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98-05-15: This amendment adopts a new airworthiness directive (AD) that applies to SIAI Marchetti, S.r.1 Models SF600 and SF600A airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
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98-05-10: This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters. This action requires replacing the aluminum elbows that connect the oil cooler lines to the engine accessory case with steel elbows. This amendment is prompted by two reports of cracks that were discovered in aluminum elbows. The actions specified in this AD are intended to prevent failure of either the 45 degree or 90 degree aluminum elbows that connect the oil lines from the oil cooler to the engine accessory case, which would cause loss of engine oil, resulting in an engine failure and a subsequent forced landing.
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85-21-07 R1: 85-21-07 R1 BEECH: Amendment 39-5295 as amended by 39-5637. Applies to Models 1900 (Serial Numbers UA-1 through UA-3) and 1900C (Serial Numbers UB-1 through UB-60) airplanes certificated in any category.
Compliance: Required within 10 hours time-in-service after receipt of this AD, unless already accomplished.
To ensure that required performance can be achieved for each approved combination of takeoff configuration, weight, altitude, and temperature, accomplish the following:
(a) Revise Beech Model 1900/1900C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM), P/N 114-590021-3, in accordance with Model 1900 and 1900C interim Addendum to POH/AFM, P/N 114-590021-3, dated October 21, 1985.
NOTE: The above cited interim Addendum was transmitted to Model 1900/1900C operators of record by Beech letter 52-85-1948, dated October 21, 1985.
(b) Conduct further operations in accordance with the POH/AFM so revised.
(c) The requirementsof paragraph (a) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173.
(d) The requirements of paragraphs (a), (b), and (c) do not apply to airplanes which have installed Beech Kit Part Number (P/N) 114-4013-1 S. Airplanes with this kit installed may operate in accordance with the limitations and procedures shown in Beech Model 1900/1900C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM), P/N 114- 590021-3.
(e) An equivalent means of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Wichita, Kansas 67209; Telephone (316) 946-4400.
All persons affected by this directive may obtain copies of the documents referred to hereinupon request to Mr. Lou Gollin, Beech Aircraft Service Engineering, Department 52, P.O. Box 85, Wichita, Kansas 67201; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.
Amendment 39-5295 became effective May 6, 1986.
This amendment, 39-5637, becomes effective on July 10, 1987.
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92-19-04: 92-19-04 AIRBUS INDUSTRIE: Amendment 39-8362. Docket No. 91-NM-252-AD.
Applicability: Model A300-B4-620, A310-221, A310-222, and A310-322 series airplanes, equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, or JT9D-7R4H1 series engines; and Model A300-B4-622, A300-B4-622R, and A310-324 series airplanes, equipped with Pratt and Whitney PW 4152 or PW 4158 series engines, certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the airplane, accomplish the following:
(a) Accomplish the requirements of paragraphs (a)(1), (a)(2), and (a)(3) of this AD as follows: For airplanes equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, and JT9D-7R4H1 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW7R4 71-90, Revision 2, dated May 14, 1992, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter JT9/71-00/SS:JDS:0-12-3-1. For airplanes equipped with Pratt and Whitney PW 4152 and PW 4158 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW4NAC 71-86, Revision 2, dated February 28, 1992, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter 4000/71.00/SS:TJF:0-12-03-1.
(1) Prior to the accumulation of 500 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracks or a broken link in the forward engine mount thrust link, in accordance with Part 1 of the applicable service bulletin.
(i) If no crack or broken link is found, repeat the visual inspection thereafter at intervals not to exceed 1,000 landings until the requirements of paragraph (a)(2) of this AD are accomplished.
(ii) If any crack or a broken link is found as a result of the visual inspection, prior to further flight, replace the link with a serviceable part that has been inspected in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD.
(2) At the next engine removal or within 4,000 hours time-in-service after the effective date of this AD, whichever occurs first, perform a initial etch inspection to detect cracks or a broken link in the forward engine mount thrust link, in accordance with the applicable service bulletin.
(i) If no crack is found as a result of the initial etch inspection, reinstall the link assembly in accordance with the applicable service bulletin. No further action is required.
(ii) If any crack or broken link is found as a result of the initial etch inspection, prior to further flight, replace the link with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD.
(3) Replacement of the forward engine mount thrust link in accordance with the applicable service bulletin constitutes terminating action for the requirements of this AD.
(b) Accomplish the requirements in paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of this AD as follows: For airplanes equipped with Pratt and Whitney JT9D-7R4D1, JT9D-7R4E1, and JT9D-7R4H1 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW7R4 71-100, Revision 1, dated July 25, 1991, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter JT9/71-00/SS:0-12-3-1. For airplanes equipped with Pratt and Whitney PW 4152 and PW 4158 series engines, accomplish the actions in accordance with Pratt and Whitney Service Bulletin PW4NAC 71-105, Revision 1, dated July 25, 1991, unless previously accomplished in accordance with Pratt and Whitney All Operator Letter 4000/71-00/SS:TJF:0-12-03-1.
(1) Prior to the accumulation of 500 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracks or forging laps in the aft engine mount beam assembly, in accordance with Part 1 of the applicable service bulletin.
(i) If no crack or forging lap is found as a result of the visual inspection, repeat the visual inspection thereafter at intervals not to exceed 1,000 landings until the requirements of paragraph (b)(2) of this AD are accomplished.
(ii) If any crack is found as a result of the visual inspection, prior to further flight, perform a dip etch and a spot fluorescent penetrant inspection to confirm the findings of cracks or forging laps, in accordance with Part 2 of the applicable service bulletin. If any finding of cracks or forging laps is confirmed, prior to further flight, replace the defective beam assembly with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (b) of this AD. As of the effective date of this AD, none of the aft beam assemblies listed in the applicable service bulletin shall be installed on any airplane.
(2) Except as provided by paragraph (b)(3) of this AD, at the next engine removal or within 4,000 hours time-in-service after the effective date of this AD, whichever occurs first, perform a dip etch and a fluorescent penetrant inspection to detect cracks or forging laps in the aft engine mount beam assembly, in accordance with Part 2 of the applicable service bulletin.
(i) If no crack or forging lap is found as a result of the dip etch and fluorescent penetrant inspection, reinstall the beam assembly in accordance with the applicable service bulletin. No further action is required.
(ii) If any crack or forging lap is found as a result of the dip etch and fluorescent penetrant inspection, prior to further flight, replace the beam assembly with a serviceable part, in accordance with the applicable service bulletin. Such replacement constitutes terminating action for the requirements of paragraph (b) ofthis AD.
(3) If the requirements of paragraph (b)(2) of this AD result in a dual engine removal, the dip etch and fluorescent penetrant inspection of one of the two aft engine mounts may be deferred to the next 4,000 hours time-in-service or engine removal, whichever occurs first, provided no crack or forging lap is found while accomplishing the visual inspections required by paragraph (b)(1) of this AD. If those inspections are deferred, repeat the visual inspection of the deferred aft engine mount, as required by paragraph (b)(1) of this AD, at intervals not to exceed 1,000 landings.
(4) Replacement of the aft engine mount beam assembly, in accordance with the applicable service bulletin, constitutes terminating action for the requirements of paragraph (b) of 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.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch.
(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(e) The inspection and replacement shall be done in accordance with the following Pratt and Whitney service bulletins, as applicable, which contain the specified effective pages:
Service Bulletin
Referenced and Date
Page Number
Revision Level
Shown on Page
Date
Shown on Page
PW4NAC 71-105,
Revision 1,
July 25, 1991,
1-19
1
July 25, 1991,
1-2
3, 6, 8,
11-16, 18
2
1
February 28, 1992
July 25, 1991PW4NAC 71-86,
Revision 2,
February 28, 1992
4-5, 7,
9-10, 17
Original
May 10, 1991
1, 16-20
2, 4-5, 7,
10
2
Original
May 14, 1992
May 10, 1991
PW7R4 71-90,
Revision 2,
May 14, 1992
3, 6, 8-9,
11-15
1
July 25, 1991
PW7R4 71-100,
Revision 1,
July 25, 1991
1, 4, 6-18
2-3, 5
1
Original
July 25, 1991
May 10, 1991
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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, 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.
(f) This amendment becomes effective on November 17, 1992.
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2012-12-03: We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) models RB211-Trent 970-84, 970B-84, 972- 84, 972B-84, 977-84, 977B-84, and 980-84 turbofan engines. That AD currently requires inspecting the intermediate-pressure (IP) shaft rigid coupling splines for wear resulting in rearward movement of the IP turbine. This AD requires the same inspections, and new inspections based on possible changes in wear rate. This AD was prompted by RR identifying wear beyond engine manual limits on the abutment faces of the splines. RR also determined that an additional IP shaft rigid coupling configuration requires inspection. We are issuing this AD to detect wear on the abutment faces of the splines, which could result in loss of disc integrity, an uncontained failure of the engine, and damage to the airplane.
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2005-13-39: The FAA is superseding an existing airworthiness directive (AD), which applies to Airbus Model A321 series airplanes. That AD currently requires revising the Limitations section of the airplane flight manual to include an instruction to use Flap 3 for landing when performing an approach in conditions of moderate to severe icing, significant crosswind (i.e., crosswinds greater than 20 knots, gust included), or moderate to severe turbulence. This new AD requires replacing existing elevator and aileron computers (ELACs) with ELACs having either L83 or L91 software, as applicable, which terminates the requirements of the existing AD. This AD also requires a related concurrent action. In addition, this AD revises the applicability by removing airplanes with these ELAC software standards incorporated in production. This AD is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. We are issuing this AD to prevent roll oscillationsduring approach and landing in certain icing, crosswind, and turbulent conditions, which could result in reduced controllability of the airplane.
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75-05-07: 75-05-07 KING RADIO CORPORATION: Amendment 39-2100. Applies to Model KCS-55 Pictorial Navigation System (magnetic stabilized compass) units, specifically the Gyro Model KG-102 ( ), Part Number 060-0011-0, Serial Numbers 1000 to 1999 and all serial numbers preceded by the letter "P" and Indicator Models KI-525 ( ), Part Number 066-3029-00/01, Serial Numbers 1000 to 1999 and all serial numbers preceded by the letter "P". The Model KCS-55 systems may be installed on various types of aircraft.
Compliance: Required as indicated, unless already accomplished.
A) Within the next 25 hours' time in service after the effective date of this AD, check the aircraft compass system installed or the aircraft permanent maintenance record to determine if the KCS-55 pictorial navigation system is installed on the aircraft.
B) If, as a result of determination required in Paragraph A of this AD, a KCS-55 pictorial navigation system is installed, check the indicator KI-525 ( ) to determineif the serial number falls within those noted in the applicability statement and if the unit has been modified and identified as Mod 1. Also, check the KG 102 gyro and determine if the serial number falls within those noted in the applicability statement and that the unit has been modified and identified as Mod 6. If both units are so identified with the modification number, make an appropriate entry in the aircraft records indicating compliance with this AD.
C) If as a result of the determinations required by Paragraphs A and B of this AD unmodified KCS-55 Pictorial Navigation System units are installed, prior to further flight, install a placard on the instrument panel in clear view of the pilot which indicates:
"KCS-55 PICTORIAL NAVIGATION SYSTEM IS NOT TO BE USED FOR PRIMARY HEADING OR IFR FLIGHT IF IT IS SOLE GYROSCOPIC HEADING SOURCE" and operate the aircraft in accordance with this limitation.
D) On or before November 15, 1975, replace any KCS-55 pictorial navigation system units which fall within the Part Number and Serial Number designations set forth in the applicability statement with modified units which are identified in accordance with King Alert Service Bulletins KI 525-1 and KG 102-6 dated January 2, 1975, or subsequent revisions, as Mod 1 and Mod 6 respectively. When this paragraph has been complied with, Paragraph C of this AD is no longer applicable.
E) Any alternative means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
This amendment becomes effective February 28, 1975.
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90-09-03: 90-09-03 MCDONNELL DOUGLAS: Amendment 39-6582. Docket No. 89-NM-136-AD. \n\n\tApplicability: Model DC-10-10 and -15 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of the main landing gear brakes, accomplish the following: \n\n\tA.\tWithin 90 days after the effective date of this amendment, inspect Airplanes Braking Systems (formerly Loral, formerly Goodyear) brakes, part numbers 5000709-1, -3, -5, -7, and -8, for wear. Any brake worn more than 1.00 inch must be replaced, prior to further flight, with one within this limit. \n\n\tB.\tWithin 90 days after the effective date of this amendment, incorporate the 1.00 inch brake wear limit into the FAA-approved maintenance inspection program. \n\n\tC.\tWithin 120 days after the effective date of this amendment, inspect Airplanes Braking Systems (formerly Loral, formerly Goodyear) brakes, part numbers 5000709-1, -3, -5, -7, and -8, for wear. Anybrake worn more than 0.60 inch must be replaced, prior to further flight, with one within this limit. \n\n\tD.\tWithin 120 days after the effective date of this amendment, incorporate the 0.60 inch brake wear limit into the FAA-approved maintenance inspection program. \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, Los Angeles 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \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\tThis amendment (39-6582, AD 90-09-03) becomes effective on May 29, 1990.
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89-23-03: 89-23-03 EMPRESA BRASILEIRA DE AERONAUTICA, S.A. (EMBRAER): Amendment 39-6368. Docket No. 89-NM-86-AD.
Applicability: Model EMB-120 series airplanes, as listed in EMBRAER Service Bulletin 120-034-0072, dated April 14, 1989, certificated in any category.
Compliance: Required within 100 days after the effective date of this AD, unless previously accomplished.
To prevent erratic glide slope information during IFR approaches, accomplish the following:
A. Replace the Chelton glide slope antenna, P/N 17-21F6P3, with a Collins glide slope antenna type 37P5, P/N 522-0700-023, and install a pedestal-type support P/N 120-47294- 001, in accordance with EMBRAER Service Bulletin 120-034-0072, dated April 14, 1989.
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.
NOTE: The request should beforwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113.
C. 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 EMBRAER, 276 S.W. 34th Street, Fort Lauderdale, Florida 33315. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia.
This amendment (39-6368, AD 89-23-03) becomes effective on November 27, 1989.
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2012-13-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report of a ground fire which was fed by oxygen escaping from a damaged third crew person oxygen line and had started in the vicinity of an electrical panel. This AD requires replacing and changing the routing of the flexible oxygen hose of the third crew person oxygen line and modifying the entrance compartment assembly. We are issuing this AD to prevent the possibility of damage to the third crew person oxygen line and of an oxygen-fed fire in the airplane.
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