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61-16-06: 61-16-06 PIPER: Amdt. 314 Part 507 Federal Register July 29, 1961. Applies to All PA- 24 and PA-24 "250" Aircraft Modified to Incorporate Brittain Wing Tip Fuel Tanks (Supplemental Type Certificates Nos. SA4-1235 and SA4-1351). Compliance required within the next 150 hours' time in service after the effective date or at the next disassembly of fuel selector valves, whichever occurs first. The fuel selector valve handles of aircraft equipped with Brittain wing tip fuel tanks can easily be reinstalled with incorrect indexing after the valves have been disassembled for servicing and lubrication. Incorrect indexing can cause serious fuel system malfunctioning and one accident resulting from this condition has been reported. To preclude future incorrect indexing of the fuel selector valve handles, the following must be accomplished: (a) Remove any valve shafts with four flat sides at the handle end and replace with Brittain P/N 4018-15 shafts, or equivalent. The Brittain P/N 4018-15 shaft is identical to the original except that one of the four sides at the handle end has been modified to a convex shape. (b) After reassembly and reinstallation of the selector valves, determine that the valve handles are properly indexed with respect to the selector valve placard. (Brittain Aircraft Enterprises Service Letter No. 4000-1 dated April 26, 1961, covers this same subject.) This directive effective August 31, 1961.
2017-25-17: We are superseding airworthiness directive (AD) 2011-27-08 for Agusta S.p.A. (Agusta) Model A109S and AW109SP helicopters. AD 2011-27- 08 required repetitively inspecting each elevator assembly for a crack. This new AD retains the initial inspection interval and adds a repetitive borescope inspection. This AD is prompted by the discovery of another crack on an elevator assembly since AD 2011-27-08 was issued. The actions of this AD are intended to prevent an unsafe condition on these helicopters.
2017-25-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracking in the webs of the stub beams at certain fuselage stations. These cracks are the result of fatigue caused by cyclical loading from pressurization, wing loads, and landing loads. This AD requires repetitive inspections for cracking of the webs of the stub beams at certain fuselage stations, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2005-07-21: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747-200F and -200C series airplanes, that currently requires repetitive detailed inspections or a one-time open-hole high frequency eddy current inspection to detect cracking of certain areas of the upper deck floor beams, and corrective actions if necessary. This amendment requires new one-time inspections for cracking of the web, upper chord, and strap of the upper deck floor beams. This action also requires modifying or repairing the upper deck floor beams, as applicable, which eventually necessitates accomplishment of new repetitive inspections for cracking of the upper deck floor beams. The actions specified by this AD are intended to prevent fatigue cracks in the upper chord and web of upper deck floor beams and the resultant failure of such floor beams. Failure of a floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent loss of controllability of the airplane. Failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 16, 2005. \n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 16, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 747-53A2420, dated March 26, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of May 11, 1998 (63 FR 20311, April 24, 1998).
2005-08-06: The FAA adopts a new airworthiness directive (AD) for all CENTRAIR 101 series gliders with other than elevator or aileron part number (P/N) SY991A hinge pins installed. This AD requires you to replace any installed elevator or aileron hinge pins that are not P/N SY991A hinge pins with P/N SY991A pins. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are issuing this AD to replace incorrectly heat-treated elevator or aileron hinge pins, which could result in failure of the elevator or ailerons. Such failure during takeoff, landing, or flight operations could lead to loss of glider control.
2017-25-14: We are adopting a new airworthiness directive (AD) for Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a report of an engine multiple fan blade-off (MFBO) event, caused by engine fan flutter. We are issuing this AD to address the unsafe condition on these products.
61-14-06: 61-14-06 SNOW: Amdt. 306 Part 507 Federal Register July 11, 1961. Applies to All Model S2A Aircraft (Restricted Category). Initial compliance required within 25 hours' time in service after the effective date of this AD unless accomplished within 75 hours' time in service preceding such date. Subsequent compliance required at each 100 hours' time in service after the initial compliance date. Due to reports of excessive cable wear occurring at two AN 210-3B pulleys in the aileron system aft of the hopper and two AN 210-3B pulleys in the elevator system on the left and right of the pilot seat, the following must be accomplished: (a) Detach the aileron and elevator cables by disconnecting the turnbuckles to obtain slack at the two pulleys in each system. Visually inspect the cables for fraying by flexing the cable in the areas of pulley contact in accordance with Snow Service Letter No. 4. Replace all frayed cables prior to further flight. (b) Inspection of theelevator cable may be discontinued when the two AN 210-3B elevator system pulleys to the left and right of the pilot seat are replaced with AN 210-4B pulleys, in accordance with Snow Service Letter No. 6. Inspection of the aileron cable may be discontinued when the aileron cable system is replaced with a push-pull tube system in accordance with Snow Service Letter No. 7. (Snow Service Letters 4, 6, and 7 cover this subject.) This directive effective July 21, 1961.
61-14-01: 61-14-01 AERO COMMANDER: Amdt. 303 Part 507 Federal Register July 7, 1961. Applies to All Model 500 Aircraft. Compliance required within the next 100 hours' time in service after the effective date of this directive and at each 100 hours' time in service thereafter. Visually inspect the inside of angles P/N 5620023-7, -8, -9, and -10 in the area of the row of Huck bolts, nearest the radius of the angle, that attach the angles to the upper and lower mount fittings, P/N 3620025-1 and -2. If cracks are found, prior to further flight, incorporate the reinforcement as indicated in Aero Commander Service Bulletin No. 68A, dated January 20, 1961, or equivalent. Angles incorporating Federal Aviation Agency approved reinforcement need not be reinspected in accordance with the provisions of this AD. (Aero Commander Service Bulletin No. 68A dated January 20, 1961, covers this subject.) This supersedes AD 60-26-01. This directive effective August 8, 1961.
89-06-01: 89-06-01 SWITLIK PARACHUTE COMPANY, INC.: Amendment 39-6075. Applicability: Switlik TSO-C13 Life Preservers and TSO-C72 Individual Flotation Devices: all models and all part numbers manufactured from September 1, 1984, through January 30, 1985, and June 1, 1985, through October 30, 1985 (date located on identification label on front surface). Compliance: Required within one year after the effective date of this AD, unless already accomplished. To prevent the improper functioning of the carbon dioxide (CO2) inflators on TSO-C13 Life Preservers and TSO-C72 Individual Flotation Devices, accomplish the following: (a) Visually inspect the CO2 inflators for cracks and chipping and, if necessary, replace CO2 inflators with serviceable parts in accordance with Paragraph 2, Accomplishment Instructions of Switlik Parachute Company, Inc., Service Bulletin No. 25-00-19, dated September 8, 1987. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, Engine and Propeller Directorate, Aircraft Certification Service, 181 South Franklin Avenue, Valley Stream, New York 11581. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, New York Aircraft Certification Office, Federal Aviation Administration, Engine and Propeller Directorate, Aircraft Certification Service, 181 South Franklin Avenue, Valley Stream, New York 11581, may adjust the compliance time specified in this AD. Switlik Service Bulletin No. 25-00-19, dated September 8, 1987, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Switlik Parachute Co., Inc., 1325 East State Street, P.O. Box 1328, Trenton, New Jersey 08607. This document may also 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-05. This amendment (39-6075, AD 89-06-01) becomes effective on April 3, 1989.
88-21-06: 88-21-06 ROLLS-ROYCE plc: Amendment 39-6031. Applies to Rolls-Royce plc (R-R) (Formerly Rolls- Royce Limited) Dart Mks. 506, 510, 511, 514, 525, 526, 527, 528, 529, 531, 532, and 542 series turboprop engines and all variants. Compliance is required as indicated, unless already accomplished. To prevent low cycle fatigue failure of high pressure (HP) impellers and low pressure (LP) impellers, accomplish the following: (a) Remove from service HP impellers installed in Dart Mks. 506, 510, 511, 514, and all variants, in accordance with the following schedule: (1) HP impellers to Mod 844 standard which have accumulated 8,000 or more total flights since new on the effective date of this AD, within the next 400 flights from the effective date of this AD, or within the next 12 calendar months from the effective date of this AD, whichever comes later. (2) HP impellers to Mod 1455 standard which have accumulated 8,600 or more total flights since new on the effective date of this AD, within the next 400 flights from the effective date of this AD, or within the next 12 calendar months from the effective date of this AD, whichever comes later. (3) HP impellers to Mod 844 standard which have accumulated less than 8,000 total flights since new on the effective date of this AD, at or prior to accumulating 8,400 total flights since new, or within 12 calendar months from the effective date of this AD, whichever comes later. (4) HP impellers to Mod 1455 standard which have accumulated less than 8,600 total flights since new on the effective date of this AD, at or prior to accumulating 9,000 total flights since new, or within 12 calendar months from the effective date of this AD, whichever comes later. NOTES: (1) Total flights since new is defined as the total number of flights accumulated by the part since first installation in an engine. This total includes all Mod standards the part has operated under. (2) This action establishes a new Overhaul Manual Chapter 5 life limit for HP impellers, as noted in items (a)(3) and (a)(4) above. (3) Reference R-R Service Bulletin (SB) DA72-496, dated June 1986. (b) Remove from service HP impellers installed in Dart Mks. 525, 526, 527, 528, 529, 531, 532, 542, and all variants, on or before the life limits in the following schedule: Life Limit in Number of Flights Dart Mk. Pre-Mod 797 Mod 797 Open Bore Processed Mod 797 Pre-Mod 1455 Mod 1455 Mod 1475 525 thru 529 4,500 11,000 14,000 NC NC 531 and 532 4,500 11,000 14,000 NC NC 542 NA NA 12,000 16,000 14,500 (Since incorp. of Mod 1455) NA - Model not applicable to specific impeller. NC - Life limits not covered by this AD. Information relating to these impellers is contained in the manufacturer's appropriate overhaul manual. NOTE: The above noted HP impeller life limits were published in AD 73-21-04, Amendment 39-1734 (38 FR 27819), and have notchanged. This section is only intended to reprint for clarity, already existing AD requirements with respect to current R-R SB information. (c) Remove from service LP impellers installed in Dart Mks. 506, 510, 511, 514, 525, 526, 527, 528, 529, 531, 532, 542, and all variants, on or before the life limits in the following schedule: Limit in Number of Flights Dart Mk. Mod 797 Open Bore Processed Mod 797 Pre-Mod 1455 Mod 1455 506 10,500 11,250 11,250 510 10,500 11,250 11,250 511 10,500 11,250 11,250 514 10,500 11,250 11,250 525 thru 529 9,000 9,000 9,000 531 and 532 9,000 9,000 9,000 542 NA 9,000 9,000 NA - Model not applicable to specific impeller. NOTES: (1) LP impellers to Mod 1455 Part 1 standard (manufactured by R-R to this standard) are not affected by this AD. Life limits for this part are quoted in the overhaul manual, Chapter 5, "Time Limits". (2) The above noted LP impeller life limits were published in AD 73-21-04, Amendment 39-1734 (38 FR 27819), and have not changed. This AD, with respect to LP impeller life limits, is only intended to reprint for clarity, already existing AD requirements with respect to current R-R SB information. (3) Rolls-Royce Dart SB 72-463 also pertains to LP impeller life limits. (d) Aircraft may be ferried in accordance with provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this 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. (f) 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 schedules specified in this AD. This amendment supersedes Amendment 39-1734 (38 FR 27819), AD 73-21-04. This amendment, 39-6031, becomes effective on November 6, 1988.
2017-25-02: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 1000, 2000, 3000, and 4000 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports indicating that certain exit signs have a hydrogen isotope that decays over time, causing the signs to lose their brightness. We are issuing this AD to address the unsafe condition on these products.
89-09-04: 89-09-04 SAAB-SCANIA: Amendment 39-6194. Applicability: Model SF-340A series airplanes, serial numbers -003 through -138, inclusive, certificated in any category. Compliance: Required as indicated below, unless previously accomplished. To prevent reduced structural capability of the fuselage, accomplish the following: A. Within 30 days after the effective date of this AD, perform an inspection of the insulation in the Environmental Control System (ECS) compartment and secure the Gamah Couplings with a locking wire, in accordance with SAAB-Scania Service Bulletin SF340-21-022, dated October 31, 1988. B. If the inspection required by paragraph A., above, reveals leakage of hot air, prior to further flight, inspect for delamination of the stringer to skin bonding, and repair, if necessary, in accordance with SAAB-Scania Service Bulletin SF340-53-025, dated October 31, 1988. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manger, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to SAAB-Scania AB, S-581 88, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6194, AD 89-09-04) becomes effective on May 16, 1989.
87-06-04: 87-06-04 AEROSPATIALE: Amendment 39-5569. Applies to Model ATR-42 series airplanes listed in Aerospatiale Service Bulletin ATR 42-25-0006, dated July 21, 1986, fitted with IPECO flight crew seats, certificated in any category. Compliance is required within 30 days after the effective date of this AD, unless already accomplished. To prevent collapse of the pilot or co-pilot seat backs, accomplish the following: A. Modify seats, P/N 3A063-0035, 3A063-0036, 3A063-0079, and 3A063-0080, in accordance with Aerospatiale Service Bulletin ATR 42-25-0006, dated July 21, 1986, or Revision 1, dated September 3, 1986 (Reference IPECO Service Bulletin A001-25-22, dated June 5, 1986). 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 the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. 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 becomes effective April 2, 1987.
88-07-52: 88-07-52 AEROSPATIALE: Amendment 39-5925. Applies to Model ATR-42-200 and -300 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent erroneous fuel quantity readings in the fuel indication system, accomplish the following: A. Within 7 days after the effective date of this AD, modify the cable in the fuel indicator panel, as follows: 1. Remove fuel quantity indicator 3 quart on the 4 VU panel (Ref: Airplane Maintenance Manual (AMM) 28-42-81-RAI 10000). 2. Disconnect cable 2842-0007 from plug 3 Qta pin R. 3. Insulate the cable from circuitry by means of heat shrinkable sleeve. 4. Attach cable to harness by suitable tie wrap. 5. Reinstall 3 Qta plug and 3 quart indicator (Ref: AMM 28-42-81-RAI 10000). 6. Perform a test of the fuel quantity indicator by pushing the test switch. Ensure that all digits indicate "eight," and that the "low level" lights illuminate. B.Accomplishment of the modification of the cable in the fuel indicator panel and functional test in accordance with Aerospatiale Service Bulletin ATR42-28-0011, dated April 6, 1988, is considered an acceptable means of compliance with this AD. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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 AD was effective earlier to all recipients of telegraphic AD T88-07-52, issued March 31, 1988. This Amendment 39-5925 becomes effective June 4, 1988.
61-12-02: 61-12-02 DOUGLAS: Amdt. 294 Part 507 Federal Register June 7, 1961. Applies to All Model DC-8 Aircraft powered with P&WA JT3C-6 and JT4A Series Engines. \n\n\tCompliance required as indicated. \n\n\tAn instance has been reported wherein a takeoff was attempted with elevator gust lock engaged. It was found that the throttle interlock did not provide adequate restriction to limit engine thrust under the prevailing temperature condition. Unless already accomplished, the following modification or FAA approved equivalent, must be accomplished within the next 500 hours' time in service. \n\n\tModify the throttle interlock system to provide further restriction of the throttles when elevator gust lock is engaged by installing the following parts or equivalent: \n\n\tPushrod - Gust Lock Interlock Pedestal, P/N 3771190. \n\n\tAdapter - Gust Lock Crank, P/N 4771191. \n\n\tArm, Gust Lock Interlock Pedestal, P/N 2772271-1 or -501. \n\n\tPer Douglas Drawing No. 5640901 Changes "CI" and "CK" - "Pedestal Assembly - Accessory Controls". \n\n\t(Douglas Service Bulletin No. A27-99, reissue No. 1, revision No. 2 dated July 19, 1961, also covers this same subject.) \n\n\tThis directive effective June 7, 1961. \n\n\tRevised August 26, 1961.
87-08-04: 87-08-04 BOEING: Amendment 39-5593. Applies to Model 757 series airplanes equipped with Rolls Royce RB211-535E4 engines, as listed in Boeing Service Bulletin 757-78-0010, dated December 23, 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo maintain the fire integrity of the thrust reverser C-ducts, accomplish the following within the next 250 flight hours after the effective date of this AD: \n\n\tA.\tInspect and repair, if necessary, the thermal blanket in the upper 45 degree section of the C-ducts, as described in Boeing Service Bulletin 757-78-0010, dated December 23, 1986, or later FAA-approved revision. Any damage to the thermal blanket (such as holes, splits, and tears) must be repaired prior to further flight. \n\n\tB.\tInspect and repair, if necessary, the thermal blanket in the lower section of the C- ducts and engine components, as described in the Boeing Service Bulletin 757-78-0010, dated December 23, 1986, or later FAA-approved revisions. Any damage discovered must be repaired within the next 250 flight hours. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial 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 repair required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124-2207. This information 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. \n\n\tThis amendment becomes effective April 16, 1987.
2017-24-07: We are superseding Airworthiness Directive (AD) 2014-08-01, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-08-01 required an inspection for part numbers of the interconnecting struts and, for affected interconnecting struts, identification of the part and serial numbers of the associated target and proximity sensors and replacement or re-identification of the flap interconnecting strut if necessary. This AD continues to require an inspection to verify the interconnecting strut part number. This AD also provides a new compliance time and an additional inspection for previously inspected airplanes. This AD was prompted by an investigation that showed that when a certain combination of target/ proximity sensor serial numbers is installed on a flap interconnecting strut, a ``target FAR'' signal cannot be detected when reaching the mechanical end stop of the interconnecting strut. We are issuing this AD to address the unsafe condition on these products.
82-18-02: 82-18-02 BRITISH AEROSPACE, AIRCRAFT GROUP (formerly British Aircraft Corporation): Amendment 39-4443. Applies to Model BAC 1-11 series 400 airplanes certificated in all categories. Compliance required as indicated unless already accomplished. To prevent overloads and possible failure of the spoiler operating rods caused by corroded turnbarrels, accomplish the following: 1. Within the next 1200 landings or 6 months after the effective date of this AD, whichever occurs first, and thereafter at intervals not exceeding 10,000 landings or 5 years from the last inspection, inspect the internal threads of the spoiler operating rod turnbarrels for corrosion and excessive thread truncation and replace the turnbarrel, if necessary, in accordance with paragraph 2, Accomplishment Instructions, of British Aerospace, Aircraft Group, BAC 1-11 Alert Service Bulletin 27-A-PM5732, Issue No. 2, dated November 13, 1980. 2. Alternate means of compliance which provide an equivalent level ofsafety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 3. 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. 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). This amendment becomes effective September 27, 1982.
61-11-05: 61-11-05 DOUGLAS: Amdt. 291 Part 507 Federal Register May 30, 1961. Applies to All Models A-26 (B-26) Series Aircraft. Compliance required as indicated. As a result of several reported cases of severe corrosion of the wing structure in the area beneath the wing fuel tanks, the following must be accomplished at the next periodic inspection and every periodic inspection thereafter, until (b) is accomplished: (a) Remove the center wing fuel tanks and inspect the internal wing structure for corrosion. If corrosion is found, FAA approved repairs and/or replacement of affected parts must be made prior to further flight. Also, inspect the sponge rubber mats under the fuel cells, and if found deteriorated they must be replaced prior to next flight. (b) When the sponge rubber mats have been replaced with closed cell neoprene sponge mats, or equivalent, and any corrosion damage present is repaired, the special inspection of (a) is no longer required. This directive effective June 29, 1961.
89-20-08: 89-20-08 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6333. (Docket No. 89-NM-69-AD) Applicability: Model DHC-8-100 series airplanes, Serial Numbers 3 through 106 inclusive, equipped with wardrobe assembly 82520145, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the wardrobe door from becoming unlatched and allowing the shifting of the contents into the path of the flight crew door, thereby hindering emergency evacuation, accomplish the following: A. Within 15 days after the effective date of this AD, install a placard on the wardrobe door, stating the following: "THIS WARDROBE IS RESTRICTED FOR USE AS A COAT/GARMENT RACK." B. Within 60 days after the effective date of this AD, modify the wardrobe door latch and strikers, in accordance with Boeing of Canada, Ltd, de Havilland Division, Service Bulletin No. 8-25-35, Revision "B," dated January 27, 1989. Once this modificationis accomplished, the placard required by paragraph A., above, may be removed. C. An alternate means of compliance which provides an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, New York Aircraft Certification Office, ANE-170. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garrett Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6333, AD 89-20-08) becomes effective on October 30, 1989.
2017-24-02: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 D-2 helicopters. This AD requires amending the rotorcraft flight manual to establish a minimum airspeed limitation for the autopilot cruise height mode. This AD is prompted by two reports of uncommanded helicopter climbs and descents. The actions of this AD are intended to address an unsafe condition on these products.
86-24-01: 86-24-01 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5468. Applies to Model 206A, 206B, and 206L helicopters certificated in any category equipped with T/R yoke Part Number (P/N) 206-011-819-101 in combination with T/R crosshead P/N 206-010-741-001 or -003. Compliance is required as indicated unless already accomplished. To prevent failure of the T/R pitch links, accomplish the following: (a) Within the next 25 hours' time in service, inspect T/R assembly and determine if T/R yoke P/N 206-011-819-101 is installed in combination with T/R crosshead P/N 206-010-741- 001 or -003. If this T/R yoke and crosshead combination is installed, either: (1) Remove T/R yoke P/N 206-011-819-101 and replace it with T/R yoke P/N 206-011-811-009; or (2) Remove T/R crosshead P/N 206-010-741-001 or -003 and replace it with T/R crosshead P/N 206-011-855-001 or 206-011-857-001. (b) Alternative inspections, modification, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Helicopter Certification Branch, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101. This amendment becomes effective December 15, 1986.
2005-07-01: The FAA is adopting a new airworthiness directive (AD) for all The Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to incorporate information into the applicable section of the Airplane Flight Manual (AFM). This AD results from several accidents/incidents of problems with the affected airplanes during operations in icing conditions, including six accidents in the previous two icing seasons and nine events in the past few months. We are issuing this AD to assure that the pilot has enough information to prevent loss of control of the airplane while in-flight during icing conditions.
88-18-02: 88-18-02 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 5999. Applies to all Model DHC-8-100 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent ingestion of flammable fluids into the engine starter-generator, which could cause a fire in the nacelle, accomplish the following: A. Within five calendar days after the effective date of this AD, and thereafter every time the brush access cover band has been loosened or whenever a starter-generator is replaced, position, secure, and re-safetywire the brush access cover band on each engine starter-generator, in accordance with Lucas Aerospace Service Information Letter No. 23088-00X-03, dated June 20, 1988. B. Within 150 flight hours after the effective date of this AD, seal the openings around the terminal post conductor bars where they enter the generator case by either using a Lucas Aerospace Power Equipment Corporation (Lucas Aerospace) grommet, Part Number 23088-1290; or applying a fillet of Dow Corning RTB-738 sealing compound and MIL-P-46112B Kapton sheet, in accordance with Lucas Aerospace Service Information Letter No. 23088-00X-04, Revision 1, dated July 28, 1988. NOTE: Care should be exercised to ensure excess sealant is not allowed to enter the interior of the starter-generator. Also, verify that sealed joint has cured in accordance with manufacturer's instructions prior to operation of the engine. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, New York Aircraft Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 and21.199 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 information from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment, 39-5999, becomes effective September 2, 1988.
61-11-04: 61-11-04 de HAVILLAND: Amdt. 290, Part 507, Federal Register May 20, 1961. Applies to de Havilland Series Airplanes Prior to Serial No. 04503. Compliance required as indicated. Due to reports of severe corrosion at the mainplane lower spar booms, the following inspections are required except that any inspection accomplished in accordance with AD 57-01- 01 may be utilized in establishing the less frequent inspection intervals permitted in this directive. (a) Inspections shall be performed on the upper and lower spar booms from rib No. 1 to the wing tip as follows: (1) Tank Bay Area, Ribs 1 to 5. Inspection required every six months, the first of such inspections to be made six months after the effective date of this directive or six months after the last inspection with a 10-power glass, whichever date is earlier. If no signs of corrosion are found after two successive inspections, inspect every twelve months thereafter. (2) Wheel Well Area Ribs 5 to 7. Inspection required every month, the first such inspection to be made one month after the effective date of this directive or one month after the last inspection with a 10-power glass, whichever date is earlier. If no signs of corrosion are found after six successive monthly inspections, inspect every six months thereafter. "This inspection may be discontinued if no signs of corrosion are found after six months and surface protection is provided in accordance with de Havilland Dove Modification 852, or an FAA- approved equivalent." (3) Rib 7 to Wing Tips. Visual inspection required every six months, the first such inspection to be made six months after the effective date of the directive or six months after the last inspection, whichever date is earlier. If no corrosion is found after a six-month period, inspect every twelve months thereafter. (b) Any corrosion that is found must be thoroughly cleaned out prior to further flight. If the depth and width of the pocketare within the limits specified by the Hawker Siddeley Dove Maintenance and Repair Manual, Section 2, Chapter 6, Appendix A1, or an FAA-approved equivalent, the surfaces must be reprotected. If after cleaning out the corrosion pockets the limits specified by the Hawker Siddeley Dove Maintenance and Repair Manual, Section 2, Chapter 6, Appendix A1, or an FAA-approved equivalent are exceeded, the spar boom must be replaced prior to further flight. Hawker Siddeley Technical News Sheet CT (104) No. 125, Issue 6, dated June 26, 1967, and Hawker Siddeley Dove Maintenance and Repair Manual, Section 2, Chapter 6, Appendix A1, cover this subject. This supersedes AD 57-01-01. This directive effective May 20, 1961. Revised October 13, 1961. Revised December 1, 1967.