated April 23, 1992. (b) If the part number is 209RAA6-135CAF (for Model BAe 146-100A and -200A series airplanes) or 209RAA6-175ABC (for Model BAe 146-300A series airplanes), prior to further flight, perform a visual inspection of the position of the foul pin holes in the mounting bracket in accordance with British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-135, dated April 23, 1992. (1) If the foul pin holes align with foul pin hole positions "CAF" (for Model BAe 146-100A and -200A series airplanes) or "ABC" (for Model BAe 146-300A series airplanes) on the mounting bracket, no further action is required by this AD. (2) If the foul pin holes do not align with foul pin hole positions "CAF" (for Model BAe 146-100A and -200A) or "ABC" (for Model BAe 146-300A series airplanes) on the mounting bracket, accomplish the requirements of paragraphs (b)(2)(i) and (b)(2)(ii) of this AD. (i) Prior to further flight, perform a torque check of the autopilot pitch servomotor mounting in accordance with the service bulletin to ensure that the slip torque corresponds to the values specified in the service bulletin. If the autopilot pitch servomotor mounting slip torque does not correspond to the values specified in the service bulletin, prior to further flight, remove the autopilot pitch servomotor mounting and install a serviceable autopilot pitch servomotor mounting having the correct slip torque in accordance with the service bulletin. (ii) Within 12 months after the effective date of this AD, modify the mounting bracket and reposition the foul pins on the servomotor mounting in accordance with the service bulletin. (c) If the part number is not 209RAA6-135CAF (for Model BAe 146-100A and -200A series airplanes) or 209RAA6-175ABC (for Model BAe 146-300A series airplanes), prior to further flight, remove the autopilot pitch servomotor and servomotor mounting, modify the mounting bracket, and install an autopilot pitch servomotor and servomotor mounting having part number 209RAA6-135CAF (for Model BAe 146-100A and -200A series airplanes) or 209RAA6-175ABC (for Model BAe 146-300A series airplanes), in accordance with British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-135, dated April 23, 1992. (d) 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) 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. (f) The inspections and corrective actions shall be done in accordance with British Aerospace BAe 146 Inspection Service Bulletin S.B. 27-135, dated April 23, 1992, which includes Appendices A1 and A2. This incorporation by reference was approved by the Directorof the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, Inc., Avro Division, 22070 Broderick Drive, Sterling, Virginia 20166. 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. (g) This amendment becomes effective on October 4, 1993.
2025-07-02: The FAA is adopting a new airworthiness directive (AD) for certain BRP-Rotax GmbH & Co KG (Rotax) Model 912 iSc2 Sport, 912 iSc3 Sport, 915 iSc2 C24, and 915 iSc3 C24 engines. This AD was prompted by a report of deviations during the manufacturing process that caused incorrect application of a certain thread-locker to certain sprag clutch housing and oil spray nozzles. This AD requires repetitive operational checks of the battery backup function with removal of the engine from service if insufficient battery power is found, one-time inspections of the oil spray nozzle and generator stator assembly, and, depending on the results of the inspections, replacement with parts eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2012-25-01: We are adopting a new airworthiness directive (AD) for Eurocopter France Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with certain Aerazur emergency flotation gear attachment brackets (brackets) installed. This AD requires an initial and recurring inspection of the brackets for a crack, and if there is a crack, replacing the cracked bracket with an airworthy bracket. This AD was prompted by reports of cracks on the brackets. The actions of this AD are intended to prevent failure of the emergency flotation system and loss of float stability in the event of a water landing.
2013-08-21: We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries Model DA 40 NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as chafing between the charge air tubing and the engine firewall that may cause a hole in the charge air tubing, which could result in loss of charged air pressure with consequent loss of engine power and loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
2025-06-04: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters (Airbus) Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 helicopters. This AD was prompted by a manufacturer assessment that determined additional actions are necessary to improve particle detection for main gearboxes (MGBs) with certain planet gear bearings installed. This AD requires repetitively inspecting the MGB bevel wheel and the MGB magnetic plug for particles and prohibits installing an affected MGB unless certain requirements are met. These actions are 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.
81-13-11: 81-13-11 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39- 4142. Applies to Model A109A series helicopters, certificated in all categories, that have main rotor blades, P/N 1090-0103-01-07, installed. Compliance required as indicated, unless already accomplished. To detect and prevent corrosion which could result in an in-flight rotor blade failure, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD: (1) Inspect the main rotor blade leading edge abrasion strip inner end and scarf joint for filler erosion, filler release, and corrosion, in accordance with Part I of the "Accomplishment" paragraph of Agusta Bollettino Tecnico No. 109-7, dated February 6, 1978, or an FAA-approved equivalent. (2) If no filler erosion or release is found during the inspection specified in paragraph (a)(1) of this AD, apply a polyurethane tape to the blade and comply with paragraph (b) of this AD. (3) If fillererosion or release is found during the inspection specified in paragraph (a)(1) of this AD, clean the area and inspect for corrosion and bond separation. (4) If corrosion or bond separation is not found during the inspection in paragraph (a)(3) of this AD, fill with urethane adhesive, apply a polyurethane tape to the blade, and comply with paragraph (b) of this AD. (5) If corrosion is not found during the inspection required by paragraph (a)(3) of this AD but marginal bonding separation not deeper than 5 mm. (0.2 in.) is found, clean and flush the area, fill with urethane adhesive, apply a polyurethane tape to the blade, and comply with paragraph (b) of this AD. (6) If corrosion or bond separation deeper than 5 mm. (0.2 in.) is found during the inspection required by paragraph (a)(3) of this AD, replace the blade with a serviceable blade of the same part number, or an FAA-approved equivalent, return the helicopter to service and comply with paragraph (b) of this AD.(b) After the last flight of each day in which the helicopter is operated after compliance with paragraph (a) of this AD, check the main rotor blade polyurethane tapes for condition and adhesion in accordance with Part II of the "Accomplishment" paragraph of Agusta Bollettino Tecnico No. 109-7, dated February 6, 1978, or an FAA-approved equivalent. The check required by this paragraph may be accomplished by the pilot. (c) If during the check required by paragraph (b) of this AD, a tape defect or abnormal condition including bond separation is found, comply with paragraph (a) of this AD before flight, except that the helicopter may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the work can be performed. (d) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Costruzioni Aeronautiche Giovanni Agusta, Cascina Costa (Gallarate), Italy. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, DC 20591. This amendment becomes effective July 20, 1981.
78-16-02 R1: 78-16-02 R1 DOWTY ROTOL LTD: Amendment 39-3272 as amended by Amendment 39-4946. Applies to Dowty Rotol Type R.209/4-40-4.5/2 propellers installed on Nihon Model YS-11 and YS-11A airplanes. Compliance is required as indicated unless already accomplished. To reduce the possibility of propeller hub failure due to cracks in the hub arm threads and subsequent loss of propeller blade retention, accomplish the following: (a) On propellers which have accumulated 10,000 flight cycles or more, within the next 1,000 flight cycles after the effective date of this AD or at a time not to exceed 3,000 flight cycles since the previous inspection for cracks, whichever occurs first, inspect the propeller hub (arm) blade bearing retaining threads for cracks in accordance with Dowty Rotol Service Bulletin 61-890 dated July 11, 1977, or an FAA-approved equivalent (hereinafter referred to as Service Bulletin). In addition - (1) If, during any inspection conducted after the effective date of this AD propeller hub cracking is found, before further operation, replace the propeller hub with a serviceable hub of the same part number; and (2) Handle defective hubs in accordance with paragraph 1.C(4) of the Service Bulletin. (3) Compliance with this AD is not required for propellers having the new strengthened hub Part No. 601023446 installed in place of hub Part No. 601023335. (b) For purposes of this AD a flight cycle is defined as a flight operation involving one takeoff and landing. For purposes of complying with this AD, when the number of flight cycles cannot be determined from propeller/airplane records, subject to acceptance by the assigned FAA maintenance inspector, the number of flight cycles may be determined by equating one flight cycle to 1/2 hour time in service. (c) If during the inspection required by paragraph (a) of this AD, or at any subsequent inspection, propeller hub cracking is detected, inspect all the operator's propellers covered by this AD, which have accumulated more than 10,000 flight cycles, in accordance with paragraph (a) within 1,000 flight cycles of the detection of the cracks, and, thereafter, at intervals not to exceed 3,000 flight cycles. (d) Airplanes may be flown in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the inspections and parts replacement required by this AD can be accomplished. (e) Upon request, the Manager, Engine and Propeller Standards Staff, ANE-110, FAA, New England Region, may adjust the inspection interval. Amendment 39-3272 became effective August 28, 1978. This Amendment 39-4946 becomes effective on November 15, 1984.