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88-21-06: 88-21-06 ROLLS-ROYCE plc: Amendment 39-6031. Applies to Rolls-Royce plc (R-R) (Formerly Rolls- Royce Limited) Dart Mks. 506, 510, 511, 514, 525, 526, 527, 528, 529, 531, 532, and 542 series turboprop engines and all variants. Compliance is required as indicated, unless already accomplished. To prevent low cycle fatigue failure of high pressure (HP) impellers and low pressure (LP) impellers, accomplish the following: (a) Remove from service HP impellers installed in Dart Mks. 506, 510, 511, 514, and all variants, in accordance with the following schedule: (1) HP impellers to Mod 844 standard which have accumulated 8,000 or more total flights since new on the effective date of this AD, within the next 400 flights from the effective date of this AD, or within the next 12 calendar months from the effective date of this AD, whichever comes later. (2) HP impellers to Mod 1455 standard which have accumulated 8,600 or more total flights since new on the effective date of this AD, within the next 400 flights from the effective date of this AD, or within the next 12 calendar months from the effective date of this AD, whichever comes later. (3) HP impellers to Mod 844 standard which have accumulated less than 8,000 total flights since new on the effective date of this AD, at or prior to accumulating 8,400 total flights since new, or within 12 calendar months from the effective date of this AD, whichever comes later. (4) HP impellers to Mod 1455 standard which have accumulated less than 8,600 total flights since new on the effective date of this AD, at or prior to accumulating 9,000 total flights since new, or within 12 calendar months from the effective date of this AD, whichever comes later. NOTES: (1) Total flights since new is defined as the total number of flights accumulated by the part since first installation in an engine. This total includes all Mod standards the part has operated under. (2) This action establishes a new Overhaul Manual Chapter 5 life limit for HP impellers, as noted in items (a)(3) and (a)(4) above. (3) Reference R-R Service Bulletin (SB) DA72-496, dated June 1986. (b) Remove from service HP impellers installed in Dart Mks. 525, 526, 527, 528, 529, 531, 532, 542, and all variants, on or before the life limits in the following schedule: Life Limit in Number of Flights Dart Mk. Pre-Mod 797 Mod 797 Open Bore Processed Mod 797 Pre-Mod 1455 Mod 1455 Mod 1475 525 thru 529 4,500 11,000 14,000 NC NC 531 and 532 4,500 11,000 14,000 NC NC 542 NA NA 12,000 16,000 14,500 (Since incorp. of Mod 1455) NA - Model not applicable to specific impeller. NC - Life limits not covered by this AD. Information relating to these impellers is contained in the manufacturer's appropriate overhaul manual. NOTE: The above noted HP impeller life limits were published in AD 73-21-04, Amendment 39-1734 (38 FR 27819), and have notchanged. This section is only intended to reprint for clarity, already existing AD requirements with respect to current R-R SB information. (c) Remove from service LP impellers installed in Dart Mks. 506, 510, 511, 514, 525, 526, 527, 528, 529, 531, 532, 542, and all variants, on or before the life limits in the following schedule: Limit in Number of Flights Dart Mk. Mod 797 Open Bore Processed Mod 797 Pre-Mod 1455 Mod 1455 506 10,500 11,250 11,250 510 10,500 11,250 11,250 511 10,500 11,250 11,250 514 10,500 11,250 11,250 525 thru 529 9,000 9,000 9,000 531 and 532 9,000 9,000 9,000 542 NA 9,000 9,000 NA - Model not applicable to specific impeller. NOTES: (1) LP impellers to Mod 1455 Part 1 standard (manufactured by R-R to this standard) are not affected by this AD. Life limits for this part are quoted in the overhaul manual, Chapter 5, "Time Limits". (2) The above noted LP impeller life limits were published in AD 73-21-04, Amendment 39-1734 (38 FR 27819), and have not changed. This AD, with respect to LP impeller life limits, is only intended to reprint for clarity, already existing AD requirements with respect to current R-R SB information. (3) Rolls-Royce Dart SB 72-463 also pertains to LP impeller life limits. (d) Aircraft may be ferried in accordance with provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. (f) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, may adjust the compliance schedules specified in this AD. This amendment supersedes Amendment 39-1734 (38 FR 27819), AD 73-21-04. This amendment, 39-6031, becomes effective on November 6, 1988.
2017-25-02: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 1000, 2000, 3000, and 4000 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports indicating that certain exit signs have a hydrogen isotope that decays over time, causing the signs to lose their brightness. We are issuing this AD to address the unsafe condition on these products.
89-09-04: 89-09-04 SAAB-SCANIA: Amendment 39-6194. Applicability: Model SF-340A series airplanes, serial numbers -003 through -138, inclusive, certificated in any category. Compliance: Required as indicated below, unless previously accomplished. To prevent reduced structural capability of the fuselage, accomplish the following: A. Within 30 days after the effective date of this AD, perform an inspection of the insulation in the Environmental Control System (ECS) compartment and secure the Gamah Couplings with a locking wire, in accordance with SAAB-Scania Service Bulletin SF340-21-022, dated October 31, 1988. B. If the inspection required by paragraph A., above, reveals leakage of hot air, prior to further flight, inspect for delamination of the stringer to skin bonding, and repair, if necessary, in accordance with SAAB-Scania Service Bulletin SF340-53-025, dated October 31, 1988. C. 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 Manger, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to SAAB-Scania AB, S-581 88, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6194, AD 89-09-04) becomes effective on May 16, 1989.
87-06-04: 87-06-04 AEROSPATIALE: Amendment 39-5569. Applies to Model ATR-42 series airplanes listed in Aerospatiale Service Bulletin ATR 42-25-0006, dated July 21, 1986, fitted with IPECO flight crew seats, certificated in any category. Compliance is required within 30 days after the effective date of this AD, unless already accomplished. To prevent collapse of the pilot or co-pilot seat backs, accomplish the following: A. Modify seats, P/N 3A063-0035, 3A063-0036, 3A063-0079, and 3A063-0080, in accordance with Aerospatiale Service Bulletin ATR 42-25-0006, dated July 21, 1986, or Revision 1, dated September 3, 1986 (Reference IPECO Service Bulletin A001-25-22, dated June 5, 1986). B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective April 2, 1987.
88-07-52: 88-07-52 AEROSPATIALE: Amendment 39-5925. Applies to Model ATR-42-200 and -300 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent erroneous fuel quantity readings in the fuel indication system, accomplish the following: A. Within 7 days after the effective date of this AD, modify the cable in the fuel indicator panel, as follows: 1. Remove fuel quantity indicator 3 quart on the 4 VU panel (Ref: Airplane Maintenance Manual (AMM) 28-42-81-RAI 10000). 2. Disconnect cable 2842-0007 from plug 3 Qta pin R. 3. Insulate the cable from circuitry by means of heat shrinkable sleeve. 4. Attach cable to harness by suitable tie wrap. 5. Reinstall 3 Qta plug and 3 quart indicator (Ref: AMM 28-42-81-RAI 10000). 6. Perform a test of the fuel quantity indicator by pushing the test switch. Ensure that all digits indicate "eight," and that the "low level" lights illuminate. B.Accomplishment of the modification of the cable in the fuel indicator panel and functional test in accordance with Aerospatiale Service Bulletin ATR42-28-0011, dated April 6, 1988, is considered an acceptable means of compliance with this AD. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This AD was effective earlier to all recipients of telegraphic AD T88-07-52, issued March 31, 1988. This Amendment 39-5925 becomes effective June 4, 1988.
61-12-02: 61-12-02 DOUGLAS: Amdt. 294 Part 507 Federal Register June 7, 1961. Applies to All Model DC-8 Aircraft powered with P&WA JT3C-6 and JT4A Series Engines. \n\n\tCompliance required as indicated. \n\n\tAn instance has been reported wherein a takeoff was attempted with elevator gust lock engaged. It was found that the throttle interlock did not provide adequate restriction to limit engine thrust under the prevailing temperature condition. Unless already accomplished, the following modification or FAA approved equivalent, must be accomplished within the next 500 hours' time in service. \n\n\tModify the throttle interlock system to provide further restriction of the throttles when elevator gust lock is engaged by installing the following parts or equivalent: \n\n\tPushrod - Gust Lock Interlock Pedestal, P/N 3771190. \n\n\tAdapter - Gust Lock Crank, P/N 4771191. \n\n\tArm, Gust Lock Interlock Pedestal, P/N 2772271-1 or -501. \n\n\tPer Douglas Drawing No. 5640901 Changes "CI" and "CK" - "Pedestal Assembly - Accessory Controls". \n\n\t(Douglas Service Bulletin No. A27-99, reissue No. 1, revision No. 2 dated July 19, 1961, also covers this same subject.) \n\n\tThis directive effective June 7, 1961. \n\n\tRevised August 26, 1961.
87-08-04: 87-08-04 BOEING: Amendment 39-5593. Applies to Model 757 series airplanes equipped with Rolls Royce RB211-535E4 engines, as listed in Boeing Service Bulletin 757-78-0010, dated December 23, 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo maintain the fire integrity of the thrust reverser C-ducts, accomplish the following within the next 250 flight hours after the effective date of this AD: \n\n\tA.\tInspect and repair, if necessary, the thermal blanket in the upper 45 degree section of the C-ducts, as described in Boeing Service Bulletin 757-78-0010, dated December 23, 1986, or later FAA-approved revision. Any damage to the thermal blanket (such as holes, splits, and tears) must be repaired prior to further flight. \n\n\tB.\tInspect and repair, if necessary, the thermal blanket in the lower section of the C- ducts and engine components, as described in the Boeing Service Bulletin 757-78-0010, dated December 23, 1986, or later FAA-approved revisions. Any damage discovered must be repaired within the next 250 flight hours. \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\tD.\tSpecial 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 repair required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124-2207. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 16, 1987.
2017-24-07: We are superseding Airworthiness Directive (AD) 2014-08-01, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-08-01 required an inspection for part numbers of the interconnecting struts and, for affected interconnecting struts, identification of the part and serial numbers of the associated target and proximity sensors and replacement or re-identification of the flap interconnecting strut if necessary. This AD continues to require an inspection to verify the interconnecting strut part number. This AD also provides a new compliance time and an additional inspection for previously inspected airplanes. This AD was prompted by an investigation that showed that when a certain combination of target/ proximity sensor serial numbers is installed on a flap interconnecting strut, a ``target FAR'' signal cannot be detected when reaching the mechanical end stop of the interconnecting strut. We are issuing this AD to address the unsafe condition on these products.
82-18-02: 82-18-02 BRITISH AEROSPACE, AIRCRAFT GROUP (formerly British Aircraft Corporation): Amendment 39-4443. Applies to Model BAC 1-11 series 400 airplanes certificated in all categories. Compliance required as indicated unless already accomplished. To prevent overloads and possible failure of the spoiler operating rods caused by corroded turnbarrels, accomplish the following: 1. Within the next 1200 landings or 6 months after the effective date of this AD, whichever occurs first, and thereafter at intervals not exceeding 10,000 landings or 5 years from the last inspection, inspect the internal threads of the spoiler operating rod turnbarrels for corrosion and excessive thread truncation and replace the turnbarrel, if necessary, in accordance with paragraph 2, Accomplishment Instructions, of British Aerospace, Aircraft Group, BAC 1-11 Alert Service Bulletin 27-A-PM5732, Issue No. 2, dated November 13, 1980. 2. Alternate means of compliance which provide an equivalent level ofsafety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 3. 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. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective September 27, 1982.
61-11-05: 61-11-05 DOUGLAS: Amdt. 291 Part 507 Federal Register May 30, 1961. Applies to All Models A-26 (B-26) Series Aircraft. Compliance required as indicated. As a result of several reported cases of severe corrosion of the wing structure in the area beneath the wing fuel tanks, the following must be accomplished at the next periodic inspection and every periodic inspection thereafter, until (b) is accomplished: (a) Remove the center wing fuel tanks and inspect the internal wing structure for corrosion. If corrosion is found, FAA approved repairs and/or replacement of affected parts must be made prior to further flight. Also, inspect the sponge rubber mats under the fuel cells, and if found deteriorated they must be replaced prior to next flight. (b) When the sponge rubber mats have been replaced with closed cell neoprene sponge mats, or equivalent, and any corrosion damage present is repaired, the special inspection of (a) is no longer required. This directive effective June 29, 1961.