Results
2021-17-09: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney PW1500G and PW1900G series turbofan engines. This AD was prompted by reports of cracks in the high-pressure compressor (HPC) rotor shaft that resulted in in-flight shutdowns (IFSDs) and unscheduled engine removals (UERs). This AD requires removal and replacement of the HPC front hub and HPC rotor shaft. The FAA is issuing this AD to address the unsafe condition on these products.
2021-17-08: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-800 and -900ER series airplanes. This AD was prompted by reports that several of the fittings that provide attachment between the radome and fuselage were cracked to the point of failure on airplanes modified in accordance with a certain supplemental type certificate (STC). This AD requires demodification of the STC installation on the airplane by removing the external equipment installed during the STC modification (including the radome, antenna, and associated structure), installing doubler and fasteners, and system deactivation by pulling and collaring associated circuit breakers if installed. This AD also requires inspecting the external and feed- through doublers, intercostals, skin, and frames in the area around the removed external equipment for cracking, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
77-15-17: 77-15-17 ISRAEL AIRCRAFT INDUSTRIES (IAI): Amendment 39-2990. Applies to Model 1123 airplanes, S/N's 107, 151, 152, 153, 155 through 180, and 182 through 186, certificated in all categories, except those previously modified in accordance with IAI Service Bulletin No. WW-7A. Compliance is required within the next 150 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible rupture of the hydraulic pressure line between the hydraulic pump and the firewall, accomplish the following: (a) Remove and discard hose P/N 6723087-43 attached between the hydraulic pump pressure port and the AN837-6 elbow installed on pylon. (b) For airplanes S/N's 175 through 180 and 182 through 186, remove and discard brackets P/N's 5723548-3 and -5. (c) Remove the AN837-6 elbow from pylon, and reinstall with washer P/N 5723548- 7 on engine side of firewall. (d) Install hose P/N 6723087-57 between hydraulic pump pressure port andAN837- 6 elbow, with 45-degree fitting of hose attached to elbow on pylon. (NOTE: Position the elbow on pylon to allow hose to be as straight as possible. Bend radius of hose may not be less than 5.0 inches.) This amendment becomes effective August 29, 1977.
2004-07-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-15, DC-9-31, and DC-9-32 airplanes, that requires repetitive visual and x-ray inspections to detect cracks of the upper and lower corners and upper center of the door cutout of the aft pressure bulkhead; corrective actions, if necessary; and follow-on actions. For certain airplanes, this AD also requires modification of the ventral aft pressure bulkhead. This action is necessary to detect and correct fatigue cracks in the corners and upper center of the door cutout of the aft pressure bulkhead, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2021-15-10: The FAA is adopting a new airworthiness directive (AD) for all GE Aviation Czech s.r.o. (GEAC) H75-200, H80-100, and H80-200 model turboprop engines. This AD was prompted by several reports of engine gas generator speed (Ng) rollbacks occurring below idle on GEAC H75- 200, H80-100, and H80-200 model turboprop engines. This AD requires an inspection of a certain part number (P/N) fuel control unit (FCU) and, if deficiencies are detected, replacement of the FCU with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2021-17-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by the potential for the flexible hose assembly of the fuel motive flow (MF), installed between the pylon and wing, to be installed twisted in the shroud, which can restrict the flow of fuel for the MF and cause fuel imbalance and damage to the shroud assembly. This AD requires inspecting for damage of the left and right MF fuel line assemblies (including the flexible-hose and shroud assemblies), and replacing damaged parts, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD \n\n((Page 44601)) \n\nto address the unsafe condition on these products.
77-24-03: 77-24-03 HILLER HELICOPTERS: Amendment 39-3088. Applies to Hiller Model UH-12C, D, E (4 place), L, E-L, and L4's certificated in all categories incorporating control levers P/N 72229 or 72210. All aircraft serial numbers up to No. 5024 are included. S/N 5024 and subsequent will have the guard installed at the time of manufacture. (a) To prevent hazardous engine power loss from inadvertent shutoff of the fuel control valve, within the next 100 hours time in service after the effective date of this AD, install a guard on the fuel shutoff valve handle in accordance with the instructions described in Paragraph 2B in Hiller Service Bulletin No. 72-1 dated June 17, 1977, or later FAA approved revision. (b) Equivalent methods of fabrication and installation of a guard on the fuel shutoff valve handle may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate helicopters to a base for accomplishment of the modification required by Paragraph (a) of this AD. This amendment becomes effective January 6, 1978.
96-08-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires modification of the engine fuel feed system. This amendment is prompted by reports indicating that the coupling nut on the fuel tube on the outboard strut (engine position 1) fractured. The actions specified by this AD are intended to prevent such fracturing of the coupling nut, which could result in release of fuel onto the engine cowling and a subsequent fire.
2021-15-51: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. (type certificate previously held by Bell Helicopter Textron Inc.) Model 204B, 205A, 205A-1, 205B, and 212 helicopters. This AD was prompted by a fatal accident in which an outboard main rotor hub strap pin (pin) sheared off during flight, resulting in the main rotor blade and the main rotor head detaching from the helicopter. This AD requires removing the pins from service before further flight and prohibits installing them on any helicopter. The FAA previously sent an emergency AD to all known U.S. owners and operators of these helicopters and is now issuing this AD to address the unsafe condition on these products.
2011-18-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installation of an automatic shutoff system for the center tank fuel boost pumps, and installation of a placard in the airplane flight deck if necessary. This AD also requires revisions to the Limitations and Normal Procedures sections of the airplane flight manual to advise the flightcrew of certain operating restrictions for airplanes equipped with an automated center tank fuel pump shutoff control. This AD further requires installation of a secondary control relay for the electrical control circuit of each of the two center tank fuel boost pumps. Additionally, this AD requires a revision to the maintenance program to incorporate Airworthiness Limitation (AWL) No. 28-AWL-23. This AD also provides an option of installation and maintenance of universal fault interrupters using a certain supplemental type certificate, which terminates certain requirements of this AD. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent center tank fuel pump operation with continuous low pressure, which could lead to friction sparks or overheating in the fuel pump inlet that could create a potential ignition source inside the center fuel tank. These conditions, in combination with flammable fuel vapors, could result in a center fuel tank explosion and consequent loss of the airplane.
90-03-12: 90-03-12 BOEING: Amendment 39-6495. Docket No. 89-NM-180-AD. \n\n\tApplicability: Model 747 series airplanes with a door 5 crew rest area, listed in Boeing Service Bulletin 747-25-2776, dated June 8, 1989, certificated in any category. \n\n\tCompliance: Required within the next 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent empennage control cables from snagging on the cable shroud brackets above the Door 5 crew rest area, accomplish the following: \n\n\tA. Install control cable block plates in accordance with Boeing Service Bulletin 747-25- 2776, dated June 8, 1989. \n\n\tB. 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then sendit to the Manager, Seattle Aircraft Certification Office. \n\n\tC. 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6495, AD 90-03-12) becomes effective on March 5, 1990.
2021-16-15: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-8, 737-9, and 737-8200 (737 MAX) airplanes; and certain Model 737-800 and 737-900ER series airplanes. This AD was prompted by the determination that the aft cargo compartment fire suppression capability is reduced if the airplane is dispatched or released with failed electronic flow control of air conditioning packs, as is currently allowed by these airplane models' master minimum equipment lists (MMELs). This AD prohibits the carriage of cargo in the aft cargo compartment when the airplane is dispatched or released with failed electronic flow control of air conditioning packs. The FAA is issuing this AD to address the unsafe condition on these products.
2021-17-01: The FAA is adopting a new airworthiness directive (AD) for all Austro Engine GmbH E4 and E4P model diesel piston engines. This AD was prompted by a report of oil pressure loss on an E4 model diesel piston engine. This AD requires removing a certain oil pump from service and replacing it with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2011-18-02: We are adopting a new airworthiness directive (AD) for the products listed above with certain part number (P/N) fan rotor spinners installed. This AD requires removing from service certain fan rotor blade retainers, and removing from service the fan rotor spinner support that was installed with those fan rotor blade retainers. This AD was prompted by a fan rotor spinner support found cracked at the attachment lugs. We are issuing this AD to prevent high-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane.
90-24-02: 90-24-02 BOEING: Amendment 39-6804. Docket No. 90-NM-96-AD. \n\n\tApplicability: Model 757 series airplanes, as listed in Boeing Service Bulletin 757-30- 0015, Revision 1, dated January 25, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect undersized wiring in the flight compartment number 1 window heat system, accomplish the following: \n\n\tA.\tWithin 90 days after the effective date of this AD, inspect for the presence of undersized wires in the number 1 window heat system, in accordance with Boeing Service Bulletin 757-30-0015, Revision 2, dated August 2, 1990. If undersized wires are found, prior to further flight, replace with wires of appropriate size, in accordance with Boeing Service Bulletin 757-30-0015, Revision 2, dated August 2, 1990.\t\n \n\tB.\tWithin 30 days after detecting any undersized wires, submit a report of findings to the Manager, Manufacturing Inspection District Office, FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. \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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\tSpecial 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. \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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may beexamined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. \n\n\tThis amendment (39-6804, AD 90-24-02) becomes effective on December 17, 1990.
96-08-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires visual and dye penetrant inspection(s) to detect cracks of the nose rib of the rudder, and stop drilling and blending of minor cracks. This amendment also requires replacement of the nose rib with a new nose rib and reinforcement of the nose rib, if extensive cracking is detected or if an operator elects to terminate the repetitive inspections. This amendment is prompted by the result of an inspection that revealed a cracked nose rib on the front spar of the rudder due to vibration-related stress. The actions specified by this AD are intended to prevent such stress and cracking, which could result in the deformation of the nose rib; this condition may lead to friction and jamming between the fin and the rudder and subsequent reduced controllability of the airplane.
2004-07-16: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model C-235 series airplanes, that requires modification of the electrical wiring of the rudder trim control unit. This action is necessary to prevent the flight crew from being able to inhibit the aural warning for the landing gear up. If the flight crew of the next flight or possibly of the same flight is unaware that the aural warning had been disabled, they could inadvertently land the airplane with the landing gear not down and locked. This action is intended to address the identified unsafe condition.
2021-15-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reports of deficiencies in the primary flight control computer (PFCC) software and the remote electronics unit (REU) software. This AD requires installation of a software update to correct deficiencies in the PFCC and REU software, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
78-01-04: 78-01-04 BOEING: Amendment 39-3112 as amended by Amendment 39-3132. Applies to all Boeing 707-300/400/300B/300C series airplanes upon the accumulation of, or with more than 8,000 landings. \n\tVisually inspect the horizontal stabilizer center section rear spar upper chord for cracks between terminal fittings in accordance with Boeing Service Bulletin 3331 or with the method specified in paragraph B at the time interval specified in paragraph A below. Chords found cracked are to be reworked in accordance with one of the methods noted in paragraph C or replaced with a chord of the same part number prior to further flight. \n\tA.\tInspect within the next 375 landings after the effective date of this AD and thereafter at intervals not to exceed 375 landings. Report all cracks found during the initial inspection to the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, noting airplane identification, hours time in service, crack locations and magnitude. \n\tB.\tInspection may be accomplished by gaining access to the upper rear surface of the center section and examining the exposed surfaces of the upper chord using a bright light and a mirror at the aft upper and lower surfaces of the chord. If indications of a crack are found, eddy-current or penetrant inspection should be used to confirm presence of crack. \n\tC.\tRework in accordance with one of the following: \n\t\t1.\tAn FAA approved repair provided by the Boeing Company. \n\t\t2.\tA method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tD.\tWith permission of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, the airplane may be flown in accordance with FAR 21.197 to a base where the inspection or repair can be accomplished. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive who have notalready received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tAmendment 39-3112 became effective January 15, 1978. \n\tThis Amendment 39-3132 becomes effective March 1, 1978.
2021-15-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -300, -800, and -900 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports that certain oxygen supply solenoid valves are a potential source of increased flow resistance within the flightcrew oxygen system. This AD requires a special detailed inspection (flow test) of certain solenoid valves, and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
76-10-01: 76-10-01 BELL: Amendment 39-2610 as amended by Amendment 39-2927. Applies to Bell Models 205A and 205A-1 helicopters certificated in all categories. Compliance required as indicated. To prevent possible loss of the tail boom as a result of possible fatigue cracks in the tail boom and fuselage attach fittings in the tail boom and fuselage, accomplish the following. (a) For helicopters with less than 500 hours' total time in service after the effective date of this AD, conduct the visual inspections of this AD prior to attaining 550 hours' total time in service and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. (b) For helicopters with 500 or more hours' total time in service on the effective date of this AD, conduct the visual inspections of this AD within the next 50 hours' time in service and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. (c) Inspect the upper tail boom attach fittings for cracks, using a light and mirror, by removing the forward dome light of the baggage compartment. Inspect the fittings in the area of the most forward rivets. Special attention must be given to inspecting the upper left-hand fitting. (d) Inspect the lower tail boom attach fittings for cracks, using a light and mirror, by removing the forward access door on the tail boom. (e) Inspect the four tail boom attach fittings on the fuselage bulkhead, using a light and mirror, for cracks around the tail boom attach bolt and most aft fasteners. Special attention must be given to inspecting the lower left-hand fitting. (f) Inspect, visually, the four tail boom barrel nut bores for cracks, after removing the plug buttons. Determine that not less than one thread or more than two threads of the tail boom attachment bolts protrude through each barrel nut. (g) If cracks are found, replace the affected fitting prior to further flight in accordance with an FAA approved procedure. (h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, FAA Southwest 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. (i) This AD no longer applies to tailbooms that have been modified, repaired, and sealed as specified in Part II of Bell Helicopter Textron Service Bulletin No. 205-77-4 dated March 11, 1977, or later approved revisions. (j) This AD does not apply to helicopters having S/N 30260 or higher. (k) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Textron, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. (Bell Helicopter message dated April 29, 1976, to all 205A/205A-1 operators pertains to this subject.) Amendment 39-2610 became effective May 18, 1976. This Amendment 39-2927 becomes effective July 1, 1977.
2004-07-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -100B, -100B SUD, -200B, - 200C, -200F, -300, 747SR, and 747SP series airplanes equipped with Pratt & Whitney JT9D-3, -7, -7Q, and -7R4G2 series engines. This amendment requires drilling witness holes through the cowl skin at the cowl latch locations in the left-hand side of the cowl panel assembly of each engine. This action is necessary to prevent improper connection of the latch, which could result in separation of a cowl panel from the airplane. Such separation could cause damage to the airplane, consequent rapid depressurization, and hazards to persons or property on the ground. This action is intended to address the identified unsafe condition.
90-02-22: 90-02-22 DEHAVILLAND: Amendment 39-6471. Applicability: Models DHC-2 Mk. I (including L-20A, YL-20, U-6, and U-6A), and DHC-2 Mk. II (serial numbers 1 through 1056) airplanes certificated in any category. Compliance: Required as indicated in the body of the AD. To ensure the structural integrity of the horizontal tailplane to fuselage front attachment brackets, accomplish the following: (a) Within the next 200 hours time-in-service (TIS), or prior to the accumulation of 1000 hours TIS, whichever occurs later after the effective date of this AD, unless already accomplished per the requirements of AD 54-11-01, and thereafter at intervals not to exceed 1000 hours TIS: (1) Inspect attachment brackets, part number (P/N) C2-FS-543A and P/N C2-FS-544A for cracks and distorted rivets in accordance with paragraph `A' of the "ACCOMPLISHMENT INSTRUCTIONS" in deHavilland Service Bulletin (S/B) No. 2/42, Revision C, dated February 2, 1989. (2) Prior to furtherflight replace any distorted rivets as indicated in the above S/B, paragraph "B", and any cracked brackets as indicated in paragraph "C" of the Service Bulletin. (b) At each interval not exceeding 1000 hours TIS since the last bolt replacement, replace all 1/4 inch diameter forward attachment bolts on the tailplane front attachment brackets with new bolts, P/N AN174-H12A, in accordance with S/B No. 2/42 Rev C. (c) The repetitive inspections or modifications in paragraph (a) of this AD are not required on airplanes modified in accordance with deHavilland Modification No. 2/1338, or Agriculture Modification No. 2/984, as applicable. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where the requirements of this AD may be accomplished. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York 11581. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Boeing of Canada, Ltd.; deHavilland Division, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5; Telephone (416) 633-7310; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD supersedes AD 54-11-01. This amendment (39-6471, AD 90-02-22) becomes effective on February 13, 1990.
2021-13-11: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2D15 (Regional Jet Series 705) and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report that the lower aft outboard supporting structure of galley 2 does not meet certification requirements for all flight and/or emergency landing loads. This AD requires modifying the floor structure between certain fuselage stations. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-04: 76-17-04 ARMSTRONG WHITWORTH: Amendment 39-2701. Applies to all Model AW-650 Series 101 airplanes certificated in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To detect cracks in the undercut at the bottom of the main undercarriage sliding cylinder and prevent possible failure of the main landing gear, accomplish the following: (a) Inspect the undercut at the bottom of the main undercarriage sliding cylinder with magnetic particle fluid in accordance with Accomplishment Instructions 2A(1) through 2A(6) of Dowty Rotol Service Bulletin No. 32-49D, dated August 15, 1975, or an FAA-approved equivalent. (b) If a crack in the sliding cylinder is detected during the inspection required by paragraph (a) of this AD, replace the main undercarriage sliding cylinder before further flight with a serviceable part of the same part number or an FAA-approved equivalent. This amendment becomes effective on September 9, 1976.