Results
83-08-01 R1: 83-08-01 R1 TRW HARTZELL PROPELLER: Amendment 39-4633. Letter issued April 29, 1983. Applies to all the TRW Hartzell Model HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC- B4TN-3, HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers. The HC-B( )TN-2, HC- B( )TN-3, and HC-B( )MP-3 propellers are installed on Pratt & Whitney Aircraft of Canada Model PT6A-( ) series engines. The HC-B( )TN-5 and HC-B( )MN-5 series propellers are installed on the AiResearch TPE-331-( ) series engines.\n \n\tCompliance required as indicated, unless already accomplished. To preclude propeller attach bolt failures or improperly secured propellers, accomplish the following:\n\n\tA.\tPrior to further flight, all new propeller installations and serviceable propellers which are being reinstalled must be installed as follows: \n\n\t\t(1)\tInstall the propeller oil seal to the engine flange after ensuring that the engine and propeller flanges are clean.\n \n\t\t(2)\tCarefully install propeller on the engine flange ensuring that complete and true contact is established.\n\n\t\t(3)\tApply MIL-T-5544 Petrolated Graphite or TRW Hartzell Lubricant P/N A3338 to bolt threads and bolt washer surfaces (and remainder of bolt if desired).\n \n\t\t(4)\tInstall eight new B-3339 bolts and eight new A-2048-2 washers through engine flange into propeller flange.\n \n\t\t(5)\tTorque all bolts, with a torque wrench and an appropriate adapter, to 40 ft.-lbs. and then to 80 ft.-lbs. following torque sequence "A" (shown to below). Final torque all bolts using "B" sequence (shown below) to 100 to 105 ft.-lbs. Safety all bolts in an FAA approved manner.\n\n\n\n\n \n\tNOTE: TRW Hartzell Instructions No. 140 dated March 15, 1982, also pertains to this subject.\n \n\tB.\tWithin the next 300 hours time in service after the effective date of this AD, accomplish the following on all applicable turbopropeller installations presently using P/N A- 2047 propeller attach bolts: \n\n\t\t(1)\tCheck the torque, with a torque wrench and an appropriate adapter,of all eight propeller attach bolts (with washers installed). Torque should be 100 to 125 ft.-lbs. with dry threads. (Caution: Do not use any lubricant with the A-2047 bolts. Safety all bolts in an FAA approved manner.)\n \n\t\t(2)\tIf the torque of any 1 of the bolts is found to be less than 100 ft.-lbs., remove all 8 bolts and washers and replace with new (B-3339) bolts and new (A-2048-2) washers in accordance with paragraphs A (1) through (5) herein. (Caution: Do not use an intermix of A-2047 and B-3339 bolts in the same installation.) NOTE: The A-2047 bolt has the letter "H" stamped inside a triangle on the bolt. The B-3339 bolt has the part number stamped inside the cupped head.\n \n\tC.\tUpon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018.\n \n\tThis amendment supersedes Amendment 39-3290 (43 FR 42731), AD78-18-01.\n \n\tAmendment 39-4633 became effective April 28, 1983.\n\n\tThis amendment becomes effective upon receipt.
98-05-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of electrical relays 15KF and 16KF, which control the auxiliary propeller control feathering system, with relays having increased load capacity. 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 failure of the auxiliary propeller control feathering system, which, in the event of an engine failure combined with failure of the primary propeller pitch control, could result in the inability to feather the propeller, and consequent reduced controllability of the airplane.
98-21-03: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires replacement of the existing load limitation labels located in the main baggage compartment with new reduced load limitation labels. This amendment also provides for optional modification of the internal access door of the main baggage compartment, which, if accomplished, terminates the requirement for reduced load limitations. 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 failure of the internal access door latches of the main baggage compartment in the event of an emergency landing, which could delay or impede passenger evacuation due to baggage spilling into the aisle and blocking the emergency exit door.
70-16-02: 70-16-02 DOWTY ROTOL: Amendment 39-1015 as amended by Amendment 39-1503. Applies to all Dowty Rotol propellers, installed on but not necessarily limited to the following airplanes: Fairchild Series F-27 and FH-227, Armstrong Whitworth AW 650, Grumman G-159, Viscount 700 and 810 series, Nihon YS-11, and Convair 240, 340, 440 turbopropeller conversions. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. (a) Inspect the blade pitch change operating link and eyebolt fork assembly for - (1) Seizure (the link and eyebolt are seized if the torque required to move the link is 300 inch pounds or more); and (2) Cadmium plating on the mating surfaces between the operating link and eyebolt fork and the holes through the eyebolt fork and the operating link. (b) If the link and eyebolt fork are not seized and have not been cadmium plated, they may remain in service. (c) If the linkand eyebolt fork are not seized but cadmium plating is found in the prohibited areas, remove the plating by means of wet or dry silicon carbide paper, fine or medium grade, and conduct a magnetic crack test. If no cracks are found, the assembly may remain in service until the next propeller overhaul for air carrier airplanes and airplanes under a continuous maintenance program or for 3,300 hours' time in service after the effective date of this AD for all other airplanes. At the next propeller overhaul for air carrier airplanes and airplanes under a continuous maintenance program, or within 3,300 hours' time in service after the effective date of this AD for all other airplanes, heat treat the links and eyebolt forks found to have been cadmium plated in order to remove embrittlement in accordance with Dowty Rotol Service Bulletin No. 61- 754, dated June 12, 1970, or later ARB-approved issue or an FAA-approved equivalent. (d) If the link and eyebolt fork are seized, remove the linkand eyebolt fork from service and replace them with an assembly having a part number approved for that model propeller that has not been cadmium plated in the prohibited areas. (e) If the link or eyebolt fork are found to be cracked during the inspection in paragraph (c), remove the cracked part from service and replace it with a part having a part number approved for that model propeller that has not been cadmium plated. (f) The inspection required by paragraph (a) need not be performed and the propeller may remain in service if - (1) The operator can show that no cadmium plating exists in the prohibited areas of that propeller; or (2) It is a new propeller that has never been overhauled. Amendment 39-1015 became effective July 25, 1970. This Amendment 39-1503 becomes effective August 21, 1972.
2019-20-05: The FAA is superseding airworthiness directive (AD) 2018-15-01 for certain Rolls-Royce plc (RR) Trent 1000-A, Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, Trent 1000-H, Trent 1000-A2, Trent 1000-C2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 model turbofan engines. AD 2018-15-01 required certain engines susceptible to intermediate- pressure turbine (IPT) blade failure not be installed on an airplane together with other engines with IPT blades of the same cyclic life. This AD requires removal of the IPT blade set at lower cyclic life limits and replacing it with a blade set eligible for installation. This AD also expands the applicability to include additional Trent 1000 turbofan engine models. This AD was prompted by the determination that certain IPT blades are susceptible to shank corrosion which leads to cracking and possible blade separation. The FAA is issuing this AD to address the unsafe condition on these products.
98-18-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, that currently requires reinforcement of the tail section of the fuselage at frames 68 and 69. This amendment adds a requirement for reinforcement of the tail section of the fuselage at frames 65 to 67. This action also revises the applicability of the existing AD. This amendment is prompted by reports indicating that the tail section has struck the runway during takeoffs and landings. The actions specified by this AD are intended to prevent structural damage to the tail section when it strikes the runway, which could result in depressurization of the fuselage during flight.
2007-11-11: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A318, A319, A320, and A321 airplanes. That AD currently requires a one-time inspection to determine the serial number of both main landing gear (MLG) sliding tubes, repetitive detailed inspections for cracking of the affected MLG sliding tubes, and corrective actions if necessary. This new AD retains these inspections and adds new repetitive inspections for cracking of the MLG sliding tubes. This AD also requires eventual replacement of both MLG shock absorbers. Doing this replacement terminates the repetitive inspection requirements of this AD. This AD results from a determination that additional inspections and mandatory replacement of the MLG shock absorbers are necessary. We are issuing this AD to detect and correct cracking in an MLG sliding tube, which could result in failure of the sliding tube, loss of one axle, and consequent reduced controllability of the airplane.DATES: This AD becomes effective June 29, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 29, 2007. On June 23, 2004, (69 FR 31867, June 8, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A320-32A1273, Revision 01, dated May 6, 2004.
98-01-08: 98-01-08 TELEDYNE CONTINENTAL MOTORS with STC SE8594SW: Priority Letter issued on December 23, 1997. Docket No. 97-ANE-48-AD. Applicability: Teledyne Continental Motors (TCM) IO-520-A, -B, -BA, -C, -CB, -D, -E, -F, -K, -L, -M, -MB, -J; TSIO-520-A, -B, -D, -E, -F, -G, -H, -J, -K, -L, -M, -N, -P, -R, -T, -U, -UB, -AF, -CE, -VB, -WB, -NB, -LB, -KB, -JB, -EB, -DB, -BB; O-470-B, -G, -K, -L, -M, -P, -R, -S, -U; IO-470-C, -D, -E, -F, -G, -H, -L, -M, -N, -P, -R, -S, -U, -V; and IO-550-B, -C, and -G series reciprocating engines, with Performance Engineering exhaust roller rocker arms, Part Number (P/N) PE92E, installed, in accordance with Supplemental Type Certificate (STC) SE8594SW. These engines are installed on but not limited to Cessna 180, 182, 185, 206, 207, 210, 310, 335, 340, 401, 402, 414; Raytheon (Beech) 33, 35, 36, 55, 58; Bellanca 17-30; New Piper PA-46; Fletcher FU-24A aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent exhaust roller rocker arm failure, which can result in bent push rods, ruptured rocker arm covers, loss of engine oil, engine power loss and roughness, and possible engine failure, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, remove from service all Performance Engineering exhaust roller rocker arms, P/N PE92E, and replace with serviceable parts, as follows: (1) For IO-520, TSIO-520, O-470, IO-470, and all IO-550 series engines except the IO-550-G, replace with serviceable TCM exhaust roller rocker arms, P/N 652130. (2) For IO-550-G series engines, replace with serviceable TCM exhaust roller rocker arms, P/N 652966. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Special Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Special Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Special Certification Office. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) Priority Letter AD 98-01-08, issued December 23, 1997, becomes effective upon receipt.
98-20-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires relocation of the engine/master 1 relay from relay box 103VU to shelf 95VU in the avionics bay. 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 simultaneous cutoff of the fuel supply to both engines, which could result in a loss of engine power and consequent reduced controllability of the airplane.
90-09-09: 90-09-09 BOEING: Amendment 39-6586. Docket No. 89-NM-217-AD. \n\n\tApplicability: Model 747 series airplanes, listed in Boeing Service Bulletin 747-53- 2064, Revision 4, dated September 23, 1983, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect cracks in the front spar pressure bulkhead chord, accomplish the following: \n\n\tA.\tFor airplanes that have not been modified in accordance with Boeing Service Bulletin 747-53-2064, dated July 25, 1972: Within the next 1,000 landings after October 15, 1984 (the effective date of AD 84-18-06, Amendment 39-4912), or prior to the accumulation of 10,000 landings, whichever occurs later, and thereafter at intervals not to exceed 7,000 landings, conduct a high frequency eddy current (HFEC) inspection of the chord to detect cracks between stringers S-37 and S-39 at the chord radius, heel, and flanges adjacent to the fastener holes identified for inspection in Boeing Service Bulletin 747-53-2064, Revision 4, dated September 23, 1983. If cracks are found in the pressure bulkhead chord, accomplish the repair in accordance with the service bulletin before further flight. Repair of cracks along the chord radius under 5 inches in length, or across a chord flange that have not severed the chord flange, may be deferred 1,000 landings by stop drilling and reinspecting for crack progression every 200 landings using HFEC. If crack progression is found, repair in accordance with the service bulletin prior to further flight. Inspections are to continue at intervals not to exceed 7,000 landings after repair. \n\n\tB.\tFor airplanes that have been modified in accordance with Boeing Service Bulletin 747-53-2064, dated July 25, 1972: Within the next 1,000 landings after October 15, 1984 (the effective date of AD 84-18-06, Amendment 39-4912), or prior to the accumulation of 10,000 landings after the modification, whichever is later, and thereafter at intervals not to exceed 10,000 landings, conduct an HFEC inspection to detect cracks in the front spar pressure bulkhead lower chord heel from stringers S-37 to S-39, and conduct an ultrasonic inspection to detect cracks in the fuselage skin originating at the indicated fastener holes beneath the forward drag splice fitting flanges, in accordance with the service bulletin. If any cracks are found, repair in accordance with Boeing Service Bulletin 747-53-2064, Revision 4, dated September 23, 1983, before further flight. Inspections are to continue at intervals not to exceed 10,000 landings after repair. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tFor the purposes of complying with this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's number of hours time in service by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\tE.\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 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 supersedes Amendment 39-4912, AD 84-18-06. \n\tThis amendment (39-6586, AD 90-09-09) becomes effective on June 4, 1990.
90-23-14: 90-23-14 BOEING: Amendment 39-6801. Docket No. 90-NM-110-AD. \n\n\tApplicability: Model 747 series airplanes, identified in Boeing Service Bulletin 747-53- 2253, Revision 2, dated March 29, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent sudden loss of cabin pressurization and the inability to withstand fail-safe loads, accomplish the following: \n\n\tA.\tFor airplanes that have not been modified in accordance with Boeing Service Bulletin 747-53-2253, Revision 2, dated March 29, 1990: In accordance with the schedule indicated below, perform a high frequency eddy current inspection of the fuselage lap joint for cracks between body station (BS) 340 and BS 400, or aft as far as the crew door, at stringer (S)- 6L and S-6R, in accordance with Boeing Service Bulletin 747-53-2253, Revision 2, dated March 29, 1990. \n\n\t\t1.\tInspection schedule: \n\n\t\t\ta.\tUnless previously accomplished within the last 2,750 landings, perform the initial inspection within the next 250 landings after the effective date of this AD, or prior to the accumulation of 10,000 landings, whichever occurs later. \n\n\t\t\tb.\tRepeat the inspection thereafter at intervals not to exceed 3,000 landings. \n\n\t\t2.\tIf cracks are found, repair prior to further flight, in accordance with Boeing Service Bulletin 747-53-2253, Revision 2, dated March 29, 1990. \n\n\tB.\tFor airplanes that have been modified in accordance with Boeing Service Bulletin 747-53-2253, Revision 2, dated March 29, 1990: In accordance with the schedule below, perform a high frequency eddy current inspection of the fuselage lap joint for cracks between BS 340 and BS 400, or aft as far as the crew door, at stringers (S)-6L and S-6R, in accordance with Boeing Service Bulletin 747-53-2253, Revision 2, dated March 29, 1990. \n\n\t\t1.\tInspection schedule: \n\n\t\t\ta.\tUnless previously accomplished within the last 2,750 landings, perform the initial inspection within the next 250 landings after the effective date of this AD, or prior to the accumulation of 10,000 landings after the modification, whichever occurs later. \n\n\t\t\tb.\tRepeat the inspection thereafter at intervals not to exceed 3,000 landings.\n \n\t\t2.\tIf cracks are found, repair prior to further flight, in accordance with Boeing Service Bulletin 747-53-2253, Revision 2, dated March 29, 1990. \n\n\tC.\tFor purposes of complying with this AD, the number of landings may be determined to be equal to the number of pressurization cycles where the cabin pressure differential was greater than 1.5 psi. \n\n\tD.\tFor Model 747SR airplanes only: Based on a continued mixed operation of lower cabin differentials, the initial inspection thresholds and the repetitive inspection intervals specified in this AD may be multiplied by a 1.2 adjustment factor. \n\n\tE.\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\tF.\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 be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tAirworthiness Directive 90-23-14 supersedes AD 85-17-05, Amendment 39-5123. \n\tThis amendment (39-6801, AD 90-23-14) becomes effectiveon December 11, 1990.
97-19-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-145 series airplanes. This action requires repetitive visual inspections to detect cracks in the firewall of the auxiliary power unit (APU), and repair, if necessary. This AD also requires installation of a visco-elastic damper blanket on the firewall, which constitutes terminating action for the repetitive inspection requirements. This amendment is prompted by reports indicating that cracks were found in the firewall of the APU due to vibration of the firewall. The actions specified in this AD are intended to prevent such cracking, which could result in reduced structural integrity of the fuselage and empennage in the event that a fire penetrates through the firewall of the APU.
98-22-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 2000 series airplanes, that requires modification of the front galley and rear lavatory water heaters. 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 failure of the water heater control thermostat and the associated electrical relay, which could lead to overheating of the water and damage to the adjacent wiring, and consequent smoke and fumes in the passenger cabin and possible injury to the flight crew and passengers.
2019-19-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that new \n\n((Page 54481)) \n\nor more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
97-18-09: 97-18-09 AIRBUS INDUSTRIE: Amendment 39-10119. Docket 97-NM-41-AD. Supersedes AD 96-08-07, Amendment 39-9573 which superseded AD 94-21-07 amendment 39-9049. Applicability: All Model A300-600 and A310 series airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent an out-of-trim condition between the trimmable horizontal stabilizer and the elevator, which could severely reduce controllability of the airplane, accomplish the following: RESTATEMENT OF ACTIONS REQUIRED BY AD 96-08-07, AMENDMENT 39-9573: (a) Within 10 days after May 23, 1996 (the effective date of AD 96-08-07, amendment 39-9573), revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the information contained in paragraph (a)(1) or (a)(2) of this AD, as applicable. This may be accomplished by inserting a copy of this AD in the AFM. The AFM limitation required by AD 94-21-07, amendment 39-9049, may be removed following accomplishment of the requirements of this paragraph. (1) For airplanes on which the flight control computers (FCC) have not been modified in accordance with the requirements of paragraph (b) of this AD: "Overriding the autopilot (AP) in pitch axis does not cancel the AP autotrim when LAND TRACK mode [green LAND on both Flight Mode Annunciators (FMA)] or GO-AROUND mode is engaged. In these modes, if the pilot counteracts the AP, the autotrim will trim against pilot input. This could lead to a severe out-of-trim situation in a critical phase of flight." (2) For airplanes on which the FCC's have been modified in accordance with requirements of paragraph (b) of this AD: "Overriding the autopilot (AP) in pitch axis does not cancel the AP autotrim when LAND TRACK mode (green LAND on both FMA's) is engaged, or GO-AROUND mode is engaged below 400 feet radio altitude (RA). In these modes, if the pilot counteracts the AP, the autotrim will trim against pilot input. This could lead to a severe out-of-trim situation in a critical phase of flight." RESTATEMENT OF ACTIONS REQUIRED BY AD 94-21-07, AMENDMENT 39-9049: (b) For airplanes equipped with FCC's having either part number (P/N)B470ABM1 (for Model A310 series airplanes) or B470AAM1 (for Model A300-600 series airplanes): Within 60 days after November 2, 1994 (the effective date of AD 94-21-07, amendment 39-9049), modify the FCC's in accordance with Airbus Service Bulletin A310-22-2036, dated December 14, 1993 (for Model A310 series airplanes), or Airbus Service Bulletin A300-22-6021, Revision 1, dated December 24, 1993 (for Model A300-600 series airplanes), as applicable. (c) As of November 2, 1994, no person shall install a FCC having either P/N B470ABM1 or B470AAM1 on any airplane. NEW ACTIONS REQUIRED BY THIS AD: (d) For airplanes on which Modification No. 11454 [reference Airbus Service Bulletin A310-22-2044 (for Model A310 series airplanes) or Airbus Service Bulletin A300-22-6032 (for Model A300-600 series airplanes)] has not been installed: Accomplish paragraphs (d)(1), (d)(2)(i) and (d)(2)(ii) of this AD. (1) Within 24 months after the effective date of this AD, modify the autopilot in accordance with Airbus Service Bulletin A310-22-2044, Revision 1, dated January 8, 1997 (for Model A310 series airplanes), or Service Bulletin A300-22-6032, Revision 1, dated January 8, 1997 (for Model A300-600 series airplanes), as applicable. The requirements of paragraph (a) of AD 95-25-09, amendment 39-9455, if applicable, must be accomplished prior to or at the same time the requirements of this paragraph are accomplished. (2) Prior to further flight following accomplishment of paragraph (d)(1) of this AD: (i) Remove the AFM revisions required by paragraph (b) of this AD; and (ii) Perform an operational test of this autopilot disconnect feature to determine that it operates properly, in accordance with Airbus Service Bulletin A310-22-2047, dated July 16, 1996 (for Model A310 series airplanes), or Service Bulletin A300-22-6035, dated July 16, 1996 (for Model A300-600 series airplanes), as applicable. If any discrepancy is detected, prior to further flight, repair it in accordance with the applicable service bulletin. Repeat this test thereafter at intervals not to exceed 18 months. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The modificationof the FCC's shall be done in accordance with Airbus Service Bulletin A310-22-2036, dated December 14, 1993, or Airbus Service Bulletin A300-22-6021, Revision 1, dated December 24, 1993, as applicable. The incorporation by reference of those documents was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of May 23, 1996 (61 FR 16873, April 18, 1996). The modification and operational test of the autopilot shall be done in accordance with Airbus Service Bulletin A310-22-2044, Revision 1, dated January 8, 1997; Airbus Service Bulletin A300-22- 6032, Revision 1, dated January 8, 1997; Airbus Service Bulletin A310-22-2047, dated July 16, 1996; or Airbus Service Bulletin A300-22-6035, dated July 16, 1996; as applicable. The incorporation by reference of those documents 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 Airbus Industrie, 1Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on October 3, 1997.
86-24-07: 86-24-07 CESSNA: Amendment 39-5475. Applies to the following model and serial number single-engine airplanes certificated in any category manufactured thru Model year 1978 equipped with ball type rod ends on the engine controls. \n\n\nMODELS\nSERIAL NUMBERS\n150C thru 150M\nS/N 15059701 thru 15079405 \nA150K thru A150M\nS/N A1500001 thru A1500734 \n152\nS/N 15279406 thru 15282031 \nA152\nS/N A1520735 thru A1520808 \n172D thru 172N\nS/N 17249545 thru 17271034 \nR172K\nS/N R1722000 thru R1722929 \nP172D\nS/N P17257120 thru P17257188\n177 thru 177B\nS/N 17700001 thru 17702752 \n177RG\nS/N 177RG0001 thru 177RG1366 \n180F thru 180K\nS/N 18051184 thru 18053000 \n182F thru 182Q\nS/N 18254424 thru 18266590 \nR182\nS/N R18200001 thru R18200583 \n185B thru 185E\nS/N 185-0513 thru 185-1599\nA185E, A185F\nS/N 18501600 thru 18503683 \n188, A188\nS/N 188-0001 thru 188-0572\nA188A, 188B\nS/N 18800573 thru 18803296 \nA188B\nS/N 18800967T thru 18803296T \n205, 205A\nS/N 205-0001 thru 205-0577\n206, U206\nS/N 206-0001 thru 206-0275\nU206A thru U206G\nS/N U206-0276 thru U206-1444 \nTU206A thru TU206G\nS/N U20601445 thru U20604649 \nP206, P206A thru P206E\nS/N P206-0001 thru P206-0603 \nTP206A thru TP206E\nS/N P20600604 thru P20600647 \n207, 207A, T207, T207A\nS/N 20700001 thru 20700482 \n210C thru 210M and\nT210K thru T210M\n\nS/N 21058086 thru 21062954 \nT210F thru T210J\nS/N T210-0001 thru T210-0454 \nP210N\nS/N P21000001 thru P21000150\nF150F thru F150M\nS/N F150-0001 thru F150-0529\nS/N F15000530 thru F15001428 \nFA150K, FA150L\nS/N FA1500001 thru FA1500120 \nFRA150L, FRA150M\nS/N FRA1500121 thru FRA1500336 \nF152\nS/N F15201429 thru F15201528 \nFA152\nS/N FA1520337 thru FA1520347\nFP172\nS/N FP172-0001 thru FP172-0003\nF172D thru F172N\nS/N F172-0001 thru F172-0654 \nS/N F17200655 thru F17201749 \nFR172E thru FR172K\nS/N FR17200001 thru FR17200630 \nF177RG\nS/N F177RG0001 thru F177RG0177 \nF182P, F182Q\nS/N F18200001 thru F18200094 \nFR182\nS/N FR18200001 thru FR18200020\nR172E thru R172H\nS/N R172-0001 thru R172-0409 \nS/N R1720410 thru R1720625 \n\n\tCompliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent engine power interruption due to loss of attachment of the engine controls, accomplish the following: \n\n\t(a)\tModify the engine controls installation by installing a drilled steel bolt, AN3l0 type castellated nut and a steel cotter pin in accordance with Cessna Single-Engine Customer Care Service Information Letter SE79-6. \n\n\t(b)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. \n\n\t(c)\tAn equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. \n\n\tAll persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Cessna Aircraft Company, Customer Services, Post Office Box 1521, Wichita, Kansas 67201; or the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. \n\n\tThis amendment becomes effective on January 7, 1987.
74-06-01: 74-06-01 PIPER: Amendment 39-1799 is amended by Amendment 39-1977. Applies to Piper Models PA-23-235, PA-23-250 and PA-E23-250 airplanes certificated in all categories with AiResearch turbosuperchargers installed in accordance with STC SA852WE, SA909WE or SA978WE,. or installed in accordance with Piper Aircraft Corporation Drawing 32016. Compliance required as indicated, unless previously accomplished. To minimize fire hazards related to engine compartment fires, accomplish the following in accordance with AiResearch Aviation Company Service Bulletin No. 14.1.10, dated February 6, 1974 or later FAA-approved revision, for serial numbers 27-2505 and subsequent (Aztec C, Aztec D, Aztec E), and, in accordance with AiResearch Service Bulletin No. 14.1.11, dated February 6, 1974 or later FAA-approved revision for serial numbers 27-1 through 27-2504 (Aztec, Aztec B, Apache 235): (a) Within the next 25 hours' time in service after the effective date of this airworthinessdirective, add drainage provisions in the airscoops, AiResearch Part No. 286-P23-066-5, of airplanes serial numbers 27-2505 and subsequent. (b) Within the next 600 hours' time in service or 365 days after March 18, 1974, whichever occurs first: (1) For airplanes serial numbers 27-1 through 27-2504: (i) Replace the existing turbosupercharger oil tanks with AiResearch Part No. 286-P23-028-81F oil tanks. (ii) Install AiResearch Part No. 286-P23-028-231 fire shrouds and seal all openings in the fire shrouds. (iii) Add drainage provisions in the oil tank fairings, AiResearch Part No. 286-P23-057. (2) For airplanes serial number 27-2505 and subsequent: (i) Replace the existing turbosupercharger oil tanks with AiResearch Part No. 286-P23-028-111F oil tanks. (ii) Seal all openings in the fire shrouds, AiResearch Part No. 286- P23-064-153. (c) Equivalent modification may be approved by the Chief, Aircraft Engineering Division, FAA WesternRegion. (d) Aircraft may be flown to a base where the maintenance required by this airworthiness directive may be performed per FARs 21.197 and 21.199. NOTE: For the requirements regarding the listing of compliance of and method of compliance with this airworthiness directive in the permanent maintenance record of the airplane, see FAR 91.173. NOTE: The extended compliance time authorized by this amendment to AD 74-06-01, as set forth in (b) above, shall be retroactive to September 14, 1974, to permit aircraft operations beyond 180 days after March 18, 1974. Amendment 39-1799 became effective March 18, 1974. This Amendment 39-1977 becomes effective October 2, 1974.
97-24-10: This amendment adopts a new airworthiness directive (AD) that applies to Burkhart Grob Luft-und Raumfahrt, GmbH. (Grob) Model G 103 Twin Astir sailplanes. This action requires replacing the airbrake over-center lever and installing new inspection holes. The AD is the result of cracked airbrake over-center levers found during routine inspections. The actions specified by this AD are intended to prevent an asymmetrical airbrake deployment, which could result in an uncontrollable roll and possible loss of control of the sailplane.
2019-16-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of unreliable performance of the water and fuel scavenge system; failure of the fuel scavenge function can cause trapped fuel, resulting in unavailable fuel reserves. This AD requires incorporating operating limitations; or modifying the water and fuel scavenge systems in the fuel tanks, modifying the fuel jettison system, making electrical changes in the main equipment center, modifying the wiring in certain panels, and installing new software. We are issuing this AD to address the unsafe condition on these products.
2019-19-17: The FAA is superseding Airworthiness Directive (AD) 2000-03-20 R1, which applied to all Airbus SAS Model A300 B4-601, B4-603, and B4- 620, Model A300 B4-600R series, and Model A300 F4-605R airplanes. AD 2000-03-20 R1 required repetitive inspections to detect cracks on the forward fittings in the radius of a certain frame, adjacent to the tension bolts in the center section of the wings, and various follow-on actions. This AD retains the requirements of AD 2000-03-20 R1, adds new airplanes to the applicability, and introduces new compliance times for the required inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of cracking due to fatigue-related stress in the radius of frame 40, adjacent to the tension bolts at the center/ outer wing junction. The FAA is issuing this AD to address the unsafe condition on these products.
96-25-06: 96-25-06 SAAB AIRCRAFT AB: Amendment 39-9848. Docket 95-NM-201-AD. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159 inclusive; and Model SAAB 340B series airplanes, serial numbers 160 through 379 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specificproposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent high bearing stress on the bushings in the flap fittings, which could result in jamming of the flaps and consequent reduced controllability of the airplane, accomplish the following: (a) Within 800 hours time-in-service after the effective date of this AD: Perform a visual inspection to detect damage or cracking of the forward and aft attachment lugs of the flap fittings at wing station (WS) 123.38, in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. (1) If no cracking or damage is found, and the flap fittings have not been modified or replaced, repeat the visual inspection thereafter at intervals not to exceed 800 hours time-in-service. (2) If any cracking is found, prior to further flight, replace the flap fittings with new improved flap fittings, and install improved bushings, in accordance with the Accomplishment Instructions (Modification 2628 - Part 3) of the service bulletin. After this modification is accomplished, no further action is required by this paragraph. (b) Within 4,500 hours time-in-service after the effective date of this AD, perform an inspection to determine the size of the inboard and outboard holes (swaged bushings) of the flap fittings, and to detect loose swaged bushings, in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. (1) If the sizes of the holes are within the limits specified in the service bulletin, and if no loose swaged bushings are found, prior to further flight, install improved bushings in accordance with the Accomplishment Instructions (Modification 2628 - Part 1) of the service bulletin. After this modification is accomplished, no further action is required by this AD. (2) If the size of any hole is outside the limits specified in the service bulletin, or if any loose swaged bushing is found, prior to further flight, install oversize bushings in the flap fittings, and install improved bushings, in accordance with the Accomplishment Instructions (Modification 2628 - Part 2) of the service bulletin. After this modification is accomplished, no further action is required by this AD. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspections, replacement, and installations shall be done in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. 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 SAAB Aircraft AB, SAAB Aircraft Product Support, S-581.88, Link ping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on January 27, 1997.
83-26-01: 83-26-01 BRITISH AEROSPACE: Amendment 39-4785. Applies to Model HS 748 airplanes, certificated in all categories, for the series listed in the service bulletins below. To prevent the development of unsafe conditions, the following three actions are required, unless previously accomplished: A. To prevent progression of cracks in the main landing gear inboard pivot brackets, part numbers 15F11365 and 16F11365, inspect the inboard pivot brackets for corrosion, loose bolts, and cracks, and repair if necessary in accordance with the Accomplishment Instructions of British Aerospace HS 748 Service Bulletin 57/59, dated October 1979, prior to accumulating 25,000 landings or within the next 750 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not exceeding 1,500 landings from the last inspection. If inboard pivot brackets are corroded to a depth greater than 0.060 inch, the operators of the aircraft must contact the manufacturer for repair instructions. B. To detect cracks in the joints between the tailplane center torsion box and outer tailplanes, inspect and repair, if necessary, the tailplane front and rear spar joint plates and webs in accordance with the Accomplishment Instructions of British Aerospace Aircraft Group HS 748 Service Bulletin 55/19, Revision 1, dated September 1982, prior to the accumulation of 18,000 hours time in service or within the next 750 hours time in service after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 hours time in service. C. Modify the aileron control quadrant assemblies on airplanes equipped with aileron control quadrant assemblies part numbers 1R4583 and 2R4583 in accordance with paragraph 2.B of British Aerospace Aircraft Group HS 748 Service Bulletin 27/75 dated April 4, 1978, prior to the accumulation of 12,000 hours time in service or within the next 750 hours time in service after the effective date ofthis AD, whichever occurs later. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, 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 inspections and/or modifications required by this AD. This amendment becomes effective January 30, 1984.
2019-19-16: The FAA is superseding Airworthiness Directive (AD) 2019-05- 09, which applied to certain Airbus SAS Model A320-251N and -271N airplanes, and Model A321-253N airplanes. AD 2019-05-09 required repetitive detailed inspections of certain electrical harnesses for discrepancies, and corrective actions if necessary. AD 2019-05-09 also provided an optional terminating modification for the repetitive detailed inspections. This AD retains the actions of AD 2019-05-09, and adds a requirement for a terminating modification for the repetitive detailed inspections, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of low clearance between the electrical harness and nearby hydraulic pipes in the inboard trailing edge of the wing. The FAA is issuing this AD to address the unsafe condition on these products.
86-26-04: 86-26-04 CESSNA: Amendment 39-5503. Applies to the following airplanes certificated in any category: MODELS SERIAL NUMBERS 120, 140 All 140A All 150 17001 thru 17,999; 59001 thru 59018 150A, 150B, 150C, 150D 150E, 150F, 150G, 150H 150J, 150K, 150L 15059019 thru 15072003 F150F, F150G, F150H F150-0001 thru F150-0529 F150K F15000530 thru F15000658 170, 170A, 170B All 172, 172A 28,000 thru 29,999 36,000 thru 36,999 46,001 thru 47,746 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K 17247747 thru 17259223 F172D, Fl72E, F172F, F172G F172-0001 thru Fl72-0654 F172H F17200655 thru F17200754 FR172E, FR172F, FR172G FR1720000l thru FR17200225 P172D All 175, 175A, 175B, 175C All 177, 177A, 177B 17700001 thru 17701530 180, 180A 30000 thru 32999 180A, 180B, 180C, 50,000 thru 50911 180D, 180E, 180F, 180G, 180H 18050912 thru 18052175 182, 182A, 182B, 33,000 thru 34999 182C 51,001 thru 53,007 182D, 182E, 182F 182G, 182H, 182J 182K, 182L, 182M, 182N 18253008 thru 18260445 185, 185A, 185B, 185C 185D, 185E, A185E 185-0001 thru 185-1599 A185E 18501600 thru 18501832 190, 195, 195A, 195B All 205, 205A All 206 All U206, U206A, U206B, U206C, U206D, TU206A, TU206B, TU206C, TU206D 206-0276 thru 206-1444 U206E, TU206E 20601445 thru 20601587 P206, P206A, P206B, P206C, P206D, TP206A, TP206B, TP206C, TP206D P206-0001 thru P206-0603 P206E, TP206E P20600604 thru P20600647 207, T207 2070001 thru 20700190 210 57001 thru 57575 210A, 210B, 210C, 210D 210E, 210F, 210G, 210H, 210J, 210K, T210K 21057576 thru 21059351 T210G, T210H, T210J All 336 All 337, 337A, 337B, 337C 337D, 337E, T337B, T337C, T337, T337E 33700001 thru 33701316 Compliance: Required within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To prevent slippage of the pilot/co-pilot shoulder harnesses, accomplish the following on airplanes which have had the shoulder harnesses installed by any of the following Cessna Accessory Kits (AK): AK140-10 AK182-75 AK210-172 AK150-7 AK195-10 AK210-173 AK150-121 AK210-77 AK210-174 AK170-10 AK210-93 AK336-32 AK177-10 AK210-171 AK336-36 AK336-103 (a) Inspect the upper shoulder harness adjuster in accordance with Cessna Single Engine Service Bulletin, SEB86-8 or Cessna Multi-Engine Service Bulletin, MEB86-22, as appropriate, for the presence of a retainer spring. If installed, prior to further flight, remove the spring and stamp out the -401 identification number in accordance with the service bulletin instructions. NOTE: There are two adjusters in each shoulder harness assembly. This AD applies only to the upper adjuster. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) The holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him may conduct the inspections and modifications required by this AD on any airplane not used in air carrier service. The person accomplishing this AD must make the appropriate maintenance record entry as prescribed by FAR 91.173. (d) Any equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Cessna Aircraft Company, Customer Service, P.O. Box 1521, Wichita, Kansas 67201; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective January 6, 1987.
83-07-11: 83-07-11 WYTWORNIA SPRZETU KOMUNIKACYJNEGO, PZL MIELEC: Amendment 39-4614. Applies to Model PZL M18 (all Serial Numbers up through and including 1Z009-30) airplanes certificated in any category. Compliance: Required within the next 100 landings, unless already accomplished. To prevent brake failure which could result in an accident during landing or rollout, accomplish the following: a) Remove the left and right braking levers Part Number (P/N) D52.310.00.1 or D52.310.00.2 from the airplane and modify them in accordance with Wytwornia Sprzetu Komunikacyjnego Bulletin U/044/82, Sections III(1) through (5). b) Install the modified levers on the airplane with the new bolt P/N D52.300.03.2 and check for proper operation in accordance with Bulletin U/044/82, Sections III(6) and (7). c) Record compliance with this Airworthiness Directive (AD) in the aircraft maintenance log book. d) Operators who do not keep records of landings must substitute airplane hours time-in-service at the rate of 2 landings per hour time-in-service. e) Airplanes may be flown in accordance with FAR 21.197 to a location where this Airworthiness Directive (AD) can be accomplished. f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 14, 1983.