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2021-07-10:
The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report that some piccolo ducts for the wing anti-ice system have bleed holes that do not conform to requirements. This AD requires, depending on airplane configuration, inspection for the presence of affected wing anti-ice system piccolo ducts and corrective actions, or replacement of affected piccolo ducts with new piccolo ducts. The FAA is issuing this AD to address the unsafe condition on these products.
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96-24-03:
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing 747-400 series airplanes in the "combi" configuration. This action requires replacing the decompression panels that are located in the smoke barrier between the passenger and main deck cargo compartment, with new panels of an improved design. This amendment is prompted by reports indicating that normal pressurization cycles are causing premature tearing or opening of these decompression panels. The actions specified in this AD are intended to prevent increased airflow in the cargo compartment caused by the tearing or opening of these panels; this condition, if not corrected, could result in delayed fire detection and reduced effectiveness of the cargo compartment fire suppression system.
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2009-04-07:
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:
An A330 aircraft experienced a sudden [uncommanded] nose down order [event] while in cruise. This order was preceded by an automatic autopilot disconnection and triggering of the "NAV IR1 FAULT'' Electronic Centralised Aircraft Monitor (ECAM) Caution.
Investigations highlighted that at time of the event the Air Data Reference 1 (ADR) part of ADIRU1 [Air Data Inertial Reference Unit] was providing erroneous and temporary wrong parameters in a random manner. This abnormal behaviour of the ADR1 led to several consequences such as unjustified stall and over speed warnings, loss of attitude information on Captain Primary Flight Display (PFD) and several ECAM warnings. Among the abnormal parameters, the provided Angle of Attack (AoA) value was such that the flight control computers commanded a sudden nose down aircraft movement, which constitutes an unsafe condition. * * *
* * * * *
These anomalies could result in high pilot workload, deviation from the intended flight path, and possible loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
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2021-04-11:
The FAA is superseding Airworthiness Directive (AD) 2020-01- 10, which applied to certain Airbus SAS Model A350-941 airplanes. AD 2020-01-10 required installing flight control and guidance system (FCGS) software (SW) X11 Standard (STD). This AD retains the requirements of AD 2020-01-10, requires modifying the electrical power supply of the air generation system (AGS) ram air outlet door actuators, and expands the applicability by adding airplanes, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by the development of a modification that forces the AGS ram air outlet doors to be flush in cases of total engine flameout or loss of the main electrical supply. Because of this additional modification, certain airplanes that were excluded from the applicability of AD 2020-01-10 are included in the applicability of this AD. The FAA is issuing this AD to address the unsafe condition on these products.
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76-09-06:
76-09-06 SIAI-MARCHETTI: Amendment 39-2595. Applies to Model S205 airplanes, S/N 5-406 and below, and Model S208 airplanes, S/N 4-64 and below, certificated in all categories.
Compliance is required as indicated.
To prevent a possible loss of aileron control, accomplish the following:
(a) Within 10 hours time in service after the effective date of this AD, unless already accomplished within the preceding 15 hours time in service and thereafter, at intervals not to exceed 25 hours time in service from the last inspection, visually inspect the rear wing spar for cracks in accordance with paragraph (a) of the 'INSTRUCTIONS" section of SIAI Marchetti Service Bulletin No. 205B42, dated January 3, 1976, or an FAA-approved equivalent.
(b) If a crack is found during an inspection required by paragraph (a) of this AD, before further flight, repair and reinforce the rear wing spar adjacent to the inboard and outboard aileron hinge attachments in accordance with paragraphs (c) and (d) of the "INSTRUCTIONS" section of SIAI Marchetti Service Bulletin No. 205B42, dated January 3, 1976, or an FAA- approved equivalent, except that, for SIAI Marchetti Model S205 airplanes, S/N's 101 through 222, 224, 228, 229, 231, 232, and 233, the reinforcement provisions of paragraph (c) of the Service Bulletin need not be accomplished.
(c) The repetitive inspections required by paragraph (a) of this AD may be discontinued after the repair and reinforcement required by paragraph (b) of this AD is accomplished.
This amendment becomes effective May 10, 1976.
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2021-07-12:
The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by a reassessment of the flight control system. This AD requires modification of the cyclic stick, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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96-23-02:
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires inspections to detect disbonding, corrosion, and cracking at the longitudinal rows of fasteners in the bonded skin panels in section 41 of the fuselage, and repair, if necessary. This amendment is prompted by a report of skin cracking due to disbonding of the internal doubler of the cracked skin panels. The actions specified in this AD are intended to prevent rapid decompression of the airplane due to disbonding and subsequent cracking of the skin panels.
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2021-07-06:
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a determination that certain airplanes have outdated magnetic variation (MagVar) tables inside navigation systems. This AD requires revising the existing airplane flight manual (AFM) to update the Flight Management System (FMS) and Inertial Reference System (IRS) limitations. The FAA is issuing this AD to address the unsafe condition on these products.
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76-17-07:
76-17-07 BOEING: Amendment 39-2706. Applies to Boeing Model 727-100 series airplanes certificated in all categories with static port heater circuits deactivated. Compliance required as indicated unless already accomplished. \n\tTo prevent the loss of altitude and airspeed reference due to a small amount of water freezing in the static port system, accomplish either of (1) or (2) below: \n\t(1)\tWithin the next 1,000 hours time in service after the effective date of this AD reactivate the static port heater circuits to the original FAA approved Boeing 727-100 configuration; or \n\t(2)\tWithin the next 2,000 hours time in service after the effective date of this AD replace the deactivated heater assembly, P/N 10-60723-1, with elbow fitting MS21908D6 in accordance with Boeing Service Bulletin 727-34-95 dated September 3, 1976, or later FAA approved service bulletins, and enlarge the static port sensing holes from .047 inch diameter to .125 inch diameter in accordance with Boeing ServiceBulletin 727-34-94 (to be released) or later FAA approved service bulletins. \n\tNotwithstanding the provisions of the above paragraph (1) the heater elements in one static system may be inoperative provided the aircraft is not flown in icing or precipitation conditions. \n\tBoeing 727-100 airplanes already incorporating Boeing Service Bulletin 727-25-42, Revision 1, dated March 4, 1968, with elbow fitting MS21908D6 and Boeing Service Bulletin 727-34-57 dated April 7, 1968, enlarging the static sense holes are in compliance with this AD. \n\tEquivalent modifications may be approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe 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). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective October 1, 1976.
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96-22-03:
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe series 1000A and Model Hawker 1000 airplanes, that requires modifications of the thrust reversers. This amendment is prompted by a review of the certification analysis of the thrust reversers and by testing of the thrust reversers, which indicated that additional design features are necessary to prevent failure of the driver link and the inadvertent deployment of a thrust reverser during flight. The actions specified by this AD are intended to prevent inadvertent deployment of a thrust reverser during flight, which could result in reduced controllability of the airplane.
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96-22-12:
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Models 1900C, 1900D, and 2000 airplanes. This action requires inspecting (one-time) the fuel filter assemblies to detect any bypass valve that is glued shut. If a bypass valve is glued shut, the AD requires replacing the associated fuel filter assembly. Three in-flight occurrences in which the low fuel pressure light illuminated prompted this action. In each of the instances, a bypass valve on the affected airplane engine was glued shut with anaerobic thread lock adhesive and when the fuel filter became clogged, proper fuel flow to the engine was not obtained. The actions specified by this AD are intended to prevent lack of fuel to the engine and eventual engine shutdown caused by a clogged fuel filter and a contaminated fuel filter bypass valve.
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93-07-04:
93-07-04 BRITISH AEROSPACE: Amendment 39-8536. Docket 92-NM-189-AD.
Applicability: Model ATP series airplanes; serial numbers 2001 through 2049, inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent possible loss of integrity and security of the flap drive system, accomplish the following:
(a) Within 14 days after the effective date of this AD, perform a one-time general visual inspection of the primary flap drive torque tubes to ensure that the four bolt and nut assemblies on the splined flanged-coupling assembly on the right gearbox drive at station 0 have split pins installed, in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992.
(1) If split pins are installed, no further action is necessary.
(2) If any split pin is missing, accomplish the requirements of both paragraphs (a)(2)(i) and (a)(2)(ii) of this AD:
(i) Prior to further flight, check tighten each of the four bolts to 8 to 10 foot pounds torque. Repeat this check tightening thereafter at intervals not to exceed 14 days.
(ii) Within 6 months after the effective date of this AD, install split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. Installation of these split pins constitutes terminating action for the inspections and check tightening requirements of this paragraph.
(b) Installation of split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992, constitutes terminating action for the requirements of paragraph (a) of this AD.
(c) 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. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, 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.
(d) 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.
(e) The inspection and installation shall be done in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. 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 Jetstream Aircraft, Inc., Librarian for Service Bulletins, P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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.
(f) This amendment becomes effective on May 10, 1993.
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2021-07-14:
The FAA is adopting a new airworthiness directive (AD) for all Yabora Industria Aeronautica S.A. Model EMB-135 and EMB-145 airplanes. This AD was prompted by a report involving disconnection of a side arm strut from the right main landing gear (MLG); a subsequent investigation found that the side arm strut lower bearing was installed inverted on the airplane. This AD requires doing a general visual inspection of the right and left MLG to verify certain conditions and doing all applicable on-condition actions, as specified in an Agencia Nacional de Aviacao Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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91-23-12:
91-23-12 LOCKHEED: Amendment 39-8081. Docket No. 91-NM-77-AD.
Applicability: Model L-1011 series airplanes, equipped with BFGoodrich brake part numbers identified in paragraph (a) of this AD, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To prevent the loss of main landing gear braking effectiveness, accomplish the following:
(a) Within 180 days after the effective date of this AD, inspect the brake part numbers shown below for wear. Any brake worn more than the maximum wear limit specified below must be replaced, prior to further flight, with a brake within this limit.
Type Certificated
Model Designation
Common Model
Designation
Maximum
GTOW
Brake
Part No.
Maximum Wear
Limit (inches)
L-1011-385-1
(-1)
430,000
2-1195-1
2.10
(-1)
430,000
2-1195-5
2.10
(-1)
430,000
2-1195-6
2.10
(-1)
430,000
2-1195-7
2.10
(-1)
430,000
2-1195-8
2.10
(-1)
430,000
2-1367
3.00
(-1)
430,000
2-1367-1
3.00
(-1)
430,000
2-1367-2
3.00
(-40)
440,000
2-1195-1
2.10
(-40)
440,000
2-1195-5
2.10
(-40)
440,000
2-1195-6
2.10
(-40)
440,000
2-1195-7
2.10
(-40)
440,000
2-1195-8
2.10
(-40)
440,000
2-1367
3.00
(-40)
440,000
2-1367-1
3.00
(-40)
440,000
2-1367-2
3.00
(-50)
450,000
2-1367-3
2.60
(-50)
450,000
2-1367-4
2.60
(-50)
450,000
2-1367-5
2.60
L-1011-385-1-14
(-100,-150,-200)
466,000
2-1367-3
2.60
(-100,-150,-200)
to
2-1367-4
2.60
(-100,-150,-200)
474,000
2-1367-5
2.60
(-250)
510,000
2-1367
3.00
(-250)
510,000
2-1367-1
3.00
(-250)
510,000
2-1367-2
3.00
L-1011-385-1-15
(-100,-150,-200)
466,000
2-1367-3
2.60
(-100,-150,-200)
to
2-1367-4
2.60
(-100,-150,-200)
474,000
2-1367-5
2.60
(-250)
510,000
2-1367
3.00
(-250)
510,000
2-1367-1
3.00
(-250)510,000
2-1367-2
3.00
L-1011-385-3
(-500)
496,000
2-1367
3.00
(-500)
to
2-1367-1
3.00
(-500)
516,000
2-1367-2
3.00
NOTE: Lockheed Service Bulletin 093-32-253, dated March 29, 1991, contains additional information concerning Model L-1011 brake configurations.
(b) Within 180 days after the effective date of this AD, incorporate the maximum brake wear limits specified in paragraph (a) of this AD into the FAA-approved maintenance inspection program.
(c) 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 Aircraft Certification Office (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.
(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.
This amendment (39-8081, AD 91-23-12) becomes effective on December 9, 1991.
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96-21-10:
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
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96-21-01:
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, that requires either replacement or modification of the hydraulic damper assembly. This amendment is prompted by reports indicating that insufficient damping of the hydraulic shimmy damper in the main landing gear (MLG) can allow high torsional vibration to occur. The actions specified by this AD are intended to prevent such vibration, which can damage the MLG assembly and lead to its collapse.
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93-04-02:
93-04-02 ROCKWELL INTERNATIONAL/COLLINS AVIATION DIVISION: Amendment 39-8504. Docket No. 93-CE-18-AD.
Applicability: TDR-94D Mode S transponders, P/N CPN 622-9210-002, installed on, but not limited to the following, certificated in any category:
Aerospatiale ATR-42 and ATR-72 series airplanes
Saab 340A and 340B airplanes
Short Model SD3-60 airplanes
de Havilland DHC-7 and DHC-8 series airplanes
British Aerospace ATP airplanes
Gulfstream G-II, G-III, and G-IV series airplanes
Dassault Mystere-Falcon 50, Mystere-Falcon 200,
and Mystere-Falcon 900 airplanes
Canadair Challenger CL-601 airplanes
British Aerospace HS 125-700A airplanes
Beechcraft 300 series airplanes
Compliance: Required as indicated, unless already accomplished.
To prevent a mid-air collision or a near-miss situation caused by failure of these Mode S transponders, accomplish the following:
(a) Within the next 10 calendar days after theeffective date of this AD, fabricate a placard with the following words in letters at least 0.10-inch in height and install this placard within the pilot's clear view on the instrument panel: "OPERATION OF TCAS II IN ANY MODE OTHER THAN THE "TA ONLY" MODE IS PROHIBITED."
(b) Within the next 6 calendar months after the effective date of this AD, modify the software of the Mode S transponders in accordance with the Accomplishment Instructions section of Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 1992. The placard required by paragraph (a) of this AD is no longer required after this modification is incorporated.
(c) If parts for the above modification are not available, the airplane operator may comply with the placard requirement of paragraph (a) of this AD until the modification is incorporated based upon a schedule established by the manufacturer through the Atlanta Aircraft Certification Office.
(d) Special flight permits may be issuedin accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office.
(f) The modification required by this AD shall be done in accordance with Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 1992. 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 Rockwell International/Collins General Aviation Division, 1100 West Hibiscus Boulevard, Melbourne, Florida 32901. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., 7th Floor, suite 700, Washington, DC.
(g) This amendment becomes effective on March 26, 1993.
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2021-07-03:
The FAA is superseding Airworthiness Directive (AD) 2015-05- 03, which applied to certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2015-05-03 required revising the existing maintenance or inspection program, as applicable, to incorporate new or revised maintenance requirements and airworthiness limitations, and incorporating structural repairs and modifications to preclude widespread fatigue damage (WFD). This AD continues to require the actions specified in AD 2015-05-03. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, and incorporating additional structural repairs and modifications to preclude WFD. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary, as well as the corresponding structural repairs and modifications to preclude WFD. The FAA is issuing this AD to addressthe unsafe condition on these products.
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2005-18-01:
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT7-5A2, -5A3, -7A, -7A1, -9B, -9B1, and -9B2 turboprop engines, with stage 2 turbine aft cooling plate, part number (P/N) 6064T07P01, 6064T07P02, 6064T07P05, or 6068T36P01 installed. This AD requires a onetime eddy current inspection (ECI) of certain P/N stage 2 turbine aft cooling plate boltholes. This AD results from reports of six stage 2 turbine aft cooling plates found cracked during inspection. We are issuing this AD to prevent stage 2 aft cooling plate separation, resulting in uncontained engine failure and damage to the airplane.
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78-17-04:
78-17-04 GENERAL DYNAMICS: Amendment 39-3283. Applies to all Model 340 and 440 series and C-131E airplanes in passenger configuration, including those modified for turbopropeller power, certificated in all categories.
To insure that the passenger emergency escape window release handle access door can be opened, accomplish the following:
(a) Within the next 10 hours time in service from the effective date of this AD unless already modified in accordance with paragraph (c) or (d), check each passenger emergency escape window release handle cover assembly to assure that the release handle access door swings open without restriction. If the release handle access door cannot be opened, modify the cover assembly per General Dynamics Alert Service Bulletin 640(340D)-25-A10 dated July 12, 1978 prior to the next flight.
(b) Repeat the checks specified in (1) on all unreworked cover assemblies prior to first flight of each day pending accomplishment of the rework defined in General Dynamics Alert Service Bulletin 640(340D)-25-A10 dated July 12, 1978.
(c) Within 30 days or 50 hours time in service, whichever occurs earlier from the effective date of this AD, accomplish the rework defined in the General Dynamics Service Bulletin noted in paragraph (b) at which time checks required by this AD may be discontinued.
(d) Alternate methods of insuring that the release handle access door can be opened may be used if approved by the Chief, Aircraft Engineering Division, FAA, Western Region.
(e) The checks specified in this AD may be performed by flight crew personnel.
(f) Record the accomplishment of check in a record maintained by the operator.
This amendment becomes effective September 5, 1978.
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92-06-12:
92-06-12 BELL HELICOPTER TEXTRON, INC.: Amendment 39-8192. Docket No. 90-ASW-48.
Applicability: All Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, certificated in any category, with the main transmission sungear, part number (P/N) 206-040-662-101, installed.
Compliance: Required as indicated, unless already accomplished.
To prevent premature wear of the sungear and mating spur gears which could result in transmission failure, accomplish the following:
(a) At the next inspection interval for the main transmission sungear, P/N 206-040-662-101, but no later than 1,500 hours' time in service after the effective date of this AD, remove and replace sungears which have the following serial numbers:
SD-0005
SD-0010
SD-0020
SD-0022
SD-0023
SD-0024
SD-0025
SD-0026
SD-0027
SD-0031
SD-0033
SD-0034
SD-0035
SD-0036
SD-0037
SD-0039
SD-0040
SD-0043
SD-0044
SD-0046
SD-0054
SD-0055
SD-0057
SD-0060
SD-0062
SD-0065
SD-0066
SD-0067
SD-0068
SD-0069
SD-0071
(b) In conjunction with (a), inspect the pinion spur gears which mate with the above listed sungears for micro pitting or hardlines in the gear teeth due to the insufficient tip relief, or improper tooth profile of the sungear. Determine if wear or damage is within specified limits according to the applicable BHTI maintenance, repair and overhaul manuals.
(c) If wear or damage exceeds the specified limits, remove and replace the affected spur gears with serviceable parts before further flight.
(d) An alternative method of compliance or adjustment of the compliance times which provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Certification Office, ASW-170, Rotorcraft Directorate, Aircraft Certification Service, FAA, Fort Worth, Texas, 76193-0170.
(e) Bell Helicopter Textron, Inc., Alert Service Bulletins No. 206-90-56, Rev. A, dated 1/15/91 or 206L-90-69, Rev. A, dated 1/15/91, as applicable, provide an acceptable, alternate means of compliance with this AD.
(f) This amendment becomes effective on April 13, 1992.
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96-20-05:
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires repetitive operational tests to verify proper deployment of the ram air turbine (RAT), and replacement of the rotary actuator motor with a new or serviceable rotary actuator motor, if necessary. This amendment is prompted by reports of corroded rotary actuator motors of the RAT found on in-service airplanes. The actions specified by this AD are intended to ensure that the RAT actuator motor is not corroded to the point where it may result in the failure of the RAT to deploy and subsequently result in loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.
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2021-07-04:
The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport Regional Model ATR42 airplanes and Model ATR72 airplanes. This AD was prompted by in-service data, which revealed that the minimum operating airspeeds in severe icing conditions, computed to provide adequate stall margins, do not provide sufficient margins to stall speeds at high bank angle while exiting severe icing conditions. This AD requires revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to provide emergency procedures and limitations for operating in severe icing conditions, 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.
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92-24-04:
92-24-04 BOEING: Amendment 39-8409. Docket No. 92-NM-103-AD. \n\n\tApplicability: Model 737-300, -400, and -500 series airplanes; as listed in Boeing Alert Service Bulletin 737-78A1055, dated April 2, 1992, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent uncommanded deployment of the thrust reverser, accomplish the following: \n\t(a)\tWithin 12 months after the effective date of this AD, modify the engine thrust reverser control system, in accordance with Boeing Alert Service Bulletin 737-78A1055, dated April 2, 1992. \n\n\t(b)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n \n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Seattle ACO. \n\n\t(c)\tSpecial 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. \n\n\t(d)\tThe modification shall be done in accordance with Boeing Alert Service Bulletin 737-78A1055, dated April 2, 1992. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\t(e)\tThis amendment becomes effective on December 14, 1992.
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96-19-13:
This amendment adopts a new airworthiness directive (AD), applicable to certain Gates Learjet Model 35 and 36 series airplanes that have been modified in accordance with Raisbeck Supplemental Type Certificate (STC) SA766NW, that requires a reduction of the maximum operating limit speed on the affected airplanes to prevent encountering certain potentially hazardous conditions. This amendment is prompted by reports of incidents of aileron buffet or buzz experienced during high speed cruise. The actions specified by this AD are intended to prevent aileron buffet or buzz conditions, which can result in the deterioration of the aircraft lateral control system characteristics to an unacceptable level.
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