Results
2006-07-26: The FAA is adopting a new airworthiness directive (AD) for all Aerospatiale Model ATR42 airplanes. This AD requires one-time inspections to detect discrepancies (e.g., cracking, loose/sheared fasteners, distortion) of the upper skin and rib feet of the outer wing boxes, and repair if necessary. This AD results from a report of cracking on the upper skin and ribs of the outer wing box on an in- service airplane. We are issuing this AD to detect and correct these discrepancies, which could result in reduced structural integrity of the airplane.
87-12-04: 87-12-04 BOEING: Amendment 39-5635. Applies to Model 747 series airplanes, listed in Boeing Service Bulletin 747-29-2063, dated December 23, 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of all four hydraulic systems in the event of severe damage to or loss of the vertical stabilizer, accomplish the following: \n\n\tA.\tWithin the next 24 months after the effective date of this AD, modify the number 4 hydraulic system by installing a hydraulic fuse in accordance with Boeing Service Bulletin 747- 29-2063, dated December 23, 1986, or later FAA-approved revision. \n\n\tB.\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\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to abase for accomplishment of the modification required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents may be examined at 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 July 13, 1987.
88-01-01: 88-01-01 BRITISH AEROSPACE: Amendment 39-5808. Applies to all Model BAe 125 800A and 800B series airplanes listed in British Aerospace BAe 125 Service Bulletin 24-259- (3171B), dated November 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent loss of critical flight instruments, accomplish the following: A. Within the next three months after the effective date of this AD, relocate the 115V. AC stall vane heater power circuit breakers, and modify power supply cable runs for the electronic flight instrument systems in accordance with the accomplishment instructions of British Aerospace BAe 125 Service Bulletin 24-259-(3171B), dated November 1986. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, 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 documents from the manufacturer may obtain copies upon request to British Aerospace, Inc, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. 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 becomes effective February 2, 1988.
99-21-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A airplanes, that requires replacement of the fuel drain tube assembly in the aft fuselage with a new, modified assembly. This amendment is prompted by a report of chafing of the fuel tube assembly against the elevator control cable due to inadequate clearance between the components. The actions specified by this AD are intended to prevent chafing of the fuel drain tube assembly, which could result in fuel leakage from the fuel drain tube assembly and consequent risk of a fire.
88-03-02: 88-03-02 BRITISH AEROSPACE: Amendment 39-5835. Applies to all Model H.S. 748 series airplanes, which have been modified in accordance with British Aerospace (BAe) Service Bulletins 57/31, 57/32, or 57/33, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent further cracking which could lead to reduced structural capability of the wing, accomplish the following: A. On airplanes previously modified in accordance with BAe Service Bulletin 57/31 or 57/33, inspect and modify the lower wing skins in accordance with BAe Service Bulletin 57/81, Revision 1, dated October 1985, prior to 7,500 hours since modification in accordance with BAe Service Bulletins 57/31 or 57/33, or within the next 750 hours time in service after the effective date of this AD, whichever occurs later. B. On airplanes previously modified in accordance with BAe Service Bulletin 57/32, inspect and modify the lower wing skins in accordance with BAe Service Bulletin 57/82, Revision 1, dated November 1985, prior to 10,000 hours since modification in accordance with BAe Service Bulletin 57/32, or within the next 750 hours time in service after the effective date of this AD, whichever occurs later. C. Any cracks found during the inspections required by paragraphs A. or B., above, must be repaired, prior to further flight, in accordance with BAe Service Bulletin 57/81, Revision 1, dated October 1985, or BAe Service Bulletin 57/82, Revision 1, dated November 1985, as applicable. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 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, Inc., Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington D.C. 20041. 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 becomes effective March 1, 1988.
2005-05-20: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2005-05-20 that was sent previously to all known affected U.S. operators of certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200F, 747-300, 747-400, 747-400D, 747SP, 747SR, 767-200, 767-300, 777- 200, 777-300, and 777-300ER series airplanes by individual notices. This AD requires modification of certain flight deck door electronic equipment. This AD results from a report indicating that this equipment is defective. We are issuing this AD to prevent failure of this equipment, which could jeopardize flight safety.
99-21-01: This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA- 360C, SA-365C, C1, and C2 helicopters. This action requires replacing certain electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. This condition if not corrected could result in loss of electrical continuity, which could cause loss of critical rotorcraft electrical systems and subsequent loss of control of the helicopter.
99-20-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires modification of the pressure web of the nose landing gear wheel well. This amendment is prompted by reports of fatigue cracks in the pressure web of the nose landing gear wheel well. The actions specified by this AD are intended to prevent cracking of the pressure web of the nose landing gear wheel well, which could result in loss of airplane pressurization.
89-13-03: 89-13-03 GQ PARACHUTES LTD: Amendment 39-6221. Applicability: Type 350 Parachute Assemblies (P/N's MRI GQ 1277, MRI GQ 1304 and MRI GQ 1325), 850 Parachute Assemblies (P/N's MRI GQ 1284, MRI GQ 1315 and MRI GQ 1330), and 4.8m SAC Parachutes (P/N's MRI GQ 1308 and MRI GQ D 22918/2). Compliance: Required as indicated, unless already accomplished. To prevent the use of FAA approved canopies which may contain understrength material, accomplish the following prior to next use after the effective date of this AD: (a) Perform an acid test on each mesh panel, in accordance with page 11 of GQ Parachutes Ltd. Service Bulletin (SB) No. 25-01, dated January 18, 1989. Those canopies found to be free of acid contamination may be approved for return to service. (b) For those canopies found to have acid contamination, perform the acid neutralization, pH test, and tensile test, in accordance with pages 5 and 6 of GQ Parachutes Ltd., (SB) No. 25-01, dated January 18, 1989. Those canopies having a pH value greater than 5.5 and a minimum tensile strength of 180 N/25mm (405.5 lbs./in.) may be approved for return to service. For those canopies found to have a pH value of 5.5 or less and/or a tensile strength less than 180 N/25mm (40.5 lbs./in.), remove or obliterate the TSO-C23c marking. (c) In lieu of compliance with paragraphs (a) and (b) above, the TSO-C23c markings must be removed or obliterated and the parachute must not be used as an approved parachute. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, may adjust the compliance times specified in this AD or approve an equivalent means of compliance with this AD. The repair and inspection procedures shall be done in accordance with GQ Parachutes Ltd. Service Bulletin No. 25-01, dated January 18, 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 GQ Parachutes Ltd., Portugal Road, Woking, Surrey, GU21 5JE England. Copies may be inspected at the Federal Aviation Administration, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, Room 8301, Washington, DC 20591. This amendment (39-6221, AD 89-13-03) becomes effective on July 31, 1989.
2006-07-18: The FAA is adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes. This AD requires a one- time inspection of the interior of the internal elevator torque tube of each elevator control surface for oxidation and corrosion, and corrective actions. This AD results from corrosion in torque tubes of the elevators found during scheduled maintenance. We are issuing this AD to detect and correct corrosion in the torque tubes of the elevators, which could lead to an unbalanced elevator and result in reduced controllability of the airplane.
87-20-06: 87-20-06 AIRBUS INDUSTRIE: Amendment 39-5734. Applies to Model A310 series airplanes with serial numbers listed in Airbus Service Bulletin A310-29-2010, Revision 3, dated August 21, 1985, certificated in any category. Compliance is required within 700 hours time in service after the effective date of this AD, unless previously accomplished. To prevent failure of the ram air turbine (RAT) extension system and ensure deployment of the RAT when required, accomplish the following: A. Test, inspect, and rework, if necessary, the RAT uplock hook and roller in accordance with Airbus Industrie Service Bulletin A310-29-2010, Revision 3, dated August 21, 1985. B. Repeat the tests, inspections, and necessary rework required by paragraph A., above, at intervals not to exceed 1,400 hours time in service. C. Incorporation of both Modification AI-5876 described in Airbus Industrie Service Bulletin A310-29-2011, Revision 1, dated September 2, 1986, and Modification AI 5958 described in Airbus Industrie Service Bulletin A310-29-2012, Revision 1, dated September 2, 1986, constitutes terminating action for the repetitive inspection requirements of paragraph B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. E. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, 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 October 30, 1987.
99-21-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-145 series airplanes. This action requires revising the Airplane Flight Manual (AFM) for operation in the rain, and modifying the anemometric static ports. This action also provides for optional terminating action for the requirements of this AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to limit or prohibit the use of the autopilot and flight director during the descent and approach to land in the rain, and to prevent fluctuations and erratic indications in the vertical speed, airspeed, and altitude readings in the cockpit during the descent and approach to land in the rain; such conditions could result in reduced controllability of the airplane during the descent and approach to land in the rain.
85-14-09: 85-14-09 McDONNELL DOUGLAS: Amendment 39-5096. Applies to McDonnell Douglas Model DC-10 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo assure the fire containment capability of the lavatory waste containers, accomplish the following: \n\n\tA.\tWithin 18 months after the effective date of this airworthiness directive (AD), modify the H/J type lavatory waste containers in accordance with the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 25-330, January 25, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to abase in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective August 16, 1985.
99-20-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires modification of the 90VU electronics rack umbrellas, the 91VU upper shelf assembly, the cockpit drain circuit, and the electrical wire routing above the 90VU electronics rack. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent damage to computer electrical connectors due to ingress of water into the avionics bay, which could result in malfunctioning of the avionics computers.
2006-07-16: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires replacing all domed anchor nuts at all attachment locations of the upper fuel access panels of the center wing in the wet bay location with new nuts. This AD results from reported cases of corroded dome anchor nuts at the attachment locations of the upper surface of the fuel access panel of the center wing. We are issuing this AD to prevent corrosion or perforation of domed anchor nuts, which could result in arcing and ignition of fuel vapor in the center wing fuel tank during a lightning strike and consequent explosion of the fuel tank.
99-19-35: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace BAe Model ATP airplanes, that requires repetitive tests for the serviceability of the nose landing gear compensator; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent a nose wheel shimmy, which could lead to the collapse of the nose landing gear during landing.
51-07-01: 51-07-01 NAVION: Applies to All Models Having Serial Numbers 1789 Through 2019; 2021 Through 2026; 2028 Through 2142; 2144 Through 2169; 2171 Through 2177; and 2180. To be accomplished as indicated below. It has been found that on some of these airplanes throttle housing slippage has occurred at the point where the cable housing is swaged to the ferrule at the instrument panel end. This slippage can result in erratic throttle operation. An inspection of these controls for evidence of housing slippage must be made not later than March 5, 1951. Any control showing evidence of slippage shall be replaced immediately. It has been found that housing slippage may be caused by the inner shaft in the control head striking the end of the housing when the throttle is moved to the full open position. To prevent such occurrence, a special stop nut must be installed on the throttle shaft in place of the existing jam nut. This special nut, which will prevent the inner shaft from striking the end of the housing, is being furnished by the Ryan Co. and must be installed by July 15, 1951. (Ryan Field Service Bulletin No. 9, dated September 1, 1950, covers this same subject.)
98-14-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes. This action requires repetitive inspections to detect cracks in the forward canted frames between fuselage frames 47a and 48 from stringer (STGR) 41 to STGR 43; and temporary repair, or replacement of the forward canted frame with a new frame, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking in the forward canted frames, which could result in failure of the forward canted frame, and consequent reduced structural integrity of the airplane.
2006-07-10: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 727 airplanes. That AD currently requires repetitive visual inspections for cracking of the forward entry doorway forward frame and repair if necessary. That AD also provides an optional modification that constitutes terminating action. This new AD requires adding new post-repair and post- modification inspections for previously repaired or modified airplanes, mandating the optional modification, and adding airplanes to the applicability of the AD. This AD results from reports of cracking of the forward entry doorway forward frame of airplanes previously modified. We are issuing this AD to prevent the loss of the structural integrity of the forward entry doorway due to cracking of the frame at Body Station 303.9, and consequent cracking of the fuselage skin and rapid decompression of the airplane.
2003-03-18: This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. This AD requires you to perform control column sweep and stop bolt inspections to verify full elevator travel to the primary up and down stops and that the stop bolt length is not excessive, re-rig the elevator control system if the airplane does not pass the control column sweep and stop inspections, and do a more detailed inspection at a later time if the airplane does pass the inspection. This AD also requires you to report the results of certain inspections. This AD is the result of recent ground testing and a review of the rigging procedures of a Raytheon Beech Model 1900D airplane, which reveals that the elevator control system could be mis-rigged to restrict elevator travel if current maintenance procedures are not properly followed. In these instances, it may appear to the crew that they have full elevator control column movement. However, the elevator may not have full travel. Such restricted travel may remain undetected until the airplane is operated in a loading condition that requires full elevator authority to control the pitch. The actions specified by this AD are intended to detect and correct any mis-rigged elevator control system, which could lead to insufficient elevator control authority and loss of control of the airplane.
2002-04-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 series airplanes and A320-200 series airplanes, that requires repetitive inspections to detect loose or missing rivets in specified areas of the door frames of the overwing emergency exits and corrective action, if necessary. This AD also requires measurement of the grip length of all rivets in the specified areas and corrective action, if necessary, which terminates the repetitive inspections. This amendment is prompted by mandatory continuing airworthiness information from a foreign airworthiness authority. The actions specified by this AD are intended to detect and correct loose or missing rivets or discrepant rivets, which could lead to reduced structural integrity of the overwing emergency exit door frames. This action is intended to address the identified unsafe condition.
2006-07-12: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires a one-time inspection for scribe lines and cracks in the fuselage skin at certain lap joints, butt joints, external repair doublers, and other areas; and related investigative/ corrective actions if necessary. This AD results from reports of fuselage skin cracks adjacent to the skin lap joints on airplanes that had scribe lines. Scribe line damage can also occur at many other locations, including butt joints, external doublers, door scuff plates, the wing-to-body fairing, and areas of the fuselage where decals have been applied or removed. We are issuing this AD to prevent rapid decompression of the airplane due to fatigue cracks resulting from scribe lines on pressurized fuselage structure.
68-03-04: 68-03-04 VICKERS: Amendment 39-551. Applies to Viscount Models 744, 745D, and 810 Series airplanes. Compliance required as indicated, unless already accomplished To detect cracking of the upper and lower torsion link hinge pins of the nose landing gear, accomplish the following: (a) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with less than 4,000 landings on the effective date of this AD, before the accumulation of 5,000 landings, and thereafter at intervals not to exceed 1,000 landings from the last inspection until the accumulation of 10,000 landings and thereafter at intervals not to exceed 500 landings from the last inspection, comply with paragraph (d). (b) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with 4,000 or more landings but less than 9,000 landings on the effective date of this AD, within the next 1,000 landings after the effective date of this AD and thereafter at intervals not to exceed 1,000 landings from the last inspection until the accumulation of 10,000 landings and thereafter at intervals not to exceed 500 landings, comply with paragraph (d). (c) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with 9,000 or more landings on the effective date of this AD, within the next 500 landings or before the accumulation of 10,000 landings, whichever occurs later, and thereafter at intervals not to exceed 500 landings from the last inspection, comply with paragraph (d). (d) Remove pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins and inspect for cracks using Magnaflux examination or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, in accordance with British Aircraft Corporation (BAC) Preliminary Technical Leaflets (PTLs) No. 233, Issue 3 (700 Series) and No. 99, Issue 3 (800 Series), or later ARB-approved issued, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (e) If cracked hinge pins are found during the inspections required by paragraphs (a), (b) and (c), before further flight, replace the pins with serviceable pins of the same part number and comply with the inspection requirements of paragraph (a), or replace the pins with Modification D.3045 (700 Series) and FG.1861 (800 Series) pins. (f) The repetitive inspections required by paragraphs (a), (b) and (c) may be discontinued on those hinge pins replaced by Modification D.3045 (700 Series) and FG.1861 (800 Series) pins. (g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective March 7, 1968.
98-05-11: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-215-6B11 (CL-215T) series airplanes. This action requires either replacement of the switching valve-to-rear inlet case sealing air tube assembly with a tube assembly that includes an integral fire detector (intercompressor case [ICC] fire detector loop), and modification of the nacelle fire detection system; or modification of the No. 5 bearing air system. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect internal engine fire within the ICC; or to prevent air/oil from leaking into the ICC, which could result in such fire.
2020-07-11: The FAA is adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R(eacute)gional Model ATR42 airplanes and Model ATR72 airplanes. This AD was prompted by reports of interference and chafing between a propeller brake hydraulic pipe and an electrical wire bundle bracket screw installed in the underwing box of the right-hand (RH) engine nacelle. This AD requires modification of the electrical wiring routing in the engine nacelles, a one-time detailed visual inspection (DVI) of the propeller brake hydraulic pipe and electrical wire bundle bracket screw head in the underwing box of the RH engine nacelle and, depending on findings, accomplishment of applicable corrective actions, 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. \n\n((Page 20397))