Results
2002-08-04: This amendment adopts a new airworthiness directive (AD) that applies to certain PIAGGIO AERO INDUSTRIES S.p.A. (PIAGGIO) Model P-180 airplanes. This AD requires you to replace the four defective horizontal stabilizer hinge bushings with replacement bushings. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to replace defective bushings before they cause failure of the horizontal stabilizer. Such failure could lead to reduced or loss of control of the aircraft.
2025-10-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -252N, -253N, -271N, -272N, -251NX, -252NX, -253NX, -271NX, and -272NX airplanes. This AD was prompted by the identification of an erroneous value of the main landing gear (MLG) tire width in the aircraft data files used for aircraft performance computation. This AD requires revising the existing airplane flight manual (AFM) to incorporate a complementary performance data file (CPDF) update 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.
2023-07-07: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440), CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL- 600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports from the supplier that sensing elements of the bleed air leak detection system were manufactured with insufficient salt fill, which can result in an inability to detect hot bleed air leaks. This AD requires testing of all affected overheat detection sensing elements of the bleed air leak detection system, and replacement if necessary. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
78-23-01: 78-23-01 PIPER AIRCRAFT CORPORATION: Amendment 39-3330. Applies to Models PA-28-235, PA-32-260, PA-32-300, PA-32S-300, PA-32R-300, PA-32RT-300 and PA- 32RT-300T airplanes, certificated in all categories. Compliance is required as indicated. To prevent inadvertent fuel drain lever actuation, accomplish the following: (a) On Model PA-28-235 serial numbers 28-10003 through 28-10660, accomplish the following: (1) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, remove the fuel drain lever cover assembly Piper Part Number 65196-05, -06, or -07. (2) Remove snap studs from spar box if installed. (3) Using existing stud holes in spar box, install new drain cover assembly, Piper Kit 763 883V. (4) Actuate fuel drain valve handle and insure adequate clearance between the handle and cover assembly. (5) Make appropriate maintenance record entry. (b) On Models PA-28-235, PA-32-260, PA-32-300, PA-32S-300, PA-32R-300, PA-32RT-300, and PA-32RT-300T, all serial numbers, accomplish the following: (1) For airplanes with 300 hours or more time in service, within the next 50 hours time in service from the effective date of this AD, and at intervals not to exceed 100 hours time in service from the last check, check the fuel drain lever cover assembly door to determine whether the door freely opens and closes freely without manual assistance and prevents actuation of the lever when the door is in the closed position. (2) If the door does not open and close freely or if the door does not prevent access to the lever when it is in the closed position, replace the fuel drain lever cover assembly with a serviceable assembly, and make the appropriate maintenance record entry. (3) If the door opens and closes freely and prevents access to the lever when it is in the closed position, make the appropriate maintenance record entry. (c) An alternate method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. The checks in this AD may be accomplished by the pilot and appropriate maintenance record entries made in accordance with FAR 91.173. Replacement must be accomplished by a person authorized by FAR 43.3. (Piper Service Letter 856 dated September 15, 1978, pertains to paragraph (a).) This amendment becomes effective November 3, 1978.
2023-07-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of broken lower attachment studs on the AFT galley complex. This AD requires repetitive detailed inspections of the lower attachment studs and, depending on findings, replacement of the lower attachment studs, 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.
2002-08-07: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767-200, -300, and -300F series airplanes. This AD requires examination of maintenance records to determine if Titanine JC5A (also known as Desoto 823E508) corrosion inhibiting compound ("C.I.C.") was ever used; inspection for cracks or corrosion and corrective action, if applicable; repetitive inspections and C.I.C. applications; and modification of the aft trunnion area of the outer cylinder, which terminates the need for the repetitive inspections and C.I.C. applications. This action is necessary to prevent severe corrosion in the main landing gear (MLG) outer cylinder at the aft trunnion, which could develop into stress corrosion cracking and consequent collapse of the MLG. This action is intended to address the identified unsafe condition. The FAA is also planning to issue additional rulemaking to exclude the use of Titanine JC5A for compliance with previously issued ADs.
2020-22-02: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80C2A5F, -80C2B1F, -80C2B2F, - 80C2B4F, -80C2B5F, -80C2B6F, -80C2B6FA, -80C2B7F, -80C2B8F, -80C2D1F, - 80C2K1F, -80C2L1F, -80E1A2, -80E1A3, -80E1A4, and -80E1A4/B model turbofan engines with a certain hydromechanical unit (HMU) installed. This AD was prompted by a report of fuel coking of the HMU fuel metering valve (FMV) electro-hydraulic servo valves (EHSV) resulting in tailpipe fire. This AD requires removal of the HMU and its replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
78-12-07: 78-12-07 PIPER: Amendment 39-3235. Applies to Piper Aircraft PA-30 and PA-39 with Serial Numbers 30-1 through 30-2000 and 39-1 through 39-155 which have had a right fuel selector valve P/N 492137 (Airborne P/N 1H7-8) changed since April, 1977, with a valve containing the designation "4C" in the valve serial number. Compliance required before further flight unless already accomplished. 1. Replace any right fuel selector valve, Piper P/N 492137 (Airborne P/N 1H7-8) containing the designation "4C" in the valve serial number with a serviceable valve without the "4C" designation. 2. The replacement fuel selector valve shall be installed and adjusted in accordance with PA-30/39 Service Manual. (Piper Service Bulletin No. 597 dated April 19, 1978, pertains to this subject.) This amendment is effective June 19, 1978.
77-24-01: 77-24-01 PIPER: Amendment 39-3083 as amended by Amendment 39-3182. Applies to the following models: PA-31 and PA-31-325, Serial Nos. 31-465, 31-7712057 thru 31-7712078, 31-7712081 and 31-7712083; PA-31-350 Serial Nos. 31-7752099, 31-7752101, 31-7752103, 31- 7752105 thru 31-7752114, 31-7752117 thru 31-7752131 and 31-7752134 thru 31-7752138, certificated in all categories. To prevent possible hazards in flight associated with missing horizontal stabilizer and fin skin to stiffener rivet attachments, accomplish the following within the next fifty hours in service from the effective date of this AD unless previously accomplished: (a) Inspect and, if required, repair the horizontal stabilizer and fin skin to stiffener rivet attachments in accordance with the "Instructions" section of Piper Service Bulletin No. 575 or equivalent procedures which must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Upon submission of substantiatingdata through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. The affected airplanes may be flown in accordance with FAR 21.197 to a location where the AD compliance procedures can be accomplished. Amendment 39-3083 was effective November 24, 1977. This amendment 39-3182 is effective April 17, 1978.
2002-08-02: This amendment supersedes Airworthiness Directive (AD) 2001-20-14, which currently requires you to replace the brake shuttle valves with parts of improved design and install a shield over the hydraulic lines on certain Fairchild Aircraft SA226 and SA227 series airplanes. AD 2001-20-14 also requires you to replace the rubber fuel hose with a metal device for certain SA226 series airplanes. This AD is the result of FAA incorrectly referencing Model SA226-T(A) airplanes and inadvertently omitting certain serial numbers of Model SA227-AC airplanes from the applicability of AD 2001-20-14. This AD retains the actions of AD 2001-20-14, corrects the reference of Model SA226-T(A) airplanes and adds additional Model SA227-AC airplanes to the applicability section of the AD. The actions specified by this AD are intended to correct potential brake shuttle valve problems, which could cause the brake assembly to drag and overheat. Hydraulic or fuel line damage could then occur if the overheated brake assembly is retracted into the main wheel well with a consequent fire if the hydraulic or fuel lines ruptured.
2023-06-14: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corporation (P&WC) PW308A and PW308C model turbofan engines. This AD is prompted by a manufacturer's design review, which identified that the combustion chamber outer case (CCOC) to rear compressor case (RCC) flange bolt low cycle fatigue life was inadequate and that those flange bolts may develop cracks resulting in flange bolt fracture. This AD requires replacing all CCOC flange bolts and modifying the CCOC and inner bypass ducts. This AD also prohibits installation of certain flange bolts on any affected engine, as specified in a Transport Canada AD, which is proposed for incorporation by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2009-18-03 R1: We are revising an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC-6 aircraft have been reported in the past. It is possible that the spherical bearing of the wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could cause failure of the upper attachment fitting, leading to failure of the wing structure and subsequent loss of control of the aircraft. To address this problem, FOCA published AD TM-L Nr. 80.627-6/ Index 72-2 andHB-2006-400 and EASA published AD 2007-0114 to require specific inspections and to obtain a fleet status. Since the issuance of AD 2007-0114, the reported data proved that it was necessary to establish and require repetitive inspections. EASA published Emergency AD 2007-0241-E to extend the applicability and to require repetitive eddy current and visual inspections of the upper wing strut fitting for evidence of cracks, wear and/or corrosion and examination of the spherical bearing and replacement of cracked fittings. Collected data received in response to Emergency AD 2007-0241-E resulted in the issuance of EASA AD 2007-0241R1 that permitted extending the intervals for the repetitive eddy current and visual inspections from 100 Flight Hours (FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, respectively. In addition, oversize bolts were introduced by Pilatus PC-6 Service Bulletin (SB) 57-005 R1 and the fitting replacement procedure was adjusted accordingly. Based onfatigue test results, EASA AD 2007-0241R2 was issued to extend the repetitive inspection interval to 1100 FH or 12 calendar months, whichever occurs first, and to delete the related flight cycle intervals and the requirement for the "Mild Corrosion Severity Zone''. In addition, some editorial changes have been made for reasons of standardization and readability. Revision 3 of this AD referred to the latest revision of the PC- 6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have included the same repetitive inspection intervals and procedures already mandated in the revision 2 of AD 2007-0241. Besides the inspections, in the latest revision of the PC-6 AMM, the replacement procedures for the fittings were included. Additionally, EASA AD 2007-0241R3 introduced the possibility to replace the wing strut fitting with a new designed wing strut fitting. With this optional part replacement, in the repetitive inspection procedure the 1100 FH interval is deleted so thatonly calendar defined intervals of inspections remained applicable. We are issuing this AD to require actions to correct the unsafe condition on these products.
77-23-03: 77-23-03 PIPER AIRCRAFT CORPORATION: Amendment 39-3071. Applies to Model PA-28-140 serial numbers 28-25001 through 28-7725172; Model PA-28-151 serial numbers 28-7415001 through 28-7615435; Model PA-28-161 serial numbers 28-7716001 through 28-7716071; Model PA-28-180 serial numbers 28-5153 through 28-7505260; Model PA-28-181 serial numbers 28-7690001 through 28-7790363; Model PA-28-235 serial numbers 28-7310001 through 28-7710016; Model PA-28R-180 serial numbers 28R-30737 through 28R-7130013; Model PA-28R-200 serial numbers 28R-35001 through 28R-7635512; Model PA-28R-201 serial numbers 28R-7737001 through 28R-7737023; Model PA-28R-201T serial numbers 28R-7703001 through 28R-7703043; Model PA-32-260 serial numbers 32-1111 through 32-7700013; Model PA-32-300 serial numbers 32-40566 through 32-7740040; Model PA-32R-300 serial numbers 32R-6780001 through 32R-7780215; Model PA-34-200 serial numbers 34-7250001 through 34-7450220; and Model PA-34-200T serial numbers 34-7570001 through 34-7770163, airplanes certificated in all categories. \n\n\tTo prevent a power loss due to thermal contraction binding a control rod end, accomplish the following: \n\n\t(a)\tWithin the next 25 hours time in service after the effective date of this A.D., unless already accomplished, perform the following check: \n\n\t\t(1)\tGain access to the engine by opening or removing the cowling as required to check the engine control rod end bearings in the engine compartment. \n\n\t\t(2)\tCheck the rod end bearings attached to the Mixture, Throttle, and Prop Governor (if applicable) Control Cables. (Refer to the picture below.) \n\n\t\t\t(i)\tIf a rod end bearing, as identified in the figure below as number two (2) (Brass Ball Retainer) or as number three (3) (Silver Ball Retainer) is installed, then no further action is required. Make appropriate log book entry. \n\n\t\t\t(ii)\tIf a rod end bearing, as identified in the figure below as number one (1) with a raised ball retainer is installed, have it removed andreplaced with an approved serviceable bearing which is identified in the figure below as number two (2) or number three (3). Refer to the appropriate Piper Service Manual for replacement and rigging instructions. \n\n\t(b)\tAn alternate method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. \n\n\tThe checks in this A.D. may be accomplished by the pilot and appropriate log book entries made in accordance with FAR 91.173. Replacement and rigging must be accomplished by a person authorized by FAR 43.3. \n\n\tThis amendment becomes effective November 14, 1977.
2002-08-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model DHC-8-400, -401, and -402 series airplanes. This action requires revising the Airplane Flight Manual to advise the flight crew of appropriate procedures to follow in the event that a main landing gear (MLG) fails to extend following a gear-down selection. This action also requires replacement of the left and right MLG uplock assemblies with new assemblies; and an inspection of the left and right MLG uplock rollers for the presence of an inner low friction liner, and corrective actions if necessary. This action is necessary to ensure that the flight crew has the procedures necessary to address failure of an MLG to extend following a gear-down selection; and to detect and correct such failure, which could result in a gear-up landing and possible injury to passengers and crew.
2023-07-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by a determination that during certain modes, the flight guidance/autopilot does not account for engine failure while capturing an altitude. This AD requires revising the existing airplane flight manual (AFM) to add new limitations and procedures. The FAA is issuing this AD to address the unsafe condition on these products.
2023-06-15: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of missing shims, a wrong type of shim, shanked fasteners, fastener head gaps, and incorrect hole sizes common to the left and right sides at a certain station (STA) frame inner chord and web. This AD requires inspecting for existing repairs, inspecting the area for cracking, and performing applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2002-06-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-06-52, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 407 helicopters by individual letters. This AD requires a one-time replacement of certain bearings and, before further flight, adding a limitation and caution to the rotorcraft flight manual (RFM) and at specified intervals, inspecting, replacing, and lubricating certain oil cooler blower bearings. This AD is prompted by several occurrences of failure of an oil cooler blower bearing. The actions specified by this AD are intended to prevent failure of an oil cooler blower bearing, loss of tail rotor drive, and a subsequent forced landing.
2002-08-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes equipped with Skidmore-Wilheim Manufacturing Co. (Skidmore-Wilheim) (formerly Hydromotive) Model V1-15-1000 brake master cylinders. This AD requires you to replace these brake master cylinders with new or overhauled units of the same design. This AD is the result of reports of dragging brakes during taxi operations. The actions specified by this AD are intended to correct and prevent future malfunctioning brake master cylinders. Malfunctioning brake master cylinders could cause dragging brakes, which can result in overheated brakes and a wheelwell fire if the dragging takes place during takeoff and the gear is later retracted.
78-02-03: 78-02-03 PIPER: Amendment 39-3128. Applies to PA-23-250 airplanes with Serial Nos. as shown below certificated in all categories. To prevent possible hazards in flight associated with weakening of the stabilator, accomplish the following unless previously accomplished: (a) The following Serial Nos. pertain to S.B. 540 dated January 4, 1977: (1) Serial Nos. 27-7654001 thru 27-7754057 Within the next 10 hours in service after the effective date of this AD, inspect both stabilator tip tube and weight assemblies for cracks in accordance with the inspection procedures of 1. and 2. under "Instructions" on the sketch/instructions page of S.B. 540, or equivalent procedures. (i) If cracks are present alter both tube and weight assemblies as indicated in 2. under "Instructions" on the first page of S.B. 540 or equivalent procedures, prior to further flight. (ii) If cracks are not present alter both tube and weight assemblies within the next 100 hours in service as indicated in 4. under "Instructions" on the first page S.B. 540, or by equivalent procedures. (iii) For altered parts, the inspection procedures of (a)(1) must be repeated within the next 100 hours in service and thereafter at intervals not to exceed 100 hours in service from the last inspection. If cracks are present replace all cracked parts with new or equivalent parts before further flight. (2) Serial Nos. 27-7754058 and up Within the next 100 hours in service after the effective date of this AD and every 100 hours thereafter, inspect both stabilator tip tube and weight assemblies for cracks in accordance with inspection procedures of 1. and 2. under "Instructions" on the sketch/instructions page S.B. 540 or equivalent procedures. If cracks are present replace all cracked parts with new or equivalent parts before further flight. (b) The following Serial Nos. pertain to Service Bulletin 547 dated March 1, 1977: (1) Serial Nos. 27-7654001 thru 27-7754054 Within the next 50 hours in service after the effective date of this AD, inspect both stabilator tip ribs for missing rivets and missing tube and weight assembly attachment screws and if necessary alter in accordance with S.B. 547 or equivalent procedures. (c) The following Serial Nos. pertain to Service Bulletin 569 dated August 24, 1977: (1) Serial Nos. 27-7654001 thru 27-7754127, 27-7754130, 27-7754131, 27-7754133 thru 27-7754136, 27-7754138 thru 27-7754144 To prevent abnormal stabilator tab horn bushing wear, within the next 50 hours in service after the effective date of this AD replace the right and left stabilator tab forward inboard rib/horn assemblies in installing Piper Kit 761 143 or equivalent Kit. (d) The following Serial Nos. pertain to Service Letter 807A dated September 8, 1977: (1) Serial Nos. 27-7654001 thru 27-7754041 equipped with stabilators Piper Part Number 15658-2, 15658-3, 15658-22 or 15658-23. Within thenext 50 hours in service after the effective date of this AD, reinforce the mounting of the stabilator tube and weight assemblies by installing additional nose- ribs by means of Piper Kit 761 141 or equivalent Kit. (e) Refer to paragraph 4-65 in the Piper PA-23-250 "Aztec" Service Manual and balance the stabilator when the alterations in paragraphs (a), (c) or (d) of this AD are incorporated. (f) Upon submission of substantiating data through an FAA Maintenance Inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (g) The affected airplanes may be flown in accordance with FAR 21.197 to a location where the AD compliance procedures can be accomplished. (h) Equivalent procedures and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective January 26, 1978.
2023-07-02: The FAA is superseding Airworthiness Directive (AD) 2022-03- 12, which applied to all Airbus SAS Model A330-200, -300, -800, and - 900 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. AD 2022-03-12 required replacing the doghouse door lock placard with an improved instruction placard. This AD was prompted by reports that the instructions on the doghouse door lock placard are unclear and incomplete, and by a determination that additional parts need to be modified. This AD continues to require the actions in AD 2022-03-12 and expands the list of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2025-10-07: The FAA is superseding Airworthiness Directive (AD) 2015-02- 14, which applied to all Airbus SAS Model A318 series airplanes; A319- 111, -112, -113, -114, -115, -131, -132, and -133 airplanes; A320-211, -212, -214, -231, -232, and -233 airplanes; and A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. AD 2015-02-14 required repetitive inspections for cracking, damage, correct installation, and correct adjustment of the main landing gear (MLG) door hinge and actuator fittings on the keel beam, corrective actions if necessary, and revision of the existing maintenance or inspection program, as applicable. Since the FAA issued AD 2015-02-14, a new design of the MLG door keel beam hinge and actuator fitting was developed. This AD continues to require the actions specified in AD 2015-02-14, adds an optional terminating action, and revises the applicability, 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.
77-14-14: 77-14-14 PIPER: Amendment 39-2965. Applies to Piper Models PA-31 and PA-31-325, Serial Nos. 31-7612064 through 31-7612110, 31-7712001 through 31-7712012, 31-7712014, 31- 7712015, 31-7712017, 31-7712018, 31-7712020 through 31-7712023 and 31-7712025 through 31-7712027; PA-31-350 Serial Nos. 31-7652104 through 31-7652120, 31-7652122, 31-7652124, 31-7652125, 31-7652127, 31-7652129, 31-7652130, 31-7652132 through 31-7652135, 31-7652137, 31-7652139, 31-7652141, 31-7652142, 31-7652145, 31-7652147, 31-7652148, 31- 7652150, 31-7652151, 31-7652153, 31-7652154, 31-7652156, 31-7652157, 31-7652159, 31-7652162 through 31-7652177, 31-7752001, 31-7752002, 31-7752004 through 31-7752006, 31-7752008, 31-7752009, 31-7752011, 31-7752012, 31-7752015, 31-7752019 through 31-7752022, 31-7752027 through 31-7752036, 31-7752038, 31-7752040, 31-7752042, and 31-7752047 through 31-7752049, certificated in all categories. To prevent possible hazards associated with a defective channel, part number 40358-5,installed in the right wing front spar accomplish the following: (a) Before further flight, inspect the right wing lower surface from the front spar fuselage attachment diagonally aft to the area of the wheel well for indications of lower wing skin deformation and loose or missing rivets. (b) Should any of the above-described conditions exist, the aircraft shall not be flown until the damage is assessed and repairs are effected. (c) If there is no visible damage, (1) on model PA-31-350 install in full view of the pilot a placard that reduces the maximum landing weight to 6650 lb. and visually check area described in paragraph (a) above after each 20 landings; (2) on models PA-31 and PA-31-325, visually check area described in paragraph (a) above after each 20 landings. If there is evidence of damage from the visual check, comply with paragraph (b). (d) Within the next 50 hours in service after the effective date of this AD unless previously accomplished, alter theinboard end of the right front wing spar in accordance with Piper Kit No. 761 137, Right Wing Front Spar Reinforcement. (e) Upon incorporating paragraph (d) or equivalent alteration the weight restriction and visual check requirement in paragraph (c) may be dispensed with. (f) Repairs and equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (g) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the compliance time specified in paragraph (d). Piper Service Bulletin 554 dated March 7, 1977, pertains to this subject. This amendment becomes effective on July 19, 1977.
2002-07-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires repetitive inspections to find cracking of the lower skin at the lower row of fasteners in the lap joints of the fuselage, and repair of any cracking found. That amendment also requires modification of the fuselage lap joints at certain locations, which constitutes terminating action for repetitive inspections of the modified areas. This amendment adds repetitive inspections and requires replacement of the current preventive modification with an improved modification. This amendment is prompted by the FAA's determination that, in light of additional crack findings, certain modifications of the fuselage lap joints do not provide an adequate level of safety. The actions specified by this AD are intended to find and fix cracking of the fuselage lap joints, which could result in sudden decompression of the airplane.
77-12-01: 77-12-01 PIPER AIRCRAFT CORPORATION: Amendment 39-2914. Applies to Models PA-28-235, PA-32-260, PA-32-300, PA-32S-300 airplanes certificated in all categories. Models and serial numbers of airplanes affected are noted in sections (a), (b), (c), (d), and (e) in the body of the A.D. \n\n\tTo prevent a fuel system malfunction and a possible power interruption, accomplish the following: \n\n\t(a)\tOn Model PA-28-235 serial numbers 28-10001 through 28-7410093; Model PA- 32-260 serial numbers 32-03, 32-04, 32-1 through 32-7400049; Model PA-32-300 serial numbers 32-15, 32-21, 32-40000 through 32-7440160, and Model PA-32S-300 serial numbers 32S-15, 32S-40000 through 32S-7240137, airplanes equipped with an Airborne Model 1H10, 1H16-1, 1H26-2, 1H26-3 or 1H26-4 model fuel selector valves, within the next five hours time in service after the effective date of this A.D. and thereafter before the first flight of each day until (b), (c), (d) and (e) are accomplished and thereafter at intervals notto exceed 50 hours time in service from the last check perform the following check: \n\n\t\t(1)\tInsure that there is fuel in each tank. Drain fuel tank sumps and fuel selector sump using normal preflight procedures. \n\n\t\t(2)\tPlace the fuel selector valve in the "OFF" detent position. \n\n\t\t(3)\tActuate the fuel selector valve drain lever for one minute, collect contents and discard. \n\n\t\tNOTE: Several attempts may be required to drain all fuel from sump bowl. A leaking fuel selector valve is indicated by continued draining, when the fuel selector is in the "OFF" position. The volume of this drainage depends on the size of the "leak." \n\n\t\t(4)\tClose drain valve and wait three minutes. Drain fuel selector again for one minute, collecting contents in a container. Close drain valve. \n\n\t\t(5)\tIf fuel collected exceeds one-half fluid ounce (one tablespoon), repeat Item (4) above. \n\n\t\t(6)\tIf the repeated drain procedure produces one-half fluid ounce or more, an excessive internal leaking fuel valve is indicated and (i) or (ii) must be accomplished. \n\n\t\t\t(i)\tRemove, clean and reinstall the fuel selector valve, and repeat steps (1) through (5). \n\n\t\t\t(ii)\tReplace the fuel selector valve with the applicable Piper fuel valve kit 757 148V or 760 895V. \n\n\tParagraph (a) does not apply to those airplanes that have installed Piper fuel valve Kit 757 148V or fuel valve kit 760 895V. \n\n\t(b)\tOn Model PA-28-235 serial numbers 28-10001 through 28-11236; Model PA- 32-260 serial numbers 32-03, 32-04, 32-1 through 32-1123; Model PA-32-300 serial numbers 32-15, 32-21, 32-40000 through 32-40629, and Model PA-32S-300 serial numbers 32S-15, 32S-40000 through 32S-40629, airplanes, within the next 100 hours time in service after the effective date of this A.D., perform the following: \n\n\t\t(1)\tCheck to determine whether the main and tip fuel tank fill caps are Piper Part Number 66817-00. Fuel tank fill cap, Piper Part Number 66817-00, contains a circular red rubber seal in thecenter of the underside of the cap. \n\n\t\t(2)\tIf any fuel tank fill cap is not Piper Part Number 66817-00, remove and replace it with Piper Part Number 66817-00. \n\n\t(c)\tOn Model PA-28-235 serial numbers 28-10001 through 28-7310125; Model PA- 32-260 serial numbers 32-03, 32-04, 32-1 through 32-7300036; Model PA-32-300 serial numbers 32- 15, 32-21, 32-40000 through 32-7340081, and Model PA-32S-300 serial numbers 32S-15, 32S- 40000 through 32S-7240110, airplanes, within the next 50 hours time in service after the effective date of this A.D., unless already accomplished, modify the fuel selector control system in accordance with Piper Service Bulletin 376 dated April 19, 1973. \n\n\t(d)\tOn Models PA-28-235 serial numbers 28-10001 through 28-7710040; Model PA-32-260 serial numbers 32-03, 32-04, 32-1 through 32-7700016; Model PA-32-300 serial numbers 32-15, 32-21, 32-40000 through 32-7740037, 32-7740039 through 32-7740053, 32- 7740055 through 32-7740062, 32-7740064 through 32-7740069; and Model PA-32S-300 serial numbers 32S-15, 32S-40000 through 32S-7240137 airplanes, within the next 50 hours time in service after the effective date of this A.D., perform the following modification and/or inspections to the main and wing tip fuel tank vent tubes: \n\n\t\t(1)\tUnless already accomplished, rework fuel tip tank vent to the dimensions shown on the sketch below: \n\n\n\n\nTIP TANK VENT TUBE \n\n\t\tNOTE: Some tip tanks were not equipped with protruding external vents, and (d)(1) of the A.D. does not apply to those tanks. \n\n\t\t(2)\tUnless already accomplished, install the new main fuel tank vent assembly contained in Piper Kit No. 760 560V. \n\n\t\t\t(i)\tRemove all screws from each main fuel tank and slide tank forward approximately six (6) inches. Remove present vent assembly. \n\n\t\t\t(ii)\tInstall the new vent assembly contained in Piper Kit. No. 760 560V. \n\n\t\t\t(iii)\tReplace each tank in its proper position, and secure in place with the screws removed in (i). \n\n\t\t(3)\tInspect bothwing tip fuel tank vent tubes scarf angle and alignment to the lower wing surface. \n\n\t\t(4)\tIf the tip tank vent tube scarf angle is not between 60 degrees and 65 degrees, or if the vent tube is not perpendicular (90 degrees) plus or minus 2 degrees, rework it to those dimensions. \n\n\t\t(5)\tInspect both main fuel tank vent tubes scarf angle and alignment to the lower wing surface. \n\n\t\t(6)\tIf the vent tube scarf angle is not 40 degrees plus or minus 2 degrees, or if the vent tube is not perpendicular (90 degrees) plus or minus 2 degrees, rework it to those dimensions. \n\n\t(e)\tOn Models PA-28-235 serial numbers 28-10001 through 28-7710040; Model PA-32-260 serial numbers 32-03, 32-04, 32-1 through 32-7700016; Model PA-32-300 serial numbers 32-15, 32-21, 32-40000 through 32-7740037, 32-7740039 through 32-7740053, 32- 7740055 through 32-7740062, 32-7740064 through 32-7740069; and Model PA-32S-300 serial numbers 32S-15, 32S-40000 through 32S-2740137 airplanes, within the next 50 hours time in service after the effective date of this A.D., inspect the two fuel hose assemblies, Piper Part Number 63901-15 or 63901-48 at each main fuel tank for proper installation as follows: \n\n\t\t(1)\tDisconnect both main landing gear strut fairings from the wings. \n\n\t\t(2)\tRemove both main landing gear access covers. \n\n\t\t(3)\tVisually inspect both fuel hose assemblies, Piper Part Number 63901-15 or 63901-48 as applicable. \n\n\t\t\t(i)\tIf the hose assembly is twisted, loosen the inboard end fitting and allow the hose to return to its natural untwisted state. \n\n\t\t\t(ii)\tIf the hose assembly does not return to its natural state with slight hand pressure, replace it with a serviceable hose assembly, Piper Part Number 63901-15 or 63901-48 as applicable. \n\n\t\t(4)\tReconnect the inboard end fittings, making sure the hose is not twisted, and reinstall the main landing gear access covers and strut fairings. \n\n\t(f)\tAlternate method of compliance must be approved by the Chief, Engineering andManufacturing Branch, Federal Aviation Administration, Southern Region. \n\n\tThe checks in this A.D. may be accomplished by the pilot and appropriate log book entries made in accordance with FAR 91.173. \n\n\tPiper Service Bulletins 342, 376 and 571 pertain to this subject. \n\n\tThis amendment becomes effective June 10, 1977.
2005-17-04: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas airplanes. This AD requires a general visual inspection for damage to the Firex discharge pipes and wye assembly of the fire extinguishing system of the number 2 engine; and corrective and other specified actions, as applicable. This AD results from reports of freezing damage to the Firex discharge pipes and wye assembly of the number 2 engine, and one report of a level 1 ENG FIRE AGENT LO alert during flight. We are issuing this AD to prevent accumulation of water in the discharge pipes and possible consequent freezing damage to the discharge pipes and wye assembly, which could lead to failure of the fire extinguishing system during a fire in the number 2 engine.