Results
70-04-01: 70-04-01 MCCAULEY PROPELLERS: Amdt. 39-939. Applies to 2D36C14- (X)/78KM, 2D34C53-(X)/74E, and B2D34C53-(X)/74E propellers on Lycoming O-360 type engines. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent propeller mid-blade and tip failures accomplish the following: a. Visually inspect blades for foreign object damage or cracks. b. If blade is damaged, repair in accordance with instructions in McCauley Service Bulletin No. 76 dated 28 November 1969, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Replace any cracked blades before further flight with a new blade which has been inspected and repaired if necessary in accordance with this AD. c. Install the following placard near the tachometer: "Avoid continuous operation, while descending, between 2250 and 2550 r.p.m. with manifold pressure settings below 15 inches mercury". This amendment is effective February 20, 1970.
2006-22-06: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B16 (CL-604) airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. These models may be referred to by their marketing designations as RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL-65. The existing AD currently requires revising the Emergency Procedures section of the airplane flight manual (AFM) to advise the flightcrew of additional procedures to follow in the event of stabilizer trim runaway. For certain airplanes, the existing AD also requires revising the Abnormal Procedures section of the AFM to advise the flightcrew of procedures to follow in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions. This AD requires revising the same Emergency and Abnormal Procedures sections of the AFM to advise the flightcrew of revised/additional procedures. This AD also requires revising the Normal section of the AFM to require a review of the location of certain circuit breakers and a functional check of the stabilizer trim system. This AD also requires installing circuit breaker identification collars and provides an optional terminating action for the requirements of the AD. This AD also removes airplanes from the applicability of the existing AD. This AD results from reports of uncommanded horizontal stabilizer trim motion. We are issuing this AD to ensure that the flightcrew is advised of appropriate procedures to follow in the event of uncommanded movement or stabilizer trim runaway. Failure to follow these procedures could result in excessive uncommanded movement of the horizontal stabilizer trim actuator (HSTA) and loss of ability to use trim switches to override uncommanded movement or yoke disconnect switches to disconnect the HSTA, which could result in reduction of or loss of pitch control and consequent reduced controllability of the airplane. \n\n\nDATES: This AD becomes effective November 14, 2006. \n\n\tThe Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 14, 2006. \n\n\tOn September 1, 2006 (71 FR 51990, September 1, 2006), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. \n\n\tWe must receive any comments on this AD by December 29, 2006.
2017-04-02: We are superseding Airworthiness Directive (AD) 2014-23-06 for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2014-23-06 required modifying the main landing gear (MLG) by installing a new bracket on the left and right lower aft-wing planks. This new AD requires modification of the MLG with an improved design. This AD was prompted by a report indicating that inboard and outboard hydraulic lines of the brakes were found connected to the incorrect ports on the swivel assembly of the MLG. We are issuing this AD to address the unsafe condition on these products.
2017-03-02: We are superseding airworthiness directive (AD) 2014-16-10 for all Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. AD 2014-16-10 required initial and repetitive ultrasonic inspections (UIs) of the affected low-pressure (LP) compressor blades. This AD requires the UIs in AD 2014-16-10 while reducing the inspection threshold. This AD was prompted by revised service information to reduce the inspection threshold for UI of the LP compressor blades. We are issuing this AD to correct the unsafe condition on these products.
50-46-01: 50-46-01 DOUGLAS: Applies to All Models DC3 and C-47 Series Aircraft Which Utilize a Standpipe in the Engine Oil Tank for Propeller Feathering Oil Reserve. \n\n\tCompliance required not later than the first engine change after December 1, 1950. \n\n\tThere have been several cases of inability to feather the propeller due to inadequate feathering oil supply, following loss of engine oil. To correct this condition ascertain the quantity of oil retained in the tank by the propeller feathering standpipe with the airplane in the level flight attitude. If the quantity so retained is less than 1 1/2 gallons, rework the standpipe so that at least this quantity is retained. \n\n\tAircraft employing C-47 type oil tanks, Douglas P/N 5110511 with Douglas P/N 1355088 standpipe will be considered satisfactory.
82-13-04 R1: 82-13-04 R1 HILLER AVIATION: Amendment 39-4400 as amended by Amendment 39- 4454. Applies to Model UH-12E and UH-12L series helicopters certificated in all categories (including military Models OH-23F and OH-23G) equipped with torsional couplings P/N 21047- 9 and -11 serial numbers 497 through 766. Compliance required within the next 50 hours' time in service after the effective date of this AD or within 300 hours' time in service since September 8, 1980, whichever occurs earlier, unless already accomplished, and thereafter at intervals not to exceed 300 hours' time in service since the last inspection. To prevent possible loss of driving torque to the helicopter rotor system, accomplish this following: (a) Inspect the P/N 21047-9 and 21047-11 torsional couplings as specified in paragraph 2 of Hiller Aviation Service Bulletin UH-12-21-1, Revision 2, dated April 2, 1982 (after this referred to as SB UH-12-21-1), or FAA approved equivalent. (b) If torsional coupling is found to be serviceable, reinstall per paragraph 2 of SB UH-12-21-1 or FAA approved equivalent and revert to the repetitive inspection schedule of this AD. (c) If torsional coupling installation does not meet the inspection requirements of paragraph (a) of this AD, replace with like serviceable part(s) and revert to the repetitive inspection schedule of this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections required by this AD. (e) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA Northwest Mountain Region. NOTE: Hiller Model UH-12 series helicopters converted to turbine power by STC SH178WE or SH177WE do not incorporate the subject parts and therefore are not affected by this AD unless restored to the original configuration. This supersedes Amendment 39-3907 (45 FR 59138), AD 80-18-13. Amendment 39-4400 became effective July 1, 1982. This amendment 39-4454 becomes effective September 13, 1982.
2016-25-30: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by certain anomalies of the flight guidance computers. We are issuing this AD to address the unsafe condition on these products.
86-19-09: 86-19-09 MCDONNELL DOUGLAS: Amendment 39-5403. Applies to McDonnell Douglas Model DC-10-10, -15, -30, and -40 and KC-10A (Military) series airplanes, certificated in any category. \n\n\tCompliance is required as indicated, unless previously accomplished. \n\n\tTo preclude potential fuel feed line failures and resulting unusable fuel or fuel imbalance, complete the following: \n\n\tA.\tWithin the next eighteen (18) months, or 4500 flight hours, whichever occurs first, after the effective date of this AD, complete the modifications and installations in accordance with the accomplishment instructions of McDonnell Douglas DC-10 Service Bulletin 28-140, Revision 1, dated October 16, 1985, and Service Bulletin 28-163, Revision 1, dated July 18, 1986, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in orderto comply with the requirements of this AD. \n\n\tC.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective October 2, 1986.
87-13-08: 87-13-08 EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER): Amendment 39-5664. Applies to Models EMB-110P1 and EMB-110P2 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To preclude operations with configurations which are contrary to the FAA approved Airplane Flight Manual/Pilot's Operating Handbook (AFM/POH) "LIMITATIONS" section, accomplish the following: (a) Within the next 30 days after the effective date of this AD , revise the EMB-110 AFM/POH by incorporating Revision 29, dated November 3, 1986, to EMBRAER Publication No. T.P.-110P1/176, "Pilot's Operating Handbook and CTA Approved Airplane Flight Manual Supplement for EMBRAER EMB-110P1/P2." (b) The requirement of paragraph (a) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him. The person accomplishing this action must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, FAA, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia 30349; Telephone (404) 991-2910. All persons affected by this directive may obtain a copy of the document referred to herein upon request to EMBRAER, P.O. Box 343-CE, 12.200 Sao Jose dos Campos, Sao Paulo, Brazil; or may examine the document referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on August 6, 1987.
88-15-02: 88-15-02 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5974. Applies to all Aerospatiale Model SA 330 series helicopters certificated in any category. Compliance is required as indicated (unless already accomplished). To prevent failure of the main rotor head spindles, accomplish the following: (a) Replace main rotor head spindles (P/N's 330A31-1122-09 and -10 and 330A31- 1782-00 and -01) as follows-- (1) For spindles which have 4,400 or more hours' time in service on the effective date of this AD, replace the spindles within the next 100 hours' time in service; and (2) For spindles which have less than 4,400 hours' time in service on the effective date of this AD, replace the spindles before they reach 4,500 hours' time in service. (b) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Rotorcraft Standards Staff, Federal Aviation Administration,Fort Worth, Texas 76193-0110, or by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. NOTE: Aerospatiale Service Bulletin No. 01.41 pertains to this subject. This amendment, 39-5974, becomes effective July 21, 1988.
2017-01-07: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FAN JET FALCON airplanes; Model FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE-FALCON 200 airplanes; Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes; and MYSTERE-FALCON 50 airplanes. This AD was prompted by a report that, during approach for landing, the main entry door detached from an airplane. This AD requires a functional test or check of the main entry door closure and warning system, and applicable door closing inspections, adjustments, operational tests, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
88-10-02: 88-10-02 DEHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: AMENDMENT 39-5905. Applies to all Model DHC-8-100 series airplanes, Post Mod. 8/0794 (Digital Air Data Computer (DADC) P/N 7000700-975), not equipped with an Electronic Flight Instrument System (EFIS), certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude erroneous Flight Director or Autopilot VOR operations, accomplish the following: A. Within 48 hours after the effective date of this AD: 1. Include the following limitation in the limitations section of the Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM: "Operation in Flight Director VOR and VOR approach mode, or Autopilot VOR and VOR approach mode, is prohibited." 2. Install a placard adjacent to the Flight Guidance Controller on the glare shield, stating: "VOR MODES PROHIBITED" B. Installation of DADC P/N 7000700-975 Mod BF, in accordance with Part B of de Havilland Service Bulletin A8-34-53, Revision B, dated April 1, 1988, constitutes terminating action for the requirements of paragraph A., above. 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, FAA, New England Region. 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 information from the manufacturer may obtain copies upon request to The de Havilland Aircraft Company of Canada, A Division of Boeing of Canada, Ltd., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment becomes effective May 18, 1988.
2006-18-05: The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model DC-9-10, DC-9- 20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. That AD currently requires a one-time inspection at a certain disconnect panel in the left forward cargo compartment to find contamination of electrical connectors and to determine if a dripshield is installed over the disconnect panel, and corrective actions if necessary. This new AD revises the applicability of the existing AD by removing certain airplanes and adding others. This AD results from a report of electrical arcing that resulted in a fire. We are issuing this AD to prevent contamination of certain electrical connectors, which could cause electrical arcing and consequent fire on the airplane.
2016-25-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead is subject to widespread fatigue damage (WFD). This AD requires replacing the aft pressure bulkhead with a new, improved aft pressure bulkhead, and doing related investigative and corrective actions if necessary. We are issuing this AD to prevent the unsafe condition on these products.
70-15-03: 70-15-03 BEECH: Amdt. 39-1037. Applies to Models 23, A23, A23A and B23 (Serial Numbers M-1 through M-1162); A23-24 (Serial Numbers MA-1 through MA-333); and A23-19 and 19A (Serial Numbers MB-1 through MB-392) Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent stiff operation, binding and seizing of Beech P/N 169-920000-127 fuel selector valve assembly, accomplish the following: Within 25 hours' time in service after the effective date of this AD, modify Beech P/N 169-920000-127 fuel selector valve assembly in accordance with Beechcraft Service Instructions No. 0364-289, or later FAA approved revision, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective July 21, 1970.
88-07-02: 88-07-02 BOEING: Amendment 39-5885. Applies to all Model 767 series airplanes and to those Model 757 series airplanes equipped with Rolls-Royce RB211 engines, certificated in any category. \n\n\tCompliance required within the next 2,000 hours time-in-service or 1 year after the effective date of this AD, whichever occurs first, unless previously accomplished. \n\n\tTo minimize the potential for inadvertent engine shutdown when using the electronic engine control (EEC) or engine limiter control (ELC) switches, accomplish the following: \n\n\tA.\tRelocate the electronic engine control switches or engine limiter control switches, as applicable, from the control stand to the overhead panel in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tThe fuel control switch guard installation made in compliance with AD T87-13- 51, Amendment 39-5718, may be removed following accomplishment of paragraph A., above. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and FAR 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. \n\n\tThis amendment supersedes AD 87-13-51, Amendment 39-5718 (52 FR 33917; September 9, 1987). \n\n\tThis amendment becomes effective May 11, 1988.
2016-25-14: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model BO-105LS A-3 helicopters. This AD requires establishing a life limit for the tension-torsion (TT) straps. This AD is prompted by an error in the Airworthiness Limitations section of the maintenance manual. These actions are intended to prevent the unsafe condition on these products.
88-19-09: 88-19-09 SAAB-SCANIA: Amendment 39-6012. Applies to Model SF-340A airplanes, manufacturer's serial numbers SF340A-003 through -108 inclusive, certificated in any category. Compliance required as indicated, unless previously accomplished. To ensure the reliability of the emergency main landing gear extension system, accomplish the following: A. For airplanes, serial numbers SF340A-003 to -078, inclusive: Within 90 days after the effective date of this AD, modify the wiring and connectors of the main landing gear emergency extension system in accordance with SAAB Service Bulletin SF340-32-028, Revision 1, dated November 25, 1986. B. For airplanes with serial numbers SF340A-003 to -108, inclusive: Within 90 days after the effective date of this AD, lengthen the electrical harnesses for the separation bolts, and re- route and secure the existing harnesses, in accordance with SAAB Service Bulletin SF340-32- 041, Revision 1, dated October 9, 1987. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to SAAB-Scania, Aircraft Division, S-58188 Linkoping, Sweden. These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment, 39-6012, supersedes AD 87-13-07, Amendment 39-5662. This Amendment, 39-6012, becomes effective October 10, 1988.
2016-25-15: We are superseding Airworthiness Directive (AD) 2011-17-05, for certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4- 103, A300 B4-203, and A300 B4-2C airplanes. AD 2011-17-05 required repetitive inspections in sections 13 through 18 of the fuselage between rivets of the longitudinal lap joints between frames (FRs) 18 and 80 for cracking, and repair or modification if necessary. This new AD requires a revised repetitive inspection program of all longitudinal lap joints and repairs between FRs 18 and 80 to address widespread fatigue damage (WFD). This AD was prompted by an evaluation done by the design approval holder indicating that certain sections of the longitudinal lap joints are subject to WFD; therefore, a revised inspection program is necessary. We are issuing this AD to address the unsafe condition on these products.
63-04-03: 63-04-03 SUD AVIATION: Amdt. 534 Part 507 Federal Register February 9, 1963. Applies to All SE-210 Caravelle Mark III and VIR Aircraft Except Serial Numbers 117, 120, 125 and Subsequent. Compliance required as indicated. To prevent the flight control system push-pull rod from jamming adjacent components in the event of loss of a connecting bolt, and thereby preventing emergency control of the aircraft by means of trim controls, accomplish the following: (a) For aircraft with 2,700 or more hours' time in service as of the effective date of this AD, compliance with (c) is required within the next 300 hours' time in service. (b) For aircraft with less than 2,700 hours' time in service as of the effective date of this AD, compliance with (c) is required prior to 3,000 hours' time in service. (c) Install push-pull rod guards at each aileron, elevator and rudder control rod in accordance with Sud Aviation Caravelle Service Bulletins Nos. 27-130, revised May 9, 1962, and 27-157 dated July 20, 1962, or an FAA approved equivalent. This directive effective March 12, 1963.
65-09-03: 65-09-03 GRUMMAN: Amdt. 39-57 Part 39 Federal Register April 21, 1965. Applies to Model G-159 Aircraft Equipped with AiResearch Gas Turbine Compressor Units Model GTC 85-37, Series 1 through 18. Unless already accomplished within the last 235 hours of APU operation or 470 starts of the APU prior to the effective date of this AD, accomplish the following within the next 15 hours of APU operation or 30 starts of the APU, whichever occurs first, and at intervals not to exceed 250 hours of APU operation or 500 starts of the APU since the last inspection: (a) Visually inspect in accordance with Grumman Gulfstream Customer Bulletin No. 180, dated February 12, 1965, or later FAA-approved revision, and AiResearch Service Bulletin No. 49-1045, Revision 1, dated January 29, 1965, or later FAA-approved revision, the APU turbine wheel and exducer for surface cracks, the shroud plate for indications of rubbing, and the blade tips for indications of erosion and over-heating. Remove fromservice any turbine wheel and any exducer found cracked, or having rubbed, eroded, or over-heated blades. (b) Check and adjust as necessary the starter clutch for proper torque value in accordance with Grumman Gulfstream Customer Bulletin No. 179, dated January 8, 1965, or later FAA-approved revision, and AiResearch Service Bulletin No. 49-1042, dated November 13, 1964, or later FAA-approved revision. (c) Check and adjust as necessary the APU fuel pump acceleration limiter for proper setting in accordance with AiResearch Service Bulletin No. 49-1045, Revision 1, dated January 29, 1965, or later FAA-approved revision. This directive effective April 21, 1965.
2016-25-10: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211- Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines. This AD requires machining and inspecting parts related to the high-pressure compressor (HPC) and replacing HPC parts found defective. This AD was prompted by inspection of RR Trent 800 engines returned from service that revealed flame erosion and axial cracking on the stage 3 disk rim of the HPC stage 1-4 rotor disks shaft. We are issuing this AD to correct the unsafe condition on these products.
79-08-07: 79-08-07 CESSNA: Amendment 39-3451. Applies to Model 441 (S/N's 441-0001 through 441-0083 and 441-0085) airplanes equipped with a Cessna installed propeller anti-icing system. COMPLIANCE: Required as indicated unless already accomplished. To preclude the possible occurrence of smoke/fire behind the pilot's instrument panel, accomplish the following: A) Within the next 10 hours time-in-service, except for those airplanes previously modified, modify the propeller anti-icing electrical wiring in accordance with Cessna Propjet Service Information Letter PJ 79-2 dated March 5, 1979. B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective on April 30, 1979 to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated March 16, 1979.
58-06-02: 58-06-02 HARTZELL: Applies to All HC-82XF/8833-0 (86 to 88 inch-diameter) Propellers, Hub Serial Numbers Between T-913 and T-2891 Except T-2564, T-2569, T-2594, T- 2595, T-2609, T-2648, T-2703 and T-2716. Compliance required prior to next flight. Two recent failures of A-159 split rings have occurred in HC-82XF/8833 propellers. In order to minimize the possibility of the occurrence of this type of serious failure, replace the present split rings with new split rings. The present rings are unmarked, but the new A-159 rings will be marked with the letter "N". (Hartzell Service Bulletin No. 57 covers this same subject.)
63-20-02: 63-20-02 CESSNA: Amdt. 628 Part 507 Federal Register October 3, 1963. Applies to All Models 190 and 195 Series Aircraft. Compliance required as indicated. As a result of a fatal accident involving fatigue failure of the front wing spar fuselage carry through lower cap the following corrective action is required: (a) Within 10 hours' time in service after the effective date of this AD, conduct the following visual and X-ray inspections in accordance with Cessna Service Letter 190/195-1 dated May 13, 1960, or FAA approved equivalent unless already accomplished within the last 100 hours' time in service: (1) Inspect using X-ray method for cracks in the lower cap of the front spar carry through member at both left and right sides of the fuselage in the area of the two most inboard steel rivets; (2) Remove rear spar to fuselage attachment bolts and visually inspect these bolts using at least a 4-power magnifying glass for evidence of wear or partial shear failures; (3) Visually inspect the rear spar to fuselage fittings of both the wing structure and carry through structure including the bolt bushings for wear or hole elongation; (4) Visually inspect the steel plates of the rear spar to fuselage attachment fittings on the wing for cracks using at least a 4-power magnifying glass; and (5) If any of the defects specified are found replace the parts with new parts or make an FAA approved repair and accomplish the modification required by (b) before further flight. (b) Within 10 hours' time in service after the effective date of this AD, accomplish the fuselage front spar modification specified in Cessna Service Letter 63-40, dated September 27, 1963. This specifies replacement of the five existing inboard lower cap high shear steel pins with NAS 464P7-A64 bolts and attachment of two 1/2 x l 3/4 4130 steel reinforcement bars on each side of the lower spar cap in accordance with Cessna Service Kits Nos. SK-195-3 and SK-195-4, dated September 23, 1963. (c) At each periodic inspection after the accomplishment of (b), visually inspect for cracks the visible portion of the lower spar cap and reinforcement bars at the inboard bolt location. If cracks are found, replace the cracked part with a new part or make an FAA approved repair before further flight. This supersedes AD 61-17-01. This directive effective October 8, 1963.