Results
2022-25-06: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-402 airplanes. This AD was prompted by an investigation that found that the actual operating temperatures within the integrated flight cabinet (IFC) were significantly higher than anticipated during certification. This AD requires a modification to improve the IFC cooling capacity. The FAA is issuing this AD to address the unsafe condition on these products.
2016-20-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, and -400ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the skin lap splice is subject to widespread fatigue damage (WFD). This AD requires repetitive external detailed and surface high frequency eddy current (HFEC) inspections of the outer skin for cracking around fastener heads common to the inboard fastener row of the skin lap splice and corrective action. We are issuing this AD to detect and correct fatigue cracking of the skin lap splice, which could grow and result in possible rapid decompression and reduced structural integrity of the airplane.
2001-13-17: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A300 B2 and A300 B4; A300 B4-600, B4-600R, and F4-600R (collectively called A300-600); and A310 series airplanes. This action requires revising the Airplane Flight Manual to advise the flight crew of appropriate procedures to follow in the event of lost or erroneous airspeed indications. This action is necessary to prevent inadvertent excursions outside the normal flight envelope. This action is intended to address the identified unsafe condition.
91-05-07: 91-05-07 PILATUS BRITTEN-NORMAN (PBN): Amendment 39-6891. Docket No. 90-CE-32-AD. Applicability: Model BN-2T Turbine Islander airplanes (all serial numbers), certificated in any category, that do not have PBN Modification Number NB/M/1415 incorporated. Compliance: Required within the next 200 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To ensure the ability to restart the engines in flight if an undetected circuit breaker trip does occur, accomplish the following: (a) Modify the airplane electrical system in accordance with the instructions in PBN Service Bulletin BN2/SB 194, dated April 11, 1990. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved bythe Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (d) All persons affected by this directive may obtain copies of the document referred to herein upon request to Pilatus Britten-Norman Limited, Bembridge Airport, Isle of Wight, PO36 5PR, England; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6891, AD 91-05-07) becomes effective on March 25, 1991.
2016-20-08: We are superseding Airworthiness Directive (AD) 95-21-09 for all Airbus Model A300 series airplanes, and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 95- 21-09 required repetitive inspections for cracking of the No. 2 flap beams, and replacement of the flap beams, if necessary; and provided optional modifications for extending certain inspection thresholds, and an optional terminating modification for certain inspections. This new AD requires reduced compliance times for inspections and also reduces the number of airplanes affected. This AD was prompted by a determination that the compliance times must be reduced. We are issuing this AD to detect and correct cracking of the No. 2 flap beams, which could result in rupture of the flap beams and reduced structural integrity of the airplane.
2016-21-04: We are adopting a new airworthiness directive (AD) for certain Continental Motors, Inc. (CMI) TSIO-550-K, TSIOF-550-K, TSIO-550-C, TSIOF-550-D, and TSIO-550-N reciprocating engines. This AD was [[Page 70930]] prompted by a report of an uncommanded in-flight shutdown (IFSD) resulting in injuries and significant airplane damage. This AD requires replacing the oil cooler cross fitting assembly. We are issuing this AD to prevent failure of the oil cooler cross fitting and engine, IFSD, and loss of the airplane.
2001-13-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes. This AD requires repetitive inspections to detect cracks and corrosion around the lower bearing of the actuator attach fittings of the inboard and outboard flaps. This AD also requires repetitive overhauls for certain actuator attach fittings or repetitive replacement of the fittings with new fittings, as applicable, which terminates the repetitive inspections. This AD also provides for replacement of actuator attach fittings with improved fittings, which terminates all requirements of this AD. This amendment is prompted by reports of cracks on the lower bearing journal of the inboard actuator attach fittings of the outboard trailing edge flaps due to stress corrosion. The actions specified by this AD are intended to detect and correct cracking on the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and consequent reduced controllability of the airplane.
86-08-04 R1: 86-08-04 R1 PRATT & WHITNEY: Amendment 39-5287 as amended by Amendment 39-5424. Applies to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines. Compliance is required as indicated unless already accomplished. To prevent crack propagation and subsequent high pressure compressor (HPC) removable sleeve spacer rupture, perform a one time, eddy current inspection of HPC removable sleeve spacers stages 7-8, 8-9, and 9-10 for cracks, and replace all stages of HPC removable sleeve spacers with the respective HPC integral sleeve spacers, in accordance with the procedures of PW Alert Service Bulletin (ASB) 5649, dated January 15, 1986, or FAA approved equivalent, per the following schedule: (a) For HPC removable sleeve spacers stages 7-8, 8-9, and 9-10: (1) Inspect spacers within the next 1,000 cycles in service from the effective date of this AD, or prior to reaching 1,700 cycles since the last in-shop fluorescent penetrant or ultrasonic inspection, whichever occurs later. (2) Remove cracked spacers from service prior to further flight. (3) Report the following information in writing for each inspection within 30 days of the inspection to the Manager, Engine Certification Office, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, (telex No. 949301 FAANE BURL) (reporting approved by the Office of Management and Budget (OMB) under OMB Number 2120-1156). (i) Engine serial number (ii) Inspection date (iii) Spacer part number and serial number (iv) Spacer total time and cycles (v) Spacer time and cycles since last inspection (vi) Spacer disposition (crack indication, no crack indication) (vii) If a crack indication is present, report confirmation of location and crack size within 30 days after engine disassembly. (b) Replace HPC removable sleeve spacers stages 7-8, 8-9, and 9-10 with the integral sleeve spacers at the next HPC rotor disassembly, but not to exceed 2 calendar years or 4,000 cycles in service, whichever occurs later from the effective date of this AD. (c) Replace HPC removable sleeve spacers stages 10-11, 11-12, and 12-13 with the integral sleeve spacers at the next HPC rotor disassembly. NOTES: (1) For the purposes of this AD, HPC rotor disassembly is defined as removal of any disk, spacer, or hub from the HPC rotor. (2) For the purposes of this AD, the last in-shop fluorescent penetrant or ultrasonic inspection is that conducted in accordance with the procedures identified and described in the PW JT8D restructured Engine Manual Part Number 481672 or FAA approved equivalent. Aircraft may be ferried in accordance with the provisions of FAR Parts 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. PW ASB 5649, dated January 15, 1986, identified and described in this directive, 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 a copy upon request to Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. This document also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-46, Room Number 311, between the hours of 8:00 a.m. and4:30 p.m., Monday through Friday except Federal holidays. The provisions of this amendment applicable to the stage 8-9 spacer become effective on the effective date of this amendment. The remaining provisions of this amendment applicable to stages 7-8 and 9-10 spacers are effective on May 27, 1986. This amendment amends Amendment 39-5287 (51 FR 12690), AD 86-08-04. This amendment becomes effective on November 4, 1986.
47-31-01: 47-31-01 NAVION: (Was Mandatory Note 10 of AD-782-3.) Applies to All Serials Up to and Including Number NAV-4-947. To be accomplished not later than October 1, 1947. To reduce the possibility of nose gear hydraulic actuating cylinder line failures due to inflexibility, the cylinders must be removed and reinstalled with the lines therefrom leading aft. Each of the present lines must be replaced with a longer line incorporating a "U" bend. (North American Field Service Bulletin No. 28 covers this same subject.)
2016-19-17: We are superseding Airworthiness Directive (AD) 2010-23-19 for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, and 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. AD 2010-23-19 required repetitive inspections for damage of the main landing gear (MLG) inboard doors and fairing, and corrective actions if necessary. This new AD requires repetitive inspections for damage of the MLG inboard doors, MLG fairing, and adjacent structures of the MLG inboard doors, and corrective actions if necessary; replacement of the MLG fairing seal; and a terminating action involving increasing the clearances between the MLG fairing and MLG door. This new AD also adds one airplane and removes others from the applicability. This AD was prompted by reports of the MLG failing to fully extend. We are issuing this AD to prevent loss of controllability of the airplane during landing.
2001-13-03: This amendment adopts a new airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters that requires reducing the life limit of the rotor shaft and teeter pin assembly and establishing a life limit for the flap clevis. This amendment is prompted by the discovery of cracks in parts that were returned to the manufacturer. The actions specified by this AD are intended to prevent failure of the rotor shaft, teeter pin assembly, or flap clevis due to fatigue cracks, and subsequent loss of control of the helicopter.
2016-19-09: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with high-pressure compressor (HPC) stage 8-10 spool, part numbers (P/Ns) 1694M80G04, 1844M90G01, or [[Page 67099]] 1844M90G02, installed. This AD was prompted by reports of cracks found on the seal teeth of the HPC stage 8-10 spool. This AD requires eddy current inspections (ECIs) or fluorescent penetrant inspections (FPIs) of the HPC stage 8-10 spool seal teeth and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.
2001-13-09: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-2C, B4-103, and B4-203 series airplanes, that requires a one-time inspection of the space between the fuel quantity indication (FQI) probes and any adjacent structures for minimum clearance, and corrective action, if necessary. The actions specified by this AD are intended to prevent the possibility of electrical arcing to the fuel tank if the airplane should be struck by lightning. This action is intended to address the identified unsafe condition.
90-26-07: 90-26-07 BRITISH AEROSPACE: Amendment 39-6834. Docket No. 90-NM-172-AD. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the glazing frame and possible rapid decompression of the airplane, accomplish the following: A. For airplanes operating at a maximum cabin differential pressure of 7.5 pounds per square inch (psi): Prior to the accumulation of 20,000 landings on the glazing frame since new, or within 1,600 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,600 landings, perform an internal and external visual inspection, or non-destructive testing (NDT) inspection, of the pilot's and co-pilot's direct view (DV) window aperture (flight deck side glazing frame at Pillars B and C), in accordance with the Accomplishment Instructions of BritishAerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March 21, 1990. B. For airplanes modified for operation above 7.5 psi to a maximum of 8.2 psi cabin differential pressure: Prior to the accumulation of 14,000 landings on the glazing frame since new, or within 1,100 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,100 landings, perform an internal and external visual inspection, or non-destructive testing (NDT) inspection, of the pilot's and co-pilot's DV window aperture (flight deck side glazing frame at Pillars B and C), in accordance with the Accomplishment Instructions of British Aerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March 21, 1990. C. If cracks are found during the inspections required by paragraph A. and B. of this AD, prior to further flight, perform an eddy current inspection, in accordance with British Aerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March21, 1990; and 1. For cracks equal to or less than 0.2 inch, damage may be blended out in accordance with Table 1 or Table 2 of the service bulletin, as appropriate. 2. All other cracks must be repaired in accordance with the Structural Repair Manual, as specified in Table 1 and Table 2 of the service bulletin, as appropriate; or repaired in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or the glazing frame must be replaced with a serviceable part. 3. If blending has been previously accomplished, all cracks must be repaired in accordance with the BAC 1-11 Structural Repair Manual, as specified in Table 1 or Table 2 of the service bulletin, as appropriate; or repaired in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. 4. Following repair or replacement, the inspections specified in paragraphs A. and B. of this AD are still required. D. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. E. 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, Dulles International Airport, P.O. Box 17414, 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 (39-6834, AD 90-26-07) becomes effective on January 16, 1991.
93-23-04: 93-23-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE AND EUROCOPTER FRANCE: Amendment 39-8738. Docket Number 93-SW-02-AD. Applicability: Model SE 3160, SA 315B, SA 316B, SA 316C, and SA 319B series helicopters equipped with main rotor blades, part number (P/N) LOM3160-100 installed in accordance with Supplemental Type Certificate (STC) No. SH778GL, certificated in any category. Compliance: Required within 25 hours' time-in-service after the effective date of this airworthiness directive (AD), unless accomplished previously. To prevent excessive main rotor vibrations that could result in failure of rotor system components, and subsequent loss of control of the helicopter, accomplish the following: (a) Install an outside air temperature (OAT) and velocity never exceed (VNE) airspeed limitation flip chart placard, P/N LOM3160-151, on top of the instrument panel immediately to the right of the existing VNE placard, using velcro strips as described in Les "Blades"De L'Helicoptere, Ltd. Service Information Letter No. 1-11-92A, dated December 3, 1992. (b) After compliance with paragraph (a) of this AD, operate the helicopter in accordance with the Helicopter Flight Manual Supplement, approved and dated November 25, 1992, that is applicable to helicopters modified in accordance with STC SH778GL. (c) An alternate 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, FAA, Transport Airplane Directorate, 3229 East Spring Street, Long Beach, California 90806-2425. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Los Angeles Aircraft Certification Office. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished, provided the indicated airspeed is limited to no more than 50 knots. (e) The installation shall be done in accordance with Les "Blades" de l'Helicoptere, Ltd. Service Information Letter No. 1-11-92A, dated December 3, 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 Les "Blades" de l'Helicoptere, Ltd., 5132 Greencrest Road, La Canada Flintridge, California 91011. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg. 3B, room 158, Fort Worth, Texas 76106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective February 17, 1994.
2025-13-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model H160-B helicopters. This AD was prompted by occurrences of premature in-service degradation of the main rotor swashplate assembly (swashplate) bearing. This AD requires repetitively inspecting the swashplate bearing for the presence of grease, and depending on the inspection results, performing corrective actions. This AD requires performing certain operational checks, downloading and analyzing certain data, and, depending on the results of the operational checks, further corrective actions. This AD also requires repetitively performing one flight under specific conditions. Additionally, this AD requires inspecting grease on the swashplate bearing and, depending on the inspection results, applying a certain grease or replacing the grease. This AD allows installing certain part- numbered swashplate bearings provided certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.
77-15-07: 77-15-07 BRITISH AIRCRAFT CORPORATION: Amendment 39-2980. Applies to Viscount Model 744, 745D, and 810 airplanes with aileron control rods, P/N 60903, sheets 185 and 187 and P/N 70103, sheets 329, 445, 447, 449, 451, 453, 455, 457, and 459, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect corrosion of the aileron control rods and prevent possible aileron failure, accomplish the following: (a) Within the next 30 days after the effective date of this AD or 18 months from the date of the last overhaul of the specified aileron control rods, whichever occurs later, and thereafter at intervals not to exceed 6 months from the last inspection, inspect the aileron control rods for corrosion in accordance with paragraph 2.2 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and NO. 174 for 810 series airplanes, or an FAA-approved equivalent. (b) If, during an inspection required by paragraph (a) of this AD, corrosion is found, before further flight, replace the corroded parts with new parts of the same part number. (c) If, during an inspection required by paragraph (a) of this AD, no corrosion is found, rework the aileron control rods in accordance with paragraph 2.2.1 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and No. 174 for 810 series airplanes, or an FAA-approved equivalent. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued upon compliance with paragraph (e) of this AD. (e) Within the next 2 years after the effective date of this AD or at the next aileron control rod overhaul, whichever occurs sooner, remove the affected aileron control rods, disassemble the external sleeves where fitted, and conducta radiographic inspection of the aileron control rod tubes and a visual inspection of the external sleeves in accordance with paragraph 2.4 "Accomplishment Instructions" and paragraph entitled "Radiographic Technique" of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and NO. 174 for 810 series airplanes, or an FAA-approved equivalent. (f) If, during the inspection required by paragraph (e) of this AD, corrosion is found, before further flight, replace the corroded parts with new parts of the same part number. (g) If, during the inspection required by paragraph (e) of this AD, no corrosion is found, rework the aileron control rods in accordance with paragraph 2.4 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and No. 174 for 810 series airplanes, or an FAA-approved equivalent.This amendment becomes effective August 22, 1977.
2016-20-01: We are adopting a new airworthiness directive (AD) for Bell Model 427 and Model 429 helicopters. This AD requires replacing certain engine and transmission oil check valves. This AD also prohibits installing the affected check valves on any helicopter. This AD is prompted by a report of several cracked or leaking check valves. These actions are intended to detect and prevent a cracked or leaking check valve which could result in loss of lubrication to the engine or transmission, failure of the engine or transmission, and subsequent loss of control of the helicopter.
2001-12-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-12-51 that was sent previously to all known U.S. owners and operators of all Boeing Model 737-800 series airplanes by individual notices. This AD requires revising the Airplane Flight Manual (AFM) to prohibit operating the airplane at speeds in excess of 300 knots indicated airspeed (KIAS) with speedbrakes extended. This AD also provides for optional terminating action for the AFM revision. This action is prompted by a report indicating that severe vibration of the horizontal stabilizer occurred on a Boeing Model 737-800 series airplane. The actions specified by this AD are intended to prevent severe vibration of the elevator and elevator tab assembly following deployment of the speedbrakes, which, if not corrected, could result in severe damage to the horizontal stabilizer, followed by loss of controllability of the airplane.
90-13-01 R1: 90-13-01 R1 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8034. Docket No. 90-ASW-35. Final rule of priority letter AD. Applicability: Model 206B, 206L, 206L-1, and 206L-3 helicopters, all serial numbers, certificated in any category. Compliance: Required before further flight, unless already accomplished. To prevent failure of a tail rotor blade assembly, which could result in loss of control of the tail rotor, accomplish the following: (a) Determine the part number and serial number of the tail rotor blade assembly installed on the helicopter. (b) If the tail rotor blade assembly installed is P/N 206-016-201-113 or P/N 206- 016-201-127 and is identified with any serial number listed below, remove and replace the blade assembly with an airworthy part before further flight: T-41361 T-41627 T-41725 T-41737 T-42088 T-42127 T-42157 T-42307 T-42311 T-42316 T-42494 T-42496 T-42497 T-42502 T-42523 T-42534 T-43276 T-44089 T-44120 T-44157 T-44174 Serial Numbers: T-44222 T-44300 T-44638 (c) If one of the tail rotor blade assemblies listed in paragraph (b) is found, report the helicopter registration, serial number, and tail rotor blade assembly serial number to the Manager, Rotorcraft Certification Office, ASW-170, Federal Aviation Administration, Fort Worth, Texas, 76193-0170, telephone (817) 624-5170, within 10 days of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056.) (d) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the tail rotor blade assembly replacement may be accomplished. NOTE: Any unairworthy blade assemblies found as a result of (b) of this AD should be permanently marked as unairworthy. (e) Record compliance with paragraph (b) of this AD in the AD compliance record and in the maintenance record of the helicopter log book. This record must include the serial numbers of any deficient blade assembly found during compliance with this AD. (f) An alternate method of compliance which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. This amendment (39-8034, AD 90-13-01 R1) becomes effective on October 17, 1991, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD's 90-13-01 and 90-13-01 R1, issued June 14 and June 22, 1990, which contained this amendment.
2016-19-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by a malfunctioning No. 2 engine intake heater with corrosion on the thermostats and the fuselage skin where the thermostats made contact with the aircraft fuselage skin. This AD requires a general visual inspection for corrosion of the thermostats' mounting surfaces and fuselage skin surface, corrective actions if necessary, and relocating the existing thermostats. We are issuing this AD to prevent corrosion within the thermostats that might cause the switch mechanism to seize in the open position and prevent the activation of the associated engine air intake heater. An inactive engine air intake heater could lead to an engine failure.
78-26-01: 78-26-01 DETROIT DIESEL ALLISON: Amendment 39-3373. Applies to Model 250-C28B engines installed in but not limited to Bell Model 206L-1 rotorcraft certificated in all categories. Compliance required as indicated, unless previously accomplished. To preclude possible engine power loss resulting from electromagnetic interference, accomplish the following: (A) Before further flight accomplish the following unless the engine electrical system has been previously modified in accordance with Detroit Diesel Allison Commercial Engine Bulletin 73-2003. (1) Pull the N2 overspeed circuit breaker and secure by wrapping with tape or placing a Ty-Wrap around the breaker stem. (2) Install placard which states "Eng Ovsp Circuit Deactivated" in 1/4" or larger letters adjacent to N2 overspeed circuit breaker. Note: The engine overspeed test outlined in Section 2 of the RFM will no longer function with the circuit breaker deactivated. (B) Not later than February 1, 1979 modify the engine electrical system in accordance with Detroit Diesel Allison Commercial Engine Bulletin 73-2003 unless previously accomplished. Concurrent with the accomplishment of CEB 73-2003 reactivate the N2 overspeed control by engaging the N2 overspeed circuit breaker and removing the placard "Eng Ovsp Circuit Deactivated," and remove the No. 4 plug from the outlet vent of the N2 overspeed solenoid valve if installed in accordance with Detroit Diesel Allison Commercial Service Letter 2008. The Detroit Diesel Allison Commercial Engine Bulletin identified in this directive is incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). The Detroit Diesel Allison Commercial Engine Bulletin incorporated herein may be obtained upon request to Detroit Diesel Allison, Division of General Motors Corporation, P.O. Box 894, Indianapolis, Indiana 46206. This document may also be examined at the FAA Great Lakes Region, 2300 East Devon Avenue, Des Plaines, Illinois 60018 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and the Great Lakes Region. (Detroit Diesel Allison Commercial Service Letter 250-C28B CSL-2008 also pertains to this subject.) This amendment becomes effective upon publication in the Federal Register, as to all persons except those persons to whom it was made immediately effective by the air mail letter dated November 3, 1978, which contained this amendment.
77-21-05: 77-21-05 ROLLS ROYCE AERO, LTD: Amendment 39-3055. Applies to Dart Engines Series 527, 528, 529, 531, 532, 533, 534, 535, 536, 550, 542-4, 542-10, and 543-10 that have modification 1425 incorporated and are installed on, but not necessarily limited to, Nihon YS-11, Convair 600 and 640, Handley Page Herald, Fokker F27, Fairchild F27, Grumman Gulfstream I, and Hawker Siddeley 748 series. Compliance is required as indicated. To prevent overheating and failure of high pressure turbine discs, accomplish the following: (a) Within the next 500 hours engine time in service after the effective date of this AD and thereafter at intervals not to exceed 1500 hours engine time in service, inspect the flame tube bridge pieces for cracking of the support legs in accordance with the instructions contained in paragraph 4.C of Rolls Royce Dart Service Bulletin Da 72-420, dated October 1975 (hereinafter referred to as the Bulletin), or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region, FAA, c/o American Embassy, APO New York, NY 09667 (hereinafter referred to as FAA-approved equivalent). (b) If, during an inspection required by this AD, flame tube bridge piece cracking is detected, replace the affected part with a serviceable part before further flight (except that the aircraft may be flown in accordance with FAR 21.197 and 21.199 to a base where the work can be performed), and continue to inspect in accordance with either paragraphs (c) or (d) of this AD, as applicable. (c) If, during an inspection required by paragraph (a) of this AD, flame tube bridge piece leg cracking is found, establish a repetitive inspection interval for all engines in the fleet in accordance with paragraph 4.A.(3)(b) of the Bulletin or an FAA-approved equivalent and continue to inspect the fleet in accordance with paragraph (a) of this AD within the fleet repetitive inspection interval established under this paragraph. (d) If, during a repetitive inspection conducted in accordance with this paragraph or paragraph (c) of this AD, a cracked bridge piece leg of any flame tube in the fleet is found, establish a further reduced repetitive inspection interval for all engines in the fleet in accordance with paragraph 4.B.(3) of the Bulletin or an FAA- approved equivalent and continue to inspect the fleet in accordance with paragraph (a) of this AD within the fleet repetitive inspection interval established under this paragraph. This amendment becomes effective November 11, 1977.
2001-12-23: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200, 747-300, 747SP, and 747SR series airplanes powered by Pratt & Whitney JT9D-3 or JT9D-7 series engines, that currently requires inspections of the vertical chords of the aft torque bulkhead of the outboard nacelle struts, and corrective action, if necessary. That AD also gives an optional modification of the vertical chords, which ends the inspections. This amendment requires the previously optional modification. The actions specified by this AD are intended to prevent cracking of the vertical chords adjacent to the lower spar fitting, which could result in separation of the diagonal brace load path. Continued operation with a separated diagonal brace load path increases loads on the upper link, midspar fitting, and dual side links, which could result in separation of the strut and engine from the airplane.
87-18-04: 87-18-04 LOCKHEED-GEORGIA: Amendment 39-5723. Applies to Model 382, 382B, 382E, 382F, and 382G series airplanes; Serial Numbers 3946 through 5024, except 4412, 5022, 5025, 5027, 5029, and 5032; certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent the potential for smoke or fire occurring in the flight deck, accomplish the following: A. Within the next 25 hours time-in-service, inspect the 6 pilot's and copilot's circuit breaker panel areas, as follows: 1. Gain access to the following 6 circuit breaker panels in the flight station: pilot's side panel, upper and lower pilot's distribution panel, copilot's side panel, upper and lower copilot's distribution panel. 2. Open each circuit breaker panel and visually inspect for scorching, chafing, or short circuiting between circuit breaker wire terminals, wire bundles, and wire bundle clamps. 3. Inspect for minimum clearance of 0.250 inch between circuit breaker wire terminals, wire bundles, and wire bundle clamps. 4. With circuit breaker door closed, visually inspecting from adjacent door opening, inspect circuit breaker and attached wiring for chafing and minimum clearance. Direct particular attention to wire bundles routed at bottom of panels. 5. If 0.250 inch minimum clearance is present and no wire chafing or damage exists, return airplane to service. 6. If damaged wire is found, prior to further flight repair or replace wire in accordance with the applicable technical manual, SMP 582, Hercules Wiring Diagram Manual. 7. If 0.250 inch clearance does not exist, prior to further flight relocate wire bundle clamps and/or spaces, if necessary, to maintain minimum clearance. Reroute wiring in accordance with the applicable technical manual, SMP 582, Hercules Wiring Diagram Manual. B. Accomplishment of the inspection, repair, and relocation procedures described in Lockheed Alert Service Bulletin A382-24-19, dated August 7, 1987, constitutes compliance with the requirements of paragraph A. above. 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. D. 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, Atlanta Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Lockheed-Georgia Company, 86 South Cobb Drive, Marietta, Georgia 30063. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, Suite 210, 1669 Phoenix Parkway, Atlanta, Georgia. This amendment becomes effective September 17, 1987.