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88-03-52: 88-03-52 PRATT & WHITNEY: Amendment 39-5957. Final copy of Telegraphic AD. Applies to Pratt & Whitney (PW) PW2037 and PW2040 turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent compressor and turbine case cooling air valve tube and 2.5 bleed valve actuator tube cracking that can lead to fuel leaks, substantial fuel quantity loss and possible engine fire, accomplish the following: (a) For the engines operated in any of the following configurations: (1) with the Fuel Quantity Indication System (FQIS) inoperative under the provisions specified in the Boeing 757 aircraft Master Minimum Equipment List (MMEL), Item 28-41-1; (2) with one of the Fuel Quantity Processor (FQP) Channels inoperative under the provisions specified in the MMEL, Item 28-41-2; (3) with both Flight Management Computer (FMC) Systems inoperative under the provisions specified in the MMEL, Item 34-61-1; or (4) with the FQIS functional, both FQP Channels functional, and at least one FMC System functional, but operating without the provisions of Boeing Operations Manual Bulletin (OMB) Number 87-7, Revision 1, dated October 28, 1987, accomplish the following prior to further flight: (a)(i) Compressor and turbine case cooling air valve tube clamping configuration: Remove loop clamp bracket assembly Part Number (P/N) 1B2224-01 from compressor and turbine case cooling air valve tubes, and install a clamping configuration that clamps the tubes to a bracket spanning the pressure and return tubes in accordance with Accomplishment Instructions contained in PW Alert Service Bulletin (ASB) Number PW2000 A75-36, dated October 28, 1987. (a)(ii) 2.5 bleed valve actuator tubes and manifold assembly clamping configuration: Install a new bracket and clamp configuration in accordance with the applicable part of the Accomplishment Instructions contained in PW ASB Number PW2000 A75-38, dated December 21, 1987. (b) For engines operated with the FQIS functional, both FQP Channels functional, at least one FMC System functional, and in accordance with the provisions of Boeing OMB Number 87-7, Revision 1, dated October 28, 1987, accomplish items (a)(i) and (a)(ii) above within 250 hours in service from the effective date of this AD. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. (e) Upon submission of substantiating data by an owner or operator through an FAA airworthiness inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. Pratt & Whitney ASB's NO. PW2000 A75-36, dated October 28, 1987, and NO. PW2000 A75-38, dated December 21, 1987, identified and described in this document 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 the engine manufacturer's ASB's may obtain copies upon request to Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 88-ANE-02, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5957, becomes effective on July 13, 1988, as to all persons except those persons to whom it was made effective 24 hours after receipt by individual Telegraphic AD T88-03-52, issued January 29, 1988, which contained this amendment.
91-07-18: 91-07-18 ING. HEINO BRDITSCHKA FLUGTECHNIK GES.M.B.H (HB AIRCRAFT INDUSTRIES AG): Amendment No. 39-8089. Docket No. 91-CE-32-AD. Applicability: Models HB-23/2400-SP powered gliders (all serial numbers), HB-23/2400 and HB-23/2400 Scanliner and Hobbyliner powered gliders that are equipped with a three-blade adjustable propeller, certificated in any category. Compliance: Required prior to further flight after the effective date of this AD, unless already accomplished. To prevent loss of the propeller while in flight that could result in damage to the powered glider and loss of control, accomplish the following: (a) Replace the three-blade propeller with a fixed-pitch, two-blade propeller in accordance with Ing. HB Instructions 23/2/90, dated December 19, 1990. (b) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe,Africa, Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (c) The inspections and replacements required by this AD shall be done in accordance with Ing. HB Instructions 23/2/90, dated December 19, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. Section 552(a) and 1 CFR Part 51. Copies may be obtained from Ing. Heino Brditschka Flugtechnik Ges.m.b.H. (HB Aircraft Industries AG), Dr. Adolf Scharfstr. 44, 4053 Haid, Austria. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-8089, AD 91-07-18) becomes effective onJanuary 3, 1992, as to all persons except those persons to whom it was made immediately effective by priority letter AD 91-07-18, issued March 29, 1991, which contained this amendment.
74-11-03: 74-11-03 AIRESEARCH: Amendment 39-1848. Applies to model GTCP36-4A, -6, -16, and -28 Auxiliary Power Units (APU) installed on, but not limited to, Grumman Gulfstream 1159, Fokker F-28, NAMC YS-11, and VFW Fokker 614 Aircraft. "Pursuant to the authority of the Federal Aviation Act of 1958, delegated to me by the Administrator (31 F.R. 13697), the following airworthiness directive applicable to all aircraft incorporating AiResearch Model GTCP36-4A, -6, -16, and -28 Auxiliary Power Units (APU), installed in, but not limited to, Grumman Gulfstream 1159, Fokker F-28, NAMC YS-11, and VFW Fokker 614 aircraft, listed in AiResearch Alert Service Bulletins GTCP36-49-A3621, dated March 19, 1974, and GTCP36-49-A3618, dated April 1, 1974, or later FAA-approved revisions, is effective immediately upon receipt of this airmail letter. This AD is required due to a manufacturing error resulting in a certain lot of fuel controls for the APU containing a case casting wall thickness below allowable design limits. As the vessel is a high pressure cavity, failure of the wall would allow H.P. fuel to leak into the APU compartment. Compliance required as indicated, unless already accomplished. Within 25 hours additional time in service of any aircraft on which the APU is installed, visually inspect the APU fuel control body per AiResearch Alert Service Bulletins GTCP36-49-A362l, dated March 19, 1974, or GTCP36-49-A3618, dated April 1, 1974, or later FAA-approved revisions. Prior to the installation of any AiResearch APU models listed herein, in any aircraft, conduct the visual inspection per the applicable Alert Service Bulletins. If, as a result of any of the foregoing inspections, fuel control units are found to have the unacceptable case casting wall thickness, either: (A) Prior to further flight, placard the APU inoperative until replaced with a new or serviceable part. The APU may not be operated until a new or serviceable part is installed. or (B) Replace, prior to further flight, with a new or serviceable part. Mark all fuel control units found to be unacceptable in a conspicuous manner to prevent inadvertent return to service. Return said units to AiResearch for exchange as indicated in the AiResearch Alert Service Bulletins. Re-identify acceptable units per the Alert Service Bulletins. Make appropriate aircraft logbook entries to reflect compliance with this AD. Aircraft may be flown to a base for performance of maintenance required by this AD, per FAR's 21.197 and 21.199, provided that the APU is inoperative for said flight." This amendment is effective May 20, 1974, for all persons except those to whom it was made effective immediately by airmail letter dated April 25, 1974.
90-23-11 R1: 90-23-11 R1 AIRBUS INDUSTRIE: Amendment 39-6802 as corrected by Amendment 39- 6947. Docket No. 89-NM-202-AD. Applicability: Model A300 series airplanes, Serial Numbers 001 through 305, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the ram air turbine to provide hydraulic power in an emergency situation, accomplish the following: A. For ram air turbines on which neither modification No. RM 370 (Dowty Rotol Service Bulletin 29-76) nor modification No. RM 401 (Dowty Rotol Service Bulletin 29-104) has been accomplished; or on which one, but not both, of those modifications has been accomplished: Perform a ground test of the ram air turbines, in accordance with Dowty Rotol Service Bulletin 29- 124, Revision 3, dated March 29, 1989, as follows: 1. Prior to a. or b., below, whichever occurs later: a. 4,000 hours time-in-service or 24 months since new or overhaul, whichever occurs first, orb. 600 hours time-in-service or 6 months after the effective date of this AD, whichever occurs first. 2. Repeat the ground test at intervals not to exceed 600 hours time-in-service or 6 months, whichever occurs first. B. For ram air turbines on which both modification No. RM 370 (Dowty Rotol Service Bulletin 29-76) and modification No. RM 401 (Dowty Rotol Service Bulletin No. 29-104) have been accomplished: Perform a ground test of the ram air turbines, in accordance with Dowty Rotol Service Bulletin 29-124, Revision 3, dated March 29, 1989, as follows: 1. Prior to a. or b., below, whichever occurs later: a. 7,500 hours time-in-service or 30 months since new or overhaul, whichever occurs first, or b. 1,500 hours time-in-service or 6 months after the effective date of this AD, whichever occurs first. 2. Repeat the ground test at intervals not to exceed 3,000 hours time-in- service or 12 months, whichever occurs first. C. If the ram air turbine fails to function properly during the ground tests required by paragraphs A. or B. of this AD, prior to further flight, replace with a serviceable unit, or overhaul the unit, in accordance with Dowty Rotol Overhaul Manual 29-21-14. D. Prior to 1. or 2., below, whichever occurs later, perform an overhaul of the ram air turbine in accordance with Dowty Rotol Overhaul Manual 29-21-14: 1. 20,000 hours time-in-service or 10 years since new or overhauled, whichever occurs first, or 2. 12 months or 3,000 hours time-in-service after the effective date of the AD, whichever occurs first. E. Accomplishment of the modifications described in all three Dowty Rotol Service Bulletins 29-125 R1, 29-76, and 29-104, constitutes terminating action for the requirements of this AD. F. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. G. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 90-23-11 R1 corrects AD 90-23-11, Amendment 39-6802. The effective date of the requirements of AD 90-23-11 R1 remains December 17, 1990, as specified in AD 90-23-11. This amendment (39-6947, AD 90-23-11 R1) is effective on March 22, 1991.
2013-22-03: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by reports indicating that a standard fuel tank access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. This AD requires an inspection of the left- and right-hand wing fuel tank access doors to determine that impact-resistant access doors are installed in the correct locations, and to replace any door with an impact-resistant access door if necessary. This AD also requires an inspection for stencils and index markers on impact-resistant access doors, and application of new stencils or index markers if necessary. This AD also requires revising the maintenance program to incorporate changes to the airworthiness limitations section. We are issuing this AD to prevent foreign object penetration of the fuel tank, which could cause a fuel leak near an ignition source (e.g., hot brakes), consequently leading to a fuel-fed fire.
99-10-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that requires replacement of fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut with new corrosion-resistant pins. This amendment is prompted by reports of cracked fuse pins in the upper link, midspar fittings, and diagonal brace of the nacelle strut due to fatigue and corrosion. The actions specified by this AD are intended to prevent cracking or corrosion of the fuse pins of the nacelle strut, which could result in failure of the fuse pin and strut-to-wing attachment, and consequent loss of the strut and separation of the engine from the airplane.
99-10-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Model Beech 2000 airplanes. This AD requires immediately incorporating temporary revisions to the Limitations Section of the Airplane Flight Manual (AFM) that include requirements of not allowing flap operation during takeoff, accomplishing the preflight visual checks (referred to as visual inspections in the AFM temporary revisions) of the aft cove panel of the wing for delamination prior to each flight, and incorporating a repair scheme if delamination is found. This AD also requires repetitively inspecting the trailing edge of the wing by looking for delamination (debonding) (also referred to as cracks in the service information) through the thickness of the trailing edge of the wing cove skin panels, and modifying the center flap track rib attachment when delamination (debonding) is found. This AD is the result of a report of the wing cove skin panel separating from the wing while in flight on one of the affected airplanes. The actions specified by this AD are intended to detect and correct delamination of the wing cove skin in the area of the support rib, which could result in the delamination propagating to the trailing edge of the wing with the wing cove skin panel possibly separating from the wing. Comments for inclusion in the Rules Docket must be received on or before July 9, 1999.
71-24-10: 71-24-10 BEECH: Amendment 39-1350 as amended by Amendment 39-1693. Applies to the following airplanes: 1) Models Serial Numbers Affected 35-C33, E33, F33 CD-1062 thru CD-1254, except CD- 1237 35-C33A, E33A, F33A CE-118 thru CE-346, except CE-324 E33C, F33C CJ-1 thru CJ-30 V35, V35TC, V35A D-8336 thru D-9285, except V35A-TC, V35B, D-9208, -9279, -9280, -9281, V35B-TC 9282 36, A36 E-1 thru E-275 95-B55, 95-B55A TC-1021 thru TC-1397, except TC- 1395, -1396 95-C55, D55, E55 TE-256 thru TE-845, except TE-836, 837 56TC, A56TC TG-1 thru TG-94 58 TH-1 thru TH-170 except TH-135, - 153, -161 D95A, E95 TD-678 thru TD-721 2) Only applicable if altered in service to incorporate P/N 60-524080 series control wheels which have provisions for a clock and light: Models Serial Numbers Affected 35-C33 CD-814 thru CD-1061 35-C33A CE-1 thru CE-117 V35 D-7977 thru D-8335 95-B55, 95-B55A TC-371 and TC-502 thru TC-1020 95-C55, 95-C55A TC-350 and TE-1 thru TE-255 D95A TD-534 thru TD-677 In order to assure security of control wheels, (1) within 50 hours' time in service after the effective date of this AD, for those airplanes which do not comply with AD 71-12-04, or (2) within 300 hours' time in service after the effective date of this AD, for those airplanes which do comply with AD 71-12-04, unless already accomplished, accomplish the following: Ascertain that two Beech inspection stamps can be seen on one tip of each control wheel adapter. (These tips may be seen while looking toward the forward face of control wheel hubs, without disassembly.) If the stamps cannot be seen on an adapter, replace it with either Beech P/N 96-524029-15 (short) or Beech P/N 96-524029-19 (long) control wheel adapters which have the aforementioned stamps, or in the alternative with Beech P/N 96-524029-31 (short) and 96- 524029-33 (long control wheel adapters, or with any equivalent part approved by the Chief, Engineeringand Manufacturing Branch, FAA, Central Region. Beechcraft Service Instruction No. 0254-156, or later revision approved by Chief, Engineering and Manufacturing Branch, FAA, Central Region, pertains to this subject. This AD Amendment 39-1350 supersedes AD 71-12-04. Amendment 39-1350 became effective December 1, 1971. This amendment 39-1693 becomes effective August 1, 1973.
2013-22-06: We are superseding Airworthiness Directive (AD) 94-13-06 for certain The Boeing Company Model 747 series airplanes. AD 94-13-06 required repetitive detailed inspections to detect cracking in certain fuselage upper deck tension ties, repair or modification of any cracked tension ties, and repetitive inspections of repaired and modified tension ties and repair or modification if necessary. AD 94-13-06 also provided for optional terminating action for the repetitive detailed inspections of tension ties that had not been repaired or modified. This new AD retains the repetitive inspections, mandates the previously optional terminating modification, and adds, for tension ties that have not been repaired or modified, repetitive inspections that must be done concurrently with the existing repetitive inspections. This AD was prompted by an evaluation by the design approval holder indicating that the upper deck tension ties of the fuselage are subject to widespread fatigue damage. We are issuing this AD to prevent widespread fatigue damage of certain fuselage upper deck tension ties, which could result in reduced structural integrity of the airplane.
2010-14-15: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A fatal accident occurred to a L-13 BLANIK sailplane, in which the main spar of the right wing failed near the root due to positive load. The right wing detached from the aircraft and the pilots lost control of the sailplane. The preliminary investigation has revealed that the fracture may have been due to fatigue. This AD requires actions that are intended to address the unsafe condition described in the MCAI.