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2022-14-01: The FAA is superseding Airworthiness Directive (AD) 2019-03- 25, which applied to certain Airbus SAS Model Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-03-25 required repetitive inspections of the center and outer wing box lower stiffeners and panels at a certain junction on the left- and right-hand sides for any cracking, and repair if necessary. AD 2019-03-25 also provided an optional modification, which would terminate the repetitive inspections. This AD was prompted by a determination that, for certain airplanes, the compliance time for the initial inspection is inadequate and must be revised. This AD continues to require the actions specified in AD 2019-03-25 with revised compliance times for certain airplanes and additional actions for certain airplanes, and expands the applicability, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-03-08: 91-03-08 LEARJET (FORMERLY GATES LEARJET): Amendment 39-6876. Docket No. 90-NM-285-AD. Applicability: Model 31 series airplanes, Serial Numbers (S/N) 001 through 023; Model 35/35A series airplanes, S/N 001 through 661; Model 36/36A series airplanes, S/N 001 through 059, 062, and 063; and Model 55/55B/55C series airplanes, S/N 001 through 144; equipped with Aerospace Lighting Corporation (ALC) inverters, Part Number (P/N) 18.95(); or Instrument and Flight Research (IFR) inverters, P/N 25-415-3-0L or 250001-240G; or Precision Winding, Incorporated inverters, P/N 6900092 or 6900054-54; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent electromagnetic interference, and smoke and/or fire in the cabin, accomplish the following: A. Within 25 hours time-in-service after the effective date of this AD, deactivate the cabinet and overhead fluorescent lighting systems, and fabricate and install placards on the deactivated circuit breakers in accordance with the accomplishment instructions specified in the following Learjet Alert Service Bulletins, all dated December 21, 1990: Model Service Bulletin 31 31-33-2A 35, 35A, 36, 36A 35/36-33-5A 55, 55B, 55C 55-33-3A NOTE: This AD applies only to airplanes with the following inverters: ALC inverters, Part Number (P/N) 18.95(); or IFR inverters, P/N 25-415-3-0L or 250001-240G; or Precision Winding, Incorporated inverters, P/N 6900092 or 6900054-54. Inverters having a different part number do not have to be deactivated. B. 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, Wichita Aircraft Certification Office (ACO), ACE-115W, FAA, Central Region, 1801 Airport Road, Room 100, Wichita, Kansas 67209. NOTE: The request should be submitted directly to the Manager, Wichita ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Wichita ACO. C. 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 Learjet Corporation, Customer Services, P.O. Box 7707, Wichita, Kansas 67277-7707. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas. This amendment (39-6876, AD 91-03-08) becomes effective on February 12, 1991.
99-11-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires detailed visual inspections to detect corrosion or chrome plating cracks on the fuse pins of the outboard support of the main landing gear (MLG) beam. This AD also would require either installation of the existing fuse pins and repetitive inspections; or installation of newer-type fuse pins, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report indicating that corrosion was found on a fuse pin in the outboard support of the MLG beam. The actions specified by this AD are intended to detect and correct such corrosion and cracking, which could result in the failure of a fuse pin and, consequently, lead to collapse of the MLG.
80-01-07 R1: 80-01-07 R1 ROCKWELL INTERNATIONAL: Amendment 39-3658 as amended by Amendment 39-3774. Applies to Rockwell Model NA 265-60 and NA 265-80 airplanes equipped with the Raisbeck Mark Five modification in accordance with STC SA687NW or STC SA847NW. To prevent failure of the wing flap support structure accomplish the following: A. On or before 430 landings after modification by The Raisbeck Group STC SA687NW, unless already accomplished, replace the outboard flap track support plates in accordance with FAA approved Raisbeck Group Service Bulletin No. 17. B. If the flap system was previously affected by AD 79-13-02, the number of landings specified in Paragraph A may be increased by the total number of landings accomplished with inoperative flaps. C. On or before 10 further landings, unless previously accomplished, perform an eddy current inspection of the flap track support structure in accordance with FAA approved Raisbeck Service Bulletin No. 18, Rev. B, on airplanes having the following serial numbers: 306- 005, 006, 012, 024, 050, 071, 109, 116, 119, 122, 380-025. For all other serial numbers, perform the above inspection prior to 100 landings after modification by Raisbeck STC SA687NW or STC SA847NW. If cracks are found, immediately inform William M. Perrella, Engineering and Manufacturing Branch, FAA Northwest Region, telephone (206) 767-2516. Before further flight, repair cracks in accordance with a method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. D. Effective before further flight, the full flap extension speed is reduced from 180 knots IAS to 160 knots IAS and the 20 degree flap extension speed is reduced from 225 knots IAS to 180 knots IAS. Install a placard in full view of the flight crew which specifies these speeds. E. The life of the flap track support structure after modification by the Raisbeck Group STC SA687NW or STC SA847NW is limited to 900 landings, except for airplane S/N 306-116 which is limited to 450 landings. F. Reinspect the flap track support structure for cracks in accordance with FAA approved Raisbeck Service Bulletin No. 18, Rev. B, or methods approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, at intervals not to exceed 100 landings. G. Alternate modifications which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. H. Modification of the flap support structure per FAA approved Raisbeck Service Bulletins 17, dated October 5, 1979; 19, Rev. B, dated April 28, 1980; and 23, dated November 30, 1979, constitutes terminating action under the provisions of this AD. Equivalent modifications are acceptable if approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. If the optional bolts listed in Paragraph III of Raisbeck Service Bulletin 23 are used, they must be replaced at intervals not exceeding 900 landings. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to The Raisbeck Group, 7777 Perimeter Road, Seattle, Washington 98108. Amendment 39-3658 became effective upon publication in the Federal Register and was effective earlier to all recipients of the emergency AD dated October 26, 1979. This Amendment 39-3774 becomes effective June 3, 1980.
2013-22-01: We are adopting a new airworthiness directive (AD) for Bell Model 206L-4 and 407 helicopters. This AD requires replacing or reworking certain aft bearing caps. This AD was [[Page 65179]] prompted by the manufacture of certain freewheel aft bearing caps without a lubrication channel to allow oil flow into the aft bearing support assembly. The actions of this AD are intended to prevent failure of the freewheel unit and subsequent loss of control of the helicopter.
2010-14-18: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Model 767-200, -300, and -300F series airplanes. The existing AD currently requires repetitive inspections to detect discrepancies of the 8 aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions if necessary. The existing AD also requires repetitive inspections for cracks of the closeout angle that covers the 2 aft-most fasteners in the lower tang of the midspar fitting, and related investigative and corrective actions if necessary. The existing AD also provides an optional terminating action for the repetitive inspections. This new AD reduces the compliance times for doing the inspections. This AD results from reports of cracks in the midspar fitting tangs. We are issuing this AD to detect and correct fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine.
93-11-09: 93-11-09 DE HAVILLAND, INC.: Amendment 39-8599. Docket 92-NM-205-AD. Applicability: All Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent degradation of the structural capabilities of the affected airplanes, accomplish the following: (a) For all affected airplanes: Within 6 months after the effective date of this AD, replace the six MS rivets with hi-strength Hi-Lok fasteners, Modification 7/2572, in the drag strut attachment fitting of the nose landing gear, in accordance with de Havilland Service Bulletin S.B. 7-53-32, dated March 15, 1991. (b) For airplanes having serial numbers 3 through 27, inclusive: Installation of a new outer drag strut attachment fitting, Modification 7/1328, in accordance with de Havilland Service Bulletin 7-53-31, dated December 15, 1989, as revised by Notice of Status Change 7-53-31-1, dated April 20, 1990, constitutes an acceptable alternative method of compliance with the requirements 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, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (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 replacement shall be done in accordance with de Havilland Service Bulletin S.B. 7-53-32, dated March 15, 1991. The installation shall be done in accordance withde Havilland Service Bulletin 7-53-31, dated December 15, 1989; and Notice of Status Change 7-53-31-1, dated April 20, 1990, for de Havilland Service Bulletin 7-53-51, dated December 15, 1989. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, Engine and Propeller Directorate, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on July 22, 1993.
99-11-11: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model SA-365N, N1 and SA-366G1 helicopters, that currently requires repetitive inspections of the main gearbox (MGB) magnetic chip plug and oil filter if certain part number/modification level MGB's are installed. This new action expands the helicopter model and MGB applicability to include the SA-365N2 and N3 helicopters and all variants of the MGB. It also requires installing a MGB planetary gear shaft (gear shaft) vibration level monitoring unit (VLMU); inserting procedures into the Rotorcraft Flight Manual (RFM) for a preflight vibration check using the VLMU and inserting a related emergency procedure and limitation for an inoperative VLMU into the RFM. This action is prompted by two occurrences of gear shaft cracks. The actions specified by this AD are intended to detect cracks in the MGB planetary gear shaft, which could lead to failure of the MGB and subsequent lossof control of the helicopter.
95-01-03: 95-01-03 DASSAULT AVIATION: Amendment 39-9114. Docket 94-NM-227-AD. Applicability: Model Mystere-Falcon 50 series airplanes having serial numbers 2 through 232 inclusive, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case doesthe presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent an electrical fire due to damage of the electrical wire bundles, accomplish the following: (a) Within 20 days after the effective date of this AD, measure the clearance between the electrical bundles in the left-hand cabinet and the counterbalancing actuator of the passenger door, in accordance with Dassault Aviation Alert Service Bulletin F50-A243 (F50-A39-1), Revision 1, dated November 10, 1994. (1) If the clearances are within the limits specified in the alert service bulletin, no further action is required by this AD. (2) If the clearances are outside the limits specified in the alert service bulletin, prior to further flight, reroute and clamp the wire bundles in accordance with the alert service bulletin. (b) An alternative method of compliance or adjustment ofthe 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 measuring, rerouting, and clamping shall be done in accordance with Dassault Aviation Alert Service Bulletin F50-A243 (F50-A39-1), Revision 1, dated November 10, 1994. This incorporation by referencewas 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 Falcon Jet Corporation, P.O. Box 967, Little Rock, Arkansas 72203-0967. 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 January 18, 1995.
2022-14-08: The FAA is superseding Airworthiness Directive (AD) 2008-16- 06, which applied to all BAE Systems (Operations) Limited Model 4101 airplanes. AD 2008-16-06 required the installation of additional bonding leads, inspection of existing bonding leads for defects, inspection of fuel system pipe runs in the wings to ensure appropriate clearances are maintained, and corrective actions. This AD continues to require the actions in AD 2008-16-06, and adds a requirement to install additional bonding leads around the crossfeed valve and accomplish a resistance check. This AD was prompted by a report that there is insufficient bonding of the crossfeed valve in the fuel tank area. The FAA is issuing this AD to address the unsafe condition on these products.
99-11-05: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that requires repetitive displacement tests of the secondary slide in the dual concentric servo valve of the power control unit (PCU) for the rudder, and replacement of the valve assembly with a modified valve assembly, if necessary. This amendment is prompted by reports of cracking found in PCU secondary servo valve slides. The actions specified by this AD are intended to prevent failure of the secondary slide and consequent rudder hardover and reduced controllability of the airplane.
91-11-12: 91-11-12 BRITISH AEROSPACE: Amendment 39-7010. Docket No. 91-NM-16-AD. Applicability: All Viscount Model 810 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent in-flight separation of an entrance or emergency door from the airplane and subsequent decompression of the passenger cabin, accomplish the following: A. Within 90 days after the effective date of this AD, perform a non-destructive testing (NDT) X-ray inspection of the forward passenger door, and of the rear entrance and rear emergency doors, for incorrectly machined door operating torque shaft coupling sleeves, in accordance with Viscount Preliminary Technical Leaflet (PTL) No. 194, Revision 1, dated December 1989. B. If incorrectly machined door operating torque shaft coupling sleeves are found, prior to further flight, replace the sleeves with correctly machined serviceable parts in accordance with Viscount PTL No. 194, Revision 1, dated December 1989. 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, Standardization Branch, ANM-113, 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, 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 in order to comply with the requirements of 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7010, AD 91-11-12) becomes effective on July 1, 1991.
92-27-15: 92-27-15 DE HAVILLAND, INC.: Amendment 39-8450. Docket No. 92-NM-137-AD. Applicability: All Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent freezing of the elevator servo drum assembly, which could lead to an uncommanded pitch excursion with the autopilot engaged and reduced controllability of the aircraft, accomplish the following: (a) Within 60 days after the effective date of this AD, install a water deflector onto the front spar of the vertical stabilizer, directly over the elevator servo assembly, Modification No. 7/2605, in accordance with paragraph III. of de Havilland Service Bulletin S.B. 7-55-10, dated October 25, 1991. (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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) 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. (d) The installation shall be done in accordance with de Havilland Service Bulletin S.B. 7-55-10, dated October 25, 1991. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 8, 1993.
99-11-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Mooney Aircraft Corporation (Mooney) Model M20R airplanes. This AD requires either fabricating and installing a placard that specifies using the air conditioning system during cruise operations only or deactivating the air conditioning system so it cannot be used. This AD is the result of reports of the existence of dangerous levels of carbon monoxide during taxi, climb, and descent operations of the above-referenced airplanes. The actions specified by this AD are intended to prevent dangerous levels of carbon monoxide from entering the airplane cabin during takeoff, climb, and descent operations caused by the present flight cabin sealing design of the affected airplanes, which could result in passenger injury.
68-16-04: 68-16-04 GENERAL DYNAMICS: Amendment 39-638. AD 68-16-04 is revised as indicated. Applies to General Dynamics Model 240 airplanes equipped with Rolls Royce MK 542-4 engines and Dowty Rotol (c)R245/4-40-4.5/13 propellers in accordance with General Dynamics Supplemental Type Certificate SA1054WE (hereinafter referred to as the CV-600) and General Dynamics Model 340 and 440 airplanes equipped with Rolls Royce MK 542-4 engines and Dowty Rotol (c) R245-4-40-4.5/13 or Dowty Rotol (c)R259/4-40-4.5/17 propellers in accordance with General Dynamics Supplemental Type Certificate SA1096WE (hereinafter referred to as the CV-640). Compliance required as indicated unless already accomplished. To eliminate potential flammable fluid ignition sources in the main landing gear wheel well accomplish the following unless already accomplished: (A) Inspection requirements, CV-600 and CV-640 (1) Compliance required within the next 50 hours' time in service after the effective date of this Airworthiness Directive unless already accomplished within the last 135 hours' time in service and thereafter not to exceed 185 hours' time in service. (a) Inspect the mating surfaces of the engine exhaust duct flange joint thermal insulation collar, P/N's 2D6220119-31, -41, and -43 with the engine exhaust duct thermal insulation blanket assemblies for possible gaps. For purposes of this inspection, the engine exhaust system component temperatures shall be no greater than the outside ambient air temperature. (b) If gaps are found, the thermal insulation collar and/or adjacent thermal insulation blanket must be replaced with new or overhauled insulation collars and/or blankets. (2) Compliance required within the next 125 hours' time in service after the effective date of this Airworthiness Directive unless already accomplished within the last 125 hours' time in service and thereafter not to exceed 250 hours' time in service. (a) Inspect the engine exhaust duct flange joints for leakage by inspection of the gaskets and the internal surface of the thermal insulation collars, Part Numbers 2D6220119-31, -41, and -43, or by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) If exhaust leakage is found, replace exhaust duct flange joint gaskets with two gaskets, General Dynamics/Convair P/N 2D6220115-15, at the forward flange and two gaskets, General Dynamics/Convair P/N 2D6220127-9, at the aft flange or equivalent replacements approved by the Chief, Aircraft Engineering Division, FAA, Western Region. (3) Upon request of the operator, FAA Maintenance Inspectors, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this Airworthiness Directive to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (4) Upon completion of the work described in (B)(1)(a), below, the inspection requirement of (A) is no longer applicable. (B) Modification and Relocation Requirements, CV-600 and CV-640 (1) Within the next 4,000 hours' time in service after the effective date of this Airworthiness Directive unless already accomplished. (a) Modify the engine exhaust duct flange joint thermal insulation collars, P/N's 2D6220119-31, -41 and -43 in accordance with General Dynamics Service Bulletin 600(240D) 640(340D) S.B. No. 78-3 or later FAA approved revision or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) Modify the electrical insulation in the alternating current generator control unit (P/N 914F597) in accordance with Westinghouse Aerospace Service Bulletins 67-802 and 67-803 or later FAA approved revisions or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region.(c) Relocate the alternating current generator control unit (P/N 914F597) as follows: (i) For CV-600 aircraft, per General Dynamics Service Bulletin 600(240D) S.B. No. 24-1 or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region; and (ii) For CV-640 aircraft per General Dynamics Service Bulletin 640(340D) S.B. No. 24-2 or later FAA approved revision or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective on December 27, 1968.
86-15-06: 86-15-06 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-5363. Applies to AMD Falcon 10 series airplanes, serial numbers 1 thru 196 inclusive, and 198 thru 201 inclusive, certificated in any category. Compliance is required within 60 days after the effective date of this AD. To ensure the proper installation of the rudder servo actuator hydraulic lines, accomplish the following, unless already accomplished: A. Modify the rudder servo actuator system in accordance with AMD-BA Service Bulletin F10-27-028 (0237), dated June 24, 1983. B. 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. C. 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 and/or modifications required by this AD. All persons affected by this directive, who have not already received the appropriate service bulletin from the manufacturer, may obtain copies upon request to the AMD-BA Representative, c/o F.J.C., Teterboro Airport, Teterboro, New Jersey 07608. This document may be examined at the 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, 39-5363, becomes effective August 25, 1986.
87-18-06 R1: 87-18-06 R1 BEECH: Amendment 39-5721 as amended by amendment 39-5837 applies to model and serial numbered airplanes listed below equipped with the optional hydrolock seat recline actuators on co-pilot and third and fourth seats, certificated in any category: MODEL SERIAL NUMBERS F33A CE-919, CE-923, CE-925, CE-927, CE-929, thru CE-1083 V35B D-10348, D-10353 thru D-10403 A36 E-1422, E-1551, E-1569, E-1581, E-1594 thru E-2327 A36TC and B36TC EA-21, EA-28, EA-33 thru EA-454 E55 TE-1152, TE-1181 thru TE-1201 58 and 58A TH-1027, TH-1062, TH-1067, TH-1080 thru TH-1507 58P and 58PA TJ-210, TJ-235 thru TJ-497 58TC and 58TCA TK-107, TK-108, TK-110 thru TK-151 Compliance: Required within the next 100 hours time-in-service or the next scheduled inspection, whichever occurs first after the effective date of this revised AD, unless already accomplished per the original issuance of this AD. To prevent the co-pilot and/or passenger chair armrest from coming in contact with the seat recline actuator handle and inadvertently releasing the locking feature on the seatback, accomplish the following: (a) Replace the seat recline actuator handle on the co-pilot's and the third and fourth passenger seats that are equipped with reclining backs, with a new P/N 102-530111-5 handle assembly in accordance with the instructions in Beech Service Bulletin No. 2175, revision dated June 1987. NOTE: The third and fourth passenger seats are the seats immediately behind the pilot's and co-pilot's seats. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Dept. 52, P.O. Box 85, Wichita, Kansas 67201-0085, or may examine these documents at the FAA, Office of the Regional Counsel, 601 East 12th Street, Room 1558, Kansas City, Missouri 64106. This amendment 39-5837 revises AD 87-18-06, Amendment 39-5721, effective October 9, 1987. This amendment 39-5837 becomes effective on February 5, 1988.
2013-21-08: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR72-101, -201, - 102, -202, -211, -212, and -212A airplanes. This AD was prompted by reports of airplane incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation that resulted in engine flameouts. This AD requires installing a fuel quantity indicator (FQI) equipped with a locking adaptor on the electrical connector. We are issuing this AD to prevent an engine flame-out, which could result in reduced controllability of the airplane.
49-18-01: 49-18-01 CURTISS-WRIGHT Applies to all Models of C-46 Series airplanes used in passenger operation under provisions of Part 41, 42, or 61 of the Civil Air Regulations as specified in Sections 41.20 (f), 61.30 and Amendment 42-8. To be accomplished not later than the dates specified in above amendments as revised by Special Civil Air Regulation No. 329 and any subsequent regulations affecting these compliance dates. (This AD pertains only to combustion heater fire protection aspects of the above Regulation Amendments. Separate AD's will be issued covering fire protection for the powerplant installation and for the baggage and cargo compartments of the airplane). (1) Each heater exhaust pipe shall be completely enclosed with well-ventilated, fireproof shrouds. (2) Each heater combustion chamber shall be drained to the exterior of the airplane. All such drain lines shall be of fireproof construction and contain no traps in the normal flight or ground attitudes.(3) The heater fuel components presently mounted on top of each heater shall be located in fuel and fume proof enclosures, ventilated and drained to the exterior of the airplane. (4) The thermal overheat switches for each heater shall be rigged to shut off the fuel supply and ignition circuits of the heaters when overheating occurs. These switches must also be arranged so as to prevent their automatically recycling to "ON" once overheating has occurred. The present overheat switches are not intended to be used as cycling switches. In cycling to produce the required heat is necessary, it must be accomplished at a lower temperature by an additional cycling switch controlling a cycling solenoid. (5) A manual fuel shutoff valve shall be provided. (USAF Technical Order 01- 25LA-211 describes such an installation.) (6) Adequate fire extinguisher and fire detector installations shall be provided for each heater. The fire detector installation shall contain at least one detector centrally located over the heaters in the heater area and one detector in the ventilating air duct of each heater just aft of the combustion chamber. The fire extinguisher system should provide at least 1 pound of carbon dioxide for each heater directed into the inlet side of the ventilating air stream. Instructions for operating this carbon dioxide system should also require that the ventilating air duct valve be closed when carbon dioxide is injected to the heater. With the arrangement as described, no flight tests of carbon dioxide contamination of the pilots compartment or cabin area need be conducted. As outlined in the Airworthiness Directive concerning fire protection for the baggage and cargo compartments, however, flight tests to establish smoke evacuation procedures for the cargo compartments when these compartments are carrying cargo, will need to be accomplished. The results of these tests will determine the procedure to be followed to rid the airplane of noxious gases. (7) Revision pages for the Airplane Flight Manual must be prepared to cover emergency fire procedures as well as smoke and other noxious gas elimination procedures.
93-07-05: 93-07-05 AMI INDUSTRIES, INC.: Amendment 39-8537. Docket 92-NM-184-AD. Applicability: Pilot and Co-Pilot Seats, Model 1108, serial numbers 004 to 189, inclusive; as installed in, but not limited to de Havilland Model DHC-8 series airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the pilot's and co-pilot's lap belts during air turbulence, which could lead to reduced ability of the pilots to control the airplane, accomplish the following: (a) Within 60 days after the effective date of this AD, remove the lap belt attachment links and install the improved lap belt attachment link kit, P/N 1B9014-3R, in accordance with AMI Industries, Inc., Service Bulletin 25-1108-03, dated May 20, 1992. (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, Seattle Aircraft Certification Office (ACO). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (c) 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. (d) The replacement shall be done in accordance with AMI Industries, Inc., Service Bulletin 25-1108-03, dated May 20, 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 AMI Industries, Inc., 1275 North Newport Road, Colorado Springs, Colorado 80916. 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 10, 1993.
2022-14-03: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by reports of cracked tailboom attachment bolts and barrel nuts. This AD requires replacing the upper left hand (LH) tailboom attachment bolt, visually inspecting the other three tailboom attachment bolts and all barrel nuts, repetitive torque checks of the tailboom attachment bolts, and corrective action if necessary, 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.
99-11-03: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA341G and SA342J helicopters. This action requires, before further flight, visually inspecting the external body of each main rotor head pitch-change rod (rod) for corrosion. If external corrosion is found, this action also requires a visual inspection of the inside of the body of that rod for corrosion. A rod with external corrosion that exceeds the repair criteria or a rod with any internal corrosion must be replaced with an airworthy rod. This amendment is prompted by the report of a deep internal corrosion fault in a rod found by a military helicopter operator performing a daily inspection. This condition, if not corrected, could result in failure of a rod and subsequent loss of control of the helicopter.
99-11-02: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney R-1340 series reciprocating engines, that requires initial and repetitive visual and fluorescent penetrant inspections of cylinders for head cracking. This amendment is prompted by reports of cylinder head cracking. The actions specified by this AD are intended to prevent cylinder head cracking, which can result in engine power loss, forced landing, and damage to the aircraft.
81-16-03: 81-16-03 DOWTY ROTOL LTD.: Amendment 39-4171. Applies to Dowty Rotol propellers Type R175/4-30-4/13E with hub and driving assembly, P/Ns 601022104 or 601022420 which do not have Dowty Rotol Service Bulletin 61-604 (Mod. No. (c)VP2388) incorporated, as installed on, but not limited to Fairchild F-27, F-27B, and Fokker F-27 Mks 100, 300 and 700 airplanes. Compliance is required as indicated, unless already accomplished To prevent propeller failure due to cracking of the propeller hub, accomplish the following repetitive actions until modified in accordance with paragraph (d) below: (a) Propeller hubs with less than 20,000 total hours time in service, inspect in accordance with paragraph (c) at next overhaul or prior to accumulating 22,000 total hours, whichever occurs first, and reinspect in accordance with paragraph (c) at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on allof his propellers that exceed 20,000 total hours. (b) Propeller hubs with 20,000 or more total hours time in service, inspect as follows: (1) Hubs with more than 1400 hours since last inspection or overhaul, inspect in accordance with paragraph (c) prior to accumulating 600 additional operating hours after the effective date of this AD and reinspect in accordance with paragraph (c) at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on all of his propellers that exceed 20,000 total hours. (2) Hubs with less than 1400 hours since last inspection or overhaul, inspect in accordance with paragraph (c) prior to accumulating 2000 hours since last inspection or overhaul and reinspect at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on all of his propellers that exceed 20,000 total hours. (c) Inspection Procedure: (1) During overhaul or propeller disassembly, crack test the hub front wall to snout radius in accordance with Part 2A of Dowty Rotol Service Bulletin No. 61-909 dated September 19, 1978, as revised March 12, 1979, or FAA approved equivalent. If cracks are found, replace the cracked hub with a hub known to be free of cracks. (2) For propellers between overhauls, remove, disassemble, inspect, reassemble and reinstall in accordance with Part 2B of Dowty Rotol Service Bulletin No. 61-909 dated September 19, 1978, as revised March 12, 1979, or FAA approved equivalent. If cracks are found during inspection, additional propeller disassembly is necessary to replace the cracked hub with a hub known to be free of cracks, and testing and rebalancing and resetting blade angles is necessary. (d) Terminating Action: The inspections required by this AD may be discontinued when propellers are modified by Dowty Rotol Service Bulletin 61-604 (Mod. No. (c)VP2388) dated July 1968 as revised by Revision 2 dated November 24, 1971, or FAA approved equivalent. Upon request of an operator, the Chief, Engineering and Manufacturing Branch, AGL- 210, Federal Aviation Administration, Great Lakes Region, may adjust the compliance time specified in paragraph (a) of this AD provided such requests are made through an FAA maintenance inspector, and the request contains substantiating data to justify the request for that operator. For purposes of this AD, an FAA approved equivalent must be approved by the Chief, Engineering and Manufacturing Branch, AGL-210, Federal Aviation Administration, Great Lakes Region. The manufacturer's specifications and procedures identified in the directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer may obtain copies upon request to Dowty Rotol, Inc., Staverton West, Sully Road, Box 5000, Sterling, VA 22170 or Dowty Rotol, Ltd., Cheltenham Road, Gloucester, England GL2 9QH. These documents may also be examined at the Great Lakes Region, FAA, 2300 East Devon Avenue Des Plaines, Illinois 60018. This amendment becomes effective July 28, 1981.
74-07-01: 74-07-01 BELL: Amendment 39-1801 as amended by Amendment 39-1864. Applies to all cyclic and collective main rotor control tube assemblies installed within a 30 degree angle of the vertical axis on Model 47 series helicopters, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this A.D., unless already accomplished, and thereafter at intervals not to exceed 1200 hours time in service from the last inspection. To detect corrosion and prevent possible failure of the control tube assemblies, accomplish the following inspection. (a) Remove the control tube assemblies from the helicopter and remove the rod end bearing and insert or clevis at each end of the tube assembly and clean the inside of the tube. (b) Inspect each control tube for internal corrosion using a light and borescope or equivalent inspection means. (c) Remove corroded control tubes from service prior to further flight, exceptas specified by paragraph (g) of this A.D. and submit a report of finding a corroded tube to Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA, P.O. Box 1689, Fort Worth, Texas, 76101. The control tube assembly part number, degree of corrosion found and total time in service should be included in the report. FAA Form 8330-2 may be used for this report. (Reporting approved by the Bureau of the Budget under BOB No. 04- R0174.) (d) Reinstall serviceable rod end bearings and inserts or clevis in the uncorroded and serviceable tubes using acceptable techniques, methods and practices as specified below. (1) Tubes with double drilled rivet holes, sharp nicks or scratches and internal corrosion are considered unserviceable. (2) Tubes must have internal corrosion protection using zinc chromate primer, hot linseed oil or other equivalent corrosion inhibitor. The tube ends must be sealed, air and water tight, as specified in Paragraphs 4 and 5, Part II, Bell Helicopter Company Service Bulletin No. 47-11-73-1, Rev. A, dated December 6, 1973 or later approved revision or as specified in an equivalent FAA approved procedure when the insert, rod end bearing or clevis and rivets are installed. (e) Install control tube assemblies on the helicopter and check the controls rigging and check tracking of the main rotor blades in accordance with pertinent Model 47 maintenance and overhaul information manual. (f) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D. C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D. C., and at the Southwest Regional Office in Fort Worth, Texas. (Bell Helicopter Company Service Bulletin No. 47-11-73-1, Rev. A, dated 12-11-73 pertains to this subject.) (g) Tubes with light corrosion over less than twenty-five percent of the area in any one-half inch length of the tube may be returned to service provided the tube is assembled and protected as noted in paragraph (d) of this A.D. and the tube is removed from service prior to accumulating 200 hours time in service after the initial inspection prescribed by this A.D. was conducted. NOTE: Advisory Circular No. 43-4, page 47 defines light corrosion. Amendment 39-1801 became effective April 22, 1974. This Amendment 39-1864 becomes effective May 30, 1974.