Results
74-16-08: 74-16-08 PIPER: Amendment 39-1912. Applies to Model PA-30 and Model PA-39 aircraft certificated in all categories except aircraft incorporating Piper Kit Part Number 760 783. Compliance required as indicated. To prevent possible hazards in flight associated with cracking of the aft bulkhead assembly, fuselage station 258, accomplish the following: 1. Within the next 50 hours in service from the effective date of this AD, unless already accomplished within the past 50 hours in service, and at intervals not to exceed 100 hours in service from the last inspection, inspect in accordance with paragraph 2. 2. Remove the tail cone and visually inspect, with five times power minimum magnification, the aft bulkhead assembly, fuselage station 258, Part Number 22893-00 on Model PA-30 and Model PA-39, Serial Nos. 39-1 through 39-83 or Part Number 22893-06 on Model PA-39, Serial Nos. 39-84 and up, for cracks in the area of the aft fin attachment brackets. 3. If cracks aredetected, repair in accordance with Fin Attachment Bracket Installation Kit, Piper Part Number 760 783 or equivalent prior to further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where a repair can be made. 4. Upon incorporation of the Fin Attachment Bracket Installation Kit, Piper Part Number 760 783 or equivalent, compliance with the requirements of this AD may be dispensed with. 5. Equivalent repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 6. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive inspection interval specified in this AD. (Piper Service Letter No. 679 refers to this subject.) This amendment is effective August 9, 1974.
80-03-05 R1: 80-03-05 R1 ROCKWELL INTERNATIONAL: Amendment 39-3685 as amended by Amendment 39-3772. Applies to Model NA-265-70 serial numbers 1 and 7 only, and NA-265-80 (all) series airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent elevator trailing edge delamination, accomplish the following: a. Within 15 hours' time in service or 10 days from the effective date of this AD, whichever occurs first, inspect elevator trailing edge for delamination as specified in paragraph 7, "Modification Instructions" of Rockwell International, Sabreliner Division, Service Bulletin No. 43 dated September 14, 1979. b. If evidence of delamination is found, prior to further flight, accomplish paragraph (d) of this AD. c. If no evidence of delamination is found, prior to the accumulation of 300 additional hours' time in service or 90 days from the effective date of this AD, whichever occurs first, accomplish paragraph (d) ofthis AD. d. Repair any delamination, enlarge existing 25 drain holes and add 75 drain holes as specified in "Modification Instructions" of Service Bulletin No. 43, and add elevator balance weights and accomplish static balance check as specified in Rockwell International, Sabreliner Division, Service Bulletin No. 44 dated September 14, 1979. e. Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. f. 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 inspections required by this AD. Amendment 39-3685 became effective February 11, 1980. This Amendment 39-3772 becomes effective May 29, 1980.
79-05-07: 79-05-07 GULFSTREAM AMERICAN (Formerly Grumman American Aviation Corporation): Amendment 39-3424. Applies to Model GA-7 airplanes, certificated in all categories, serial numbers GA7-0002 through GA7-0009, GA7-0011 through GA7-0057, and GA7-0059. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To detect and prevent fuel leakage from cracks in the inboard fuel tank ribs at Wing Station (W.S.) 109, at the forward fuel tank outlet fittings in the left and right wings, accomplish the following: (a) Inspect, repair, and modify these aircraft in accordance with Gulfstream American Service Bulletin No. ME-9, dated November 13, 1978, and Supplement No. 1 dated December 18, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. In accomplishing the repair instructions of the service bulletin the additional defueling safety practices containedin GA-7 Maintenance Manual, Section 28-0, page 201, Fuel System-Maintenance Policies, must be observed. (b) Equivalent methods of compliance with this AD may be acceptable if approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where the needed inspection and repairs and fuel line replacement required by this AD may be accomplished. This amendment becomes effective March 9, 1979.
2019-24-15: The FAA is adopting an airworthiness directive (AD) for certain The Boeing Company Model 737-900ER series airplanes. This AD requires replacement of nonconforming head strike pads with conforming head strike pads. This AD was prompted by a report of nonconforming head strike pads on the left and right mid exit doors. The FAA is issuing this AD to address the unsafe condition on these products.
74-14-06: 74-14-06 PIPER: Amendment 39-1885. Applies to all Model PA-36-285 airplanes, S/N 36-7360001 through 36-7460016 certificated in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD unless already accomplished. To preclude the possibility of having bolts installed in the wing spar carry through assembly which could be subject to deformation, accomplish the following: (a) Remove a total of four AN 4C-11A bolts and corresponding nuts and washers from the spar center section carry through left and right end vertical stiffeners. (b) Enlarge these four holes to 5/16" + .005 - .001 diameter. If the maximum hole size above does not eliminate evidence of elongation or wear, damaged parts should be replaced or further repaired in a method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (c) Install an AN5-11A bolt, AN960-516L washer under bolt head, MS20365-524C nut and anAN960-516 washer under nut in each of the four holes. Torque to 100-140 inch pounds. Piper Service Bulletin No. 425 pertains to this same subject. This amendment becomes effective July 8, 1974.
2007-20-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: To prevent fuel system leaks inspect the bronze/brass hollow threaded fuel line fittings for type and leaks, per Avions Pierre Robin Service Bulletin (SB) No. 86. We are issuing this AD to require actions to correct the unsafe condition on these products.
82-12-05: 82-12-05 ROLLS-ROYCE, LTD.: Amendment 39-4398. Applies to Rolls-Royce, Ltd., RB211-22B and -524 series turbofan model engines. Compliance required as indicated unless already accomplished. To preclude possible loss of the fan assembly, install the Rolls-Royce axial fan retention modification as specified in Rolls-Royce Service Bulletin 72-6574, Revision 2, dated March 19, 1982, or later revision approved by the FAA, applicable to RB211-22B, -524B-02, -524B2-19, -524B2-39, and -524C2-19 engines and as specified in Rolls-Royce Service Bulletin 72-6576, Revision 2, dated March 19, 1982, or later revision approved by the FAA, applicable to RB211-524B3-02, -524B4-02, and -524D4-19 engines in accordance with the following schedule: 1. Center (fuselage mounted) engines on Lockheed L1011 aircraft by September 30, 1982. 2. Wing mounted engines on Lockheed L1011 and Boeing B747 by December 31, 1982. All persons affected by this directive who have not already received the referenced service bulletins from the manufacturer may obtain copies upon request to Technical Publications Department, Rolls-Royce, Ltd., P.O. Box 31, Derby, England DE2 8BJ. This document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. A historical file on this AD is maintained by the FAA at the New England Regional Office. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Aircraft Certification Division, FAA, New England Region, may adjust the compliance date(s) specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the adjustment for that operator. This amendment becomes effective June 7, 1982.
2019-24-11: The FAA is superseding Airworthiness Directive (AD) 2014-16-26 and AD 2017-19-04, which applied to certain Dassault Aviation Model FALCON 900EX airplanes. Those ADs required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. Since the FAA issued AD 2014-16-26 and AD 2017-19-04, the FAA determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require those maintenance or inspection program revisions, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
74-09-04: 74-09-04 PIPER: Amendment 39-1821. Applies to Model PA-28-140 Serial Numbers 28-7225001 through 28-7325674; Model PA-28-180 Serial Numbers 28-7205001 through 28- 7305601; Model PA-28-235 Serial Numbers 28-7210001 through 28-7310176; and Model PA- 28R-200 Serial Numbers 28R-7235001 through 28R-7335446, certificated in all categories. Compliance required within the next 100 hours time in service from the effective date of this AD, unless already accomplished. To provide a safer rear seat belt installation, accomplish the following: Relocate the rear seat safety belt outboard attachments in accordance with Piper Service Bulletin Number 393 or equivalent approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, Atlanta, Georgia. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made apart 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 Piper Aircraft Corporation, Vero Beach Division, Vero Beach, Florida 32960. These documents may also be examined at the Federal Aviation Administration, Southern Region, 3400 Whipple Street, East Point, Georgia 30344 and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at the Federal Aviation Administration, Southern Region. This amendment becomes effective April 24, 1974.
88-24-02: 88-24-02 PRATT & WHITNEY CANADA (PWC): Priority letter AD issued November 16, 1988. Applies to PT6A-50 turboprop engines installed on Dehavilland of Canada DHC-7 aircraft. This priority letter AD is effective immediately upon receipt. Compliance is required as indicated, unless already accomplished. To prevent uncontained PT blade failure resulting from a PT blade shed overspeed event due to a RG assembly failure, accomplish the following: (a) Within one calendar day after receipt of this priority letter AD, inspect the airframe chip detector flag system and reinspect each day of operation, in accordance with Dehavilland Canada Dash 7 Maintenance Manual, Section 71-05-00. If the chip detector flag is actuated, accomplish paragraphs (b) (1), (b)(2), and (b) (4), of this AD, prior to further flight. (b) Within the next 50 hours in service after receipt of this priority letter AD, accomplish the following, unless already accomplished: (1) Remove and visually inspectthe engine chip detector for metal debris, in accordance with PWC PT6A-50 Maintenance Manual, Section 79-35-02, and based on the inspection results, accomplish the applicable procedures specified in Section 79-35-02. (2) Remove from service chip detector Part Number (P/N) 3020019, if installed, and replace with chip detector P/N 3026609. (3) Inspect the circuit wiring of the installed or replacement chip detector, P/N 3026609 in accordance with PWC PT6A-50 Maintenance Manual, Section 79-35-02. Remove from service, prior to further flight, chip detectors found with an open circuit and replace with serviceable parts. (4) Perform a one time-inspection check of the airframe chip detector flag system by grounding the wiring pins in the connector to the chip detector, in accordance with PWC Alert Service Information Letter (SIL) No. 4019, dated October 20, 1988. If chip detector flag is not actuated in the nacelle, correct defects, and repeat this inspection check until the chip detector flag actuation is confirmed (reference DeHavilland Canada Dash 7 Maintenance Manual, Section 71-05-00, dated July 15, 1977). (5) Inspect the main oil filter for contamination and, based on the inspection results, accomplish the applicable procedures specified in PWC PT6A-50 Maintenance Manual, Section 79-25-04. (c) Reinspect the main oil filter, thereafter, at intervals not to exceed 100 hours in service since last inspection in accordance with the requirements of paragraph (b) (5) above. If visible metallic debris is evident, accomplish paragraph (b) (1) above prior to further flight. (d) Remove, inspect, and reinstall the chip detector of non-installed engines, in accordance with paragraphs (b) (1), (b) (2), and (b) (3) above, prior to entering service. (e) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where the priority letter AD can be accomplished. (f) Upon request, an equivalent means of compliance with the requirements of this priority letter AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. (g) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, may adjust the compliance times specified in this priority letter AD. The applicable engine manufacturer's alert SIL No. 4019 and Maintenance Manual, Sections 79-35-02 and 79-25-04, may be obtained from Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1. The applicable aircraft Maintenance Manual, Section 71-05-00, may be obtained from Boeing Canada, DeHavilland Division, Garrett Boulevard, Downsview, Ontario, Canada M3K 145. The documents referenced inthis priority letter AD also may be examined at the Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket No. 88-ANE-38, between the hours of 8:00 a.m. and 4:30 p.m. Monday through Friday except federal holidays. This priority letter AD 88-24-02 is effective immediately upon receipt.
2019-24-17: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model MD-90-30 airplanes. This AD was prompted by reports indicating that certain center wing stringers and skins are potentially susceptible to cracking. This AD requires repetitive eddy current, low frequency (ETLF) inspections of the left and right side fastener holes for any crack; repetitive eddy current, high frequency (ETHF) inspections of the lower skin for any crack; and repair if any crack is found. The FAA is issuing this AD to address the unsafe condition on these products.
99-01-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage; and corrective action, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane.
2021-09-16: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report of a number of low altitude engine surge incidents during takeoff. This AD requires revising the existing airplane flight manual and applicable corresponding operational procedures to provide the flightcrew with procedures to require the engine bleeds to be ''ON'' during takeoff. The FAA is issuing this AD to address the unsafe condition on these products.
74-09-02: 74-09-02 PIPER: Amendment 39-1816. Applies to Model PA-32-260 Airplanes, Serial Numbers 32-7300001 through 32-7300024 and Model PA-32-300, Serial Numbers 32-7340001 through 32-7340081, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To provide an unobstructed view of the stall warning light, accomplish the following: Relocate stall warning light in accordance with Piper Service Bulletin Number 403 or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320. 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. 522(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Piper Aircraft Corporation, Vero Beach Division, Vero Beach, Florida 32960. These documents may also be examined at the FAA, Southern Region, 3400 Whipple Avenue, East Point, Georgia 30344 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the FAA, Southern Region office. This amendment becomes effective April 18, 1974.
98-07-14: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
2007-20-02: The FAA is adopting a new airworthiness directive (AD) for all Viking Air Limited Model DHC-7 airplanes. This AD requires an inspection of certain SM-200 servo drive units (power servo motor and housing assemblies) for certain markings, related investigative action if necessary, and modification if necessary. This AD results from a report that some SM-200 servo drive units that were not in configuration MOD H are installed on Model DHC-7 airplanes. MOD H prevents the internal clutch fasteners from backing out. We are issuing this AD to prevent the possibility of internal clutch fasteners from backing out, which could cause an inadvertent servo engagement and consequent reduced controllability of the airplane.
2007-19-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: While they were gaining access to the THS (trimmable horizontal stabilizer) fuel tank for maintenance check, several operators have found one or several of the 8 THS hoist point fitting bases cracked or broken-off. The breakage resulted in metallic debris being released within the Trim Tank. The origin of the damage is most probably due to interference with the THS hoisting lugs that are stowed in the hoist point fittings in the reverse position, being screwed too deep inside the THS hoist fittings. Damaged hoist point fittings could cause the release of metallic debris within the THS fuel system. * * * Compliance with the requirements of this AD will also eliminate potential contributing factor[s] to ignition risks. We are issuing this AD to require actions to correct the unsafe condition on these products.
2019-23-11: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Model GVI airplanes. This AD requires revising the airplane flight manual (AFM) for your airplane by adding an airplane flight manual supplement (AFMS), which contains operating limitations and abnormal procedures for loss of rudder or yaw damper. This AD was prompted by a report of an inflight rudder surface shutdown that resulted in lateral-directional oscillations of the airplane. The FAA is issuing this AD to address the unsafe condition on these products.
73-14-02: 73-14-02 PIPER: Amdt. 39-1673. Applies to PA-34-200 airplanes, Serial Numbers 34-E4 and 34-7250001 and up equipped with exhaust systems Piper Part Numbers 96465-00 and 96466-00. Compliance required within the next 10 hours time in service after the effective date of this AD or before the accumulation of 60 hours time in service whichever occurs later and thereafter at intervals not to exceed 25 hours time in service from the last inspection. To insure that cracks are not present in the exhaust system, accomplish the following: (a) Remove both right and left nose cowls, Piper Part Numbers 96500-34 and 96500-35, and open both right and left cowl doors on both right and left engines. Inspect the entire exhaust system for any evidence of cracks or failed ducts or flanges. Use an inspection mirror as required, a minimum 100 watt light and a minimum four power magnifying glass. (b) If the exhaust systems are found to contain cracked or broken ducts, flanges or parts, replace with new replacement parts or repair the affected parts in accordance with Advisory Circular 43.13-1 before further flight. Piper Service Bulletin No. 373A pertains to this subject. This supersedes amendment 39-1564 (37 F.R. 25221) AD 72-25-01. This amendment becomes effective June 29, 1973.
82-23-05: 82-23-05 GULFSTREAM AMERICAN: Amendment 39-4492. Applies to Model 685 (S/Ns 12000 through 12043, and 12045 through 12066) airplanes certificated in any category. COMPLIANCE: Required within 25 hours after the effective date of this AD, unless already accomplished. To prevent possible contamination of cabin air by engine exhaust, accomplish the following: (a) Replace the existing induction air elbow with an improved P/N 610597-501 elbow and inspect the exhaust system in accordance with Gulfstream American Corporation Service Bulletin No. 192 dated August 20, 1982. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used if approved by the Manager, Aircraft Certification Division, ASW-100, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 624-4911, extension 511. This amendment becomes effective on November 15, 1982.
84-02-07: 84-02-07 AVCO LYCOMING WILLIAMSPORT DIVISION: Amendment 39-4856. Applies to Avco Lycoming Model LTS101-600A-2 gas turbine engines. Compliance is required as indicated (unless already accomplished). To prevent power loss and power turbine overspeed, accomplish the following: 1. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, part numbers (P/Ns) 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines which have had the torquemeter gear assembly replaced without concurrent replacement of the output gear assembly, and which presently have output gear assembly P/Ns 4-081-120-11, -12, -13, or -14 installed, within the next 25 operating hours. 2. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, P/Ns 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines which have had the output gear assembly replaced without concurrent replacement of the torquemeter gear assembly, and which presently have output gear assembly P/Ns 4-081-120- 11, -12, -13, or -14 installed, within the next 25 operating hours. 3. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, P/Ns 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines having output gear assembly P/Ns 4-081-120-11, -12, -13, or -14 installed, within the next 100 operating hours or before reaching 1,000 operating hours, whichever occurs later. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulation (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, FAA, New England Region. This amendment becomes effective May 7, 1984, as to all persons except those persons to whom it was made immediately effective by priority letter AD 84-02-07, issued January 27, 1984, which contained this amendment.
2019-23-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
72-24-02: 72-24-02 PIPER: Amendment 39-1557. Applies to Model PA-28-140, PA-28-150, PA- 28-160, PA-28-S-160, PA-25 (150 HP) airplanes, equipped with Lycoming O-320 engines and Marvel Schebler carburetors Model MA-4SPA, Part Number 10-3678-32 certificated in all categories. Compliance required within the next 10 hours' time in service after the effective date of this airworthiness directive, unless already accomplished: To prevent power interruption as a result of abrupt throttle movement, accomplish the following: (a) Attach the following operating limitation placard to the instrument panel near the throttle control in full view of the pilot using 1/8" minimum size type: "DO NOT OPEN THE THROTTLE RAPIDLY. (IDLE TO FULL THROTTLE IN 2 SECONDS MINIMUM.)" The placard may be fabricated by the owner/operator. This amendment becomes effective November 17, 1972.
96-01-01: This amendment adopts a new airworthiness directive (AD) that is applicable to Hamilton Standard Propeller Models 14RF-9, 14RF-19, 14RF-21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F. This action supersedes priority letter AD 95-18-06 R1, that was issued on August 30, 1995, that currently requires ultrasonic shear wave inspection on all Hamilton Standard 14RF-9 propeller blades, and ultrasonic shear wave inspection on certain Hamilton Standard Propeller Models 14RF-19, 14RF-21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propeller blades. This action requires that all blades of applicable Hamilton Standard propellers be calibrated for ultrasonic transmissibility before conducting the ultrasonic shear wave inspection. This action improves the crack detection capability of the ultrasonic shear wave inspection.This action also decreases the repetitive inspection interval for the 14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 from 1,250 flight cycles to 500 flight cycles. This action also establishes a new ultrasonic shear wave inspection interval of 1,000 flight cycles for the 14RF-19 and 2,500 flight cycles for the 14RF-21 and the 6/5500/F. This AD also removes 14SFL11 propellers from service. This AD is prompted by reports that the existing ultrasonic shear wave inspection may not detect cracks as originally determined with some blades due to geometric differences. The actions specified by this AD are intended to prevent separation of a propeller blade due to cracks initiating in the blade taper bore, that can result in aircraft damage, and possible loss of the aircraft.
97-08-04: 97-08-04 AIRBUS INDUSTRIE: Amendment 39-9992. Docket 96-NM-93-AD. Applicability: Model A320-111, -211, -212, and -231 series airplanes, as listed in Airbus Service Bulletin A320-53-1110, dated August 28, 1995; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.Compliance: Required as indicated, unless accomplished previously. To prevent structural damage to the tail section of the airplane when it strikes the runway which, if undetected, could result in depressurization of the fuselage during flight, accomplish the following: (a) Within 6 years after the effective date of this AD, modify the fuselage by reinforcing frames 68 and 69 in accordance with Airbus Service Bulletin A320-53-1110, dated August 28, 1995. (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, 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. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The actions shall be done in accordance with Airbus Service Bulletin A320-53-1110, dated August 28, 1995. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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. (e) This amendment becomes effective on May 15, 1997.